QA300

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

TITLE : 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.C2 ) 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 N0.1 - MAR 19/87

REVISION N0.2 - -)UL J.0/89

7 DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-143

REVISION No: 2 JUI, 10/8 9 PAGE: 1 of 1

Prtn<«4 In Ffno*
®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

TITLE : 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 :3UL 10/8^^^,^ PAGE: 1 of 2
AIR BUS'INDUSTRIE

A300 SERVICE BULLETIN

SUMMARY

MANPOWER

Kit No. : A300-57-U3-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,

OUTER SHROUD BOX

DATE: DEC 17/86 SERVICE BULLETIN REF :A300-57-U3

REVISION NO: PAGE: 2

Printed In Franc*
®A300

AIRBUS INDUSTRIE

PRODUCT SUPPORT DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLA6NAC CEDEX FRANCE A300 SERVICE BULLETIN

Tel (33)61-93-33-33

Telex AIRBU 530526 F

MODIFICATION No: 6661H1033 ATA SYSTEM: 57

TITLE : WINGS - AUXILIARY STRUCTURE - TO INTRODUCE IMPROVED AFT HINGE

BRACKETS TO OUTER SHROUD BOX.

1.PLANNING INFORMATION

A.EFFECTIVITY

( 1 ) Aircraft Models : B1, B2-1C, B2K-3C, B2-203, B4-2C, B4-102,

B4-103, B4-120, B4-203, B4-220 and C4-203.

(2) Aircraft.

Customer and MSN Qty of Kits

Fleet No. A300-57-143

-A 01

AP001-003 005,006,007 3

AF009 104 1

AF051-054 019,023,045,047 4

AF056-064 074,078,100,129,145,146,175,178,183 9

AI101-103 177,180,190 3

AY001.002 299,302 2

AZ151-158 101,106,107,123,139,140,142,173 8

CI001-006 193,197,221,232,179,171 6

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 17

216,220,259,261,271,274

EA291.292 049,051 2

7 DATE: DEC 17/86 SERVICE BULLETIN No; A300-57-143

REVISION No: 2^1- ^'^..a^.,.. PAGE: 1 of 15
A) R 8 U S (% NOUSTRC

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 1

HF 169,174 2

HF301-304 009,012,017,020 4

HF307 083 1

IB251-256 130,133,135,136,156,170 6

1C 026 1

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 9

J0101 256 1

JM001.002 127,131 2

KE001-008 014,016,018,024,028,030,031,081 8

KE101.102 277,292 2

L6001 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

OA001-008 046,056,058,103,105,148,184,189 8

PA001-012 195,227,198,247,234,236,304,305,238, 12

235,208,210

PK001-004 096,098,099,114 4

PK010-013 064,144,268,025 4

PR001-005 063,069,125,203,219 5

RK551-553 137,243,282 3

SA001-004 032,037,039,040 4

SA051-053 138,192,222 . 3

DATE: DEC 17/86 SERVICE BULLETIN No:A300-57-143

REVISION NO: PriBfd I- Fr.nc. PAGE:2
®A300

Customer and MSN Qty of Kits

Fleet No. A300-57-143

-A 01

SA101 212 1

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 1

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^

 l^„8

,

^/

„„.^ PAGE: 3
®A300

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 I'Aviation

Civile - FRANCE (O.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^ 10/^.,^.^

 p^ ^
AIRBUS^NOUSTRC

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 (1.5 8 Lbs) .

Moment + 23.5 Kg. m (169.9 2 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

 p^i"t

'

d ln Fr•nc• PAGE:5-6
®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 arc 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,572GB,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.

- If 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 N0= Z JUL 10.,:,:..,,.^ P*GE= 7
AIRBUS'%«NOUSTWE

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) Carefully 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 17/8 6 SERVICE BULLETIN NO:A300-57-143

REVISION NO: ?„„..<.. pr.nc. PA6E:8
AIRBUS INDUSTRIE

A300 SERVICE BULLETIN

(d) Spot-face 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

spptfaces with Genklene (Mat. No.11-004). Restore protective

treatment using Primer (Mat. No.16-006) and Polyurethane Finish (Mat

No.16-018).

(c) 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 H19200C-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 (A572486410Q195, 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,

Item 1 LH (Item 2 RH) from the inner shroud box, retain the bolts and

sliding bush installed at op.2.B.(4)(a).

(h) Perform ops.2.B.(3)(c) to 2.B.(3)(f) inclusive.

DATE: DEC 17/8 6 SERVICE BULLETIN No:A300-57-143

REVISION No.1 MAR 19/87 prrfo in Fr.nc. PAGE:9
®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.d).(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 ^UL ^^r.no<

 PAGE: 10
ACCESS PANEL

A572-4R980

AIRBUS^^NDUSTRE

A300 SERVICE BULLETIN

Installation of new Hinge Bracket Assembly

Figure 1

DATE: DEC 17/86 SERVICE BULLETIN No:A300-57-143

REVISION NO: Pnnled in Franct PAGE: 11-1 2
A I R BU S (^INDUSTRIE

A300 SERVICE BULLETIN

SLIDING ZERO CLEARANCE

 SLIDING MIN- 0

-

008 INBUSH (REF ) IS NORMAL BUSH-(REF ) (0.20MM)

FIXED ,.-,. n-1

BEARING ^"^

FIXED -

BEARING ^'-"^U

DETAIL F

PRE MOD. 1096

DETAIL F

POST MOD. 1096

Q 0 Q iJnjJ MAKE SURE AN EQUAL

LANDING GEAR BAY

TOP PANEL

GAP EXISTS BETWEEN

THE BEARING AND

THE BRACKET FACES

Views showing clearances when installing

the new Hinge Brackets.

Figure 2

DATE: npp ,-,/,,,, SERVICE BULLETIN No:A300-57-143

DLL 17/0 0

REVISION NO: 2 JUL 10/8 9 Printed in France PAGE:13-14
AIRBUS^INOUSTRC

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.

1 A5724864100095 1 Hinge Bracket A57241917000 A,B, C

Assembly (LH )

2 A5724864100195 1 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 4 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

procured by Spares Purchase Order from: AIRBUS INDUSTRIE

SPARES SUPPORT CENTER

WEG DEIM 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 ?,,„, . a m Franc . PAGE:15