A300B2 ATA 23

HIGHLIGHTS __________

REVISION NO. 52 Mar 01/07

Pages which have been revised are outlined below, together with the Highlights of theRevision

--------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES--------------------------------------------------------------------------------------

CHAPTER 23__________

L.E.P. 1- 4 Revised to Reflect this revision indicating new,revised, and/or deleted pages23-31-00 01 Effectivity updated 1- 6, 18, 26, 33, 36- 38

23-61-21 01 Revised para. 6D.(2) Install the retainers6 006-101, 104-104, 106-999, 401, 407- according to 6Stork Memo6. 408 Minor additions and amplification 006-101, 104-104, 106-999,

23-61-21 02 Revised para. 6D.(2) Installation of static 001-005, 102-103, 105-105, 401, 405- discharger retainers on low speed ailerons, 407 Flap track Fairings and vertical stabilizer tip.6 according to 6Stork Memo6. Minor additions and amplification 001-005, 102-103, 105-105,

23-HIGHLIGHTS REVISION NO. 52 of 1 JAS Mar 01/07

CHAPTER 23 __________

COMMUNICATIONS

LIST OF EFFECTIVE PAGES _______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary

CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

RECORD 23-11-00 02 23 Oct01/92 23-11-33 01 403 Oct01/92OF TEMP. 23-11-00 02 24 Oct01/92 23-11-33 01 404 Oct01/92REVISION 23-11-00 02 25 Oct01/92 23-11-33 02 401 Oct01/92 23-11-00 02 26 Oct01/88 23-11-33 02 402 Oct01/92L.E.P. R 1- 4 Mar01/07 23-11-00 02 27 Oct01/92 23-11-36 401 Oct01/91T. of C. 1 Oct01/92 23-11-00 02 28 Oct01/92 23-11-36 402 Jul01/89T. of C. 2 Mar01/05 23-11-00 02 29 Mar01/05 23-11-36 403 Oct01/88T. of C. 3 Jul01/98 23-11-00 02 30 Oct01/88 23-11-36 404 Oct01/91T. of C. 4 Jul01/98 23-11-00 02 31 Oct01/92 23-11-36 405 Oct01/91T. of C. 5 Mar01/05 23-11-00 02 32 Oct01/92 23-11-36 406 Jul01/89T. of C. 6 Mar01/05 23-11-00 02 33 Oct01/92T. of C. 7 Mar01/05 23-11-00 02 34 Mar01/05 23-20-00 01 1 Mar01/05 23-11-00 02 35 Oct01/92 23-20-00 01 2 Oct01/9223-00-00 1 Oct01/91 23-11-00 02 36 Oct01/92 23-20-00 01 3 Mar01/0523-00-00 2 Oct01/91 23-11-00 101 Jul30/82 23-20-00 02 1 Oct01/8823-00-00 3 Oct01/88 23-11-00 01 501 Oct01/92 23-20-00 02 2 Oct01/8823-00-00 4 Oct01/88 23-11-00 01 502 Mar01/0523-00-00 301 Jul30/82 23-11-00 01 503 Oct01/92 23-21-00 01 1 Mar01/0523-00-00 601 Jan01/88 23-11-00 01 504 Oct01/92 23-21-00 01 2 Mar01/05 23-11-00 01 505 Oct01/92 23-21-00 01 3 Mar01/0523-11-00 02 1 Oct01/92 23-11-00 01 506 Oct01/92 23-21-00 01 4 Mar01/0523-11-00 02 2 Oct01/92 23-11-00 01 507 Oct01/92 23-21-00 01 5 Mar01/0523-11-00 02 3 Oct01/92 23-11-00 01 508 Mar01/05 23-21-00 01 6 Mar01/0523-11-00 02 4 Oct01/92 23-11-00 01 509 Oct01/92 23-21-00 01 7 Oct01/9223-11-00 02 5 Mar01/05 23-11-00 01 510 Oct01/92 23-21-00 01 8 Oct01/9223-11-00 02 6 Mar01/05 23-11-00 01 511 Oct01/92 23-21-00 01 9 Oct01/9223-11-00 02 7 Oct01/92 23-11-00 01 512 Oct01/92 23-21-00 01 10 Oct01/9223-11-00 02 8 Mar01/05 23-11-00 01 513 Oct01/92 23-21-00 01 11 Mar01/0523-11-00 02 9 Oct01/92 23-11-00 01 514 Oct01/92 23-21-00 01 12 Oct01/9223-11-00 02 10 Oct01/88 23-11-11 401 Oct01/91 23-21-00 01 13 Oct01/9223-11-00 02 11 Oct01/92 23-11-11 402 Mar01/05 23-21-00 01 14 Oct01/9223-11-00 02 12 Oct01/92 23-11-11 403 Jul01/88 23-21-00 01 15 Oct01/9223-11-00 02 13 Oct01/92 23-11-11 404 Jul01/88 23-21-00 01 16 Oct01/9223-11-00 02 14 Oct01/92 23-11-11 405 Mar01/05 23-21-00 01 17 Mar01/0523-11-00 02 15 Oct01/92 23-11-11 406 Mar01/05 23-21-00 01 18 Oct01/9223-11-00 02 16 Oct01/88 23-11-11 601 Oct01/91 23-21-00 01 19 Mar01/0523-11-00 02 17 Oct01/92 23-11-11 602 Oct01/91 23-21-00 01 20 Mar01/0523-11-00 02 18 Oct01/92 23-11-13 401 Oct01/92 23-21-00 01 21 Mar01/0523-11-00 02 19 Oct01/92 23-11-13 402 Oct01/92 23-21-00 01 22 Oct01/9223-11-00 02 20 Oct01/92 23-11-13 403 Oct01/92 23-21-00 01 23 Oct01/9223-11-00 02 21 Oct01/92 23-11-33 01 401 Oct01/92 23-21-00 01 24 Mar01/0523-11-00 02 22 Oct01/92 23-11-33 01 402 Oct01/92 23-21-00 101 Jan01/88

23-L.E.P. Page 1 JAS Mar 01/07


23-21-00 01 501 Mar01/05 23-31-00 01 R 6 Mar01/07 23-31-00 02 17 Jul01/8823-21-00 01 502 Mar01/05 23-31-00 01 7 Oct01/92 23-31-00 02 18 Jul01/8823-21-00 01 503 Mar01/05 23-31-00 01 8 Oct01/92 23-31-00 02 19 Jul01/8823-21-00 01 504 Mar01/05 23-31-00 01 9 Oct01/92 23-31-00 02 20 Jul01/8823-21-00 01 505 Mar01/05 23-31-00 01 10 Oct01/92 23-31-00 02 21 Jul01/8823-21-00 01 506 Mar01/05 23-31-00 01 11 Oct01/92 23-31-00 02 22 Jul01/8823-21-00 01 507 Mar01/05 23-31-00 01 12 Oct01/92 23-31-00 02 23 Jul01/8823-21-00 01 508 Mar01/05 23-31-00 01 13 Oct01/92 23-31-00 02 24 Jul01/8823-21-00 01 509 Mar01/05 23-31-00 01 14 Oct01/92 23-31-00 02 25 Jul01/8823-21-11 401 Jul01/98 23-31-00 01 15 Oct01/92 23-31-00 02 26 Jul01/8823-21-11 402 Oct01/88 23-31-00 01 16 Oct01/92 23-31-00 03 1 Oct01/8923-21-11 403 Mar01/05 23-31-00 01 17 Oct01/92 23-31-00 03 2 Oct01/8923-21-11 404 Jan30/81 23-31-00 01 R 18 Mar01/07 23-31-00 03 3 Oct01/8923-21-11 405 Oct01/88 23-31-00 01 19 Oct01/92 23-31-00 03 4 Oct01/8923-21-13 01 401 Mar01/05 23-31-00 01 20 Oct01/92 23-31-00 03 5 Oct01/8923-21-13 01 402 Mar01/05 23-31-00 01 21 Mar01/05 23-31-00 03 6 Oct01/8923-21-13 01 403 Mar01/05 23-31-00 01 22 Mar01/05 23-31-00 03 7 Oct01/8923-21-33 01 401 Mar01/05 23-31-00 01 23 Mar01/05 23-31-00 03 8 Oct01/8923-21-33 01 402 Mar01/05 23-31-00 01 24 Oct01/92 23-31-00 03 9 Oct01/8923-21-33 01 403 Mar01/05 23-31-00 01 25 Oct01/92 23-31-00 03 10 Oct01/89 23-31-00 01 R 26 Mar01/07 23-31-00 03 11 Oct01/8923-22-00 03 1 Oct01/92 23-31-00 01 27 Oct01/92 23-31-00 03 12 Oct01/8923-22-00 03 2 Oct01/92 23-31-00 01 28 Oct01/92 23-31-00 03 13 Oct01/8923-22-00 03 3 Oct01/92 23-31-00 01 29 Oct01/92 23-31-00 03 14 Oct01/8923-22-00 03 4 Oct01/92 23-31-00 01 30 Oct01/92 23-31-00 03 15 Oct01/8923-22-00 03 5 Oct01/92 23-31-00 01 31 Oct01/92 23-31-00 03 16 Oct01/8923-22-00 03 6 Oct01/92 23-31-00 01 32 Oct01/92 23-31-00 03 17 Oct01/8923-22-00 03 7 Oct01/92 23-31-00 01 R 33 Mar01/07 23-31-00 03 18 Oct01/8923-22-00 03 8 Oct01/92 23-31-00 01 34 Oct01/92 23-31-00 03 19 Oct01/8923-22-00 03 9 Oct01/92 23-31-00 01 35 Mar01/05 23-31-00 03 20 Oct01/8923-22-00 03 10 Oct01/92 23-31-00 01 R 36 Mar01/07 23-31-00 03 21 Oct01/8923-22-00 03 11 Oct01/92 23-31-00 01 R 37 Mar01/07 23-31-00 03 22 Oct01/8923-22-00 101 Jan01/88 23-31-00 01 R 38 Mar01/07 23-31-00 03 23 Oct01/8923-22-00 02 501 Oct01/92 23-31-00 01 39 Oct01/92 23-31-00 03 24 Oct01/8923-22-00 02 502 Oct01/92 23-31-00 01 40 Oct01/92 23-31-00 03 25 Oct01/8923-22-00 02 503 Oct01/92 23-31-00 02 1 Jul01/88 23-31-00 03 26 Oct01/8923-22-00 02 504 Mar01/05 23-31-00 02 2 Jul01/88 23-31-00 03 27 Oct01/8923-22-00 02 505 Mar01/05 23-31-00 02 3 Jul01/88 23-31-00 03 28 Oct01/8923-22-00 02 506 Oct01/92 23-31-00 02 4 Jul01/88 23-31-00 03 29 Oct01/8923-22-12 401 Jul01/88 23-31-00 02 5 Jul01/88 23-31-00 03 30 Oct01/8923-22-12 402 Jul01/88 23-31-00 02 6 Jul01/88 23-31-00 101 Jul30/8223-22-12 403 Jul01/88 23-31-00 02 7 Jul01/88 23-31-00 501 Oct01/9123-22-34 401 Oct01/88 23-31-00 02 8 Jul01/88 23-31-00 502 Oct01/9123-22-34 402 Oct01/88 23-31-00 02 9 Jul01/88 23-31-00 503 Oct01/9123-22-34 403 Oct01/88 23-31-00 02 10 Jul01/88 23-31-00 504 Oct01/91 23-31-00 02 11 Jul01/88 23-31-00 505 Oct01/9223-31-00 01 R 1 Mar01/07 23-31-00 02 12 Jul01/88 23-31-00 506 Oct01/9223-31-00 01 R 2 Mar01/07 23-31-00 02 13 Jul01/88 23-31-00 507 Oct01/9223-31-00 01 R 3 Mar01/07 23-31-00 02 14 Jul01/88 23-31-00 508 Oct01/9223-31-00 01 R 4 Mar01/07 23-31-00 02 15 Jul01/88 23-31-00 509 Oct01/9223-31-00 01 R 5 Mar01/07 23-31-00 02 16 Jul01/88 23-31-00 510 Oct01/92



23-31-00 511 Oct01/92 23-41-00 01 2 Oct01/92 23-42-12 403 Jul01/8623-31-00 512 Oct01/92 23-41-00 01 3 Oct01/92 23-42-21 401 Jul30/8323-31-00 513 Oct01/92 23-41-00 01 4 Oct01/92 23-42-21 402 Jul30/8223-31-00 514 Oct01/92 23-41-00 01 5 Oct01/92 23-42-21 403 Jul30/8223-31-00 515 Oct01/92 23-41-00 01 6 Oct01/92 23-42-34 401 Jan01/8823-31-00 516 Oct01/92 23-41-00 01 7 Oct01/92 23-42-34 402 Jul30/8223-31-00 517 Oct01/92 23-41-00 01 8 Oct01/9223-31-00 518 Oct01/92 23-41-00 01 9 Oct01/92 23-51-00 02 1 Oct01/9223-31-00 519 Oct01/92 23-41-00 01 10 Oct01/91 23-51-00 02 2 Oct01/9223-31-00 520 Oct01/92 23-41-00 01 11 Oct01/92 23-51-00 02 3 Oct01/9223-31-12 401 Oct01/87 23-41-00 01 12 Oct01/92 23-51-00 02 4 Oct01/9223-31-12 402 Oct01/87 23-41-00 02 1 Oct01/92 23-51-00 02 5 Oct01/9223-31-18 401 Jan01/88 23-41-00 02 2 Oct01/92 23-51-00 02 6 Oct01/9223-31-18 402 Apr30/80 23-41-00 02 3 Oct01/92 23-51-00 02 7 Oct01/9223-31-35 401 Jan01/88 23-41-00 02 4 Oct01/92 23-51-00 02 8 Oct01/9223-31-35 402 Apr30/80 23-41-00 02 5 Oct01/92 23-51-00 02 9 Oct01/92 23-41-00 02 6 Oct01/92 23-51-00 02 10 Oct01/9223-33-00 1 Mar01/05 23-41-00 02 7 Oct01/92 23-51-00 02 11 Oct01/9223-33-00 2 Mar01/05 23-41-00 02 8 Oct01/92 23-51-00 02 12 Oct01/9223-33-00 3 Jul01/98 23-41-00 02 9 Oct01/92 23-51-00 02 13 Oct01/9223-33-00 4 Jul01/98 23-41-00 02 10 Jan01/86 23-51-00 02 14 Oct01/9223-33-00 5 Jul01/98 23-41-00 02 11 Oct01/92 23-51-00 02 15 Oct01/9223-33-00 6 Jul01/98 23-41-00 02 12 Oct01/92 23-51-00 02 16 Oct01/9223-33-00 7 Jul01/98 23-41-00 02 13 Oct01/92 23-51-00 02 17 Oct01/9223-33-00 8 Jul01/98 23-41-00 101 Jan01/88 23-51-00 02 18 Oct01/9223-33-00 9 Mar01/05 23-41-00 01 501 Jul01/89 23-51-00 02 19 Oct01/9223-33-00 10 Mar01/05 23-41-00 01 502 Jul01/89 23-51-00 02 20 Oct01/9223-33-00 11 Jul01/98 23-41-00 01 503 Jul01/89 23-51-00 02 21 Oct01/9223-33-00 12 Jul01/98 23-41-00 01 504 Jul01/89 23-51-00 02 22 Oct01/9223-33-00 13 Jul01/98 23-41-00 02 501 Jul01/88 23-51-00 02 23 Oct01/9223-33-00 14 Jul01/98 23-41-00 02 502 Jul01/88 23-51-00 02 24 Oct01/9223-33-00 501 Oct01/92 23-41-00 02 503 Jul01/88 23-51-00 101 Jul30/8223-33-00 502 Oct01/91 23-41-00 02 504 Jul01/88 23-51-00 01 501 Oct01/8823-33-00 503 Oct01/88 23-41-21 401 Jul30/82 23-51-00 01 502 Oct01/8823-33-00 504 Oct01/92 23-41-21 402 Jul30/82 23-51-00 01 503 Oct01/8823-33-00 505 Oct01/92 23-51-00 01 504 Oct01/8823-33-00 506 Oct01/92 23-42-00 1 Oct01/92 23-51-00 01 505 Oct01/8823-33-00 507 Oct01/92 23-42-00 2 Oct01/92 23-51-00 01 506 Oct01/8823-33-12 401 Mar01/05 23-42-00 3 Oct01/92 23-51-00 01 507 Oct01/8823-33-12 402 Jul01/89 23-42-00 4 Oct01/90 23-51-00 01 508 Mar01/0523-33-14 401 Mar01/05 23-42-00 5 Oct01/90 23-51-00 901 Mar01/0623-33-14 402 Jul01/88 23-42-00 6 Oct01/90 23-51-00 902 Mar01/0623-33-15 401 Oct01/95 23-42-00 7 Oct01/90 23-51-00 903 Mar01/0623-33-15 402 Oct01/95 23-42-00 8 Oct01/90 23-51-11 401 Mar01/05 23-42-00 9 Jul01/88 23-51-11 402 Jul30/8223-40-00 1 Oct01/92 23-42-00 10 Jul01/88 23-51-17 401 Oct01/9423-40-00 2 Oct01/92 23-42-00 101 Jul30/82 23-51-19 401 Jan01/8823-40-00 3 Oct01/91 23-42-00 501 Jan01/89 23-51-19 402 Jul30/8223-40-00 4 Oct01/92 23-42-00 502 Mar01/05 23-51-19 403 Jul30/82 23-42-12 401 Jul30/84 23-51-31 401 Jul30/8223-41-00 01 1 Oct01/92 23-42-12 402 Jul30/80 23-51-31 402 Jul30/82



23-60-00 1 Oct01/92 23-71-00 04 5 Oct01/9323-60-00 2 Oct01/92 23-71-00 04 6 Oct01/9323-60-00 3 Oct01/92 23-71-00 04 7 Oct01/9323-60-00 4 Oct01/92 23-71-00 04 8 Oct01/9323-60-00 5 Mar01/05 23-71-00 04 9 Oct01/9323-60-00 601 Mar01/02 23-71-00 04 10 Oct01/9223-60-00 602 Mar01/02 23-71-00 04 11 Oct01/9323-60-00 603 Mar01/02 23-71-00 04 12 Oct01/9323-60-00 604 Mar01/02 23-71-00 04 13 Oct01/93 23-71-00 04 14 Oct01/9323-61-11 401 Mar01/05 23-71-00 04 15 Oct01/9323-61-11 402 Dec30/84 23-71-00 101 Jan01/8823-61-11 403 Dec30/84 23-71-00 01 501 Oct01/9223-61-11 404 Dec30/84 23-71-00 01 502 Oct01/9223-61-11 405 Dec30/84 23-71-00 01 503 Mar01/0323-61-21 01 R 401 Mar01/07 23-71-00 01 504 Oct01/9223-61-21 01 402 Mar01/06 23-71-00 01 505 Oct01/9723-61-21 01 403 Oct01/92 23-71-00 01 506 Oct01/9723-61-21 01 404 Oct01/92 23-71-00 01 507 Oct01/9723-61-21 01 405 Oct01/92 23-71-00 02 501 Jul01/8923-61-21 01 406 Oct01/92 23-71-00 02 502 Jul01/8923-61-21 01 R 407 Mar01/07 23-71-00 02 503 Jul01/8923-61-21 01 R 408 Mar01/07 23-71-00 03 501 Oct01/9223-61-21 02 R 401 Mar01/07 23-71-00 03 502 Oct01/9223-61-21 02 402 Mar01/06 23-71-00 03 503 Mar01/0523-61-21 02 403 Oct01/96 23-71-00 03 504 Oct01/9223-61-21 02 404 Oct01/96 23-71-00 03 505 Oct01/9223-61-21 02 R 405 Mar01/07 23-71-00 03 506 Oct01/9223-61-21 02 R 406 Mar01/07 23-71-00 03 507 Mar01/0523-61-21 02 R 407 Mar01/07 23-71-12 401 Jan01/88 23-71-12 402 Jul30/8223-71-00 01 1 Oct01/92 23-71-35 401 Jan01/8823-71-00 01 2 Oct01/92 23-71-35 402 Oct01/9223-71-00 01 3 Oct01/92 23-71-35 403 Oct01/9223-71-00 01 4 Oct01/92 23-71-35 404 Oct01/9223-71-00 01 5 Oct01/92 23-71-35 405 Mar01/0523-71-00 01 6 Oct01/92 23-71-36 401 Oct01/9223-71-00 01 7 Oct01/92 23-71-36 402 Oct01/9223-71-00 01 8 Oct01/92 23-71-36 403 Oct01/9223-71-00 01 9 Oct01/92 23-71-36 404 Oct01/9723-71-00 01 10 Oct01/9223-71-00 01 11 Oct01/9223-71-00 01 12 Oct01/9223-71-00 01 13 Oct01/9223-71-00 01 14 Oct01/9223-71-00 01 15 Oct01/9223-71-00 01 16 Oct01/9223-71-00 04 1 Oct01/9323-71-00 04 2 Oct01/9323-71-00 04 3 Oct01/9323-71-00 04 4 Oct01/93


CHAPTER 23 __________

COMMUNICATIONS

TABLE OF CONTENTS _________________

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ GENERAL 23-00-00 _______ Description and Operation 1 ALL General 1 ALL Description 1 ALL Servicing 301 ALL Inspection/Check 601 ALL HF SYSTEM 23-11-00 02 Description and Operation 1 101-108, General 1 101-108, Component Location 1 101-108, System Description 1 101-108, HF Control Unit 5 101-108, HF Transceiver 6 101-108, HF Antenna Coupler 29 101-108, Description 29 101-108, Operation of Antenna Couplers 34 101-108, Antenna Coupler Monitoring 34 101-108, Antenna Coupler 34 101-108, Interface 36 101-108, HF SYSTEM 23-11-00 Fault Isolation Manual 101 ALL HF SYSTEM 23-11-00 01 Adjustment/Test 501 101-999, Operational Test 501 101-999, Functional Test 507 101-999, System Test 507 101-999, HF ANTENNA 23-11-11 Removal/Installation 401 ALL Inspection/Check 601 ALL Visual Check 601 ALL HF CONTROL UNIT 23-11-13 Removal/Installation 401 101-999, HF TRANSCEIVER 23-11-33 01 Removal/Installation 401 101-106,108-999, HF TRANSCEIVER 23-11-33 02 Removal/Installation 401 107-107, ANTENNA TUNER 23-11-36 Removal/Installation 401 ALL VERY HIGH AND ULTRA HIGH FREQUENCY 23-20-00 01 __________________________________ (VHF/UHF) _________ Description and Operation 1 101-101,103-999, VHF System (Ref. 23-21-00) 1 101-101,103-999, SELCAL System (Ref. 23-22-00) 1 101-101,103-999, VERY HIGH AND ULTRA HIGH FREQUENCY 23-20-00 02 __________________________________

23-CONTENTSR Page 1 JAS Oct 01/92

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ (VHF/UHF) _________ Description and Operation 1 001-100,

VHF SYSTEM 23-21-00 01 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL Description 3 ALL Component Description 6 ALL VHF Transceiver 6 ALL VHF-COM Control Unit 9 105-106,109-999, VHF COM Control Unit 11 102-102, VHF-COM Control Unit 13 001-101, VHF-COM Control Unit 15 107-107, VHF-COM Control Unit 17 103-104, VHF Antenna 19 ALL Operation 21 ALL Frequency Selection 21 001-102,105-999, Job Set-Up 21 ALL Reception 21 ALL Transmission 21 ALL Squelch Adjustment on the VHF 24 001-102,107-108, COM Control Unit VHF SYSTEM 23-21-00 Fault Isolation Manual 101 ALL VHF SYSTEM 23-21-00 01 Adjustment/Test 501 ALL Operational Test 501 ALL Functional Test 505 ALL System Test 505 ALL ANTENNAS - VHF COM 23-21-11 Removal/Installation 401 ALL VHF COM 1 (2RC1) AND VHF COM 2 (2RC2) 23-21-13 01 CONTROL UNITS Removal/Installation 401 ALL VHF 1 (1RC1) AND VHF 2 (1RC2) 23-21-33 01 TRANSCEIVERS Removal/Installation 401 ALL

SELECTIVE CALLING SYSTEM 23-22-00 03 Description and Operation 1 101-108, General 1 101-108, Component Location 1 101-108, System Description 3 101-108, Component Description 5 101-108, SELCAL Decoder 5 101-108, SELCAL Control Unit 5 101-108, Operation 9 101-108, Principle 9 101-108, Selective Calling 9 101-108, Resetting 9 101-108, Tests 11 101-108,

23-CONTENTSR Page 2 JAS Mar 01/05

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Power Supply 11 101-108, SELECTIVE CALLING SYSTEM 23-22-00 Fault Isolation Manual 101 ALL SELCAL SYSTEM 23-22-00 02 Adjustment/Test 501 101-108, Operational 501 101-108, Reason for the Job 501 101-108, Equipment and Materials 501 101-108, Procedure 501 101-108, Functional Test 503 101-108, Reason for the Job 503 101-108, Equipment and Materials 503 101-108, Procedure 503 101-108, SELCAL CONTROL UNIT (2RW) 23-22-12 Removal/Installation 401 101-101,103-999, Equipment and Materials 401 101-101,103-999, Procedure 401 101-101,103-999, Job Set-Up 401 101-101,103-999, Removal 401 101-101,103-999, Installation 401 101-101,103-999, Test 403 101-101,103-999, Close-Up 403 101-101,103-999, SELCAL DECODER (1RW) 23-22-34 Removal/Installation 401 101-999, Equipment and Materials 401 101-999, Procedure 401 101-999, Job Set-Up 401 101-999, Removal 402 101-999, Installation 402 101-999, Test 402 101-999, Close-Up 402 101-999, PASSENGER ADDRESS 23-31-00 01 Description and Operation 1 001-101,105-999, General 1 001-101,105-999, Component Location 1 001-101,105-999, System Description 18 001-101,105-999, Component Description 20 001-101,105-999, Operation 24 001-101,105-999, Interface 39 001-101,105-999, PASSENGER ADDRESS 23-31-00 02 Description and Operation 1 103-104, General 1 103-104, Component Location 1 103-104, System Description 4 103-104, Component Description 11 103-104, Operation 14 103-104, Interface 23 103-104, PASSENGER ADDRESS 23-31-00 03 Description and Operation 1 102-102, General 1 102-102, Component Location 1 102-102, System Description 12 102-102,

23-CONTENTSR Page 3 JAS Jul 01/98

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Component Description 14 102-102, Operation 19 102-102, Interface 29 102-102, PASSENGER ADDRESS 23-31-00 Fault Isolation Manual 101 ALL Adjustment/Test 501 ALL Operational Test 501 ALL Functional Test 510 ALL System Test 510 ALL Maintenance Practices 518 108-108, TAPE REPRODUCER CONTROL UNIT 23-31-12 Removal/Installation 401 ALL PASSENGER ADDRESS AMPLIFIER 23-31-18 Removal/Installation 401 ALL TAPE REPRODUCER 23-31-35 Removal/Installation 401 ALL

PASSENGER ENTERTAINMENT (MUSIC) 23-33-00 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL Description 9 ALL Operation 9 ALL Adjustment/Test 501 ALL AUDIO REPRODUCER 23-33-12 Removal/Installation 401 101-106, AMPLIFIER 23-33-14 Removal/Installation 401 101-104, MAIN MULTIPLEXER 23-33-15 Removal/Installation 401 ALL INTERPHONE 23-40-00 __________ Description and Operation 1 ALL General 1 ALL

SERVICE INTERPHONE 23-41-00 01 Description and Operation 1 107-107,109-999, General 1 107-107,109-999, Component Location 1 107-107,109-999, System Description 6 107-107,109-999, Component Description 8 107-107,109-999, Operation 9 107-107,109-999, Interface 9 107-107,109-999, SERVICE INTERPHONE 23-41-00 02 Description and Operation 1 001-106,108-108, General 1 001-106,108-108, Component Location 1 001-106,108-108, System Description 6 001-106,108-108, Component Description 8 001-106,108-108, Operation 8 001-106,108-108, Interface 13 001-106,108-108,

23-CONTENTSR Page 4 JAS Jul 01/98

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ SERVICE INTERPHONE 23-41-00 Fault Isolation Manual 101 ALL SERVICE INTERPHONE 23-41-00 01 Adjustment/Test 501 001-101,107-999, Operational Test 501 001-101,107-999, SERVICE INTERPHONE 23-41-00 02 Adjustment/Test 501 103-104, Operational Test 501 103-104, SERVICE INTERPHONE AMPLIFIER 23-41-21 Removal/Installation 401 ALL

GROUND CREW CALL SYSTEM 23-42-00 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL System Description 4 ALL Component Description 6 ALL Fault Isolation Manual 101 ALL Adjustment/Test 501 ALL INTERPHONE BOX 23-42-12 Removal/Installation 401 ALL HORN 23-42-21 Removal/Installation 401 ALL CALL LOGIC UNIT 23-42-34 Removal/Installation 401 ALL AUDIO INTEGRATING (FLIGHT INTERPHONE) 23-51-00 02 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL System Description 6 ALL Component Description 9 ALL Operation 14 101-108, Interface 23 101-108, AUDIO INTEGRATING (FLIGHT INTERPHONE) 23-51-00 Fault Isolation Manual 101 ALL AUDIO INTEGRATING (FLIGHT INTERPHONE) 23-51-00 01 Adjustment/Test 501 001-101,103-999, Operational Test 501 001-101,103-999,R SWITCH - INTPH/RAD 23-51-00 Deactivation/Reactivation 901 ALLR Deactivation 901 ALLR Ref. MMEL Sect. 1-23, Item 9 901 ALLR Reactivation 902 ALL AUDIO SELECTOR PANEL 23-51-11 Removal/Installation 401 ALL INTPH/RAD SWITCH (11RL, 12RL) 23-51-17 Removal/Installation 401 ALL INTERPHONE JUNCTION BOX/AMPLIFIER 23-51-19 Removal/Installation 401 ALL JACK BOX 23-51-31 Removal/Installation 401 ALL

23-CONTENTS Page 5 JAS Mar 01/05

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ STATIC DISCHARGING 23-60-00 __________________ Description and Operation 1 ALL Component Location 1 ALL Description 5 ALL Operation 5 ALL Inspection/Check 601 ALL

STATIC DISCHARGER 23-61-11 Removal/Installation 401 ALL STATIC DISCHARGER RETAINER 23-61-21 01 Removal/Installation 401 006-101,104-104,106-999, STATIC DISCHARGER RETAINER 23-61-21 02 Removal/Installation 401 001-005,102-103,105-105, COCKPIT VOICE RECORDER 23-71-00 01 Description and Operation 1 108-999, General 1 108-999, Component Location 1 108-999, System Description 4 108-999, Component Description 6 108-999, Cockpit Voice Recorder Control 6 108-999, Unit Cockpit Voice Recorder 7 108-999, Operation 10 108-999, Interface 15 108-999, COCKPIT VOICE RECORDER 23-71-00 04 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL System Description 4 ALL Component Description 6 ALL Cockpit Voice Recorder Control 6 ALL Unit Cockpit Voice Recorder 7 ALL Operation 9 ALL Interface 14 ALL COCKPIT VOICE RECORDER 23-71-00 Fault Isolation Manual 101 ALL COCKPIT VOICE RECORDER 23-71-00 01 Adjustment/Test 501 001-104,108-999, Operational Test 501 001-104,108-999, Functional Test 504 108-108, Functional Test 505 001-104, COCKPIT VOICE RECORDER 23-71-00 02 Adjustment/Test 501 105-105, Operational Test 501 105-105, COCKPIT VOICE RECORDER 23-71-00 03 Adjustment/Test 501 106-107, Operational Test 501 106-107, System Test 502 106-107, COCKPIT VOICE RECORDER CONTROL UNIT 23-71-12 Removal/Installation 401 ALL COCKPIT VOICE RECORDER 23-71-35

23-CONTENTSR Page 6 JAS Mar 01/05

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Removal/Installation 401 ALL UNDERWATER LOCATING BEACON 23-71-36 Removal/Installation 401 001-102,108-108, Removal/Installation of Underwater 401 001-102,108-108, Locating Beacon

23-CONTENTS Page 7 JAS Mar 01/05

GENERAL - DESCRIPTION AND OPERATION ___________________________________

1. General _______ The communication systems allow crew members to communicate with each other, with the passengers, other aircraft and the ground stations.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 001 )

**ON A/C 001-101,

(Ref. Fig. 002 )

**ON A/C ALL

2. Description ___________ The communication systems comprise :

A. The Radio Equipment

**ON A/C 001-101,

(1)Not applicable.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(1)High Frequency (HF) system (Ref. 23-11-00) Two transceivers and associated equipment allow voice communications within 2 to 29.999 MHz frequency range, with 1 kHz spacing.

**ON A/C 001-101, 103-999,

(2)Very High Frequency (VHF) system (Ref. 23-21-00) Two transceivers and their associated equipment allow short range voice communications.

**ON A/C 101-101, 103-999,

After SB 23-085 For A/C 101-101,

(3)Selective Calling system (SELCAL) (Ref. 23-22-00)

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Communications - Block Diagram Figure 001

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Communications - Block Diagram Figure 002


A decoder enables a ground station to call a single aircraft in flight.

**ON A/C ALL

B. Interphone System (1)Flight interphone (Ref. 23-51-00) The flight interphone system provides a means of communication between the crew members. (2)Service interphone (Ref. 23-41-00) The service interphone provides a means of communication between the cabin attendant stations and the crew. Additionally, ground service jacks may be connected to the service interphone.

C. Passenger Address System (PA) (Ref. 23-31-00) The passenger address system allows transmission of announcements, instructions and pre-recorded music to passengers.

D. Cockpit Voice Recorder (Ref. 23-71-00) The cockpit voice recorder records and stores crew communications and conversations during flight for playback in case of accident.

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GENERAL - SERVICING ___________________

WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT _______ __________________________________________________ CONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS, ASSOCIA- TED DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUND SAFETIES AND/OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENT INADVERTENT OPERATION OF CONTROLS.

BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE CERTAIN THAT ELECTRICAL ________________________________________ CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED.

BEFORE PRESSURIZING HYDRAULIC SYSTEMS, MAKE CERTAIN THAT HYDRAULIC _____________________________________ SYSTEM UNDER MAINTENANCE HAS BEEN ISOLATED. WHEN EQUIPMENT IN RACKS AND/OR FLIGHT COMPARTMENT INSTRUMENTS ARE SUPPLIED WITH POWER FROM THE GROUND POWER UNIT, THE AVIONICS COMPART- MENT COOLING SYSTEM AND APPROPRIATE VENTILATION SYSTEMS MUST BE IN OPERATION. THE GROUND DEPRESSURIZATION VALVE MUST BE OPEN. FURTHER- MORE, IF AMBIENT TEMPERATURE IS ABOVE 30•C IN THE FLIGHT COMPART- MENT, THE GROUND AIR PRECONDITIONING SYSTEM MUST BE IN OPERATION. IF THE AIR CONDITIONING SYTEM IS NOT AVAILABLE, FLIGHT COMPARTMENT SIDE WINDOWS AND AVIONICS COMPARTMENT ACCESS DOORS MUST BE OPEN TO AVOID OVERHEATING OF EQUIPMENT.

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GENERAL - INSPECTION/CHECK __________________________

1. Inspection/Checks of Communication Systems __________________________________________ Inspection/checks are divided into two separate groups. - Cursory inspections which, without the necessity of removal, allow a visual check of directly accessible components. - Detailed inspections which, after removal or opening of any component obstructing access, allow thorough visual checks of all components of the systems inspected.

A. Cursory Inspection (1)Check the external mechanical condition, attachment and appearance of the following components : - panels and their equipment, - connectors, - rack-mounted system components, - panel instruments, - antennas, - bonding braids. (2)Check the condition of the wiring (signs of ageing, deterioration, overheating, chafing and kinking which may have an adverse effect on their characteristics). (3)Change defective components.

B. Detailed Inspection (1)Open access doors and housings, remove or open panels, shielding and components obtructing inspection (if necessary) in order to gain access to wiring, connectors, electrical interconnections and the various system components. (a)For the various components. - remove dust by means of a vacuum-cleaner and clean if necessary, - check labels and their identification markings, - check attachment and appearance of these components. (b)For wiring - check condition of identification sleeves or labels, coatings, fittings and protective devices, - check wiring condition (signs of ageing, deterioration, overheating, chafing and kinking which may have an adverse effect on their characteristics). (c)For connectors and electrical interwiring. - disconnect connectors, check their mechanical and electrical condition, look for rusting and corrosion and replace defective parts (seals, gaskets, grommets, bindings, etc.), - check that interconnections between all electrical units, bonding and grounding braids, bus and terminal bars are tight. - check locking of non wirelocked connectors. (2)Change defective components. (3)Return aircraft installation to operating condition.

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After SB 23-085 For A/C 101-101,

HF SYSTEM - DESCRIPTION AND OPERATION _____________________________________

1. General _______ Two control units associated with two systems allow two-way voice communications with ground stations and other aircraft. The frequency range is from 2.000 to 29.999 MHz (wide band) or from 2.8 to 23.999 MHz (narrow band) with channel spacing of 100 Hz or 1 KHz.

2. Component Location __________________ (Ref. Fig. 001 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RE1 Transceiver - HF1 (Ref. 23-11-33) 95VU 122 121BL 1RE2 Transceiver - HF2 (Ref. 23-11-33) 95VU 122 121BL 2RE1 Control Unit - HF COM1 (Ref. 20VU 210 23-11-13) 2RE2 Control Unit - HF COM2 (Ref. 20VU 210 23-11-13) 4RE1 Circuit Breaker - HF1 21VU 210 4RE2 Circuit Breaker - HF2 21VU 210 7RE1 Antenna Tuner - HF1 (Ref. 23-11-36) 323 312AR 7RE2 Antenna Tuner - HF2 (Ref. 23-11-36) 323 311AZ 6RE1 Mount - HF1 Transceiver (Ref. 95VU 122 121BL 23-11-37) 6RE2 Mount - HF2 Transceiver (Ref. 95VU 122 121BL 23-11-37) 9RE Antenna - HF (Ref. 23-11-11) 322 20RE1 Magnetic Indicator - HF1 XMTR 242VU 212 20RE2 Magnetic Indicator - HF2 XMTR 242VU 212 21RE1 Magnetic Indicator - HF1 CPLR 242VU 212 21RE2 Magnetic Indicator - HF2 CPLR 242VU 212 22RE1 Diode 323 312AR 22RE2 Diode 323 311AZ

3. System Description __________________ (Ref. Fig. 002 )

A. HF1 System The HF1 system consists of : (1)An HF COM1 control unit 2RE1 enabling starting and selection of HF1 transceiver operating frequency and mode. (2)An HF1 transceiver 1RE1 generating transmission signals. (3)An HF1 antenna tuner 7RE1 enabling automatically to match antenna impedance in the 2 to 29.999 MHz frequency range to obtain maximum efficiency when transmitting. (4)An HF antenna 9RE enabling transmission and reception of HF signals.

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HF System - Component Location Figure 001


HF System - Block Diagram Figure 002


(5)A circuit breaker 4RE1 supplying HF transceiver with three-phase 115VAC electrical power. (6)Two XMTR and CPLR locking magnetic indicators 20RE1 and 21RE1.

B. HF2 System The HF2 system is strictly identical with the HF1 system. It consists of : (1)An HF COM2 control unit 2RE2 (2)An HF2 transceiver 1RE2 (3)An HF2 antenna tuner 7RE2 (4)An HF antenna 9RE (5)A circuit breaker 4RE2 (6)Two locking magnetic indicators 20RE2 and 21RE2.


4. HF Control Unit _______________ (Ref. Fig. 003 )

**ON A/C 101-108,

HF Control Unit Figure 003

The HF control unit is secured by means of four Dzus fasteners located on the face. Electrical connections are made through a connector at the back of the unit. The HF control unit allows :

A. Frequency selection Selection of the operating freqency of the transceiver is made by means of four knobs. These knobs are associated with an indicator, which gives a direct reading of the operating frequency.

B. Mode selection The transceiver operating mode is selected, and the HF system energized, by the function selector switch. (1)OFF position The system is de-energized

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(2)AM (Amplitude Modulation) position Transmission and reception are possible in amplitude modulation. (3)SSB (Single Side Band) position Transmission and reception are possible in single side band.

C. 6SQUELCH6 adjustment The SQL potentiometer is used to adjust the level at which the transceiver squelch device is actuated, according to efficient signal and noise levels.

5. HF Transceiver (Ref. Fig. 004 ) ______________ (1)The face is split into two parts (a)The face of the transceiver (LH side), on which are : 1 A PHONE jack for connection of a headset. _ 2 A MIC jack for connection of a microphone. _ 3 A SQL/LAMP TEST pushbutton used for lamp test and to restore back- _ ground noise to check correct transceiver operation. 4 A red LRU FAIL warning light to indicate transceiver failures. _ 5 A red KEY INTERLOCK warning light to indicate tuning change and _ antenna circuit failures. 6 A red CONTROL INPUT FAIL warning light to indicate that the serial _ message is faulty. 7 A handle. _ 8 An identification plate. _ (b)The face of the adapter (RH side), on which are : 1 A SQL-SENS potentiometer used to remove background noise or to remove _ unused frequencies during test. 2 A GND/UNGND potentiometer used to reduce background noise. _ 3 An ANT A coaxial connector for an antenna with a tuner. _ 4 An AUX ANT B coaxial connector for an antenna with a tuner. _ 5 An ANT SELECT switch used to select ANT A or ANT A + B. _ 6 One MIC jack and one PHONE jack for connection of a hand microphone _ and a headset to test transceiver. 7 A wing-nut fastener which attaches the adapter to the transceiver. _ (2)Rear part The transceiver is connected electrically to the adapter by a dual connector composed of a pin connector and a coaxial connector. The connectors are located correctly during plugging in by a locating pin. An identical dual connector is installed on the rear of the adapter for connection of the transceiver/adapter assembly to the aircraft mount. (3)Interior The sub-assemblies are compact modules installed on articulated mobile supports which facilitate access to components. The sub-assemblies are as follows : - on the RH side, the antenna connector, the power amplifier, the low-pass filters, the power supply and the DC regulator - on the LH side the receiver, the synthetizer and the frequency control.

B. Characteristics The HF transceiver complies with the standards defined in ARINC 719 and 600. It enables transmission and reception of :


HF Transceiver Figure 004


- voice radio communication messages through electroacoustic equipment (headset, hand microphone, boomset and loudspeaker) - coded messages in keeping with ARINC 429. The HF transceiver operates in the 2 to 29.9999 MHz frequency range (wide range) or in the 2.8 to 23.9999 MHz frequency range (narrow range) on channels spaced by 1 KHz or 100 Hz. (1)Transmitter Output power : 125 W (average power) 400 W (peak-to-peak) Antenna impedance : 50 ohms Type of emission : AM (A3H), SSB (A3J-USB-LSB) CW (A1), A9 (transmission data) A7J (multichannel voice frequency telegraphy). (2)Receiver Output power : ≥5 mW into 600 ohms Sensitivity : SSB : 1 µV for 10 dB (s+n)/n AM : 4 µV for 10 dB (s+n)/n Selectivity : SSB : -6 dB at +350 Hz to +2500 Hz -60 dB at -1.5 KHz to +4.5 KHz AM : -6 dB at ±2700 Hz -60 dB at ±7000 Hz (3)Power supply Voltage : 3-phase, 115VAC, 400 Hz Power : reception : 70 W (without blower) transmission : 875 W (including 100-W blower)

C. Operation (1)Power supply (Ref. Fig. 005 ) The HF transceiver is supplied with 115 V, 400 Hz, 3-phase power. It is to be noted that one phase is used to supply with power the antenna tuner via the transceiver. Filtered +51VDC is provided for the transmission power circuits. For the other circuits, four voltages are provided from the +28VDC source : +20 V +10 V, -12 V and +5 V. (2)Block Diagram (Ref. Fig.006 and 007)


HF System - Power Supply Figure 005


INTENTIONALLY BLANK

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HF Transceiver - Block Diagram Sheet 1/2 Figure 006

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HF Transceiver - Block Diagram Sheet 2/2 Figure 007


(3)Receiver (Ref. Fig. 008 ) In receive mode, the antenna of the HF transceiver receives a signal of a frequency comprised between 2 and 29.9999 MHz. This signal is modulated in AM, USB or LSB mode. The signal from the antenna tuner is sent to a bandpass filter through the antenna relay. This filter covers the frequency range between 2 and 30MHz which obviates the need for tuned circuits. The filter output is applied through a transformer to an attenuator controlled by the AGC circuit and by an RF sensitivity circuit. The signal is then amplified in a wideband class A amplifier and sent to a first mixer. This mixer which is common to the transmit and receive parts receives the signal from the antenna (frequency between 2 and 29.9999 MHz) and the 71.8 to 99.7999 MHz signal from the synthesizer. When both signals are mixed, a 69.8 MHz signal is obtained. This 69.8 MHz signal is sent, after filtering and amplification, to a second mixer (common to the transmitter and receiver). This second mixer also receives a signal of 69.3 MHz in USB and AM operation or of 70.3 MHz in LSB operation. At the mixer output, a second intermediate frequency of 500 KHz is obtained. This 500 KHz signal is processed in two different ways depending on the mode of operation, i.e. SSB or AM mode.


INTENTIONALLY BLANK

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Functional Block Diagram Figure 008


(a)SSB mode Whatever the signal received (USB or LSB) the 500 KHz signal obtained after previous frequency transpositions is always an LSB signal. This signal is applied to the 500 KHz LSB filter, amplified and then applied to a product detector circuit. This circuit receives the LSB 500 KHz signal and a 500 KHz square wave from synthesizer. The output is the detected audio signal. This signal is filtered, amplified and transmitted via the AGC circuit and an AF input circuit which receives the signals from the AM and SSB channel. This circuit is used to power the data output (0.5 V) and the audio output through a final amplifier controlled by a squelch circuit. (b)AGC circuits In SSB mode, two different AGC circuits are used to check the gain of the receiver : an IF AGC and an RF AGC circuit. The detected signal is applied to an AGC detection circuit which produces a DC output directly proportional to the detected voltage. This voltage is applied to an IF AGC curve shaper which regulates the third IF amplifier input. In the event of a momentary interruption of the signal, the AGC hold circuit maintains the last DC voltage level for 1 s. The AF AGC circuit is also controlled by the DC voltage coming from the AGC detection but acts on the receiver input circuits at the level of the attenuator. (c)Squelch circuit The squelch circuit is checked by the DC voltage coming from the AGC detection. This voltage is applied to a comparator circuit. The other input of the comparator is provided with a voltage dependent on the value of the control unit squelch potentiometer. Preponderance of one signal can disable the final audio circuit. (d)AM mode The 500 KHz signal from the second mixer is applied to a first amplifier. It is then filtered by a 6 KHz band pass mechanical filter centered on 500 KHz. The signal is amplified three times by an amplifier controlled by the AGC circuit and then detected. It is amplified again and sent to two circuits : AGC circuit and AF circuit (SELCAL and AUDIO). The SELCAL output delivers a 0.5 V on a 600-ohm load. At audio output, the signal is sent to the AF input circuit described above. (e)AGC circuits In AM/SELCAL mode, three different AGC circuits are used : - AGC audio circuit : The AGC audio circuit acts upon the last stage of the SELCAL audio amplification depending on the detected AF output level. - AGC intermediate frequency circuit : The AGC intermediate frequency circuit acts upon the third stage of the intermediate frequency amplifier and ensures regulation depending on the detected IF signal value. - AGC HF circuit : The AGC HF circuit acts upon the HF stages (RF attenuator) depending


on the detected IF signal. (4)Transmitter (Ref. Fig.009 and 010) The modulation signal (audio, data or CW tone) is applied to a selection circuit, a low-pass filter and an amplifier. A signal compressor enables regulation of the input signal. After amplification, the audio signal modulates, within a balanced modulator, a 500 KHz injection signal from the frequency synthesizer. The 500 KHz carrier is cancelled and only the two sidebands are present on either side of the 500 KHz at the modulator output. This signal is amplified in a first 500 KHz amplifier before it is applied to a lower sideband (LSB) mechanical filter. This filter removes the upper sideband (USB). The signal is then amplified in a second 500 KHz amplifier before it is applied to a first mixer. When transmitting in AM mode, the second 500 KHz amplifier receives a 500 KHz carrier signal from the synthesizer through a carrier injection circuit. The 500 KHz signal, with or without a carrier, is then mixed, in a first mixer stage, with a 69.3 MHz signal in USB mode and with a 70.3 MHz signal in LSB mode. These signals from the frequency synthesizer mixed with the lower band 500 KHz produce a 69.8 MHz signal. The 69.8 MHz signal is sent to a second mixer through a crystal filter. Within the second mixer, the 69.8 MHz signal is mixed with the 71.8-to- 99.799 MHz frequency signal from the synthesizer. The resulting signal is a 2-to-29.9999 MHz signal. The output signal of the second mixer is amplified in three stages and then filtered. The signal output level is maintained constant through an automatic load control (ALC) attenuator. This signal is then applied to a 4-stage power amplifier which raises the power to 400 W peak-to-peak. The power amplifier stage has protective circuits which provide instantaneous reduction of the output power in the event of component overload or overheating. The signal is routed through seven filters which can be switched in by a motor, according to the operating frequency. These filters cover the frequency band from 2 to 29.999 MHz and cancel the harmonics of the output frequency. The signal is then sent to the antenna tuner and to the antenna through an antenna relay and internal directional wattmeter. Forward and reflected power measured by the wattmeter provides voltage which is used for modulation control, automatic load control (ALC) attenuator and power amplifier protection.


Transmitter - Sheet 1/2 Figure 009


Transmitter - Sheet 2/2 Figure 010


(5)Synthesizer (Ref. Fig. 011 ) The frequency synthesizer provides the four following frequency sources : - a fixed 500 KHz square wave signal - an USB 69.3 MHz sine wave or an LSB 70.3 MHz sine wave signal - a variable 71.8 to 99.7999 MHz sine wave signal - a fixed 19.8 KHz square wave signal. These signals are generated or derived from a 9.9 MHz frequency standard. (a)500 KHz signal The 500 KHz signal is derived from a 9 MHz crystal oscillator. It is then divided by 9 and by 2. A monitoring circuit compares the signal from the crystal oscillator with the signal from the frequency standard in order to obtain a great stability. The 500 KHz signal is used in the balanced modulator and in the mixer detector used in SSB reception. (b)69.3 MHz (USB) - 70.3 MHz (LSB) signals These two signals are delivered by a 69.3 or 70.3 MHz voltage- controlled oscillator (VCO). The signal is divided by 693 or 703 and is compared with a 100 KHz signal delivered by the frequency standard (9.9 MHz divided by 11 and 9). These frequencies are utilized in the mixer to produce an intermediate frequency of 69.8 MHz in transmission or a 500 KHz signal in reception. (c)71.8 to 99.7999 MHz signal This signal which is used as a local oscillator is produced by two cross-checked phase-locked loops. With this system, the local oscillator loop output is mixed with the output signal of the other loop oscillator in order to ensure frequency accuracy. These two loops utilize a reference signal of 9.9 KHz from the frequency standard and BCD data from the frequency controller. (d)19.8 KHz signal The 19.8 KHz signal is derived from the frequency standard 9.9 MHz. The 9.9 MHz frequency is divided twice by 10 and then by 5 (total division by 500). This is a square-wave voltage which is used in the power supply for the +5 V regulator and which, when divided by 2, delivers a 9.9 KHz frequency used as a reference by the preceding circuit.


INTENTIONALLY BLANK


Frequency Synthesizer Figure 011


(6)ARINC 429 message decoder selection (Ref. Fig. 012 ) The various steps are controlled by the control unit and transmitted to the transmitter through a serial low-speed message in keeping with ARINC 429 characteristics. The message can be made up of one or two words of 32 bits for the CW mode or for 100 Hz channel spacings. Frequency and mode decoding within the word is carried out by a microprocessor. The latter checks the message from the control unit and checks system operation. In the event of a failure, it controls the illumination of the lights located on the face and/or acts on the transmitter.

D. Test Correct operation of the transceiver can be checked by means of the various lights located on its face. - LRU FAIL warning light (LED) The LRU FAIL warning light comes on in the event of a transceiver failure such as : output power drop, microprocessor or synthesizer failure, etc. - KEY INTERLOCK warning light (LED) The KEY INTERLOCK warning light comes on in the event of an antenna circuit failure such as : tuner failure, excessive tuning time, excessive antenna reactance, etc. - CONTROL INPUT FAIL warning light (LED) The CONTROL INPUT FAIL warning light comes on when the serial message is faulty : absence of label, insufficient data repetition, message not valid. - SQL/LAMP TEST pushbutton When pressing the SQL/LAMP TEST pushbutton, all the lights come on, the squelch is disabled and causes background noise to be heard in the headset.

6. HF Antenna Coupler __________________

A. Description (Ref. Fig. 013 ) The antenna coupler is located in zone 323, at the base of the vertical stabilizer. Two multipin connectors, a coaxial connector and a pressurizing valve are located on the face. The case is sealed and pressurized before installation on the aircraft. The tuner allows automatic impedance matching in the 2 to 29.999 MHz frequency range. It contains the necessary switching and interlock circuits for use in either a single or a dual HF system. An internal power supply converts the aircraft power to the voltages required by the various circuits. Two magnetic indicators (XMTR and CPLR) located on maintenance panel 470VU monitor antenna coupler operation. The magnetic indicators display white clover when there is a fault. - tuning sequence too long (more than 15 sec.) - tuning sequence too long (more than 15 sec.) when transmission signal


INTENTIONALLY BLANK


Frequency Control - Functional Block Diagram Figure 012


R **ON A/C 101-108,

HF Antenna Coupler Figure 013

is too low or missing - internal arcing or pressure drop in antenna coupler.


B. Operation of Antenna Couplers The antenna coupler dual system is able to operate with an antenna and two transceivers. In transmit mode, priority is given to the system which first starts to operate. The logic circuit of the antenna coupler provides the latter with the possibility of taking three decisions which determine : - Whether both antenna couplers are in receive mode or not. - Whether an antenna coupler is in receive mode or not. - Which antenna coupler received a key (ground) first. If antenna coupler No.1 receives a key (ground) signal before antenna coupler No.2, the antenna coupler No.1 is switched from receive mode to tune or operating mode. Antenna coupler No.2 is disconnected from the antenna and the isolation amplifier inputs are grounded. When the tune cycle is completed or when the key signal is suppressed, the isolation amplifier inputs are no longer grounded and both antenna couplers come back to receive mode. If the tuning of an antenna coupler is in progress or if the latter is in the transmit mode, a key signal sent to the other antenna coupler has no effect.

C. Antenna Coupler Monitoring Antenna tuner faults are displayed by two magnetic indicators located on Flight EngineerSs panel. - The HF1 (HF2) XMTR magnetic indicators indicate that the coupler has failed to tune because the transmitter power is too low - The HF1 (HF2) CPLR magnetic indicators indicate that the tuning sequences have not been performed or that there is arcing in the coupler and a pressure drop inside the tuner itself. - A three-position (TEST-BITE-RESET) switch located on Flight EngineerSs panel 54VU allows to reset the magnetic indicators after a test or a fault.

7. HF Antenna Coupler __________________ (Ref. Fig. 014 ) The HF antenna consists of a U-section anodized aluminum extrusion, 2650 mm long and 100 mm wide. It is mounted on five insulating supports attached to the vertical stabilizer structure. The coaxial cable is connected to the lower part of the antenna and is connected to the antenna tuner through an insulated/partition feedthrough terminal. The upper end of the antenna is connected to ground by a conducting support. The antenna is protected by the vertical stabilizer leading edge and is thus maintenance free.


HF Antenna Figure 014


8. Interface _________ (Ref. Fig. 015 )

R **ON A/C 101-108,

HF System - Interface Figure 015

The HF system is connected with :

A. The flight interphone system, which receives the AF signals from the various reception stations and provides microphone and PTT (push to talk) switch signals.

B. The flight recorder, which receives a ground signal from the PTT switch during HF system transmission.

C. The HF system in the AM function only which provides the audio data enabling the SELCAL decoder to operate.


HF SYSTEM - FAULT ISOLATION ___________________________

Refer FI/MM 23-11-00, P. Block 101


After SB 23-085 For A/C 101-101,

HF SYSTEM - ADJUSTMENT/TEST ___________________________

1. Operational Test ________________

A. Reason for the Job To check briefly that HF1 and HF2 systems operate correctly

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/ 200 V, 400 Hz, 90 KVA (2) 150 Ohm Hand Microphone (High Level) (3) 600 Ohm Headset Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Job Set-Up NOTE : The aircraft must be outside hangar. ____ (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation system is operating (Ref. 21-20-00, P. Block 301). (3)Make certain that the following circuit breakers are closed : (a)HF1 system ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU HF1/28 VDC 3RE1 103/L10 21VU HF1/115 VAC 4RE1 103/L12 21VU BITE 1WB 112/B 5 22VU CONTRL PNL/1ST OBSV & AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11 22VU INTPH AMPLI/FLT 19RL 209/E 9 22VU CONTRL PNL/FLT ENGR 50RL 209/E12

(b)HF2 system ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU HF2/28 VDC 3RE2 101/N10 21VU HF2/115 VAC 4RE2 101/N12 21VU BITE 1WB 112/B 5 22VU CONTRL PNL/1ST OBSV & AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11


------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU INTPH AMPLI/FLT 19RL 209/E 9 22VU CONTRL PNL/FLT ENGR 50RL 209/E12

(4)On panel 29VU - place RADIO MASTER SUPPLY SYS1-OFF switch in SYS1 position for HF1 system. - place RADIO MASTER SUPPLY SYS2-OFF switch in SYS2 position for HF2 system. (5)On CaptainSs and First OfficerSs control column handwheels and at Second ObserverSs station : - place RAD-INT PTT switches in intermediate position (6)On CaptainSs, First OfficerSs, Flight EngineerSs, First ObserverSs and avionics compartment audio selector panels : - place RAD-INT PTT switches in intermediate position - engage INT transmission key - engage all reception push-buttons. (7)On CaptainSs, First OfficerSs, Flight EngineerSs, First and Second ObserversS jack boxes - connect a boomset to BOOM interphone connection receptacle - place MIC SELECT OXY-BOOM switch in BOOM position (8)In avionics compartment, on LH electronics rack 80VU - connect a headset to jack - connect a hand microphone to interphone connection receptacle (9)On overhead panel - place function selector switch on HF1 and HF2 control units (2RE1 and 2RE2) in AM position. - HF1 and HF2 transceiver fans start operating. CAUTION : IF TRANSCEIVER FAN DOES NOT START OPERATING, RETURN _______ FUNCTION SELECTOR SWITCH TO OFF POSITION IMMEDIATELY. (10)Allow equipment to warm up for approximately 2 minutes

D. Test NOTE : The following adjustment/test procedures are for HF1 system. ____ Procedures for HF2 system are identical, the electrical identifiers and labels being shown in parentheses. (1)Test of maintenance components on Flight EngineerSs panel. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 54VU - place TEST-BITE-RESET switch in - On panel 242VU, magnetic indica- TEST position tors HF MONITOR 1XMTR (2XMTR) and 1CPLR (2CPLR) display white clover - place TEST-BITE-RESET switch in - Magnetic indicators HF MONITOR RESET position 1XMTR (2XMTR) and 1CPLR (2CPLR) display black

NOTE : TEST-BITE-RESET switch enables to reset magnetic indicators ____

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 101-999, K 23-11-00 K K CONF. 01 K KR 2 K K JAS Mar 01/05

after either a test or a failure cancellation. (2)Reception Test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On CaptainSs audio selector panel - disengage HF1 (HF2) reception push- button - turn clockwise potentiometer integral with the push-button - engage HF1 (HF2) transmission key

2. On overhead panel, on HF1 (HF2) control unit - select the transmitting frequency of a station in operation

3. On CaptainSs control column handwheel, - During tuning period (approximate- place PTT switch in RAD position, then ly 8 seconds), a 1000 Hz signal is release osition, then release received at headset.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

4. On overhead panel, on HF1 (HF2) - Make certain that squelch func- control unit, turn SQL potentiometer tion is inhibited (a permanent clockwise background noise can be heard)

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

5. On CaptainSs audio selector panel, - Action of potentiometer on recep- turn HF1 (HF2) reception push-button tion level must be progressive clockwise and without any crackling.

(3)Transmission Test CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED _______ FREQUENCY IS FREE AND OBSERVE THE RADIO REGULATIONS. IF THE FAN ROTATION SPEED DOES NOT INCREASE DURING TRANSMIS- SION, STOP TRANSMITTING IMMEDIATELY. WARNING : DO NOT KEY HF SYSTEM WHILE AIRCRAFT IS BEING FUELED. INJURY _______ TO PERSONNEL OR FIRE MAY RESULT.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On overhead panel, on HF1 (HF2) control unit, select an authorized frequency.

2. On CaptainSs control column handwheel, - Make certain that reception is hold PTT switch in RAD position then inhibited during turning period release (approximately 8 seconds)

3. When turning period is over, hold - HF1 (HF2) transceiver fan rotation PTT switch on CaptainSs control co- speed increases immediately lumn handwheel in RAD position

4. Speak into boomset microphone - Check quality of reception at headset.

5. Release PTT switch

6. Successively repeat test described in paragraphs 1.D.(2) and 1.D.(3) at First OfficerSs Flight EngineerSs, First and Second ObserverSs and avionics compartment stations, using appropriate PTT switch at each station.

NOTE : The Second ObserverSs station depends on selections ____ made on Flight EngineerSs audio selector panel. (4)Simultaneous operation of both HF systems. (a)Reception test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On overhead panel, on HF1 control unit - place function selector switch in AM position - select a transmitting station

2. On overhead panel, on HF2 control unit - place function selector switch in AM position - select a transmitting station, different from the former one

3. On CaptainSs audio selector panel - disengage HF1 reception push-button - make certain that all other reception push-buttons are engaged

4. On panel 241VU


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - disengage and turn LOUDSPEAKER - Make certain that transmission is VOLUME push-button clockwise received at CaptainSs loudspeaker

5. On First OfficerSs audio selector panel - disengage HF2 reception push-button - make certain that all other reception push-buttons are engaged

6. On panel 240VU, disengage and turn - Make certain that transmission LOUDSPEAKER VOLUME push-button (different from the former one) is clockwise received at First OfficerSs loudspeaker.

(b)Transmission test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. In avionics compartment, on electronics rack 90VU, on HF1 and HF2 transceivers place test selector switch in PAMA position

2. On one audio selector panel, engage HF1 transmission key

3. On other audio selector panel, engage HF2 transmission key

4. Transmit on HF1 system

5. Transmit on HF2 system while conti- nuing transmission on HF1 system - Make certain that HF2 transmceiver pointer does not deflect - Make certain that HF1 system is in operation

6. Carry out test described in paragraph - Check that priority is left to the 1.D (4) (6), selecting first HF2 sys- first system in operation instead of HF1 system

E. Close-Up (1)On overhead panel, on HF1 (HF2) control unit - place function selector switch in OFF position (2)On audio selector panels - engage HF1 (HF2) reception push-button - engage INT transmission key.


(3)On panel 29VU - place RADIO MASTER SUPPLY SYS1-OFF switch in OFF position, for HF1 system - place RADIO MASTER SUPPLY SYS2-OFF switch in OFF position, for HF2 system. (4)In avionics compartment, on LH electronics rack 80VU - disconnect headest and hand microphone. (5)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (6)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


2. Functional Test _______________

3. System Test ___________

A. Reason for the job To check HF1 and HF2 systems for correct operation.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-phase, 115/ 200V, 400 Hz, 90 KVA (2) Ohmmeter (3) 150 Ohm Hand Microphome (High Level) (4) 600 Ohm Headset (5)99A23201001000 Wiring - Connecting for Testing HF System Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Job Set-Up NOTE : The aircraft must be outside hangar. ____ (1)Connect electrical groung power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation system is operating. (Ref. 21-20-00, P. Block 301) (3)Make certain that the following circuit breakers are closed : (a)HF1 system ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU HF1/28 VDC 3RE1 103/L10 21VU HF1/115 VAC 4RE1 103/L12 21VU BITE 1WB 112/B 5 22VU CONTRL PNL/1ST OBSV & AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11 22VU INTPH AMPLI FLT 19RL 209/E 9 22VU CONTRL PNL/FLT ENGR 50RL 209/E12

(b)HF2 system ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU HF2/28 VDC 3RE2 101/N10 21VU HF2/115 VAC 4RE2 101/N12 21VU BITE 1WB 112/B 5 22VU CONTRL PNL/1ST OBSV & AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11 22VU INTPH AMPLI/FLT 19RL 209/E 9


------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU CONTRL PNL/FLT ENGR 50RL 209/E12

(4)On panel 29VU - place RADIO MASTER SUPPLY SYS1-OFF switch in SYS1 position for HF1 system - place RADIO MASTER SUPPLY SYS2-OFF switch in SYS2 position for HF2 system. (5)On CaptainSs and First OFficerSs control column handwheels and at Second ObserverSs station : - place RAD-INT PTT switches in intermediate position (6)On CaptainSs First OfficerSs, Flight EngineerSs, First ObserverSs and avionics compartment audio selector panels : - place RAD-INT PTT switches in intermediate position - engage INT transmission key - engage all reception push-buttons. (7)On CaptainSs, First OfficerSs Flight EngineerSs, First and Second ObserverSs jack boxes : - connect a boomset to BOOM interphone connection receptacle - place MIC SELECT OXY-BOOM switch in BOOM position (8)In avionics compartment, on LH electronics rack 80VU - connect a headset to jack - connect a hand microphone to interphone connection receptacle. (9)On overhead panel - place function selector switch on HF1 and HF2 control units (2RE1 and 2RE2) in AM position - HF1 and HF2 transceiver fans start operating. CAUTION : IF TRANSCEIVER FAN DOES NOT START OPERATING, RETURN _______ FUNCTION SELECTOR SWITCH TO OFF POSITION IMMEDIATELY. (10)Allow equipment to warm up for approximately 2 minutes.

D. Test NOTE : The following adjustment/test procedures are for HF1 system. ____ Procedures for HF2 system are identical, the electrical identifiers the electrical identifiers and labels being shown in parentheses. (1)Test of maintenance components on Flight EngineerSs panel. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 54VU - On panel 242VU, - place TEST-BITE-RESET switch in magnetic indicators HF MONITOR TEST position 1XMTR (2XMTR) and 1CPLR (2CPLR) display white clover - place TEST-BITE-RESET switch in - magnetic indicators HF MONITOR RESET position 1XMTR (2XMTR) and 1CPLR (2CPLR) display black

NOTE : TEST-BITE-RESET switch ____ enables to reset magnetic


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- indicators after either a test or a failure cancellation

2. Disconnect connector 7RE1-A (7RE2-A) from antenna tuner

3. On electrical connector 7RE1-A (7RE2- - Magnetic indicator HF MONITOR 1CPLR A), connect terminal V to ground and (2CPLR) displays white clover disconnect immediately

4. On panel 54VU - Magnetic indicator HF MONITOR 1CPLR - place TEST-BITE-RESET switch in (2CPLR) displays black RESET position

5. On electrical connector 7RE1-A - Magnetic indicator HF MONITOR 1CPLR (7RE2-A), connect terminal B to (2CPLR) displays white clover ground and disconnect immediately

6. On panel 54VU - Magnetic indicator HF MONITOR 1CPLR - place TEST-BITE-RESET switch in (2CPLR) displays black RESET position

7. On electrical connector 7RE1-A - Magnetic indicator HF MONITOR 1XMTR (7RE2-A), connect terminal C to (2XMTR) displays white clover ground and disconnect immediately

8. On panel 54VU - Magnetic indicator HF MONITOR 1XMTR - place TEST-BITE-RESET in RESET (2XMTR) displays black position

9. Connect electrical connector 7RE1-A (7RE2-A) to antenna tuner

(2)Reception Test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On CaptainSs audio selector panel - disengage HF1 (HF2) reception push- button - turn clockwise potentiometer integral with this push-button - engage HF1 (HF2) transmission key

2. On overhead panel, on HF1 (HF2) control unit - select the transmitting frequency of a station in operation


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 3. On CaptainSs control column handwheel, - During tuning period (approxima- place PTT switch in RAD position, then tely 8 seconds) a 1000 Hz signal release is received at headset.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

4. On overhead panel, on HF1 (HF2) - Make certain that squelch func- control unit, turn SQL potentio- ion is inhibited (a permanent meter clockwise background noise can be heard)

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

5. On CaptainSs audio selector panel, - Action of potentiometer on recep- turn HF1 (HF2) reception push-button tion level must be progresseve clockwise and without any crackling

(3)Transmission test CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED _______ FREQUENCY IS FREE AND OBSERVE THE RADIO REGULATIONS IF THE FAN ROTATION SPEED DOES NOT INCREASE DURING TRANSMIS- SION, STOP TRANSMITTING IMMEDIATELY. WARNING : DO NOT KEY HF SYSTEM WHILE AIRCRAFT IS BEING FUELED. INJURY TO _______ PERSONNEL OR FIRE MAY RESULT. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On overhead panel, on HF1 (HF2) control unit, select an authorized frequency

2. On CaptainSs control column handwheel, - Make certain that reception is hold PTT switch in RAD position, then inhibited during tuning period release (approximately 8 seconds)

3. When tuning period is over, hold PTT - HF1 (HF2) transceiver fan rotation switch on CaptainSs control column speed increases immediately handwheel in RAD position

4. Speak into boomset microphone while - Check quality of reception at holding associated PTT switch in RAD headset


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- RAD position

5. Release PTT switch

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(4)Repeat test described in paragraph 1.D(2) and 1.D(3), placing function selector switch on HF1 (HF2) control unit in SSB position.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(5)Repeat test described in paragraph 1.D (2) and 1.D (3), successively from First OfficerSs, Flight EngineerSs, First and Seconds Obser- verSs and avionics compartment stations, using appropriate PTT switch at each station NOTE : The Second ObserverSs station depends on selections made ____ on Flight EngineerSs audio selector panel. (6)Standing Wave Ratio (SWR) measurement (a)On shelf 95VU (94VU) - interpose a directional HF wattmeter between HF1 (HF2) transceiver coaxial output and HF1 (HF2) antenna feeder - measure and note transmitted and reflected powers for the three following frequencies : 2000 KHz, 15,000 KHz and 29,990 KHz - check that SWR is below 2 (7)Test of frequency automatic display CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED _______ FREQUENCY IS FREE AND OBSERVE RADIO REGULATION. (a)Establish a communication on HF1 (HF2) system (in AM mode) with a ground radio station for each of the following frequencies : 2721 KHz, 4270 KHz, 8189 KHz, 19,818 KHz and 23,000 KHz. (8)Test of interconnection with flight data recorder (a)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU RECORDERS/PWR SUPPLY 115VAC 7TU 110/D 3 22VU RECORDERS/FLT PWR SUPPLY 12TU 210/D10

(b)On electronics rack 90VU, on shelf 94VU, remove flight data acquisition unit (c)Test


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At one Crew MemberSs station place - Make certain that terminal 33 (30) corresponding PTT switch in RAD posi- of rack connector 2TU-BB is con- tion then release HF1 (HF2) transmis- nected to ground sion key on audio selector panel being engaged)

2. Release PTT switch - Make certain that terminal 33 (30) of rack connector 2TU-BB is no longer connected to ground

(d)On electronics rack 90VU, on shelf 94VU, install flight data acquisition unit. (e)Remove safety clips and tags and close the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU RECORDERS/PWR SUPPLY 115VAC 7TU 110/D 3 22VU RECORDERS/FLT PWR SUPPLY 12TU 210/D10

(9)Simultaneous operation of both HF systems. (a)Reception test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On overhead panel, on HF1 control unit - place function selector switch in AM position - select a transmitting radio station.

2. On overhead panel, on HF2 control unit - place function selector switch in AM position - select a transmitting station, different from the former one

3. On CaptainSs audio selector panel - Make certain that transmission is - disengage HF1 reception push-button received at CaptainSs loudspeaker - Make certain that all other reception push-buttons are engaged

4. On panel 241VU - disengage and turn LOUDSPEAKER VOLUME push-button clockwise

5. On First OfficerSs audio selector


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- panel - disengage HF2 reception push-button - make certain that all other reception push-buttons are engaged

6. On panel 240VU - Make certain that transmission - disengage and turn LOUDSPEAKER (different from the former one) VOLUME push-button clockwise is received at First OfficerSs loudspeaker

(b)Transmission test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. In avionics compartment, on electronics rack 90VU, on HF1 and HF2 transceivers, place test selector switch PAMA position

2. On one audio selector panel, engage HF1 transmission key

3. On other audio selector panel, engage HF2 transmission key

4. Transmit on HF1 system

5. Transmit on HF2 system while conti- - Make certain that HF2 transceiver nuing transmission on HF1 system pointer does not deflect - Make certain that HF1 system is still in operation

6. Carry out test described in paragraph - Check that priority is left to the 1.D (4) (6), selecting first HF2 sys- first system in operation tem instead of HF1 system

E. Close-Up (1)On overhead panel, on HF1 (HF2) control unit - place funtion selector switch in OFF position. (2)On audio selector panels : - engage HF1 (HF2) reception push-button - engage INT transmission key. (3)On panel 29VU - place RADIO MASTER SUPPLY SYS1-OFF switch in OFF position for HF1 system - place RADIO MASTER SUPPLY SYS2-OFF switch in OFF position for HF2 system. (4)In avionics compartment, on LH electronics rack 80VU


- disconnect headset and hand microphone (5)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (6)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


HF ANTENNA - REMOVAL/INSTALLATION _________________________________

WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE CERTAIN THAT CIRCUITS, _______ UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED.

1. Reasons for the Job ___________________

A. Replacement of defective antenna.

B. Replacement of defective feeder.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform, 10 m (33 ft.)

B. Warning Notices C. Crane D. Hoisting Equipment E. Material No. 16-003 Structure Paint (Ref. 20-31-00) Referenced Procedures - 55-32-11, P. Block 401 Vertical Stabilizer Leading Edge - 23-11-00, P. Block 501 High Frequency System

3. Procedure _________

A. Job Set-Up (1)Statically ground aircraft. (2)Place warning notices on rudder and elevator controls in flight compartment. (3)Open, safety and tag following circuit breakers:

**ON A/C 001-101,

------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 21VU RAD-NAV & COM/HF/28 VDC 3RE 101/N10 21VU RAD-NAV & COM/HF/115 VAC 4RE 101/N12

R **ON A/C 105-999,

------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 21VU RAD-NAV & COM/HF1/28 VDC 3RE1 103/L10 21VU RAD-NAV & COM/HF1/115 VAC 4RE1 103/L12 21VU RAD-NAV & COM/HF2/28 VDC 3RE2 101/N10 21VU RAD-NAV & COM/HF2/115 VAC 4RE2 101/N12


**ON A/C 102-104,

-------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION -------------------------------------------------------------------------------- 21VU RAD-NAV & COM/HF1/28 V DC 3RE1 103/L10 21VU RAD-NAV & COM/HF1/115 V AC 4RE1 103/L12

**ON A/C 101-101,

After SB 23-085 For A/C 101-101,

-------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION -------------------------------------------------------------------------------- 21VU RAD-NAV & COM/HF1/28 V DC 3RE1 103/L10 21VU RAD-NAV & COM/HF1/115 V AC 4RE1 103/L12 21VU RAD-NAV & COM/HF2/28V DC 3RE2 101/N10 21VU RAD-NAV & COM/HF2/115 V AC 4RE2 101/N12

**ON A/C ALL

(4)Position access platform at zone 322. (5)Position crane and hoisting equipment at zone 322. NOTE : Removal/installation of double and single feeders is similar, ____ therefore only one will be described.

B. Removal (Ref. Fig. 401 ) (1)Removal of antenna (Ref. Fig. 401 ) (a)Remove vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401). (b)Remove cotter pin (15), nut (16) and washer (17). (c)Remove feeder (13). (d)Remove nut (18), washers (19, 7) and bolt (6). (e)Remove nuts (5), washers (4, 3), screws (2) from antenna brackets and remove antenna (1). (2)Removal of feeder (Ref. Fig. 401 ) (a)Remove vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401). (b)Remove cotter pin (15), nut (16) and washer (17). (c)Remove nut (8), washer (9), bolt (20) and feeder clip (14). (d)Remove nut (10), washer (11) and feeder (13) from ball pin connector (12). (e)Remove feeder (13).

(1)Removal of antenna (Ref. Fig. 402 ) (a)Removal vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401).

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: ALL K 23-11-11 K K K KR Page 402 K K JAS Mar 01/05

HF Antenna and Feeder Figure 401


HF Antenna and Feeder Figure 402


(b)Remove nut (7), washer (6), feeder (13) and washer (5). (c)Remove nut (4), washers (3, 2) and bolt (1). (d)Remove nuts (12), washers (11, 10), screws (9) from antenna brackets and remove antenna (8). (2)Removal of feeder (Ref. Fig. 402 ) (a)Remove vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401). (b)Remove nut (7), washers (6), feeder (13) and washer (5). (c)Remove nut (18), washers (17, 14), bolt (15) and feeder clip (16). (d)Remove nut (19), washer (20) and feeder (13) from ball pin connector (21). (e)Remove feeder (13).

C. Installation (1)Installation of antenna (Ref. Fig. 401 ) (a)Install antenna (1), with screws (2), washers (3, 4) and nuts (5) (b)Establish feeder connection to antenna, with bolt (6), washers (7, 19) and nut (18). (c)Assemble feeder (13), with washer (17), nut (16) and cotter pin (15). (d)Coat feeder hardware with lacquer (Material No. 16-003). (e)Install vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401). (2)Installation of feeder (Ref. Fig. 401 ) (a)Install feeder (13), to antenna with washer (17), nut (16) and cotter pin (15). (b)Assemble feeder clip (14), with bolt (20), washer (9) and nut (8). (c)Assemble feeder to ball pin connector (12), with washer (11) and nut (10). (d)Coat feeder hardware with lacquer (Material No. 16-003). (e)Install vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401).

(1)Installation of antenna (Ref. Fig. 402 ) (a)Install antenna (8), with screws (9), washers (10, 11) and nuts (12). (b)Install bolt (1), washers (2, 3) and nut (4).

**ON A/C 001-006, 102-106, 108-108,

(c)Slide grommet (22), if not previously fitted, over feeder (13). Assemble feeder (13) with washers (5, 6) and nut (7). Ensure grommet is positioned as shown in fig.

**ON A/C 007-101, 107-107, 109-999,

(c)Assemble feeder (13) complete with grommet (22) using washers (5, 6) and nut (7). Ensure grommet is positioned as shown in fig.

**ON A/C ALL

(d)Coat feeder hardware with lacquer (Material No. 16-003). (e)Install vertical stabilizer lower leading edge panel (Ref. 55-32-11,


P. Block 401). (2)Installation of feeder (Ref. Fig. 402 ) (a)Assemble feeder (13) complete with grommet (22) using washers (5, 6) and nut (7). (b)Install feeder clip (16), with bolt (15), washers (14, 17) and nut (18). (c)Assemble feeder to ball pin connector (21), with washer (20) and nut (19). (d)Ensure grommet (22) is correctly positioned on feeder as shown in fig. (e)Coat feeder hardware with lacquer (Material No. 16-003). (f)Install vertical stabilizer lower leading edge panel (Ref. 55-32-11, P. Block 401).

D. Test (1)Test high frequency system (Ref. 23-11-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove crane and hoisting equipment. (4)Remove warning notices from rudder and elevator controls in flight compartment. (5)Remove static ground connection.


HF ANTENNA - INSPECTION/CHECK _____________________________

1. Visual Check ____________

A. Reason for the Job (1)Visual inspection of the HF-antenna feeder.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Access Platform, 10 m (33 ft.) (2) Circuit Breaker Safety Clips Referenced Procedures - 53-53-12, P. Block 401 Dorsal Fin - 23-11-11, P. Block 401 HF Antenna

C. Procedure (1)Job Set-Up (a)Open, safety and tag the following circuit breakers: ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION -------------------------------------------------------------------------------

**ON A/C 001-101,

21VU RAD-NAV&COM/HF 28VDC 3RE 101/N10 21VU RAD-NAV&COM/HF 115VAC 4RE 101/N12

R **ON A/C 103-999,

21VU RAD-NAV&COM/HF1 28VDC 3RE1 103/L10 21VU RAD-NAV&COM/HF1 115VAC 4RE1 103/L12 21VU RAD-NAV&COM/HF2 28VDC 3RE2 101/N10 21VU RAD-NAV&COM/HF2 115VAC 4RE2 101/N12

**ON A/C 102-104,

21VU RAD-NAV&COM/HF1 28VDC 3RE1 103/L10 21VU RAD-NAV&COM/HF1 115VAC 4RE1 103/L12

**ON A/C 101-101,

After SB 23-085 For A/C 101-101,

21VU RAD-NAV&COM/HF1 28VDC 3RE1 103/L10 21VU RAD-NAV&COM/HF1 115VAC 4RE1 103/L12 21VU RAD-NAV&COM/HF2 28VDC 3RE2 101/N10 21VU RAD-NAV&COM/HF2 115VAC 4RE2 101/N12


**ON A/C ALL

(b)Position access platform. (c)Remove dorsal fin (Ref. 53-53-12, P. Block 401). (2)Visual inspection of HF-antenna feeder. (a)Check that HF-antenna feeder is in operating condition. (b)Check that HF-antenna feeder is free from damage. (c)Check HF-antenna feeder for security of attachment. (d)Check HF-antenna feeder and attachment for corrosion. NOTE : Damaged or broken HF antenna feeders must be replaced ____ (Ref. 23-11-11, P. Block 401). (3)Close-Up (a)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (b)Install dorsal fin (Ref. 53-53-12, P. Block 401). (c)Remove access platform.

**ON A/C 001-101,

(d)Remove safety clips and tags, and close circuit breakers 3RE and 4RE.

R **ON A/C 105-999,

(d)Remove safety clips and tags, and close circuit breakers 3RE1, 4RE1 3RE2 and 4RE2.

**ON A/C 101-101,

After SB 23-085 For A/C 101-101,

(d)Remove safety clips and tags, and close circuit breakers 3RE1, 4RE1 3RE2 and 4RE2.

**ON A/C 102-104,

(d)Remove safety clips and tags, and close circuit breakers 3RE1 and 4RE1.


After SB 23-085 For A/C 101-101,

HF CONTROL UNIT - REMOVAL/INSTALLATION ______________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- Circuit Breaker Safety Clips Blanking Caps Referenced Procedure 23-11-00, P. Block 501 HF System

R **ON A/C 101-108,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 401 )

**ON A/C 101-999,

After SB 23-085 For A/C 101-101,


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU HF1/28VDC 3RE1 103/L10 21VU HF1/115VAC 4RE1 103/L12 21VU HF2/28VDC 3RE2 101/N10 21VU HF2/115VAC 4RE2 101/N12

**ON A/C 101-999,

After SB 23-085 For A/C 101-101,

B. Removal (1)Unlock Dzus fasteners (4) and pull out HF control unit (3). (2)Disconnect electrical connector (1). (3)Remove HF control unit. (4)Cap electrical connectors (1) and (2).

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HF Control Unit Figure 401


C. Installation (1)Clean and inspect HF control unit (3) interface. (2)Make certain that electrical connectors (1) and (2) are in correct condition. (3)Position HF control unit and connect electrical connector (1). (4)Install HF control unit and attach with Dzus fasteners (4).

**ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(5)Remove safety clips and tags and close circuit breakers 3RE1, 4RE1, 3RE2 and 4RE2.

**ON A/C 101-999,

After SB 23-085 For A/C 101-101,

D. Test Carry out an operational test of HF system (Ref. 23-11-00, P. Block 501).

E. Close-Up Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


After SB 23-085 For A/C 101-101,

HF TRANSCEIVER - REMOVAL/INSTALLATION _____________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips

R **ON A/C 108-999,

**ON A/C 101-106,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 402 )

R **ON A/C 101-106, 108-999,

After SB 23-085 For A/C 101-101,



R **ON A/C 101-106, 108-999,

After SB 23-085 For A/C 101-101,

B. Removal (1)Loosen nut (5) to clear stud (4) on transceiver (3). (2)Pull out transceiver from mounting tray (6). (3)Remove transceiver.

C. Installation

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(1)Clear and inspect transceiver interface. (2)Make certain that electrical connectors (1) and (2) are in correct condition. (3)Position transceiver on mounting tray and push in rack. (4)Engage nuts (5) on transceiver studs and tighten nuts.

R **ON A/C 101-106, 108-999,

After SB 23-085 For A/C 101-101,

(5)Remove safety clips and tags and close circuit breakers 3RE1, 4RE1, 3RE2 and 4RE2.

R **ON A/C 101-106, 108-999,

After SB 23-085 For A/C 101-101,

D. Test (1)Carry out HF system operational test (Ref. 23-11-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

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HF TRANSCEIVER - REMOVAL/INSTALLATION _____________________________________




B. Removal (1)Loosen nuts (5) to clear studs (4) on transceiver (3). (2)Pull out transceiver/adapter assembly from mounting tray (6) using handle (7). (3)Remove transceiver, first checking that it is correctly attached to adapter (8) by wing nut fastener (9).

C. Preparation of Replacement Component Check transceiver type to determine if adapter is necessary for installation.

D. Installation (1)Clean and inspect transceiver installation area. (2)Position transceiver on mounting tray and push in rack, making certain that locating pin positions correctly in hole (10). (4)Engage nuts (5) on transceiver studs and tighten nuts. (5)Remove safety clips and tags and close circuit breakers 3RE1, 4RE1, 3RE2 and 4RE2.

E. Test Select frequency of local airport traffic control, transmit from a crew station using appropriate PTT switch, and check reception in headsets.


ANTENNA TUNER - REMOVAL/INSTALLATION ____________________________________

WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE CERTAIN THAT THE _______ CIRCUITS, UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------ ITEM DESIGNATION ------------------------------------------------------------------------------ A. Access Platform, 6 m (19 ft.) B. Warning Notices C. Blanking Caps Referenced Procedure - 23-11-00, P. Block 501 High Frequency System


A. Job Set-Up

**ON A/C 001-101,

(1)Open, safety and tag the following circuit breakers: -------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION -------------------------------------------------------------------------------- 21VU RADIO-NAV & COM/HF/28VDC 3RE 101/N10 21VU RADIO-NAV & COM/HF/115VAC 4RE 101/N12 21VU PITCH TRIM 1/PWR SUPPLY 28VDC 13CC1 106/H 2 21VU PITCH TRIM 1/PWR SUPPLY 115VAC 14CC1 106/H 4 21VU PITCH TRIM 1/26VAC 15CC1 106/H 6 21VU PITCH TRIM 2/PWR SUPPLY 28VDC 13CC2 106/H 7 21VU PITCH TRIM 2/PWR SUPPLY 115VAC 14CC2 106/H 9 21VU PITCH TRIM 2/26VAC 15CC2 106/H11

R **ON A/C 105-999,

(1)Open, safety and tag the following circuit breakers: ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 21VU RADIO-NAV & COM/HF1/28VDC 3RE1 103/L10 21VU RADIO-NAV & COM/HF1/115VAC 4RE1 103/L12 21VU RADIO-NAV & COM/HF2/28VDC 3RE2 101/N10 21VU RADIO-NAV & COM/HF2/115VAC 4RE2 101/N12 21VU PITCH TRIM 1/PWR SUPPLY 28VDC 13CC1 106/H 2 21VU PITCH TRIM 1/PWR SUPPLY 115VAC 14CC1 106/H 4 21VU PITCH TRIM 1/26VAC 15CC1 106/H 6 21VU PITCH TRIM 2/PWR SUPPLY 28VDC 13CC2 106/H 7 21VU PITCH TRIM 2/PWR SUPPLY 115VAC 14CC2 106/H 9 21VU PITCH TRIM 2/26VAC 15CC2 106/H11


**ON A/C 102-104,

(1)Open, safety and tag the following circuit breakers: ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 21VU RADIO-NAV & COM/HF1/28VDC 3RE1 103/L10 21VU RADIO-NAV & COM/HF1/115VAC 4RE1 103/L12 21VU PITCH TRIM 1/PWR SUPPLY 28VDC 13CC1 106/H 2 21VU PITCH TRIM 1/PWR SUPPLY 115VAC 14CC1 106/H 4 21VU PITCH TRIM 1/26VAC 15CC1 106/H 6 21VU PITCH TRIM 2/PWR SUPPLY 28VDC 13CC2 106/H 7 21VU PITCH TRIM 2/PWR SUPPLY 115VAC 14CC2 106/H 9 21VU PITCH TRIM 2/26VAC 15CC2 106/H11

**ON A/C 101-102,

After SB 23-085 For A/C 101-101,

(1)Open, safety and tag the following circuit breakers: -------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION -------------------------------------------------------------------------------- 21VU RADIO-NAV & COM/HF1/28VDC 3RE1 103/L10 21VU RADIO-NAV & COM/HF1/115VAC 4RE1 103/L12 21VU RADIO-NAV & COM/HF2/28VDC 3RE2 101/N10 21VU RADIO-NAV & COM/HF2/115VAC 4RE2 101/N12 21VU PITCH TRIM 1/PWR SUPPLY 28VDC 13CC1 106/H 2 21VU PITCH TRIM 1/PWR SUPPLY 115VAC 14CC1 106/H 4 21VU PITCH TRIM 1/26VAC 15CC1 106/H 6 21VU PITCH TRIM 2/PWR SUPPLY 28VDC 13CC2 106/H 7 21VU PITCH TRIM 2/PWR SUPPLY 115VAC 14CC2 106/H 9 21VU PITCH TRIM 2/26VAC 15CC2 106/H11

**ON A/C ALL

(2)Place warning notices on rudder and elevator controls in flight compartment. (3)Position access platform, open access door 312AR. (4)Position stepladder if required, open access door 311AZ.

B. Removal

**ON A/C 001-102,

(Ref. Fig. 401 )


Single HF Antenna Tuner Figure 401


R **ON A/C 105-999,

(Ref. Fig. 402 ) NOTE : Since removal/installation of double HF system tuner is similar ____ to single HF system tuner, only one will be described.

**ON A/C 101-101,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 403 ) NOTE : Since removal/installation of double HF system tuner is similar ____ to single HF system tuner, only one will be described.

**ON A/C ALL

(1)Disconnect electrical connectors (2) from antenna tuner. (2)Cap electrical connectors. (3)Loosen hold-down fastener (4) at mount by turning knurled nuts (3) counterclockwise. (4)Hold antenna tuner (1) in position and open hold-down fastener (4). (5)Carefully withdraw antenna tuner (1) from mount.

C. Installation (1)Carefully slide antenna tuner (1) into mount and hold in position. NOTE : Check that connection of HF antenna feeder fits correctly. ____ (2)Close hold-down fastener (4) at mount. (3)Turn knurled nuts (3) of hold-down fastener (4) clockwise, until antenna tuner is secured firmly. (4)Remove caps from electrical connectors. (5)Connect electrical connectors (2) to antenna tuner (1).

D. Test (1)Test high frequency system (Ref. 23-11-00, P. Block 501).

E. Close-Up (1)Close access doors 311AZ and 312AR. (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (3)Remove warning notices from flight compartment.


Double HF Antenna Tuner Figure 402


Double HF Antenna Tuner Figure 403

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VERY HIGH AND ULTRA HIGH FREQUENCY (VHF/UHF) - DESCRIPTION AND OPERATION ________________________________________________________________________

1. General _______ This part of the communication systems comprises the SELECTIVE CALLING (SELCAL) system and the two VERY HIGH FREQUENCY (VHF) installations.

2. Functional Description ______________________

**ON A/C 101-108,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 001 )

**ON A/C 101-101, 103-999,

After SB 23-085 For A/C 101-101,

A. VHF System (Ref. 23-21-00) The aircraft is equipped with two identical VHF installations, which are independent of each other. The system provides a means of communication between the aircraft and ground stations or with other aircraft in flight.

B. SELCAL System (Ref. 23-22-00)

**ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(1)The aircraft is equipped with a two-channel SELCAL system. Connection with the first channel can be switched either to the VHF1 receiver or to the HF1 receiver. Connection with the second channel can be switched either to the VHF2 receiver or to HF2 receiver.

**ON A/C 101-101, 103-999,

After SB 23-085 For A/C 101-101,

(2)The SELCAL system makes it unnecessary for the crew to listen in constantly to the ground station transmissions intended for the various aircraft in flight at the same time. A particular code is pre-assigned to each aircraft. The ground operator transmits signals in the code assigned to the


VHF/UHF - Block Diagram Figure 001


aircraft he wishes to call. The SELCAL system triggers visual and aural warnings in the aircraft when the ground station transmitting code corresponds to the aircraft code. The crew then know that the ground transmission is for them.

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VERY HIGH AND ULTRA HIGH FREQUENCY (VHF/UHF) - DESCRIPTION AND OPERATION ________________________________________________________________________

1. General _______

This part of the communication systems comprises the SELECTIVE CALLING (SELCAL) system and the two VERY HIGH FREQUENCY (VHF) installations.

2. Functional Description (Ref. Fig. 001 ) ______________________

A. VHF System (Ref. 23-21-00) The aircraft is equipped with two identical VHF installations, which are independent of each other. The system provides a means of communication between the aircraft and ground stations or with other aircraft in flight.

B. SELCAL System There is a full provision for the SELCAL system ; the components (decoder and control unit) are not installed.


VHF/UHF - Block Diagram Figure 001


VHF SYSTEM - DESCRIPTION AND OPERATION ______________________________________

1. General _______ The VHF (Very High Frequency system) serves for communications between ground radio stations and the crew, and also between different aircraft. The aircraft is equipped with two identical VHF systems which are independent of each other (A full provision is installed for installation of a third VHF system).

2. Component Location __________________

R

(Ref. Fig. 001 )

R

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RC1 Transceiver - VHF1 (Ref. 23-21-33) 96VU 122 121BL 1RC2 Transceiver - VHF2 (Ref. 23-21-33) 85VU 121 121BL 2RC1 Control Unit - VHF COM 1 11VU 210 (Ref. 23-21-13) 2RC2 Control Unit - VHF COM 2 11VU 210 (Ref. 23-21-13) 3RC1 Antenna - VHF1 (Ref. 23-21-11) 233 3RC2 Antenna - VHF2 (Ref. 23-21-41) 153 4RC1 Circuit Breaker - VHF/COM/1 22VU 212 4RC2 Circuit Breaker - VHF/COM/2 21VU 211

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Component Location Figure 001


3. Description ___________

**ON A/C 105-106, 109-999,

(Ref. Fig. 002 )

VHF - Block Diagram Figure 002

**ON A/C 001-104, 107-108,

(Ref. Fig. 003 )

R **ON A/C ALL

A. VHF1 system consists of :


**ON A/C 001-104, 107-108,

VHF - Block Diagram Figure 003

(1)One VHF1 antenna 3RC1 - which transmits VHF signals received to VHF1 transceiver 1RC1, - which radiates VHF signals from VHF1 transceiver 1RC1

**ON A/C 105-106, 109-999,

(2)One VHF COM 1 control unit 2RC1 - which transmits frequency selection data to VHF1 transceiver 1RC1

**ON A/C 001-104, 107-108,

(2)One VHF COM 1 control unit 2RC1 - which transmits frequency selection and squelch control signals to VHF1 transceiver 1RC1.

R **ON A/C ALL

(3)One VHF1 transceiver 1RC1 - which transmits audio frequency signals to interphone and Selcal


systems, - which receives audio frequency signals from the interphone system and transmit signals (PTT signals), (4)One VHF/COM/1 circuit breaker 4RC1 - which supplies VHF1 system with 28VDC power

B. VHF2 system is strictly identical with VHF1 system and consists of : (1)One VHF2 antenna 3RC2 (2)One VHF COM 2 control unit 2RC2 (3)One VHF2 transceiver 1RC2 (4)One VHF-COM/2 circuit breaker 4RC2


4. Component Description _____________________

R

A. VHF Transceiver (1)Description (Ref. Fig. 004 )

VHF Transceiver Figure 004

(a)Physical characteristics The face carries : - one SQUELCH DISABLE push-button to inhibit the squelch function - one TRANSMIT POWER indicator light which comes on when the transceiver operates correctly in transmit mode - one MIC jack for direct emission cat the station through a hand microphone - one PHONE jack for direct reception at the station through a headset - one fold-down handle to carry the transceiver All connections to the aircraft electrical network are made through two connectors located on the back of the transceiver.

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R

(b)Electrical characteristics The VHF transceiver which is fully transistorized operates in the 118 to 135.975 MHz frequency range with 25 KHz spacing. The transceiver does not include mechanical devices. It is supplied with 28VDC power. Its power consumption is 1A in reception and 7A in transmission. Its transmission power is 20 Watts with an impedance of 52 ohms.

R

(2)Operation (Ref. Fig. 005 ) (a)Receive mode The receiver is of the superheterodyne type provided with single frequency change. The VHF signals are received by the antenna and applied to the band preselector stage via the antenna switching relay ; this stage is continually tuned by a tuning voltage from the synthesizer. Frequency selection data from the control unit are applied to the synthesizer in the 2-out-of-5 code. From these data, the synthesizer derives a frequency, 20 MHz above the frequency selected on the control unit, which is applied to the first mixer. The first mixer processes the difference between the VHF signal and the frequency issued from the synthesizer. The resulting 20 MHz frequency is amplified and detected. The audio frequency signal is sent to the squelch and audio frequency amplifier circuits which direct it to the aircraft audio frequency reception system. The receiver is supplied with 28VDC power and is provided with one SELCAL output and one AGC circuit. (b)Transmit mode When fed with PTT signal from aircraft PTT switch, the synthesizer derives the same frequency as that selected on the control unit. This signal is amplified and directed to the driver stage which also receives audio frequency modulations from the modulator. The modulated VHF signal is amplified until the transmission power available is 20 Watts at least. The signal is then fed to the antenna switching circuit which, when receiving PTT signal, directs it to the antenna. Part of the modulated VHF signal is detected and directed to audio frequency amplifier and to the aircraft AF reception system for sidetone check. The transmission power available is monitored by TRANSMIT POWER indicator light which comes on on transceiver face when power exceeds 10 Watts.

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VHF Transceiver - Block Diagram Figure 005

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R **ON A/C 105-106, 109-999,

B. VHF-COM Control Unit (1)The VHF-COM control unit face carries : (Ref. Fig. 006 )

VHF-COM Control Unit Figure 006

(a)A dual frequency selection system, each including : 1 One 5-digit frequency display counter. _ 2 One green indicator light to show which display counter is used. _ 3 One double frequency selector knob _ - the outer knob for selection of units and tens of MHz. - the inner knob for selection of hundredths and tenths of MHz. The VHF COM control unit permits selection of frequencies in a 118 to 135.975 MHz frequency range with 25 KHz (and also 50 KHz) spacing. VHF frequencies are selected according to a 2 out-of-5 code, which uses five wires for each digit making up the operating frequency. The frequency is selected by connecting to ground two of the five


wires of each group corresponding to one digit. (b)One TFR switch The VHF COM control unit allows to display two distinct VHF frequencies. The operating frequency is selected by means of the TFR switch located between the two numerical counters. Placing the switch to the right (or to the left) causes - connection of the frequency selection common to the RH (LH) mechanism - supply of 28VDC power to the RH (LH) green indicator light. (2)The VHF COM control unit is connected to the aircraft electrical network by means of one electrical connector located on the back.


**ON A/C 102-102,

B. VHF COM Control Unit (1)The VHF COM control unit face carries : (Ref. Fig. 007 )

VHF COM Control Unit Figure 007

(a)A dual frequency selection system, each including : 1 One 5-digit frequency display counter. _ 2 One double frequency selector knob : _ - the outer knob for selection of units and tens of MHz - the inner knob for selection of hundredths and tenths of MHz. The VHF COM control unit permits selection of frequencies in a 108.00 to 135.975 MHz frequency range with 25 KHz (and also 50 KHz) spacing. VHF frequencies are selected according to a 2-out-of-5 code which uses five wires for each digit making up the operating frequency. The frequency is selected by connecting to ground two of the five wires of each group corresponding to one digit.


(b)One TFR switch The VHF COM control unit allows to display two distinct VHF frequencies The operating frequency is selected by means of the TFR switch located between the two numerical counters. Placing TFR switch to the right (or to the left) causes connection of the frequency selection common to the RH (LH) mechanism and appearance of a horizontal bar on the LH (RH) numerical counter. (c)One SQ DISABLE switch - which inhibits the squelch function when placed in DISABLE position. (2)The VHF COM control unit is connected to the aircraft electrical network by means of one electrical connector on the back.


**ON A/C 001-101,

B. VHF-COM Control Unit (1)The VHF-COM control unit face carries : (Ref. Fig. 008 )


(a)A dual VHF, COM frequency selection system, each including : 1 One 5-drum frequency display counter. _ 2 One double frequency selector knob _ - the outer knob for selection of units and tens of MHz. - the inner knob for selection of hundredths and tenths of MHz. The VHF COM control unit permits selection of frequencies in a 108.00 to 135.975 MHz frequency range with 25 KHz (and also 50 KHz) spacing. VHF frequencies are selected according to a 2 out-of-5 code which uses five wires for each digit making up the operating frequency. The frequency is selected by connecting to ground two of the five wires of each group corresponding to one digit.


(b)One TFR switch The VHF COM control unit allows to display two distinct VHF frequencies The operating frequency is selected by means of the TFR switch located between the two numerical counters. Placing TFR switch to the right (or to the left) causes connection of the frequency selection common to the RH (LH) mechanism and appearance of a horizontal bar on the LH (RH) numerical counter. (c)One SQL/OFF disable switch - which OFF disable inhibits the squelch function when placed in OFF position. (2)The VHF COM control unit is connected to the aircraft electrical network by means of one electrical connector located on the back.


R **ON A/C 107-107,

B. VHF-COM Control Unit (Ref. Fig. 009 )


(1)The VHF-COM control unit face carries : (a)A dual VHF-COM frequency selection system, each including : 1 One 5-drum frequency display counter _ 2 One double VHF frequency selector knob _ - the outer knob for selection of units and tens of MHz - the inner knob for selection of hundredths and tenths of MHz. The VHF-COM control unit permits selection of frequencies in a 116.00 to 151.975 MHz frequency range with 25 KHz spacing. VHF frequencies are selected according to a 2 out-of-5 code which uses five wires for each digit making up the operating frequency. The frequency is selected by connecting to ground two of the five wires of each group corresponding to one digit.


(b)One TFR switch The VHF-COM control unit allows to display two distinct VHF frequencies ; the operating frequency is selected by means of the TFR switch located between the two counters. (c)One COM/TEST pushbutton for starting up the built-in VHF system - which allows to close the test circuit in the VHF-COM control unit. (d)One ON/OFF switch - which closes the supply circuit in the VHF-COM control unit - which connects display counter lighting circuit. (2)The VHF-COM control unit is connected to the aircraft electrical network by means of one electrical connector on the back.


**ON A/C 103-104,

B. VHF-COM Control Unit (1)The VHF-COM control unit face carries (Ref. Fig. 010 )


(a)A dual frequency selection system, each including: 1 One 5-digit frequency display counter. _ 2 One green indicator light to show which display counter is used. _ 3 One double frequency selector knob _ - the outer knob for selection of units and tenths of MHz. - the inner knob for selection of hundredths and tenths of MHz. The VHF COM control unit permits selection of frequencies in a 116 to 151.975 MHz frequency range with 25KHz spacing. VHF frequencies are selected according to a 2 out-of-5 code, which uses five wires for each digit making up the operating frequency. The frequency is selected by connecting to ground two of the five wires of each group corresponding to one digit. (b)One TFR switch


The VHF COM control unit allows to display two distinct VHF frequencies The operating frequency is selected by means of the TFR switch located between the two numerical counters. Placing the switch to the right (or to the left) causes - connection of the frequency selection common to the RH (LH) mechanism - supply of 28VDC power to the RH (LH) green indicator light. (c)One SQ DISABLE switch which allows the squelch function to be inhibited when placed in DISABLE position. (2)The VHF COM control unit is connected to the aircraft electrical network by means of one electrical connector located on the back.


R **ON A/C ALL

C. VHF Antenna (1)Description (Ref. Fig. 011 )

VHF Antenna Figure 011

The VHF antenna is a blade antenna. The forward part has a metal leading edge which protects it against erosion and increases lightning protection. The rear part is made of fiberglass. It also includes a heating system (not used on aircraft). The antenna is connected to the coaxial cable leading to the transceiver by a C-type connector. The coaxial connector is located at the lower rear part of the antenna and is isolated by a moisture barrier. The VHF antenna is attached to the fuselage by screws. (2)Operation The VHF antenna is an omni-directionalantenna, designed to allow transmission and reception of VHF signals over the 116 to 156 MHz range


in vertical polarization. It has a transmission and reception efficiency of approximately 90%. Its impedance is 50 ohms and its standing-wave ratio 2.


5. Operation _________

**ON A/C 105-106, 109-999,

(Ref. Fig. 012 )

**ON A/C 001-102, 107-108,

(Ref. Fig. 013 )

R **ON A/C 001-102, 105-999,

A. General The two VHF systems are identical and independent of each other, component interconnection and operation principles are identical.

B. Frequency Selection VHF frequencies are selected form the VHF COM control unit which transmits frequency data to the VHF transceiver in the form of a 2-out-of-5 code. Two different frequencies can be displayed, which are switched to operate via the TFR transfer switch. One frequency is operational (that selected by the TFR switch) the other frequency is in standby.

R **ON A/C ALL

C. Job Set-Up The VHF1 and VHF2 systems are operated as soon as they are supplied with power, when closing circuit breakers. The VHF1 system is supplied with 28VDC power through circuit breaker 4RC1. The VHF2 system is supplied with 28VDC power through circuit breaker 4RC2.

R

D. Reception The VHF systems when de-energized are in receive mode. VHF communications can be received by connecting a headset at one radio station in the aircraft and selecting VHF1 (VHF2) reception on the relevant audio selector panel. The audio level can be adjusted by the corresponding potentiometer. The VHF signals received by the antenna are applied to the transceiver which detects the modulation : - Selcal modulation is transmitted to the aircraft Selcal system - voice modulation is transmitted to the aircraft interphone system

E. Transmission The VHF system receives from the interphone system : - the voice modulation fed to the VHF transceiver.


VHF System - Interconnection Schematic Figure 012


VHF System - Interconnection Schematic Figure 013


This modulation is available by connecting a hand microphone at one radio station in the aircraft and selecting VHF1 (VHF2) transmission on the relevant audio selector panel - the transmit control (PTT signal) fed to the VHF transceiver and to the aircraft Selcal and Flight recorder systems through operation of PTT switch at one of the various audio selector panels. The VHF transceiver derives a modulated VHF carrier which is transmitted to the aircraft interphone system (in receive mode) after it has been detected and to the VHF antenna which radiates the modulated carrier.

**ON A/C 001-102, 107-108,

F. Squelch Adjustment on the VHF-COM Control Unit The SQ/OFF switch allows to inhibit the squelch function when placed in OFF position.


VHF SYSTEM - FAULT ISOLATION ____________________________

Refer to FI/MM 23-21-00, P. Block 101.


VHF SYSTEM - ADJUSTMENT/TEST ____________________________


A. Reason for the Job (1)To check briefly that aircraft VHF system operates correctly.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200V, 400Hz, 90KVA Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Procedure WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THAT ELEC- _______ ________________________________________ TRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED. NOTE 1 : The aircraft should preferably be placed outside. ______ NOTE 2 : The following adjustment/test procedure is for VHF1 system. ______ Procedure for VHF2 system is identical, the electrical identifiers being shown in parentheses. (1)Job set-up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward services ventilation operates (Ref. 21-20-00, P. Block 301). (c)On overhead panel 29VU - make certain that RADIO MASTER SUPPLY switches 27PN, 43XC and 26PN are respectively in SYS1, ESS SYS and SYS2 positions. (d)At CaptainSs station - perform operations to enable reception and transmission of VHF1 (VHF2). (e)Make certain that the following circuit breakers are closed ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU For VHF1 System VHF/COM/1 4RC1 213/A10 21VU For VHF2 System VHF/COM/2 4RC2 101/N 5 22VU CONTRL PNL/1st OBSV AND AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11 22VU INTPH AMPLI/FLT 19RL 209/E 9 22VU CONTRL PNL/FLT ENGR 50RL 209/E12 (2)Tests (a)Reception test


------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------

**ON A/C 103-106, 109-999,

1. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - select in LH window the fre- - green indicator light located quency of a transmitting above the LH window comes on station by means of the At CaptainSs station frequency selector knobs - selected transmission is received. - select in RH window the frequency of another transmitting station - place TFR switch to LH window.

**ON A/C 001-102, 107-108,

1. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - select in LH window the fre- - a horizontal bar comes into view quency of a transmitting in RH window station by means of the At CaptainSs station frequency selector knobs - selected transmission is received. - select in RH window the frequency of another transmitting station - place TFR switch to LH window.

R **ON A/C ALL

2. At CaptainSs station - adjust VHF1 (VHF2) reception - it should operate progressively volume potentiometer to desired without causing any crackling. level.

**ON A/C 103-106, 109-999,

3. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - place TFR switch to RH - green indicator light located window. above the RH window comes on while the other indicator light goes off.

**ON A/C 001-102, 107-108,

3. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2)


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - place TFR switch to RH - a horizontal bar comes into view window. on LH window only.

R **ON A/C ALL

4. At CaptainSs station - check that the received station is changed.

**ON A/C 103-106, 109-999,

(b)Not applicable.

**ON A/C 001-104, 107-108,

(b)Disabling of squelch circuit ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On control unit VHF COM1 2RC1 At CaptainSs station (VHF COM2 2RC2) - background noise is amplified - place SQ DISABLE switch in at the headset. DISABLE position - place it in SQ position.

R **ON A/C ALL

(c)Transmission test CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED FREQUENCY _______ IS FREE AND OBSERVE RADIO REGULATIONS. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On control unit VHF COM1 2RC1 (VHF COM2 2RC2) - select a frequency (in RH window)

2. At CaptainSs station At CaptainSs station - transmit a message. - the message is integrally received at the headset.

(3)Close-up


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(a)Not applicable

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(b)At CaptainSs station - perform operation to cancel VHF1 (VHF2) transmission - perform operations to enable interphone transmission. (c)De-energize the aircraft electrical network and disconnect electrical ground power unit (d)Remove all ground handling and maintenance equipment, standard and special tools together with ground power equipment, all access equipment and miscellaneous items.


2. Functional Test _______________ Refer to Operational Test - Identical

3. System Test ___________

A. Reason for the Job To check aircraft VHF system for correct operation.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200V, 400Hz, 90KVA (2) 150 ohms Hand Microphone (High Level) (3) 600 ohms Headset (4) Circuit Breaker Safety Clips (5) Directional VHF Wattmeter (6)99A23201000000 Wiring Connecting Case Referenced Procedures - 21-20-00, P. Block 301 Distribution - Extraction - 24-41-00, P. Block 301 External Power - 31-31-15, P. Block 301 FDAU Removal/Installation

C. Procedure WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THAT ELEC- _______ ________________________________________ TRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED. NOTE 1 : The aircraft should preferably be placed outside. ______ NOTE 2 : The following adjustment/test procedure is for VHF1 system. ______ Procedure for VHF2 system is identical, the electrical identifiers being shown in parentheses. (1)Job set-up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward services ventilation operates (Ref. 21-20-00, P. Block 301). (c)On overhead panel 29VU - make certain that RADIO MASTER SUPPLY switches 27PN, 43XC and 26PN are respectively placed in SYS1, ESS SYS and SYS2 positions. (d)At each station (CaptainSs, First OfficerSs, Flight EngineerSs, First and Second ObserverSs and avionics compartment) - perform operations to enable reception and transmission of VHF1 (VHF2). (e)Make certain that the following circuit breakers are closed ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU For VHF1 System VHF/COM/1 4RC1 213/A10 21VU For VHF2 System VHF/COM/2 4RC2 101/N 5 22VU CONTRL PNL/1ST OBSV AND AVIONICS 16RL 209/E 7 22VU CONTRL PNL/F/O 17RL 209/E 8 22VU CONTRL PNL/CAPT 18RL 209/E11


------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU INTPH AMPLI/FLT 19RL 209/E 9 22VU CONTRL PNL/FLT ENGR 50RL 209/E12 (2)Tests (a)Reception test ------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------

**ON A/C 103-106, 109-999,

1. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - select in LH window the fre- - green indicator light located quency of a transmitting above the LH window comes on station by means of the At each station frequency selector knobs - selected transmission is received. - select in RH window the frequency of another transmitting station - place TFR switch to LH window.

**ON A/C 001-102, 107-108,

1. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - select in LH window the fre- - a horizontal bar comes into view quency of a transmitting in RH window station by means of the At each station frequency selector knobs - selected transmission is received. - select in RH window the frequency of another transmitting station - place TFR switch to LH window.

R **ON A/C ALL

2. At each station - adjust VHF1 (VHF2) reception - it should operate progressively volume potentiometer to desired without causing any crackling. level.

**ON A/C 103-106, 109-999,

3. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - place TFR switch to RH - green indicator light located window. above the RH window comes on while


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- the other indicator light goes off.

**ON A/C 001-102, 107-108,

3. On control unit VHF COM1 2RC1 On control unit VHF COM1 2RC1 (VHF COM2 2RC2) (VHF COM2 2RC2) - place TFR switch to RH - a horizontal bar comes into view window. on LH window only.

R **ON A/C ALL

4. At each station - check that the received station is changed.

**ON A/C 103-106, 109-999,

(b)Not applicable.

**ON A/C 001-104, 107-108,

(b)Disabling of squelch circuit ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On control unit VHF COM1 2RC1 At CaptainSs station (VHF COM2 2RC2) - background noise is amplified - place SQ DISABLE switch in at the headset. DISABLE position - place it in SQ position.

R **ON A/C ALL

(c)Transmission test CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED FREQUENCY _______ IS FREE AND OBSERVE RADIO REGULATIONS. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On control unit VHF COM1 2RC1 (VHF COM2 2RC2) - select a frequency (in RH window)


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 2. At each station At each station - transmit a message. - the message is integrally received at the headset.

(d)Check connection with flight data recorder 1 Open, safety and tag the following circuit breakers _ ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU RECORDERS/PWR/SUPPLY/115VAC 7TU 110/D 3 22VU RECORDERS/FLT PWR/SUPPLY 12TU 210/D10 2 On electronics rack 90VU, on shelf 94VU (Ref. 31-31-15, P. Block 401) _ - remove flight data acquisition unit 2TU ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel in On shelf 94VU avionics compartment - check continuity between terminal - press and hold VHF1 (VHF2) 5TU BA/25 (5TU BB/22) and the transmission PTT switch ground. - release PTT switch. - no continuity.

3 On shelf 94VU (Ref. 31-31-15, P. Block 401) _ - install flight data acquisition unit 2TU. 4 Remove safety clips and tags and close circuit breakers 7TU and 12TU _ (e)Measure standing wave ratio (SWR) 1 On shelf 96VU (85VU) _ - interpose a directional VHF wattmeter between shelf output and VHF1 (VHF2) antenna feeder - check and note reflected and transmitted power for the three following frequencies : 118Mhz, 127Mhz and 136Mhz - check that the SWR is below 2 (f)Check frequency automatic display CAUTION : BEFORE TRANSMITTING, MAKE CERTAIN THAT THE SELECTED FREQUENCY _______ IS FREE AND OBSERVE RADIO REGULATIONS.

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1 Establish a VHF communication with a ground radio station using VHF1 _ (VHF2) system for each of the following frequencies : 118.00 Mhz, 120.10 Mhz, 122.35 Mhz, 124.20 Mhz, 126.30 Mhz, 127.80 Mhz, 129.90 Mhz, 131.40 Mhz, 133.50 Mhz, 135.40 Mhz, 135.70 Mhz.

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(3)Close-up


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(a)Not applicable

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(b)At CaptainSs station - perform operation to disable VHF1 (VHF2) transmission - perform operations to enable interphone transmission. (c)De-energize the aircraft electrical network and disconnect electrical ground power unit (d)Remove all ground handling and maintenance equipment, standard and special tools together with ground power equipment, all access equipment and miscellaneous items.


ANTENNAS - VHF COM - REMOVAL/INSTALLATION _________________________________________

NOTE : The text includes the removal/installation procedure for VHF COM No. 1, ____ VHF COM No. 2 and, where fitted, VHF COM No. 3. Unless otherwise stated, an instruction applies to all antenna installations. WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THAT THE _______ ELECTRICAL CIRCUITS, UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED. WARNING : METHYLETHYLKETONE (MAT. NO. 11-003) IS DANGEROUS. AVOID INHALING _______ FUMES. USE IN WELL VENTILATED AREA ONLY. METHYLETHYLKETONE (MAT. NO. 11-003) IS A SKIN IRRITANT. WEAR PROTEC- TIVE GLOVES OR USE A BARRIER CREAM. WASH IMMEDIATELY WITH CLEAN WATER IF SKIN IS SPLASHED WITH SOLVENT.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platforms, 8 m (26 ft. 3 in.) and/or 2 m (6 ft. 6 in.)R B. Material No. 09-019 Sealant (Ref. 20-31-00) C. Material No. 11-003 Cleaning Agent (Ref. 20-31-00) D. Material No. 05-013 Separating Agent (Ref. 20-31-00) E. Blanking Cap and Plug F. Torque Wrench, 0.40/050 m.daN (35/44 lbf.in.) Referenced Procedure - 23-21-00 P. Block 501 VHF System

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A. Job Set-Up (1)Open, safety and tag the following circuit breakers: ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 22VU VHF COM 1 4RC1 213/A10 21VU VHF COM 2 4RC2 101/N 5

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: ALL K 23-21-11 K K K KR Page 402 K K JAS Oct 01/88

(2)Position access platform.

B. Removal (Ref. Fig. 401 ) (1)Remove screws (1 and where fitted 9) from VHF antenna (2). (2)Lift/Lower VHF antenna (2) from fuselage until coaxial cable connector (3) is visible. (3)Bottom-mounted antennas only, release clamp (4) and loosen cover (5) from coaxial cable connector (3). (4)Disconnect coaxial cable connector (3) from VHF antenna connector (6). (5)Top-mounted antennas only, secure coaxial cable connector (3) to prevent it falling into fuselage. (6)VHF antenna 1 installation only, retain adaptor plate (10) in position on fuselage. (7)Fit blanking cap and plug to VHF antenna connector (6) and coaxial cable connector (3). WARNING : METHYLETHYLKETONE (MAT. NO. 11-003) IS DANGEROUS. _______ (8)VHF antennas 2 and 3 installation only, remove old sealant from fuselage using cleaning agent (Mat. No. 11-003).

C. Preparation of Replacement Component (1)For installation of VHF antennas, apply separating agent (Mat. No. 05-013) to bottom surface of antenna (2). (2)Install blanking plug, supplied with antenna, in base air input (7). (3)Ensure correct installation of antenna SOS ring (8). (4)Antenna mounting screws and holes in antenna provide electrical bonding, between antenna and fuselage. Ensure screws and holes are clean.

D. Installation (Ref. Fig. 401 ) NOTE : Ensure that the four longer screws (9) securing the bottom mounted ____ antenna are fitted in the correct positions. (1)For installation of VHF antennas, apply sealant (Mat. No. 09-019) to mounting surfaces of VHF antenna (2) and fuselage. (2)Remove blanking cap and plug from coaxial cable connector(3) and VHF antenna connector (6). (3)Release coaxial cable (3), if previously secured, and connect to VHF antenna connector (6). (4)Bottom mounted antenna only, replace cover (5) and secure with clamp (4). (5)VHF antennas 2 and 3 installation only, install antenna to fuselage with screws (1 and where fitted 9). (6)VHF antenna 1 installation only, ensure adaptor plate (10) is in position, install antenna to fuselage with screws (1). (7)Tighten screws, alternating from side to side and TORQUE to 0.40/0.50 m.daN (35/44 lbf.in.). (8)VHF antennas 2 and 3 installation only, remove excess sealant.

(9)Remove safety clips and tags, and close circuit breakers 4RC1 and 4RC2.


ANTENNAS VHF COMR Figure 401

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E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform.

F. Test (1)Test VHF system (Ref. 23-21-00 P. Block 501).


VHF COM 1 (2RC1) AND VHF COM 2 (2RC2) CONTROL UNITS - _____________________________________________________ REMOVAL/INSTALLATION ____________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Plugs/Caps Referenced Procedure - 23-21-00, P. Block 501 VHF System Operational Test

2. Procedure (Ref. Fig. 401 ) _________

A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 129VU INTEGRATE LT/PED & ROOF PNLS 3LF 903/A13 - for VHF COM 1 control unit (2RC1) : 22VU VHF/COM/1 4RC1 213/A10 - for VHF COM 2 control unit (2RC2) : 21VU VHF-COM/2 4RC2 101/N 9

B. Removal (1)Unlock the four dzus fasteners (1). (2)Pull out control unit (2). (3)Disconnect electrical connector (4). (4)Cap electrical connectors (3) and (4). (5)Remove control unit (2).

C. Installation (1)Clean and inspect the area where control unit is to be installed. (2)Uncap electrical connectors (3) and (4) and visually check connector pins. (3)Position control unit (2). (4)Connect electrical connector (4). (5)Install control unit (2) on structure (5). (6)Lock the four dzus fasteners (1).

D. Test (1)For VHF COM 1 control unit (2RC1) - carry out an operational test of VHF 1 system (Ref. 23-21-00, P. Block 501). (2)For VHF COM 2 control unit (2RC2) - carry out an operational test of VHF 2 system (Ref. 23-21-00, P. Block 501).

E. Close-Up


VHF COM Control Unit - Removal/Installation Figure 401


(1)Remove safety clip and tag and close circuit breaker 3LF. (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


VHF 1 (1RC1) AND VHF 2 (1RC2) TRANSCEIVERS - REMOVAL/INSTALLATION _________________________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Caps Referenced Procedure - 23-21-00, P. Block 501 VHF System Operational Test


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ - for VHF 1 transceiver (1RC1) : 22VU VHF/COM/1 4RC1 213/A10 - for VHF 2 transceiver (1RC2) : 21VU VHF-COM/2 4RC2 101/N 9 (2)Open door 121BL to gain access to avionics compartment. (3)Gain access to VHF transceiver to be removed.

B. Removal (1)Loosen nuts (6) until lugs (5) are free. (2)Remove VHF transceiver (3) from rack (8), slowly pulling it out by means of handle (4), in order to disconnect electrical connector (1) and to disengage centering pins (7). (3)Cap connectors (1) and (2). (4)Remove VHF transceiver (3)

C. Installation (1)Clean and inspect the area where VHF transceiver (3) is to be installed on rack (8). (2)Uncap electrical connectors (1) and (2) and visually check connector pins. (3)Position VHF transceiver (3) on rack (8) and slowly push it on rails until it bottoms. (4)Position nuts (6) upwards, engage lugs (5) in clamps and tighten nuts (6)

D. Test (1)For VHF 1 transceiver (1RC1) - carry out an operational test of VHF 1 system (Ref. 23-21-00, P. Block 501). (2)For VHF 2 transceiver (1RC2) - carry out an operational test of VHF 2 system (Ref. 23-21-00, P. Block 501).


VHF Transceiver - Removal/Installation Figure 401


E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close access door 121BL.


After SB 23-085 For A/C 101-101,

SELECTIVE CALLING SYSTEM - DESCRIPTION AND OPERATION ____________________________________________________

1. General _______ SELCAL is an abbreviation of 6Selective Calling6. The SELCAL system allows the ground operator to call a single aircraft among a group on aircraft in flight, without requiring the crew to listen in constantly on the ground station frequency.

2. Component Location __________________ (Ref. Fig. 001 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RW Decoder - SELCAL (Ref.23-22-34) 15VU 211 2RW Control Unit - SELCAL (Ref.23-22-12)11VU 210 3RW Circuit Breaker - SELCAL 21VU 210 5RW Diode 80VU 121 121BL 6RW Diode 80VU 121 121BL 7RW Diode 80VU 121 121BL 8RW Diode 80VU 121 121BL 9RW Diode 80VU 121 121BL 10RW Diode 80VU 121 121BL 11RW Relay 80VU 121 121BL 12RW Relay 80VU 121 121BL 15RW Diode 80VU 121 121BL 16RW Diode 80VU 121 121BL 34RW SELCAL TEST pushbutton 295VU 210


SELCAL System - Component Location Figure 001



R **ON A/C 101-108,

SELCAL System - Block Diagram Figure 002

The SELCAL system is made up of two symmetrical installations, the components being grouped into two symmetrical channels (SELCAL control unit and decoder included). The system comprises :

A. A Control Unit 2RW - which switches SELCAL signals from one of the VHF receivers to the SELCAL decoder. - which transmits the reset signals to the SELCAL decoder. - which displays the SELCAL visual warnings.

B. Switching circuits (1)On SELCAL 1 channel The switching circuit including relay 11RW receives SELCAL signals from VHF1 and HF1 receivers and switching control signals from the control unit, then it transmits the selected signal to SELCAL decoder.


(2)On SELCAL 2 channel The switching circuit including relay 12RW receives SELCAL signals from VFH2 and HF2 receivers and also switching control signals from the control unit, then it transmits the selected signal to SELCAL decoder.

C. A SELCAL decoder 1RW - which transmits the visual warning signals to the control unit - which transmits the aural warning signals to the aircraft master warning system.



A. SELCAL Decoder (1)Description (Ref. Fig. 003 ) The face of the SELCAL decoder presents four coding wheels which serve to select the call code. Each coding wheel has 16 positions (from A to S). Connection to the aircraft electrical network is made by a connector located on the back of the decoder. there is a handle on the face for carrying the unit. (2)Operation (Ref. Fig. 004 ) (a)General The decoder is composed of two identical operating channels. These two channels are physically and electrically independent of each other. Each SELCAL channel is composed of : - an amplifier circuit - a signal codification and detection circuit - a warning distribution circuit. - a self test circuit. (b)Amplifier circuit The signal received by the decoder is applied to the primary of an isolation transformer. The signal obtained on the secondary is sent to a two stage amplifier then a series of active filters enabling selection of the received signal frequencies. (c)Signal codification and detection systems. The call code is selected on the SELCAL decoder by means of four coding wheels, corresponding to a predetermined frequency. When the output signals from the active filters have frequencies which are identical to and in the same order as the preset frequencies, the outputs of four demultiplexers trip. (d)Warning Distribution The demultiplexer output is amplified and the signal obtained is directed to : - a circuit comprising an optoisolator and a relay which energize a continuous warning - a circuit comprising an oscillator which activates a relay via an optoisolator which energizes an intermittant warning. The SELCAL decoder is reset by an internal circuit when a reset push-button is pressed. (e)Self-test circuit When the self-test circuit is energized the call signals corresponding to the preselected code are generated by the SELCAL decoder. These signals are then processed as described above.

B. SELCAL Control Unit (Ref. Fig. 005 ) The face comprises : LH side - a SELCAL 1 section on the left, corresponding to SELCAL 1 channel of the SELCAL decoder, including - an amber warning light - a two-position (VHF1 and HF1) reception selector switch - a center section with a RESET push-button which provides simultaneous resetting of both channels.


SELCAL Decoder Figure 003


SELCAL Decoder - Block Diagram Figure 004


R **ON A/C 101-108,

SELCAL Control Unit Figure 005

- a SELCAL 2 section on the RH side, corresponding to SELCAL 2 channel of the SELCAL decoder, including - an amber warning light - a two-position (VHF2 and HF2) reception selector switch. The SELCAL control unit has integral lighting supplied by 5V power. On the back, a circular connector is provided for electrical connections with the aircraft network.



A. Principle The SELCAL system assigns a particular calling code to each aircraft. All the ground operator has to do is to press on a control unit the four keys corresponding to the code assigned to a particular aircraft. The SELCAL system on the aircraft responds only to that code and eliminates all others. The calling code is identified by a combination of four letters (For example 6AM-BL6) selected from among the twelve available letters 6A6 tp 6M6. Each letter represents a transmitting frequency for the ground station. The four frequencies corresponding to the letters are transmitted by the ground station in two pairs, the pairs being transmitted for 1.0 ±.25 second each and at a .2 ±.1 second interval.

B. Selective Calling Reception Selection (Ref. Fig. 006 ) The system is energized by closing circuit breaker 3RW. The SELCAL decoder consists of two operating channels : - the first receives signals from aircraft VHF1 or HF1 receivers through relay 11RW which is controlled by the VHF1/HF1 selector switch on SELCAL control unit. The relay is energized when VHF1 is selected and de-energized when HF1 is selected. - the second receives signals from the aircraft VHF2 or HF2 receivers through relay 12RW, which is controlled by the VHF2/HF2 selector switch on SELCAL control unit. The relay is energized when VHF2 is selected and de-energized when HF2 is selected. The two SELCAL channels can thus operate simultaneously. SELCAL signal processing Of all the signals applied to both SELCAL channels, only those transmitted in their pre-assigned code will be accepted. The four letter code can be seen on an identification plate located on center pedestal 11VU. When a channel decodes a signal, it energizes an amber warning light on SELCAL control unit through diode 5RW (6RW) and triggers, through diode 15RW (16RW), an intermittent buzzer (1s/1s), which sounds in the warning loudspeakers.

C. Resetting (1)Immediate reply To answer a call received on SELCAL channel 1 or 2, the crew members must operate VHF1, VHF2 or HF PTT switch in order to transmit on the system corresponding to both the amber warning light alluminated and the reception mode selected on the control unit. Operation of the PTT switch connects SELCAL decoder to ground, thereby resulting in an automatic resetting of the decoder and cancellation of the aural and visual warnings. (2)Delayed reply If the pilot is otherwise occupied, possibility is given to him : - to cancel aural and visual warnings by operating the RESET push-button located on the control unit (resetting of both SELCAL channels simul-


SELCAL System - Block Diagram Figure 006


taneously) - to cancel the disturbing aural warning while keeping the visual warning, by pressing the AUDIO CANCEL indicator light/switch located on master warning panel.

D. Tests (1)Warning lights test The dimmable-type amber warning lights on SELCAL control unit can be checked for correct operation by means of the ANNUN LIGHTS filament test push-button on overhead panel 27VU which is common to all aircraft circuits (2)SELCAL test The dimmable-type amber warning lights on SELCAL control unit and the buzzer can be checked for correct operation by means of the SELCAL TEST pushbutton (34RW) on center pedestal (295VU).

E. Power Supply The SELCAL system is supplied with direct current through circuit breaker 3RW and RADIO MASTER SUPPLY switch 27PN located on overhead panel 29VU.


SELECTIVE CALLING SYSTEM - FAULT ISOLATION __________________________________________



After SB 23-085 For A/C 101-101,

SELCAL SYSTEM - ADJUSTMENT/TEST _______________________________


A. Reason for the Job (1)To make certain that SELCAL control unit warning lights operate correctly.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200V, 400Hz, 90KVA Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Procedure WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THAT _______ ELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED. (1)Job set-up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward services ventilation system is in operation (Ref. 21-20-00, P. Block 301). (c)Make certain that the following circuit breaker is closed: ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU RADIO NAV & COM/SELCAL 3RW 101/N 8

(2)Test (a)By means of the SELCAL test system. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On center pedestal (295VU) On SELCAL control unit 2RW - press and release SELCAL TEST - SELCAL 1 and SELCAL 2 amber warning pushbutton (34RW) lights come on In warning loudspeakers 7WK and 8WK - buzzer (1 sec/1 sec) sounds

On SELCAL control unit 2RW - SELCAL 1 and SELCAL 2 amber - press then release RESET warning lights go off pushbutton In warning loudspeakers 7WK and 8WK - buzzer stops


(3)Close-up (a)De-energize the aircraft electrical network and disconnect electrical ground power unit. (b)Remove all ground handling and maintenance equipment, standard and special tools together with ground power and replenishing equipment, all access equipment and miscellaneous items.



A. Reason for the Job (1)Brief check of SELCAL system operation.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase 115/200V, 400Hz, 90KV Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

CAUTION : THIS TEST REQUIRES COMMUNICATION WITH A GROUND SELCAL STATION. IF A _______ SELCAL STATION IS NOT AVAILABLE THIS TEST MUST BE PERFORMED USING THE APPROPRIATE SELCAL TEST EQUIPMENT (VHF AND HF TRANSMITTERS WITH A TONE GENERATOR AND ITS CONTROL BOX).

C. Procedure WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT, MAKE CERTAIN THAT ELEC- _______ ________________________________________ TRICAL CIRCUITS, UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED. NOTE : The aircraft must be outside. ____ (1)Job set-up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward services ventilation system is in operation (Ref. 21-20-00, P. Block 301). (c)On overhead panel 29VU - check that RADIO MASTER SUPPLY switches (27PN, 43XC, 26PN) are in SYS1, ESS SYS and SYS2 positions respectively. (d)On Captain audio selector panel - make certain that transmission and reception in interphone mode are possible. (e)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU ANNUN LT CONTRL/PILOTS &/OVERHEAD PNLS 1LP 113/A 4 22VU VHF/COM/1 4RC1 213/A10 21VU VHF/COM/2 4RC2 101/N 6 21VU HF1/28VDC 3RE1 103/L10 21VU HF2/28VDC 3RE2 101/N10 21VU HF1/115VAC 4RE1 103/L12 21VU HF2/115VAC 4RE2 101/N12 22VU AUDIO SYS/CONTRL/PNL/CAPT 18RL 209/E11 21VU RADIO NAV & COM/SELCAL 3RW 101/N 8 21VU WARNING/AUDIO/PWR/SUPPLY 3WK 111/C 2 21VU WARNING/MASTER/PWR SUPPLY/2 4WW 111/C 5 21VU WARNING/MASTER/PWR SUPPLY/1 15WW 111/C 4 21VU WARNING/MONITOR 16WW 111/C 3


(2)Tests CAUTION : FOLLOW THE RADIO COMMUNICATION PROCEDURES AND BEFORE TRANSMIT- _______ TING, MAKE CERTAIN THAT THE SELECTED FREQUENCY IS FREE. (a)SELCAL VHF1 (VHF2) test 1 On Captain audio selector panel _ - perform operations necessary for VHF1 (VHF2) transmission and VHF1 and VHF2 reception 2 On center pedestal 11VU, on VHF COM control units 2RC1 and 2RC2 _ - place ON/OFF switch in ON position - select SELCAL ground station frequency 3 On center pedestal 11VU, on SELCAL control unit 2RW _ - place SELCAL 1 (SELCAL 2) selector in VHF1 (VHF2) position 4 Reception and reset test _ ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At CaptainSs station - contact a SELCAL ground station using the aircraft VHF1 (VHF2) system - request a SELCAL call on an authorized VHF frequency

2. On VHF1 (VHF2) COM control units 2RC1, (2RC2) - select VHF frequency corresponding to SELCAL call

3. On VHF2 (VHF1) COM control units 2RC2 (2RC1) - select a different VHF frequency of SELCAL CALL

4. On panel 15VU On SELCAL control unit 2RW - select SELCAL ground station - SELCAL 1 (SELCAL 2) amber warning call code on the SELCAL1 (SELCAL2) light comes on channel of SELCAL decoder In warning loudspeakers 7WK and 8WK - buzzer (1 sec/1 sec) sounds

5 Dimming test _ -------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------- 1. On Panel 27VU On SELCAL control unit 2RW - place ANNUN LT switch 6LP in - SELCAL 1 and SELCAL 2 warning DIM position lights dim.

- place ANNUN LT switch 6LP in BRT - SELCAL 1 and SELCAL 2 warning position. lights return to normal intensity.


6 Reset test _ -------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------- 1. On SELCAL control unit 2RW - press then release RESET pushbutton - SELCAL 1 (SELCAL 2) warning light goes off. In warning loudspeakers 7WK and 8WK - buzzer stops

2. At CaptainSs station On SELCAL control unit 2RW - request again a SELCAL call - SELCAL 1 (SELCAL 2) amber warning from the SELCAL ground station light comes on In warning loudspeakers 7WK and and 8WK - buzzer (1 sec/1 sec) sounds

- press then release the PTT - SELCAL 1 (SELCAL 2) warning light switch goes off. In warning loudspeakers 7WK and 8WK - buzzer stops

(b)SELCAL HF1 (HF2) test 1 On Captain audio selector panel _ - switch off VHF1 and VHF2 transmission and reception - perform operations required for HF1 transmission and HF1 and HF2 reception 2 On overhead panel 20VU, on HF1-HF2 dual control unit, 2RE for _ HF1 and HF2 systems - place function selector in AM position - select SELCAL ground station frequency 3 On center pedestal 11VU, on SELCAL control unit 2RW _ - place SELCAL 1 (SELCAL 2) selector in HF1 (HF2) position 4 Reception and reset test _ ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At CaptainSs station - contact a SELCAL ground station using the aircraft HF1 (HF2) system - request a SELCAL call on an authorized HF frequency

2. On H1-HF2 dual control unit 2RE, for HF1 and HF2 systems - select HF1 frequency corresponding to SELCAL call - select a different HF2 frequency of SELCAL call


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 3. On panel 15VU On SELCAL control unit 2RW - select SELCAL ground station - SELCAL 1 (SELCAL 2) amber call code on SELCAL 1 (SELCAL 2) warning light comes on channel of SELCAL decoder 1RW In warning loudspeakers 7WK and 8WK - buzzer (1 sec/1 sec) sounds

4. On SELCAL control unit 2RW On SELCAL control unit 2RW - press then release RESET - SELCAL 1 (SELCAL 2) warning pushbutton light goes off

In warning loudspeakers 7WK and 8WK - buzzer stops

5. At CaptainSs station On SELCAL control unit 2RW - request again a SELCAL call - SELCAL 1 (SELCAL 2) amber from the SELCAL ground station warning light comes on In warning loudspeakers 7WK and 8WK - buzzer sounds. - press then release the PTT - SELCAL 1 (SELCAL 2) amber warning switch light goes off. - In warning loudspeakers 7WK and 8WK - buzzer stops.

(3)Close-up (a)On HF1-HF2 dual control unit 2RE, for HF1 and HF2 systems - place function selector in OFF position (b)On VHF COM control units 2RC1 and 2RC2 - place ON/OFF switch in OFF position (c)On Captain audio selector panel - switch off HF1 transmission and HF1 and HF2 reception. - perform operations required for transmission in interphone mode. (d)De-energize the aircraft electrical network and disconnect electrical ground power unit. (e)Remove all ground handling and maintenance equipment, standard and special tools together with ground power and replenishing equipment, all access equipment and miscellaneous items.


After SB 23-085 For A/C 101-101,

SELCAL CONTROL UNIT (2RW) - REMOVAL/INSTALLATION ________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Caps Referenced Procedure - 23-22-00, P. Block 501 SELCAL VHF Operational Test


A. Job Set-Up (1)Open, safety and tag the following circuit breakers

R **ON A/C 101-101, 103-999,

After SB 23-085 For A/C 101-101,

------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 129VU INTEGRATE LT/PED & ROOF PNLS 3LF 903/A13 21VU RADIO NAV & COM/SELCAL 3RW 101/N 8

R **ON A/C 101-101, 103-999,

After SB 23-085 For A/C 101-101,

B. Removal (1)Unlock the two dzus fasteners (1). (2)Pull control unit (2) outwards. (3)Disconnect electrical connector (4). (4)Blank connector (4) and receptacle (3). (5)Remove control unit (2).

C. Installation (1)Clean and inspect component interface. (2)Remove blanking caps from connector (4) and receptacle (3) and visually check condition of pins. (3)Position control unit (2). (4)Connect electrical connector (4). (5)Push control unit (2) into position on support structure (5).

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 101-101, 103-999, K 23-22-12 K K K K Page 401 K K JAS Jul 01/88

SELCAL Control Unit - Removal/Installation Figure 401


(6)Lock the two dzus fasteners (1).

D. Test Perform SELCAL VHF operational test (Ref. 23-22-00, P. Block 501).

E. Close-Up (1)Remove safety clip and tag and close circuit breaker 3LF. (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


After SB 23-085 For A/C 101-101,

SELCAL DECODER (1RW) - REMOVAL/INSTALLATION ___________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Caps Referenced Procedure - 23-22-00, P. Block 501 SELCAL System


R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(Ref. Fig. 401 )

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

A. Job Set-Up (1)Open, safety and tag the following circuit breakers ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU VHF/COM/1 4RC1 213/A10 21VU VHF/COM/2 4RC2 101/N 9

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

21VU HF1/28VDC 3RE1 103/L10 21VU HF2/28VDC 3RE2 101/N10 21VU HF1/115VAC 4RE1 103/L12 21VU HF2/115VAC 4RE2 101/N12

R **ON A/C 101-999,


------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ After SB 23-085 For A/C 101-101,

21VU RADIO NAV & COM/SELCAL 3RW 101/N 8

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(2)On panel 15VU - open transparent access door.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

B. Removal (1)Slacken thumbscrew (6) to free lug (5). (2)Remove SELCAL decoder (3) from rack (8) by gently pulling handle (4) in order to free connector (7) and locating spigots (1). (3)Blank connectors (2) and (7).

C. Installation (1)Clean and inspect SELCAL decoder (3) and rack (8) interfaces. (2)Remove blanks from connectors (2) and (7) and visually check condition of pins. (3)Position SELCAL decoder (3) on rack (8) and push gently until resistance is met. (4)Position thumbscrew (6) and tighten onto lug (5).

D. Test (1)Perform System Test of SELCAL (Ref. 23-22-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

R **ON A/C 101-999,

After SB 23-085 For A/C 101-101,

(2)Close transparent access door.


SELCAL Decoder - Removal/Installation Figure 401


PASSENGER ADDRESS - DESCRIPTION AND OPERATION _____________________________________________

1. General _______ The passenger address system enables crew members and Cabin Attendants to transmit instructions, announcements and music programs pre-recorded on a tape reproducer.


**ON A/C 001-101, 107-999,

(Ref. Fig. 001 )

**ON A/C 105-106,

(Ref. Fig. 002 )

**ON A/C 001-006,

(Ref. Fig. 003 ) Transformers in Cabin

**ON A/C 007-101, 107-108,

(Ref. Fig. 004 ) Transformers in Cabin

**ON A/C 105-106,

(Ref. Fig. 005 )

**ON A/C 001-101, 105-108,

(Ref. Fig. 006 ) Lavatories

**ON A/C 001-101, 105-999,

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------

1RY Amplifier - Passenger Address 96VU 122 121BL (Ref. 23-31-18) 5RY Circuit Breaker-PUBLIC 22VU 210 ADDRESS 7RY Potentiometer 97VU 122 121BL 8RY Diode 90VU 122 121BL 9RY Potentiometer 97VU 122 121BL 10RY Diode 90VU 122 121BL 11RY Diode 95VU 122 121BL 12RY Relay - Time Delay 95VU 122 121BL


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 13RY Relay 95VU 122 121BL 15RY1 Loudspeaker - Forward Cabin 884VU1220 Attendant Station

**ON A/C 107-999,

15RY2 Loudspeaker - Center Cabin 884VU2230 Attendant Station

**ON A/C 001-101, 105-999,

16RY Loudspeaker - Aft Cabin 811VU 260 Attendant Station

**ON A/C 001-101, 105-108,

74RY Loudspeaker - Aft Lavatory 817VU1261 74RY Loudspeaker - Aft Lavatory 817VU2261

**ON A/C 001-101, 105-999,

79RY Loudspeaker - Forward 819VU 223 Lavatory

80RY Loudspeaker - Aft Lavatory 816VU1262 80RY Loudspeaker - Aft Lavatory 816VU2262 81RY Transformer - Forward 801VU 223 Lavatory Loudspeaker 82RY Transformer - Aft Lavatory 814VU 262 Loudspeaker 83RY Transformer - Aft Lavatory 815VU 261 Loudspeaker 84RY Transformer - Aft Lavatory 812VU 262 Loudspeaker 85RY Transformer - Aft Lavatory 813VU 261 Loudspeaker 86RY Loudspeaker - Lateral (Ref. corresponding figure) 86RY Loudspeaker - Center (Ref. corresponding figure) 87RY Loudspeakers - Lateral (Ref. corresponding figure) 87RY Loudspeakers - Center (Ref. corresponding figure) 88RY Transformers - Lateral Loud-


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ speakers (Ref. corresponding figure) 88RY Transformers - Center Loud- speakers (Ref. corresponding figure) 89RY Transformers - Lateral Loud- speakers (Ref. corresponding figure) 89RY Transformers - Center Loud- speakers (Ref. corresponding figure) 90RY Loudspeaker - Forward 894VU 220 91RY Transformer - Forward 894VU 220 Loudspeaker 93RY Potentiometer 97VU 122 121BL

**ON A/C 001-101, 106-999,

100RY Reproducer - Tape (Ref. 95VU 122 121BL 23-00-00)

**ON A/C 001-101, 107-999,

102RY Control Unit - Tape 877VU 221 Reproducer 103RY Potentiometer 877VU 221 104RY Push-Button - ON 877VU 221

**ON A/C 105-106,

102RY Control Unit - Tape 801VU 221 Reproducer 103RY Potentiometer 746VU 221

**ON A/C 001-101, 105-999,

105RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/115 VAC 106RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/28 VDC 107RY Rectifier Box 95VU 122 121BL 108RY Relay 95VU 122 121BL 109RY Diode 90VU 122 121BL 111RY Relay - Reception Cut-Off 878VU 221 112RY Relay - Passenger Address/ 878VU 221 Interphone Switching 113RY Relay - Reception Cut-Off 890VU 233 114RY Relay - Passenger Address/ 890VU 233 Interphone Switching


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 115RY Relay - Reception Cut-Off 727VU 261 116RY Relay - Passenger Address/ 727VU 261 Interphone Switching 117RY Diode 878VU 221 118RY Diode 890VU 233 119RY Diode 727VU 261 120RY Push-Button - PA 878VU 221 121RY Push-Button - PA 729VU 231 122RY Push-Button - PA 727VU 261

**ON A/C 107-999,

248RY Transformer - Center Lavatory 819VU 230 Loudspeaker

**ON A/C 108-999,

253RY Loudspeaker - Lateral 851VU 230 254RY Loudspeaker - Lateral 852VU 230 255RY Transformer - Lateral Loudspeaker 851VU 320 256RY Transformer - Lateral Loudspeaker 852VU 230

**ON A/C 001-101,

262RY Diode 90VU 122

**ON A/C 001-101, 105-999,

267RY Diode 90VU 122 268RY Diode 90VU 122 269RY Diode 90VU 122

**ON A/C 001-101, 105-108,

277RY Diode 90VU 122 278RY Diode 90VU 122 295RY Diode 726VU 262 296RY Relay - Passenger Address/ 726VU 262 Interphone Switching 297RY Pushbutton - PA 726VU 262 298RY Relay - Reception Cut-Off 726VU 262 303RY Pushbutton - PA 880VU 251 304RY Relay - Reception Cut-Off 880VU 251 305RY Diode 880VU 251 306RY Relay - Passenger Address/ 880VU 251 Interphone Switching 307RY Pushbutton - PA 882VU 252 308RY Relay - Reception Cut-Off 882VU 252 309RY Diode 882VU 252


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 310RY Relay - Passenger Address/ 882VU 252 Interphone Switching 311RY Pushbutton - PA 730VU 232 312RY Diode 890VU 230 313RY Relay - Passenger Address/ 890VU 230 Interphone Switching 314RY Relay - Reception Cut-Off 890VU 230 315RY Diode 890VU 230 316RY Relay - Passenger Address/ 890VU 230 Interphone Switching 317RY Relay - Reception Cut-Off 890VU 230 318RY Pushbutton - PA 784VU 222

**ON A/C 007-101, 106-108,

321RY Diode 90VU 122 121BL

**ON A/C 007-101, 105-108,

322RY Loudspeaker - RH Cabin Attendant, 798VU 250 Aft Passenger/Crew Door 323RY Loudspeaker - LH Cabin Attendant, 799VU 250 Aft Passenger/Crew Door

**ON A/C 001-101,

1005RY Relay - Passenger Address/ 890VU 230 Interphone - Switching

**ON A/C 001-101, 105-108,

1013RY Diode 90VU 122 88RL Telephone Handset 878VU 221 89RL Telephone Handset 882VU 252 90RL Telephone Handset 729VU 231 91RL Telephone Handset 880VU 251 111RL Telephone Handset 726VU 262 112RL Telephone Handset 727VU 261 117RL Telephone Handset 730VU 232 152RL Telephone Handset 784VU 222 305LN Switch - Telephone Handset 878VU 221 306LN Switch - Telephone Handset 730VU 232 307LN Switch - Telephone Handset 729VU 231 308LN Switch - Telephone Handset 882VU 252 309LN Switch - Telephone Handset 880VU 251 310LN Switch - Telephone Handset 726VU 262 311LN Switch - Telephone Handset 727VU 261 723LN Switch - Telephone Handset 784VU 222 320LG Switch - ENTRY LIGHT & 811VU 260


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ SPEAKER OFF

**ON A/C 001-003, 107-999,

88RL Telephone Handset 878VU 221 90RL Telephone Handset 729VU 231 112RL Telephone Handset 727VU 261 305LN Switch - Telephone Handset 878VU 221 307LN Switch - Telephone Handset 729VU 231 311LN Switch - Telephone Handset 727VU 261 320LG Switch - ENTRY LIGHT & 811VU 260 SPEAKER OFF

**ON A/C 001-101, 105-108,

3MK6 Pushbutton - BGM ON/OFF 801VU 221

**ON A/C 001-101, 105-999,

5RK Circuit Breaker - RECORDERS/ 22VU 210 VOICE/CONTRL RELAY 19WR Relay 252VU 122 121BL 42XC Relay 101VU 120 121BL S1-295 Switch - Low Oil Pressure, 435 435AL Eng 1 (Ref. 79-34-11) S1-295 Switch - Low Oil Pressure, 445 445AL Eng 2 (Ref. 79-34-11)


Passenger Address - Component Location in Flight Compartment and Avionics Compartment Figure 001 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-101, 107-999, K 23-31-00 K K CONF. 01 K K Page 7 K K JAS Oct 01/92

INTENTIONALLY BLANK

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ K K 23-31-00 K K CONF. 01 K KR Page 8 K K JAS Oct 01/92

Passenger Address - Component Location in Flight Compartment and Avionics Compartment Figure 002 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 105-106, K 23-31-00 K K CONF. 01 K K Page 9- 10 K K JAS Oct 01/92

Passenger Address - Location of Loudspeakers and Figure 003


Passenger Address - Location of Loudspeakers and Figure 004

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 007-101, 107-108, K 23-31-00 K K CONF. 01 K K Page 13- 14 K K JAS Oct 01/92

Passenger Address - Location of Loudspeakers and Transformers in Cabin Figure 005 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 105-106, K 23-31-00 K K CONF. 01 K K Page 15- 16 K K JAS Oct 01/92

Passenger Address - Location of Loudspeakers in Figure 006



A. The passenger address system consists of : (1)One amplifier 1RY enabling amplification of the audio frequency signals for the cabin loudspeakers and also for Cabin AttendantsS station loudspeakers via impedance matching transformers. (2)One loudspeaker system associated with impedance matching transformers located throughout the cabin. (3)Three loudspeakers located at the main Cabin AttendantsS stations.

**ON A/C 007-101, 105-108,

Two Cabin Attendant loudspeakers located at LH and RH aft passenger/crew doors.

**ON A/C 001-101, 105-999,

(4)One tape reproducer 100RY enabling playback of pre-recorded music and announcement magazines. (5)One tape reproducer control unit 102RY enabling selection, starting and resetting for a pre-recorded announcement.

**ON A/C 001-101, 107-999,

(6)One ON push-button 104RY associated with potentiometer 103RY enabling music starting and volume adjustment.

**ON A/C 105-106,

(6)One ON push-button 3MK6 associated with potentiometer 103RY enabling music starting and volume adjustment.

**ON A/C 001-101, 105-999,

(7)One circuit breaker 5RY supplying amplifier 1RY with 28VDC power. (8)Two circuit breakers 106RY and 105RY supplying the tape reproducer with 28VDC and 115VAC power.


Passenger Address - Block Diagram Figure 007

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 001-101, 105-999, K 23-31-00 K K CONF. 01 K KR Page 19 K K JAS Oct 01/92


A. Passenger Address Amplifier 1RY (Ref. Fig. 008 )

Passenger Address Amplifier Figure 008

(1)The passenger address amplifier consists of : (a)Four input channels, each having a rank of priority. (b)An electronic chime associated with the call circuits. (c)One 60W and one 5W output stages - the 60W output is supplied to the cabin and lavatory loudspeakers via impedance matching transformers. - the 5W output is supplied to the Cabin Attendant station loudspeakers. (d)On the face - a three position NORM-CAL-TEST selector switch . The CAL position is used for testing operation of the amplifier (test of 60 W amplifier output level). . The TEST position feeds a 600 Hz test signal through the amplifier in order to provide an aural check of the loudspeakers.


(e)An electrical connector located at the back of the amplifier for connection to the rest of the system.

B. Cabin and Lavatory Loudspeakers Each loudspeaker is connected to the secondary winding of a transformer which matches the impedance with the 60W amplifier output.

C. Passenger Address Music and Announcement Tape Reproducer 100RY (Ref. Fig. 009 )

Music and Announcement Tape Reproducer Figure 009

(1)On the front panel : (a)a hinged panel, when unlatched, enables to gain access to the four following tape magazines - the three announcement magazines A, B, C. Each announcement magazine includes 8 tracks, each for reproduction of a different announcement with a maximum playtime of 30 minutes. - the background music (BGM) magazine including 4 tracks, each with a maximum of one hour playtime.


The endless loop magnetic tape fitted in each magazine is driven at a 9.5 cm/sec. (3 -3/4 inches/sec.) speed. (b)a five-position rotary selector switch enablesto select the 4 tracks of the BGM magazine, either manually (positions 1, 2, 3, 4) or automatically (position A) from forward Cabin AttendantSs station (PurserSs station). (c)a handle to facilitate transport and installation of the tape reproducer in the mounting tray. (2)An electrical connector at the back of the tape reproducer for connection to the rest of the system.

D. Tape Reproducer Control Unit (Ref. Fig. 010 )

Passenger Address - Tape Reproducer Control Unit Figure 010

Tape reproducer control unit 102RY is located at the forward Cabin AttendantSs station (PurserSs station). An electrical connector at the back of the control unit allows connection to the rest of the system. On the face are the following : (1)Three keys, labelled A, B and C for selection of pre-recorded


announcement magazines. (2)Eight keys numbered from 1 to 8 for selection of the 8 different tracks in each magazine. Selection of one announcement is by means of these eleven keys. Example : for selection of announcement B1, press key B and key 1 which come on. (3)One ANN push-button for broadcasting the announcement selected. (4)One CANCEL push-button for interrupting the announcement in progress. (5)Three yellow status lights indicating the position of the tape in the three magazines. (a)If the status light associated with the selected magazine is off, the selected announcement is ready for immediate playback. (b)If the status light associated with the selected magazine is on, this indicates either one of the following cases : - the tape is winding to the position corresponding to the selected announcement - an announcement is in progress - there is no announcement pre-recorded at this location on the tape. NOTE : Emergency announcement A1 which has a top ____ priority over the other announcements cannot be selected on the control unit. It is automatically triggered in the event of cabin depressurization

E. Background Music Controls

**ON A/C 001-100, 107-999,

(1)ON push-button 104RY

**ON A/C 105-106,

(1)ON push-button 3MK6

**ON A/C 001-101, 105-999,

- When pressed, this push-button comes on and triggers starting of the background music (BGM) tape. - As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement. (2)Potentiometer 103RY This potentiometer enables to adjust the audio level of the music broadcast in the cabin and lavatories.



A. Passenger Address Amplifier 1RY

R **ON A/C 001-101, 105-108,

(Ref. Fig. 011 )

**ON A/C 001-101, 105-999,

(1)Amplification The passenger address amplifier comprises 4 input channels which have been given a rank of priority - priority 1 (corresponding to input 1), assigned to the crew membersS stations, is used from the audio selector panels (PA transmission key pressed). - priority 2 (corresponding to input 2), assigned to the Cabin Atten- dantsS stations. NOTE : input 2A is available but not presently in use on aircraft. ____

R **ON A/C 001-101, 105-108,

- priority 3 (corresponding to input 3), assigned to the pre- recorded music and announcement broadcasting system. - priority 4 (corresponding to input 4), assigned to the passenger entertainment system. The audio frequency (AF) signals from inputs 1, 2, 3 and 4 are applied to the 60W amplifier.

**ON A/C 001-101, 105-999,

The output signal from the 60W amplifier is applied to the cabin and lavatory loudspeakers via impedance matching transformers. Only the AF signal from input 1 is applied to the 5W amplifier. The output signal from the 5W amplifier is applied to the Cabin Attendant stations loudspeakers. (2)Electronic chime An electronic chime incorporated in the amplifier produces three tones : high tone (HI), low tone (LO), and high/low tone (HI/LO). It is controlled by four different channels - channel 1 assigned to Passenger-to-Cabin Attendant calls, producing a high tone (HI) - channel 2 assigned to Captain-to-Cabin Attendant calls, producing a high/low (HI/LO) tone. - channel 3 assigned to FASTEN SEAT BELT sign, producing a low tone (LO). - channel 4 assigned to NO SMOKING sign, producing a low tone (LO). The 60W amplifier receives the three tones through selector gates. The 5W amplifier always receives the three tones independently from the combination of these selector gates. (3)Amplifier 1RY interconnections.


Passenger Address Amplifier - Block Diagram Figure 011


**ON A/C 007-101, 105-108,

(Ref. Fig. 012 )

**ON A/C 001-006,

(Ref. Fig. 013 )

**ON A/C 001-101, 105-999,

(a)Interconnection with the loudspeakers - The output from the 60W amplifier is connected to all primary windings of the parallel-connected transformers of cabin and lavatory loudspeakers. Each loudspeaker is connected to the secondary winding of an impedance matching transformer.

**ON A/C 001-006, 109-999,

- The output from the 5W amplifier is connected to the three parallel-connected loudspeakers at the Cabin AttendantsS stations.

**ON A/C 007-101, 105-108,

- The output from the 5W amplifier is connected to the five parallel- connected loudspeakers at the Cabin AttendantsS stations.

**ON A/C 001-101, 105-999,

(b)Interconnection with crew membersS circuits Engaging PA keys on crew membersS audio selector panels results in feeding the microphone and PTT signals to input 1 of the amplifier via the interphone junction box. The amplifier sidetone output is fed to crew membersS stations reception channels. (c)Interconnection with cabin attendantsS circuits

**ON A/C 001-101, 105-108,

(Ref. Fig. 014 )

**ON A/C 001-101, 105-999,

Mic and PTT signals from the three Cabin AttendantsSstations are fed to input 2 of the amplifier via the normally open (NO) contacts of a passenger address/interphone switching relay. This relay is energized when PA key is engaged, and de-energized when the Cabin AttendantSs telephone handset is put back on its holder. The amplifier sidetone output is fed to potentiometer 93RY providing adjustment of audio level at telephone handsets.


Passenger Address - Amplifier - Interconnection Schematic Figure 012


Passenger Address System/Cabin AttendantsS Circuits - Interconnection Schematic Figure 014 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-101, 105-108, K 23-31-00 K K CONF. 01 K K Page 31- 32 K K JAS Oct 01/92

**ON A/C 001-101, 105-108,

(d)Interconnection with Captain-to-Cabin Attendant call circuits. (Ref. Fig. 011 )

**ON A/C 001-101, 105-999,

1 Captain-to-all Cabin Attendants call _ The electronic chime 28VDC control signal is directly applied to terminal 9 of amplifier connector 1RY-A. The 60W and 5W amplifiers receive the HI/LO tone corresponding to this call which is broadcast at all Cabin, lavatory and Cabin Attendant stations loudspeakers. 2 Captain-to-one Cabin Attendant call _ The loudspeakers at Cabin AttendantsS stations only broadcast the HI/LO tone corresponding to this call. Cancellation of the HI/LO tone at cabin and lavatory loudspeakers is performed by applying electronic chime 28VDC control signal to the coil of time-delay relay 12RY which energizes and connects terminal 22 of amplifier connector 1RY-A to ground via its normally open (NO) contact. The other contact which opens the line between pin 20 and pin 21 of amplifier connector 1RY-A has no function on the aircraft. Time- delay relay 12RY has an opening delay of 3 seconds, thus enabling broadcasting of the HI/LO tone in Cabin AttendantsS loudspeakers, independently of the time the call push-button is pressed. (e)Sensitivity and gain controls 1 A pressure switch in each engine sends a _ ground signal to terminal 13 of the amplifier (engine shut down). When one of the engines is started, the ground signal is no longer fed to the amplifier, resulting in an increase in passenger address audio level. 2 Potentiometer 7RY controls the lighting of a photo-resistor which in _ turn controls the gain of the 60W amplifier. 3 Potentiometer 9RY controls amplifier sensivity by acting on the _ lighting of a photoresistor incorporated in the amplifier. Potentiometer action is effective only for inputs 1 and 2.

B. Pre-recorded Music and Announcement Tape Reproducer

**ON A/C 001-006, 109-999,

(Ref. Fig. 015 )

**ON A/C 007-101, 107-108,

(Ref. Fig. 016 )

**ON A/C 105-106,

(Ref. Fig. 017 )


Passenger Address - Tape Reproducer - Interconnection Schematic Figure 015 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 001-006, 109-999, K 23-31-00 K K CONF. 01 K KR Page 34 K K JAS Oct 01/92

Passenger Address - Tape Reproducer - Interconnection Schematic Figure 016 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 007-101, 107-108, K 23-31-00 K K CONF. 01 K K Page 35 K K JAS Mar 01/05

Passenger Address - Tape Reproducer - Interconnection Schematic Figure 017 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 105-106, K 23-31-00 K K CONF. 01 K K Page 36 K K JAS Mar 01/07

**ON A/C 001-101, 105-999,

(1)Power Supply The tape reproducer is supplied with 28VDC and 115 VAC (supplying motor). A 28VDC signal is applied via rectifier box 107RY and relay 108RY to the tape reproducer only if the 115VAC supply is present (no power supply to the tape reproducer in an ultimate emergency). (2)Operation (a)Announcement playback Eight playback heads installed on two mounts facing each announcement magazine, provide for separate reproduction of the eight tracks of the magnetic tape. The selection logic signals from the control unit are decoded before playback of the selected announcement on the relevant track. Twenty three announcements can be selected on the control unit. In the event of cabin depressurization, the oxygen mask release circuit energizes relay 19WR which, via its normally open (NO) contacts, applies a ground to terminal 16 of tape reproducer connector A, thus enabling broadcasting of oxygen mask utilization instructions (announcement A1). The emergency announcement (A1) takes priority over music and other announcements with an increased audio level.

**ON A/C 001-101, 107-999,

(b)Music playback Four playback heads installed on a mount facing the BGM magazine provide for separate reproduction of the four tracks of the magnetic tape. Pressing ON push-button 104RY starts moving the tape for immediate playback, the audio level being controlled by potentiometer 103RY. Playback always starts from track 1 followed by the other tracks in sequential order (BGM selector switch on tape reproducer placed in position A). As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement.

**ON A/C 105-106,

(b)Music playback Four playback heads installed on a mount facing the BGM magazine provide for separate reproduction of the four tracks of the magnetic tape. Pressing ON push-button 3MK6 starts moving the tape for immediate playback, the audio level being controlled by potentiometer 103RY. Playback always starts from track 1 followed by the other tracks in sequential order (BGM selector switch on tape reproducer placed in position A). As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement.

**ON A/C 001-101, 105-999,

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-101, 105-999, K 23-31-00 K K CONF. 01 K K Page 37 K K JAS Mar 01/07

(c)Tape reproducer/amplifier interconnection The music or announcement output signals are applied to Input 4 of passenger address amplifier together with the PA keyline.


6. Interface (Ref. Fig. 018 ) _________ The passenger address system is interconnected with the following system :

A. Flight Interphone System This system provides microphone and PTT signals from the audio selector panels.

B. Service Interphone System This system provides microphone and PTT signals from the Cabin AttendantsStelephone handsets.

C. Call System This system provides signals to trigger the electronic chime. - the passenger-to-Cabin Attendant call signals which trigger the HI tone. - the Captain-to-Cabin Attendant call signals which trigger the HI/LO tone.

D. Passenger Sign System This system provides signals to trigger the electronic chime LO tone when NO SMOKING OR FASTEN SEAT BELT signs illuminate and extinguish.

E. Engine Low Oil Pressure Warning A pressure switch installed on each engine applies a ground signal to the passenger address amplifier in order to increase the audio level in the cabin as soon as one engine is running (presence of a ground signal : low level, no ground signal : high level).

F. Oxygen Mask Release Circuit A ground signal is applied to the tape reproducer to trigger the emergency announcement in the event of cabin depressurization.


Passenger Address System - Interface Figure 018




2. Component Location __________________ (Ref. Fig. 001 ) (Ref. Fig. 002 ) (Ref. Fig. 003 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------

1RY Amplifier - Passenger Address 96VU 122 121BL (Ref. 23-31-18) 5RY Circuit Breaker-PUBLIC ADDRESS 22VU 210 7RY Potentiometer 97VU 122 121BL 8RY Diode 90VU 122 121BL 9RY Potentiometer 97VU 122 121BL 10RY Diode 90VU 122 121BL 11RY Diode 95VU 122 121BL 12RY Relay - Time Delay 95VU 122 121BL 13RY Relay 95VU 122 121BL 15RY1 Loudspeaker - Forward Cabin 884VU1220 Attendant Station 15RY2 Loudspeaker - Center Cabin 884VU2230 Attendant Station 16RY Loudspeaker - Aft Cabin 811VU 260 Attendant Station 74RY1 Loudspeaker - Aft Lavatory 817VU1261 74RY2 Loudspeaker - Aft Lavatory 817VU2261 79RY1 Loudspeaker - Forward 819VU1223 Lavatory 79RY2 Loudspeaker - Lavatory K 819VU2234 80RY1 Loudspeaker - Aft Lavatory 816VU1262 80RY2 Loudspeaker - Aft Lavatory 816VU2262 81RY Transformer - Forward Lavatory 801VU 223 Loudspeaker 82RY Transformer - Aft Lavatory 814VU 242 Loudspeaker 83RY Transformer - Aft Lavatory 815VU 261 Loudspeaker 84RY Transformer - Aft Lavatory 812VU 262 Loudspeaker 85RY Transformer - Aft Lavatory 813VU 261 Loudspeaker 86RY Loudspeaker - Lateral (Ref. corresponding figure) 86RY Loudspeaker - Center (Ref. corresponding figure)

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 1 K K JAS Jul 01/88

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 87RY Loudspeakers - Center (Ref. corresponding figure) 87RY Loudspeakers - Lateral (Ref. corresponding figure) 88RY Transformers - Lateral Loud- speakers (Ref. corresponding figure) 88RY Transformers - Center Loud- speakers (Ref. corresponding figure) 89RY Transformers - Center Loud- speakers (Ref. corresponding figure) 89RY Transformers - Lateral Loud- speakers (Ref. corresponding figure) 90RY Loudspeaker - Forward 894VU 220 91RY Transformer - Forward 894VU 220 Loudspeaker 93RY Potentiometer 97VU 122 121BL 100RY Reproducer - Tape (Ref. 95VU 122 121BL 23-31-35) 102RY Control Unit - Tape 801VU 221 Reproducer (Ref. 23-31-12) 103RY Potentiometer 746VU 221 105RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/115 VAC 106RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/28 VDC 107RY Rectifier Box 95VU 122 121BL 108RY Relay 95VU 122 121BL 109RY Diode 90VU 122 121BL 111RY Relay - Reception Cut-Off 878VU 221 112RY Relay - Passenger Address/ 878VU 221 Interphone Switching 113RY Relay - Reception Cut-Off 890VU 233 114RY Relay - Passenger Address/ 890VU 233 Interphone Switching 115RY Relay - Reception Cut-Off 727VU 261 116RY Relay - Passenger Address/ 727VU 261 Interphone Switching 117RY Diode 878VU 221 118RY Diode 890VU 233 119RY Diode 727VU 261 120RY Push-Button - PA 878VU 221 121RY Push-Button - PA 729VU 231 122RY Push-Button - PA 727VU 261 248RY Transformer - Lavatory K 819VU2234 Loudspeaker


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 262RY Diode 90VU 122 267RY Diode 90VU 122 268RY Diode 90VU 122 269RY Diode 90VU 122 277RY Diode 90VU 122 278RY Diode 90VU 122 295RY Diode 726VU 262 296RY Relay - Passenger Address/ 726VU 262 Interphone Switching 297RY Push-Button - PA 726VU 262 298RY Relay - Reception Cut-Off 726VU 262 303RY Push-Button - PA 880VU 251 304RY Relay - Reception Cut-Off 880VU 251 305RY Diode 880VU 251 306RY Relay - Passenger Address/ 880VU 251 Interphone Switching 307RY Push-Button - PA 882VU 252 308RY Relay - Reception Cut-Off 882VU 252 309RY Diode 882VU 252 310RY Relay - Passenger Address/ 882VU 252 Interphone Switching 311RY Push-Button - PA 730VU 232 312RY Diode 890VU 230 313RY Relay - Passenger Address/ 890VU 230 Interphone Switching 314RY Relay - Reception Cut-Off 890VU 230 315RY Diode 890VU 230 316RY Relay - Passenger Address/ 890VU 230 Interphone Switching 317RY Relay - Reception Cut-Off 890VU 230 318RY Push-Button - PA 784VU 222 1005RY Relay - Passenger Address/ 890VU 230 Interphone Switching 1013RY Diode 90VU 122 88RL Telephone Handset 878VU 221 89RL Telephone Handset 882VU 252 90RL Telephone Handset 729VU 231 91RL Telephone Handset 880VU 251 111RL Telephone Handset 726VU 262 112RL Telephone Handset 727VU 261 117RL Telephone Handset 730VU 232 152RL Telephone Handset 784VU 222 305LN Switch - Telephone Handset 878VU 221 306LN Switch - Telephone Handset 730VU 232 307LN Switch - Telephone Handset 729VU 231 308LN Switch - Telephone Handset 882VU 252 309LN Switch - Telephone Handset 880VU 251 310LN Switch - Telephone Handset 726VU 262 311LN Switch - Telephone Handset 727VU 261


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 723LN Switch - Telephone Handset 784VU 222 320LG Switch - ENTRY LIGHT & SPEAKER OFF 811VU 260 3MK6 Push-Button 746VU 221 5RK Circuit Breaker - RECORDERS/VOICE/ 22VU 210 CONTRL RELAY 19WR Relay 252VU 122 121BL 42XC Relay 101VU 120 121BL S1-295 Switch - Low Oil Pressure, 435 435AL Eng 1 (Ref. 79-34-11) S1-295 Switch - Low Oil Pressure, 445 445AL Eng 2 (Ref. 79-34-11)


A. The passenger address system consists of : (1)One amplifier 1RY enabling amplification of the audio frequency signals for the cabin loudspeakers and also for Cabin AttendantsS station loudspeakers. (2)One loudspeaker system associated with impedance matching transformers located throughout the cabin. (3)Three loudspeakers located at main Cabin AttendantsS stations. (4)One tape reproducer 100RY enabling playback of pre-recorded music and announcement magazines. (5)One tape reproducer control unit 102RY enabling selection, starting and resetting of a pre-recorded announcement. (6)One BGM ON/OFF push-button 3MK6 associated with potentiometer 103RY enabling music starting and volume adjustment. (7)One circuit breaker 5RY supplying amplifier 1RY with 28VDC power. (8)Two circuit breakers 106RY and 105RY supplying the tape reproducer with 28VDC and 115VAC power.


Passenger Address - Component Location in Flight Compartment and Avionics Compartment Figure 001 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 5- 6 K K JAS Jul 01/88

Passenger Address - Location of Loudspeakers and Transformers in Cabin Figure 002 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 7- 8 K K JAS Jul 01/88

Passenger Address - Location of Loudspeakers in Lavatories Figure 003 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 9 K K JAS Jul 01/88


A. Passenger Address Amplifier 1RY (Ref. Fig. 005 )


(1)The passenger address amplifier consists of : (a)Four input channels, each having a rank of priority. (b)An electronic chime associated with the call circuits. (c)One 50W and one 5W output stages - the 50W output is supplied to the cabin and lavatory loudspeakers via impedance matching transformers. - the 5W output is supplied to the Cabin Attendant station loudspeakers. (d)On face - a three-position NORM-CAL-TEST selector switch . The CAL position enables operation of the amplifier to be tested (test of 50W amplifier output level) . The TEST position initiates a 600Hz test signal to the amplifier in order to provide an aural check of


the loudspeakers (e)An electrical connector located at the back of the amplifier for connection to the rest of the system.


C. Passenger Address Music and Announcement Tape Reproducer 100RY (Ref. Fig. 006 )


(1)On the face (a)a hinged panel, when unlatched, enables access to the four following tape magazines - the three announcement magazines A, B, C. Each announcement magazine includes 8 tracks, each for reproduction of a different announcement with a maximum playtime of 30 minutes. - the background music (BGM) magazine including 4 tracks, each


with a maximum of one hour playtime. The endless loop magnetic tape fitted in each magazine is driven at a 9.5 cm/sec. (3 -3/4 inches/sec.) speed. (b)a five-position rotary selector switch enablesselection of the 4 tracks of the BGM magazine, either manually (positions 1, 2, 3, 4) or automatically (position A) from forward Cabin AttendantSs station (PurserSs station). (c)a handle to facilitate transport and installation of the tape reproducer in the mounting tray. (2)An electrical connector at the back of the tape reproducer for connection to the rest of the system.

D. Tape Reproducer Control Unit (Ref. Fig. 007 )


Tape reproducer control unit 102RY is located at the forward Cabin AttendantSs station (PurserSs station). An electrical connector at the back of the control unit allows connection to the rest of the system. On the face are the following :


(1)Three keys, labelled A, B and C for selection of pre-recorded announcement magazines. (2)Eight keys numbered from 1 to 8 for selection of the 8 different tracks in each magazine. Selection of one announcement is by means of these eleven keys. Example : for selection of announcement B1, press key B and key 1 which come on. (3)One ANN push-button for broadcasting of the announcement selected. (4)One CANCEL push-button for interrupting the announcement in progress. (5)Three yellow status lights indicating the position of the tape in the three magazines. (a)If the status light associated with the selected magazine is off, the selected announcement is ready for immediate playback. (b)If the status light associated with the selected magazine is on, this indicates either one of the following cases : - the tape is winding to the position corresponding to the selected announcement - an announcement is in progress - there is no announcement pre-recorded at this location on the tape. NOTE : Emergency announcement A1 which has a top ____ priority over the other announcements cannot be selected on the control unit. It is automatically triggered in the event of cabin depressurization

E. Background Music Controls (1)BGM ON/OFF push-button 3MK6 - When pressed, this push-button triggers starting of the background music (BGM) tape. - As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement. (2)Potentiometer 103RY This potentiometer enables adjustment of the audio level of the music broadcast in the cabin and lavatories.


A. Passenger Address Amplifier 1RY (Ref. Fig. 008 ) (Ref. Fig. 009 ) (a)Interconnection with the loudspeakers - The output from the 50W amplifier is connected to all primary windings of the parallel-connected transformers. Each loudspeaker is connected to the secondary winding of an impedance matching transformer. - The output from the 5W amplifier is connected to the three parallel- connected loudspeakers at the Cabin AttendantsS stations. (b)Interconnection with crew membersS circuits Input 1 receives microphone and PTT signals from crew membersS stations via the interphone junction box.


INTENTIONALLY BLANK

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR K K 23-31-00 K K CONF. 02 K K Page 16 K K JAS Jul 01/88


HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 17- 18 K K JAS Jul 01/88

The amplifier sidetone output is fed to crew membersS stations reception channels. (c)Interconnection with Cabin AttendantsS circuits (Ref. Fig. 010 ) Input 2 receives microphone and PTT signals from Cabin AttendantsS stations. Microphone and PTT signals from the various stations are fed to input 2 of the amplifier via the normally open (NO) contacts of a passenger address/interphone switching relay. This relay is energized when PA key at Cabin AttendantsS stations is engaged ; the relay is de-energized when telephone handset is put back on its holder. Potentiometer 93RY installed on amplifier sidetone output provides adjustment of audio level at the telephone handsets. (d)Interconnection with Captain-to-Cabin Attendant call circuits (Ref. Fig. 008 ) 1 Captain-to-all Cabin Attendants call _ The electronic chime 28VDC control signal is directly applied to terminal 9 of amplifier connector 1RY-A. The 50W and 5W amplifiers receive the HI/LO tone corresponding to this call which is broadcast at all Cabin, lavatory and Cabin Attendant stations loudspeakers. 2 Captain-to-one Cabin Attendant call _ The loudspeakers at Cabin AttendantsS stations only broadcast the HI/LO tone corresponding to this call. Cancellation of the HI/LO tone at cabin and lavatory loudspeakers is performed by applying electronic chime 28VDC control signal to the coil of time-delay relay 12RY which energizes and connects terminal 22 of amplifier connector 1RY-A to ground via its normally open (NO) contact. The other contact which opens the line between pin 20 and pin 21 of amplifier connector 1RY-A has no function on the aircraft. Time- delay relay 12RY has an opening delay of 3 seconds, thus enabling broadcasting of the HI/LO tone in Cabin AttendantsS loudspeakers, independently of the time the call push-button is pressed. (e)Sensitivity and gain controls 1 A pressure switch in each engine sends a ground signal to terminal 13 _ of the amplifier (engine shut down). When one of the engines is started, the ground signal is no longer fed to the amplifier, resulting in an increase in passenger address audio level. 2 Potentiometer 7RY controls the lighting of a photo-resistor which in _ turn controls the gain of the 50W amplifier. 3 Potentiometer 9RY controls amplifier sensivity by acting on the _ lighting of a photoresistor incorporated in the amplifier. Potentiometer action is effective only for inputs 1 and 2.


INTENTIONALLY BLANK

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ K K 23-31-00 K K CONF. 02 K KR Page 20 K K JAS Jul 01/88

Passenger Address System/Cabin AttendantsS Circuits - Interconnection Schematic Figure 010 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 21- 22 K K JAS Jul 01/88

B. Pre-recorded Music and Announcement Tape Reproducer (Ref. Fig. 011 ) (1)Power supply The tape reproducer is supplied with 28VDC and 115 VAC (supplying motor). A 28VDC signal is applied via rectifier box 107RY and relay 108RY to the tape reproducer only if the 115VAC supply is present (no power supply to the tape reproducer in an ultimate emergency). (2)Operation (a)Announcement playback Eight playback heads installed on two mounts facing each announcement magazine, provide for separate reproduction of the eight tracks of the magnetic tape. The selection logic signals from the control unit are decoded before playback of the selected announcement on the relevant track. Twenty three announcements can be selected on the control unit. In the event of cabin depressurization, the oxygen mask release circuit energizes relay 19WR which, via its normally open (NO) contacts, applies a ground to terminal 16 of tape reproducer connector A, thus enabling broadcasting of oxygen mask utilization instructions (announcement A1). The emergency announcement (A1) takes priority over music and other announcements with an increased audio level. (b)Music playback Four playback heads installed on a mount facing the BGM magazine provide for separate reproduction of the four tracks of the magnetic tape. Pressing BGM ON/OFF push-button 3MK6 starts the tape moving for immediate playback, the audio level being controlled by potentiometer 103RY. Playback always starts from track 1 followed by the other tracks in sequential order (BGM selector switch on tape reproducer placed in position A). As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement. (c)Tape reproducer/amplifier interconnection The music or announcement output signals are applied to Input 3 of passenger address amplifier together with the PA keyline. (d)Interconnection with passenger entertainment system. The music output signals are applied to input 4 of passenger address amplifier.

6. Interface (Ref. Fig. 012 ) _________ The passenger address system is interconnected with the following systems :



C. Call System


Passenger Address Tape Reproducer - Interconnection Schematic Figure 011 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 103-104, K 23-31-00 K K CONF. 02 K K Page 24 K K JAS Jul 01/88

This system provides signals to trigger the electronic chime. - the passenger-to-Cabin Attendant call signals which trigger the HI tone. - the Captain-to-Cabin Attendant call signals which trigger the HI/LO tone.

D. Passenger Sign System This system provides signals to trigger the electronic chime LO tone when NO SMOKING OR FASTEN SEAT BELT signs come on and go off.



G. Passenger Entertainment System Passenger entertainment tape reproducer signals are fed to input 4 of passenger address amplifier.




2. Component Location __________________ (Ref. Fig. 001 )

R

(Ref. Fig. 002 ) (Ref. Fig. 003 )

R

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RY Amplifier - Passenger Address 96VU 122 121BL (Ref. 23-31-18) 5RY Circuit Breaker-PUBLIC 22VU 210 ADDRESS 7RY Potentiometer 97VU 122 121BL 8RY Diode 90VU 122 121BL 9RY Potentiometer 97VU 122 121BL 10RY Diode 90VU 122 121BL 11RY Diode 95VU 122 121BL 12RY Relay - Time Delay 95VU 122 121BL 13RY Relay 95VU 122 121BL 15RY1 Loudspeaker - Forward Cabin 884VU1220 Attendant Station 15RY2 Loudspeaker - Center Cabin 884VU2230 Attendant Station 16RY Loudspeaker - Aft Cabin 811VU 260 Attendant Station 74RY1 Loudspeaker - Aft Lavatory 817VU1261 74RY2 Loudspeaker - Aft Lavatory 817VU2261 79RY Loudspeaker - Forward Lavatory 819VU 223 80RY1 Loudspeaker - Aft Lavatory 816VU1262 80RY2 Loudspeaker - Aft Lavatory 816VU2262 81RY Transformer - Forward 801VU 223 Lavatory Loudspeaker 82RY Transformer - Aft Lavatory 814VU 242 Loudspeaker 83RY Transformer - Aft Lavatory 815VU 261 Loudspeaker 84RY Transformer - Aft Lavatory 812VU 262 Loudspeaker 85RY Transformer - Aft Lavatory 813VU 261 Loudspeaker


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------

R

86RY Loudspeakers - Lateral 860VU (Ref. corresponding figure) 86RY Loudspeakers - Center 860VU (Ref. corresponding figure) 87RY Loudspeakers - Lateral 859VU (Ref. corresponding figure) 87RY Loudspeakers - Center 859VU (Ref. corresponding figure) 88RY Transformers - Lateral 860VU Loudspeakers (Ref. corresponding figure) 88RY Transformers - Center Loud- 860VU speakers (Ref. corresponding figure) 89RY Transformers - Lateral 859VU Loudspeakers (Ref. corresponding figure) 89RY Transformers - Center 859VU Loudspeakers (Ref. corresponding figure) 90RY Loudspeaker - Forward 894VU 91RY Transformer - Forward 894VU Loudspeaker

R

93RY Potentiometer 97VU 122 121BL 100RY Reproducer - Tape (Ref. 95VU 122 121BL 23-31-35) 102RY Control Unit - Tape 801VU 221 Reproducer (Ref. 23-31-12) 103RY Potentiometer 746VU 221 105RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/115 VAC 106RY Circuit Breaker - TAPE 22VU 210 REPRODUCER/28 VDC 107RY Rectifier Box 95VU 122 121BL 108RY Relay 95VU 122 121BL 109RY Diode 90VU 122 121BL 111RY Relay - Reception Cut-Off 878VU 221 112RY Relay - Passenger Address/ 878VU 221 Interphone Switching 113RY Relay - Reception Cut-Off 890VU 233 114RY Relay - Passenger Address/ 890VU 233 Interphone Switching 115RY Relay - Reception Cut-Off 727VU 261


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 116RY Relay - Passenger Address/ 727VU 261 Interphone Switching 117RY Diode 878VU 221 118RY Diode 890VU 233 119RY Diode 727VU 261 120RY Push-Button - PA 878VU 221 121RY Push-Button - PA 729VU 231 122RY Push-Button - PA 727VU 261 241RY Relay-Reception 90VU 122 Cut-Off 242RY Relay - Passenger 90VU 122 Address/Interphone Switching 243RY Relay 90VU 122 244RY Diode 90VU 122 245RY Switch - Telephone 11VU 210 Handset 246RY Indicator Light/Switch 32VU 210 PA ON 247RY Diode 90VU 122 264RY Diode 90VU 122 265RY Diode 90VU 122 267RY Diode 90VU 122 268RY Diode 90VU 122 269RY Diode 90VU 122 275RY Loudspeaker - Forward 764VU 222 Lavatory 276RY Transformer - Forward 764VU 222 Lavatory Loudspeaker 277RY Diode 90VU 122 278RY Diode 90VU 122

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295RY Diode 726VU 262 296RY Relay - Passenger Address/ 726VU 262 Interphone Switching 297RY Push-Button - PA 726VU 262 298RY Relay - Reception Cut-Off 726VU 262 303RY Push-Button - PA 880VU 251 304RY Relay - Reception Cut-Off 880VU 251 305RY Diode 880VU 251 306RY Relay - Passenger Address/ 880VU 251 Interphone Switching 307RY Push-Button - PA 882VU 252 308RY Relay - Reception Cut-Off 882VU 252 309RY Diode 882VU 252 310RY Relay - Passenger Address/ 882VU 252 Interphone Switching 311RY Push-Button - PA 730VU 232


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 312RY Diode 890VU 230 313RY Relay - Passenger Address/ 890VU 230 Interphone Switching 314RY Relay - Reception Cut-Off 890VU 230 315RY Diode 890VU 230 316RY Relay - Passenger Address 890VU 230 Interphone Switching 317RY Relay - Reception Cut-Off 890VU 230 318RY Push-Button - PA 784VU 222

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1005RY Relay 890VU 230

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1013RY Diode 90VU 122 49RL Jack - Interphone 11VU 210

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88RL Telephone Handset 878VU 221 89RL Telephone Handset 882VU 252 90RL Telephone Handset 729VU 231 91RL Telephone Handset 880VU 251 92RL Telephone Handset 11VU 210 111RL Telephone Handset 726VU 262 112RL Telephone Handset 727VU 261 117RL Telephone Handset 730VU 232 152RL Telephone Handset 784VU 222 305LN Switch - Telephone Handset 878VU 221 306LN Switch - Telephone Handset 730VU 232 307LN Switch - Telephone Handset 729VU 231 308LN Switch - Telephone Handset 882VU 252 309LN Switch - Telephone Handset 880VU 251 310LN Switch - Telephone Handset 726VU 262 311LN Switch - Telephone Handset 727VU 261 723LN Switch - Telephone Handset 784VU 222

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320LG Switch - ENTRY LIGHT & 811VU 260 SPEAKER OFF 3MK6 Push-Button - BGM ON/OFF 746VU 221 5RK Circuit Breaker - RECORDERS/ 22VU 210 VOICE/CONTRL RELAY 19WR Relay 252VU 122 121BL 42XC Relay 101VU 120 121BL S1-295 Switch - Low Oil Pressure, 435 435AL


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ Eng 1 (Ref. 79-34-11) S1-295 Switch - Low Oil Pressure, 445 445AL Eng 2 (Ref. 79-34-11)


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Passenger Address - Component Location in Flight Compartment and Avionics Compartment Figure 001 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 7- 8 K K JAS Oct 01/89

Passenger Address - Location of Loudspeakers and Transformers in Cabin Figure 002 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 9- 10 K K JAS Oct 01/89

Passenger Address - Location of Loudspeakers in Lavatories Figure 003 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 11 K K JAS Oct 01/89

3. System Description (Ref. Fig. 004 ) __________________

A. The passenger address system consists of : (1)One amplifier 1RY enabling amplification of the audio frequency signals for the cabin loudspeakers and also for Cabin AttendantsS station loudspeakers via impedance matching transformers. (2)One loudspeaker system associated with impedance matching transformers located throughout the cabin. (3)Three loudspeakers located at the main Cabin AttendantsS stations. (4)One tape reproducer 100RY enabling playback of pre-recorded music and announcement magazines. (5)One tape reproducer control unit 102RY enabling selection, starting and resetting for a pre-recorded announcement. (6)One BGM ON/OFF push-button 3MK6 associated with potentiometer 103RY enabling music starting and volume adjustment. (7)One circuit breaker 5RY supplying amplifier 1RY with 28VDC power. (8)Two circuit breakers 106RY and 105RY supplying the tape reproducer with 28VDC and 115VAC power.



A. Passenger Address Amplifier 1RY

R

(Ref. Fig. 005 )


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(1)The passenger address amplifier consists of : (a)Four input channels, each having a rank of priority. (b)An electronic chime associated with the call circuits. (c)One 60W and one 5W output stages - the 60W output is supplied to the cabin and lavatory loudspeakers via impedance matching transformers. - the 5W output is supplied to the Cabin Attendant station loudspeakers.

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 14 K K JAS Oct 01/89

(d)On the face

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- a three-position NORM-CAL-TEST selector switch . The CAL position enables operation of the amplifier (test of 60W amplifier output level) to be tested. . The TEST position enables a 600Hz test signal to be fed to the amplifier in order to provide an aural check of all the loudspeakers

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(e)An electrical connector located at the back of the amplifier for connection to the rest of the system.


C. Passenger Address Music and Announcement Tape Reproducer 100RY (Ref. Fig. 006 ) (1)On the face (a)a hinged panel, when unlatched, enables to gain access to the four following tape magazines - the three announcement magazines A, B, C. Each announcement magazine includes 8 tracks, each for reproduction of a different announcement with a maximum playtime of 30 minutes. - the background music (BGM) magazine including 4 tracks, each with a maximum of one hour playtime. The endless loop magnetic tape fitted in each magazine is driven at a 9.5 cm/sec. (3 -3/4 inches/sec.) speed. (b)a five-position rotary selector switch enablesto select the 4 tracks of the BGM magazine, either manually (positions 1, 2, 3, 4) or automatically (position A) from forward Cabin AttendantSs station (PurserSs station). (c)a handle to facilitate transport and installation of the tape reproducer in the mounting tray. (2)An electrical connector at the back of the tape reproducer for connection to the rest of the system.



D. Tape Reproducer Control Unit (Ref. Fig. 007 ) Tape reproducer control unit 102RY is located at the forward Cabin AttendantSs station (PurserSs station). An electrical connector at the back of the control unit allows connection to the rest of the system. On the face are the following : (1)Three keys, labelled A, B and C for selection of pre-recorded announcement magazines. (2)Eight keys numbered from 1 to 8 for selection of the 8 different tracks in each magazine. Selection of one announcement is by means of these eleven keys. Example : for selection of announcement B1, press key B and key 1 which come on. (3)One ANN push-button for broadcasting the announcement selected. (4)One CANCEL push-button for interrupting the announcement in progress. (5)Three yellow status lights indicating the position of the tape in the three magazines.



If the status light associated with the selected magazine is on, this indicates either one of the following cases : - the tape is winding to the position corresponding to the selected announcement - an announcement is in progress - there is no announcement pre-recorded at this location on the tape. NOTE : Emergency announcement A1 which has a top ____ priority over the other announcements cannot be selected on the control unit. It is automatically triggered in the event of cabin depressurization

E. Background Music Controls (1)BGM ON/OFF push-button 3MK6 - When pressed, this push-button comes on and triggers starting of the background music (BGM) tape. - As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement.


(2)Potentiometer 103RY This potentiometer enables to adjust the audio level of the music broadcast in the cabin and lavatories.



A. Passenger Address Amplifier 1RY (Ref. Fig. 008 ) (1)Amplification The passenger address amplifier comprises 4 input channels which have been given a rank of priority - priority 1 (corresponding to input 1), assigned to the crew membersS stations, is used from the mask microphones. - priority 2 (corresponding to input 2), assigned to the Cabin Atten- dantsS stations. - priority 3 (corresponding to input 3) assigned to the pre-recorded music and announcement broadcasting system. - priority 4 (corresponding to input 4), assigned to the passenger entertainment system. The audio frequency (AF) signals from inputs 1, 2, 3 and 4 are applied to the 60W amplifier. The output signal from the 60W amplifier is applied to the cabin and lavatory loudspeakers via impedance matching transformers. Only the AF signal from input 1 is applied to the 5W amplifier. The output signal from the 5W amplifier is applied to the Cabin Attendant stations loudspeakers. (2)Electronic chime An electronic chime incorporated in the amplifier produces three tones : high tone (HI), low tone (LO), and high/low tone (HI/LO). It is controlled by four different channels - channel 1 assigned to Passenger-to-Cabin Attendant calls, producing a high tone (HI) - channel 2 assigned to Captain-to-Cabin Attendant calls, producing a high/low (HI/LO) tone. - channel 3 assigned to FASTEN SEAT BELT sign, producing a low tone (LO). - channel 4 assigned to NO SMOKING sign, producing a low tone (LO). The 60W amplifier receives the three tones through selector gates. The 5W amplifier always receives the three tones independently from the combination of these selector gates. (3)Amplifier 1RY Interconnections

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(Ref. Fig. 009 )

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(a)Interconnection with the loudspeakers - The output from the 60W amplifier is connected to all primary windings of the parallel-connected transformers of cabin and lavatory loudspeakers. Each loudspeaker is connected to the secondary winding of an impedance matching transformer. - The output from the 5W amplifier is connected to the three parallel-connected loudspeakers at the Cabin AttendantsS stations. (b)Interconnection with crew membersS circuits


Passenger Address - Amplifier - Interconnection Schematic Figure 009 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 21- 22 K K JAS Oct 01/89

Input 1 receives microphone and PTT signals, from crew membersS stations via the interphone junction box. The amplifier sidetone output is fed to crew membersS stations reception channels. (c)Interconnection with cabin attendantsS circuits

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(Ref. Fig. 010 )

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Input 2 receives microphone and PTT signals from the three Cabin AttendantsS stations and from crew membersS station. Telephone handset 92RL located on center control pedestal enables the crew to establish communications with Cabin Attendants and also to transmit announcements to passengers by pressing PA ON indicator light/switch 246RY located on panel 32VU. Mic and PTT signals from the various sta tions are fed to Input 2 of the amplifier via the normally open (NO) contacts of a passenger address, interphone switching relay.This relay is energized when PA key at Cabin AttendantsSstations is engaged or when PA ON indicator light/switch at crew memberSs station is pressed ; the relay is de- energized when telephone handset is put back on its holder. Potentiometer 93RY installed on amplifier sidetone output provides adjustment of audio level at the telephone handsets. (d)Interconnection with Captain-to-Cabin Attendant call circuits (Ref. Fig. 008 ) 1 Captain-to-all Cabin Attendants call _ The electronic chime 28VDC control signal is directly applied to terminal 9 of amplifier connector 1RY-A. The 60W and 5W amplifiers receive the HI/LO tone corresponding to this call which is broadcast at all Cabin, lavatory and Cabin Attendant stations loudspeakers. 2 Captain-to-one Cabin Attendant call _ The loudspeakers at Cabin AttendantsS stations only broadcast the HI/LO tone corresponding to this call. Cancellation of the HI/LO tone at cabin and lavatory loudspeakers is performed by applying electronic chime 28VDC control signal to the coil of time-delay relay 12RY which energizes and connects terminal 22 of amplifier connector 1RY-A to ground via its normally open (NO) contact. The other contact which opens the line between pin 20 and pin 21 of amplifier connector 1RY-A has no function on the aircraft. Time- delay relay 12RY has an opening delay of 3 seconds, thus enabling broadcasting of the HI/LO tone in Cabin AttendantsS loudspeakers, independently of the time the call push-button is pressed. (e)Sensitivity and gain controls 1 A pressure switch in each engine sends a _ ground signal to terminal 13 of the amplifier (engine shut down). When one of the engines is started, the ground signal is no longer fed to the amplifier, resulting in an increase in passenger address audio level.


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Passenger Address System/Cabin AttendantsS Circuits - Interconnection Schematic Figure 010 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K K Page 25- 26 K K JAS Oct 01/89

2 Potentiometer 7RY controls the lighting of _ a photo-resistor which in turn controls the gain of the 60W amplifier. 3 Potentiometer 9RY controls amplifier sensivity by acting on the _ lighting of a photoresistor incorporated in the amplifier. Potentiometer action is effective only for inputs 1 and 2.

B. Pre-recorded Music and Announcement Tape Reproducer

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(Ref. Fig. 011 )

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(1)Power Supply The tape reproducer is supplied with 28VDC and 115 VAC (supplying motor). A 28VDC signal is applied via rectifier box 107RY and relay 108RY to the tape reproducer only if the 115VAC supply is present (no power supply to the tape reproducer in an ultimate emergency). (2)Operation (a)Announcement playback Eight playback heads installed on two mounts facing each announcement magazine, provide for separate reproduction of the eight tracks of the magnetic tape. The selection logic signals from the control unit are decoded before playback of the selected announcement on the relevant track. Twenty three announcements can be selected on the control unit. In the event of cabin depressurization, the oxygen mask release circuit energizes relay 19WR which, via its normally open (NO) contacts, applies a ground to terminal 16 of tape reproducer connector A, thus enabling broadcasting of oxygen mask utilization instructions (announcement A1). The emergency announcement (A1) takes priority over music and other announcements with an increased audio level. (b)Music playback Four playback heads installed on a mount facing the BGM magazine provide for separate reproduction of the four tracks of the magnetic tape. Pressing BGM ON/OFF Push-button 3MK6 starts moving the tape for immediate playback, the audio level being controlled by potentiometer 103RY. Playback always starts from track 1 followed by the other tracks in sequential order (BGM selector switch on tape reproducer placed in position A). As the announcements take priority over music, music playback is interrupted by any selected announcement and is resumed at the end of the announcement. (c)Tape reproducer/amplifier interconnection The music or announcement output signals are applied to Input 3 of passenger address amplifier together with the PA keyline.


Passenger Address Tape Reproducer - Interconnection Schematic Figure 011 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 102-102, K 23-31-00 K K CONF. 03 K KR Page 28 K K JAS Oct 01/89

6. Interface (Ref. Fig. 012 ) _________ The passenger address system is interconnected with the following system :



C. Call System This system provides signals to trigger the electronic chime. - the passenger-to-Cabin Attendant call signals which trigger the HI tone. - the Captain-to-Cabin Attendant call signals which trigger the HI/LO tone.

D. Passenger Sign System This system provides signals to trigger the electronic chime LO tone when NO SMOKING OR FASTEN SEAT BELT signs illuminate and extinguish.



G. Passenger Entertainment System Passenger entertainment tape reproducer signals are fed to input 4 of passenger address amplifier.


PASSENGER ADDRESS - FAULT ISOLATION ___________________________________



PASSENGER ADDRESS - ADJUSTMENT/TEST ___________________________________


A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit -3-Phase, 115/200V, 400Hz, 90KVA Referenced Procedures - 21-20-00, P. Block 301 - 24-41-00, P. Block 301 External Power

B. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that the forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (3)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU FLT DECK CALLS 1LN 112/B 1 22VU RECORDERS/VOICE/CONTRL RELAY 5RK 204/K11 22VU AUDIO SYS/CONTRL PNL/1ST OBSV & AVIONICS 16RL 209/E 7 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12 22VU PUBLIC ADDRESS 5RY 213/A11 22VU TAPE REPRODUCER 115VAC 105RY 209/E 2 22VU TAPE REPRODUCER 28VDC 106RY 209/E 1 129VU PASSENGER SIGNS/FASTEN BELT 28WJ 902/B 5 129VU PASSENGER SIGNS/RETURN TO YR SEAT 29WJ 902/B 6 129VU PASSENGER SIGNS/RETURN TO YR SEAT 30WJ 902/B 7 129VU PASSENGER SIGNS/NO SMOKING 31WJ 902/B 8 800VU CALL-SYSTEM/ATTN 10LN 800VU CALL-SYSTEM/LAVATORY 14LN 800VU CALL-SYSTEM/PASS 15LN 811VU CALL-SYSTEM/LAVATORY 19LN 811VU CALL-SYSTEM/PASSENGER 95LN (4)On panel 26VU - place SEAT BELTS and NO SMOKING switches in OFF position. (5)On CaptainSs and First OfficerSs control column handwheels - make certain that PTT switches are in intermediate position.

R **ON A/C 001-101, 103-999,

(6)On panel 223VU, at Second ObserverSs station


- place RADIO-INTPH switch in intermediate position.

**ON A/C 102-102,

(6)Not applicable.

**ON A/C ALL

(7)On CaptainSs, First OfficerSs, Flight EngineerSs, First ObserverSs and avionics compartment audio selector panels :

R **ON A/C 107-999,

- place RAD-INT PTT switches in intermediate position

R **ON A/C 001-101, 103-999,

- engage INT transmission square key

**ON A/C 102-102,

- engage FLT INT transmission square key

**ON A/C ALL

- engage all reception push-buttons

**ON A/C 001-102, 105-106,

- make certain that VOICE push-button is disengaged.

R **ON A/C 103-104, 107-999,

- make certain that VOICE ONLY push-button is disengaged.

R **ON A/C 103-104,

- place MIC SELECT OXY-BOOM switch in BOOM position.

**ON A/C ALL

(8)On CaptainSs, First OfficerSs. Flight EngineerSs, First and Second ObserverSs jacks boxes : - connect a boomset to interphone connection receptacle

R **ON A/C 001-100, 102-102, 107-999,


**ON A/C ALL


(9)In avionics compartment, on LH electronics rack 80VU - connect a headset to associated jack - connect a hand microphone to associated interphone connection receptacle.

(10)On panel 29VU - place ESS SYS-OFF switch in ESS SYS position. (11)At PurserSs station, make certain that ON push-button is disengaged off

C. Test (1)Test of announcements made by the crew members ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel at each crew memberSs station and in avionics compartment - engage PA transmission square key

- disengage PA reception push- button and turn integral potentiometer clockwise

R **ON A/C 001-100, 102-102, 107-999,

2. At CaptainSs station, - Check reception at each of speak into boomset microphone passenger compartment, Cabin while operating associated PTT Attendant station and lavatory switch. loudspeakers. - Check reception at boomset, at all other crew membersS stations and also operation of volume potentiometer integral with reception push-button.

**ON A/C ALL

3. Repeat tests from : - First OfficerSs station - Flight EngineerSs station - First ObserverSs station - Second ObserverSs station - Avionics compartment station.

NOTE : The Second ObserverSs station is dependent upon PA selec- ____ tion and audio volume adjustment made on Flight EngineerSs audio


selector panel. (2)Test of announcements made by Cabin Attendants ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs - Check recption at passenger com- station, make an announcement partment and lavatory louds- on passenger address (PA) system. speakers - Check that the announcement is not received at Cabin AttendantsS loudspeakers.

2. Repeat tests from the other Cabin AttendantsS stations where transmission on passenger address system is possible.

(3)Test of transmission priorities ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make an announcement from one - Check that the transmission heard Cabin AttendantSs station at passenger compartment loudspeakers is that from crew memberSs 2. At the same time, make an announ- station and not that from Cabin cement from one crew memberSs AttendantSs station. station

(4)Test of Crew-to-Cabin Attendant call circuits. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 32VU - press one of the following - Check that the HI/LO tone is indicator lights. received at the Cabin Attendant - FWD ATTND CALL station loudspeakers. - MID ATTND CALL - AFT ATTND CALL

- press PURS CALL indicator - Check that the HI/LO tone is light. received at passenger compartment Cabin Attendant station and lavatory loudspeakers.

- press ALL ATTND CALL push- - Check that the HI/LO tone is button received at passenger compartment Cabin Attendant station and lavatory loudspeakers.

(5)Test of Cabin Attendant-to-Cabin Attendant call circuits


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At each Cabin AttendantSs - Check that the HI/LO tone is station, press push-button to received at Cabin AttendantsS call other Cabin AttendantSs loudspeakers. station.

(6)Test of passenger-to-Cabin Attendant call circuits ------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------

R **ON A/C 001-107,

1. Press one of the Cabin Attendant - Check that the HI tone is received call push-buttons located in pas- at Cabin Attendant station senger compartment. loudspeakers.

R **ON A/C 108-999,

1. Press one of the Cabin Attendant - Check that the HI tone is received call push-buttons located in pas- at Cabin Attendant station senger compartment. loudspeakers, and at all passenger compartment/lavatory loudspeakers.

R **ON A/C ALL

(7)Test of passenger sign circuits ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 26VU - place SEAT BELTS-OFF switch - Check that the LO tone is received in SEAT BELTS position at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- place SEAT BELTS-OFF switch - Check that the LO tone is recei- in OFF position ved at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- place NO SMOKING-OFF switch - Check that the LO tone is recei- in NO SMOKING position ved at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- place NO SMOKING-OFF switch - Check that the LO tone is in OFF position received at passenger compartment, Cabin Attendant station and lavatory loudspeakers.


(8)Operational test of pre-recorded music and annoucement tape reproducer. (a)Broadcasting of pre-recorded announcements NOTE : Before starting broadcast of an announcement, make ____ certain that the selected track is impressed. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs station, on tape reproducer control unit : - press key A to select magazine A - key A comes on

- press key 2 to select track 2 - key 2 comes on

- press ANN push-button, making - Check that the announcement broa- certain first that the status cast at the passenger compartment light at the LH side of key A and lavatory loudspeaker is that is extinguished recorded on the selected track. - Check that the associated status light is on

- press CANCEL push-button - the announcement in progress is stopped - The status light is on

2. Repeat tests for magazines B and C.

(b)Broadcasting of emergency announcement - Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU PASSENGER OXYGEN/ACTUATION 2WR 203/L 3 22VU PASSENGER OXYGEN/ACTUATION 3WR 203/L 4 22VU PASSENGER OXYGEN/ACTUATION 4WR 203/L 5 22VU PASSENGER OXYGEN/ACTUATION 5WR 203/L 6 22VU PASSENGER OXYGEN/ACTUATION 6WR 203/L 7 22VU PASSENGER OXYGEN/ACTUATION 7WR 203/L 8 22VU PASSENGER OXYGEN/ACTUATION 21WR 203/L 9 22VU PASSENGER OXYGEN/ACTUATION 22WR 203/L10 22VU PASSENGER OXYGEN/ACTUATION 23WR 203/L11 - Make certain that the following circuit breaker is closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU PASSENGER OXYGEN/CONTRL & WARN 1WR 203/L12 - Test of emergency annoucement priority over other announcements


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Select and start any announcement - The announcement is received at from magazine B or C. passenger compartment and lavatory loudspeakers.

2. On panel 63VU, hold AUTO-MAN - Check that the emergency announce- O/RIDE switch in MAN O/RIDE ment is received at all passenger position and release. compartment and lavatory loudspeakers.

3. On tape reproducer control unit - press CANCEL pushbutton - Check that the emergency announcement is stopped.

4. On panel 63VU - press PASSENGER OXYGEN/RESET pushbutton switch to reset oxygen system.

(c)Broadcasting of music to passengers - On electronics rack 90VU, on pre-recorded music and announcement tape reproducer, make certain that rotary selector switch is in A position. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs station - engage ON push-button - ON push-button comes on

- turn volume potentiometer - Check that music is correctly clockwise to obtain normal received at passenger compartment audio level. and lavatory loudspeakers

(d)Test of priorities - Priority of Cabin AttendantsS announcements over pre-recorded announcements. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On tape reproducer control unit, - The announcement is received at select and start a pre-recorded passenger compartment and lavatory announcement. loudspeakers.

2. Transmit a message from forward - Check that the message from Cabin Cabin AttendantSs station AttendantSs station replaces the announcement at the loudspeakers.

3. Press CANCEL push-button


- Priority of pre-recorded announcements over music ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs - Music is received at passenger station compartment and lavatory - engage ON push-button loudspeakers.

- on tape reproducer control - Check that the selected announ- unit, select an announcement cement replaces music at the by pressing the appropriate loudspeakers and that music keys. is resumed at the end of the announcement.

- disengage ON push-button - ON push-button goes off

- Remove safety clips and tags and close circuit breakers 2WR, 3WR, 4WR, 5WR, 6WR, 7WR, 21WR, 22WR and 23WR. (9)Variations in passenger address audio level ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. While making an announcement - Check that the audio level from crew memberSs station, open increases in passenger compartment, circuit breaker 5RK on Cabin AttendantsSstations and panel 22VU lavatory loudspeakers.

2. Close circuit breaker 5RK - The audio level decreases in passenger compartment, Cabin Atten- dantsS stations and lavatory loudspeakers.

D. Close-Up (1)On audio selector panel at each crew memberSs station and in avionics compartment :

**ON A/C 001-101, 103-999,


**ON A/C 102-102,


**ON A/C ALL

- engage PA reception push-button. (2)In avionics compartment, on LH electronics rack 80VU - Disconnect hand microphone and headset. (3)On panel 29VU


- place ESS SYS-OFF switch in OFF position. (4)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (5)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


2. Functional Test _______________ Refer to Operational Test - Identical.

3. System Test ___________

A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200V, 400 Hz, 90KVA (2) Ohmmeter Circuit Breaker Safety Clips Referenced Procedures - 21-20-00, P. Block 301 Distribution+Extraction - 24-41-00; P. Block 301 External Power

B. Adjustment of Audio Volume in Passenger Address System Check that the audio volume adjusting potentiometers operate correctly as follows : (1)On panel 22VU, open, safety and tag circuit breaker 5RY (213/A11). (2)In avionics compartment, on RH electronics rack 90VU, on panel 97VU, disconnect electrical connector 168VC-A. (3)Connect the ohmmeter between terminals K and J of connector 168VC and adjust potentiometer 9RY to obtain a resistance of 2.2 kilohms. (4)Connect the ohmmeter between terminals G and H of electrical connector 168VC and adjust potentiometer 7RY to obtain a resistance of 0 ohm.

**ON A/C 102-102,

(5)Not applicable.

**ON A/C 001-101, 103-999,

(5)Connect the ohmmeter between terminals V and W of electrical connector 168VC and adjust potentiometer 93RY to obtain a resistance of 0 ohm.

**ON A/C ALL

(6)Not applicable (7)Connect electrical connector 168VC-A on panel 97VU. (8)Remove safety clip and tag and close circuit breaker 5RY on panel 22VU.

C. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that the forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (3)In avionics compartment, in RH electronics rack 90VU, remove fireproof panel protecting shelf 96VU.


(4)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU FLT DECK CALLS 1LN 112/B 1 22VU RECORDERS/VOICE/CONTRL RELAY 5RK 204/K11 22VU AUDIO SYS/CONTRL PNL/1ST 16RL 209/E 7 OBSV & AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12 22VU PUBLIC ADDRESS 5RY 213/A11 22VU TAPE REPRODUCER 115VAC 105RY 209/E 2 22VU TAPE REPRODUCER 28VDC 106RY 209/E 1 129VU PASSENGER SIGNS/FASTEN BELT 28WJ 902/B 5 129VU PASSENGER SIGNS/RETURN TO YR SEAT 29WJ 902/B 6 129VU PASSENGER SIGNS/RETURN TO YR SEAT 30WJ 902/B 7 129VU PASSENGER SIGNS/NO SMOKING 31WJ 902/B 8 800VU CALL-SYSTEM/ATTN 10LN 800VU CALL-SYSTEM/LAVATORY 14LN 800VU CALL-SYSTEM/PASS 15LN 811VU CALL-SYSTEM/LAVATORY 19LN 811VU CALL-SYSTEM/PASSENGER 95LN (5)On panel 26VU - place SEAT BELTS and NO SMOKING switches in OFF position. (6)On CaptainSs and First OfficerSs control column handwheels - make certain that PTT switches are in intermediate position.

**ON A/C 001-101, 103-999,

(7)On panel 223VU, at Second ObserverSs station - place RADIO-INTPH switch in intermediate position.

**ON A/C 102-102,

(7)Not applicable.

**ON A/C ALL

(8)On CaptainSs, First OfficerSs, Flight EngineerSs First ObserverSs and avionics compartment audio selector panels : - place RAD-INT PTT switches in intermediate position. - engage INT transmission square key

**ON A/C 102-102,



**ON A/C ALL

- engage all reception push-buttons

**ON A/C 001-100, 102-102,

- make certain that VOICE push-button is disengaged

**ON A/C 103-104, 107-999,

- make certain that VOICE ONLY push-button is disengaged

**ON A/C 103-104,


**ON A/C ALL

(9)On CaptainSs, First OfficerSs, Flight EngineerSs, First and Second ObserverSs jack boxes - connect a boomset to interphone connection receptacle

**ON A/C 001-100, 102-102, 107-999,


**ON A/C ALL

(10)In avionics compartment, on LH electronics rack 80VU - connect a headset to the associated jack - connect a hand microphone to the associated interphone connection receptacle. (11)On panel 29VU - place ESS SYS-OFF switch in ESS SYS position. (12)At PurserSs station, make certain that ON push-button is disengaged off.

D. Test (1)Test of loudspeakers ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. In electronics rack 90VU, on - Check that a 600Hz test signal shelf 96VU, place TEST TONE-OFF- is received at each loudspeaker CAL rotary selector switch in passenger compartment, at located on front panel of Cabin AttendantsS station and in passenger address amplifier 1RY lavatories in TEST TONE position.

2. Place rotary selector switch in OFF position


(2)Test of announcement made by the crew members ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel at each crew memberSs station and in avionics compartment - engage PA transmission square key.

- disengage PA reception push- button and turn integral potentiometer clockwise

2. At CaptainSs station, - Check that the message is received speak into boomset microphone at all passenger compartment, Cabin while operating associated PTT Attendant station and lavatory switch. loudspeakers. - Check reception at boomset at all other crew membersS stations and also operation of volume potentiometer integral with reception push-button.

3. Repeat tests from : - First OfficerSs station - Flight EngineerSs station - First ObserverSs station - Second ObserverSs station - Avionics compartment station. NOTE : The Second ObserverSs station is dependent upon PA ____ selection and audio volume adjustment made on Flight EngineerSs audio selector panel. (3)Test of announcements made by Cabin Attendants ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs - Check reception at passenger com- station, make an announcement partment and lavatory loudspeakers. on passenger address (PA) system - Check that the announcement is not received at Cabin AttendantsS loudspeakers

2. Repeat tests from the other Cabin AttendantsS stations where transmission on passenger address system is possible.

(4)Test of transmission priorities


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make an announcement from one - Check that the transmission heard Cabin AttendantSs station at passenger compartment loudspeakers is that from crew memberSs 2. At the same time, make an announ- station and not that from Cabin cement from one crew memberSs AttendantsS station station.

(5)Test of Crew-to-Cabin Attendant call circuits ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 32VU - press one of the following - Check that the HI/LO tone is recei- indicator lights ved at the Cabin Attendant station - FWD ATTND CALL Loudspeakers - MID ATTND CALL - AFT ATTND CALL

- press PURS CALL indicator - Check that the HI/LO tone is recei- light ved at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- press ALL ATTND CALL push- - Check that the HI/LO tone is recei- button ved at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

(6)Test of Cabin Attendant-to-Cabin Attendant call circuits. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At each Cabin AttendantSs sta- - Check that the HI/LO tone is re- tion, press push-button to call ceived at Cabin AttendantsS loud- other Cabin AttendantSs station speakers.

(7)Test of passenger-to-Cabin Attendant call circuits ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Press one of the Cabin Attendant - Check that the HI tone is received call push-buttons located in pas- at Cabin Attendant station loud- senger compartment. speakers.

(8)Test of passenger sign circuits


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- On panel 26VU - place SEAT BELTS-OFF switch - Check that the LO tone is received in SEAT BELTS position. at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- place SEAT BELTS-OFF switch - Check that the LO tone is received in OFF position. at passenger compartment, Cabin Attendant station and lavatory loudspeaker.

- place NO SMOKING-OFF switch - Check that the LO tone is received in NO SMOKING position at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

- place NO SMOKING-OFF switch - Check that the LO tone is received in OFF position at passenger compartment, Cabin Attendant station and lavatory loudspeakers.

(9)Operational test of pre-recorded music and announcement tape reproducer. (a)Broadcasting of pre-recorded announcements NOTE : Before starting broadcast of an announcement, make ____ certain that the selected track is impressed. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs station, on tape reproducer control unit - press key A to select magazine - Key A comes on

- press key 2 to select track 2 - Key 2 comes on

- press ANN push-button, making - Check that the announcement certain first that the status broadcast at the passenger compart- light at the LH side of key A ment and lavatory loudspeakers is is extinguished. that recorded on the selected track. - Check that the associated status light is on

- press CANCEL push-button - the announcement in progress is stopped - the status light is on


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 2. Repeat tests for magazines B and C.

(b)Broadcasting of emergency announcement - Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU PASSENGER OXYGEN/ACTUATION 2WR 203/L 3 22VU PASSENGER OXYGEN/ACTUATION 3WR 203/L 4 22VU PASSENGER OXYGEN/ACTUATION 4WR 203/L 5 22VU PASSENGER OXYGEN/ACTUATION 5WR 203/L 6 22VU PASSENGER OXYGEN/ACTUATION 6WR 203/L 7 22VU PASSENGER OXYGEN/ACTUATION 7WR 203/L 8 22VU PASSENGER OXYGEN/ACTUATION 21WR 203/L 9 22VU PASSENGER OXYGEN/ACTUATION 22WR 203/L10 22VU PASSENGER OXYGEN/ACTUATION 23WR 203/L11 - Make certain that the following circuit breaker is closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU PASSENGER OXYGEN/CONTRL & WARN 1WR 203/L12 - Test of emergency announcement priority over other announcements ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Select and start any announcement - The announcement is received at from magazine B or C. passenger compartment and lavatory loudspeakers.

2. On panel 63VU, hold AUTO-MAN - Check that the emergency announ- O/RIDE switch in MAN O/RIDE cement is received at all passenger position and release. compartment and lavatory loudspeakers.

3. On tape reproducer control unit - press CANCEL pushbutton - Check that the emergency announcement is stopped.

4. On panel 63VU - press PASSENGER OXYGEN/RESET pushbutton switch to reset oxygen system.

(c)Broadcasting of music to passengers - On electronics rack 90VU, on prerecorded music and announcement tape reproducer, make certain that rotary selector switch is in A position.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs - ON push-button comes on station - engage ON push-button

- turn volume potentiometer - check that music is correctly re- clockwise to obtain normal ceived at passenger compartment audio level. and lavatory loudspeakers.

(d)Test of priorities - Priority of Cabin AttendantsS announcements over pre-recorded announcements. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On tape reproducer control unit, - the announcement is received at select a pre-recorded announce- passenger compartment and lavatory ment. loudspeakers.

2. Transmit a message from forward - Check that the message from Cabin Cabin AttendantSs station. AttendantSs station replaces the announcement at the loudspeakers.

3. Press CANCEL push-button.

- Priority of pre-recorded announcements over music ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At forward Cabin AttendantSs - Music is received at passenger station compartment and lavatory loudspeakers. - engage ON push-button

- on tape reproducer control - Check that the selected unit, select an announcement announcement replaces music at the by pressing the appropriate loudspeakers and that music is keys. resumed at the end of the announcement.

- disengage ON push-button - ON push-button goes off.

- Remove safety clips and tags and close circuit breakers 2WR, 3WR, 4WR, 5WR, 6WR, 7WR, 21WR, 22WR and 23WR

(10)Variations in passenger address audio level


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. While making an announcement - Check that the audio level from crew memberS station, increases in passenger compartment, open circuit breaker 5RK Cabin AttendantsS stations and on panel 22VU lavatory loudspeakers

2. Close circuit breaker 5RK - The audio level decreases in passenger compartment, Cabin AttendantsS stations and lavatory loudspeakers

E. Close-Up (1)On audio selector panel at each crew memberSs station and in avionics compartment :

**ON A/C 001-101, 103-999,


**ON A/C 102-102,


**ON A/C ALL

- engage PA reception push-button (2)In avionics compartment, on LH electronics rack 80VU - disconnect hand microphone and headset. (3)On panel 29VU - place ESS SYS-OFF switch in OFF position. (4)In avionics compartment, on RH electronics rack 90VU, install fireproof panel on shelf 96VU. (5)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (6)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

R **ON A/C 108-108,

After AMP LH23-003 *

4. Maintenance Practices * _____________________

A. General * A random noise test is provided. This test is used whenever a definitive * test is required for the overall system or for any part of the system. * It provides a calibrated input to the system and a measurement of the * audio output to the speakers. *


B. Equipment and Materials * (1)Random noise generator Model 543-1, Pacific Electro Dynamics. * (2)Sound level meter - Bruel/Kjaer 2205 (or equivalent). *

C. Prepare for Test * (1)Provide power to passenger address system (Ref. 23-11-00 adjustment *

test). * (2)Calibrate Random noise generator as follows : * (a)Set noise generator POWER/PTT switch to ON. * (b)Set noise generator SIGNAL/SPEAKER switch to SPEAKER. * (c)Switch on sound level meter and preset it as follows : * Scala - 100 db * Curve - B * Damping - Slow * (d)Press sound level meter microphone against random noise generator * speaker, and adjust AUDIO ADJ level control on noise generator to * read 100 db + 1 on the sound level meter. *

D. AUDIO LEVEL Test * (1)Test from purser station * (a)Insert microphone of Purser station handset into noise generator * speaker mouth, select Passenger Address function on Purser panel and * activate handset push to talk. * (b)Closely couple sound level meter to a speaker. * (c)Move sound level meter across speaker to obtain maximum reading - * Check that output of speaker is as follows : * Seat rows 1 to 11 = 100 db ± 4 * Seat rows 12 to 23 = 102 db ± 4 * Seat rows 24 to 32 = 104 db ± 4 * Seat rows 33 to 38 = 106 db ± 4 * Lavatories = 96 db ± 4 * FWD attendant and galleys = not applicable. * (d)Repeat steps (b) (c) for other speakers to be checked * (2)Repeat steps (a) to (c) on one speaker from : * (a)Attendant station 2G * (b)Attendant station 4G * (3)Repeat steps (a) to (c) on one speaker from one cockpit microphone - * Valves to be found are : * Seat rows 1 to 11 = 90 db ± 4 * Seat rows 12 to 23 = 92 db ± 4 * Seat rows 24 to 32 = 94 db ± 4 * Seat rows 33 to 38 = 96 db ± 4 * Lavatories = 86 db ± 4 * FWD attendant and galleys = 95 db ± 4 (auxiliary amplifier) * (a)Place passenger address into flight mode (Ref. 23-31-00 adjustment/ * test = Pull breaker 6Recorder Voice Control Relay on 22VU panel). * (b)From any speaker check that sound level meter indication increases * by 6 db ± 2. * (c)Place passenger address system into ground mode. * (4)If valves in steps above are not met : *


Replace defective loudspeakers. * Check 9RY and 7RY potentiometers setting (Ref. 23-31-00 system test - * 9RY/2.2K - 7RY/0Ω) * Replace P.A amplifier. * (5)Disconnect test equipment *


TAPE REPRODUCER CONTROL UNIT - REMOVAL/INSTALLATION ___________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- Circuit Breaker Safety Clips

R 2. Procedure (Ref. Fig. 401 ) _________

A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU TAPE REPRODUCER 115VAC 105RY 209/E 2 22VU TAPE REPRODUCER 28VDC 105RY 209/E 1

B. Removal (1)Press push-buttons (6) to open housing (5). (2)Remove adjusting knob (7). (3)Remove screws (3) and remove plate (2). (4)Disconnect electrical connector (8). (5)Remove screws (1) attaching tape reproducer control unit to structure and remove control unit (4). (6)Cap electrical connectors.

C. Installation (1)Clean and inspect control unit interface. (2)Uncap electrical connectors and check that they are in correct condition. (3)Install tape reproducer control unit (4) on structure with screws (1). (4)Connect electrical connector (8). (5)Install plate (2) with screws (3). (6)Install adjusting knob (7). (7)Close and latch housing (5). (8)Remove safety clips and tags and close the circuit breakers 150RY and 160RY

D. Test On tape reproducer control unit select then broadcast a pre-recorded announcement and check that selected announcement is heard in passenger compartment.

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


Tape Reproducer Control UnitR Figure 401


PASSENGER ADDRESS AMPLIFIER - REMOVAL/INSTALLATION __________________________________________________



A. Job Set-Up (1)Open, safety and tag the following circuit breaker : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU PUBLIC ADDRESS 5RY 213/A11

(2)Unlock Dzus fasteners and remove shelf 96VU protective panel.

B. Removal (1)Loosen locknut (3) until stud (4) is released. (2)Pull out amplifier (6) from mounting (5).

C. Installation (1)Clean and inspect amplifier interface. (2)Make certain that electrical connectors are in correct condition. (3)Push in amplifier on mounting and make certain that connector (1) is fully engaged is connector (2). (4)Tighten locknut (3) on stud (4). (5)Remove safety clip and tag and close circuit breaker 5RY

D. Tests Make an announcement from one Cabin AttendantSs station and check that it is heard at passenger compartment loudspeakers.

E. Close-Up (1)Install protective cover on shelf 96VU and attach with Dzus fasteners. (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


Passenger Address AmplifierR Figure 401

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TAPE REPRODUCER - REMOVAL/INSTALLATION ______________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- Circuit Breaker Safety Clips Blanking Caps


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU TAPE REPRODUCER 115VAC 105RY 209/E 2 22VU TAPE REPRODUCER 28VDC 106RY 209/E 1

B. Removal (1)Loosen nuts (5) to free tape reproducer studs (4). (2)Remove tape reproducer from mounting tray (6). (3)Remove tape reproducer.

C. Installation (1)Clean and inspect tape reproducer interface. (2)Make certain that electrical connectors (1) and (2) are in correct condition. (3)Position tape reproducer on mounting tray and slide it to bottom of rack. (4)Tighten nuts (5) on tape reproducer studs (4). (5)Remove safety clips and tags and close circuit breakers 105RY and 106RY.

D. Test On tape reproducer control unit, select then broadcast a pre-recorded announcement. Check that selected announcement is heard in passenger compartment.

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


Tape ReproducerR Figure 401

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PASSENGER ENTERTAINMENT (MUSIC) - DESCRIPTION AND OPERATION ___________________________________________________________

1. General _______ The passenger entertainment system (PES) provides stereo and monaural music programs via the passenger control unit installed at each seat. The facility is also provided to play boarding music over the passenger address (PA) speaker system.

2. Component Location __________________ ------------------------------------------------------------------------------- ITEM NAME PANEL ZONE ACCESS DOOR -------------------------------------------------------------------------------

3MK1 Pushbutton Switch - BGM 1 746VU 3MK2 Pushbutton Switch - BGM 2 746VU 3MK3 Pushbutton Switch - BGM 3 746VU 3MK4 Pushbutton Switch - BGM 4 746VU 3MK5 Pushbutton Switch - PES ON/OFF 746VU 3MK6 Pushbutton Switch - MUSIC ON/OFF 746VU 4MK Potentiometer - Volume Control 746VU

8MK Amplifier 95VU

**ON A/C 101-101,

10MK Tape Reproducer 95VU

**ON A/C 001-100, 102-108,

10MK Tape Reproducer - Galley 1 222

**ON A/C ALL

11MK Circuit Breaker - PES 800VU

**ON A/C 101-101,

13MK Circuit Breaker - PES 800VU


------------------------------------------------------------------------------- ITEM NAME PANEL ZONE ACCESS DOOR -------------------------------------------------------------------------------

**ON A/C ALL

Passenger Control Units (Ref. corresponding figure) 200 806MK Rectifier Unit 132 807MK A.C. Power Relay 132 43XC Switch - RADIO MASTER SUPPLY/ 29VU ESS SYS 44XC Circuit Breaker - ESS RADIO 22VU

53XC Control Relay 101VU

**ON A/C 001-100, 102-108,

(Ref. Fig. 001 )

**ON A/C 101-101,

(Ref. Fig. 002 )

**ON A/C ALL

(Ref. Fig. 003 )

(Ref. Fig. 004 )


Passenger Entertainment Figure 001

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Passenger Control Units and Junction Boxes Figure 004

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3. Description ___________

A. The music system, which is controlled from panel 746VU, comprises individually selected programs played over the passenger headsets and boarding music played over the PA speaker system. (1)The PES music is played back from a tape reproducer via an audio amplifier into the passenger control units installed at each seat. (a)Each passenger control unit consists of a receptacle for a headset connector, a 12-position program selector switch with numerical display and a volume control switch with associated dot display. (2)The tape reproducer is a sixteen-channel, endless loop cartridge type. The sixteen channels are contained on four tape cartridges and four of the channels are used for boarding music (BGM). (a)Any one of the four BGM programs can be selected by pressing one of the ganged selector switches on 746VU. (3)The music system is overridden whenever a PA announcement is made. 4. Operation _________

A. Operation of passenger entertainment system

**ON A/C 101-101,

(1)AC power for the tape reproducer and audio amplifier is supplied via a circuit breaker and AC power relay from the 115V AC busbar 101XP or 110XP. DC power is supplied via a circuit breaker from the 28V DC busbar 102PP.

**ON A/C 001-100, 102-108,

(1)Power for the tape reproducer and audio amplifier is provided, via a circuit breaker from the 115VAC busbar 110XP and the 28V DC busbar 102PP.

**ON A/C ALL

(2)With the PES and ESS RADIO circuit breakers closed and the RADIO MASTER SUPPLY switch in the position ESS SYS, 115VAC is applied to the rectifier unit. The AC power relay is energized, supplying the audio amplifier and tape reproducer with 115VAC. (3)With the applicable PA system circuit breakers closed, on pressing push- button switch PES, the tape reproducer is started and music is played at each passenger headset. (4)Passengers may select various music programs by rotating the thumbwheel of the 12-position selector switch in the seat control unit. Volume con-


trol is obtained by rotating the knurled wheel.

B. Operation of boarding music system (1)On pressing one of the pushbutton switches marked BGM, the tape reproducer is started and one of the BGM channels is selected. A ground return is completed for the PA amplifier and music is played over the PA speaker system. The four BGM selector switches are ganged and provide the necessary four logic inputs to the tape reproducer in order to select all the BGM music programs. (2)Audio output level may be adjusted by the volume control potentiometer on control unit 746VU.

NOTE : Any PA announcement overrides the music programs played over ____ the passenger headsets or PA speaker system.

**ON A/C 001-100, 102-108,

(Ref. Fig. 005 )

**ON A/C 101-101,

(Ref. Fig. 006 )



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Passenger Entertainment - Block Diagram Figure 006

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PASSENGER ENTERTAINMENT - (MUSIC) _________________________________ ADJUSTMENT/TEST _______________


A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200 V, 400 Hz (2) Acoustic Headset (3) Tape Cassettes for Tape Reproducer Referenced Procedures - 21-21-00, P. Block 501 Distribution/Extraction - Forward Fuselage Equipment - 23-31-00, P. Block 501 Passenger Address - 23-41-00, P. Block 501 Service Interphone - 24-41-00, P. Block 301 External Power - 33-23-40, P. Block 501 Call System

B. Procedure (1)Job Set-Up (a)Connect electrical ground power unit and energize aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that switch RADIO MASTER SUPPLY ESS SYST on panel 29VU is in position ESS SYST. (c)Make certain that forward services ventilation system is operating (Ref. 21-21-00, P. Block 501). (d)Make certain that service interphone system is operating (Ref. 23-41-00, P. Block 501). (e)Make certain that passenger address system is operating (Ref. 23-31-00, P. Block 501). (f)Make certain that the following circuit breakers are closed: ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 800VU PES 11MK D 7

R **ON A/C 101-104, 108-999,

800VU PES 13MK D 8

**ON A/C 001-100, 105-107,

(2)Test (a)Test of Boarding Music


-------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------- 1 At tape reproducer: _ - install a 4-track tape cassette in slot 3. 2 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM1, ro- - verify that boarding music played tate volume control 4MK clockwise over the PA speakers varies smooth- thru complete range. ly in volume from minimum to maximum. 3 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM2, ro- - verify that the second music pro- tate volume control 4MK counterclock- gram is played over the PA speakers wise thru complete range. and varies smoothly in volume from maximum to minimum. 4 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM3, ro- - verify that the third music pro- tate volume control 4MK clockwise gram is played over the PA speakers thru complete range. and varies smoothly in volume from minimum to maximum. 5 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM4, ro- - verify that the fourth music pro- tate volume control 4MK counterclock- gram is played over the PA speakers wise then clockwise thru complete and varies smoothly in volume from range. maximum to minimum and back to maximum. 6 On panel 800VU: Passenger compartment: _ - open circuit breaker 11MK. - boarding music goes off. 7 On panel 800VU: Passenger compartment: _ - close circuit breaker 11MK. - boarding music is played over PA speakers. 8 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM4. - boarding music goes off. 9 On panel 746VU: Passenger compartment: _ - press pushbutton switch BGM4, ro- - verify that boarding music played tate volume control 4MK counter- over PA speakers varies smoothly clockwise thru complete range. from maximum to minimum. 10 On panel 746VU: Passenger compartment: __ - press pushbutton switch BGM4. - boarding music goes off.

(b)Test of Seat Music

**ON A/C 101-104,

(2)Test (a)Test of Boarding Music


-------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------- 1 At tape reproducer: _ - install a 4 track tape cassette in slot 3. 2 On panel 746VU: On panel 746VU: _ - press pushbutton switch BGM 1, ro- - integral light in selected push- tate volume control 4MK clockwise button switch BGM1 comes on. thru complete range. Passenger compartment: - verify that boarding music played over the PA speakers varies smoothly in volume from minimum to maximum. 3 On panel 746VU: On panel 746VU: _ - press pushbutton switch BGM2, ro- - integral light in pushbutton tate volume control 4MK counterclock- switch BGM1 goes off. wise thru complete range. - integral light in pushbutton switch BGM2 comes on. Passenger compartment: - verify that the second music program is played over the PA speakers and varies smoothly in volume from maximum to minimum. 4 On panel 746VU: On panel 746VU: _ - press pushbutton switch BGM3, ro- - integral light in pushbutton tate volume control 4MK clockwise switch BGM2 goes off. thru complete range. - integral light in pushbutton switch BGM3 comes on. Passenger compartment: - verify that the third music program is played over the PA speakers and varies smoothly in volume from minimum to maximum. 5 On panel 746VU: On panel 746VU: _ - press pushbutton switch BGM4, ro- - integral light in pushbutton tate volume control 4MK counterclock- switch BGM3 goes off. wise then clockwise thru complete - integral light in pushbutton range. switch BGM4 comes on. Passenger compartment: - verify that the fourth music program is played over the PA speakers and varies smoothly in volume from maximum to minimum and back to maximum. 6 On panel 800VU: Passenger compartment: _ - open circuit breaker 11MK. - boarding music goes off. 7 On panel 800VU: Passenger compartment: _ - close circuit breaker 11MK. - boarding music is played over PA speakers. 8 On panel 746VU: On panel 746VU: _ - press pushbutton switch BGM4. - integral light in pushbutton


-------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------- switch BGM4 goes off. Passenger compartment: - boarding music goes off.

**ON A/C 101-106,

(b)Test of Seat Music ------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------

R **ON A/C 001-107,

1 At tape reproducer: _ - install a stereo tape cassette in slot 1. 2 On panel 746VU: _ - press pushbutton switch PES ON/OFF. 3 At each passenger control unit: At each passenger control unit: _ - connect headset, select channel 3 and - verify over headset that the two channel 4, at both selections different music programs played on rotate volume control thumbwheel thru channels 3 and 4 vary smoothly in complete range. volume. 4 On panel 800VU: At passenger control units: _ - open circuit breaker 11MK. - music programs go off. 5 At tape reproducer: _ - install a stereo tape cassette in slot 2. 6 On panel 800VU: _ - close circuit breakers 11MK. 7 At each passenger control unit: At each passenger control unit: _ - connect headset, select channel 5 - verify over headset that the two and channel 6 at both selections different music programs played rotate volume control thumbwheel on channels 5 and 6 vary smoothly thru complete range. in volume. 8 On panel 800VU: At passenger control units: _ - open circuit breaker 11MK. - music programs go off. 9 At tape reproducer: _ - install a mono tape cassette in slot 4. 10 On panel 800VU: __ - close circuit breaker 11MK. 11 At each passenger control unit: At each passenger control unit: __ - connect headset, select channel 7 - verify over headset that the and channel 8, at both selections two different music programs rotate volume control thumbwheel played on channels 7 and 8 thru complete range. vary smoothly in volume. 12 On panel 800VU: At passenger control units: __ - open circuit breaker 11MK. - music programs go off.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 13 At tape reproducer: __ - install a mono tape cassette. in slot 3. 14 On panel 800VU: __ - close circuit breaker 11MK. 15 At any attendant call station: At passenger control units: __ - remove handset, press P.A. push- - over headset, music program button press PTT pushbutton and goes off and on channel 1 make an announcement. thru 8 and 10 announcement comes on. 16 At pilots station: At passenger control units: __ - while announcement is being made - over headset, announcement from from attendantSs call station, attendantSs station goes off remove PA microphone, press PTT and announcement from pilots pushbutton and make an station come on. announcement. 17 At pilots station: At passenger control units: __ - release PTT pushbutton and replace - over headset, announcement from PA microphone. pilotSs station goes off and announcement from attendantSs station comes on. 18 At attendant call station: At passenger control units: __ - release PTT pushbutton, release - over headset, announcement PA pushbutton and replace handset. from attendants station goes off and music program comes on. 19 On panel 746VU: At passenger control units: __ - press pushbutton switch PES ON/OFF. - music programs go off.

R **ON A/C 108-999,

(2)Test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- (a)At tape reproducer: - install a stereo tape cassette in slot 3. (b)On panel 746VU: - press pushbutton switch PES ON/OFF. (c)At each passenger control unit: At each passenger control unit: - connect headset, select channel 4, - verify over headset that music rotate volume control thumbwheel thru program played on channel 4 varies complete range. smoothly in volume. (d)On panel 800VU: - open circuit breaker 11MK. (e)At tape reproducer: - install stereo/mono tape cassette in slot 1.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- (f)On panel 800VU: - close circuit breaker 11MK. (g)At each passenger control unit: At each passenger control unit: - connect headset, select channel 6, - verify over headset that the channel 7 and channel 3 and at three different music programs each selection rotate volume con- played over channels 6, 7, and 3 trol thru complete range. vary smoothly in volume. (h)On panel 800VU: At passenger control units: - open circuit breaker 11MK. - music goes off. (j)At tape reproducer: - install a stereo tape cassette in slot 2. (k)On panel 800VU: - close circuit breaker 11MK. (l)At each passenger control unit: At each passenger control unit: - connect headset, select channel 1 - verify over headset that the and channel 2 and at both selec- two different music programs tions rotate volume control thru played over channels 1 and 2 vary complete range. smoothly in volume. (m)On panel 800VU: At passenger control units: - open circuit breaker 11MK. - music goes off. (n)At tape reproducer: - install a stereo tape cassette in slot 4. (p)On panel 800VU: - close circuit breaker 11MK. (q)At each passenger control unit: At each passenger control unit: - connect headset, select channel 5 - verify over headset that the and rotate volume control thru com- music program played on channel 5 plete range. varies smoothly in volume. (r)At any attendantSs call station: At passenger control unit: - remove handset, press PA pushbutton, - over headset, music program goes press PTT pushbutton and make an off and the announcement comes on. announcement. (s)At pilotSs station: At passenger control units: - while announcement is being made - over headset, announcement from from the attendantSs call station, attendantSs call station goes off remove PA microphone, press PTT and announcement from pilotSs sta- pushbutton and make an announce- tion comes on. ment. (t)At pilotSs station: At passenger control units: - release PTT pushbutton and replace - over headset, announcement from PA microphone. pilotSs station goes off and announcement from attendantSs call station comes on. (u)At attendantSs call station: At passenger control units: - release PTT pushbutton, release PA - over headset, announcement from pushbutton, and replace handset. attendantSs call station goes off and music program comes on.

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------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- (v)On panel 746VU: At passenger control units: - press pushbutton switch PES ON/OFF. - over headset, music programs go off.

R **ON A/C ALL

(3)Close-Up (a)De-energize aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (b)De-activate forward service ventilation system (Ref. 21-21-00, P. Block 501). (c)De-activate service interphone system (Ref. 23-41-00, P. Block 501). (d)De-activate passenger address system (Ref. 23-31-00, P. Block 501).


AUDIO REPRODUCER - REMOVAL/INSTALLATION _______________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Caps Referenced Procedure - 23-33-00, P. Block 501 Passenger Entertainment - (Music)


A. Job Set-Up (1)Open, safety and tag the following circuit breakers: ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 800VU PES 11MK D 7

(2)Open access door 121BL.

B. Removal (1)Unscrew knurled nuts (2) and free lugs (1) of reproducer. (2)Withdraw reproducer from mount (3). (3)Remove reproducer (5). (4)Cap electrical connectors (4).

C. Installation (1)Clean and inspect reproducer interface. (2)Remove blanking caps from electrical connectors (4). Check for correct condition of connectors. (3)Position reproducer on mount and fully push. (4)Position knurled (2) and tighten onto lugs (1) of reproducer. (5)Remove safety clip and tag and close circuit breakers.

D. Test Carry out an operational test of Passenger Entertainment - (Music) (Ref. 23-33-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close access door 121BL.

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Audio Reproducer Figure 401

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AMPLIFIER - REMOVAL/INSTALLATION ________________________________



A. Job Set-Up (1)Open, safety and tag the following circuit breaker : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 800VU PES 11MK D 7


B. Removal (1)Unscrew knurled nuts (2) and free lugs (1) of amplifier. (2)Withdraw amplifier from mount (3). (3)Remove amplifier (5). (4)Cap electrical connectors (4).

C. Installation (1)Clean and inspect amplifier interface. (2)Remove blanking caps from electrical connectors (4). Check for correct condition of connectors. (3)Position amplifier on mount and fully push. (4)Position knurled nuts (2) and tighten onto lugs (1) of amplifier. (5)Remove safety clip and tag and close circuit breakers. NOTE : Before the installation of a new amplifier, the cover of the box ____ has to be removed and the switch S1 inside the amplifier has to be closed.

D. Test Carry out an operational test of Passenger Entertainment - (Music) (Ref. 23-33-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close access door 121BL.

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Power AmplifierR Figure 401

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MAIN MULTIPLEXER - REMOVAL/INSTALLATION _______________________________________



A. Job Set-Up (1)Open, safety and tag the following circuit breaker : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 800VU PES 11MK D 7


B. Removal (1)Unscrew knurled nut (2) and free lug (1) of multiplexer. (2)Withdraw multiplexer from mount (3). (3)Remove multiplexer (5). (4)Cap electrical connectors (4).

C. Installation (1)Clean and inspect amplifier interface. (2)Remove blanking caps from electrical connectors (4). Check for correct condition of connectors. (3)Position multiplexer on mount and fully push. (4)Position knurled nuts (2) and tighten onto lugs (1) of multiplexer. (5)Remove safety clip and tag and close circuit breaker 11MK.

D. Test Carry out an operational test of Passenger Entertainment - (Music) (Ref. 23-33-00, P. Block501)

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close access door 121BL.


Main Multiplexer Figure 401


INTERPHONE - DESCRIPTION AND OPERATION ______________________________________

1. General _______ The service interphone is a means of voice communication between : - the crew members and cabin attendants - the cabin attendants - the crew members and ground personnel at the ground service jacks - the cabin attendants and ground personnel at the ground service jacks. A ground crew call system is available for use by the crew members in order to call the ground personnel.

R **ON A/C 107-107, 109-999,

(Ref. Fig. 001 )

**ON A/C 103-104,

(Ref. Fig. 002 )

R **ON A/C 001-102, 105-106, 108-108,

(Ref. Fig. 003 )


Service Interphone - Block Diagram Figure 001

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HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-102, 105-106, 108-108, K 23-40-00 K K K K Page 4 K K JAS Oct 01/92

SERVICE INTERPHONE - DESCRIPTION AND OPERATION ______________________________________________

1. General _______

The service interphone allows : - In flight, service interphone communications between crew members and Cabin Attendants. - On the ground, interphone communications, for maintenance purposes, between crew members, Cabin Attendants and the various parts of the aircraft fitted with ground service jacks.


(Ref. Fig. 001 ) (Ref. Fig. 002 ) (Ref. Fig. 003 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 20RL Circuit Breaker AUDIO SYS/INTPH 22VU 210 AMPLI/SERV 5RY Circuit Breaker - PUBLIC ADDRESS 22VU 210 21RL Amplifier - Service Interphone 80VU 121 121BL 22RL Relay 80VU 121 121BL 23RL Switch - SERVICE INTPH ON-OFF 67VU 212 31RL Jack - Ground Service (inside the 110 radome, below the radar antenna) 32RL Jack - Ground Service (avionics 121 121BL compartment, near the inner ladder) 33RL Jack - Ground Service (in ground 108VU 122 122AR power receptacle housing) 35RL Jack - Ground Service (forward 132 811 cargo compartment, inside compartment, near entrance door) 36RL Jack - Ground Service (forward - 136 136AR air-conditioning compartment, inside compartment, RH side, near access door) 37RL Jack - Ground Service (front part 143 147GZ of main landing gear compartment, internal connection, on air conditioning system fairing) 38RL Jack - Ground Service (air-condi- 144 148GZ tioning compartment below wing spar box, inside air-conditioning compartment) 39RL Jack - Ground Service (hydraulic 147 734 compartment and L/G well, LH side) 40RL Jack - Ground Service (end of LH 591 591AB wing) 41RL Jack - Ground Service (end of RH 691 691AB wing)


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 42RL Jack - Ground Service (rear cargo 152 812 compartment, internal connection, in front of compartment, near access door) 43RL Jack - Ground Service (rear cargo 862VU 162 813 compartment, internal connection, in rear of compartment, near entrance door) 44RL Jack - Ground Service (rear fuse- 312 312AR lage) 45RL Jack - Ground Service (rear fuse- 313 313AL lage, internal connection, LH side) Jack - Ground Service (LH engine) 433 Jack - Ground Service (RH engine) 443 88RL Handset - Telephone 878VU 221 89RL Handset - Telephone 882VU 242 90RL Handset - Telephone 729VU 231 91RL Handset - Telephone 880VU 241 111RL Handset - Telephone 726VU 262 112RL Handset - Telephone 727VU 261 113RL Relay - Reception Cut-Off 890VU 233 114RL Relay - Reception Cut-Off 882VU 242 115RL Relay - Reception Cut-Off 726VU 262 116RL Relay - Reception Cut-Off 880VU 241 117RL Handset - Telephone 730VU 232 111RY Relay - Reception Cut-Off 878VU 221 112RY Relay - Switching, PA-INTPH 878VU 221 113RY Relay - Reception Cut-Off 890VU 233 114RY Relay - Switching, PA-INTPH 890VU 233 115RY Relay - Reception Cut-Off 727VU 261 116RY Relay - Switching, PA-INTPH 727VU 261 305LN Switch - Telephone Handset 878VU 221 306LN Switch - Telephone Handset 730VU 232 307LN Switch - Telephone Handset 729VU 231 308LN Switch - Telephone Handset 882VU 242 309LN Switch - Telephone Handset 880VU 241 310LN Switch - Telephone Handset 726VU 262 311LN Switch - Telephone Handset 727VU 261


Service Interphone - Component Location in Flight Compartment and in Avionics Compartment Figure 001 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 107-107, 109-999, K 23-41-00 K K CONF. 01 K K Page 3 K K JAS Oct 01/92

Service Interphone - Location of Ground Service Jacks Figure 002


Service Interphone - Component Location in Passenger Compartment Figure 003



A. The interphone system includes : (1)One service interphone amplifier 21RL which amplifies microphone audio signals and supplies power to energize the microphones. (2)Sixteen ground service jacks which enable on the ground voice communications between the various parts of the aircraft. (3)One INTPH ON-OFF switch 23RL connected to relay 22RL enabling connection of the various ground service jacks to the service interphone amplifier. (4)One circuit breaker 20RL supplying amplifier 21RL with 28VDC power. (5)Not applicable (6)Seven Cabin AttendantsS stations (a)Each station is equipped with : - one handset connecting plug - one telephone handset switch - one telephone handset - one reception cut-off relay (b)The PURSER, ATTND 5 and ATTND 9 stations are equipped with an additio- nal PA-INTPH switching relay to allow broadcasting of announcements to passengers. (7)One circuit breaker 5RY which supplies the relays at Cabin AttendantsS stations with 28VDC power.



A. Service Interphone Amplifier 21RL The service interphone amplifier takes the form of a rectangular case connected to the rest of the system by an electrical connector. The service interphone amplifier supplies power to the microphones and amplifies the microphone signals. It is supplied with 28VDC power through the aircraft electrical network. The amplifier has seven microphone inputs and provides two audio outputs - one 125 ohm output which supplies the ground service jack audio system. - one 50 ohm output which supplies the audio system of the various crew membersS and Cabin AttendantsS stations.

B. Ground Service Jacks A ground service jack is a two-pin connector used for connection of a ground service telephone. The ground service jacks located on engine cowls (one per engine) are identified by engine manufacturerSs item number J1-41.

C. SERVICE INTPH ON-OFF switch 23RL This switch enables isolation of ground service jack circuit through the normally open (NO) contacts of relay 22RL, connecting ground service jack circuit to service interphone amplifier 21RL.

D. Not applicable

E. Cabin AttendantSs Station Each Cabin AttendantSs station is composed of : - A service interphone plug and a telephone handset holder - A telephone handset and associated PTT switch - A telephone handset switch enabling to cut off the reception circuit when the telephone handset is put back on the holder.


5. Operation _________ (Ref. Fig. 005 )

A. Service Interphone Amplifier/Ground Service Jack Interconnection All the ground service jacks are mounted in parallel. The microphone input No.7 of amplifier 21RL receives audio frequency signals from ground service jack microphone inputs through the normally open contacts of relay 22RL. The amplifier 125 ohm audio output is applied to all ground service jack reception outputs through the normally open contacts of relay 22RL. Relay 22RL is controlled by SERVICE INTPH ON-OFF switch 23RL and enables isolation of ground service jack circuit in flight.

B. Service Interphone Amplifier, Cabin AttendantsS and Crew MembersS Stations Interconnection The audio frequency signals from the various Cabin AttendantsS stations are applied to the microphone inputs of amplifier 21RL. Amplifier microphone input No.6 is fed with the audio frequency signals from the crew membersS stations through interphone junction box/amplifier 9RL and through the audio selector panel 30RL in avionics compartment. The amplifier 50 ohm audio output is applied to - Cabin AttendantsS reception circuits - Crew membersS reception circuits through interphone junction box/amplifier 9RL - Avionics compartment reception circuit.

C. Interconnection with Passenger Address System Switching relays at PURSER, ATTND 5 and ATTND 9 stations enable interconnection of the telephone handsets and passenger address amplifier 1RY in order to allow broadcasting of announcements in the loudspeakers. Through the normally open contacts of each relay, the microphone, audio and PTT outputs of each telephone handset are connected to the relevant input of passenger address amplifier 1RY.

6. Interface _________ The service interphone system is interconnected with :

A. The Flight Interphone System (Ref. 23-51-00, RL circuit). Enables Crew Members to hear announcements broadcast to passengers.

B. The Passenger Address System (Ref. 23-31-00, RY circuit). Enables Crew Members or Cabin Attendants to broadcast announcements to passengers.

C. The Call System (Ref. 33-23-30, LN circuit). Enables Crew Members or passengers to call Cabin Attendants.


INTENTIONALLY BLANK


Service Interphone - Interconnection - Schematic Figure 005


SERVICE INTERPHONE - DESCRIPTION AND OPERATION ______________________________________________

1. General _______ The service interphone allows : - In flight, service interphone communications between crew members and Cabin Attendants. - On the ground, interphone communications, for maintenance purposes, between crew members, Cabin Attendants and the various parts of the aircraft fitted with ground service jacks.


(Ref. Fig. 001 )

R

(Ref. Fig. 002 ) (Ref. Fig. 003 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 20RL Circuit Breaker AUDIO SYS/INPTH 22VU 210 AMPLI/SERV 5RY Circuit Breaker - PUBLIC ADDRESS 22VU 210 21RL Amplifier - Service Interphone 80VU 121 121BL 22RL Relay 80VU 121 121BL 23RL Switch - SERVICE INTPH ON-OFF 67VU 212 31RL Jack - Ground Service (inside the 110 radome, below the radar antenna) 32RL Jack - Ground Service (avionics 121 121BL compartment, near the inner ladder) 33RL Jack - Ground Service (in ground 108VU 122 122AR power receptacle housing) 35RL Jack - Ground Service (forward 132 811 cargo compartment, inside compartment, near entrance door) 36RL Jack - Ground Service (forward - 136 136AR air-conditioning compartment, inside compartment, RH side, near access door) 37RL Jack - Ground Service (front part 143 147GZ of main landing gear compartment, internal connection, on air conditioning system fairing) 38RL Jack - Ground Service (air-condi- 144 148GZ tioning compartment below wing spar box, inside air-conditioning compartment) 39RL Jack - Ground Service (hydraulic 147 734 compartment and L/G well, LH side) 40RL Jack - Ground Service (end of LH 591 591AB wing)


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 41RL Jack - Ground Service (end of RH 691 691AB wing) 42RL Jack - Ground Service (rear cargo 152 812 compartment, internal connection, in front of compartment, near access door) 43RL Jack - Ground Service (rear cargo 862VU 162 813 compartment, internal connection, in rear of compartment, near entrance door) 44RL Jack - Ground Service (rear fuse- 312 312AR lage) 45RL Jack - Ground Service (rear fuse- 313 313AL lage, internal connection, LH side) Jack - Ground Service (LH engine) 433 Jack - Ground Service (RH engine) 443 88RL Handset - Telephone 878VU 221 89RL Handset - Telephone 882VU 242 90RL Handset - Telephone 729VU 231 91RL Handset - Telephone 880VU 241 111RL Handset - Telephone 726VU 262 113RL Relay - Reception Cut-Off 890VU 233 114RL Relay - Reception Cut-Off 882VU 242 115RL Relay - Reception Cut-Off 726VU 262 116RL Relay - Reception Cut-Off 880VU 241 117RL Handset - Telephone 730VU 232 152RL Handset - Telephone 784VU 233 153RL Relay - Reception Cut-Off 890VU 233 305LN Switch - Telephone Handset 878VU 221 306LN Switch - Telephone Handset 730VU 232 307LN Switch - Telephone Handset 729VU 231 308LN Switch - Telephone Handset 882VU 242 309LN Switch - Telephone Handset 880VU 241 310LN Switch - Telephone Handset 726VU 262 311LN Switch - Telephone Handset 727VU 261


Service Interphone - Component Location in Flight Compartment and in Avionics Compartment Figure 001 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-106, 108-108, K 23-41-00 K K CONF. 02 K K Page 3 K K JAS Oct 01/92

Service Interphone - Location of Ground Service Jacks Figure 002


Service Interphone - Compartment Location in Passenger Compartment Figure 003




A. The interphone system includes : (1)One service interphone amplifier 21RL which amplifies microphone audio signals and supplies power to energize the microphones. (2)Sixteen ground service jacks for communications between the various parts of the aircraft for maintenance purposes, on the ground. A ground connection jack located next to refuel/defuel panel 110VU allows sounds or discussions in the flight compartment to be heard (Area Microphone Ref. 23-71-00). (3)One INTPH ON-OFF switch 23RL connected to relay 22RL enabling connection of the various ground service jacks to the service interphone amplifier. (4)One circuit breaker 29RL supplying amplifier 21RL with 28VDC power. (5)The Cabin AttendantsS stations (a)Each station is equipped with - one handset connecting plug - one telephone handset switch - one telephone handset


- one reception cut-off relay (b)The PURSER,ATTND 5 and ATTND 9 stations are equipped with an additio- nal PA-INTPH switching relay to allow broadcasting of announcements to passengers. (6)One circuit breaker 5RY which supplies the relays at Cabin AttendantSs stations with 28VDC power. (7)One Crew MemberSs station, equipped with : - one service jack - one telephone handset switch - one telephone handset - one reception cut-off relay.



A. Service Interphone Amplifier 21RL The service interphone amplifier takes the form of a rectangular case connected to the rest of the system by an electrical connector. The service interphone amplifier supplies power to the microphones and amplifies the microphone signals. It is supplied with 28VDC power through the aircraft electrical network. The amplifier has seven microphone inputs and two audio outputs - one 125 ohm output which supplies the ground service jack audio system. - one 50 ohm output which supplies the audio system of the various crew membersS and Cabin AttendantsS stations.

B. Ground Service Jacks A ground service jack is a two-pin connector used for connection of a ground service telephone. The ground service jacks located on engine cowls (one per engine) are identified by engine manufacturerSs item number J1-41.

C. SERVICE INTPH ON-OFF switch 23RL This switch enables to isolate ground service jack circuit through the normally open (NO) contacts of relay 22RL, connecting ground service jack circuit to service interphone amplifier 21RL.

D. Cabin AttendantSs Station Each Cabin AttendantSs station is composed of : - A service interphone plug and a telephone handset holder - A telephone handset and associated PTT switch - A telephone handset switch enabling to cut off the reception circuit when the telephone handset is put back on the holder.

5. Operation (Ref. Fig. 005 ) _________ (Ref. Fig. 006 )

A. Service Interphone Amplifier/Ground Service Jack Interconnection All the ground service jacks are mounted in parallel. The microphone input No.7 of amplifier 21RL receives audio frequency signals from ground service jack microphone inputs through the normally open contacts of relay 22RL when SERVICE INTPH ON-OFF switch 23RL is in ON position.

B. Service Interphone Amplifier, Cabin AttendantsS and Crew MembersS Stations Interconnection The audio frequency signals from the various Cabin AttendantsS stations and the five flight interphone microphone inputs (Ref. 23-51-00), fed from crew membersS stations through interphone junction box/amplifier 9RL, are mixed at the input of service interphone amplifier 21RL. The common 50 Ω audio output transmits signals simultaneously to Cabin AttendantsS and Crew MembersS stations.

C. Interconnection with Passenger Address System


Service Interphone - Ground Service Jack Interconnection - Schematic Figure 005


INTENTIONALLY BLANK

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Service Interphone - Cabin AttendantsS Stations Interconnection - Schematic Figure 006 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: 001-106, 108-108, K 23-41-00 K K CONF. 02 K K Page 11- 12 K K JAS Oct 01/92

Switching relays at PURSER, ATTND 5 and ATTND 9 stations enable interconnection of the telephone handsets and passenger amplifier 1RY in order to allow broadcasting of announcements in the loudspeakers. Through the normally open contacts of each relay, the microphone, audio and PTT outputs of each telephone handset are connected to the relevant input of passenger address amplifier 1RY.

6. Interface _________ The service interphone system is interconnected with :

A. The Flight Interphone System (Ref. 23-51-00, RL circuit) enables Crew Members to hear announcements broadcast to passengers.

B. The Passenger Address System (Ref. 23-31-00, RY circuit) enables Crew Members or Cabin Attendants to broadcast announcements to passengers.

C. The Call System (Ref. 33-23-30, LN circuit) enables Crew Members or passengers to call Cabin Attendants.


SERVICE INTERPHONE - FAULT ISOLATION ____________________________________



SERVICE INTERPHONE - ADJUSTMENT/TEST ____________________________________


A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit 3-Phase, 115/200V, 400Hz, 90KVA (2) 150 Ohm Hand Microphone (High Level) (3) 600 Ohm Headset (4) Ground Service Telephone - 150 Ohm Micro (High Level), 600 Ohm Earphones Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

B. Procedure (1)Job Set-Up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward ventilation system operates (Ref. 21-20-00, P. Block 301). (c)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1st OBSV & AVIONICS 16RL 209/E 7 22VU AUDIO SYS/CONTRL PNL/F/0 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

(d)Make certain that telephone handsets are connected at all Cabin Atten- dantsS stations. (e)On jack box of each crew member, make certain that : - a boomset is connected to BOOM interphone connection receptacle - a headset is connected to HEADSET jack - OXY-BOOM switch is in BOOM position (f)Make certain that a hand microphone is connected to the relevant jack at each crew memberSs station. (g)In avionics compartment, on LH electronics rack 80VU - connect a headset to jack 621VC - connect a hand microphone to interphone connection receptacle 617VC (h)At each audio selector panel, make certain that all reception push- buttons are engaged. (i)Make certain that the PTT switches are in intermediate position. (2)Test of Communications between Cabin AttendantsS Stations

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------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- Establish voice communications between Check quality of the voice communi- Cabin AttendantsS stations, two by two cations

NOTE : Press PTT switch on telephone hanset when transmitting. ____ (3)Test of voice communications between crew memberSs stations, avionics compartment (transmission trough hand microphone, reception at headset) and Cabin AttendantsS stations (transmission and reception through telephone handset). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel at each crew memberSs station and in avionics compartment - engage CABIN transmission square key - disengage CABIN reception push-button - turn clockwise potentiometer integral with CABIN reception push-button.

2. Speak in hand microphone while pres- Check reception at each Cabin Atten- sing its PTT switch at each crew dantSs station using telephone hand- memberSs station and in avionics com- set partment

3. Speak in microphone of telephone Check reception at each crew memberSs handset at each Cabin AttendantSs station and in avionics compartment station using headset and turning potentiometer to adjust audio level

(4)Test of voice communications between crew memberSs stations (transmission and reception through boomset) and Cabin AttendantSs stations (transmission and reception through telephone handsets). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Speak in boomset microphone at each Check reception at the telephone crew memmberSs station (RAD INT PTT handset at each Cabin AttendantSs switch on corresponding audio selector panel placed in RAD position)

2. Speak in telephone handset at each Check reception at boomset at each Cabin AttendantSs station crew memberSs station

(5)Test of voice communications between ground service jacks (transmission and reception through ground service telephones)


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 67VU, place SERVICE INPTH ON-OFF switch in ON position

2. Establish voice communications Check quality of the communications between ground service jacks, two by two, using two ground service telephones

(6)Test of voice communications between ground service jacks (transmission and reception through ground service telephones) and Cabin AttendantSs stations (transmission and reception using telephone handsets). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make certain that SERVICE INTPH ON- OFF switch is in ON position

2. Establish voice communications Check quality of the communications between one ground service jack and one Cabin AttendantSs station

(7)Test of voice communications between ground service jacks (transmission and reception through ground service telephones) and crew membersS stations (transmission and reception through boomset). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make certain that SERVICE INTPH ON- OFF switch is in ON position

2. On audio selector panel at each crew memberSs station, make certain that : - CABIN transmission square key is engaged - CABIN reception push-button is disengaged and turned clockwise

3. Speak in boomset microphone at each Check quality of the communication crew memberSs station (RAD-INT PTT at the ground service telephone switch on audio selector panel pla- connected to a ground service jack ced in RAD position)

4. Speak in microphone of ground ser- Check reception at boomset at each vice telephone crew memberSs station

C. Close-Up (1)On audio selector panel at each crew memberSs station - engage INT transmission square key


- engage CABIN reception push-button - place RAD-INT PTT switch in intermediate position (2)On panel 67VU, place SERVICE INTPH ON-OFF switch in OFF position. (3)In avionics compartment, on electronics rack 80VU (a)Disconnect headset (b)Disconnect hand microphone. (c)On audio selector panel - engage INT transmission square key - engage CABIN reception push-button - place RAD-INT PTT switch in intermediate position (4)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (5)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


SERVICE INTERPHONE - ADJUSTMENT/TEST ____________________________________


A. Reason for the Job To check that the service interphone system is in operating condition.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit -3-Phase, 115/ 200V, 400Hz, 90KVA (2) 150 Ohm Hand Microphone (High Level) (3) 600 Ohm Headset (4) Ground Service Telephone - 150 Ohm Microphone (High Level) and 600 Ohm Earphones Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Procedure (1)Job Set-UP (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)Make certain that forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (c)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1st OBSV & AVIONICS 16RL 209/E 7 22VU AUDIO SYS/CONTRL PNL/F/0 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

(d)Make certain that telephone handsets are connected at all Cabin Atten- dantsS stations. (e)On jack box at each crew memberSs station, make certain that : - a boom set is connected to BOOM interphone connection receptacle - a headset is connected to HEADSET jack (f)Make certain that a hand microphone is connected to the relevant jack at each crew memberSs station. (g)On each audio selector panel, make certain that : - all reception push-buttons are engaged - OXY-BOOM switch is in BOOM position (h)Make certain that the PTT switch at each crew memberSs station is in intermediate position. (i)In avionics compartment, on electronics rack 80VU

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- connect a headset to jack 612VC - connect a hand microphone to interphone connection receptacle 617VC (2)Test of voice communications between Cabin AttendantsSstations ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- Establish voice communications between Check quality of the communications Cabin AttendantsS stations, two by two

NOTE : Press PTT switch on telephone handset when transmitting ____ (3)Test of voice communications between crew membersS stations, avionics compartment (transmission through hand microphone, reception at headset) and Cabin AttendantsS stations (transmission and reception through telephone handset) ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At overhead panel, place CABIN INTPH ON-OFF switch in ON position 2. On audio selector panel at each crew memberSs station and in avionics compartment - engage INPH transmission square key - disengage INPH reception push-button - turn clockwise potentiomemter integral with INPH reception push- button

3. Speak in hand microphone while pres- Check reception at each Cabin sing its PTT switch at each crew AttendantSs station using telephone memberSs station and in avionics handset compartment

4. Speak in microphone of telephone Check reception at each crew memberSs handset at each Cabin AttendantSs station and in avionics compartment station using headset and turning potentiometer to adjust audio level

(4)Test of voice communications between crew membersS stations (transmission and reception through boomset) and Cabin AttendantsS stations (transmission and reception through telephone handsets). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Speak in boomset at each crew mem- Check reception at the telephone berSs station (RAD-INTPH PTT switch handset at each Cabin AttendantSs placed in INTPH position) station

2. Speak in microphone of telephone Check reception at boomset at each handset at each Cabin AttendantSs crew memberSs station station


(5)Test of voice communications between ground service jacks (transmission and reception through ground service telephones) ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 67VU, place SERVICE INTPH ON-OFF switch in ON position

2. Establish voice communications between Check quality of the communications ground services jacks, two by two, using two ground service telephones

(6)Test of voice communications between ground service jacks (transmission and reception through ground service telephones) and Cabin AttendantsS stations (transmission and reception through telephone handsets) ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make certain that SERVICE INTPH ON- OFF switch is in ON position

2. Establish voice communications Check quality of the communications between one ground service jack and one Cabin AttendantSs station

(7)Test of voice communications between ground service jacks (transmission and reception through ground service telephone) and crew memberSs stations (transmission and reception through boomset). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Make certain that CABIN INTPH ON-OFF and SERVICE INTPH ON-OFF switches are in ON position

2. On audio selector panel at each crew memberSs station, make certain that : - INTPH reception push-button is disengaged and turned clockwise - OXY-BOOM switch is in BOOM position

3. Speak in boomset microphone at each Check quality of the communication crew memberSs station (RAD-INTPH at the ground service telephone con- PTT switch placed in INTPH position) nected to a ground service jack

4. Speak in microphone of a ground ser- Check reception at boomset at each vice telephone crew memberSs station

D. Close-Up (1)On audio selector panel at each crew memberSs station, engage INPH reception push-button.


(2)On overhead panel, place CABIN INTPH ON-OFF switch in OFF position. (3)On panel 67VU, place SERVICE INTPH ON-OFF switch in OFF position. (4)In avionics compartment, on electronics rack 80VU (a)Disconnect headset (b)Disconnect hand microphone (c)On audio selector panel, disengage INPH transmission square key. (5)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (6)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


SERVICE INTERPHONE AMPLIFIER - REMOVAL/INSTALLATION ___________________________________________________



A. Job Set-Up (1)Open, safety and tag the following circuit breaker : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10

B. Removal (1)Disconnect electrical connector (4). (2)Remove screws (2). (3)Remove service interphone amplifier (1). (4)Cap electrical connectors (3) and (4).

C. Preparation of Replacement Component Not applicable.

D. Installation (1)Clean and inspect service interphone amplifier interface. (2)Make certain that electrical connectors (3) and (4) are in correct condition. (3)Install service interphone amplifier (1) and attach with screws (2). (4)Connect electrical connector (4).R (5)Remove safety clip and tag and close the circuit breaker 20RL.

E. Test Carry out an operational test of service interphone (Ref. 23-41-00, P. Block 501).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


Service Interphone Amplifier Figure 401


GROUND CREW CALL SYSTEM - DESCRIPTION AND OPERATION ___________________________________________________

1. General _______ The ground crew call system, through aural and visual indications, enables communications - from the flight compartment to the ground. - from the ground to the flight compartment.


R **ON A/C 107-107, 109-999,

(Ref. Fig. 001 )

R **ON A/C 001-106, 108-108,

(Ref. Fig. 002 )

**ON A/C ALL

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1LN Circuit Breaker - FLT/DECK/CALLS 21VU 210 2LN Pushbutton - RESET 32VU 210 2WC Indicator Light/Switch - MECH CALL 32VU 210 3WC Interphone Box (Ref. 23-42-12) 711 4WC Horn (Ref. 23-42-21) 124 5WC Diode 250VU 122 121BL 14WC Logic Unit - Call 122 121BL 72GB Relay - RH Gear Shock Absorber 104VU 120 121BL


Ground Crew Call System - Component Location Figure 001


Ground Crew Call System - Component Location Figure 002


3. System Description (Ref. Fig. 003 ) __________________ The ground crew call system consists of :

A. A call logic unit 14WC containing the control circuitry.

B. An interphone box 3WC enabling when aircraft is on the ground calls and voice communications between the crew members in the flight compartment and the ground mechanic.

C. A Blue/White MECH CALL indicator light/switch 2WC associated with a RESET pushbutton 2LN located on panel 32VU.

D. A horn 4WC which sounds when the crew members call the ground mechanic.

E. A circuit breaker 1LN supplying the call logic unit, the indicator lights and the horn with 28VDC power.


Ground Crew Call - Block DiagramR Figure 003



A. Call Logic Unit The call logic unit located in zone 122 is attached to a support bracket by means of four screws. Two electrical connectors allow connections with the rest of the system. The call logic unit contains all logic circuits to operate MECH CALL and COCKPIT CALL indicator lights.

B. Interphone Box (Ref. Fig. 004 )

Ground Crew Call - Interphone Box Figure 004

The interphone box is located on nose gear leg. (1)On the face : - A Blue COCKPIT CALL indicator light illuminating when the crew members want to establish communication with the ground mechanic. - A RESET pushbutton enabling to extinguish the Blue COCKPIT CALL indicator light. - A COCKPIT CALL pushbutton enabling the ground mechanic to call the crew members in the flight compartment.


- A LIGHT TEST pushbutton enabling the test of the COCKPIT CALL indicator light. Also, a jack and an APU SHUT OFF pushbutton, both protected by covers, and one APU FIRE and one INS RACK VENT red warning lights are located on the interphone box.

C. A Blue/White MECH CALL indicator light/switch 2WC - the Blue lamp with CALL legend comes on when the ground mechanic wants to establish communication with the crew members. - the white lamp with MECH legend comes on during dimming. ANNUN LT switch 6LP on FLT DECK LT panel 27VU enables test and dimming of indicator light.

D. RESET pushbutton 2LN This pushbutton enables to extinguishing the MECH CALL indicator light/ switch after a call from the ground mechanic.

E. Horn 4WC The horn located in the nose gear will, supplied with 28VDC through the contacts of MECH CALL indicator light/switch, sounds just the time the indicator light/switch is pressed.



A. Crew Member-to-Ground Mechanic Call When pressing MECH CALL indicator light/switch, a + 28VDC signal is applied to the logic circuits controlling the COCKPIT CALL indicator light through - the normally open (NO) contacts of relay 72GB. - the auxiliary contacts of the MECH CALL indicator light/switch. Horn 4WC is supplied with +28VDC power through - the normally open (NO) contacts of relay 72GB. - the auxiliary contacts of MECH CALL indicator light/switch when pressed. - diode 5WC The logic circuits keep the COCKPIT CALL indicator light on after the call. Pressing the RESET pushbutton located on the interphone box returns the logic circuits to their initial configuration, thus causing the COCKPIT CALL indicator light to go off.

B. Ground Mechanic-to-Crew Member Call When pressing the COCKPIT CALL pushbutton on the interphone box, a + 28VDC signal is applied to the logic circuits controlling the MECH CALL indicator light/switch through - the normally open (NO) contacts of relay 72GB. - the normally open (NO) contacts of COCKPIT CALL pushbutton. This control signal triggers a flip-flop which connects the MECH CALL indicator light/switch 2WC to ground. The blue CALL lamp of the indicator light comes on fed with 28VDC through the normally closed (NC) contacts of relay 10LT and with a ground resulting from flip-flop switching. The 28VDC signal is also applied to the aural warning box 1WK to trigger the buzzer circuit which feeds the aural signal to the audio warning loudspeakers for one second. The blue CALL lamp of the indicator light/switch is dimmed through the normally open (NO) contacts of relay 10LT. The indicator light/switch is dimmed by switch 6LP which also provides a ground connection for the illumination of the white MECH lamp of indicator light/switch. The blue CALL lamp of the indicator light/switch can be extinguished by pressing RESET pushbutton 2LN and a +28VDC signal returns the flip-flop to its original configuration.


Ground Crew Call - Interconnection Schematic Figure 005

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GROUND CREW CALL SYSTEM - FAULT ISOLATION _________________________________________



GROUND CREW CALL SYSTEM - ADJUSTMENT/TEST _________________________________________


A. Reason for the Job To check that the ground crew call system is in operating condition.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit 3-phase, 115/200V, 400Hz, 90KVAR (2) AmmeterR Referenced Procedures - 24-41-00, P. Block 301 Electrical PowerR - 23-42-21, P. Block 401 Horn

C. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU ANNUN LT CONTRLS/PILOTS & OVERHEAD PNLS 1LP 113/A 4 21VU ANNUN LT CONTRLS/FLT ENG PNL 2LP 113/A 5 21VU FLT/DECK/CALLS 1LN 112/B 1 128VU LDG GEAR/RELAYS & RETRACT CONTROL 2GB 805/A 9 128VU LDG GEAR/SAFETY RELAYS 119GB 805/A 8 21VU WARNING/AUDIO PWR SUPPLY 3WK 111/C 2

D. Tests (1)Test of Indicator Lights ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 27VU, place On panel 32VU, the blue, the blue ANNUN LT switch in TEST position and white lamp of the following indicator lights come on : - MECH CALL - AFT ATTND CALL - MID ATTND CALL - FWD ATTND CALL - PURSER CALL

2. On nose gear leg, on interphone box The following indicator lights 3WC, press LIGHT TEST pushbutton come on : - COCKPIT CALL - APU FIRE - INS RACK VENT

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(2)Test of Crew Member-to-Ground Mechanic Call ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On panel 32VU, press then release - On interphone box 3WC, COCKPIT MECH CALL indicator light/switch CALL indicator light comes on. - the horn 4WC sounds during the time MECH CALL indicator light/ switch is pressed

2. On interphone box 3WC, press RESET - COCKPIT CALL indicator light pushbutton goes off.

(3)Test of Ground Mechanic-to-Crew Members Call ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On interphone box 3WC, press then - On panel 32VU, the blue CALL lamp release COCKPIT CALL pushbutton of MECH CALL indicator light/ switch comes on - The buzzer aural warning is broadcast in the audio warning loudspeakers for one second

2. On panel 32VU, press RESET pushbutton - The blue CALL lamp of MECH CALL indicator light/switch goes off.

R

E. Close-Up (1)De-energize the aircraft electrical network and disconnect electrical ground power unit. (2)Make certain that working area is clean and clear of tolls and miscellaneous items of equipments.

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INTERPHONE BOX - REMOVAL/INSTALLATION _____________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety ClipsR B. Material No.09-001 Sealant (Ref. 20-30-00) C. Blanking Plugs/Caps D. Lockwire 0.6 mm (0.024 in.) Dia, Corrosion-Resistant Steel Referenced Procedures - 21-20-00, P. Block 501 Air Distribution/Extraction, Forward Section - 23-42-00, P. Block 501 Ground Crew Call System - 23-51-00, P. Block 501 Flight Interphone - 32-51-00, P. Block 501 Steering - 49-62-00, P. Block 501 Emergency Shutdown


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 128VU NOSE WHEEL STEER 1GC 803/C 2 21VU FLT/DECK/CALLS 1LN 112/B 1 21VU AVIONICS VENT/GRND CALL/1 13WC 112/B 2 21VU AVIONICS VENT/GRND CALL/2 12WC 112/B 3

B. Removal (Ref. Fig. 401 ) (1)Remove rubber coating with a spatula taking care not to damage protective finish on bolt (3) heads and nuts (6). (2)Cut and remove lockwire from electrical connectors (2). (3)Disconnect electrical connectors (2) from interphone box (1). (4)Remove cotter pins (7), remove nuts (6), washers (5) and bolts (3). (5)Remove interphone box from its mounting (4). (6)Blank off electrical connectors (2).

C. Preparation of Replacement Component (1)Remove blanking caps from electrical connectors.

D. Installation (Ref. Fig. 401 ) (1)Make certain electrical connectors (2) ends are in good condition. (2)Place interphone box (1) on its mounting (4). (3)Install bolts (3) washers (5) nuts (6). Tighten and safety with cotter pins (7). (4)Coat bolt (3) heads and nuts with Material No.351. (5)Connect electrical connectors (2) to interphone box and safety with 0.6 mm (0.024 in.) corrosion-resistant steel lockwire.


Interphone Box Figure 401


E. Tests (1)Carry out a test of the ground crew call system (Ref. 23-42-00, P. Block 501).R (2)Carry out an operational test of the air distribution extraction systemR (Ref. 21-21-00, P. Block 501). (3)Carry out an operational test of the steering control system (Ref. 32-51-00, P. Block 501). (4)Carry out a test communication between the flight compartment and the ground from the nose gear leg (Ref. 23-51-00, P. Block 501R paragraph 1.C.(8)). (5)Carry out an operational test of the emergency shut-down system (Ref. 49-62-00, P. Block 501).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


HORN - REMOVAL/INSTALLATION ___________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3.20 m (10 ft. 6 in.) B. Circuit Breaker Safety Clips - 23-42-00, P. Block 501 Ground Crew Call System - 32-22-11, P. Block 301 Nose Gear Doors - Ground Door Opening


A. Job Set-Up (1)Open nose gear doors (Ref. 32-22-11, P. Block 301). (2)Position access platform 3.20 m (10 ft. 6 in.) to gain access to noseR gear well. (3)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU AVIONICS VENT/GRND CALL/2 12WC 112/B 3 21VU AVIONICS VENT/GRND CALL/1 13WC 112/B 2 21VU FLT/DECK/CALLS 1LN 112/B 1

B. Removal (Ref. Fig. 401 ) (1)Remove the six screws (4) securing casing door (5). (2)Open casing door (5). (3)Remove nut (3) - Disconnect electrical supply wire (2). (4)Remove nut (6) and washer (7). (5)Remove horn (1) from its bracket (8).


D. Installation (Ref. Fig. 401 ) (1)Install horn (1) on its bracket (8). (2)Install washer (7) and nut (6), and tighten. (3)Connect electrical supply wire (2), install nut (3), and tighten. (4)Close casing door (5). (5)Install screws (4) and tighten.

E. Test (1)Test the ground crew call system (Ref. 23-42-00, P. Block 501).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Close nose gear doors (Ref. 32-22-11, P. Block 301). (4)Remove safety clips and tags, and close the following circuit breakers :


Horn Figure 401


R 12WC, 13WC and 1LN.


CALL LOGIC UNIT - REMOVAL/INSTALLATION ______________________________________


Blanking Caps


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU ANNUN LT CONTRLS/PILOTS & OVERHEAD PNLS 1LP 113/A 4 21VU ANNUN LT CONTRLS/FLT ENG PNLS 2LP 113/A 5 21VU FLT DECK CALLS 1LN 112/B 1

B. Removal (1)Disconnect electrical connectors (4) (2)Remove screws (1) (3)Remove call logic unit (2) (4)Cap electrical connectors (3) and (4)

C. Preparation of Replacement Component Not applicable

D. Installation (1)Clean and inspect call logic unit interface (2)Install call logic unit (2) and attach with screws (3)Uncap and connect electrical connectors (4) (4)Remove safety clips and tags and close the following circuit breakers 1LP, 2LP and 1LN.

E. Test (1)Carry out an operational test of ground crew call system (Ref. 23-42-00, P. Block 501).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


Call Logic Unit Figure 401


AUDIO INTEGRATING (FLIGHT INTERPHONE) - DESCRIPTION AND OPERATION _________________________________________________________________

1. General _______ The audio integrating system (flight interphone) provides a means of telephone communication between the crew members, and integrates the possibilities of selection for reception and transmission through the radio communication and radio navigation systems (HF, VHF, VOR, etc...).

2. Component Location __________________ (Ref. Fig.001 and 002) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RL Selector Panel - Audio, Captain 11VU 210 (Ref. 23-51-11) 2RL Selector Panel - Audio, First 11VU 210 Officer (Ref. 23-51-11) 3RL Selector Panel - Audio, Flight 50VU 212 Engineer (Ref. 23-51-11) 4RL Selector Panel - Audio, First 1VU 211 Observer (Ref. 23-51-11) 5RL Jack Box - First Observer 1VU 211 (Ref. 23-51-31) 6RL Jack Box - Second Observer 15VU 211 (Ref. 23-51-31) 9RL Amplifier (AUDIO INTEG.)/ 121 121BL Junction Box (Ref. 23-51-19) 10RL PTT Switch - INT/RAD, Second 223VU 211 Observer 11RL PTT Switch - INT/RAD, Captain 12VU 211 12RL PTT Switch - INT/RAD, First 14VU 212 Officer 16RL Circuit Breaker - AUDIO SYS/ 22VU 210 CONTRL PNL/1ST OBS & AVIONICS 17RL Circuit Breaker - AUDIO SYS/ 22VU 210 CONTRL PNL/F/O 18RL Circuit Breaker - AUDIO SYS/ 22VU 210 CONTRL PNL/CAPT 19RL Circuit Breaker - AUDIO SYS/ 22VU 210 INTPH AMPLI/FLT 21RL Amplifier - Service Interphone 121 121BL 30RL Selector Panel - Audio, 121 121BL Avionics Compartment (Ref. 23-51-11) 50RL Circuit-Breaker - AUDIO SYS/ 22VU 210 CONTRL PNL/FLT ENGR 51RL Jack Box - Captain (Ref. 23-51-31) 1VU 211 52RL Jack Box - First Officer 7VU 212 (Ref. 23-51-31) 53RL Jack Box - Flight Engineer 50VU 212 (Ref. 23-51-31) 54RL Mask Assy (Microphone) - 1VU 211


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ Oxygen, First Observer 55RL Mask Assy (Microphone) - 1VU 211 Oxygen, Captain 56RL Mask Assy (Microphone) - 7VU 212 Oxygen, First Officer 57RL Mask Assy (Microphone) - 212 Oxygen, Flight Engineer 58RL Mask Assy (Microphone) - 15VU 211 Oxygen, Second Observer 75RL Hand Microphone - Captain 1VU 211 76RL Hand Microphone - First 7VU 212 Officer 77RL Hand Microphone - Flight 67VU 212 Engineer 78RL Hand Microphone - First 1VU 211 Observer 79RL Hand Microphone - Second 15VU 211 Observer 83RL Headset - Captain 1VU 211 84RL Headset - First Officer 7VU 212 85RL Headset - Flight Engineer 50VU 212 105RL Potentiometer 241VU 211 106RL Potentiometer 240VU 212 3WC Interphone Box (Ref. 23-42-12) 711 7WK Loudspeaker - Captain 211 8WK Loudspeaker - First Officer 212


Flight Interphone - Component Location in Flight Compartment Figure 001

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Flight Interphone - Component Location in Avionics Compartment and on Nose Gear Figure 002 HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJR KEFFECTIVITY: ALL K 23-51-00 K K CONF. 02 K K Page 5 K K JAS Oct 01/92

3. System Description (Ref. Fig. 003 ) __________________ The flight interphone installation comprises :

A. A junction box/amplifier 9RL for interconnection of the various radio stations on aircraft and for amplification of microphone signals.

B. Five audio selector panels 1RL, 2RL, 3RL, 4RL and 30RL for selection of the various reception and transmission channels at CaptainSs, First OfficerSs, Flight EngineerSs, First ObserverSs and avionics compartment stations respectively.

C. Five jack boxes at CaptainSs, First OfficerSs, Flight EngineerSs, First and Second ObserverSs stations respectively. Each jack box allows connection of a headset and a hand microphone.

D. Five oxygen mask microphones 55RL, 56RL, 57RL, 54RL and 58RL for the various crew membersS stations.

E. Five hand microphones : 75RL, 76RL, 77RL, 78RL and 79RL.

F. Three PTT switches : 11RL, 12RL and 10RL at CaptainSs, First OfficerSs and Second ObserverSs stations.

G. Two push-buttons 105RL and 106RL associated with two potentiometers to control both reception and audio volume in CaptainSs and First OfficerSs loudspeakers 7WK and 8WK.

H. A jack on interphone box 3WC on nose gear leg for voice communications between the crew members and the ground mechanic.

I. Five circuit breakers 19RL, 16RL, 17RL, 18RL and 50RL supplying amplifier 9RL and the five audio selector panels 1RL, 2RL, 3RL, 4RL and 30RL.


Flight Interphone - Block Diagram Figure 003



A. Interphone Junction Box/Amplifier 9RL (Ref. Fig. 004 ) This unit features an amplifier and interconnecting circuits. (1)The purpose of the amplifier is : - to supply the microphones - to amplify microphone signals The amplifier features seven microphone inputs, six of them being used. Two audio outputs are available from the amplifier : - one 125 ohm output supplying the audio circuit of the service jack located on the nose gear leg - one 50 ohm output supplying the audio circuit of the various crew membersS stations. (2)Interconnections are made by means of printed circuit boards. (3)On the faces seen in the 3/4 front view : (a)A connector connecting the unit to CaptainSs audio selector panel 1RL. (b)A connector connecting the unit to audio selector panel 30RL in the avionics compartment. (c)A connector connecting the unit to First OfficerSs audio selector panel 2RL. (d)A connector connecting the unit to the service jack on the nose gear leg. (e)An unused connector. (f)A connector connecting the unit to the Second ObserverSs station. (4)On the faces seen in the 3/4 rear view : (a)A connector connecting the unit to First ObserverSs audio selector panel 4RL. (b)A connector connecting the unit to Flight EngineerSs audio selector panel 3RL. (c)A grounding lead connecting the unit to the ground.

B. Audio Selector Panel

**ON A/C 001-101,

(Ref. Fig. 005 ) (1)On the face are located : (a)The keyboard with 6 square keys for selecting microphone and PTT circuits of VHF, HF, flight interphone (INT), service interphone (SI) and passenger address (PA) channels. Engagement of any one of these keys unlocks the key previously engaged. (b)13 push-buttons for selecting reception of communication channels (VHF, HF, INT, SI, PA) and of navigation channels (MKR, VOR, DME, ADF). Each of these push-buttons has an integral potentiometer which enables control of the audio level by turning the push-button.

R **ON A/C 101-108,

After SB 23-085 For A/C 101-101,


Interphone Junction Box/Amplifier 9RL Figure 004


**ON A/C 001-101,

Flight Interphone - Audio Selector Panel Figure 005

(Ref. Fig. 006 ) (1)On the face are located : (a)The keyboard with 7 square keys for selecting microphone and PTT circuits of VHF, HF, flight interphone (INT), service interphone (SI) and passenger address (PA) channels. Engagement of any one of these keys unlocks the key previously engaged. (b)13 push-buttons for selecting reception of communication channels (VHF, HF, INT, SI, PA) and of navigation channels (MKR, VOR, DME, ADF). Each of these push-buttons has an integral potentiometer which enables control of the audio level by turning the push-button.

R **ON A/C 101-108,

(c)One INT/RADIO switch - INT position : operation in interphone mode between the various stations - RADIO position : operation in transmit mode for VHF, HF systems, for communications with Cabin Attendants and for broadcasting of announcements to passengers (PA).


Flight Interphone - Audio Selector Panel Figure 006


(d)2 integrally lighted keys (RANGE and VOICE) ; with these keys engaged, the coded signal (above 1020 Hz) identifying radio navigation stations is eliminated. Key indicator lights come on when this function is selected. (e)One EMR/NORM switch For selecting power amplifier standby circuit in the event of failure of normal circuit. (2)On the rear, two connectors allow connection to the rest of the system.

C. Jack Box (Ref. Fig. 007 )

Jack Box Figure 007

(1)On the face are located : (a)A jack for connecting a boomset. (b)A jack for connecting a headset. (c)A MIC SELECT OXY-BOOM switch for selecting either boomset or mask microphone depending on which microphone is used to transmit. (2)On the back, a connector allows connection to the rest of the system. (3)Inside the jack box, a pre-amplifier stage increases the level of boomset microphone signals.



A. Operation in Interphone Mode (Ref. Fig. 008 ) Amplifier 9RL features a seven input preamplifier and mixer stage and an amplifier stage. As CaptainSs, First OfficerSs, Flight EngineerSs and ObserversS channels are identical, only CaptainSs channel is described. The preamplified signal from the hand microphone or the signal from the mask microphone is fed to input 1 of the preamplifier. Placing Captain INT/RAD PTT switch 11RL in INT position energizes relay KI. The mask microphone signal is fed to the interphone amplifier. The signal from the hand microphone is also fed to the amplifier via : - the normally closed (NC) contacts of relay K3 - the normally open (NO) contacts of engaged INT square key. Input 2 receives the microphone signals from First OfficerSs channel. Input 3 receives the microphone signals from Flight EngineerSs channel and Second ObserverSs microphone signals. Input 4 receives signals from Second ObserverSs mask microphone or boomset microphone via the contacts of PTT switch 10RL in INTPH position. Input 5 is not used. Input 6 receives microphone signals from service interphone box 3WC. Input 7 receives microphone signals from First ObserverSs channel and from the avionics compartment. The amplifier stage has two outputs : - Output 2 (125 ohms) supplies the jack on service interphone box 3WC - Output 1 (50 ohms) supplies the audio circuits of all crew membersS stations and avionics compartment station. The output signal for each station is fed to headset via : - INT push-button and its integral potentiometer - EMR/NORM switch in NORM position. - isolation amplifier A1. NOTE 1 : At Second ObserverSs station, transmission is by means of a ______ hand microphone or a mask microphone and reception by means of a headset. As the hand microphone and headset are connected in parallel with the equipment at Flight EngineerSs station, the Second Observer is therefore dependent upon selections and adjustments made by the Flight Engineer. NOTE 2 : At avionics compartment station, transmission is by means ______ of a hand microphone connected to interphone connection receptacle 617VC ; reception is by means of a headset connected to jack 621VC.

B. Operation in Radio Transmit Mode (Ref. Fig. 009 ) (1)Microphone and PTT signals As CaptainSs, First OfficerSs, Flight EngineerSs and First ObserverSs channels are identical, only CaptainSs channel is described. - Relay K3 switches microphone or PTT signals to amplifier 9RL whether hand microphone or mask microphone is used. This relay is de-energized when transmitting with hand microphone and energized when transmitting


Flight Interphone - Operation in Interphone Mode Figure 008


Flight Interphone - Operation in Transmit Mode Figure 009


with mask microphone (PTT switch on control wheel or on audio selector panel placed in RADIO position). - The square keys on the audio selector panel provide switching of microphone and PTT signals to the selected system. Example : transmission on VHF1 system - the transmit signal (from hand microphone or mask microphone) from each station is fed to VHF1 transceiver via the normally open (NO) contacts of VHF1 square key. - the PTT ground signal is also fed to VHF1 transceiver via the VHF1 square key. The interphone junction box 9RL provides interconnections between the various radio stations. (2)Audio signals The audio signals from each system are fed to all crew membersS stations for reception at the headsets via : - the interphone junction box 9RL - the isolation amplifier A1, or A2 on standby. - the push-button and its integral potentiometer corresponding to the selected system. - the EMR/NORM switch. NOTE 1 : As the hand microphone and headset at Second ObserverSs ______ station are connected in parallel with the equipment at Flight EngineerSs station, the Second Observer is therefore dependent upon selections and adjustments made by the Flight Engineer. NOTE 2 : At avionics compartment station, transmission is by means ______ of a hand microphone connected to interphone connection receptacle 617VC ; reception is by means of a headset connected to jack 621VC. Connections between the systems and audio selector panel 30RL are not via the interphone junction box. NOTE 3 : Interconnection with service interphone 21RL is only ______ available for audio and microphone signals (and not for PTT signals).

C. Operation in Radio Navigation Receive Mode (Ref. Fig. 010 ) (1)Connection with VOR, ILS, DME, ADF and MKR systems As selection of reception channels at audio selector panels is identical, only selection of CaptainSs reception channel is described. The signal identifying ADF and VOR (ILS) ground stations is fed to the audio selector panel through the interphone junction box 9RL. Each push-button selects a station. The signal passes through the VOICE and RANGE keys. In the case of simultaneous reception of station identification and spoken signals, the VOICE and RANGE keys eliminate the station identification signal (1020 Hz). DME and marker (MKR) signals are not filtered. (2)Connection with radio altimeter system The modulated altitude variation indicator signal is received permanently in the headsets. It cannot be eliminated by the audio selector panel.


Flight Interphone - Audio Selection - Schematic Figure 010


D. Audio Signal Pick-Up (Ref. Fig. 010 ) (1)Audio signal recording The audio signals from CaptainSs, First OfficerSs and Flight EngineerSs audio selector panels are fed to cockpit voice recorder 2RK via the interphone junction box. (2)Reception at CaptainSs and First OfficerSs loudspeakers The audio signals from CaptainSs and First OfficerSs audio selector panels 1RL and 2RL are fed to aural warning box 1WK and then broadcast at loudspeakers 7WK and 8WK. Push-buttons 105RL and 106RL when disengaged allow connection with the loudspeakers, the integral potentiometers providing for audio level adjustment.

E. Operation of Loudspeaker Muting Circuit (Ref. Fig. 011 ) The muting circuits attenuate reception level at CaptainSs and First Offi- cerSs loudspeakers during VHF, HF, INT and PA transmissions using CaptainSs or First OfficerSs PTT switches (on control wheel, on hand microphone or on audio selector panel). A ground signal from a PTT switch energizes a relay in the aural warning box. The audio frequency signal is attenuated by a variable resistor in the input circuit of loudspeaker amplifier.


Flight Interphone - Loudspeaker Muting Circuits Figure 011


6. Interface (Ref. Fig. 012 ) _________ The flight interphone system is interconnected with the following systems :

A. HF System The HF system feeds the audio frequency signal from the HF transceivers to the flight interphone.

B. VHF System The VHF system feeds the audio frequency signals from the VHF transceivers to the flight interphone.

C. Passenger Address System The passenger address system feeds audio sidetone to the flight interphone during the announcement made by the crew members

D. Service Interphone The service interphone feeds microphone signals to the flight interphone from Cabin Attendant telephone handsets, and from Flight EngineerSs station when aircraft in on the ground.

E. VOR/ILS System The VOR/ILS system feeds the identification signals (in Morse code) from the selected VOR/ILS station to the flight interphone.

F. Radio Altimeter System The radio altimeter system feeds a modulated audio signal to the flight interphone when aircraft descends below 2500 feet.

G. Marker System The Marker system feeds marker beacon localizing AF signals (3 separate frequencies) to the flight interphone.

H. DME System The DME system feeds the identification signals (in Morse code) of the selected DME station to the flight interphone.

I. ADF System The ADF system feeds ADF beacon identification signals (spoken or in Morse code) to the flight interphone.

J. Cockpit Voice Recorder The audio signals from CaptainSs, First OfficerSs and Flight EngineerSs audio selector panels are directed to the cockpit voice recorder for recording on a magnetic tape.


Flight Interphone - Interfaces Figure 012


AUDIO INTEGRATING (FLIGHT INTERPHONE) - FAULT ISOLATION _______________________________________________________



AUDIO INTEGRATING (FLIGHT INTERPHONE) - ADJUSTMENT/TEST _______________________________________________________


A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit 3-Phase, 115/200V, 400Hz, 90KVA (2) 150 Ohm Hand Microphone (High Level (3) 600 Ohm Headset (4) Ground Telephone Equipment - 150 Ohm Micro- phone (High Level), 600 Ohm Headset Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

B. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (3)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1st OBSV & 16RL 209/E 7 AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12 (4)On CaptainSs and First OfficerSs control column hand-wheels : - Make certain that PTT switches are in intermediate position. (5)On panel 223VU, at Second ObserverSs station : - Place RADIO-INTPH switch in intermediate position. (6)On audio selector panels at CaptainSs, First OfficerSs, Flight EngineerSs, First ObserverSs and avionics compartment stations, make certain that : - RADIO-INT PTT switches are in intermediate position, - INT transmission key is engaged - INT reception push-button is disengaged and turned clockwise - all other reception push-buttons are engaged (7)On jack box at each crew memberSs station : - make certain that a boomset and a headset are connected to their respective jacks - place OXY-BOOM switch in BOOM position. (8)At each crew memberSs station, make certain - that the hand microphone is connected to the associated jack - that the oxygen mask microphone is in place and connected to the asso-


ciated jack. (9)In avionics compartment, on electronics rack 80VU - connect a hand microphone to interphone connection receptacle 617VC - connect a headset to jack 621VC.

C. Tests (1)Test of direct interphone communications between crew membersS stations using boomsets. NOTE : When testing direct interphone communications using boomsets, it ____ is not necessary to engage INT transmission keys on audio selector panels. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At CaptainSs station, speak into Check reception at boomset at other boomset microphone while holding crew memberSs stations. PTT switch on control column handwheel in INT position or placing RADIO INT PTT switch on audio selector panel in INT position.

2. On each audio selector panel, turn At each crew memberSs station, check counterclockwise potentiometer action of potentiometer on integral with the INT reception reception level. push-button

NOTE : The Second ObserverSs ____ station depends on the reception selection and audio level adjustment made at FlightEngineerSs audio selector panel.

3. At First OfficerSs station, speak Check reception at boomset at other into boomset microphone while crew membersS stations holding PTT switch on control column handweel in INT position or placing RADIO INT PTT switch on audio selector panel in INT position

4. At Flight EngineerSs station, speak Check reception at boomset at into boomset microphone while other crew memberSs stations placing RADIO-INT PTT switch on audio selector panel in INT position.

5. At First ObserverSs station, speak Check reception at boomset at into boomset microphone while other crew membersS stations placing RADIO-INT PTT switch on audio selector panel in INT position.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 6. At Second ObserverSs station, Check reception at boomset at speak into boomset microphone other crew membersS stations while placing RADIO-INTPH PTT switch on panel 223VU in INT PH position.

(2)Test of direct interphone communications between crew memberSs stations using mask microphones and headsets. NOTE : When testing direct interphone communications using mask micro- ____ phones, it is not necessary to engage INT transmission keys on audio selector panels. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On jack box at each crew memberSs station, place OXY-BOOM switch in OXY position.

2. At CaptainSs station, speak into Check reception at headset at oxygen mask microphone while other crew memberSs stations. holding PTT switch on control column handwheel in INT position or placing RADIO INT PTT switch on audio selector panel in INT position.

3. Repeat test described from Check reception at headset at paragraphs 1. C. (1) 3. to 1. other crew membersS stations. C. (1) 6. using oxygen mask microphone at each crew memberSs station.

NOTE : The Second ObserverSs station depends on the reception selection ____ and audio level adjustment made at Flight EngineerSs audio selector panel. (3)Test of interphone communications using hand microphones and headsets. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel at each crew memberSs station, make certain that INT transmission key is engaged.

2. At CaptainSs station, speak into Check reception at headset at hand microphone while holding other crew membersS stations. its PTT switch pressed.

3. Repeat test described from Check reception at headset at


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- paragraphs 1. C. (1) 3. to 1. other crew membersS stations. C. (1) 6. using the hand microphones at each crew memberSs station.

(4)Test of interphone communications between crew membersS stations using boomsets. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On jack box at each crew memberSs station, place OXY-BOOM switch in BOOM position.

2. At CaptainSs station, speak into Check reception at boomset at boomset microphone while holding other crew membersS stations. PTT switch on control column handwheel in RAD position or placing RADIO-INT PTT switch on audio selector panel in RADIO position.

3. On each audio selector panel, turn At each crew memberSs station, clockwise potentiometer integral check action of potentiometer on with the INT reception push- reception level. button.

NOTE : The Second ObserverSs sta- ____ tion depends on the reception selection and audio level adjustment performed at Flight EngineerSs audio selector panel.

4. At First OfficerSs station, speak Check reception at boomset at into boomset microphone while other crew membersS stations. holding PTT switch on control column handwheel in RAD position or placing RADIO INT PTT switch on audio selector panel in RADIO position.

5. At Flight EngineerSs station, speak Check reception at boomset at into boomset microphone while other crew membersS stations. placing RADIO-INT PTT switch on audio selector panel in RADIO position.

6. At First ObserverSs station, Check reception at boomset at


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- speak into boomset microphone other crew membersS stations. while placing RADIO-INT PTT switch in RADIO position.

7. At Second ObserverSs station, Check reception at boomset at speak into boomset microphone other crew membersS stations. while placing RADIO-INTPH PTT switch on panel 223VU in RADIO RADIO position.

(5)Test of interphone communications between crew membersS stations using oxygen mask microphones and headsets. NOTE : When testing direct interphone communications using mask micro- ____ phones, it is not necessary to engage INT transmission keys on audio selector panels. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On jack box at each crew memberSs station, place OXY-BOOM switch in OXY position.

2. At CaptainSs station, speak into Check reception at headset at oxygen mask microphone while other crew membersS stations. holding PTT switch on control column handwheel in RAD position or placing RADIO INT PTT switch on audio selector panel in RADIO position.

3. Repeat test described from Check reception at headset at paragraphs 1. C. (3) 4 to 1. other crew memberSs stations. C. (3) 7. using oxygen mask microphone at each crew memberSs station.

NOTE : The Second ObserverSs station depends on the reception selection and ____ audio level adjustment made at Flight EngineerSs audio selector panel. (6)Test of reception at CaptainSs and First OfficerSs loudspeakers. (a)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 21VU WARNING/AUDIO PWR SUPPLY 3WK 111/C 2

(b)Make certain that PTT switches on CaptainSs and First OfficerSs control column handwheels are in intermediate position.


(c)On panels 240VU and 241VU, disengage push-buttons and turn clockwise the potentiometers integral with these push-buttons. (d)On CaptainSs and First OfficerSs audio selector panels : - make certain that RADIO-INT PTT switch is in intermediate position. - make certain that INT transmission key is engaged - make certain that INT reception push-button is disengaged - turn clockwise the potentiometer integral with INT reception push- button (e)Test ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Speak into CaptainSs hand micro- Check that : phone while holding its PTT - CaptainSs loudspeaker operates switch pressed. at low level - First OfficerSs loudspeaker operates at normal level - the reception level can be adjusted by potentiometer 105RL located on panel 241VU - there is no Larsen effect when the hand microphone is used in normal position.

2. Speak into First OfficerSs hand Check that : microphone while holding its - First OfficerSs loudspeaker PTT switch pressed operates at low level - CaptainSs loudspeaker operates at normal level - the reception level can be adjusted by potentiometer 106RL located on panel 240VU - there is no Larsen effect when the hand microphone is used in normal position.

3. On CaptainSs and First OfficerSs jack boxes, make certain that OXY- BOOM switch is in OXY position

4. At CaptainSs station, speak into Check that : oxygen mask microphone while - CaptainSs loudspeaker operates holding PTT switch out control at low level column handwheel in RAD position - First OfficerSs loudspeaker or placing RADIO-INT PTT switch operates at normal level on audio selector panel in RADIO - there is no Larsen effect when position CaptainSs oxygen mask microphone tion is used in normal position.

5. At First OfficerSs station, Check that : speak into oxygen mask micro- - First OfficerSs loudspeaker phone while holding PTT switch operates at low level


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- on control column handwheel in - there is no Larsen effect when RAD position or placing RADIO- First OfficerSs oxygen mask mi- INT PTT switch on audio selec- crophone is used in normal po- tor panel in RADIO position.

6. At Flight EngineerSs, First and Check that : Second ObserverSs stations, - CaptainSs and First OfficerSs loud- speak into each oxygen mask mi- speakers operate at normal level crophone while placing corres- - there is no Larsen effect when ponding PTT switch in INT using successively Flight Engi- position. neerSs, First and Second OberverSs oxygen mask microphones in normal position.

(7)Test of interphone communication between crew membersS stations and avionics compartment (electronics rack 80VU) ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On audio selector panel 30RL located in LH electronics racks : - engage INT transmission key - disengage INT reception push- button - turn clockwise potentiometer integral with the reception push-button.

2. On jack box at each crew memberSs station, place OXY-BOOM switch in BOOM position

3. At CaptainSs station, speak into Chek reception at headset at boomset microphone while placing avionics compartment station. corresponding PTT switch in INT position.

4. Repeat test described in paragraph 1. C. (7) 3. from other crew membersS stations

5. At avionics compartment station, Check reception at boomset at speak into hand microphone while each crew memberSs station. holding its PTT switch pressed.

(8)Test of interphone communications between crew membersS stations and ground service jack on nose gear leg.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Connect a ground telephone equipment to ground service jack on nose gear leg

2. Carry out a communication bet- Check quality of each communication ween the ground service jack and the various crew memberSs stations.

3. Disconnect ground telephone equipment from ground service jack on nose gear leg.

D. Close-Up (1)On CaptainSs and First OfficerSs control column handwheels, place PTT switches in intermediate position. (2)On panels 240VU and 241VU, engage push-buttons associated with potentiometers 106RL and 105RL. (3)On audio selector panel at each crew memberSs station (a)Engage INT reception push-button (b)Make certain that INT transmission key is engaged (4)In avionics compartment (a)Disconnect hand microphone from interphone connection receptacle 617VC. (b)Disconnect headset from jack 621VC (5)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (6)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


SWITCH - INTPH/RAD - DEACTIVATION/REACTIVATION ______________________________________________

1. Deactivation ____________

A. Reason for the Job Ref. MMEL Sect. 1-23, Item 9

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Contact Insertion/Extraction Tool C. Heat-shrink Sleeve D. Hot Air Generator E. Cable Tie F. Adhesive INOP Label Referenced ProceduresR - 23-51-00, P. Block 501 Audio Integrating (Flight Interphone) - 23-51-11, P. Block 401 Audio Selector Panel - 24-41-00, P. Block 301 External Power - ESPM 20-25-31 Hot Air Generators - ESPM 20-42-12 Shrink Sleeves

C. Procedure (1)Job set-up (a)Energize the ground service network (Ref. 24-41-00, P. Block 301). (b)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 22VU AUDIO SYS/CTL PNL/CAPT 18RL E11 22VU AUDIO SYS/CTL PNL/F/O 17RL E8

(2)Deactivation (a)Remove the ACP associated with the failed control wheel INTPH/RAD switch (Ref. 23-51-11, P. Block 401).R (b)Disconnect the electrical plug 1RL-B (Captain station) or 2RL-B (F/O station) then using the extraction tool, remove the cables connectedR to pins 16-22 (control wheel INTPH/RAD switch connection). (c)Stow the cables using an NSA937502 (Ref. ESPM 20-42-12) type heat- shrink sleeve and a hot air generator (Ref. ESPM 20-25-31). (d)Fasten the heat-shrink sleeve/cable assembly on the existing bundle using a cable tie. NOTE : During this operation, the bend radius of the cables ____ must be complied with. (e)Connect the plug and install the ACP (Ref. 23-51-11, P. Block 401). Remove safety clips and tags and close circuit breakers. (f)Affix an adhesive INOP label to the failed control wheel (Captain or F/O).R (g)Remove safety clips and tags and close circuit breakers : 18RL, 17RL.


D. Test (1)Perform the operational test of the hand microphone (Ref. 23-51-00, P. Block 501).

R E. Close-upR (1)De-energize the ground service network (Ref. 24-41-00, P. Block 301).R (2)Make certain that working area is clean and clear of tools and miscel-R laneous items of equipment.

2. Reactivation ____________

A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Contact Insertion/Extraction ToolR C. Cable Tie Referenced ProceduresR - 23-51-00, P. Block 501 Audio Integrating (Flight Interphone) - 23-51-11, P. Block 401 Audio Selector Panel - 24-41-00, P. Block 301 External Power

B. Procedure (1)Job set-upR (a)Energize the ground service network (Ref. 24-41-00, P. Block 301).R (b)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------- 22VU AUDIO SYS/CTL PNL/CAPT 18RL E11 22VU AUDIO SYS/CTL PNL/F/O 17RL E8

(2)Reactivation (a)Remove the ACP associated with the failed control wheel INTPH/RADR switch (Ref. 23-51-11, P. Block 401). Disconnect the plug (1RL-B orR 2RL-B). (b)Cut the cable tie on the heat-shrink sleeve/cable assembly.R (c)Remove the heat-shrink sleeve. NOTE : Never use a scalpel, you may damage the cable protection sleeve. ____R (d)Connect the cables to plug 1RL-B or 2RL-B using the insertion tool.R Connect the plug and install the ACP (Ref. 23-51-11, P.Block 401).R (e)Remove the adhesive INOP label.R (f)Remove safety clips and tags and close circuit breakers : 18RL, 17RL.

C. TestR (1)Perform the operational test of the control wheel INTPH/RAD switch (Ref. 23-51-00, P. Block 501).

D. Close-upR (1)De-energize the ground service network (Ref. 24-41-00, P. Block 301).


R (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


AUDIO SELECTOR PANEL - REMOVAL/INSTALLATION ___________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Plugs/Caps


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1ST OBSV 16RL 209/E 7 & AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

B. Removal (1)Unlock Dzus fasteners (1). (2)Remove audio selector panel (2) from receptacle. (3)Disconnect electrical connectors (4). (4)Cap audio selector panel electrical connectors (4) and (3).


D. Installation (1)Clean and inspect component interface and adjacent area. (2)Uncap connectors (4) and (3) and check that they are in correct condition. (3)Connect electrical connectors. (4)Install audio selector panel (2) into receptacle and lock Dzus fasteners (1). (5)Remove safety clips and tags and close the following circuit breakers 16RL, 17RL, 19RL, 18RL and 50RL

E. Tests Test replaced component by operating flight interphone, checking that reception is normal.

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Restore system and aircraft to normal operating condition.


Audio Selector Panel Figure 401


INTPH/RAD SWITCH (11RL, 12RL) - REMOVAL/INSTALLATION ____________________________________________________

For removal of the INTPH/RAD switch (11RL and 12RL), remove the control wheel (Ref. AMM 27-11-11, P. Block 401 and CMM 27-31-12).


INTERPHONE JUNCTION BOX/AMPLIFIER - REMOVAL/INSTALLATION ________________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Plugs/Caps


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1ST OBSY & 16RL 209/E 7 AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

B. Removal (1)Disconnect electrical connectors (3) (2)Disconnect grounding lead (4) (3)Remove screws (1) attaching interphone junction box/amplifier to structure. (4)Remove interphone junction box/amplifier (5) (5)Cap connectors (2) and (3)

C. Preparation of Replacement Component Not applicable

D. Installation (1)Clean and inspect component interface and adjacent area (2)Uncap connectors and check that they are in good condition. (3)Install interphone junction box/amplifier (5) and attach to structure using screws (1). (4)Connect electrical connectors (3). (5)Connect grounding lead (4). (6)Remove safety clips and tags and close the following circuit breakers : 16RL, 17RL, 19RL, 18RL and 50RL.

E. Tests Test replaced component by operating flight interphone, checking that reception is normal.

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscel-


Interphone Junction Box/Amplifier Figure 401


laneous items of equipment. (2)Restore system and aircraft to normal operating condition.


JACK BOX - REMOVAL/INSTALLATION _______________________________

RR 1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Blanking Plugs/Caps

R 2. Procedure _________ (Ref. Fig. 401 )

A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1ST 16RL 209/E 7 OBSV & AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

B. Removal (1)Unlock Dzus fasteners (4). (2)Remove jack box (3) from receptacle. (3)Disconnect electrical connector (1). (4)Cap connectors (1) and (2).


D. Installation (1)Clean and inspect component interface and adjacent area. (2)Uncap electrical connectors (1) and (2) and check that they are in good condition. (3)Connect electrical connector (1). (4)Install jack box into receptacle and lock Dzus fasteners (4). (5)Remove safety clips and tags and close the following circuit breakers :R 16RL, 17RL, 19RL, 18RL and 50RL

E. Test Test replaced component by operating flight interphone, checking that reception is normal.

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Restore system and aircraft to normal operating condition.


Jack Box Figure 401


STATIC DISCHARGING - DESCRIPTION AND OPERATION ______________________________________________

1. General _______ Through the 6CORONA effect6, the static dischargers disperse the static electricity accumulated on the aircraft in flight.


R **ON A/C 001-107,

(Ref. Fig.001 and 002)

R **ON A/C 108-999,

After AMP LH23-004 For A/C +AF1004009 +AF2006014 +IB2001006 +AZ1001008 (Ref. Fig.003 and 002) *

R **ON A/C 001-107,

------------------------------------------------------------------------------ STATIC DISCHARGERS LOCATION QUANTITY ZONE ------------------------------------------------------------------------------ Wing Tip 4 631-531 Outboard Trailing Edge 6 692-688-592-588 Flap Tracks Flap Track Fairing (right) 4 636-635-634-633 Flap Track Fairing (left) 4 536-535-534-533 Elevator Trailing Edge 6 345-335 Vertical Stabilizer Tip 2 324 Rudder 8 326

R **ON A/C 108-999,

-------------------------------------------------------------------------------- | | QUANTITY | | STATIC DISCHARGERS |--------------------------------------| | LOCATION | Short Discharger | Long Discharger | | | P/N : 16310 | P/N : 16305 | |---------------------------------------|-------------------|------------------| | Wing tip L/H | 3 | 1 | | Wing tip R/H | 3 | 1 | | Low Speed Aileron L/H | - | 6 | | Low Speed Aileron R/H | - | 6 | | Outbd tab of outer flaps LH | - | 1 | | Outbd tab of outer flaps RH | - | 1 | | Flap track fairings L/H | - | 4 | | Flap track fairings R/H | - | 4 | | Elevator L/H | - | 6 | | Elevator R/H | - | 6 | | Rudder | - | 8 | | Vertical Stab. tip | 2 | - |


Static Dischargers - Location Figure 001


Static Discharges - Further Details Figure 002


Static Dischargers - Location * Figure 003


**ON A/C ALL

3. Description ___________ A static discharging point consists of a permanently attached retainer and a removable static discharger held with a screw. Each aluminium retainer is attached to the aircraft structure by rivets. The static discharge points are installed at the tips of the wings, elevator and vertical stabilizer, along the trailing edges of the outboard wings, elevators and rudder. They are also installed on flap track fairings. Two types of trailing edge and tip dischargers, made by GRANGER or CHELTON, can be installed. Both types interface with two differently mounted retainers : - Trailing - edge mounted type, - Tip mounted type. GRANGER type dischargers, colored yellow, consist of a moulded nylon rod housing a resistance element. At the end is a transverse discharge pin with two needle like discharge points, protected by guards to prevent possible injury to personnel. CHELTON type dischargers, colored black, consist of a tapered glass filter rod with a discharge tip of carbon composite material.

4. Operation _________ The dischargers dissipate static electric charge in the following three ways : - By reduction of the voltage level required to start corona discharge, - By causing the discharge to take place perpendicularly to antenna coupling fields. - By making regions of practically zero radio frequency field strength (null - field) and causing the discharge to occur in these regions.


STATIC DISCHARGING - INSPECTION/CHECK _____________________________________

R WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT _______ __________________________________________________R CONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS, ASSOCIATEDR DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUND SAFETIESR AND/OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENT INADVERTENTR OPERATION OF CONTROLS.R WARNING : ON AIRCRAFT HAVING HF SYSTEMS, MAKE CERTAIN THAT HF CIRCUIT BREAKERS _______R ARE OPEN, SAFETIED AND TAGGED BEFORE ATTEMPTING TO REMOVE OR TESTR STATIC DISCHARGERS LOCATED ON VERTICAL STABILIZER.

R 1. Static Dischargers - Visual and Resistance Check ________________________________________________

R A. Equipment and MaterialsR -------------------------------------------------------------------------------R ITEM DESIGNATIONR -------------------------------------------------------------------------------R A. OhmmeterR B. MegohmmeterR C. MilliohmmeterR D. Access platform 6 m (20 ft)R orR E. Access platform 8 m (26 ft)R orR F. Access platform 17 m (56 ft)R G. Warning Notices Prohibiting Operation ofR Elevators, Rudder and FlapsR H. Circuit Breaker Safety Clips and Tags

R 2. Procedure _________

R A. Job Set-UpR (1)Put warning notices in flight compartment.R (2)Put access platform at the static dischargers to be checked.R (3)On aircraft having HF systems, open safety and tag the following circuitR breakers before attempting to remove or test static dischargers locatedR on the vertical stabilizer.R ------------------------------------------------------------------------------R PANEL SERVICE IDENT. LOCATIONR ------------------------------------------------------------------------------R 21VU RADIO/NAV & COM/HF1 4RE1 106/D03R 21VU RADIO/NAV & COM/HF2 4RE2 106/D12R 21VU FAC1/28VDC 306CC1 103/G03R 21VU FAC1/115VAC 309CC1 103/G05R 21VU FAC1/26VAC 305CC1 103/G07R 21VU FAC2/26VAC 305CC2 103/G08R 21VU FAC2/115VAC 309CC2 103/G10R 21VU FAC2/28VDC 306CC2 103/G12

R B. CheckR WARNING : SOME DISCHARGERS HAVE NEEDLE-LIKE PINS WHICH CAN CAUSE INJURY. _______


R ALL ARE RIGID AND A DANGER TO EYES.R CAUTION : DO NOT DAMAGE COMPONENTS OR AIRCRAFT STRUCTURE WITH SHARP END _______R PRODS.R (1)Visual check ; at each discharger :R (a)Visually make certain dischargers are secure on retainer.R (b)Make certain there is no lightning damage as shown by burned or pittedR discharger retainer.R - Granger dischargers (color yellow) :R (c)Make certain there are no bent or broken pins.R NOTE : Broken plastic guards do not affect discharger performances. ____R - Chelton dischargers (color black) :R (d)Make certain carbon composite tip is not missing.R (e)Make certain sleeving is not split or eroded.R (f)Gently flex to make certain that discharger is not broken internally.R (2)Resistance check ; at each static discharger retainer :R (a)For static dischargers of metallic structure, measure resistanceR between the metal part of static discharger and the adjacent structureR using a milliohmmeter. Refer to the table of maximum permissibleR resistance values.R (b)For static dischargers of composite structure, measure resistanceR between the metal part of static discharger and the adjacent structureR using an ohmmeter. Refer to the table of maximum permissibleR resistance values.R (c)Install a new discharger if resistance is out of the tolerance limitsR in the table of maximum permissible resistance values.R (3)Resistance check ; at each static discharger tip (tip TYPE A and trailingR edge TYPE B) :R (a)For static dischargers of metallic or composite structure, measureR resistance between the static discharger retainer and the staticR discharger tip, using a megohmmeter. Refer to the table of maximumR permissible resistance values.R (b)Install a new discharger if resistance is out of the tolerance limitsR in the table of maximum permissible resistance values.

R C. Table of Maximum Permissible Resistance ValuesR -------------------------------------------------------------------------------R CATEGORY RESISTANCE LOCATION HOW TESTEDR MEASUREMENTSR (1) (2) (3) (4)R -------------------------------------------------------------------------------R Static 50 milliohms At the respective Using aR dischargers (maximum) structure tip or milliohmmeter :R installed either trailing edge - measure theR on metallic interfaces : resistance valueR structure or - elevator between theR metallic strip - vertical metal part ofR stabilizer static dischargerR - rudder retainer and theR - wing adjacentR - aileron structure.R - horizontalR stabilizer.


R -------------------------------------------------------------------------------R CATEGORY RESISTANCE LOCATION HOW TESTEDR MEASUREMENTSR (1) (2) (3) (4)R -------------------------------------------------------------------------------RR Static 50 kilo-ohms At the respective Using anR dischargers structure tip or ohmmeter :R installed on trailing edge - measure theR composite interfaces : resistance valueR structure - elevator between theR - vertical metal part ofR stabilizer static dischargerR - rudder retainer and theR - wing adjacentR - aileron structure.R - flap trackR fairingR - horizontalR stabilizer.RR Static Between 6 At the respective Using aR dischargers and 120 structure tip or megohmmeter :R of TYPE A, Megohms trailing edge - measure theR (Tip type). interfaces : resistance valueR Granger make, - elevator between theR color coded - vertical dischargerR Yellow stabilizer retainer and theR or - rudder discharger tipR Chelton make, - wingR color coded - horizontalR Black. stabilizer.

R Static 6 and 200 At the respective Using aR dischargers Megohms structure tip or megohmmeter :R of TYPE B, trailing edge - measure theR (Trailing interfaces : resistance valueR edge type). - elevator between theR Granger make, - vertical dischargerR color coded stabilizer retainer and theR Yellow - rudder. discharger tip.R orR Chelton make,R color codedR Black.

R NOTE : Put megohmmeter crocodile-clip jaws over a small piece of damp sponge or ____R fine wire wool wrapped around the discharger tip to obtain the mostR accurate reading.

R D. Close-Up


R (1)On aircraft with HF systems, remove the safety clips and tags and closeR the following circuit breakers, 4RE1, 4RE2, 306CC1, 309CC1, 305CC1,R 305CC2, 309CC2 and 306CC2.R (2)Remove the access platform(s).R (3)Make sure that the working area is clean and clear of tools andR miscellaneous items of equipment.R (4)Remove the warning notices.


STATIC DISCHARGER - REMOVAL/INSTALLATION ________________________________________

WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT _______ __________________________________________________ CONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS, ASSOCIATED DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUND SAFETIES AND/OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENT INADVERTENT OPERATION OF CONTROLS. WARNING : ON AIRCRAFT HAVING HF SYSTEMS, MAKE CERTAIN THAT HF CIRCUIT BREAKERS _______ ARE OPEN, SAFETIED AND TAGGED BEFORE ATTEMPTING TO REMOTE OR CHECK STATIC DISCHARGERS LOCATED ON TAIL CONE. NOTE : As removal/installation procedures are identical for all static ____ dischargers, only one typical removal/installation procedure is described.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform, 6 m (19 ft. 8 in.) or B. Access Platform, 7.5 m (24 ft. 7 in.) or C. Access Platform, 16.46 m (54 ft.)

2. Procedure _________ (Ref. Fig. 401 )

A. Job Set-Up (1)Position access platform to gain access to static dischargers located at wing tips and on flap track fairings. (2)Position access platform to gain access to static dischargers located on elevators. (3)Position access platform to gain access to static dischargers located at vertical stabilizer tip.

B. Removal (1)Remove attach screw (1). (2)Remove static discharger (2) from base (3). WARNING : AVOID CONTACTING PRODS TO PREVENT INJURY. _______

C. Preparation of Replacement Component (1)Check that the new static discharger does not show evidence of defect, corrosion, or traces of preservative. (2)Clean and inspect the area adjacent to the component on aircraft.

D. Installation (1)Position static discharger (2) on base (3) : avoid contacting prods. (2)Tighten attach screw (1).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscel-


INTENTIONALLY BLANK

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Static Dischargers - LocationR Figure 401

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laneous items of equipment. (2)Remove access platform.

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STATIC DISCHARGER RETAINER - REMOVAL/INSTALLATION _________________________________________________

WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT _______ __________________________________________________ CONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS, ASSOCIATED DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUND SAFETIES AND/ OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENT INADVERTENT OPERATION OF CONTROLS. WARNING : ON AIRCRAFT HAVING HF SYSTEMS, MAKE CERTAIN THAT HF CIRCUIT _______ BREAKERS ARE OPEN, SAFETIED AND TAGGED BEFORE ATTEMPTING TO REMOVE OR CHECK STATIC DISCHARGERS LOCATED ON TAIL CONE.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform, 6 m (19 ft. 8 in.) or B. Access Platform, 7.5 m (24 ft. 7 in.) or C. Access Platform, 16.46 m (54 ft.)RR D. Material No.11-003 Cleaning Agents (Ref. 20-31-00)R E. Material No.09-001 Sealants (Ref. 20-31-00)R F. TEKELEC AIRTRONIC Milliohmmeter, Series Number TE952N or EquivalentR G. RivetsR H. Rivet Gun and AccessoriesR J. Circuit Breaker Safety Clips and TagsR K. Warning Notices - Prohibiting Operation of Elevators, Rudder and FlapsR L. Abrasive Paper (Grade 448)R M. Lint-free ClothR N. Masking PaperR P. Masking TapeR Q. OhmmeterR R. Plastic ScraperR S. Tool, Sharp, Broad Bladed - Retainer Removal Referenced Procedures - 20-30-00, P. Block 1 List of Materials - 23-60-00, P. Block 601 Static Discharging - 23-61-11, P. Block 401 Static Discharger - 51-30-29, P. Block 1 Fastener Installation and Removal (SRM) - 51-12-00, P. Block 801 Repair of Paint Coatings - 55-23-11, P. Block 401 Elevator Tips and Inboard End Caps - 55-34-11, P. Block 401 Vertical Stabilizer Tip - 55-43-11, P. Block 401 Rudder Tip - 57-24-11, P. Block 401 Wing Tip - Structure Complete - 57-36-11, P. Block 401 Flap Track Fairings

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**ON A/C 006-101, 104-104, 106-107,

(Ref. Fig. 401 )


**ON A/C 108-999,

(Ref. Fig. 402 )


**ON A/C 006-101, 104-104, 106-999,

A. Job Set-Up (1)Position access platform to gain access to static dischargers located at wing tips and on flap track fairings. or (2)Position access platform to gain access to static dischargers located on elevators or (3)Position access platform to gain access to static dischargers located at vertical stabilizer tip.R (4)On aircraft having HF systems. Before you attempt to remove, or test,R static dischargers located on the vertical stabilizer, or on the outerR wing if the wing tip has antenna fitted. You must open, safety and tagR the following circuit breakers:R ------------------------------------------------------------------------------R PANEL SERVICE IDENT. LOCATIONR ------------------------------------------------------------------------------R 21VU RADIO - NAV & COM - HF1 4RE1 103/L12R 21VU RADIO - NAV & COM - HF2 4RE2 101/N12

R (5)Position warning notices in flight compartment.

R B. RemovalR WARNING : SOME DISCHARGERS HAVE NEEDLE-LIKE PINS WHICH CAN CAUSE INJURY. _______R ALL ARE RIGID AND A DANGER TO EYES.R (1)Remove static discharger (Ref. 23-61-11, P. Block 401).R (2)Mark position of discharger base beyond cleaning area with aR non-destructive marking.R (3)For removal of static discharger retainers (3) at their respectiveR structure tip, or trailing-edge interfaces:R (a)Remove flap-track movable fairing (Ref. 57-36-11, P. Block 401).R (b)Remove elevator tip (Ref. 55-23-11, P. Block 401).R (c)Remove vertical stabilizer tip (Ref. 55-34-11, P. Block 401).R (d)Remove rudder tip (Ref. 55-43-11, P. Block 401).R (e)Remove wing tip (Ref. 57-24-11, P. Block 401).R (4)Remove rivets (1) (Ref. 51-40-20, P. Block 1, SRM).R (5)Using the plastic scraper, remove fillet of sealant from one edge of

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Static Discharger Retainers - Location Figure 401

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retainer (3). CAUTION : DO NOT DAMAGE AIRCRAFT SURFACES. _______ (6)Insert removal tool under edge of retainer (3) and prize off retainer.

C. Preparation of Replacement Component (1)Make sure that the new retainer (3), does not show signs of defects, corrosion or traces of storage material. (2)Examine the retainer (3) and the aircraft interface for the correct condition.

D. Installation (1)Before the retainer (3) is installed: (a)Drill the new retainer (3) to match with the existing holes. (b)Protect the area surrounding the position of the retainer (3) with masking tape and paper. (c)Lightly abrade and polish the aircraft structure and the retainer (3) with abrasive paper. (d)Remove the dust with a dry, lint-free cloth. (e)Clean the aircraft structure and the retainer (3) interfaces thoroughly with cleaning agent (Material No. 11-003). NOTE : Start to apply Sealant (Material No. 09-001) to the retainer (3) ____ interface, within 5 minutes after it has been cleaned, to prevent aluminium oxidation. (2)Install the retainer (3):R (a)Apply sealant (Material No. 09-001) to the aircraft structure (and theR shim where fitted) and the retainer interfaces.R (b)Affix the retainer (and the shim where fitted) firmly to the aircraftR surface. Squeeze out excess sealant.R (c)Make sure that the retainer is aligned with the non-destructiveR marking.R (d)Wet assemble the rivets (Ref. 51-40-20, P. Block 1, SRM) immediatelyR after applying the sealant.R (e)Remove the excess sealant, but make sure that a fillet of sealant hasR exuded around the edges of the retainer. (3)For the installation of the retainer (3) on the movable fairing, elevator tip, wing tip, and vertical stabilizer tip, respectively: (a)Install the movable fairing (Ref. 57-36-11, P. Block 401). (b)Install the elevator tip, (Ref. 55-23-11, P. Block 401). (c)Install the wing tip (Ref. 57-30-11, P. Block 401). (d)Install the vertical stabilizer tip (Ref. 55-34-11, P. Block 401). (4)On completion of the retainer (3) installation: (a)Make sure that the adhesive compound is dry (24 hours at 21 deg C). NOTE : If required, blow c0ean, hot air on the retainer (3) to reduce ____ the drying time. (5)If required, restore the protective finish with primary and top coats to match the existing paint finish (Ref. 51-12-00, P. Block 801).

E. Test (1)Measure the resistance between the static discharger retainer on the flap track fairings and the aircraft structure using a megohmmeter (Ref. 23-60-00, P. Block 601).


(2)Measure the resistance between all the other static discharger retainers and the aircraft adjacent structure using an ohmmeter (Ref. 23-60-00, P. Block 601).

F. Close-Up (1)Install static discharger on new retainer (Ref. 23-61-11, P. Block 401). (2)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (3)On aircraft having HF systems, remove the safety clips and tags and close circuit breakers 4RE1, 4RE2. (4)Remove access platform(s). (5)Remove warning notices.

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STATIC DISCHARGER RETAINER - REMOVAL/INSTALLATION _________________________________________________

WARNING : BEFORE PROCEEDING WITH MAINTENANCE WORK ON OR NEAR MECHANICAL FLIGHT _______ __________________________________________________ CONTROLS OR PRIMARY FLIGHT CONTROL SURFACES, LANDING GEARS, ASSOCIATED DOORS OR ANY MOVING COMPONENT, MAKE CERTAIN THAT GROUND SAFETIES AND/ OR WARNING NOTICES ARE IN CORRECT POSITION TO PREVENT INADVERTENT OPERATION OF CONTROLS. WARNING : ON AIRCRAFT HAVING HF SYSTEMS, MAKE CERTAIN THAT HF CIRCUIT _______ BREAKERS ARE OPEN, SAFETIED AND TAGGED BEFORE ATTEMPTING TO REMOVE OR CHECK STATIC DISCHARGERS LOCATED ON TAIL CONE.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform, 6 m (19 ft. 8 in.) or B. Access Platform, 7.5 m (24 ft. 7 in.) or C. Access Platform, 16.46 m (54 ft.) D. Material No.11-003 Cleaning Agents (Ref. 20-31-00) E. Material No.09-001 Sealants (Ref. 20-31-00) F. TEKELEC AIRTRONIC Milliohmmeter, Series Number TE952N or Equivalent G. 500V Megohmmeter (GENERAL RADIO 1862C Type or equivalent)RR H. Material No.05-025B Aluminum Oxide (Ref. 20-31-00)R J. Material No.12-005 COMORCAP B1 OR B7 (Ref. 20-31-00)R K. Circuit Breaker Safety Clips and TagsR L. Warning Notices - Prohibiting Operation of Elevator, Rudder and FlapsR M. Abrasive Paper (Grade 448)R N. Lint-free clothR P. Masking PaperR Q. Masking TapeR R. OhmmeterR S. RivetsR T. Rivet Gun and AccessoriesR U. Plastic ScraperR V. Tool, sharp, broad bladed - Retainer Removal

Referenced Procedures - 23-60-00, P. Block 601 Static Discharging - 51-12-00, P. Block 801 Repair of Paint Coatings - 51-30-29, P. Block 1 Fastener Installation and Removal (SRM)


------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------

Referenced Procedures - 20-30-00, P. Block 1 List of MaterialsR - 23-61-11, P. Block 401 Static DischargerR - 55-23-11, P. Block 401 Elevator Tips and Inboard End CapsR - 55-34-11, P. Block 401 Vertical Stabilizer TipR - 55-43-11, P. Block 401 Rudder TipR - 57-24-11, P. Block 401 Wing Tip - Structure CompleteR - 57-36-11, P. Block 401 Flap Track Fairing


(Ref. Fig. 401 )

A. Job Set-Up (1)Position access platform to gain access to static dischargers located at wing tips and on flap track fairings. or (2)Position access platform to gain access to static dischargers located on elevators or (3)Position access platform to gain access to static dischargers located at vertical stabilizer tip.R (4)Position warning notices in flight compartment.R (5)On aircraft having HF systems. Before you attempt to remove, or test,R static dischargers located on the vertical stabilizer, or on the outerR wing if the wing tip has antenna fitted. You must open, safety and tagR the following circuit breakers:R ------------------------------------------------------------------------------R PANEL SERVICE IDENT. LOCATIONR ------------------------------------------------------------------------------R 21VU RADIO - NAV & COM - HF1 4RE1 103/L12R 21VU RADIO - NAV & COM - HF2 4RE2 101/N12

R B. RemovalR WARNING : SOME DISCHARGERS HAVE NEEDLE-LIKE PINS WHICH CAN CAUSE INJURY. _______R ALL ARE RIGID AND A DANGER TO EYES.R (1)Remove static discharger (Ref. 23-61-11, P. Block 401).R (2)Mark position of discharger base beyond cleaning area with aR non-destructive marking.R (3)For removal of static discharger retainers at their respective structure



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tip, or trailing-edge interfaces: (a)Remove flap-track movable fairing (Ref. 57-36-11, P. Block 401). (b)Remove elevator tip (Ref. 55-23-11, P. Block 401). (c)Remove vertical stabilizer tip (Ref. 55-34-11, P. Block 401). (d)Remove rudder tip (Ref. 55-43-11, P. Block 401). (e)Remove wing tip (Ref. 57-24-11, P. Block 401). (4)Remove rivets (Ref. 51-40-20, P. Block 1, SRM). (5)Using the plastic scraper, remove fillet of sealant from one edge of retainer. CAUTION : DO NOT DAMAGE AIRCRAFT SURFACES. _______ (6)Insert removal tool under edge of retainer and prize off retainer.

C. Preparation of Replacement Component (1)Check that the new static discharger retainer does not show evidence of defect, corrosion or traces of storage material. (2)Inspect the area where the retainer is to be installed.

D. Installation (1)Before installing retainer on low speed ailerons and flap track fairings. (a)Clean the retainer location area with a neutral solvent such as trichlorethylene (Material No.11-003). Then make certain that the area is clean (do not touch with fingers). (b)Mix aluminum oxide (Material No.05-025B) with clear water to get a thick paste. Rub concerned area with this compound until any bright spot has been eliminated and the compound becomes dark grey due to the removed aluminum particles. Do not let the compound become too dry. (c)Fully rinse the area with water. The area is clean when it is possible to spread a perfectly even film of water over the surface . (d)Just before applying adhesive compound, carefully dry the surface to _________________________________ remove any trace of moisture. (e)Adhesive compound must be applied within 8 hours following surface cleaning. (f)For laminated surfaces, degreasing is sufficient. (2)Installation of static discharger retainers on low speed ailerons, flap track fairings and vertical stabilizer tip.R (a)Apply sealant (Material No. 09-001) to the aircraft structure (and theR shim where fitted) and the retainer interfaces.R (b)Affix the retainer (and the shim where fitted) firmly to the aircraftR surface. Squeeze out excess sealant.R (c)Make sure that the retainer is aligned with the non-destructiveR marking.R (d)Wet assemble the rivets (Ref. 51-40-20, P. Block 1, SRM) immediatelyR apply the sealant.R (e)Remove the excess sealant, but make sure that a fillet of sealant hasR exuded around the edges of the retainer. (3)Not applicable

(3)Installation of static discharger retainers on rudder.


(a)Job set-up To embody this modification it is necessary to : - make certain that aircraft is statically grounded - position platform to gain access to modification area on rudder. (b)Before the retainer is installed: 1 Drill the new retainer to match with the existing holes. _ 2 Protect the area surrounding the position of the retainer with _ masking tape and paper. 3 Lightly abrade and polish the aircraft structure and the retainer _ with abrasive paper. 4 Remove the dust with a dry, lint-free cloth. _ 5 Clean the aircraft structure and the retainer interfaces thoroughly _ with cleaning agent (Material No. 11-003). NOTE : Start to apply Sealant (Material No. 09-001) to the retainer ____ (1) interface, within 5 minutes after it has been cleaned, to prevent aluminium oxidation. (c)Install the retainer: 1 Apply sealant (Material No. 09-001) to the aircraft structure and the _ retainer interfaces. 2 Affix the retainer firmly to the aircraft surface. Squeeze out excess _ sealant. 3 Make sure that the retainer is aligned with the non-destructive _ marking. 4 Wet assemble the rivets (Ref. 51-30-29, P. Block 1, SRM) immediately _ after applying the sealant. 5 Remove the excess sealant. Make sure that a fillet of sealant has _ exuded around the edges of the retainer. (d)For the installation of the retainer on the movable fairing, elevator tip, wing tip, and vertical stabilizer tip, respectively: 1 Install the movable fitting (Ref. 57-36-11, P. Block 401). _ 2 Install the elevator tip, (Ref. 55-23-11, P. Block 401). _ 3 Install the wing tip (Ref. 57-24-11, P. Block 401). _ 4 Install the vertical stabilizer tip (Ref. 55-34-11, P. Block 401). _ (e)On completion of the retainer installation: 1 Make sure that the adhesive compound is dry (24 hours at 21 deg C). _ NOTE : If required, blow clean, hot air on the retainer to reduce the ____ drying time. (f)If required, restore the protective finish with primary and top coates to match the existing paint finish (Ref. 51-12-00, P. Block 801).

E. Test (1)Measure the resistance between the static discharger retainer on the flap track fairings and the aircraft structure using a megohmmeter (Ref. 23-60-00, P. Block 601). (2)Measure the resistance between all the other static discharger retainers and the aircraft adjacent structure using an ohmmeter (Ref. 23-60-00, P. Block 601).

F. Close-Up (1)Install static discharger on new retainer (Ref. 23-61-11, P. Block 401). (2)Make certain that working area is clean and clear of tools and


miscellaneous items of equipment. (3)On aircraft having HF systems, remove the safety clips and tags and close circuit breakers 4RE1, 4RE2. (4)Remove access platform(s). (5)Remove warning notices.

(4)On completion of retainer installation. (a)Make certain that conducting compound is dry (after 24 hours at 24• C (75• F)). (b)Apply a bead of PR 1422 sealant (Material No. 09-001) at static discharger retainer periphery. (c)Install static discharger on new retainer (Ref. 23-61-11, P. Block 401).

E. Test (Ref. 23-60-00, P. Block 601).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platforms and maintenance equipment.


COCKPIT VOICE RECORDER - DESCRIPTION AND OPERATION __________________________________________________

1. General _______ The cockpit voice recorder is designed to record on magnetic tape crew communications and conversations during flight thus providing a record in the event of a crash. The recorder is a four-track system with all four tracks being recorded simultaneously. The recordings are made on an endless magnetic tape (loop) with total recording capacity of half an hour. When the tape is fully recorded the system progressively erases the earliest recordings while simultaneously recording new information; thus only information recorded during the last half hour of operation is retained. The recorded conversations and communications can be intentionally erased when the aircraft is on the ground with parking brake control handle 7GG pulled up and locked. Playback is not possible unless the recorder is removed from the aircraft and the tape played back on a tape reproducer.

2. Component Location __________________ (Ref. Fig. 001 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RK Control Unit - Cockpit Voice 20VU 210 Recorder (Ref. 23-00-00) 2RK Recorder - Cockpit Voice 171 813 (RECORDER - CKPT VOICE) (Ref. 23-71-35) 4RK Circuit Breaker - RECORDERS/VOICE/ 22VU 210 PWR SUPPLY 5RK Circuit Breaker - RECORDERS/VOICE/ 22VU 210 CONTRL/RELAY 12TU Circuit Breaker - FLT PWR/SUPPLY/ 22VU 210 28VDC 6RK Relay 251VU 122 121BL 7RK Relay 251VU 122 121BL 20RK Switch - Magnetic Latch, AUTO-ON 75VU 212 21RK Indicator Light - FLT RCDR 75VU 212 22RK Diode 122 121BL 23RK Relay 251VU 122 121BL 24RK Relay 251VU 122 121BL 25RK Diode 210 9RL Amplifier - AUDIO INTEG. 121 121BL (Ref. 23-00-00) 13RY Relay 95VU 122 121BL 18GB Relay - RH Gear shock 104VU 120 121BL Absorber (Flight/Ground) 21GB Relay - LH Gear Shock 104VU 120 121BL Absorber (Flight/Ground) 115GB Relay - Nose Gear Shock 104VU 120 121BL Absorber (Flight/Ground) S1-295 Pressure Switch - Low Oil, 435 435AL Engine 1 (Ref. 79-34-11)


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ S1-295 Pressure Switch - Low Oil, 445 445AL Engine 2 (Ref. 79-34-11)


Cockpit Voice Recorder - Component Location Figure 001



Cockpit Voice Recorder - Block Diagram Figure 002

The cockpit voice recorder system consists of :

A. Control unit 1RK providing for cockpit voice recorder test and bulk erase as well as for simultaneous playback of the four recorded tracks. NOTE : Playback is possible in laboratory only using a tape reproducer. ____

B. Cockpit voice recorder 2RK recording communications and conversations between the crew members and also warnings broadcast in the audio warning loudspeakers.

C. Two relays 6RK and 7RK automatically energizing cockpit voice recorder under certain aircraft configurations.

D. Relay 24RK controlling intentional erasure of the magnetic tape.

E. Time-delay relay 23RK enabling cockpit voice recorder to operate during


the five minutes following engine shutdown (aircraft on the ground).

F. Magnetic latch switch 20RK, associated with a blue FLT RCDR indicator light 21RK, enabling the cockpit voice recorder to be switched on manually. The blue indicator light comes on when the switch is placed in ON position.

G. Circuit breaker 4RK supplying cockpit voice recorder with 115VAC power.

H. Circuit breaker 5RK supplying relays 6RK, 7RK, 23RK and 24RK with 28VDC power.

I. Circuit breaker 12TU supplying switch 20RK and indicator light 21RK with 28VDC power.



A. Cockpit Voice Recorder Control Unit (Ref. Fig. 003 )

Cockpit Voice Recorder Control Unit Figure 003

The control unit is attached by means of four dzus fasteners located on the face. An electrical connector is provided at the back for electrical connections. On the face : (1)An area microphone picks up crew membersS conversations and also warnings broadcast in the audio warning loudspeakers. The microphone signal is pre-amplified before being fed to the cockpit voice recorder. (2)An ERASE push-button controls complete erasure of the magnetic tapes. When pressing this push-button, a + 30VDC signal is applied to the erase control relay. (3)A TEST push-button tests cockpit voice recorder for correct operation. (4)A galvanometer monitors recording level during the test sequence (pointer moved by two pulses in the white zone of galvanometer track). (5)A jack allows connection of a headset to check : - either energization or de-energization of the cockpit voice recorder.


- reception of the signals from the three Cabin AttendantsS stations and from the area microphone - the 400 Hz frequency signal from the monitor head in the test sequence - the pulsating 400 Hz frequency signal indicating that bulk erase is taking place.

B. Cockpit Voice Recorder (Ref. Fig. 004 )

Cockpit Voice Recorder Figure 004

The cockpit voice recorder is located in the tail cone of the aircraft. It is attached to a shock mount by means of two locking tabs. (1)On the face - a galvanometer is connected in series with that on the control unit ; it has the same function in the test procedure (deflection of the pointer in the white zone). - a jack allows connection of a headset (function identical to that on control unit) - a TEST 1, 2, 3, 4 selector switch allows separate checking of channel operation. - a TEST push-button allows the application of a 400 Hz test signal to


the four recording channels through TEST 1, 2, 3, 4 selector switch, thus resulting in deflection of the galvanometer pointer in the white zone. - A grip handle allows transportation of the cockpit voice recorder.

R **ON A/C 108-108,

After AMPAF 23-001 - an underwater locating beacon (ULB) enabling radio-electrical search, * is installed on a mounting bracket on the front face of the recorder. *

R **ON A/C 108-999,

(2)The voice recorder is connected to the rest of the system by a connector located at the back. (3)On the left hand side (voice recorder as seen looking aft) a removable panel allows access to the magazine assembly. The magazine is made from laminated plastic, the mechanical resistance of which is not affected by temperature. This provides protection of the recording against fire and shocks. The record, monitor and erase heads are mounted on a separate base inside the magazine. They can be easily removed for maintenance or inspection. Inside the magazine is an endless magnetic tape about 39 m (130 ft.) long, which provides 30 minutes of recording. It is arranged so that the last 30 minutes of conversation are stored on the tape. Intentional erasure is possible on the ground only during the five minutes following engine shut down and with the parking brake control handle pulled up and locked.

C. Relay 6RK In FLIGHT configuration, a ground signal energizes relay 6RK which supplies cockpit voice recorder with 115VAC power through its normally open (NO) contact.

D. Relay 7RK In GROUND configuration, relay 7RK is de-energized and through its normally closed (NC) contact supplies cockpit voice recorder with 115VAC power.

E. Relay 24RK Relay 24RK is energized when parking brake control handle is pulled up and through its normally open (NO) contact transmits a + 30VDC erase signal to erase head.

F. Relay 23RK This time-delay relay energizes after a 5 minutes delay, thereby keeping cockpit voice recorder energized during 5 minutes after engine shutdown in order to enable complete erasure of the tape by the crew.

G. Magnetic latch switch 20RK This switch controls manual energization of the cockpit voice recorder when placed in ON position. Its returns automatically to AUTO position


when one engine is started or by manual override.

H. Blue FLT RCDR indicator light 21RK This blue indicator light indicates manual energization of cockpit voice recorder. It comes on when switch 20RK is in ON position. It is dimmable.



A. Power Supply (1)Automatic power supply The cockpit voice recorder is automatically supplied with 115VAC power in the two following configurations: - in FLIGHT configuration : aircraft in flight with engines running or stopped. - in GROUND configuration : aircraft on the ground with at least one engine running. (a)FLIGHT configuration In flight, relay 115GB on nose gear is de-energized and through its normally closed (NC) contact sends a ground signal to energize relay 6RK. The normally open (NO) contact of relay 6RK power supplies the cockpit voice recorder. (b)GROUND configuration Relay 6RK is de-energized as it no longer receives the ground signal from relay 115GB (aircraft on the ground, relay 115GB energized). Relay 7RK is normally energized by a ground signal from the engine low oil pressure switch (engines shut down). With one engine running, the ground signal to relay 7RK is cut off, thereby de-energized relay 7RK which, through its normally closed (NC) contact, power supplies the cockpit voice recorder. (2)Manual power supply (a)Purpose Manual selection of power supply to cockpit voice recorder allows the following on the ground , with engines shut down : - to test cockpit voice recorder for correct operation - to record the beginning of the check list before the engines start running. (b)Operation Switch 20RK remains latched in ON position by a ground signal from the low oil pressure switch (engines shut down). The ground signal through the normally open (NO) contact of switch 20RK illuminates indicator light 21RK and energizes relay 6RK. Relay 6RK then energizes the cockpit voice recorder. Switch 20RK returns to AUTO position either manually or automatically when one engine at least is running (ground signal from low oil pressure switch cut off). (3)Power supply cut-off The cockpit voice recorder is de-energized when the aircraft is on the ground with engines shut down. A time delay relay enables further operation of the cockpit voice recorder during the five minutes following engine shutdown, for magnetic tape erasure. This is achieved by relay 23RK which, through a five minutes closure delay, cuts off supply to relay 7RK.

B. Recording The recording system contains four identical recording channels. All channels are independent of each other and are separated at input by isolation


Cockpit Voice Recorder - Interconnection Schematic Figure 005


transformers. Channels 3, 2, 1 respectively allow the recording of signals from CaptainSs, First OfficerSs and Flight EngineerSs audio selector panels. Channel 4 allows the recording of the ambient noises picked up by the area microphone on control unit 1RK. Since the four channels are identical, only the operation of channel 1 is described. The AF signal generated from the Flight EngineerSs station is applied to channel 1 of the recorder amplifier. This signal is amplified and con- verted to a constant current signal. The output of the record amplifier is fed to the bias oscillator and mixer module. The bias signal (45 KHz frequency), mixed with the signal corresponding to the recording, is sent to the record head (CH1) which causes channel 1 signal to be recorded magnetically on track 1 of the magnetic tape. Each record head creates its own magnetic impression on the corresponding track. The internal power supply provides a +30VDC voltage to control the relays and a +18VDC voltage to feed area microphone pre-amplifier in the control unit.

C. Monitoring (1)Monitoring using the TEST push-button located on cockpit voice recorder 2RK A 400 Hz AF local test signal is applied to one channel of the recorder amplifier through : - The normally open (NO) contacts of recorder TEST push-button. - Contacts CH1, CH2, CH3, CH4, S1 of recorder TEST selector switch. This signal is processed, then recorded as a normal signal on the selected track of the magnetic tape. The full-width monitor head picks up signals from all four channels. These signals are amplified to a level sufficient to drive a 600 ohm headset. Thus, the monitor signal recorded on the tape can be heard as a 400 Hz beep. The monitor signal is further amplified and detected to drive current through two galvanometers, one located on cockpit voice recorder 2RK, the second on control unit 1RK. The galvanometer return circuit passes through a transistor switch so that the galvanometer is only activated when monitor signals (400 Hz) are expected. (2)Monitoring using the TEST push-button located on control unit (1RK) Actuation of the TEST push-button of the control unit energizes relay K1 in the cockpit voice recorder. One of its normally open (NO) contacts allows application of the 400 Hz remote test to the four recorder amplifiers. Operation is then identical to that described in paragraph 5.C. (1).

D. Bulk Erase (1)Automatic erasure The erase head is permanently activated by a 45 KHz signal. This head, which is located upstream of the record heads, erases the earlier information before a new recording is made.


(2)Controlled erasure This function can only be fulfilled on the ground : - Before engine shutdown with parking brake control handle 7GG pulled up and locked. - Within 5 minutes after engine shutdown with parking brake control handle 7GG pulled up and locked. Bulk erase is instantly performed. A +30VDC signal generated by the cockpit voice recorder power supply is applied to the coil of relay K2 in the cockpit voice recorder through: - The normally open (NO) contacts of RH gear shock absorber relay 18GB. - The normally open (NO) contacts of LH gear shock absorber relay 21GB. - The normally open (NO) contacts of relay 24RK, this relay being energized when parking brake control handle is pulled up and locked. - The normally open contacts of the ERASE push-button located on the control unit. The normally open (NO) contact of relay K2 allows power to be supplied to the bulk erase coil, which generates a magnetic field for erasure of the whole tape.


6. Interface (Ref. Fig. 006 ) _________

Cockpit Voice Recorder - Interface Figure 006

The cockpit voice recorder is interconnected with the following systems :

A. The Flight Interphone System This system transmits information from CaptainSs, First OfficerSs and Flight EngineerSs audio selector panels.

B. The Landing Gear and Associated Doors - Nose gear : relay 115GB transmits a ground signal which energizes relay 6RK (cockpit voice recorder is power supplied). - Main gear : through the normally open (NO) contacts of relays 21GB (LH gear) and 18GB (RH gear) a +30VDC signal is directed to the bulk erase module of the cockpit voice recorder.

C. The low Oil Pressure Warning System A pressure switch on each engine transmits a ground signal (engines shut down) controlling time-delay relay 23RK (supply of recorder with aircraft on the ground during the five minutes following engine shutdown) or con-


trolling latching of switch 20RK (manual energization of cockpit voice recorder).

D. The Public Address System With the engines shutdown, a ground signal from the low oil pressure switch passes through the normally open (NO) contact of relay 13RY and energizes time-delay relay 23RK or latches switch 20RK.

E. The Parking Brake When the parking brake control handle is pulled up and locked, a ground signal energizes relay 24RK and 1 +30VDC signal passing through the normally open (NO) contact controls the bulk erase module of the cockpit voice recorder.

F. The Indicator Light Dimming Circuit FLT RCDR indicator light 21RK is dimmed by application of a reduced voltage through the normally open (NO) contact of relay 23LT. Dimming control is achieved by a switch located on LT panel 65VU.


COCKPIT VOICE RECORDER - DESCRIPTION AND OPERATION __________________________________________________

1. General _______ The cockpit voice recorder is designed to record on magnetic tape crew communications and conversations during flight thus providing a record in the event of a crash. The magnetic tape includes eight tracks : four forward tracks for recording of four independent signals and four reverse tracks performing the same function. When the tape is fully recorded the system progressively erases the earliest recordings while simultaneously recording new information; thus only information recorded during the last half hour of operation is retained. The recorded conversations and communications can be intentionally erased only when the aircraft is on the ground with parking brake control handle pulled up and locked. Playback is not possible unless the recorder is removed from the aircraft and the tape played back on a tape reproducer.

2. Component Location __________________ (Ref. Fig. 001 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1RK Control Unit - Cockpit Voice 20VU 210 Recorder (Ref. 23-71-12) 2RK Recorder - Cockpit Voice 171 813 (RECORDER CKPT VOICE) 162AZ (Ref. 23-71-35) 4RK Circuit Breaker - RECORDERS/ 22VU 210 VOICE/PWR SUPPLY 5RK Circuit Breaker - RECORDERS/ 22VU 210 VOICE/CONTRL/RELAY 6RK Relay 251VU 122 121BL 7RK Relay 251VU 122 121BL 20RK Switch - Magnetic Latch, 75VU 212 AUTO-ON 21RK Indicator Light - FLT RCDR 75VU 212 22RK Diode 122 121BL 23RK Relay 251VU 122 121BL 24RK Relay 251VU 122 121BL 25RK Diode 210 9RL Amplifier - AUDIO INTEG. 121 121BL 13RY Relay 95VU 122 121BL 12TU Circuit Breaker - FLT PWR/ 22VU 210 SUPPLY/28 VDC 18GB Relay - RH Gear Shock 104VU 120 121BL Absorber (Flight/Ground) 21GB Relay - LH Gear Shock 104VU 120 121BL Absorber (Flight/Ground) 115GB Relay - Nose Gear Shock 104VU 120 121BL Absorber (Flight/Ground) S1-295 Pressure Switch - Low Oil, 435 435AL


------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ Engine 1 (Ref. 79-34-11) S1-295 Pressure Switch - Low Oil, 445 445AL Engine 2 (Ref. 79-34-11) 1329VC Jack 144


Cockpit Voice Recorder - Component Location Figure 001



Cockpit Voice Recorder - Block Diagram Figure 002

The cockpit voice recorder system consists of :

A. Control unit 1RK providing for cockpit voice recorder test and bulk erase as well as for simultaneous playback of the four recorded tracks.

B. Cockpit voice recorder 2RK which permanently records interphone conversations and ambient noise in the flight compartment (conversations, aural warnings...). NOTE : Playback is possible in laboratory only using a tape reproducer. ____

C. Two relays 6RK and 7RK automatically energizing cockpit voice recorder under certain aircraft configurations.

D. Relay 24RK controlling complete erasure of the magnetic tape.

E. Time-delay relay 23RK enabling cockpit voice recorder to operate during


the five minutes following engine shutdown.

F. Magnetic latch switch 20RK, associated with a blue FLT RCDR indicator light 21RK, enabling the cockpit voice recorder to be switched on manually.

G. Three power supply circuit breakers : - 4RK, which supplies cockpit voice recorder with 115VAC. - 5RK, which supplies the relays with 28VDC. - 12TU, which supplies magnetic latch switch and blue FLT RCDR indicator light with 28VDC.



A. Cockpit Voice Recorder Control Unit (Ref. Fig. 003 )

Cockpit Voice Recorder Control Unit Figure 003

The control unit is attached by means of four dzus fasteners located on the face. An electrical connector is provided at the back for electrical connections. On the face : (1)An area microphone picks up ambient noise (aural warnings, conversations between crew members). The power is internally adjustable. (2)An ERASE push-button controls complete erasure of the magnetic tape. (3)A TEST push-button tests cockpit voice recorder for correct operation. (4)A galvanometer monitors recording level during the test sequence. (5)A jack allows connection of a headset to check energization or de-energization of the cockpit voice recorder, to listen to the signals received by the four cockpit voice recorder channels and to listen to the 400 Hz frequency signal from the monitor head in test sequence. During bulk erasure, the pulsating 400 Hz frequency signal indicating


that erasure is taking place can be listened to.

B. Cockpit Voice Recorder (Ref. Fig. 004 )


The cockpit voice recorder is located in the tail cone of the aircraft. It is attached to a shock mount by means of two locking tabs. (1)On the face : - a status indicator controlled by pressing the test push-button, enables the recording level to be monitored and faulty channels to be detected. - a phone jack allows connection of a headset (function identical to that on control unit). - a handle allows transportation and installation of the recorder. The recorder is enclosed in a removable orange case with the following French and English legend on each side : ENREGISTREUR DE VOL-NE PAS OUVRIR/FLIGHT RECORDER-DO NOT OPEN. The case is made of stainless steel and is fireproof - an underwater locating device (ULD) enabling radio-electrical search, is installed on a mounting bracket under the handle.


(2)The voice recorder is connected to the rest of the system by a connector located at the back. (3)On the left hand side (cockpit voice recorder as seen looking aft) a removable panel allows access to the magazine assembly. (4)Inside the cockpit voice recorder there are three plug-in cards, a base on which are mounted the record, monitor and erase heads and a magnetic tape for eight track recording, 69m (230ft.) long. The magnetic tape moves at 7cm/sec (2 3/4in./sec), enabling the last 30 minutes of recording to be retained. At the end of the tape, direction change is automatic and the recording continues on the second set of four tracks, erasing anything previously recorded on these tracks.

C. The sequencing relays are controlled as follows : - relay 6RK is controlled by nose gear shock absorber position (by relay 115GB). - relays 7RK and 23RK supply the cockpit voice recorder when aircraft is in GROUND configuration. - relay 24RK is energized when parking brake control handle is pulled up and locked. - relay 23RK is controlled by the engine low oil pressure switch (slow operating relay).

D. Monitoring and Control - magnetic latch switch 20 RK must be placed manually in ON position to supply the cockpit voice recorder on the ground. It returns automatically to AUTO position as soon as one engine is started up. - blue FLT RCDR indicator light 21RK indicates manual energization of the cockpit voice recorder. It comes on as soon as switch 20RK is placed in ON position. This indicator light is dimmable.



A. Power Supply (1)Automatic power supply The cockpit voice recorder is automatically supplied with 115VAC power in the two following configurations : - FLIGHT configuration : Relay 115GB (de-energized as nose gear shock absorber is extended) sends a ground signal to energize relay 6RK. Relay 6RK contact A (closed) power supplies the cockpit voice recorder. - GROUND configuration : Relay 115GB is energized (nose gear shock absorber compressed). Relay 6RK contact A (open) cuts cockpit voice recorder power supply. Relay 7RK contact A (energized, ground sent through relay 23RK relay 13RY which is energized, and low oil pressure switch S1-295) cuts cockpit voice recorder power supply. As soon as an engine is started up, relay 7RK is de-energized (ground signal is cut by relay 13RY and low oil pressure switch S1-295). The cockpit voice recorder is then power supplied through relay 7RK contact A. (2)Manual power supply (a)Purpose Manual selection of power supply to cockpit voice recorder allows the following on the ground, with engines shut down - to test cockpit voice recorder for correct operation - to record the beginning of the check list before the engines start running. (b)Operation Magnetic latch switch 20RK is magnetically held in the ON position by a ground signal from relay 13RY (contact B) and engine 2 low oil pressure switch S1-295. Relay 6RK is energized and supplies the cockpit voice recorder. As soon as an engine is started, magnetic latch switch 20RK is no longer self-held and returns to AUTO position (ground signal cut by engine low oil pressure switch). Cockpit voice recorder is supplied by relay 7RK which is de-energized. (3)Power supply cut-off The cockpit voice recorder is normally de-energized when the aircraft is on the ground with engines shut down. After engine shutdown, a time delay relay (23RK) enables further operation of the cockpit voice recorder during the five minutes following engine shutdown, for magnetic tape erasure. This time delay relay delays energization of relay 7RK.

B. Recording The recording system contains four identical recording channels. All channels are independent of each other and are separated at input by isolation transformers. Channels 1, 2 and 3 respectively allow the recording of signals from Flight EngineerSs, First OfficerSs and CaptainSs audio selector panels. Channel 4 allows the recording of ambient noises in the flight compartment


INTENTIONALLY BLANK


Cockpit Voice Recorder - Interconnection Schematic Figure 005


picked up by the area microphone on control unit 1RK. Since the four channels are identical, only the operation of channel 1 (Flight EngineerSs) is described. The AF signal generated from the Flight EngineerSs station is applied to channel 1 of the recorder amplifier through the isolation transformer. The mixer stage adjusts the signals and sends them to the record head which records on the appropriate track. At the end of the tape the control motor switches the track 1 signal to the other record head and reverses tape direction. A 45 KHz signal erases all but the last 30 minutes of the previous recording. A monitoring circuit with 2 amplifiers (one for each tape direction) supplies the jack outputs on the cockpit voice recorder and on the control unit. The main internal power supplies and signals are as follows - + 24VDC for motors and transfer relays. - + 15VDC for channel amplifier polarization. - + 18VDC for control unit area microphone amplifier. - a 400 Hz signal generator for recording test.

C. Monitoring (1)Monitoring using the TEST push-button located on cockpit voice recorder 2RK. A 400 Hz signal is applied at the input of the amplifier for each of the four channels. This signal is recorded on each track and can be monitored by the head-set or checked by the status indicator, which must flash. If the status indicator does not come on, at least two channels are faulty. If the status indicator flashes once only, one channel is faulty. (2)Monitoring using the TEST push-button located on control unit (1RK). This push-button is connected in parallel with the TEST push-button on the cockpit voice recorder. It operates as described above (producing galvanometer pointer deviations).

D. Erasure (1)Automatic erasure The erase heads are activated alternately by a permanent 45KHz signal from the bias/erase osc. and driver stage. (2)Controlled erasure Controlled erasure can only be carried out on the ground (condition given by relays 21GB and 18GB) with parking brake control handle 7GG pulled up and locked, before engine shutdown or within 5 minutes after engine shutdown (condition given by relay 23RK). ERASE push-button on the control unit must be pressed and held for at least 14 seconds. A 24VDC signal generated in the cockpit voice recorder controls the bulk erase switch relay through : - contact B of relay 18GB (RH main gear) - contact A of relay 21GB (LH main gear) - contact A of relay 24RK (energized by a ground connection being made across a contact of parking brake control handle 7GG). As soon as the engines are shut down - relay 13RY is energized (grounded by low oil pressure switch S1-295). - relay 23RK is energized (grounded through contact B of relay 13RY). - 5 minutes after engine shutdown, relay 23RK contact B grounds relay


7RK which cuts off cockpit voice recorder power supply (contact A). A ground connection jack located next to refuel/defuel panel 110VU allows sounds or discussions in the flight compartment to be heard.

6. Interface _________ (Ref. Fig. 006 )

Cockpit Voice Recorder - Interface Figure 006

The cockpit voice recorder is interconnected with the following systems :

A. Flight Interphone System (Ref. 23-51-00) Information to be recorded is picked off from CaptainSs, First OfficerSs and Flight EngineerSs audio selector panels.

B. Landing Gear (Ref. 32-61-03) - The nose gear enables cockpit voice recorder power supply. - The main gears authorize magnetic tape erasure on the ground.

C. Parking Brake (Ref. 32-42-00) The main landing gears and the parking brake (circuit connected in series)


authorize magnetic tape erasure on the ground.

D. Engines (Ref. 79-30-01) Start-up of one engine inhibits magnetic tape erasure and authorizes cockpit voice recorder power supply (ground connection out by low oil pressure switch).


COCKPIT VOICE RECORDER - FAULT ISOLATION ________________________________________



COCKPIT VOICE RECORDER - ADJUSTMENT/TEST ________________________________________


A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase 115/200 V, 400 Hz, 90KVA (2) Headset (600Ω) Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

B. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation is operating (Ref. 21-20- 00, P. Block 301). (3)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU RECORDERS/VOICE/PWR/SUPPLY 4RK 210/K10 22VU RECORDERS/VOICE/CONTRL/RELAY 5RK 210/K11 22VU FLT/PWR/SUPPLY/28VDC 12TU 210/K12 128VU LDG GEAR/RELAY 1GB 805/A11 128VU LDG GEAR/RELAYS & RETRACT CONTRL 2GB 805/A 9

(4)On overhead panel 20VU, on control unit 1RK connect a headset (600 ohms) to jack.

C. Test (1)Test of cockpit voice recorder

R **ON A/C 108-999,

------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At Flight EngineerSs - Switch is latched in ON position station, on panel 75VU, - Blue FLT RCDR indicator light place ON-AUTO switch comes on. in ON position.

2. On panel 20VU, on Approximately two seconds later, control unit 1RK, hold - on control unit galvanometer, TEST push-button pressed pointer deflects in white sector - a 400 Hz audio frequency signal is audible in headset.


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 3. Release TEST push- Approximately two seconds later, button - galvanometer pointer no longer deflects - 400 Hz audio frequency signal is no longer audible in headset

4. Press and release TEST Approximately 1 to 1.5 second later, push-button - galvanometer, pointer is moved by two pulses in white sector - A 400 Hz audio frequency signal is audible in headset during deflections of pointer

R **ON A/C 001-104,

------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At Flight EngineerSs Switch latches in ON position. station, on panel 75VU, Blue FLT RCDR indicator light place ON-AUTO switch in comes on. ON position.

2. On panel 20VU, on con- Approximately 2 seconds later trol unit 1RK, press and - on control unit 1RK galvanometer, hold TEST push-button. pointer deflects twice and returns to zero. - a 400 Hz audio frequency signal is audible in headset.

3. Release TEST pushbutton Approximately 2 seconds later - galvanometer pointer no longer deflects. - 400 Hz audio frequency signal is no longer audible in headset.

R **ON A/C 001-104, 108-999,

(2)Test of manual erasure ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On center pedestal, pull up and lock parking brake control handle


------------------------------------------------------------------------------- ACTION RESULT -------------------------------------------------------------------------------

R **ON A/C 008-008, 108-999,

2. On control unit 1RK, - 400Hz signal is audible in press ERASE pushbutton headset. no more than 7 seconds.

R **ON A/C 001-007, 009-104,

2. On control unit 1RK, - Pulsating 400 Hz signal is audible press ERASE push-button in headset. no more than 7 seconds.

**ON A/C 001-104, 108-999,

3. On panel 75VU, place - Blue FLT RCDR indicator light ON-AUTO switch in goes off. AUTO position. (3)Audio check (a)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1ST 16RL 209/E 7 OBSV AND AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

(b)Speak in a normal voice in flight compartment at least 4 feet from area microphone, continue to monitor audio with headset, and ascertain that spoken audio is present after approximately 2 seconds. Check message for clarity and loudness. (c)Cover area microphone on voice recorder control unit to prevent pickup of sound. (d)Check CaptainSs recorder channel 1 Monitor voice recorder audio. _ 2 Select interphone at CaptainSs audio selector panel. _ 3 Speak into CaptainSs hand microphone. _ 4 Ascertain that spoken test message is present in recorder output _ audio after delay of approximately 2 seconds. Check message for clarity and loudness. (e)Repeat step (d) at First OfficerSs and Flight EngineerSs stations.

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 001-104, 108-999, K 23-71-00 K K CONF. 01 K K Page 503 K K JAS Mar 01/03

D. Close-Up (1)On overhead panel 20VU, on control unit 1RK, disconnect headset. (2)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (3)Remove all ground handling and maintenance equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.

R **ON A/C 108-108,

After AMPAF 23-001


A. Of System Identical with Operational Test

B. Of Underwater Acoustic Beacon (1)Reason for the job (a)To check correct operation of beacon (2)Equipment and materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (a)42A12 or 42A12A Ultrasonic Test Set (b) Stopwatch

(3)Job set-up (a)On test set, place INPUT SELECTOR in INT position. (b)Check correct operation of test set by jingling a bunch of keys, coins or other noise producing objects near the microphone. Place TUNING CONTROL between 35 and 40 KHz. (c)Establish a temporary circuit across the beacon battery by means of a metal braid or other flexible conductor. Place the test set microphone as near as possible to the beacon and tune test set to obtain the best signal. (4)Test (a)Using stopwatch, count the number of pulses in a 10-second period. Divide the number by ten to obtain the pulse repetition rate. The repetition rate must be between 0.6 and 2. (b)Pulse duration can be determined by displaying the output of the test set on an oscilloscope. (c)Operating frequency can be read on the dial by tuning the test set to the acoustic signal. NOTE : In air, the pulse duration will be longer and the pulse ____ repetition rate slower than during tests performed by the manufacturer . However, an accelerated or increasing repetition rate indicates an expired battery . If normal operation does not occur after installation of a new battery, beacon should be replaced.


(5)Close-up (a)Remove temporary circuit established with metal braid or flexible conductor. (b)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

**ON A/C 001-104,


A. Identical with Operational Test System

B. Underwater Acoustic Beacon (1)Equipment and materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (a) - Ultrasonic Test Set PINGLITE Model PL1 (b) - Stopwatch NOTE : Functional test can be performed without removing beacon from CVR. ____

(2)Test (a)Short water switch on beacon with metal braid or wire from center pin to case. (b)Press end of PL1 test set to beacon body approximately, 16 from switch end. (c)Press and hold operation button on Pl1 test set. (d)Light flashes with each output pulse of beacon indicating it is operating. (e)Using stopwatch, count the number of pulses in a 10-second period. Divide the number by ten to obtain the pulse repetition rate. The repetition rate must be between 0.6 and 2. NOTE : In air, the pulse duration will be longer and the pulse ____ repetiton rate slower than during tests performed by the manufacturer. An accelerated or increasing pulse repetition rate indicates an expired battery. (3)Close-up (a)Remove short-circuit. (b)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

R **ON A/C 103-104,

R 2. Functional Test _______________

R A. Of SystemR Identical with Operational Test


R B. Functional Test of the Underwater Locating Beacon (ULB)R CAUTION : DO NOT PUT MARKINGS OR LABELS ON THE ULB (ONLY THE BATTERY _______R REPLACEMENT LABEL IS PERMITTED). THEY CAN DECREASE THER PROPAGATION.R (1)Reason for the jobR To do a check of the Operation of the ULB.R (2)Job set-up informationR (a)Fixtures, tools, test and support equipmentR -------------------------------------------------------------------------------R REFERENCE QTY DESIGNATIONR -------------------------------------------------------------------------------R No specific electrical leadR No specific stopwatchR No specific access platform 6 m (19 ft. 8 in.)R 42A12B 1 ULTRASONIC TEST SET

R (b)Consumable materialsR -------------------------------------------------------------------------------R REFERENCE DESIGNATIONR -------------------------------------------------------------------------------R Material No. 11-005 TRICHLOROTRIFLUORO ETHANE (Ref. 20-31-00)

R (c)Referenced informationR -------------------------------------------------------------------------------R REFERENCE DESIGNATIONR -------------------------------------------------------------------------------R 23-71-36 P. Block 401 Discard Underwater Locator Beacon (ULB)R Battery of Cockpit Voice Recorder

R (3)Job set-upR NOTE : Make sure that a new ULB is available for ULB replacement. ____R (a)Get accessR 1 Put the access platform in position at the access door 312AR. _R 2 Open the access door 312AR. _R (b)Aircraft maintenance configurationR 1 On the ULB, look at the date on the battery replacement label. If the _R date is expired, replace the battery (Ref. 23-71-36).R NOTE : If the ULB Type DK100 is installed, send the ULB to the ____R related vendor to replace the battery.R 2 On the ULTRASONIC TEST SET (42A12B) : _R - set the INPUT switch to INT,R - set the TUNING potentiometer to between 35 KHz and 40 KHz.R - set the GAIN potentiometer to the maximum position.R 3 Make a short circuit between the water switch of the ULB and the body _R of the battery. Use an electrical lead.R 4 Put the microphone of the test receiver as near as possible to the _R ULB. Tune the test receiver to get the best signal.R (4)Procedure


R -------------------------------------------------------------------------------R ACTION RESULTR -------------------------------------------------------------------------------R 1. With a stopwatch, count theR number of pulses from the ULBR during a cycle of 10 seconds.RR 2. Calculate the pulse rate : The pulse rate must be approximatelyR - divide the number of pulses one pulse per second.R during the cycle by the numberR of seconds (10 seconds).RR 3. You can measure the pulseR duration with an oscilloscopeR connected to the output of theR test receiver.RR 4. You can measure the transmission On the test receiver :R frequency of the ULB with the - read the frequency at the TUNINGR test receiver tuned to this potentiometer.R frequency.RR NOTE : For this test in air : ____R - the pulse duration will be longerR - the pulse rate will be slowerR than in the test by the manufacturer (in water).R But if the pulse rate increases or is much faster, you mustR replace the battery.R If the ULB does not operate correctly after the replacement of theR battery, you must replace the ULB.

R (4)Close-upR (a)Put the aircraft back to its initial configurationR 1 On the test receiver : _R - set the TUNING potentiometer to zero,R - set the GAIN potentiometer to OFF.R 2 Disconnect the electrical lead that connects the water switch to the _R body of the battery (short circuit).R 3 Make sure that there is no grease on the support of the ULB and the _R water switch.R If you find grease, clean it off with CLEANING AGENTS (Material No.R 11-005).R 4 Make sure that there are no markings or labels other than the battery _R replacement label on the ULB.R They can decrease the propagation.R (b)Close accessR 1 Close the access door 312AR. _R 2 Remove the access platform(s). _




A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-phase, 115/200 V, 400 Hz, 90KVA (2) Headset (600Ω) Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

B. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (3)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU RECORDERS/VOICE/PWR/SUPPLY 4RK 210/D 8 22VU RECORDERS/VOICE/CONTRL/RELAY 5RK 210/D 9 22VU FLT/PWR/SUPPLY/28VDC 12TU 210/D10 128VU LDG GEAR/RELAY 1GB 805/A11 128VU LDG GEAR/RELAYS & RETRACT CONTRL 2GB 805/A 9

(4)On overhead panel 20VU, on control unit 1RK connect a headset (600 ohms) to jack.

C. Test (1)Test of cockpit voice recorder ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At Flight EngineerSs station,on panel 75VU - place ON-AUTO switch in ON position Switch is latched in ON position Blue FLT RCDR indicator light comes on

2. On overhead panel 20VU, on control Approximately one second later unit 1RK - press and hold TEST switch - indicator light comes on - a 800 Hz audio frequency signal is audible in headset

- release TEST switch - indicator light goes off - the 800 Hz audio frequency signal


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- is no longer audible in headset


2. On control unit 1RK, press ERASE No signal is audible in headset switch no more than 7 seconds

3. At Flight EngineerSs station, on Check that blue FLT RCDR indicator panel 75VU light goes off - place ON-AUTO switch in AUTO position

(3)Audio check (a)Make certain that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL/1ST OBSV AND 16RL 209/E 7 AVIONICS 22VU AUDIO SYS/CONTRL PNL/F/O 17RL 209/E 8 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/INTPH AMPLI/SERV 20RL 209/E10 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12

(b)Speak in a normal voice in flight compartment at least 4 feet from area microphone, continue to monitor audio with headset, and ascertain that spoken audio is present after approximately 2 seconds. Check message for clarity and loudness. (c)Cover area microphone on voice recorder control unit to prevent pickup of sound. (d)Check CaptainSs recorder channel 1 Monitor voice recorder audio. _ 2 Select interphone at CaptainSs audio selector panel. _ 3 Speak into CaptainSs hand microphone. _ 4 Ascertain that spoken test message is present in recorder output _ audio after delay of approximately 2 seconds. Check message for clarity and loudness. (e)Repeat step (d) at First OfficerSs and Flight EngineerSs stations.

E. Close-Up (1)On overhead panel 20VU, on control unit 1RK, disconnect headset. (2)De-energize the aircraft electrical network and disconnect electrical


ground power unit (Ref. 24-41-00, P. Block 301). (3)Remove all ground handling and maintenance equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.




A. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit -3-Phase, 115/200 V, 400 Hz, 90KVA (2) Headset (600 Ω) Referenced Procedure - 24-41-00, P. Block 301 External Power

B. Job Set-Up (1)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (2)Make certain that forward services ventilation is operating. (3)Make certain that the following circuit breakers are closed :

------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU RECORDERS/VOICE/PWR SUPPLY 4RK 210/K10 22VU RECORDERS/VOICE/CONTRL RELAY 5RK 210/K11 22VU FLT/PWR/SUPPLY/28VDC 12TU 210/K12 ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 128VU LDG GEAR/RELAY 1GB 805/A11 128VU LDG GEAR/RELAYS & RETRACT CONTRL 2GB 805/A 9

(4)On overhead panel 20VU, on control unit 1RK, connect a headset (600 ohms) to jack.

C. Test (1)Test of cockpit voice recorder ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At Flight EngineerSs station, - switch is latched in ON position on panel 75VU, place ON-AUTO - Blue FLT RCDR indicator light switch in ON position comes on

2. On panel 20VU, on control Approximately two seconds later, unit 1RK, hold TEST push-button - on control unit galvanometer, pressed pointer deflects in green sector - a 600 Hz audio frequency signal is audible in headset

3. Release TEST push-button Approximately two seconds later, - galvanometer pointer no longer


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- deflects - the 600 Hz audio frequency signal is no longer audible


2. On control unit 1RK, press ERASE Check that a 400 Hz erase signal is push-button for minimum 2 seconds audible in headset and release

3. On panel 75VU, place ON-AUTO Blue FLT RDCR indicator light goes switch in AUTO position off

(3)Audio check (a)Make certain that the following circuit breakers are closed : 16RL, 17RL, 18RL, 19RL, 20RL and 50RL. (b)Speak in a normal voice in flight compartment at least 4 feet from area microphone, continue to monitor audio with headset, and ascertain that spoken audio is present after approximately 2-second. Check message for clarity and loudness. (c)Cover area microphone on voice recorder control unit to prevent pickup of sound. (d)Check CaptainSs recorder channel 1 Monitor voice recorder audio. _ 2 Select interphone at CaptainSs audio selector panel. _ 3 Speak into CaptainSs hand microphone. _ 4 Ascertain that spoken test message is present in recorder ouput _ audio after delay of approximately 2 seconds. Check message for clarity and loudness. (e)Repeat step (d) at First OfficerSs and Flight EngineerSs stations.

D. Close-Up (1)On control unit 1RK, disconnect headset. (2)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (3)Remove all ground handling and maintenance equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.

2. System Test ___________

A. Initial Conditions (1)Make certain that interface systems are in operating condition :


- Service interphone (Ref. 23-41-00, circuit RL) - Control and indicating of landing gear legs and doors (Ref. 32-30-00, circuits GA and GB) - Digital Flight Data Recorder (Ref. 31-31-00, circuit TU). - Engine oil pressure (Ref. 79-33-00)

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Electrical Ground Power Unit - 3-Phase, 115/200 V, 400 Hz, 90KVAR (2)860135953100000 or Main Landing Gear Safety Relay ControlR 97A32602004000 Simulator Test Set. (3)860135950100000 - Engine Oil Pressure Simulator - Test Set (4) - Hand Microphone and Headset Referenced Procedures - 21-20-00, P. Block 301 Distribution/Extraction - 24-41-00, P. Block 301 External Power

C. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU RECORDERS/VOICE/PWR SUPPLY 4RK 210/K10 22VU RECORDERS/VOICE/CONTRL RELAY 5RK 210/K11 22VU FLT PWR SUPPLY 28VDC 12TU 210/K12 ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU AUDIO SYS/CONTRL PNL F/O 17RL 209/E 8 22VU AUDIO SYS/CONTRL PNL/CAPT 18RL 209/E11 22VU AUDIO SYS/INTPH AMPLI/FLT 19RL 209/E 9 22VU AUDIO SYS/CONTRL PNL/FLT ENGR 50RL 209/E12 128VU LDG GEAR/RELAY 1GB 805/A11 128VU LDG GEAR/RELAYS & RETRACT CONTRL 2GB 805/A 9 123VU ENG1/FUEL HP VALVE/WARNLT 1KC 302/C 5 123VU ENG1/FUEL HP VALVE/CONTRL 3KC 302/C 6 123VU ENG2/FUEL HP VALVE/WARN LT 2KC 302/C12 123VU ENG2/FUEL HP VALVE/CONTRL 4KC 302/C13

(2)Install main landing gear safety relay control simulator test set On test set (a)place TRAIN GAUCHE AMORTIS 63GB and TRAIN DROIT AMORTIS 62GB switches in VOL position (b)place TRAIN AVANT AMORTIS 55GB switch in SOL position. (3)Install engine oil pressure simulator test set. On simulator test set : - place switches in 6Engine shut down6 mode or in 6Low oil pressure6 function.

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 106-107, K 23-71-00 K K CONF. 03 K K Page 503 K K JAS Mar 01/05

WARNING : BEFORE POWER IS SUPPLIED TO THE AIRCRAFT MAKE CERTAIN THAT _______ ELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED. (4)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (5)Make certain that forward services ventilation is operating (Ref. 21-20-00, P. Block 301). (6)On overhead panel 20VU, on control unit 1RK, connect a headset to jack. (7)On each audio selector panel - disengage transmission keys - disengage reception push-buttons. (8)At each crew memberSs station - connect a hand microphone - place RAD-INT PTT switch in intermediate position. (9)Remove safety clips and tags and close circuit breakers : (a)1KC, 2KC, 3KC and 4KC on panel 123VU (b)1GB and 2GB on panel 128VU (c)4RK, 5RK, 12TU, 17RL, 18RL, 19RL and 50RL on panel 22VU.

D. Test (1)Test conditions required ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. Five minutes after closing of circuit breakers 4RK and 5RK on panel 75VU - place FLT - RCDR switch 20RK in On panel 75VU ON position - switch 20RK is magnetically held in ON position - blue FLT RCDR indicator light 21RK comes on In bulk cargo compartment - cockpit voice recorder 2RK is supplied.

2. On main landing gear safety relay control simulator test set - place switch 55GB in VOL position.

On engine oil simulator test set On panel 75VU - place switches in NORMAL posi- - switch 20RK returns to AUTO tion position - FLT RCDR indicator light 21RK goes off In bulk cargo compartment - cockpit voice recorder 2RK is still supplied.

(2)Check of recordings from the three crew memberSs stations and area microphone.


NOTE : Recordings from the four different areas last 30 mn maximum ____ (beyond this limit, recording is automatically erased). (a)Test set up - connect a hand microphone and an earphone in each area. On each audio selector panel - select reception and adjust power level - select transmission (b)Prepare a text to be used as locating message when recording and such as 6this is a transmission from CaptainSs station preceding recording on channel No.36 (channel No.2 for First Officer, Channel No.1 for Flight Engineer, channel No.4 for area microphone). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. At CaptainSs Station Check reception at headset while - press hand microphone PTT speaking into hand microphone. switch and announce test and locating messages.

2. At First OfficerSs station - repeat test with corresponding Check reception at headset while locating message speaking into hand microphone

3. At Flight EngineerSs Station Check reception at headset while - repeat test with corresponding speaking into hand microphone. locating message

4. Repeat test with corresponding Check reception at headset while locating message at approximately speaking into hand microphone 1m from area microphone.

(3)Recording of aural warnings via area microphone - trigger some aural warning such as continuous horn by pressing GEAR GROUND TEST push-button 12GB on panel 6VU. (4)Test of cockpit voice recorder ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On control unit 1RK On control unit 1RK - connect headset - an intermittent 600 Hz signal is audible - press TEST push-button during - indicator pointer deflects in green 5 seconds approx. sector

(5)Check of erasure control ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- 1. On main landing gear safety relay control simulator test set - place TRAIN GAUCHE switch 63GB in SOL position


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - place TRAIN DROIT switch 62GB in SOL position

2. On center pedestal pull up and lock parking brake.

3. At one crew memberSs station - check recording with a headset. carry out a transmission with recording

4. On control unit - connect a headset - press ERASE push-button for On control unit 2 seconds minimum then release - a 400 Hz signal is audible in head set.

NOTE : Total erasure of the tape lasts 6 seconds maximum ____

5. On main landing gear safety relay control simulator test set - place TRAIN GAUCHE switch 63GB in VOL position - place TRAIN DROIT switch 62GB in VOL position.

6. On control unit - press ERASE push-button - recording is heard at headset (erasure impossible).

7. On main landing gear safety relay control simulator test set - place TRAIN GAUCHE switch 63GB in SOL position - place TRAIN DROIT switch 62GB in SOL position

On center pedestal, release parking brake

On control unit, press ERASE - recording is heard at headset push-button (erasure impossible)

8. On main landing gear safety relay control simulator test set - place switch 55GB in SOL position

9. On engine oil pressure simulator The cockpit voice recorder remains test set energized, during 5 min. - place switches in BP (LP) posi-


------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- tion

10.Five minutes later, on center pedestal, pull up and lock parking brake.

E. Close-Up (1)On crew memberSs audio selector panels, select reception and cancel transmission. (2)Disconnect headset from control unit 1RK. (3)At each crew memberSs station - disconnect hand microphone - disconnect headset - place PTT switches in intermediate position (4)Open, safety and tag circuit breakers : (a)1KC, 2KC, 3KC and 4KC on panel 123VU (b)1GB and 2GB on panel 128VU (c)4RK, 5RK, 12TU, 17RL, 18RL, 19RL and 50RL on panel 22VU. (5)Remove main landing gear safety relay control simulator test set. (6)Make certain that connector of engine 1 low oil pressure switch S1-295) is correctly safetied. (7)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301). (8)Remove all ground handling and maintenance equipment, standard and special tools together with ground power and replenishing equipment, all access equipment and miscellaneous items.


COCKPIT VOICE RECORDER CONTROL UNIT 1RK - REMOVAL/INSTALLATION ______________________________________________________________


Control Unit - Removal/Installation Figure 401


A. Job Set-Up (1)Open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 22VU RECORDERS/VOICE/PWR/SUPPLY 4RK 204/K10 22VU RECORDERS/VOICE/CONTRL/RELAY 5RK 204/K11 22VU RECORDERS/FLT/PWR/SUPPLY/28VDC 12TU 204/K12


B. Removal (1)Unlock the four dzus fasteners (1) and withdraw control unit (2)Disconnect electrical connector (2) and leave it free outside panel.


D. Installation (1)Connect electrical connector (2). (2)Position control unit and lock the four dzus fasteners (1). (3)Remove safety clips and tags and close the circuit breakers listed above.

E. Test Carry out a cockpit voice recorder operational test (Ref. 23-71-00, P. Block 501).

F. Close-Up Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


COCKPIT VOICE RECORDER - REMOVAL/INSTALLATION _____________________________________________

WARNING : BEFORE POWER IS APPLIED TO THE AIRCRAFT MAKE CERTAIN THAT CIRCUITS, _______ UPON WHICH WORK IS IN PROGRESS, ARE ISOLATED.

1. Equipment and Materials _______________________ ----------------------------------------------------------------------------- ITEM DESIGNATION ----------------------------------------------------------------------------- A. Access Platform, 5 m (16 ft.) B. Access Platform, 3 m (10 ft.) Referenced Procedure - 23-71-00, P. Block 501 Cockpit Voice Recorder



A. Job Set-Up (1)Open, safety and tag the following circuit breakers: ----------------------------------------------------------------------------- PANEL SERVICE IDENT. LOCATION ----------------------------------------------------------------------------- 22VU RECORDERS/VOICE/PWR SUPPLY 4RK 210/D 8 22VU RECORDERS/VOICE/CONTRL RELAY 5RK 210/D 9

(2)Position access platform 3 m (10 ft.) at zone 162. (3)Open aft cargo compartment door 813 and access doors 152AZ and 162AZ. B. Removal

R **ON A/C 001-107,

(Ref. Fig. 401 )

R **ON A/C 108-999,

(Ref. Fig. 402 )

(1)Release cage locks (7). (2)Tilt vertical longitudinal strap (6).

R **ON A/C 001-107,

(1)Not applicable (2)Not applicable

R **ON A/C ALL

(3)Loosen hold-down fasteners (2) on frame of recorder shockmount (3RK) by turning two knurled nuts (3). (4)Pull down hold-down fasteners. (5)Remove recorder (1) from shockmount frame.

C. Installation (1)Using integral handle, push voice recorder (1) carefully into shockmount frame (4). NOTE : Check that guide pins are correctly located in shockmount frame. ____ (2)Push up two hold-down fasteners (2). (3)Turn knurled nuts (3) on hold-down fasteners until voice recorder is firmly seated on shockmount.

R **ON A/C 108-999,


(4)Locate vertical longitudinal strap (6) in cage locks and close cage locks (7).

**ON A/C ALL

D. Test (1)Test cockpit voice recorder (Ref. 23-71-00, P. Block 501).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close access doors 162AZ and 152AZ. (3)Close aft cargo compartment door 813. (4)Remove access platform.


UNDERWATER LOCATING BEACON - REMOVAL/INSTALLATION _________________________________________________

1. Removal/Installation of Underwater Locating Beacon __________________________________________________

A. Reason for the Job (1)Removal/installation of underwater locating beacon for replacement or inspection of battery.

B. Equipment and Materials ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (1) Spanner Wrench (P/N 810325 DUKANE CORP) (2) Access Platform 6 m (19 ft. 8 in.) Referenced Procedure - 23-71-00, P. Block 501 Cockpit Voice Recorder

C. Procedure (1)Job set-up (a)Position access platform at zone 312. (b)Open access door 312AR. (2)Removal (Ref. Fig. 401 ) (a)Between FR76 and FR77 remove CVR from rack. After AMPAF 23-001 WARNING : DO NOT REMOVE BATTERY FROM DK100 ULB. * _______ DO NOT DISCARD THE DK100 ULB. * Before the expired date or at battery expired date, send the DK100 to * the manufacturer for servicing. *

R **ON A/C 001-102,

(b)Untighten the four nuts (1) retaining the two straps (3). (c)Remove beacon (2) from retainer straps.

R **ON A/C 001-102, 108-108,

(3)Battery removal/installation (Ref. Fig. 402 ) (a)Support beacon (1) by means of a split hose (8). (b)Using spanner wrench (7), turn end cap (3) marked BATTERY ACCESS, counterclockwise and remove O-ring (4). (c)Remove shock cushion (5). (d)Tap case of beacon (1) with fingers to slide out battery (6). If shock cushion (2) comes out at the same time as the battery, replace immediately. (e)If battery is not replaced, visually inspect battery. Check for absence of corrosion on battery contacts. (f)If battery is replaced, affix new label indicating date of battery replacement and cover with lacquer. CAUTION : DO NOT AFFIX ANY LABELS EXCEPT AS SPECIFIED ON THE BEACON _______


Underwater Locating Beacon Figure 401


Battery Replacement Figure 402


BODY. (g)Install new battery, making certain that end marked INSERT THIS END is inserted first, as indicated by arrow on battery end cap. CAUTION : INCORRECT POLARITY WILL PERMANENTLY DAMAGE THE BEACON. _______R WARNING : INCORRECT POLARITY CAN CAUSE THE BATTERY TO EXPLODE AND _______R CREATE A HAZARD FOR PERSONNEL.R (h)Off-current testR Connect positive (+) probe of microammeter to positive (+) batteryR terminal and negative (-) probe of microammeter to beacon body. CheckR for current leakage between battery and beacon body. Leakage should beR less than 2 microamperes.R (j)Clean threads and slots with cleaner and lint free cloth.R (k)Apply a thin coat of lubricant to O-ring groove and threads in body ofR beacon.R (l)Install O-ring (4) under end cap flange (3). Install shock cushion (5)R on end cap and using spanner wrench tighten end cap clockwise intoR beacon body.R CAUTION : DO NOT TIGHTEN BEACON IN A VICE OR SIMILAR TOOL. _______R TIGHTEN END CAP SLIGHTLY NOT TO DAMAGE O-RING.R (m)Clean the beacon with CLEANING AGENTS (Material No. 11-005).R CAUTION : DO NOT TIGHTEN BEACON IN A VICE OR SIMILAR TOOL. _______R TIGHTEN END CAP SLIGHTLY NOT TO DAMAGE O-RING.R (4)TestsR (a)Carry out functional test of beacon (Ref. 23-71-00, P. Block 501).R (5)Installation (Ref. Fig. 401 )

**ON A/C 001-102,

(a)Position beacon (2) in retainer straps (3) with cap flange facing up. (b)Tighten nuts (1) retaining straps (3) to maintain beacon (2).

**ON A/C 001-102, 108-108,

(6)Close-up (a)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (b)Close access door 312AR. (c)Remove access platform.

HIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIIJ KEFFECTIVITY: 001-102, 108-108, K 23-71-36 K K K K Page 404 K K JAS Oct 01/97

A300B2 ATA 23

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Transcript of A300B2 ATA 23