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 France
A320

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 F

This 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 France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

SUMMARY

REFERENCES/REPERCUSSIONS

TFU : 52.81.13.001

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : None

OTHER : None

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 France
A320

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 France
A320

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

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 1 of 19

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 2

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 3

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 4

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 5

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 6

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 7

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Customer and

Fleet No.

MSN Kit No. Qty

of kits

Config

521100 No.

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,

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 8

Printed in France
A320

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.

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 9

Printed in France
521000 1

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 10

Printed in France
A320

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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 11

Printed in France
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

- Mar 12/99 PAGE : 12

Printed in France

This Page Intentionally Left Blank
A320

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).

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Printed in France
A320

A319/A320/A321

REVISION No. : 

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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.

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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A320

A319/A320/A321

REVISION No. : 

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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.

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Printed in France
A320

A319/A320/A321

REVISION No. : 

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SERVICE BULLETIN

Figure 1 Sheet 1

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Printed in France

MLG Fixed Fairing Upper and Lower Forward Attachment/Adjustment Stud
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Figure 1 Sheet 2

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Printed in France

MLG Fixed Fairing Upper and Lower Forward Attachment/Adjustment Stud
A320

A319/A320/A321

REVISION No. : 

-1100

0101

SERVICE BULLETIN

Figure 2 Sheet 1

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Tap Test Inspection Area
A320

A319/A320/A321

REVISION No. : 

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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

DATE : Dec 07/98 SERVICE BULLETIN No. : -52

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Printed in France
A320

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

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Printed in France