^A300-600

AIRBUS INDUSTRIE

PRODUCT SUPPORT DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TeL. : (33) 61-93-33-33

Telex: AIRBU 530526F

SERVICE BULLETIN CHANGE NOTICE

S.B. No. A300-57-6011 REV.2 DATED; Dec 17/86

MOD. N0.6661H1033

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

TO OUTER SHROUD BOX

MODEL: ALL models Listed on the S.B.

DESCRIPTION!

This notice is issued to inform the affected operators that subject Service

Bulletin is changed as stated below.

Service Bulletin

Page 1 paragraph 1.A.(2)

read: Customer and Qty of Kits

Fleet No. MSN A300-57-6011

-A01

KE 501-503 361, 365, 358 3

KU 101-103 327, 332, 344 3

LH 601-607 380, 391, 401, 405, 408, 411, 414 7

RF 001,051 354, 374 2

SV 001-011 284, 294, 301, 307, 312, 317, 321

336, 341, 348, 351 11

TG 051-056 368, 371, 377, 384, 395, 398 6

XQ-001 252 1

AA-050 423 1

instead of: Customer and Qty of Kits

Fleet No. MSN A300-57-6011

-A01

KE501-503 361, 365, 358 3

KU101-103 327, 332, 344 3

LH601-607 380, 391, 401, 405, 408, 411, 414 7

RF001, 051 354, 374 2

SV001-011 284, 294, 301, 307, 312, 317, 321,

336, 341, 348, 351 11

TG051-056 368, 371, 377, 384, 395, 398 6

XX 252, 423

This change will be incorporated in the next revision of this Service Bulletin;

however no revision is planned at the present time.

FILING INSTRUCTIONS

File this Change Notice in front of this Service Bulletin.

SERVICE BULLETIN No: A300-57-6011

7 DATE: Mar 20/90 CHANGE NOTICE No.:2A

Printed in France
@A300-600

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 SB.A300-57-6011. 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 Notices 1A and IB. Revision No.2 added,

SERVICE BULLETIN

Page 1 - Inclusion of Change Notice 1B, Revision No.2 added.

Page 2 - Inclusion of Change Notice 1A. DESCRIPTION sub-para (35

revised. Revision No.2 added.

Page 5 - Paragraph 2.A.(1)(c) revised. Revision No.2 added.

Page 7-8 - Paragraph 2.C.(2) revised. Revision No.2 added.

Page 11-12 - Drawing change. Revision No.2 added.

FILING INSTRUCTIONS

1. Remove and destroy page 1 of the Summary and pages 1,2,5,7-8 and 11-12.

2. Insert page 1 of the Summary and pages 1,2,5,7-8 and 11-12 at Revision

No.2.

REVISION SEQUENCE

ORIGINAL - DEC 17/86

REVISION N0.1 - MAR 19/87

REVISION N0.2 -

7 DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-6011

REVISION NO: 2 JU|... 10/89 PfM.d In Fr.nc. pAGE: 1 Of 1
^A300-600

AIRBUS INDUSTRIE

PRODUCT SUPPORT DIRECTORATE

1 ROND POINT MAURICE BELLONTE SERVICE BULLETIN

31707 BLAGNAC CEDEX FRANCE SUMMARY

TeL (33)61-93-33-33

Telex AIRBU 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 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) A300-57-6010 details methods of

detecting cracked brackets. Embodiment of this modification renders

further compliance with ISB A300-57-6010 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 the following

A300-600 aircraft:- 252,284,294,301,307,312,317,321,327,332,336,341,344,

348,351,354,358,361,365,368,371,374,377,380,384,391,395,398,401,405,408,411

and 423. Embodied prior to delivery on aircraft MSN 388,417,420,459 and

subsequent.

COMPLIANCE

Recommended

7 DATE: DEC 17/86 SERVICE BULLETIN REF:A300-57-6011

Printed In Fr«nc«

REVISION NO: 2 -:H)l 10/R 9 PAGE: 1 of 2
AIRBUS (% MDUSTRC

A300-600 SERVICE BULLETIN

SUMMARY

MANPOWER

Kit NO.A300-57-60TI-A01

Manhours : 26.75

Elapsed time (hours, 2 fitters) 13.75

MATERIAL INFORMATION

Kit No.A300-57-6011-A01

2 Hinge Bracket Assemblies, 18 Cotter pins, 20 Nuts.

nA

OUTER SHROUD BOX

DATE: DEC 17/86 SERVICE BULLETIN REF:A300-57-6011

REVISION NO: ?„„,., i. F,,nc. PAGE: 2 of 2
^A300~600

AIRBUS INDUSTRIE

PRODUCT SUPPORT DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE A300-600 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 : B4-601, B4-602, B4-602R, B4-602 B4-621R, C4-620.

(2) Aircraft

Customer and MSN Qty of Kits

Fleet No. A300-57-6011

-A01

KE501-503 361, 365, 358 3

KU101-103 327, 332, 344 3

LH601-607 380, 391, 401, 405, 408, 411, 414 7

RF001, 051 354, 374 2

SV001-011 284, 294, 301, 307, 312, 317, 321,

336, 341, 348, 351 11

TG051-056 368, 371, 377, 384, 395, 398 6

XX 252, 423

This modification is embodied prior to delivery on aircraft MSN

388,417,420,459 and subsequent. The above effectivity and kit

allocation is based on aircraft modification status and 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.

7 DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-6011

REVISION No: 2 :il.ll 10/6"

 pf""•d ln Ff•nc• PAGE: 1 of 13
'^y/^^fvu-auu

Inspection Service Bulletin (ISB) A300-57-6010 details methods of

detecting cracked brackets. Embodiment of this modification renders

further compliance with ISB A300-57-6010 unnecessary.

This Service Bulletin introduces new Steel Brackets to replace the

existing aluminium brackets in order to improve the fatigue Life.

This Service Bulletin is subject to airworthiness authorities

monitoring.

C.DESCRIPTION

Accomplishment of this Service Bulletin consists of :-

AIRCRAFT

Kit NO.A300-57-6011-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 box.

(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 Brackets at existing positions.

(9) Re-installing inner shroud boxes.

(10) Re-installing and function testing inner airbrakes.

(11) Closing up all access panels.

D.APPROVAL

This Service Bulletin is approved by Direction Generale de L'Aviation

Civile - FRANCE (D.G.A.C.).

7 DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-6011

Printed In Ffnc* ..,.,..- -,

REVISION No: 23UL. 10/89 PAGE: 2
AIRBUS (% INDUSTRC

A300-600 SERVICE BULLETIN

E. MANPOWER

Manhours pe r aircraft

Gain access

Removal of Brackets

InstaLLation of new Brackets

Close up and test

TOTAL MANHOURS

ELAPSED TIME (HOURS) (2 FITTERS)

Kit NO.A300-57-6011-

A01

9.25

1.00

6.50

10.00

2677^

13.75

NOTE : This Service BuLLetin assumes that the aircraft has been placed in

a maintenance status. The manhours/eLapsed time do not include

preparation for the modification, non-productive elapsed time or

administrative functions.

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 Lb)

Moment + 23.5 kg.m (+ 169.92 Lb ft)

I. REFERENCES

Aircraft Maintenance Manual (AMM) 06-41-57, 27-61-54, 20-31-00

Inspection Service Bulletin (ISB) A300-57-6010

J. PUBLICATIONS AFFECTED

Illustrated Parts Catalog (IPC) 57-51-11

Structural Repair Manual (SRM) 57-51-11

DATE: SERVICE BULLETIN No: A300-57-6011

REVISION NO: 1 MAR 19/87 PrinfO In Fr.ne. DACF. 7-A
^A300-600

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, 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 ne'w 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.

(d) Refer to Figure 1, View A.

- Place suitable supports beneath the inner shroud box to

prevent excessive movement 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*.

7 DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-6011

Prinlid In Ff»nc«

REVISION No: 2 JUL 10/89 PAGE: 5
AIR BUS INDUSTRIE

A300-600 SERVICE BULLETIN

- 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 sit'-ated o 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 or pipes are not strained. Removal

of 'P'-clips will allow increased movement of the shroud box.

B. MODIFICATION

Kit NO.A300-57-6011-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 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 A5724664100095, Item 1, LH,

(A5724864100195, Item 2, RH) to the pencil outline on the shroud box

and clamp.

(b) Ensure sufficient hole landings and that 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. at positions

previously marked.

(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.d) with new Nuts H19200C-3 Item 6 using Secant PR1431-G

(Mat. No. 09-005) on interfaying sur-foces, nuts c id bolts.

DATE: DEC 17/86 SERVICE BULLETIN No: A300-57-6011

REVISION NO: Prinfd In Franc*
^A300-600

(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 bolts 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 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'. Clamp new Hinge Bracket

Assembly, Item 1 LH (item 2 RH) to the outer shroud box

ensuring that a minimum gap of 0.008 in. (0.20 mm) exists

between the flange of the fixed bearing and the washer.

(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 op.2.B.(3)(c) to 2.B.(3)(f).

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.3) and

MS24665-155, Item 4 (Qty.2), to attachment points.

(3) Reinstall attaching bolts retained in op.2.A.(1)(d) into the

landing gear bay top panel using Sealant PR1431-G (Mat. No.09-005).

(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, Item 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: A300-57-6011

Printed In Fr.nc*

REVISION No: 2 JUL 10 89

 PA6E: 7

-

8
AIRBUS ^NDUSTRC i

A300-60D SERVICE BULLETIN I

!

•

_A_ i OUT'BD ^

/''I$~'-^

:

f

::^^^^?^^^^^^^^?=::=s:^^ ' T SEE FIGURE 2

J

^

:=:=:::=:-^^:^'*^L^^——^^^_::::::^^^^^^^^^^.^ ^ No.l INBOARD SPOILER DETAIL F

.^,^--——-=:====:^^^^^^^^^^^' I ATTACHMENT POINTS \ ^CESS PANEL

>^'^\ / ~~~~————=—^^ \ \ | /^^-^^ \ A572-40980

\ \ / (REF)1-

381 ^ 4—————^ Q 40 IN. ! ^——— J ^^^^. ^^^^^^^f^\ /

\ \ / I <35.05mm) ,,•_,, '(REF) iah ________L____________^rn^^rh__________^^iC . \ /

VJ^ 1 ...__ - ^^ , % B ^>N ,

' /

r-iD-Dra-E/^D.-Kt—f ^ I ' ^ .^' '

•

, . 0.50 IN. /// ^-J.-.'^-^yZT^Y7"""""""/ 'i

 it;

-

<

'-•' /

'^^(IZ./Omm) /7 , u , / \0.6D IN. / 1

/ / .A- '--J^^ (15.24mm)'"I" I l

/ l^^ "', L-P '< ^ I INNER SHROUD

/.^ i

 t I---------X 7 ! I BOX SEE dGURE 2

/^-^^^ ^ i^ \ (^ ^\-^, // ; i DETAIL E

/ ^^S^^^LLj"'"'/" - - -- - - V • ' REMOVE AND RETAIN BOLTS \

/

 D/Dr^~^7^~=E^5~-=^./ , ~~~------_ / i I (QTY 42) SECURING LANDING \ l

ENSURE CORNER RADIUS ON / Dr^gT^^r^^,, \ : \\ GEAR BAY TOP PANEL TO V- ~ ,

HOLES (STY 3) o-f 0.015/O.U25IN. / ul ^^^""--^^ ! A' INNER SHROUD BOX. /p! \ / I

TO ALLOW BOLT HEADS TO / i (•J^___________\__________________________________fe;;.'Ja g-^W \

SEAT CORRECTLY WHEN INSTALLED. 1 (LH) |C -^,. <,.o.,.oXo.,,ooooB.o..,o<iooooooB.o. o .A ,",7 | ";' /

2(RH) ___ i ^^. \ |/ /

| Q | "^^ LANDING GEAR BAY^~---i^ /

| P | | ^\ TOP PANEL || /

! ^"^-———————.I - |-————... ^__,___——~^_/OUTER SHROUD

VIEW SHOWING POSITION OF AFT | |A| Box

HINGE BRACKET ON OUTER SHROUD | ' •

Box

 VIEW LOOKING DOWN ON

INNER SHROUD BOX LH

RH SIMILAR BUT OPPOSITE

i

• I

InstaLLation of new Hinge Bracket Assembly i

Figure 1 ;

DATE: D&C 17/8 6 SERVICE BULLETIN No: A300-57-60n I

REVISION NO: Printed m France PAGE: 9-10

 [
A I R B US (^INDUSTRIE

A300-600 SERVICE BULLETIN

SLIDING MIN. 0.008 IN.

BUSH (REP) (0.20MM)

FIXED ,,_.,. _-,

BEARING ^^-ffl

LANDING GEAR BAY

TOP PANEL

Views showing clearances when instaLLing

the new Hinge Bracket

Figure 2

DATE: DEC 17/8 6 SERVICE BULLETIN No: A300-57-6011

REVISION NO: 2 JUL 10/8 9 printed in France PAGE: 11-12
AIRBUS^INOUSTRC

A300-600 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. A300-57-6011-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 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: A300-57-6011

REVISION NO: 1 MAR 19/87 PAGE: 13

Printed In Frjnc*