A320 

# A319/A320/A321

REVISION No. : 7 -1100 0101 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : DOORS - MAIN GEAR DOORS - INTRODUCE LEG FAIRING ATTACHMENT STUDS WITH INCREASED STRENGTH MODIFICATION No. : 27716J1969 ATA SYSTEM : 52 This page transmits Revision No. 01 of Service Bulletin A320-52-1100. ADDITIONAL WORK No additional work is required by this revision for aircraft modified by any previous revision. REASON This revision is issued to update the effectivity and to revise the point of embodiment statement. CHANGES SUMMARY : - Para. EFFECTIVITY, Customer codes EDW, SAB and TAM added. SERVICE BULLETIN Planning Information : - Para. A.(2), Effectivity table updated and the point of embodiment statement revised. FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISION None. REVISION SEQUENCE ORIGINAL : Dec 07/98 REVISION No. : 01 - Mar 12/99

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 1 of 1 Printed in FranceA320 

# A319/A320/A321

REVISION No. : 7 -1100 0101 SERVICE BULLETIN SUMMARY AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 FThis summary is for information only and is not approved for modification of the aircraft TITLE : DOORS - MAIN GEAR DOORS - INTRODUCE LEG FAIRING ATTACHMENT STUDS WITH INCREASED STRENGTH MODIFICATION No. : 27716J1969 ATA SYSTEM : 52 REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES There have been reported failures of the upper forward attachment/adjustment stud on the Main Landing Gear (MLG) fixed-fairing assembly. Previously, failures of the lower forward attachment/adjustment stud led to the issue of Inspection Service Bulletin (ISB) A320-52-1083. This gives instructions for a Tap Test inspection of the composite insert and the surrounding area and the replacement of the attachment/adjustment stud at the forward lower position. An increase of the clearances at the stud to fixed-fork assembly was introduced by Modification 25373J1502. Subsequently, the rigging procedures were amended in the Aircraft Maintenance Manual (AMM). Because of these improvements the failure rate at the lower forward attachment/adjustment stud has diminished. More recently, cracking has been found in the forward upper attachment/adjustment stud. This Service Bulletin introduces a re-designed location stud, rod end and location plate at the forward upper and lower leg fixed-fairing positions. It also gives instructions for a Tap Test inspection of the composite insert and the surrounding area and the subsequent repair if found to be necessary. The re-designed stud is stronger and therefore will be less likely to crack. This Service Bulletin supersedes Service Bulletin A320-52-1083. EFFECTIVITY This Service Bulletin is applicable to these customers : AAA, AAR, ACA, ADR, AEF, AES, AFR, AIB, AJM, ALK, AMC, AMU, ANA, AUA, AZA, BAW, BMA, BV, CDN, CES, CFG, CJG, CNW, CSC, CSN, CTN, CYP, DLH, EDW, EIN, EWG, FHA, FIN, GES, GFA, HDA, HP, IAC, IBE, IWD, KAC, K9G, LEI, MON, MSR, MXA, NWA, OHY, OYC, PAL, QAF, RGA, RJA, SAA, SAB, SHJ, SHK, SLK, SWR, SYR, TAI, TAM, TAP, TAR, TAS, UAL, USA, TAR, TAS, UAL, USA, WS, XF, XP, XR, XW, XZ, ZZ. SERVICE BULLETIN TO BE ACCOMPLISHED PREVIOUSLY OR SIMULTANEOUSLY None

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 1 of 3 Printed in FranceA320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN SUMMARY REFERENCES/REPERCUSSIONS 52.81.13.001 TFU :None OEB :None AOT :None SIL : LIFE LIMIT : None LINE MAINTENANCE AFFECTED : None None OTHER : NATURE OF THE WORK AIRCRAFT : Yes. EQUIPMENT : No. HARD : No. SOFT : No. OBRM : No. COMPLIANCE Recommended. MANPOWER Aircraft TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0 MATERIAL INFORMATION AIRCRAFT DATA Modification of one aircraft requires Kit No. 521100B01. EQUIPMENT DATA None APPENDICES None

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 2 Printed in FranceA320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN SUMMARY

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 3 Printed in FranceA320 

# A319/A320/A321

REVISION No. : 7 -1100 0101 SERVICE BULLETIN
AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : DOORS - MAIN GEAR DOORS - INTRODUCE LEG FAIRING ATTACHMENT STUDS WITH INCREASED STRENGTH MODIFICATION No. : 27716J1969 ATA SYSTEM : 52 1. PLANNING INFORMATION A. EFFECTIVITY (1) Aircraft models : A319-112, A319-113, A319-114, A319-131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-231 (2) Aircraft Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 AAA001-017 022,023,024,025,026,027, 029,030,140,142,157,229, 547,615,622,632,662 B01 17

101 726 B01 01 AAR001-002 771,855 B01 02 ACA201-234 059,068,073,084,122,126, 127,141,149,150,154,159, 183,233,242,248,253,254, 255,265,277,290,310,311, 324,330,333,341,342,350, 359,378,384,426 B01 34

251-285 572,634,639,649,656,670, 672,682,688,691,693,695, 697,711,719,721,728,732, 736,740,742,752,757,769, 773,779,785,800,813,817, 829,831,840,845,546 B01 35

ADR001-003 043,113,114 B01 03 AEF001-002 575,659 B01 02 051-054 565,580,661,667 B01 04 101 792 B01 01 151-152 787,954 B01 02 AES001-004 739,743,839,892 B01 04

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 AFR001-002 005,007 B01 02 004-013 014,019,020,021,002,004, 003,010,012,013 B01 10
015 016 B01 01 031-048 061,062,063,100,101,102, 128,129,133,186,187,188, 226,227,228,285,286,287 B01 18
066-068 033,036,044 B01 03 071-078 108,115,130,155,156,184, 214,239 B01 08 080-085 278,337,352,236,237,377 B01 06 101-105 498,509,521,529,544 B01 05 131-132 777,796 B01 02 201-202 144,145 B01 02 226-227 131,132 B01 02 231-232 203,220 B01 02 301-302 204,211 B01 02 305 085 B01 01 401-403 215,244,270 B01 03 411 491 B01 01 501-504 674,675,684,761 B01 04 551 956 B01 01 901-906 598,600,608,618,625,637 B01 06 947-949 644,647,660 B01 03 951 985 B01 01 976 938 B01 01 AIB401-402 376,386 B01 02 AJM001-004 624,626,628,630 B01 04 ALK001-002 374,406 B01 02 AMC001-002 112,293 B01 02 AMU001 908 B01 01

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 ANA001-025 138,139,148,151,167,170, 196,212,219,245,300,328, 365,383,413,482,501,507, 531,534,549, 554,658,669, 685 B01 25

051-053 802,811,963 B01 03 AUA426-428 768,776,797 B01 03 476-478 552,570,581 B01 03 479-480 920,935 B01 02 AZA001-022 477,488,494,495,434,524, 526,532,515,516,513,514, 576,583,586,593,599,765, 819,848,940,959 B01 22

101 951 B01 01 BAW001-010 006,008,011,017,018,039, 042,103,109,120 B01 10 BMA001-002 835,864 B01 02 101-104 806,810,968,974 B01 04 201 934 B01 01 BV051-052 185,191 B01 02 CDN401-405 174,175,210,231,232 B01 05 407-411 283,284,302,305,309 B01 05 415-416 403,404 B01 02 CES001-002 772,799 B01 02 201-204 828,883,914,925 B01 04 CFG001-008 774,793,809,884,894,905, 957,971 B01 08 CJG001-002 707,724 B01 02 101-102 876,921 B01 02 CNW001-010 665,754,838,854,897,909, 939,967,984,986 B01 10
CSC001 919 B01 01 051-053 540,551,556 B01 03 101-102 878,915 B01 02

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 CSN001-017 696,698,704,705,709,710, 712,718,720,722,849,859, 881,895,900,950,966 B01 17
CTN001-002 767,833 B01 02 101 258 B01 01 CYP001-008 028,035,037,038,180,256, 295,316 B01 08 DLH001-010 069,070,071,072,078,083, 086,093,094,104 B01 10 012-034 110,111,116,117,135,137, 147,161,162,172,200,201, 202,209,216,217,218,267, 268,269,346,382,401 B01 23

101-120 458,468,473,474,484,493, 412,502,505,518,560,563, 564,567,595,652,692,699, 887,901 B01 20

201-220 609,610,616,623,627,636, 641,651,679,689,694,700, 717,723,729,738,744,853, 860,875 B01 20

EDW701-702 942,947 B01 02 EIN001 926 B01 01 501-502 815,841 B01 02 EWG001-003 646,654,794 B01 03 FHA001-004 332,369,791,822 B01 04 101-106 538,555,602,606,731,746 B01 06 FIN001-002 941,961 B01 02 GES002-003 714,716 B01 02 005-009 730,735,737,749,764 B01 05 015 978 B01 01 GFA801-812 313,325,345,375,419,421, 438,445,459,466,481,497 B01 12
814 537 B01 01 HDA001 812 B01 01 HP620-622 052,053,054 B01 03 624-629 055,064,065,066,067,076 B01 06

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 631-637 077,081,082,091,092,098, 099 B01 07
652 953 B01 01 801-803 889,924,931 B01 03 IAC001-012 045,046,047,048,049,050, 051,056,057,058,074,075 B01 12 014-031 080,089,090,095,096,097, 396,398,416,423,431,432, 451,469,486,490,492,499 B01 18
IBE001-022 134,136,143,146,158,173, 176,177,199,207,223,224, 240,241,246,264,266,274, 303,312,323,356 B01 22

IWD001-002 879,888 B01 02 KAC001-003 181,182,195 B01 03 K9G001 913 B01 01 LEI001-002 677,852 B01 02 101 781 B01 01 MON001-002 379,389 B01 02 101 983 B01 01 MSR001-007 165,166,178,194,198,351, 366 B01 07 101-104 680,687,715,725 B01 04 MXA001-010 252,259,260,261,275,276, 296,320,321,353 B01 10
012 368 B01 01 016 433 B01 01 NWA301-366 031,032,034,040,041,060, 106,107,118,121,125,152, 153,160,171,192,197,206, 208,213,262,263,272,273, 281,282,297,298,306,307, 318,319,329,339,340,355, 358,360,367,372,380,381, 387,388,399,400,408,410, 417,418,766,778,786,801, 807,818,830,832,846,903, 907,911,923,962,964,981 B01 66

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 OHY001-002 385,364 B01 02 OYC001-006 163,164,168,169,179,193 B01 06 PAL001 706 B01 01 003-004 745,753 B01 02 QAF001 927 B01 01 RGA001-010 590,594,601,605,607,611, 617,619,648,650 B01 10 RJA001-003 087,088,569 B01 03 SAA001-007 243,249,250,251,334,335, 440 B01 07
SAB501 970 B01 01 SHJ001 910 B01 01 SHK001-003 322,326,344 B01 03 SLK001-003 872,899,969 B01 03 SWR201-208 578,588,612,621,629,713, 727,734 B01 08 226-245 533,545,548,553,559,562, 566,574,577,585,596,603, 635,643,673,681,701,703, 782,870 B01 20

276-286 517,519,520,522,535,541, 642,664,827,891,987 B01 11 SYR001-002 886,918 B01 02 TAI001-002 558,561 B01 02 051-054 448,453,460,461 B01 04 201-208 733,741,747,789,874,902, 912,916 B01 08
TAM001 976 B01 01 TAP001-007 750,755,821,837,906,917, 933 B01 07 051-053 763,790,979 B01 03 101-102 945,982 B01 02 151 960 B01 01 TAR001-010 119,124,205,370,390,402, 123,511,958,975 B01 10 101-102 869,880 B01 02

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 TAS001 937 B01 01 UAL401-452 435,439,442,450,452,454, 456,457,462,463,464,465, 470,472,475,479,483,485, 487,489,500,503,504,506, 508,510,512,523,539,568, 571,587,589,592,613,638, 655,678,683,702,751,780, 820,824,826,834,836,842, 851,857,865,955 B01 52

801-825 686,690,748,759,783,788, 798,804,825,843,847,850, 858,862,867,871,873,882, 893,898,944,948,952,965, 980 B01 25

USA001-005 936,844,861,863,868 B01 05 700-708 885,890,896,904,922,929, 946,949,972 B01 09 WS001-010 758,762,770,803,856,866, 928,932,943,977 B01 10 XF001-009 393,394,414,430,443,447, 415,405,361 B01 09 053-056 428,496,527,530 B01 04 101-114 425,573,582,640,542,543, 676,756,760,784,805,816, 877,930 B01 14
201-208 550,557,591,597,604,614, 620,631 B01 08 251-253 633,663,668 B01 03 351-352 666,775 B01 02 401 973 B01 01 501-502 446,422 B01 02 504-508 371,397,409,427,528 B01 05 510 525 B01 01 551-556 279,579,645,671,795,814 B01 06 XP053-059 221,222,294,299,301,348, 349 B01 07 062-063 391,392 B01 02 502-506 362,363,455,471,584 B01 05

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Customer and Fleet No. MSN Kit No. Qty of kits Config No. 521100 XR501-525 225,230,238,247,257,271, 280,291,292,304,308,314, 315,317,327,336,338,429, 444,449,467,476,478,480, 437 B01 25

XW501-506 347,354,357,373,411,424 B01 06 509 441 B01 01 XZ003-004 189,190 B01 02 101-110 234,235,288,289,331,343, 395,407,420,436 B01 10 201-202 653,657 B01 02 ZZ002-003 808,823 B01 02 This modification is embodied before delivery on A319 aircraft MSN 989 and subsequent, on A320 aircraft MSN 988 and subsequent and on A321 aircraft MSN 991 and subsequent. This document contains Airbus Industrie PROPRIETARY INFORMATION and shall at all times remain the property of Airbus Industrie; no intellectual property right or licence is granted by Airbus Industrie in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes for performing the tasks described here under and provided that any recipient of such document shall comply with the conditions herein), without Airbus Industrie’s prior written consent. (3) Spares None B. REASON (1) History There have been reported failures of the upper forward attachment/adjustment stud on the Main Landing Gear (MLG) fixed-fairing assembly. Previously, failures of the lower forward attachment/adjustment stud led to the issue of Inspection Service Bulletin (ISB) A320-52-1083. This gives instructions for a Tap Test inspection of the composite insert and the surrounding area and the replacement of the attachment/adjustment stud at the forward lower position. An increase of the clearances at the stud to fixed-fork assembly was introduced by Modification 25373J1502. Subsequently,

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN the rigging procedures were amended in the Aircraft Maintenance Manual (AMM). Because of these improvements the failure rate at the lower forward attachment/adjustment stud has diminished. More recently, cracking has been found in the forward upper attachment/adjustment stud. (2) Objective/Action This Service Bulletin introduces a re-designed location stud, rod end and location plate at the forward upper and lower leg fixed-fairing positions. It also gives instructions for a Tap Test inspection of the composite insert and the surrounding area and the subsequent repair if found to be necessary. (3) Advantages The new location studs have increased strength and will therefore be less likely to crack. This Service Bulletin supersedes Service Bulletin A320-52-1083. (4) Operational/Maintenance Consequences None (5) Accomplishment Timescale It is recommended that this Service Bulletin is accomplished at the next 2C Check or when the aircraft is next raised on jacks, whichever is sooner. For operators who have already accomplished Service Bulletin A320-52-1083 it is recommended to accomplish this Service Bulletin within the same timescale. C. DESCRIPTION To accomplish this Service Bulletin it is necessary to : (1) Lift the aircraft on jacks. (2) Make the work area safe. (3) Remove the MLG fixed fairing. (4) Remove the adjustment studs, location plates and rod-end assemblies at the lower and upper forward positions on the MLG fixed fairing. (5) Do a Tap Test around the composite insert and the surrounding area at the upper and lower forward positions. (6) Assemble new adjustment studs, location plates and rod-end assemblies. (7) Install and adjust the MLG fixed fairing. (8) Do a retraction/extension test on the MLG. (9) Lower the aircraft off jacks. (10) Close up and complete the aircraft documentation.

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A320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN
D. APPROVAL The technical content of this Service Bulletin has been approved under the authority of the DGAC Design Organisation Approval No. F.JA.02. E. MANPOWER This Service Bulletin is written for an aircraft in a maintenance status. The manhours/elapsed time estimates do not include the time to prepare for the modification, non-productive elapsed time, or administration. Kit No. 521100B01 Get Access 1.0 Modification 5.0 Test 1.0 Close up 1.0 TOTAL MANHOURS 8.0 ELAPSED TIME (HOURS) 4.0 F. MATERIAL - COST AND AVAILABILITY (1) Material Customers with aircraft shown in the effectivity of the Service Bulletin should send a purchase order to Airbus Industrie. Quote the number of this Service Bulletin. The address is : AIRBUS INDUSTRIE MATERIEL SUPPORT CENTER P.O.Box 630262 22312 Hamburg GERMANY. (2) Cost and availability Kit No. Cost (US Dollars) Availability : Calendar days from receipt of order B01 1320 150 The Kit availability given above is the standard lead time from the date of your purchase order. If you require the Kit(s) before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (cost and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. G. TOOLING - PRICE AND AVAILABILITY None

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN
H. WEIGHT AND BALANCE A319 A/C : Manufacturers Empty Weight : 0.16kg (0.35lb) E f f e c t o n B a l a n c e :2.94kgm (21.3lb.ft) A320 A/C : Manufacturers Empty Weight : 0.16kg (0.35lb) E f f e c t o n B a l a n c e :3.19kgm (23.0lb.ft) A321 A/C : Manufacturers Empty Weight : 0.16kg (0.35lb) E f f e c t o n B a l a n c e :3.89kgm (28.1lb.ft) I. REFERENCES Aircraft Maintenance Manual (AMM) : 07-11-00, 32-00-00, 32-12-14 Nondestructive Test Manual (NTM) : 51-10-03 Structure Repair Manual (SRM) : 52-81-13 J. PUBLICATIONS AFFECTED AMM : 32-12-14 Illustrated Parts Catalog (IPC): 32-12-14, 52-81-13Service Bulletin (SB):A320-52-1083

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN
2. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR : - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND RELATED DOORS - COMPONENTS THAT MOVE. (1) Preparation (a) Lift the aircraft on jacks (Refer to AMM: 07-11-00, P. Block 201). (b) On the panel 400VU, make sure that the landing-gear control-lever 6GA is in the down position. (c) Put a warning notice on the landing-gear control-lever 6GA (panel 400VU) to tell persons not to operate the landing gear. (d) On the panel 110VU, make sure that the GRAVITY GEAR EXTN handle is folded into the center console. (e) Make sure that the GROUND LOCK SLEEVE (460005833) is on the MLG (Refer to AMM: 32-00-00, P. Block 201). (f) Put the access platforms in position. (2) Standard Practices None B. MODIFICATION The procedures that follow must be done on the LH and RH MLG fixed fairings. (1) Remove the MLG fixed fairing assembly (Refer to AMM: 32-12-14, P. Block 401). (2) At the upper and lower forward locations : Refer to Figure 1 , Sheet No. 1 (a) Measure and write down the distance DIM. E. between the center of the rod end, Item (7) and Item (8) and the raised face of the serrated plate, Item (10). (b) Remove and discard the lockwire from the nut, Item (3) to the lock-washer, Item (1).

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN
(c) Remove the nut, Item (3), the lock-washers, Items (2) and (1) and the serrated plate, Item (4). (d) Remove and discard, the stud, Item (6), the rod end, Item (7) and (8), the nut, Item (9) and the support plate, Item (5). (3) Resonance Frequency Inspection (Tap Test) at the upper and lower forward locations. Refer to Figure 1 , Sheet No. 1 and Refer to Figure 2 , Sheet No. 1 (a) Do a Tap Test of the composite insert, Item (11) and the honeycomb area around the insert (Refer to NTM: 51-10-03, P. Block 501). (b) Start the Tap Test from as close as possible to the center of the insert and work outwards in the steps as shown on Figure 2. If debonding or delamination is found, continue the inspection through and over the limits shown to find the limits of the area affected. Record the area affected by debonding or delamination. (c) If there is debonding of the composite insert, Item (11) or delamination of the surrounding area, refer to SRM: 52-81-13, P. Block 201 for the applicable repair scheme. (4) At the upper and lower forward locations, install the items that follow to the fixed fairing assembly. Refer to Figure 1 , Sheet No. 2 (a) Apply a thin layer of sealant (Mat. No. 09-013) as necessary to the support plate D52856006200, Item 5 and the stud D52856007200, Item 6 and put them in position on the fixed fairing assembly. (b) Apply a thin layer of sealant (Mat. No. 09-013) as necessary and install the serrated plate, Item (4), the lock-washers, Items (1) and (2) and the nut, Item (3). Temporarily tighten the nut, Item (3). This will help you to get a more accurate distance DIM. E. when you do step (5). (c) Apply a thin layer of sealant (Mat. No. 09-013) as necessary to the rod end assemblies and install as follows : 1 At the upper forward location : a Install the rod end D52856005000, Item 8 together with the nut NAS1423-9, Item 9. Screw the rod end, Item 8 into the stud, Item 6 until the distance DIM. E. (between the center of the rod end, Item 8 and the raised face of the serrated plate, Item (10)) is approximately the same as you recorded in step (2)(a). Hold the stud, Item 6 by the flats and temporarily tighten the nut, Item 9. b Make sure that the threads of the rod end, Item 8, can be seen through the check hole of the stud, Item 6.

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

2 At the lower forward location : a Install the rod end D52856004000, Item 7 together with the nut NAS1423-9, Item 9. Screw the rod end, Item 7 into the stud, Item 6 until the distance DIM. E. (between the center of the rod end, Item 7 and the raised face of the serrated plate, Item (10)) is approximately the same as you recorded in step (2)(a). Hold the stud, Item 6 by the flats and temporarily tighten the nut, Item 9. b Make sure that the threads of the rod end, Item 7, can be seen through the check hole of the stud, Item 6. (5) Install the MLG Fixed Fairing Assembly Refer to Figure 1 , Sheet No. 2 (a) Install the MLG fixed fairing assembly and do the adjustments as necessary (Refer to AMM: 32-12-14, P. Block 401). NOTE 1 :Refer to step (5)(b) when torque tightening the nut, Item (3). NOTE 2:Refer to step (5)(c) when torque tightening the nut, Item 9. (b) When torque tightening the nut, Item (3), hold the stud, Item 6 by the flats and torque the nut, Item (3) to a new torque value of between 4.0 m.daN (354.0 lbf in.) and 4.3 m.daN (380.0 lbf in.). Safety the nut, Item (3) to the lock-washer, Item (1) with lockwire. (c) When torque tightening the nut, Item 9, make sure that the rod ends, Items 7 and 8 are parallel to the MLG bracket lugs. C. TEST (1) Do an extension/retraction test of the MLG (Refer to AMM: 32-12-14, P. Block 401). D. CLOSE-UP (1) Make sure that the work areas are clean and clear of tools and other items of equipment. (2) Remove the access platforms. (3) Lower the aircraft off jacks (Refer to AMM: 07-11-00, P. Block 201). E. DOCUMENTATION Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

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# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Figure 1 Sheet 1

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 16 Printed in France MLG Fixed Fairing Upper and Lower Forward Attachment/Adjustment StudA320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Figure 1 Sheet 2

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 17 Printed in France MLG Fixed Fairing Upper and Lower Forward Attachment/Adjustment StudA320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN

Figure 2 Sheet 1

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 18 Printed in France Tap Test Inspection AreaA320 

# A319/A320/A321

REVISION No. : -1100 0101 SERVICE BULLETIN
3. MATERIAL INFORMATION A. LIST OF COMPONENTS ITEM NEW PART NO. QTY KEYWORD ITEM OLD PART NO. INT INST DISP 5 D5285600620000 4 Plate (5) D5284024820200 * 6 D5285600720000 4 Stud (6) D5284024420000 * 7 D5285600400000 2 Rod End (7) D5284000500000 * 8 D5285600500000 2 Rod End (8) D5284000600000 * 9 NAS1423-9 4 Nut (9) NAS509-8 * NOTE: * discard B. SPECIAL TOOLS None C. LIST OF MATERIAL - OPERATOR SUPPLIED DESCRIPTION REFERENCE TO CML QTY PER A/C Sealant (Mat. No. 09-013) As required NOTE: To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the AMM: 32-12-14, P. Block 401. D. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

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# A319/A320/A321

REVISION No. : 7 -1100 0101 SERVICE BULLETIN ACCEPTANCE/REJECTION SHEET AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX FRANCE Tel: (33) 5 61-93-33-33 Telex: AIRBU 530526 F TITLE : DOORS - MAIN GEAR DOORS - INTRODUCE LEG FAIRING ATTACHMENT STUDS WITH INCREASED STRENGTH MODIFICATION No. : 27716J1969 ATA SYSTEM : 52

IS BEING HEREWITH SUBMITTED TO YOU FOR REVIEW Please fill : ...REJECTED ...WILL BE EMBODIED ...EFFECTIVITY

This SB can only be incorporated in your "customized" documentation within the agreed time schedule in so far as this sheet returned to us on purchase date and signed by a duly authorized and empowered officer or representative.

FROM : AIRLINE :

NAME :

DATE : Please return to : AIRBUS INDUSTRIE CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn : AI/SE-D32 Technical Data and Documentation Services FAX : (+33) 5 61 93 28 06

DATE : Dec 07/98 SERVICE BULLETIN No. : -52 - Mar 12/99 PAGE : 1 of 1 Printed in France