# Airbus Service Bulletin A300-57-143

Copy: Revision 2 ("FAA-2015-6550_SB A300-57-143_Rev2"), 15 pages: PDF https://openairdocs.org/files/sha256/02/80/0280b6aae5bb647c432f59a82cfed05b10d99ea386adad423678033dc4b74427; text https://openairdocs.org/service-documents/airbus/a300-57-143/file/0280b6aae5bb.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-6550; AD 2016-18-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A300-57-143
- Latest revision known: A300-57-143, Revision 2, dated July 10, 1989 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-57-143

## ADs that cite it (2) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2016-18-08](https://openairdocs.org/ad/2016-18-08.md), effective Oct 20, 2016: Revisions 1 and 2
- [AD 90-11-05](https://openairdocs.org/ad/90-11-05.md), effective Jun 19, 1990: Revision 2

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-57-143/proposed.md).

## Text (15 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2015-6550; AD 2016-18-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1 (OCR)

• A300
AIRBUS INDUSTRIE
PRODUCT SUPPORT DIRECTORATE
1 ROND POINT MAURICE BELLONTE
31707 BLAGNAC CEDEX FRANCE  SERVICE BULLETIN
Tel (33) 61-93-33-33  REVISION TRANSMITTAL SHEET
Telex AIRBU 530526 F
MODIFICATION No: 6661H1033  ATA SYSTEM: 57
T I T L E : WINGS - AUXILIARY STRUCTURE - TO INTRODUCE IMPROVED AFT HINGE
BRACKETS TO OUTER SHROUD BOX.
Find herewith Revision No.2 of S.B.A300-57-143. No additional work is
required by this revision.
REASON
To inform Operators of revised clearances when installing new hinge
brackets.
SUMMARY
Page 1 - Inclusion of Change Notice 1.A. Revision No.2 added.
SERVICE BULLETIN
Page 1  - Revision No.2 added.
Page 3  - Inclusion of Change Notice 1.A. Revision No.2 added.
Page 4  - DESCRIPTION sub-para (3) revised. Revision No.2 added.
Page 7  - Paragraph 2.A. (1)(c) revised. Revision No.2 added.
Page 10  - Paragraph 2.C.(2) revised. Revision No.2 added.
Page 13-14 - Drawing changes. Revision No.2 added.
FILING INSTRUCTIONS
1. Remove and destroy page 1 of the Summary and pages 1,3,4,7,10 and 13-14.
2. Insert page 1 of the Summary and pages 1,3,4,7,10 and 13-14 at Revision
No. 2.
REVISION SEQUENCE
ORIGINAL - DEC 17/86
REVISION NO.1 - MAR 19/87
REVISION NO.2 - JUL 10/89
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL 10/89  PAGE: 1 of 1
Primad in Franco

### Page 2 (OCR)

• A300
AIRBUS INDUSTRIE
PRODUCT SUPPORT DIRECTORATE
1 ROND POINT MAURICE BELLONTE
31707 BLAGNAC CEDEX FRANCE  A300 SERVICE BULLETIN
Tel (33) 61-93-33-33  SUMMARY
Telex ARBOUR 530526 F
This summary is for information only and
is not D.G.A.C. approved for modification of the aircraft
MODIFICATION No: 6661H1033  ATA SYSTEM: 57
T IT LE: WINGS - AUXILIARY STRUCTURE - TO INTRODUCE IMPROVED AFT HINGE
BRACKETS TO OUTER SHROUD BOX
REASON
Cracking of hinge bracket assemblies, which are situated on the outer
shroud box and form the rear attachment between the inner and outer shroud
boxes has been discovered during routing maintenance checks on some
in-service A300 aircraft which had accumulated between 15150 and 20380
flights, and 14070 to 18740 flight hours. Failure of the bracket would
allow vertical movement of the inner shroud box structure in the immediate
area and probable fouling of the inboard flap top skin. Additionally the
loads carried through this bracket will be transferred to the remaining
supports which may eventually crack; extensive structural damage could
then result.
Inspection Service Bulletin (ISB) A300-57-142 details methods of detecting
cracked brackets. Embodiment of this modification renders further
compliance with ISB A300-57-142 unnecessary.
This Service Bulletin introduces new Steel Brackets to replace the
existing aluminium alloy brackets in order to improve the fatigue Life.
This Service Bulletin is subject to airworthiness authorities monitoring.
ACTION
At each wing the No.1 inner airbrake is removed. The inner shroud box
attachment bolts are removed and the shroud box is raised to allow removal
of the existing aluminium alloy bracket assembly. A new steel bracket
assembly is installed. The inner airbrake is reinstalled and function
tested.
EFFECTIVITY
This modification is applicable by Service Bulletin on all A300 aircraft.
COMPLIANCE
Recommended.
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL 10/89  Printed in France  PAGE: 1 of 2

### Page 3 (OCR)

AIRBUS O NOUSTRIE
A300 SERVICE BULLETIN
SUMMARY
MANPOWER
Kit No. : A300-57-143-A01
Manhours : 26.75
Elapsed time (hours 2 fitters) 13.75
MATERIAL INFORMATION
Kit No. : A300-57-143-A01
2 Hinge Bracket Assemblies, 18 Cotter pins, 20 Nuts.
BRACKET ASSEMBLY
OUTER SHROUD BOX
DATE: DEC 17/86  SERVICE BULLETIN REF: A300-57-143
REVISION NO:  PAGE: 2
Printed

### Page 4 (OCR)

• A300
AIRBUS INDUSTRIE
PRODUCT SUPPORT DIRECTORATE
1 ROND POINT MAURICE BELLONTE
31707 BLAGNAC CEDEX FRANCE A300 SERVICE BULLETIN
Tel (33) 61-93-33-33
Telex AIRBU 530526 F
MODIFICATION No: 6661H1033  ATA SYSTEM: 57
T I T L E: WINGS - AUXILIARY STRUCTURE - TO INTRODUCE IMPROVED AFT HINGE
BRACKETS TO OUTER SHROUD BOX.
1.PLANNING INFORMATION
A. EFFECTIVITY
(1) Aircraft Models: B1, B2-10, B2K-36, B2-203, B4-2C, B4-102,
84-103, B4-120, 84-203, B4-220 and C4-203.
(2) Aircraft.
Customer and  MSN  Qty of Kits
Fleet No.  A300-57-143
-A01
AF001-003  005,006,007  3
AF 009  104
AF051-054  019,023,045,047
AFOS6-064  074,078,100,129,145,146,175,178,183  9
AI101-103  177,180,190  3
AY001,002  299,302
AZ151-158  101,106,107,123,139,140,142,173  8
C1001-006  193,197,221,232,179,171
C0966-968  117,121,126  3
C0970-972  250,262,289  3
EA201-210  041,042,043,044,065,066,067,068,086,087  10
EA212,213  091,092  2
EA215-217  108,118,119  3
EA219-235  120,124, 152,153,154, 155,158,161,204,207,211
216,220,259,261,271,274
EA291,292  049,051  2
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2JUL 10/89  Printed in France  PAGE: 1 of 15

### Page 5 (OCR)

AIRBUS!  1/ NOUSTRE
A300 SERVICE BULLETIN
Customer and  MSN  Qty of Kits
Fleet No.  A300-57-143
-A01
GA001 -009  159,164,165,166,167,168,213,214,215  9
HE001  002
HF  169,174
HF301-304  009,012,017,020
HF 307  083  1
IB251--256  130,133,135,136,156,170  6
IC  026
IC001-008  034,036,038,059,060,088,111,113  8
IC051,052  181,182  2
IR001-006  061,080,185,186,187,226  6
IT031-046  015,004,008,027,062,097,112,011,013,  16
010,021,050,132,102,048,052
IT091  029  1
JD001--009  082,089,090,160,163,176,209,244,253
JD 101  256  1
JM001,002  127,131  2
KE001-008  014,016,018,024,028,030,031,081  8
KE101,102  277,292  2
LG001  269  1
LH351-355  053.057,075,076,077  5
MH001--004  073,093,095,147  4
MS001--008  115,116,150,199,200,239,240,255  8
0A001--008  046,056,058,103,105,148,184,189  8
PA001--012  195,227,198,247,234,236,304,305,238,  12
235,208,210
PK001--004  096,098,099,114
PK010-013  064,144,268,025  4
PRO01--005  063,069,125,203,219  5
RK551-553  137,243,282  3
SA001-004  032,037,039,040
SA051--053  138,192,222  3
DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION NO:  Printed in France  PAGE: 2

### Page 6 (OCR)

• A300
Customer and  MSN  Qty of Kits
Fleet No.  A300-57-143
-A01
SA101  212
SC001-004  109,110,143,194  4
SK201,202  079,094  2
SK204  128  1
SY002  003  1
TG001-012  033,035,054,055,071,072,084,085,141,149,  12
249,265
TN001-005  134,151,157,196,218  5
TU001  188
VP001-003  202,205,225  3
The above effectivity and kit allocation is based on aircraft
modification status at delivery and subsequent Airbus Service
Bulletin accomplishment reported to Airbus Industrie.
(3) Spares
None.
B-REASON
Cracking of hinge bracket assemblies, which are situated on the outer
shroud box and form the rear attachment between the inner and outer
shroud boxes has been discovered during routine maintenance checks on
some in-service A300 aircraft which had accumulated between 15150 and
20380 flights, and 14070 to 18740 flight hours. Failure of the bracket
would allow vertical movement of the inner shroud box structure in the
immediate area and probable fouling of the inboard flap top skin.
Additionally the loads carried through this bracket will be
transferred to the remaining supports which may eventually crack;
extensive structural damage could then result.
Inspection Service Bulletin (ISB) A300-57-142 details methods of
detecting cracked brackets. Embodiment of this modification renders
further compliance with ISB A300-57-142 unnecessary.
This Service Bulletin introduces new Steel Brackets to replace the
existing aluminium alloy brackets in order to improve the fatigue life.
This Service Bulletin is subject to airworthiness authorities
monitoring.
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL 10/87  Priloo mn Franoo  PAGE: 3

### Page 7 (OCR)

C. DESCRIPTION
Accomplishment of this Service Bulletin consists of :-
AIRCRAFT
Kit No.A300-57-143-A01. All aircraft listed in Para.1.A.(2).
(1) Removing inner airbrake No.1, LH and RH.
(2) Removing access panels.
(3) Checking for equal clearance between the bearing and bracket faces
of the forward attachment bracket.
(4) Removing 42 bolts attaching landing gear bay top panel to inner
shroud.
(5) Removing inner shroud box attaching bolts.
(6) Raising inner shroud box sufficient to gain access to hinge
bracket.
(7) Removing existing aft hinge bracket.
(8) Installing new Steel hinge bracket at existing position.
(9) Re-installing inner shroud box.
(10) Re installing and function testing inner airbrake No.1.
(11) Closing up all panels.
D. APPROVAL
This Service Bulletin is approved by Direction Generale de L'Aviation
CiVile - FRANCE (D.G.A.C.).
E. MANPOWER
Manhours per aircraft  Kit No. A300-57-143-
A01
Gain access  9.25
Removal of Brackets  1.00
Installation of new Brackets  6.50
Close up and test  10.00
Total manhours  26.75
Elapsed time (hours) (2 fitters)  13.75
NOTE : This Service Bulletin assumes that the aircraft has been placed
in a maintenance status. The manhours/elapsed times do not
include preparation for the modification, non-productive
elapsed time or administrative functions.
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL 10/89  Printad in Franco  PAGE: 4

### Page 8 (OCR)

AIRBUS  INDUSTRIE
A300 SERVICE BULLETIN
F. MATERIAL-COST AND AVAILABILITY
Refer to paragraph 3 - MATERIAL INFORMATION
G. TOOLING - COST AND AVAILABILITY
None.
H. WEIGHT AND BALANCE
MEW + 0.72 Kg (1.58 lbs).
Moment + 23.5 Kg.m (169.92 lb ft).
I. REFERENCES
Aircraft Maintenance Manual (AMM) 06-21-57, 27-61-54, 20-31-00.
Inspection Service Bulletin (ISB) A300-57-142.
J. PUBLICATIONS AFFECTED
Illustrated Parts Catalogue (IPC) 57-22-13.
Structural Repair Manual (SRM) 57-22-11.
DATE:  SERVICE BULLETIN No: A300-57-143
REVISION No.1 MAR 19/87  Printed In France  PAGE: 5-6

### Page 9 (OCR)

• A300
2. ACCOMPLISHMENT INSTRUCTIONS
AIRCRAFT
A. GENERAL
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.
The following instructions are applicable to both LH and RH wings.
(1) Job set up
(a) Refer to Aircraft Maintenance Manual (AMM) 27-61-54 page block
401. Remove and retain inner airbrake No.1.
(b) Refer to AMM 06-41-57
- Lower flap deflector panels 572AB, 572CB,5726B, 672AB, 672CB
and 672GB.
- Remove and retain access panel A57240980 from the inboard aft
edge of each outer shroud box as shown in Figure 1, View A.
- Remove and retain wing to fuselage fairing panels
577CT, 577DT, 677CT and 677DT.
(c) Refer to Figure 1 View A, and Figure 2 Detail E.
- Gain access to the forward attachment point which connects
the inner shroud box to the outer shroud box.
- Using a suitable light source and mirror make sure that an
equal gap exists between the bearing and the bracket faces
as shown in Figure 2, Detail E.
- It a gap exists, METHOD ONE (op.B(3) refers) can be used to
install the new aft hinge bracket.
- If there is no gap at all, METHOD TWO (op.B(4) refers) must
be used to install the new aft hinge bracket.
7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL 10/89  Priied in Franco  PAGE: 7

### Page 10 (OCR)

AIRBUS  , INOUSTRIE
A300 SERVICE BULLETIN
(d) Refer to Figure 1, View A.
- Place suitable supports beneath the inner shroud box to prevent
excessive movements when the shroud box is released from the wing.
- Remove and retain the 42 bolts attaching the landing gear bay top
panel to the forward edge of the inner shroud box.
- Remove and discard the cotter pins from each of the bolts at the
main attachment points denoted 'C'.
- Remove and retain nuts, washers and special bolts (Qty 5) from the
attachment points.
- Remove and retain the sliding bush from the aft inner-to-outer
shroud box attachment.
(e) (arefully raise the aft edge of the inner shroud box just sufficient to
gain access to the aft hinge bracket situated on the inboard edge of
the outer shroud box, as shown in Figure 1, View B.
NOTE: Movement of the inner shroud box is severely restricted by
electrical looms and hydraulic pipes. When raising the shroud
box ensure that the looms and pipes are not strained. Removal
of 'p' clips will allow increased movement of the shroud box.
B.MODIFICATION
Kit No.A300-57-143-A01
(1) Mark around the outline of the existing aft hinge bracket on the outer
shroud box using a sharpened pencil.
(2) Remove and discard the existing aft hinge bracket from the outer shroud
box taking note of the direction of installation and position of all the
attaching bolts. Retain bolts and washers; discard nuts.
(3) METHOD ONE. Refer to Figure 1, View B.
(a) Position the new Hinge Bracket Assembly A5724864100095, Item 1, LH
(A5724864100195, Item 2, RH) to the pencil outline on the shroud box
and clamp.
(b) Ensure sufficient hole landings and that reference dimensions shown
are correct. Mark the position of holes to be drilled in the hinge
bracket from the existing vacant bolt holes in the shroud box.
(c) Remove the hinge bracket assembly from the shroud box and drill/ream
sixteen holes 0.190/0.192 in. (4.83/4.88 mm) dia.
DATE: DEC 17/86  SERVICE BULLETIN NO: A300-57-143
REVISION No:  • Printad la Franco  PAGE: 8

### Page 11 (OCR)

AIRBUS  → NOUSTRIE
A300 SERVICE BULLETIN
(d) Spotface ten holes denoted 'D' 0.5625 in. (14.3 mm) dia. (spotface
corner radius to be 0.0625 in. (1.53 mm)). Spotface to minimum depth
to provide correct nut seating. Deburr all holes. Ensure corner
radius of 0.015/0.025 in. (0.38/0.63 mm) is achieved on three holes as
shown to allow bolt heads to seat correctly. Thoroughly clean
spotfaces with Genklene (Mat. No.11-004). Restore protective
treatment using Primer (Mat. No.16-006) and Polyurethane Finish (Mat
No. 16-018).
(e) Install new Anchor Nuts NAS1067C3 to bracket assembly as shown with
Sealant PR1431-G (Mat. No.09-005) using new Rivets L21217024008DCA.
(f) Install new Bracket Assembly to shroud box using bolts retained in
op. B.(2) with new Nuts H192000-3 Item 6 using Sealant PR1431-G
(Mat. No. 09-005) on interfaying surfaces, nuts and bolts.
(4) METHOD TWO: Refer to Figure 1 View A, and Figure 2.
(a) Refer to Figure 2 Detail 'F'. Bolt the new Hinge Bracket Assembly
A5724864100095, Item 1, LH (A5724864100195, Item 2, RH) to the inner
shroud box outboard aft attachment bracket using the appropriate nut,
bolt and washer retained in op.2.A. (1) (d) together with sliding bush.
(b) Temporarily reinstall the inner shroud box to the remaining main
attachment points and suitably support.
(c) Refer to Figure 2 Detail 'E'. Reinstall two bolts denoted 'G' so that
the threads are just engaged, to the landing gear bay top panel.
(d) Refer to Figure 2, Detail 'F'.
For aircraft post mod. 1096 (MSN 016 and subsequent):-
Clamp new Hinge Bracket Assembly, Item 1 LH (Item 2 RH) to the outer
shroud box ensuring that the minimum gap between the washer and fixed
bearing exists as detailed.
For aircraft pre mod. 1096:-
Clamp new Hinge Bracket Assembly, Item 1 L.H. (Item 2 RH) to the outer
shroud box. A zero clearance between the flange of the sliding bush
and the flange of the fixed bearing is normal; if clearance exists,
then this is acceptable.
(e) Mark the position of holes to be drilled in the new Hinge Bracket from
the existing vacant bolt holes. Ensure that sufficient hole landing
exists.
(f) Support inner shroud box, remove and retain all bolts installed at
op.2.B. (4) (b) and (c).
(g) Refer to Figure 1, View B. Remove the new Hinge Bracket AssemblY' and  Item 1 LH (Item 2 RH) from the inner shroud box, retain the bolts
sliding bush installed at op.2.B.(4) (a).
(h) Perform ops.2.B.(3) (c) to 2.B.(3) (f) inclusive.
DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No.1 MAR 19/87  Priated in France  PAGE: 9

### Page 12 (OCR)

• A300
C.CLOSE UP AND TEST
(1) Carefully lower the inner shroud box to its original position
Lining up with attachment points.
(2) Reinstall sliding bush to the aft inner to outer shroud box
attachment. Install special bolts with nuts and washers retained
in op.A. (1). (d) and new Cotter Pins MS24665-304, Item 3 (Qty 2),
to attachment points.
(3) Reinstall attaching bolts retained in op.2.A.(1)(d) into the
landing gear bay top panel.
(4) Refer to AMM 27-61-54 page block 401. Re-install inner airbrake
No. 1 retained at op.A. (1) (a) using new Cotter Pins MS24665-304
Item 3, (Qty 2) and MS24665-374 Items 5, (Qty 2). Perform relevant
tests as detailed.
(5) Ensure work areas are clean and clear of tools and miscellaneous
items of equipment.
(6) Re-install all access panels removed or opened in
op.A. (1) (b).
• 7 DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
REVISION No: 2 JUL Inton Pranos  PAGE: 10

### Page 13 (OCR)

AIRBUS I NOLSTRE
A300 SERVICE BULLETIN
OUT 'BD
SEE FIGURE 2
No.1 INBOARD SPOILER  DETAIL F
ATTACHMENT POINTS
ACCESS PANEL
A572-40980
(REF)(35.05mm)  1.38 IN.  0.40 IN= (REF)  10.16mm)
REF) [12.70mm  0.50 IN  0.60 IN. (REF)
INNER SHROUD
BOX
SEE FIGURE
DETAIL E
REMOVE AND RETAIN BOLTS
(QTY 42) SECURING LANDING
ENSURE CORNER RADIUS ON  GEAR BAY TOP PANEL TO
HOLES (QTY 3) of 0.015/0.025IN.  INNER SHROUD BOX.
TO ALLOW BOLT HEADS TO
SEAT CORRECTLY WHEN INSTALLED.  1 (LH)
2 (RH)
LANDING GEAR BAY
TOP PANEL
OUTER SHROUD
VIEW SHOWING POSITION OF AFT  BOX
HINGE BRACKET ON OUTER SHROUD
BOX
VIEW LOOKING DOWN ON
INNER SHROUD BOX LH
RH SIMILAR BUT OPPOSITE
Installation of new Hinge Bracket Assembly
Figure 1
DATE: DEC 17/86  SERVICE BULLETIN NO:A300-57-143
REVISION No:  Prated in France  PAGE: 11-12

### Page 14 (OCR)

AIRBUS  INDUSTRIE
A300 SERVICE BULLETIN
BUSH (REF)  SLIDING  ZERO CLEARANCE  IS NORMAL  BUSH. (REF)  SLIDING  MIN. 0.008 IN.  (0.20MM)
FIXED  BEARING (REF).  FIXED
(REF).
BEARING
2 (RH)  1 CLH.  2 (RH.
DETAIL F  DETAIL F
PRE MOD. 109%  POST MOD. 1096
MAKE SURE AN EQUAL
GAP EXISTS BETWEEN
THE BEARING AND
LANDING GEAR BAY  THE BRACKET FACES
TOP PANEL
DETAIL E
Views showing clearances when installing
the new Hinge Brackets.
Figure 2
DATE: DEC 17/86  SERVICE BULLETIN No: A300-57-143
| REVISION No: 2 JUL 10/89  Printed in France  PAGE: 13-14

### Page 15 (OCR)

AIRBUS  * INDUSTRIE
A300 SERVICE BULLETIN
3. MATERIAL INFORMATION
A. DATA BASIS
Quantity specified in B.(1) Kit A01 is per aircraft listed in
Para. 1.A. (2).
B. MATERIALS
(1) Parts required
ITEM  NEW PART  QTY PER KIT  DESCRIPTION  OLD PART  REMARKS
NO.  NO.  A300-57-143-A01  NO -
A5724864100095  Hinge Bracket  A57241917000  A,B, C
Assembly (LH)
2  A5724864100195  Hinge Bracket  A57241917001  A,B,C
Assembly (RH)
3  MS24665-304  10  Cotter pin  A,C
4  MS24665-155  4  Cotter pin  A,C
5  MS24665-374  Cotter pin  A,C
6  H19200C-3  20  Nut  A.C
Remarks
A - Old part discarded.
B - Hinge Bracket Assemblies are supplied with anchor nuts and rivets loose
in bag.
C - New parts required to accomplish this Service Bulletin are to be
precured by Spares Purchase Order from: AIRBUS INDUSTRIE
SPARES SUPPORT CENTER
WEG BEIM JAEGER 150
D2000 HAMBURG 63
GERMANY
(2) Special tools required
None .
(3) Materials required (Operator supplied)
DESCRIPTION  REFERENCE  QTY
AMM 20-31-00
GenkLene  Mat. No. 11-004  As  required
Epoxide Primer  Mat. No. 16-006  AS  required
Polyurethane Finish  Mat. No. 16-018  As  required
Sealant PR1431-G  Mat. No. 09-005  As required
C.PARTS TO BE RE-IDENTIFIED BY OPERATOR
None .
DATE:  SERVICE BULLETIN No:A300-57-143
REVISION No: 1 MAR 19/87  Printed In France  PAGE: 15

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