57-54!00!201 a330 - inboard flap rt repair

STRUCTURAL REPAIR MANUAL

Page 201 57−54−00Printed in Germany

Apr 01/15

INBOARD FLAP

1. General

These repairs are applicable for damage to the inboard flap. The repairsare listed in Table 201 and are described in more detail in the text thatfollows.

NOTE: For a detailed definition of repair categories, refer to Chapter51−11−14.

NOTE: For damage / repair data recording, refer to Chapter 51−11−15.

2. Safety Precautions

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIALMANUFACTURER INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

WARNING: OBEY THE MANUFACTURERS INSTRUCTIONS WHEN YOU USE CLEANING AGENT,PRETREATMENT FOR PAINTING, BONDING AND ADHESIVE COMPOUND, SEALANTAND STRUCTURE PAINT. THESE MATERIALS ARE DANGEROUS.

WARNING: BE CAREFUL WHEN YOU DO WORK WITH COMPOSITE MATERIALS:

− CARBON DUST IS ELECTRICALLY CONDUCTIVE AND CAN CAUSE AN EXPLO�SION. IMMEDIATELY REMOVE THE DUST WITH A VACUUM CLEANER

− DO NOT USE THESE MATERIALS NEAR A FLAME, SPARKS OR SOURCES OFHEAT

− USE PROTECTIVE GLOVES, GOGGLES AND A FILTER MASK WHEN YOU CUT,ABRADE OR DRILL CFRP MATERIALS

− MAKE SURE THAT THERE IS A GOOD FLOW OF AIR THROUGH THE WORKAREA

− IF YOU GET THE DUST ON YOUR SKIN, REMOVE IT WITH SOAP AND AFLOW OF CLEAN WATER

− IF YOU GET THE DUST IN YOUR EYES, FLUSH IT AWAY WITH A FLOW OFCLEAN WATER. GET MEDICAL AID

− IF YOU GET THE DUST IN YOUR LUNGS, GO OUTDOORS IMMEDIATELY ANDBREATHE FRESH AIR. GET MEDICAL AID

− OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS AND THE LOCAL REG�ULATIONS.

WARNING: BE CAREFUL WHEN YOU DO WORK WITH METALLIC MATERIALS:

− USE PROTECTIVE GLOVES, GOGGLES AND A FILTER MASK WHEN YOU CUT,ABRADE OR DRILL

− OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS AND THE LOCAL REG�


02 57−54−00Printed in Germany

Apr 01/15

ULATIONS.

CAUTION: USE ONLY SPECIFIED SOLVENTS AND CLEANING PRODUCTS, OR THEIR EQUIV�ALENTS. SOLVENTS AND CLEANING PRODUCTS THAT ARE NOT APPROVED CANCAUSE DAMAGE TO THE SURFACE PROTECTION.

CAUTION: MAKE SURE THAT YOU COVER THE AREA ADJACENT TO THE REPAIR WITHPLASTIC FOIL MASKING TAPE. IF YOU DO NOT OBEY THIS INSTRUCTION,YOU CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO THE MECHAN�ICAL AND ELECTRICAL SYSTEMS.

CAUTION: MAKE SURE THAT YOU OBEY THE REPAIR INSTRUCTIONS APPLICABLE TO YOURAIRCRAFT TYPE, WEIGHT VARIANT AND REPAIR AREA. THESE INSTRUCTIONSARE GIVEN IN THE APPLICABLE PARAGRAPH.

CAUTION: OBEY THE EFFECTIVITY BY MODIFICATION GIVEN IN THE RELEVANT PARA�GRAPH.

CAUTION: OBEY THE GIVEN INSPECTION INSTRUCTION REFERENCE (IIR) WHICH LEADSTO THE APPLICABLE INSPECTION PROGRAM DEFINED IN THE STRUCTURAL RE�PAIR INSPECTIONS (SRI) OF THE SRM, IF NECESSARY.

CAUTION: FOR THE REPAIR EFFECTIVITY RELATED TO AIRCRAFT TYPE, REFER TOPARAGRAPH 3. GIVEN IN THE INTRODUCTION OF THE SRM.

CAUTION: REPAIRS MUST NOT HINDER THE OPERATION OF MOVING COMPONENTS. IT ISIMPORTANT TO MAKE SURE THAT ALL CLEARANCE DIMENSIONS FOR COM�PONENTS ARE KEPT WITHIN THE SPECIFIED LIMITS.

CAUTION: HIDDEN DAMAGE CAN LEAD TO A FAILURE OF THE REPAIR OR SURROUNDINGSTRUCTURE.

3. Repair Scheme for Specific Repairs

REPAIR PROCEDURE PARAGRAPH FIGUREREPAIRCATEGORY

INSPECTIONINSTRUCTION REF�ERENCE (IIR)

External Bonded Metal Dou�bler and Core Repair inZone E

This repair principle isinactive since revisiondated Jul 01/11

4.A.

INACTIVE

201

INACTIVEA −

Upper and Lower Skin andCore Repair in Zone E

This repair principle isinactive since revisiondated Jul 01/11

4.B.

INACTIVE

202

INACTIVEA −

Repairs − Specific

Table 201



Apr 01/15

REPAIR PROCEDUREINSPECTION

INSTRUCTION REF�ERENCE (IIR)

REPAIRCATEGORY

FIGUREPARAGRAPH

Inboard Flap − TrailingEdge Replacement Procedure

4.C. 203 A −

External Bonded Metal Dou�bler and Core Repair forthe Trailing Edge − Zone E

4.D. 204 A −

Upper and Lower Skin andCore Repair for the Trail�ing Edge − Zone E

4.E. 205 A −

Replacement of Leading EdgeCovers

4.F. 206 A −

Repair of Dents in theTrailing Edge − Zone E

4.G. 207 A −

Skin between Two Stringers− Flush Repair

4.H. 208 C −

Skin between Two Stringers− External Doubler Repair

4.I. 209 B 57−54−00−2−001−00

Skin at Rib, betweenStringers − Flush Repair

4.J. 210 C −

Skin at Rib and Stringer −Flush Repair

4.K. 211 C −

Skin at Rib and Stringer −External Doubler Repair

4.L. 212 B 57−54−00−2−002−00

Rubbing Strip − TemporaryRepair

This repair principle isinactive since revisiondated Oct 01/11, it hasbeen moved to applicableChapter 57−54−12 Page Block201

4.M.

INACTIVE

213

INACTIVEC −

Rubbing Strip − PermanentRepair


4.N.

INACTIVE

214

INACTIVEA −


Table 201



Apr 01/15

REPAIR PROCEDUREINSPECTION

INSTRUCTION REF�ERENCE (IIR)

REPAIRCATEGORY

FIGUREPARAGRAPH

Wear Resistant Paint − Tem�porary Repair


4.O.

INACTIVE

215

INACTIVEC −

Wear Resistant Paint − Per�manent Repair


4.P.

INACTIVE

216

INACTIVEA −

Repair of Rubbing Plate −Bonded Permanent Repair


4.Q.

INACTIVE

217

INACTIVEA −

Repair of Rubbing Plate −Riveted Permanent Repair


4.R.

INACTIVE

218

INACTIVEA −


Table 201



Apr 01/15

4. Inboard Flap − Repairs

CAUTION: OBEY THE REPAIR EFFECTIVITY PER WEIGHT VARIANT AND AIRCRAFT TYPEGIVEN IN THE RELEVANT TABLE.

CAUTION: THIS ALLOWABLE REWORK LIMITS INFORMATION IS APPLICABLE AS FOLLOWS:

− BEFORE MODIFICATION 49008D42923

FOR THE EFFECTIVITY OF THE GIVEN MODIFICATION REFER TO MODIFI�CATION/SERVICE BULLETIN LIST GIVEN IN CHAPTER 57−50−00 PAGE BLOCK001.

A. External Bonded Metal Doubler and Core Repair in Zone E.

NOTE: This repair principle is inactive since revision dated Jul 01/11.

NOTE: This repair is applicable in Zone E when the upper or lower skinand the honeycomb core is damaged and is valid as shown in Table202.

AIRCRAFT WEIGHT VARIANT

A330−200 020, 021, 024, 025, 026, 027

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014

020, 024, 025

Effectivity per Weight Variant and Aircraft Type

Table 202

NOTE: Refer to Paragraph 22. ’Weight Variant Information’ in theINTRODUCTION of the SRM. Tables in the subparagraphs give necessarydata about all weight variants and their required information forallowable damage and repair applicability.

For this repair there are two different repair principles available, re�fer to the following Paragraph to get the relevant repair:

− Paragraph 4.A.(2) describes a Permanent Repair at Room Temperature(RT).

− Paragraph 4.A.(3) describes a Permanent Repair − Hot Bond Repair

NOTE: For the definition of the Repair Zones refer to Chapter 57−54−00Page Block 101.

NOTE: Before you repair the damaged structure, you must do a damageevaluation, refer to Chapter 51−77−10, Paragraph 3. for details andprocedure.



Apr 01/15

(1) Repair Materials

ITEM NOMENCLATURE QTY MATERIAL/REMARKS

1 Doubler − Refer to Figure 2012 Honeycomb Core − Refer to Figure 201− Special Material AR Material No. 05−007, refer to

Chapter 51−35−00− Special Material AR Material No. 05−033, refer to



Chapter 51−35−00− Bonding and Adhesive Com�

poundAR Material No. 08−001B, refer to


poundAR Material No. 08−010, refer to




poundAR Material No. 08−042A, refer to








poundAR Material No. 08−070 (refer to





Chapter 51−35−00− Sealant AR Material No. 09−013, refer to

Chapter 51−35−00− Cleaning Agent AR Material No. 11−003, refer to


Chapter 51−35−00− Structure Paint AR Material No. 16−001, refer to


Chapter 51−35−00



Apr 01/15

ITEM MATERIAL/REMARKSQTYNOMENCLATURE

− Structure Paint AR Material No. 16−018A, refer toChapter 51−35−00


− Emery Cloth AR Grade 280/400, local purchase

(2) Repair Instruction − Room Temperature (RT) Repair

(a) Mark the cutout according to Figure 201.

(b) Drill out all affected fastener if necessary.

(c) Cutout the damaged material. Cut the skin and the honeycomb intoa regular shape and deburr the edges.

(d) Carefully abrade the mating surface of the skin with emery cloth,grade 400 to obtain a rough surface.

NOTE: Do not abrade the CAA−layer of the existing skin.

(e) Remove the waste from the repair area with a vacuum cleaner andclean the repair area with cleaning agent (Material No. 11−003)or cleaning agent (Material No. 11−004).

(f) Apply bonding and adhesive compound (Material No. 08−074) (Mask�ing tape) around the outer edge of the overlap area. This willhelp you to remove unwanted adhesive and sealant from the repairarea.

(g) Apply bonding and adhesive compound (Material No. 08−055) to theskin surface to protect the CAA−layer.

(h) Prepare the honeycomb core plug, refer to Chapter 51−77−11, Para�graph 4.I. for details and procedure.

(i) Mix bonding and adhesive compound (Material No. 08−010) or bond�ing and adhesive compound (Material No. 08−078) with special ma�terial (Material No. 05−089) and apply the mixed paste to thefaying surfaces of the core plug, refer to Chapter 51−77−11,Paragraph 5.F. for procedure.

(j) Install and fix the honeycomb core plug, let the mixed pastecure for the defined cure cycle, refer to Chapter 51−77−11,Paragraph 6.B.(1) or manufacturer instructions for details.

(k) After the curing process, smooth the surface using emery clothgrade 280 and finish with grade 400.

(l) Prepare the repair doubler, refer to Figure 201.



Apr 01/15

(m) If necessary position the doubler to the repair area and transferthe existing fastener holes to the doubler, refer to Figure 201.

(n) Drill the required fastener holes and deburr the doubler.

NOTE: For countersinking refer to Chapter 51−46−00.

(o) Clean the doubler and the repair area with cleaning agent (Mate�rial No. 11−003) or cleaning agent (Material No. 11−004).

(p) Apply bonding and adhesive compound (Material No. 08−055) to thedoubler. Let bonding and adhesive compound cure according tomanufacturers instruction.

(q) Apply bonding and adhesive compound (Material No. 08−001B) orbonding and adhesive compound (Material No. 08−078) to the fayingsurface of the doubler.

(r) Position the doubler to the repair area and install the applica�ble fasteners if necessary, refer to Figure 201.

NOTE: Ensure that the fastener are installed during the curingtime of the bonding and adhesive compound.

(s) Let the repair cure for the defined cure cycle at RT (room tem�perature) and under pressure. To apply pressure use weights,clamps or a vacuum bag, refer to Chapter 51−77−11, Paragraph 5.D.for additional information.

NOTE: The cure process can be accelerated by the use of heat,refer to Chapter 51−77−11, Paragraph 5.E. and 6.B.(1) fordetails.

(t) Prepare special material (Material No. 05−097) or bonding andadhesive compound (Material No. 08−070) (Lamination resin) andapply a thin layer to the rear edge of the repair area if nec�essary, refer to Figure 201 and to Chapter 51−77−11, Paragraph6.B.(2) for mixing/curing details.

(u) Laminate the special material (Material No. 05−007) or specialmaterial (Material No. 05−033) to the rear edge of the repairarea, refer to Figure 201 and to Chapter 51−77−11, Paragraph 5.A.for procedure and details.

NOTE: Step 4.A.(2)(t) and 4.A.(2)(u) are necessary only in caseof damage to the rear edge, refer to Figure 201.

(v) Apply sealant (Material No. 09−013) to the circumferential edgesof the doubler, refer to Figure 201.

(w) Clean the repair area with cleaning agent (Material No. 11−003)or cleaning agent (Material No. 11−004).

(x) Apply structure paint (Material No. 16−003) or structure paint(Material No. 16−021A) to the sealant bead.



Apr 01/15

(y) Apply structure paint (Material No. 16−001) to the repair area.

(z) Apply structure paint (Material No. 16−018A) to the repair areato match the surrounding structure.

(aa)Inspect the repair, refer to Chapter 51−77−10, Paragraph 5. forprocedure and details.

(3) Repair Instruction − Hot Bond Repair

(a) Carry out repair steps 4.A.(2)(a) thru 4.A.(2)(h) above.

(b) Wrap a layer of bonding and adhesive compound (Material No.08−047A) or bonding and adhesive compound (Material No. 08−047B)around the core plug and position the prepared core plug to thecutout, refer to Chapter 51−77−11, Paragraph 5.G. for installa�tion details.

(c) Install the required heating equipment and the vacuum bag, referto Chapter 51−77−11, Paragraph 5.D. for details.

(d) Let the installed core plug cure for the defined temperature,time and vacuum, refer to Chapter 51−77−11, Paragraph 5.E. andParagraph 5.G. for details.

(e) After the curing process, smooth the surface using emery clothgrade 280 and finish with grade 400.

(f) Prepare the repair doubler, refer to Figure 201.

(g) If necessary position the doubler to the repair area and transferthe existing fastener holes to the doubler, refer to Figure 201.

(h) Drill the required fastener holes and deburr the doubler.

(i) Clean the doubler and the repair area with cleaning agent (Mate�rial No. 11−003) or cleaning agent (Material No. 11−004).

(j) Apply bonding and adhesive compound (Material No. 08−042) orbonding and adhesive compound (Material No. 08−042A) to the fay�ing surface of the repair area.

(k) Position the doubler to the repair area and install the requiredheating equipment and the vacuum bag, refer to Chapter 51−77−11,Paragraph 5.D. for details.

NOTE: Fasteners inside the range of the heating blanket have tobe removed to avoid damage to the fasteners. In this casedrill out the fasteners in the heat affected area.

(l) Let the installed doubler cure for the defined temperature, timeand vacuum, refer to Chapter 51−77−11, Paragraph 5.E. and Para�graph 5.G. for details.



Apr 01/15

(m) If necessary, install the applicable fasteners to the doubler andthe adjacent area, refer to Figure 201.

(n) Continue with step 4.A.(2)(t) thru 4.A.(2)(aa).



Apr 01/15

External Bonded Metal Doubler and Core Repair in Zone EFigure 201 (sheet 1)



Apr 01/15




Apr 01/15


CAUTION: THIS ALLOWABLE REWORK LIMITS INFORMATION IS APPLICABLE AS FOLLOWS:

− BEFORE MODIFICATION 49008D42923

FOR THE EFFECTIVITY OF THE GIVEN MODIFICATION REFER TO MODIFI�CATION/SERVICE BULLETIN LIST GIVEN IN CHAPTER 57−50−00 PAGE BLOCK001.

B. Upper and Lower Skin and Core Repair in Zone E

NOTE: This repair principle is inactive since revision dated Jul 01/11.

NOTE: This repair is applicable in Zone E when the upper and lower skinand the honeycomb core is damaged and is valid as shown in Table203.


A330−200 020, 021, 024, 025, 026, 027

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014

020, 024, 025


Table 203



− Paragraph 4.B.(2) describes a Permanent Repair at Room Temperature(RT).

− Paragraph 4.B.(3) describes a Permanent Repair − Hot Bond Repair

NOTE: For the definition of the Repair Zones refer to Chapter 57−54−00Page Block 101.




Apr 01/15



1 Doubler − Refer to Figure 2022 Honeycomb Core − Refer to Figure 202− Special Material AR Material No. 05−007, refer to



















poundAR Material No. 08−070 (refer to





Chapter 51−35−00− Sealant AR Material No. 09−013, refer to








Apr 01/15




− Emery Cloth AR Grade 280/400, local purchase

(2) Repair Instruction − Room Temperature (RT) Repair


(b) Drill out all affected fastener if necessary.

(c) Cutout the damaged material. Cut the skin and the honeycomb intoa regular shape and deburr the edges.


NOTE: Do not abrade the CAA−layer of the existing skin.

(e) Remove the waste from the repair area with a vacuum cleaner andclean the repair area with cleaning agent (Material No. 11−003)or cleaning agent (Material No. 11−004).

(f) Apply bonding and adhesive compound (Material No. 08−074) (Mask�ing tape) around the outer edge of the overlap area. This willhelp you to remove unwanted adhesive and sealant from the repairarea.

(g) Apply bonding and adhesive compound (Material No. 08−055) to theskin surface to protect the CAA−layer.

(h) Prepare the honeycomb core plug, refer to Chapter 51−77−11, Para�graph 4.I. for details and procedure.

(i) Mix bonding and adhesive compound (Material No. 08−010) or bond�ing and adhesive compound (Material No. 08−078) with special ma�terial (Material No. 05−089) and apply the mixed paste to thefaying surfaces of the core plug, refer to Chapter 51−77−11,Paragraph 5.F. for procedure.

(j) Install and fix the honeycomb core plug, let the mixed pastecure for the defined cure cycle, refer to Chapter 51−77−11,Paragraph 6.B.(1) or manufacturer instructions for details.

NOTE: Support the core plug during the curing process by an ap�propriate device.




Apr 01/15





(o) Clean the doubler and the repair area with cleaning agent (Mate�rial No. 11−003) or cleaning agent (Material No. 11−004).

(p) Apply bonding and adhesive compound (Material No. 08−055) to thedoubler. Let bonding and adhesive compound cure according tomanufacturers instruction.

(q) Apply bonding and adhesive compound (Material No. 08−001B) orbonding and adhesive compound (Material No. 08−078) to the fayingsurface of the doubler.



(s) Let the repair cure for the defined cure cycle at RT (room tem�perature) and under pressure. To apply pressure use weights,clamps or a vacuum bag, refer to Chapter 51−77−11, Paragraph 5.D.for additional information.

NOTE: The cure process can be accelerated by the use of heat,refer to Chapter 51−77−11, Paragraph 5.E. and 6.B.(1) fordetails.

(t) Prepare special material (Material No. 05−097) or bonding andadhesive compound (Material No. 08−070) (Lamination resin) andapply a thin layer to the rear edge of the repair area if nec�essary, refer to Figure 202, Sheet 2, Option 4 and to Chapter51−77−11, Paragraph 6.B.(2) for mixing/curing details.

(u) Laminate the special material (Material No. 05−007) or specialmaterial (Material No. 05−033) to the rear edge of the repairarea, refer to Figure 202 and to Chapter 51−77−11, Paragraph 5.A.for procedure and details.

(v) Apply sealant (Material No. 09−013) to the circumferential edgesof the doubler, refer to Figure 202.

(w) Clean the repair area with cleaning agent (Material No. 11−003)or cleaning agent (Material No. 11−004).

(x) Apply structure paint (Material No. 16−003) or structure paint(Material No. 16−021A) to the sealant bead.



Apr 01/15

(y) Apply structure paint (Material No. 16−001) to the repair area.

(z) Apply structure paint (Material No. 16−018A) to the repair areato match the surrounding structure.

(aa)Inspect the repair, refer to Chapter 51−77−10, Paragraph 5. forprocedure and details.

(3) Repair Instruction − Hot Bond Repair

(a) Carry out repair steps 4.B.(2)(a) thru 4.B.(2)(h) above.

(b) Wrap a layer of bonding and adhesive compound (Material No.08−047A) or bonding and adhesive compound (Material No. 08−047B)around the core plug and position the prepared core plug to thecutout, refer to Chapter 51−77−11, Paragraph 5.G. for installa�tion details.

(c) Install the required heating equipment and the vacuum bag, referto Chapter 51−77−11, Paragraph 5.D. for details.

(d) Let the installed core plug cure for the defined temperature,time and vacuum, refer to Chapter 51−77−11, Paragraph 5.E. andParagraph 5.G. for details.






(i) Clean the doubler and the repair area with cleaning agent (Mate�rial No. 11−003) or cleaning agent (Material No. 11−004).

(j) Apply bonding and adhesive compound (Material No. 08−042) orbonding and adhesive compound (Material No. 08−042A) to the fay�ing surface of the repair area.

(k) Position the doubler to the repair area and install the requiredheating equipment and the vacuum bag, refer to Chapter 51−77−11,Paragraph 5.D. for details.



Pages 219/220 57−54−00Printed in Germany

Apr 01/15

(l) Let the installed doubler cure for the defined temperature, timeand vacuum, refer to Chapter 51−77−11, Paragraph 5.E. and Para�graph 5.G. for details.


(n) Continue with step 4.B.(2)(t) thru 4.B.(2)(aa).



Apr 01/15

Upper and Lower Skin and Core Repair in Zone EFigure 202 (sheet 1)



Apr 01/15

Upper and Lower Skin and Core Repair in Zone EFigure 202 (sheet 2)


4 57−54−00Printed in Germany

Apr 01/15


C. Inboard Flap − Trailing Edge Replacement

This repair is applicable for the trailing edge of the inboard flap.

NOTE: This replacement procedure is applicable for the inboard flap partnumbers F57570200XXX, F57585000XXX and G57570503XXX only.


A330−200 ALL

A330−300 ALL


Table 204




Apr 01/15

(1) Repair Material


1 Trailing Edge Inner Part 1 Refer to Figure 2032 Trailing Edge Outer Part 1 Refer to Figure 2033 Rubbing Strip 1 Refer to Figure 2034 Insert 2 Refer to Figure 2035 Setscrew 2 Refer to Figure 2036 Trailing Edge Installation

Jig2 Refer to Figure 203

− Fastener AR Refer to Figure 203− Bonding and Adhesive Com�

pound (Masking Tape)AR Material No. 08−074 (Refer to

Chapter 51−35−00)− Sealant (Corrosion Inhibit�

ing Brush Consistency)AR Material No. 09−013 (Refer to

Chapter 51−35−00)− Cleaning Agent (Methyl−

Ethyl−Ketone)AR Material No. 11−003 (Refer to

Chapter 51−35−00)− Cleaning Agent (Trichloroe�

thane Methyl Chloroform)AR Material No. 11−004 (Refer to

Chapter 51−35−00)− Pretreatment for Painting

(Chemical Conversion Coat�ing, Yellow Aluminum)

AR Material No. 13−002 (Refer toChapter 51−35−00)

− Storage Preservation (Cor�rosion Preventive, Tempo�rary Protective Compound)

AR Material No. 15−005A (Refer toChapter 51−35−00)

− Storage Preservation (Cor�rosion Preventive, Tempo�rary Protective Compound)


− Structure Paint (Anti−Cor�rosion Primer)


− Structure Paint (Polyure�thane Top Coat, Grey)


− Structure Paint (WashPrimer)


− Chromic Acid Anodizing(CAA)

AR Refer to Chapter 51−21−11

(2) Repair Instructions, refer to Chapter 51−72−11 and Figure 203.

(a) Remove the inboard flap assembly, refer to AMM Chapter 27−54−71.

(b) Put the inboard flap assembly on a suitable support fixture.



Apr 01/15

CAUTION: MAKE SURE YOU DO NOT DAMAGE THE FLAP DURING JIG MANUFAC�TURE.

CAUTION: YOU MUST MAKE THE TRAILING EDGE INSTALLATION JIGS BEFOREYOU REMOVE THE DAMAGED TRAILING EDGE FROM THE INBOARD FLAPASSEMBLY.

(c) Make the trailing edge installation jigs to match the contour ofthe inboard flap, refer to Figure 203, sheet 2.

(d) Install the jigs, refer to Figure 203, sheet 2.

1 Put the jigs on the flap and align with the rivet centers onRib 4 and Rib 8 and the trailing edge.

2 Identify a minimum of 3 rivet positions along the length ofRib 4 and Rib 8 to attach the jigs.

3 Drill out the rivets and transfer the hole positions to thejigs.

4 Drill the holes in the jigs for the same size fastener, referto Chapter 51−44−00.

5 Deburr all holes and install the jigs with blind universal−headrivets with the same size as the removed rivets.

6 Mark the exact position of the trailing edge on each jig.

(e) Drill out all affected rivets from the trailing edge for removal,refer to Figure 203, sheet 3 thru 7.

(f) Remove the rubbing strip and attachment parts as necessary at Rib1, refer to drawing F57570200, F57585000 or G57570503.

(g) Remove the attachment parts as necessary at Rib 13, refer todrawing F57570200, F57585000 or G57570503.

(h) Mark the reference points on the inboard flap assembly as fol�lows, refer to Figure 203, sheet 8.

NOTE: The trailing edge flanges are cut from the damaged trailingedge in step 4.C.(2)(j). These flanges are used as tem�plates to install the new trailing edge.

1 Apply masking tape (bonding and adhesive compound) (MaterialNo. 08−074) along the length of the center box.

2 Mark a cross with a pencil every 500 mm (19.685 in) on themasking tape.

3 Use a compass to mark arcs on the upper flange of the trailingedge of a fixed radius with the circumference intersecting at atangent midway between the rear spar and the auxiliary spar.



Apr 01/15

4 Mark several lines along the length of the flap with a pencilfrom the centre box to the trailing edge flange.

5 Repeat work steps 4.C.(2)(h)1 thru 4.C.(2)(h)4 for the lowerflange of the trailing edge.

(i) Remove the trailing edge from the flap center box.

(j) Cut the upper and lower flanges (including rivet holes) from thedamaged trailing edge to use templates and deburr the edges, re�fer to Figure 203, sheet 9.

CAUTION: MAKE SURE THAT YOU DO NOT REMOVE THE PENCIL MARKS FROM THEFLANGE TEMPLATES DURING CLEANING.

(k) Clean the upper and lower flange templates with cleaning agent(methyl−ethyl−ketone) (Material No. 11−003) or cleaning agent(trichloroethane methyl chloroform) (Material No. 11−004).

(l) Before you install new trailing edge on flap part numbersF57570200XXX and F57585000XXX, make sure that you do the worksteps that follow:

1 Plug the two existing holes at joint of trailing edge withfasteners. For fastener detail and location refer to Figure203, sheet 11.

2 Drill four new fastener holes for trailing edge connection torear spar. Refer to Figure 203, sheet 11 and Chapter 51−44−00.

(m) Temporarily install the new trailing edge.

(n) Align the trailing edge with the installation jigs to get thecorrect contour position. You must obey the tolerances in drawingF57570200, F57585000 or G57570503 as applicable.

(o) Attach the template flanges on the new trailing edge and alignthe pencil marks from work step 4.C.(2)(h).



Apr 01/15

CAUTION: YOU MUST NOT DRILL INTO THE REAR SPAR. DUE TO MANUFACTURINGTOLERANCES THE NEW AND OLD TRAILING EDGE ASSEMBLIES CAN BEDIFFERENT DIMENSIONS. THERE CAN BE HOLE POSITION MIS�ALIGNMENT BETWEEN THE REAR SPAR AND THE FLANGE TEMPLATES.BEFORE YOU DRILL THE FINISHED FASTENER HOLE SIZE, YOU MUST:

− MAKE SURE THAT YOU USE A DRILL 0.2 MM (0.008 IN) SMALLERIN DIAMETER THAN FINISHED HOLE SIZE TO TRANSFER DRILL.

− DO A VISUAL INSPECTION TO MAKE SURE THAT THE HOLE IN THENEW TRAILING EDGE ALIGNS WITH THE HOLE IN THE REAR SPAR.

CAUTION: MAKE SURE THAT YOU DO NOT EXCEED A DRILL DEPTH OF MORETHAN 2 MM (0.080 IN).

(p) Set the drill depth to 2 mm (0.080 in) and transfer drill thetrailing edge with a drill size 0.2 mm (0.008 in) smaller in di�ameter than the finished hole size, refer to Chapters 51−43−00,51−44−00 and 51−47−00.

(q) Do a visual inspection to make sure that the holes in the newtrailing edge and the rear spar align.

(r) Drill the finished hole size, refer to Chapters 51−43−00,51−44−00 and 51−47−00.

(s) Repeat work steps 4.C.(2)(p) thru 4.C.(2)(r) for all the fastenerholes.

(t) Remove the trailing edge assembly and deburr the holes.

(u) Clean the trailing edge and the repair area with cleaning agent(Methyl−ethyl−ketone) (Material No. 11−003) or cleaning agent(trichloroethane methyl chloroform) (Material No. 11−004).

(v) Pretreat all bare surfaces of the repair area and trailing edgewith pretreatment for painting (chromic acid anodizing (CAA) orchemical conversion coating) (Material No. 13−002) or structurepaint (wash primer) (Material No. 16−020).

NOTE: For application of chemical conversion coating, refer toChapter 51−21−11.

(w) Apply structure paint (anti−corrosion primer) (Material No.16−001) to the repair area and trailing edge.

(x) Restore the paint finish around the repair area and trailing edgewith structure paint (polyurethane top coat, grey) (Material No.16−002).

WARNING: DO NOT APPLY STORAGE PRESERVATION (MATERIAL NO. 15−005A) INAREAS OF OXYGEN EQUIPMENT AND OXYGEN PIPES.

(y) If necessary, apply a corrosion preventive temporary protectivecompound to the repair area and trailing edge. First apply stor�



Apr 01/15

age preservation (corrosion preventive, temporary protective com�pound) (Material No. 15−005A) and after that storage preservation(corrosion preventive, temporary protective compound) (MaterialNo. 15−007).

NOTE: Allow storage preservation (corrosion preventive, temporaryprotective compound) (Material No. 15−005A) to cure forapprox. 1 hour before applying storage preservation (corro�sion preventive, temporary protective compound) (MaterialNo. 15−007).

NOTE: This is a supplement and means to prevent corrosion inareas where special protection required, refer to Chapter51−23−12 for information about these areas.

(z) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the mating surfaces, refer to Chapter 51−24−00.

(aa)Temporarily install trailing edge inboard assembly (1) and alignwith the installation jig.

(ab)Do a visual inspection to make sure that the trailing edge andrear spar holes are aligned and make any adjustments as neces�sary.

(ac)Install the inboard trailing edge (1) rivets, refer to Chapters51−43−00, 51−44−00 and 51−47−00 and drawing F57570200, F57585000or G57570503.

(ad)Repeat work steps 4.C.(2)(aa) thru 4.C.(2)(ac) for the outboardassembly (2).

(ae)Install the rubbing strip between Rib 1 and Rib 2, refer toChapter 57−54−12 and attachment parts as necessary, refer todrawing F57570200, F57585000 or G57570503.

(af)Install the attachment parts as necessary at Rib 13, refer todrawing F57570200, F57585000 or G57570503.

(ag)Drill out the blind head rivets and remove the trailing edgeinstallation jigs.

(ah)Reinstall the rivets removed in work step 4.C.(2)(d)2, refer toChapters 51−43−00, 51−44−00 and 51−47−00.

(ai)Install the rigging points, refer to Figure 203, sheet 10 anddrawing G57570506.

NOTE: You can use the old trailing edge to make a template toinstall the rigging points in the same position.

(aj)Install the inboard flap assembly, refer to AMM Chapter 27−54−71.



Apr 01/15

Inboard Flap − Trailing Edge ReplacementFigure 203 (sheet 1)



Apr 01/15




Apr 01/15


D. External Bonded Metal Doubler and Core Repair for the Trailing Edge −Zone E

NOTE: This repair is applicable in Zone E when the upper or lower skinand the honeycomb core is damaged and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

080, 081, 082, 083 <1>

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056, 057

080, 081, 082, 083 <1>


Table 205

<1> Only applicable After Modification 49008D42923.


For this repair there are two different repair principles available, re�fer to the following paragraph to get the relevant repair:

− Paragraph 4.D.(2) describes a permanent repair at room temperature(RT).

− Paragraph 4.D.(3) describes a permanent repair − hot bond repair.

NOTE: For the definition of the repair zones, refer to Chapter 57−54−00Page Block 101.




1 Doubler AR Refer to Figure 2042 Honeycomb Core AR Refer to Figure 204



Apr 01/15


− Special Material (GlassCloth for Laminates)

AR Material No. 05−007, refer toChapter 51−35−00

− Special Material (GlassCloth)


− Special Material (Thicken�ing Agent)


− Special Material (Resin(Epoxy))


− Bonding and Adhesive Com�pound (Epoxy Resin andHardener Adhesive)

AR Material No. 08−010D, refer toChapter 51−35−00

− Bonding and Adhesive Com�pound (Adhesive Film)


− Bonding and Adhesive Com�pound (Splice Adhesive Film(120°C) (248°F))

AR Material No. 08−047A, refer toChapter 51−35−00


AR Material No. 08−047B, refer toChapter 51−35−00

− Bonding and Adhesive Com�pound (Epoxy Resin)


− Bonding and Adhesive Com�pound (Bonding Primer)


− Bonding and Adhesive Com�pound (Composite Wet LayUp Resin)


− Bonding and Adhesive Com�pound (Masking Tape)


− Sealant (Corrosion Inhibit�ing Brush Consistency)


− Cleaning Agent (Methyl−Ethyl−Ketone)


− Cleaning Agent (Trichloroe�thane (Methyl Chloroform))


− Structure Paint (Anti Cor�rosion Primer Polyurethane)


− Structure Paint (Polyure�thane Finish Paint)


− Structure Paint (FlexiblePolyurethane)


− Emery Cloth AR Grade 280/400

(2) Repair Instructions − Room Temperature (RT) Repair (Refer to Figure204)



Apr 01/15


(b) Drill out all affected fasteners if necessary, refer to Chapter51−42−11.

(c) Cut out the damaged material. Cut the skin and the honeycombinto a regular shape and deburr the edges.


NOTE: Do not abrade the chromic acid anodizing (CAA) − layer ofthe existing skin.

(e) Remove the waste from the repair area with a vacuum cleaner andclean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane (methylchloroform)) (Material No. 11−004).

(f) Apply bonding and adhesive compound (masking tape) (Material No.08−074) around the outer edge of the overlap area. This willhelp you to remove unwanted adhesive and sealant from the repairarea.

(g) Apply bonding and adhesive compound (bonding primer) (MaterialNo. 08−055) to the skin surface to protect the chromic acid an�odizing (CAA) − layer.

(h) Prepare the honeycomb core plug, refer to Chapter 51−77−11, Para�graph 4.I for the details and procedure.

(i) Mix bonding and adhesive compound (epoxy resin and hardener adhe�sive) (Material No. 08−010D) or bonding and adhesive compound(epoxy resin) (Material No. 08−051) with special material (thick�ening agent) (Material No. 05−089) and apply the mixed paste tothe faying surfaces of the core plug, refer to Chapter 51−77−11.

(j) Install and fix the honeycomb core plug, let the mixed pastecure for the defined cure cycle, refer to Chapter 51−77−11.



(m) Clean the external doubler with cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003) or cleaning agent (trichloroethane(methyl chloroform)) (Material No. 11−004).

(n) Treat and protect the external doubler with bonding and adhesivecompound (bonding primer) (Material No. 08−055), refer to Chapter51−77−13 Paragraph 3.A.2.(b) or Paragraph 3.A.1.(b).(4) or Para�graph 3.A.1.(b).(5).



Apr 01/15

(o) If necessary position the doubler to the repair area and transferthe existing fastener holes to the doubler, refer to Figure 204.

(p) Drill the required fastener holes and deburr the doubler.


(q) Clean the doubler and the repair area with cleaning agent (meth�yl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichlo�roethane (methyl chloroform)) (Material No. 11−004).

(r) Apply bonding and adhesive compound (epoxy resin and hardeneradhesive) (Material No. 08−010D) or bonding and adhesive compound(epoxy resin) (Material No. 08−051) to the faying surface of thedoubler.

(s) Position the doubler to the repair area and install the applica�ble fasteners if necessary, refer to Figure 204.


(t) Let the repair cure for the defined cure cycle at RT (room tem�perature) and under pressure. To apply pressure use weights,clamps or a vacuum bag, refer to Chapter 51−77−11 Paragraph 5.D.

NOTE: The cure process can be accelerated by the use of heat,refer to Chapter 51−77−11 Paragraph 5.E.(1).

(u) Prepare special material (resin (epoxy)) (Material No. 05−097) orbonding and adhesive compound (composite wet lay up resin) (Mate�rial No. 08−070) and apply a thin layer to the rear edge of therepair area if necessary, refer to Figure 204 and to Chapter51−77−11.

(v) Laminate the special material (glass cloth for laminates) (Mate�rial No. 05−007) or special material (glass cloth) (Material No.05−033) to the rear edge of the repair area, refer to Figure 204and to Chapter 51−77−11.

NOTE: Step 4.D.(2)(u) and 4.D.(2)(v) are necessary only in caseof damage to the rear edge, refer to Figure 204.

(w) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the circumferential edges of the doubler, refer toFigure 204.

(x) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane (methylchloroform)) (Material No. 11−004).

(y) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead.



Apr 01/15

(z) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the repair area.

(aa)Apply structure paint (polyurethane finish paint) (Material No.16−018A) to the repair area to match the surrounding structure.

(ab)Inspect the repair, refer to Chapter 51−77−10.

(3) Repair Instructions − Hot Bond Repair (Refer to Figure 204)

(a) Carry out repair steps 4.D.(2)(a) thru 4.D.(2)(h) above.

(b) Wrap a layer of bonding and adhesive compound (splice adhesivefilm (120°C) (248°F)) (Material No. 08−047A) or bonding and adhe�sive compound (splice adhesive film (120°C) (248°F)) (MaterialNo. 08−047B) around the core plug and position the prepared coreplug to the cutout, refer to Chapter 51−77−11.

(c) Install the required heating equipment and the vacuum bag, referto Chapter 51−77−11.

(d) Let the installed core plug cure for the defined temperature,time and vacuum, refer to Chapter 51−77−11.



(g) Clean the external doubler with cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003) or cleaning agent (trichloroethane(methyl chloroform)) (Material No. 11−004).

(h) Treat and protect the external doubler with bonding and adhesivecompound (bonding primer) (Material No. 08−055), refer to Chapter51−77−13 Paragraph 4.A.2.(b) or Paragraph 4.A.1.(b).(4) or Para�graph 4.A.1.(b).(5).

(i) If necessary position the doubler to the repair area and transferthe existing fastener holes to the doubler, refer to Figure 204.

(j) Drill the required fastener holes and deburr the doubler.

(k) Clean the doubler and the repair area with cleaning agent (meth�yl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichlo�roethane (methyl chloroform)) (Material No. 11−004).

(l) Apply bonding and adhesive compound (adhesive film) (Material No.08−042) to the faying surface of the repair area.



Apr 01/15

(m) Position the doubler to the repair area and install the requiredheating equipment and the vacuum bag, refer to Chapter 51−77−11.


(n) Let the installed doubler cure for the defined temperature, timeand vacuum, refer to Chapter 51−77−11.

(o) If necessary, install the applicable fasteners to the doubler andthe adjacent area, refer to Figure 204.

(p) Continue with step 4.D.(2)(u) thru 4.D.(2)(ab).



Apr 01/15

External Bonded Metal Doubler and Core Repair for the Trailing Edge − Zone EFigure 204 (sheet 1)



Apr 01/15




Apr 01/15


E. Upper and Lower Skin and Core Repair for the Trailing Edge − Zone E

NOTE: This repair is applicable in Zone E when the upper and lower skinand the honeycomb core is damaged and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

080, 081, 082, 083 <1>

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056, 057

080, 081, 082, 083 <1>


Table 206

<1> Only applicable After Modification 49008D42923.



− Paragraph 4.E.(2) describes a permanent repair at room temperature(RT).

− Paragraph 4.E.(3) describes a permanent repair − hot bond repair.

NOTE: For the definition of the repair zones, refer to Chapter 57−54−00Page Block 101.




1 Doubler AR Refer to Figure 2052 Honeycomb Core AR Refer to Figure 205



Apr 01/15


− Special Material (GlassCloth for Laminates)


− Special Material (GlassCloth)


− Special Material (Thicken�ing Agent)


− Special Material (Resin(Epoxy))


− Bonding and Adhesive Com�pound (Epoxy Resin andHardener Adhesive)

AR Material No. 08−010D, refer toChapter 51−35−00

− Bonding and Adhesive Com�pound (Adhesive Film)





AR Material No. 08−047B, refer toChapter 51−35−00

− Bonding and Adhesive Com�pound (Epoxy Resin)


− Bonding and Adhesive Com�pound (Bonding Primer)


− Bonding and Adhesive Com�pound (Composite Wet LayUp Resin)








− Cleaning Agent (Trichloroe�thane (Methyl Chloroform))








− Emery Cloth AR Grade 280/400

(2) Repair Instructions − Room Temperature (RT) Repair (Refer to Figure205)



Apr 01/15


(b) Drill out all affected fasteners if necessary, refer to Chapter51−42−11.

(c) Cut out the damaged material. Cut the skin and the honeycombinto a regular shape and deburr the edges.


NOTE: Do not abrade the chromic acid anodizing (CAA) − layer ofthe existing skin.

(e) Remove the waste from the repair area with a vacuum cleaner andclean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane (methylchloroform)) (Material No. 11−004).

(f) Apply bonding and adhesive compound (masking tape) (Material No.08−074) around the outer edge of the overlap area. This willhelp you to remove unwanted adhesive and sealant from the repairarea.

(g) Apply bonding and adhesive compound (bonding primer) (MaterialNo. 08−055) to the skin surface to protect the chromic acid an�odizing (CAA) − layer.

(h) Prepare the honeycomb core plug, refer to Chapter 51−77−11 Para�graph 4.I. for details and procedure.

(i) Mix bonding and adhesive compound (epoxy resin and hardener adhe�sive) (Material No. 08−010D) or bonding and adhesive compound(epoxy resin) (Material No. 08−051) with special material (thick�ening agent) (Material No. 05−089) and apply the mixed paste tothe faying surfaces of the core plug, refer to Chapter 51−77−11.

(j) Install and fix the honeycomb core plug, let the mixed pastecure for the defined cure cycle, refer to Chapter 51−77−11 Para�graph 6.B.(1).









Apr 01/15

(o) Clean the doubler and the repair area with cleaning agent (meth�yl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichlo�roethane (methyl chloroform)) (Material No. 11−004).

(p) Apply bonding and adhesive compound (bonding primer) (MaterialNo. 08−055) to the doubler. Let bonding and adhesive compoundcure according to manufacturers instruction.

(q) Apply bonding and adhesive compound (epoxy resin and hardeneradhesive) (Material No. 08−010D) or bonding and adhesive compound(epoxy resin) (Material No. 08−051) to the faying surface of thedoubler.



(s) Let the repair cure for the defined cure cycle at RT (room tem�perature) and under pressure. To apply pressure use weights,clamps or a vacuum bag, refer to Chapter 51−77−11.

NOTE: The cure process can be accelerated by the use of heat,refer to Chapter 51−77−11 Paragraph 5.D.

(t) Prepare special material (resin (epoxy)) (Material No. 05−097) orbonding and adhesive compound (composite wet lay up resin) (Mate�rial No. 08−070) and apply a thin layer to the rear edge of therepair area if necessary, refer to Figure 205 sheet 3 option 4and Chapter 51−77−11.

(u) Laminate the special material (glass cloth for laminates) (Mate�rial No. 05−007) or special material (glass cloth) (Material No.05−033) to the rear edge of the repair area, refer to Figure 205and Chapter 51−77−11.

(v) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the circumferential edges of the doubler, refer toFigure 205.

(w) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane (methylchloroform)) (Material No. 11−004).

(x) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead.

(y) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the repair area.

(z) Apply structure paint (polyurethane finish paint) (Material No.16−018A) to the repair area to match the surrounding structure.

(aa)Inspect the repair, refer to Chapter 51−77−10.



Apr 01/15

(3) Repair Instructions − Hot Bond Repair (Refer to Figure 205)

(a) Carry out repair steps 4.E.(2)(a) thru 4.E.(2)(h) above.

(b) Wrap a layer of bonding and adhesive compound (splice adhesivefilm (120°C) (248°F)) (Material No. 08−047A) or bonding and adhe�sive compound (splice adhesive film (120°C) (248°F)) (MaterialNo. 08−047B) around the core plug and position the prepared coreplug to the cutout, refer to Chapter 51−77−11 Paragraph 5.G.

(c) Install the required heating equipment and the vacuum bag, referto Chapter 51−77−11 Paragraph 5.D.

(d) Let the installed core plug cure for the defined temperature,time and vacuum, refer to Chapter 51−77−11 Paragraph 5.E. and5.G.






(i) Clean the doubler and the repair area with cleaning agent (meth�yl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichlo�roethane (methyl chloroform)) (Material No. 11−004).

(j) Apply bonding and adhesive compound (adhesive film) (Material No.08−042) to the faying surface of the repair area.

(k) Position the doubler to the repair area and install the requiredheating equipment and the vacuum bag, refer to Chapter 51−77−11.


(l) Let the installed doubler cure for the defined temperature, timeand vacuum, refer to Chapter 51−77−11.


(n) Continue with step 4.E.(2)(t) thru 4.E.(2)(aa).



Apr 01/15

Upper and Lower Skin and Core Repair for the Trailing Edge − Zone EFigure 205 (sheet 1)



Apr 01/15




Jul 01/15


F. Replacement of Leading Edge Covers

NOTE: Before you repair the damaged structure, you must do a damageevaluation. Refer to Chapter 51−77−10.

NOTE: This repair is applicable for replacement of leading edge skinonly. STGR11 must remain installed and undamaged, if not contactAIRBUS.

NOTE: This repair gives information about replacement of leading edgecovers in inboard flap and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061, 080, 081, 082, 083

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056, 057, 080, 081, 082, 083


Table 207




− Aluminum Templates AR Refer to Figure 206− Bonding and Adhesive Com�

pound (Masking Tape)AR Material No. 08−074, refer to

CML− Sealant (Low Adhesion

Polysulfide Sealant)AR Material No. 09−018, refer to

CML− Sealant (Low Adhesion

Polysulfide Sealant)AR Material No. 09−019, refer to

CML− Cleaning Agent (Methyl−

Ethyl−Ketone)AR Material No. 11−003, refer to

CML

(2) Repair Instructions (Refer to Figure 206)

(a) Remove the screws common to the leading edge and carefully removethe leading edge skin.



Apr 01/15

(b) Remove the sealant from the flap substructure and the leadingedge skin.

(c) Manufacture aluminum templates at each rib location to match theouter surface contour of the existing leading edge skin. Thetemplates should pick−up all holes common to the upper surface ofthe skin and rib and be wide enough to pick−up one hole on eachside of the rib to locate the template, refer to Figure 206,sheet 1, step 1.

(d) Clamp the templates to the existing leading edge skin and backdrill the rib holes from the skin into the templates. Remove thetemplates from the existing leading edge skin.

(e) Manufacture an upper surface template from the existing leadingedge skin by sawing off a spanwise section of the upper surfacewith holes common to flap upper skin (refer to Figure 206, sheet1, step 2). Maintain a three hole diameter distance from theforward row of fastener holes.

(f) Manufacture a lower surface template similar to as given inParagraph 4.F.(2)(e) by using the lower surface of the existingleading edge skin.

(g) Place new skin on flap and trim excess as required at upper andlower surface aft edges to eliminate any interference with radius(minimum of 1 mm (0.039 in) clearance) in rebate area of upperand lower flap skins. Locate inboard and outboard to adjacentleading edge skins and trim excess as required (minimum of 1 mm(0.039 in) clearance).

(h) With the replacement leading edge skin removed, select four holelocations in outer flap skin along the forward row of fastenerholes and the aft row to be index holes to locate the new lead�ing edge skin on the upper and lower flap skin, refer to Figure206, sheet 1, step 3.

(i) Lay strips of bonding and adhesive compound (masking tape) (Mate�rial No. 08−074) (about 127 mm (5 in) long) from the edge ofthe hole extending through the rebate area onto the skin, referto Figure 206, sheet 1, step 3. The strips should be at anangle to each other to form an intersection point at the centerof the hole. Using a straight edge draw a line on each piece ofmasking tape from the center of the index hole. Leave the tapein place.

(j) Place the new leading edge skin and locate in the proper posi�tion. Draw the index hole intersecting lines from the lines onthe bonding and adhesive compound (masking tape) (Material No.08−074) on the upper and lower surface of the new leading edgeskin, refer to Figure 206, sheet 1, step 4). At intersectionpoints drill and ream original fastener holes as shown in Figure206, sheet 2, step 7.



Apr 01/15

(k) Locate the template manufactured from the old leading edge uppersurface on the new leading edge along the upper fastener holerow at index holes and wedge lock in place. Drill and ream fas�tener holes, refer to Figure 206, sheet 2, step 6.

(l) Relocate template manufactured from the old leading edge uppersurface on the new leading edge along the lower fastener holerow at index holes and wedge lock in place. Drill and ream fas�tener holes, refer to Figure 206, sheet 2, step 6.

(m) Repeat the procedure given in Paragraphs 4.F.(2)(k) and4.F.(2)(l) for the lower surface fasteners.

(n) Locate the aluminum templates for the ribs on the upper surfaceof leading edge skin at index holes and wedge lock in place.Drill and ream fastener holes, refer to Figure 206, sheet 2,step 7.

(o) Countersink and edge radius bottom of countersink at all holelocations.

(p) Deburr all holes. Place the new leading edge skin to check fitand alignment of holes.

(q) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(r) Prepare leading edge and structure for sealing. Wipe area thor�oughly with a clean cloth moistened with the cleaning agent(methyl−ethyl−ketone) (Material No. 11−003). Finish with a dry,clean cloth.

(s) Seal mating surfaces of skin and substructure with sealant (lowadhesion polysulfide sealant) (Material No. 09−018) or (low adhe�sion polysulfide sealant) (Material No. 09−019) and install newleading edge.

(t) Wet install new fasteners with sealant (low adhesion polysulfidesealant) (Material No. 09−018) or (low adhesion polysulfide seal�ant) (Material No. 09−019).

NOTE: It is important that all rivets are installed within thework life of the sealant (low adhesion polysulfide sealant)(Material No. 09−018) or (low adhesion polysulfide sealant)(Material No. 09−019). If this is not possible, install ev�ery third rivet within the work life of the sealant. Forwork life of the sealant, refer to the manufacturersinstructions.

(u) Fillet seal leading edge skin with sealant (low adhesion polysul�fide sealant) (Material No. 09−018) or (low adhesion polysulfidesealant) (Material No. 09−019).

(v) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).



Apr 01/15

(w) Replace the surface protection of the repair area, refer toChapter 51−75−12.



Apr 01/15

Replacement of Leading Edge CoversFigure 206 (sheet 1)



Apr 01/15

Replacement of Leading Edge CoversFigure 206 (sheet 2)



Jul 01/15


G. Repair of Dents in the Trailing Edge − Zone E

NOTE: Before you repair the damaged structure, you must do a damageevaluation. Refer to Chapter 51−77−10.

NOTE: For repair size limitations, refer to Chapter 57−54−00 Page Block101, Paragraph 11.C. and Figure 106.

NOTE: This repair gives information about repair of dents in the trailingedge of inboard flap in Zone E and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061, 080, 081, 082, 083

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056, 057, 080, 081, 082, 083


Table 208


Refer to Figure 207 and use the repair procedure as stated in Chapter51−77−13.

NOTE: It is recommended to use an adhesive with a low viscosity to ob�tain a good core filling, refer to Chapter 51−77−11. For the dentfilling, use bonding and adhesive compound (adhesive structuralflexible) (Material No. 08−017A) mixed with special material(thickening agent) (Material No. 05−089).



Apr 01/15

Repair of Dents in the Trailing Edge − Zone EFigure 207



Apr 01/15


CAUTION: FOR BEFORE MODIFICATION 49008D42923, THIS TEMPORARY REPAIR MUST BEREPLACED BY A PERMANENT REPAIR SOLUTION WITHIN 28 800 FC (FH NOTRELEVANT).

CAUTION: FOR AFTER MODIFICATION 49008D42923, THIS TEMPORARY REPAIR MUST BEREPLACED BY A PERMANENT REPAIR SOLUTION WITHIN 24 600 FC (FH NOTRELEVANT).

H. Skin between Two Stringers − Flush Repair

NOTE: This repair is applicable for damaged skin between two stringers −flush repair in Zone C (stringer undamaged) and is effective asfollows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056


Table 209

NOTE: Refer to Paragraph 22. ’Weight Variant Information’ in theINTRODUCTION of the SRM. Tables in the subparagraphs give the nec�essary data about all weight variants and their required informa�tion for allowable damage and repair applicability.



Apr 01/15



1 Repair Skin − Refer to Figure 2082 Repair Doubler (Internal) − Refer to Figure 208− Shim − Refer to Figure 208− Sealant (Interfay Sealant) AR Material No. 09−005, refer to

Chapter 51−35−00− Sealant (Corrosion Inhibit�

ing Brush Consistency)AR Material No. 09−013, refer to

Chapter 51−35−00− Cleaning Agent (Methyl−


Chapter 51−35−00− Pretreatment For Painting
















(a) Mark the repair area.

CAUTION: MAKE SURE NOT TO DAMAGE INTERNAL STRUCTURE OR SYSTEM WHENDRILLING.

(b) Remove the existing fasteners in the repair area, refer to Chap�ter 51−42−11.



Apr 01/15

CAUTION: A METAL SHEET MUST BE PLACED UNDERNEATH THE CUTTING AREA TOAVOID DAMAGE TO THE STRUCTURE.

(c) Cut out the damaged skin area and deburr the edges of the cut�out.

NOTE: The cutout must be parallel and perpendicular to thestringer and in the shape of a rectangle.

NOTE: The cutout must not exceed the adjacent edge of the string�er.

(d) Clean the edges of the cutout with cleaning agent (methyl−ethyl−ketone) (Material No. 11−003).

(e) Treat the edges of the cutout with structure paint (wash primer)(Material No. 16−020), refer to Chapter 51−23−00.

(f) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the edges of the cutout, refer to Chapter51−23−00.

(g) Prepare the repair parts according to Figure 208.

NOTE: Precut the doubler to oversize.

NOTE: Adapt the repair parts to the flap−contour.

(h) Put the repair parts in position.

NOTE: For steps < 0.3 mm (0.012 in) no shim must be applied. Forsteps ≥ 0.3 mm (0.012 in) and < 0.5 mm (0.02 in) applyliquid shim (sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013)). For steps ≥ 0.5 mm (0.02 in) usesolid shim.

(i) Measure the step and determine if a liquid shim, solid shim orno shim is required. Remove the repair parts.

(j) Prepare the solid shim if required.

CAUTION: MAKE SURE NOT TO DAMAGE INTERNAL STRUCTURE OR SYSTEM WHENDRILLING.

(k) Put the repair parts in position, transfer drill the existingfastener holes, drill the additional fastener holes and drill theinspection hole (if required).

(l) Make the countersinks for the fasteners in the repair skin, referto Chapter 51−46−11.

(m) Remove the repair parts and deburr the fastener holes.

(n) Cut the repair doubler (internal) to size and deburr.



Apr 01/15

(o) Clean the repair parts and repair area with cleaning agent(methyl−ethyl−ketone) (Material No. 11−003) and treat repair partswith chromic acid anodizing (CAA) or pretreatment for painting(chemical conversion coating, yellow aluminum) (Material No.13−002), refer to Chapter 51−21−11.

(p) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the repair parts, refer to Chapter 51−23−00.

(q) Apply sealant (interfay sealant) (Material No. 09−005) or sealant(corrosion inhibiting brush consistency) (Material No. 09−013) tothe mating surfaces of the repair parts, refer to Chapter51−76−11.

(r) Put the repair parts in position including the liquid shim ifrequired and install all fasteners with wet sealant (interfaysealant) (Material No. 09−005) or sealant (corrosion inhibitingbrush consistency) (Material No. 09−013), refer to Chapter51−42−11 and Chapter 51−76−11.

NOTE: For fastener installation and layout dimensions, refer toFigure 208, sheet 2.

NOTE: Make sure that the installation process is completed, or atleast one fastener is set in every third hole, during thecuring time of the sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013), refer to Chapter 51−76−00.

(s) Fill the gap between skin and repair skin (1 mm − 2 mm (0.039in − 0.079 in)) with sealant (corrosion inhibiting brush consis�tency) (Material No. 09−013).

(t) Seal the edges of the repair parts with sealant (interfay seal�ant) (Material No. 09−005) or sealant (corrosion inhibiting brushconsistency) (Material No. 09−013), refer to Chapter 51−76−11.

(u) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead, refer to Chapter 51−23−00.

(v) Apply structure paint (polyurethane top coat, grey) (Material No.16−002) to the internal surface of repair area, refer to Chapter51−23−00.

(w) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the external surface of repair area to match the sur�rounding structure, refer to Chapter 51−23−00.



Apr 01/15

Skin between Two Stringers − Flush RepairFigure 208 (sheet 1)



Apr 01/15

Skin between Two Stringers − Flush RepairFigure 208 (sheet 2)



Apr 01/15


CAUTION: THIS REPAIR MUST BE INSPECTED AT DEFINED INTERVALS. THE INSPECTIONINSTRUCTION REFERENCE (IIR) IS 57−54−00−2−001−00 AND IS DESCRIBEDIN THE STRUCTURAL REPAIR INSPECTIONS (SRI) SECTION OF THE SRM. IN�FORM YOUR PLANNING DEPARTMENT AND PROVIDE THEM WITH THE NECESSARYINFORMATION.

I. Skin between Two Stringers − External Doubler Repair

NOTE: This repair is applicable for damaged skin between two stringers −external doubler repair in Zone C (skin damage only) and is effec�tive as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056


Table 210




Apr 01/15



1 External Doubler − Refer to Figure 209− Sealant (Interfay Sealant) AR Material No. 09−005, refer to





Chapter 51−35−00− Pretreatment for Painting
















NOTE: Before you repair the damaged structure, you must do a damageevaluation, refer to Chapter 51−77−10.

(a) Mark the repair area, according to Figure 209.

CAUTION: MAKE SURE YOU DO NOT DAMAGE INTERNAL STRUCTURE OR SYSTEMWHEN DRILLING.




Apr 01/15




NOTE: The cutout must not exceed the adjacent edge of the string�er.

(d) Clean the edges of the cutout with the cleaning agent (methyl−ethyl−ketone) (Material No. 11−003).

(e) Treat the edges of the cutout with structure paint (wash primer)(Material No. 16−020), refer to Chapter 51−23−00.

(f) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the edges of the cutout, refer to Chapter51−23−00.

(g) Prepare the repair part (external doubler).


NOTE: Adapt the repair part (external doubler) to the flap−con�tour.

(h) Put the repair part (external doubler) in position, transferdrill the existing fastener holes, drill the required additionalfastener holes and drill the inspection hole (if required).

(i) Make the countersinks for the fasteners in the doubler, refer toChapter 51−46−11.

(j) Remove the repair part (external doubler) from the repair areaand deburr the fastener holes.

(k) Cut the external doubler to size and deburr.

(l) Chamfer the external doubler, refer to Chapter 51−47−00.

(m) Clean the repair part (external doubler) with the cleaning agent(methyl−ethyl−ketone) (Material No. 11−003) and treat with chromicacid anodizing (CAA) or pretreatment for painting (chemical con�version coating, yellow aluminum) (Material No. 13−002), refer toChapter 51−21−11.

(n) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to the repair part (external doubler), refer toChapter 51−23−00.

(o) Fill existing countersinks with repair washers if necessary, re�fer to Chapter 51−71−15.



Apr 01/15

(p) Apply sealant (interfay sealant) (Material No. 09−005) or sealant(corrosion inhibiting brush consistency) (Material No. 09−013) tothe mating surfaces of the repair part (external doubler), referto Chapter 51−76−11.

(q) Put the repair part (external doubler) in position and installall fasteners with wet sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency) (Mate�rial No. 09−013), refer to Chapter 51−42−11 and Chapter 51−76−11.

NOTE: For fastener layout dimensions, refer to Figure 209, sheet2.

NOTE: For fastener installation, refer to Figure 209, sheet 3.

NOTE: Make sure that the installation process is completed, or atleast one fastener is set in every third hole, during thecuring time of the sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013).

(r) Seal the edges of the external doubler with sealant (interfaysealant) (Material No. 09−005) or sealant (corrosion inhibitingbrush consistency) (Material No. 09−013), refer to Chapter51−76−11.

(s) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead, refer to Chapter 51−23−00.

(t) Apply structure paint (polyurethane top coat, grey) (Material No.16−002) to the internal surface of repair area, refer to Chapter51−23−00.

(u) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the external surface of repair area to match the sur�rounding structure, refer to Chapter 51−23−00.



Apr 01/15

Skin between Two Stringers − External Doubler RepairFigure 209 (sheet 1)



Apr 01/15




Apr 01/15




J. Skin at Rib, between Stringers − Flush Repair

NOTE: This repair is applicable for skin and rib damage between stringers− flush repair in Zone C (stringer undamaged) and is effective asfollows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056


Table 211




Apr 01/15



1 Repair Skin − Refer to Figure 2102 Repair Doubler (Internal) − Refer to Figure 2103 Repair Angle (Rib Foot) − Refer to Figure 2104 Shim − Refer to Figure 210− Sealant (Interfay Sealant) AR Material No. 09−005, refer to






















CAUTION: ONLY USE A MECHANICAL PROCEDURE TO REMOVE THE SURFACEPROTECTION. REFER TO CHAPTER 51−75−11.

(a) Remove paint and surface protection from the repair area.

(b) Mark the repair area, refer to Figure 210.


(c) Remove the existing fasteners in the repair area, refer to Chap�ter 51−42−11.



Apr 01/15


CAUTION: FOR REPAIR CUTOUT LIMITATIONS, REFER TO FIGURE 210, SHEET1).

(d) Cut out the damaged skin area and deburr the edges of the cut�out.

NOTE: The cutout must be parallel and perpendicular to thestringer and in shape of a rectangle.

(e) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(f) Measure all skin, stringer thickness and all stringer distancesof the whole repair area.


(h) Measure the steps and determine if liquid shims and solid shimsare required.

(i) Prepare the solid shims, if required.

NOTE: For steps < 0.3 mm (0.012 in) no shim must be applied. Forsteps ≥ 0.3 mm (0.012 in) and < 0.5 mm (0.02 in) applyliquid shim (sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013)). For steps ≥ 0.5 mm (0.02 in) usesolid shim (3.1364T3 / T42, clad 2024T3 / T42).


(j) Put the repair parts in position and transfer drill existingholes, drill the additional fastener holes and the inspectionhole (if required).

NOTE: For fastener layout dimensions, refer to Figure 210, sheet4).

(k) If necessary make the countersinks for the fasteners, refer toChapter 51−46−11.

(l) Remove all repair parts.

(m) Deburr the repair fasteners holes and the inspection hole (ifrequired).

(n) Cut the repair parts to size and deburr.

(o) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).



Apr 01/15

(p) Apply pretreatment for painting (chemical conversion coating, yel�low aluminum) (Material No. 13−002) to the repair parts or treatwith chromic acid anodizing (CAA), refer to Chapter 51−21−11.

(q) Apply structure paint (wash primer) (Material No. 16−020) to theedges of the cutout, refer to Chapter 51−23−00.

(r) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to repair parts and edges of the cutout, referto Chapter 51−23−00.

(s) Apply structure paint (polyurethane top coat, grey) (Material No.16−002) to repair parts and edges of the cutout, refer to Chap�ter 51−23−00.

(t) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(u) Put the repair parts in position.

(v) Install all fasteners in the repair area with sealant (interfaysealant) (Material No. 09−005) or sealant (corrosion inhibitingbrush consistency) (Material No. 09−013), refer to Chapter51−42−11 and Chapter 51−76−11.

NOTE: It is important that all fasteners are installed within thework life of the sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013). If this is not possible, install ev�ery third rivet within the work life of the sealant. Forwork life of the sealant refer to the manufacturersinstruction.

(w) Fill all gaps of the repair area with sealant (corrosion inhib�iting brush consistency) (Material No. 09−013) and remove excesssealant, refer to Chapter 51−76−11.

(x) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead, refer to Chapter 51−23−00.

(y) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the external surface of the repair area to match thesurrounding structure, refer to Chapter 51−23−00.



Apr 01/15

Skin at Rib, between Stringers − Flush RepairFigure 210 (sheet 1)



Apr 01/15




Apr 01/15




K. Skin at Rib and Stringer − Flush Repair

NOTE: This repair is applicable for skin, rib and stringer damage −flush repair in Zone C and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056


Table 212




Apr 01/15



1 Repair Skin − Refer to Figure 2112 Repair Doubler (Internal) − Refer to Figure 2113 Repair Angle (Rib Foot) − Refer to Figure 2114 Repair Stringer (Lower

Skin)− Refer to Figure 211

5 Repair Stringer (L−Profile,Upper Skin)

− Refer to Figure 211

6 Stringer Splice (LowerSkin)


7 Stringer Splice (L−Profile,Upper Skin)


8 Stringer Section (LowerSkin)


9 Stringer Section (L−Pro�file, Upper Skin)


10 Shim − Refer to Figure 211− Sealant (Interfay Sealant) AR Material No. 09−005, refer to






















Apr 01/15

CAUTION: ONLY USE A MECHANICAL PROCEDURE TO REMOVE THE SURFACEPROTECTION. REFER TO CHAPTER 51−75−11.

(a) Remove paint and surface protection from the repair area.

(b) Mark the repair area, refer to Figure 211.


(c) Remove the existing fasteners in the repair area, refer to Chap�ter 51−42−11.



(d) Cut out the damaged skin area and deburr the edges of the cut�out.

NOTE: The cutout must be parallel and perpendicular to thestringer and in shape of a rectangle.

(e) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(f) Measure all skin, stringer thickness and all stringer distancesof the whole repair area.




(h) Measure the steps and determine if liquid shims and solid shimsare required.

(i) Prepare the solid shims if required.

NOTE: For steps < 0.3 mm (0.012 in) no shim must be applied. Forsteps ≥ 0.3 mm (0.012 in) and < 0.5 mm (0.02 in) applyliquid shim (sealant (interfay sealant) (Material No.09−005) or sealant (corrosion inhibiting brush consistency)(Material No. 09−013)). For steps ≥ 0.5 mm (0.02 in) usesolid shim (3.1364T3 / T42, clad 2024T3 / T42).


(j) Put the repair parts in position as follows:



Apr 01/15

1 Put the rib repair parts in position and transfer drill exist�ing holes.

− For before Modification 49008D42923 lower skin area, refer toFigure 211, sheet 3,

− For after Modification 49008D42923 lower skin area, refer toFigure 211, sheet 4,

− For upper skin area, refer to Figure 211, sheet 5.

NOTE: For fastener layout dimensions, refer to Figure 211,sheet 6.

2 Put the stringer repair parts in position and transfer drillexisting holes.

− For before Modification 49008D42923, damaged stringer replacedby repair stringer, refer to Figure 211, sheet 5.

− For after Modification 49008D42923, splice repair, refer toFigure 211, sheet 5.


(k) Drill the inspection hole (if required) and the additional re�quired fastener holes in the skin and in the repair skin.

(l) If necessary make the countersinks for the fasteners in the skinand repair skin, refer to Chapter 51−46−11.

(m) Remove all the repair parts from the repair area.

(n) Deburr the repair fasteners holes and the inspection hole (ifrequired).

(o) Cut the repair parts to size and deburr.

(p) Apply pretreatment for painting (chemical conversion coating, yel�low aluminum) (Material No. 13−002) to the repair parts or treatwith chromic acid anodizing (CAA), refer to Chapter 51−21−11.

(q) Apply structure paint (wash primer) (Material No. 16−020) to theedges of the cutout, refer to Chapter 51−23−00.

(r) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to repair parts and edges of the cutout, referto Chapter 51−23−00.

(s) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(t) Coat the connecting surfaces of the repair parts with sealant(interfay sealant) (Material No. 09−005) or sealant (corrosioninhibiting brush consistency) (Material No. 09−013), refer toChapter 51−76−11.



Apr 01/15

(u) Put the repair parts in position.

(v) Install all fasteners in the repair area with sealant (interfaysealant) (Material No. 09−005) or sealant (corrosion inhibitingbrush consistency) (Material No. 09−013), refer to Chapter51−42−11 and Chapter 51−76−11.

(w) Fill all gaps of the repair area with sealant (interfay sealant)(Material No. 09−005) or sealant (corrosion inhibiting brush con�sistency) (Material No. 09−013) and remove excess sealant, referto Chapter 51−76−11.

(x) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead, refer to Chapter 51−23−00.

(y) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the external surface of the repair area to match thesurrounding structure, refer to Chapter 51−23−00.



Apr 01/15

Skin at Rib and Stringer − Flush RepairFigure 211 (sheet 1)



Apr 01/15




Apr 01/15


CAUTION: THIS REPAIR MUST BE INSPECTED AT DEFINED INTERVALS. THE INSPECTIONINSTRUCTION REFERENCE (IIR) IS 57−54−00−2−002−00 AND IS DESCRIBEDIN THE STRUCTURAL REPAIR INSPECTIONS (SRI) SECTION OF THE SRM. IN�FORM YOUR PLANNING DEPARTMENT AND PROVIDE THEM WITH THE NECESSARYINFORMATION.

L. Skin at Rib and Stringer − External Doubler Repair

NOTE: This repair is applicable for skin, rib and stringer damage − ex�ternal doubler repair in Zone C and is effective as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300

000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053,054, 056


Table 213




Apr 01/15



1 Repair Doubler (External) − Refer to Figure 2122 Repair Angle (Rib Foot,

Straight)− Refer to Figure 212

3 Repair Angle (Rib Foot,Joggled)


4 Repair Stringer (LowerSkin)


5 Repair Stringer (L−Profile,Upper Skin)


6 Stringer Splice (LowerSkin)


7 Stringer Splice (L−Profile,Upper Skin)


8 Stringer Section (LowerSkin)


9 Stringer Section (L−Pro�file, Upper Skin)


10 Shim − Refer to Figure 21211 Shim − Refer to Figure 21212 Shim − Refer to Figure 212− Sealant (Interfay Sealant) AR Material No. 09−005, refer to





Chapter 51−35−00− Pretreatment for Painting















Apr 01/15



(a) Mark the repair area.







(d) Clean the edges of the cutout with the cleaning agent (methyl−ethyl−ketone) (Material No. 11−003).

(e) Measure all skin, stringer thickness and all stringer distancesof the whole repair area.

(f) Prepare the repair parts according to Figure 212.




(g) Put the repair parts in position as follows:

1 Put the rib repair parts in position and transfer drill exist�ing holes.

− For before Modification upper and lower skin areas, refer toFigure 212, sheet 3,

− For after Modification lower skin area, refer to Figure 212,sheet 5.

NOTE: Use repair parts for upper and lower skin areas as ap�plicable.




Apr 01/15

2 Put the stringer repair parts in position and transfer drillexisting holes.

− For before Modification, damaged stringer replaced by one re�pair stringer, refer to Figure 212, sheet 4,

− For After Modification, damaged stringer replaced by a splicerepair, refer to Figure 212, sheet 5.

NOTE: Use repair parts for upper and lower skin areas as ap�plicable.


(h) Drill the inspection hole (if required).

(i) Position the repair doubler and transfer drill existing holes anddrill the additional required holes in the doubler.

NOTE: Pay attention to the correct sequence installation of therepair parts.

(j) If necessary make the countersinks for the fasteners in the dou�bler, refer to Chapter 51−46−11.

(k) Remove all the repair parts from the repair area and deburr allholes.

(l) Apply pretreatment for painting (chemical conversion coating, yel�low aluminum) (Material No. 13−002) to the repair parts or treatwith chromic acid anodizing (CAA), refer to Chapter 51−21−11.

(m) Apply structure paint (wash primer) (Material No. 16−020) to theedges of the cutout, refer to Chapter 51−23−00.

(n) Apply structure paint (anti corrosion primer polyurethane) (Mate�rial No. 16−001) to repair parts and edges of the cutout, referto Chapter 51−23−00.

(o) Clean the repair area with the cleaning agent (methyl−ethyl−ke�tone) (Material No. 11−003).

(p) Fill existing countersinks with repair washers if necessary, re�fer to Chapter 51−71−15.

(q) Coat the connecting surfaces of the repair parts with sealant(interfay sealant) (Material No. 09−005) or sealant (corrosioninhibiting brush consistency) (Material No. 09−013), refer toChapter 51−76−11.

(r) Put the repair parts in position.

(s) Install all fasteners in the repair area with sealant (interfaysealant) (Material No. 09−005) or sealant (corrosion inhibiting



Apr 01/15

brush consistency) (Material No. 09−013), refer to Chapter51−42−11 and Chapter 51−76−11.

(t) Fill all gaps of the repair area with sealant (interfay sealant)(Material No. 09−005) or sealant (corrosion inhibiting brush con�sistency) (Material No. 09−013) and remove excess sealant, referto Chapter 51−76−11.

(u) Apply structure paint (flexible polyurethane) (Material No.16−021) to the sealant bead, refer to Chapter 51−23−00.

(v) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the external surface of the repair area to match thesurrounding structure, refer to Chapter 51−23−00.



Apr 01/15

Skin at Rib and Stringer − External Doubler RepairFigure 212 (sheet 1)



Apr 01/15




Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS ONLY APPLICABLE BEFORE MODIFICATION55884D46413.

CAUTION: THIS TEMPORARY REPAIR MUST BE REPLACED BY A PERMANENT REPAIR WITH�IN 30 MONTHS (FC AND FH NOT RELEVANT). REFER TO PARAGRAPH 4.N.FOR RUBBING STRIP PERMANENT REPAIR.

M. Rubbing Strip − Temporary Repair

NOTE: This repair principle is inactive since revision dated Oct 01/11,it has been moved to applicable Chapter 57−54−12 Page Block 201.

NOTE: This temporary repair is applicable for damage to the rubbing stripof the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 214




− Bonding and Adhesive Com�pound (Self Adhesive Alu�minum Tape)






− Cleaning Agent (Trichloroe�thane Methyl Chloroform)


− Emery Cloth AR Grade 240, Local Purchase




Apr 01/15

(a) Mark the repair area according to Figure 213 and cover the adja�cent area with bonding and adhesive compound (masking tape) (Ma�terial No.08−074). This will help you to protect adjacent skinsurface.

CAUTION: TAKE CARE NOT TO DAMAGE THE FLAP SKIN PANEL. FURTHERMORE DONOT CAUSE ANY DEBONDING AT THE EDGE OF THE REMAINING RUB�BING STRIP PORTION.

(b) Remove the damaged rubbing strip.

(c) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004).

NOTE: For cleaning with cleaning agent (methyl−ethyl−ketone) (Ma�terial No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004) use paper or pure−cottoncloths only. Do not use fabrics containing synthetic mate�rials. Synthetics are dissolved by cold solvents and forman oil film which produces a non−adhesive surface.

(d) Lightly abrade the designated repair area with emery cloth (grade240).

(e) Carefully clean the inboard flap with cleaning agent (methyl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichloroe�thane methyl chloroform) (Material No. 11−004).

(f) Allow the cleaning agent to evaporate.

(g) To build up the damaged area of the rubbing strip, it is neces�sary to prepare three layers of bonding and adhesive compound(self adhesive aluminum tape) (Material No. 08−052), refer toFigure 213, sheet 2.

(h) Position the prepared bonding and adhesive compound (self adhe�sive aluminum tape) (Material No. 08−052) to the repair area,refer to Figure 213, sheet 2. The strips must be laid in thedirection of the flap drive (direction of the flap travel).

NOTE: If the damage is greater than the width of the tape, pre�pare sufficient strips to be laid with a butt joint betweenthe strips.

(i) Smooth out the layers from the center to remove air andwrinkles.

NOTE: Repeat this step after each layer is applied.

NOTE: If the position of the bonding and adhesive compound (selfadhesive aluminum tape) (Material No. 08−052) is not corrector if there is any indication of air bubbles, remove allthe strips and fix again.



Apr 01/15

(j) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).



Apr 01/15

Rubbing Strip − Temporary RepairFigure 213 (sheet 1)



Apr 01/15

Rubbing Strip − Temporary RepairFigure 213 (sheet 2)



Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS ONLY APPLICABLE BEFORE MODIFICATION55884D46413.

N. Rubbing Strip − Permanent Repair


For this repair there are two repair principles available, refer to thefollowing paragraphs to get the relevant repair:

− Paragraph 4.N.(2) describes a permanent repair of rubbing strip withbonding and adhesive compound (acrylic pressure sensitive tape) (Mate�rial No. 08−066)

− Paragraph 4.N.(3) describes a permanent repair of rubbing strip withsealant (corrosion inhibiting brush consistency) (Material No. 09−013).

NOTE: This permanent repair is applicable for damage to the rubbing stripof the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 215




Apr 01/15



1 Rubbing Strip − Refer to Figure 214− Bonding and Adhesive Com�

pound (Acrylic PressureSensitive Tape)











− Material No. 16−018, refer toChapter 51−35−00

− Emery Cloth AR Grade 240/320, Local Purchase

(2) Repair Instructions of Rubbing Strip with Adhesive Film (Refer toFigure 214)


(b) Remove the damaged rubbing strip, adhesive film and sealant usinga wooden spatula.




(e) Prepare the new rubbing strip according to the original.



Apr 01/15

CAUTION: CARE MUST BE TAKEN DURING GRINDING AND CLEANING OPERATIONSTO AVOID DEFORMATION OF THE RUBBING STRIPS AS THEY HAVEMINIMAL THICKNESS VALUES.

(f) Roughen the mating surface of the new rubbing strip with emerycloth (grade 240).

(g) Carefully clean the mating surface of the rubbing strip and in�board flap with cleaning agent (methyl−ethyl−ketone) (Material No.11−003) or cleaning agent (trichloroethane methyl chloroform) (Ma�terial No. 11−004).

(h) Allow the cleaning agent to evaporate.

(i) Cut the amount of bonding and adhesive compound (acrylic pressuresensitive tape) (Material No. 08−066) necessary for each rubbingstrip approximately 20 mm (0.787 in) longer.

(j) Remove the release paper from one side of the bonding and adhe�sive compound (acrylic pressure sensitive tape) (adhesive film)(Material No. 08−066) and apply the adhesive film immediately tothe mating surface of the rubbing strip. Ensure that the adhesivefilm is correctly positioned and free of air bubbles.

NOTE: The adhesive film must be positioned to cover the rubbingstrip exactly. The width of the adhesive film must be thesame as the width of the rubbing strip.

(k) Remove the release paper from the other side of the adhesivefilm.

(l) Install the rubbing strip to the inboard flap. Smooth out fromthe center to remove air.

NOTE: If any position of the rubbing strip is not correct or ifthere is any indication of air bubbles, the entire rubbingstrip must be removed and reaffixed.

(m) Apply bonding and adhesive compound (masking tape) (Material No.08−074) to the rubbing strip and to the adjacent area to give anunmasked area of 5 mm (0.197 in) from the edge of the rubbingstrip, refer to Figure 214 sheet 2. This will help you to removeunwanted sealant from the rubbing strip.

(n) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the circumferential edge of the rubbing strip,refer to Figure 214 sheet 2. Let the sealant cure according tomanufacturers instruction.

(o) Carefully remove the bonding and adhesive compound (masking tape)(Material No. 08−074) only from the rubbing strip and the adja�cent area.

(p) Apply bonding and adhesive compound (masking tape) (Material No.08−074) to the rubbing strip and to the adjacent area to give an



Apr 01/15

unmasked area of 3 mm (0.118 in) thru 5 mm (0.197 in) from thesealant, refer to Figure 214 sheet 2.

(q) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the unmasked repair area, refer to Figure 214, sheet2.

(r) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).

(3) Repair Instructions of Rubbing Strip with Sealant (Refer to Figure214)

(a) Mark the repair area according to Figure 214 and cover the adja�cent area with bonding and adhesive compound (masking tape) (Ma�terial No. 08−074). This will help you to protect adjacent skinsurface.

(b) Remove the damaged rubbing strip, adhesive film and sealant usinga wooden spatula.

(c) Roughen the repair area with emery cloth (grade 240).

(d) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004).


(e) Prepare the new rubbing strip according to the original.

CAUTION: CARE MUST BE TAKEN DURING GRINDING AND CLEANING OPERATIONSTO AVOID DEFORMATION OF THE RUBBING STRIPS AS THEY HAVEMINIMAL THICKNESS VALUES.

(f) Roughen the mating surface of the new rubbing strip with emerycloth (grade 240).

(g) Clean the rubbing strip with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004).

(h) Apply an even coat of sealant (corrosion inhibiting brush consis�tency) (Material No. 09−013) 0.25 mm (0.01 in) thick to bothmating surfaces.

(i) Install the rubbing strip to the inboard flap. Smooth out fromthe center to remove air.



Apr 01/15

(j) Apply a uniform and constant pressure to the rubbing strip witha vacuum bag or other suitable means. If a vacuum bag is used,maintain a pressure of between 0.4 and 0.6 bar (5.8 and 9.66psi).

NOTE: Let the sealant cure according to manufacturers instruction.

NOTE: If position of the rubbing strip is not correct or ifbubbles appear, the entire rubbing strip must be removedand reaffixed.

(k) Apply bonding and adhesive compound (masking tape) (Material No.08−074) to the rubbing strip and to the adjacent area to give anunmasked area of 5 mm (0.197 in) from the edge of the rubbingstrip, refer to Figure 214 sheet 2. This will help you to removeunwanted sealant from the rubbing strip.

(l) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the circumferential edge of the rubbing strip,refer to Figure 214 sheet 2. Let the sealant cure according tomanufacturers instruction.

(m) Carefully remove the bonding and adhesive compound (masking tape)(Material No. 08−074) only from the rubbing strip and the adja�cent area.

(n) Apply bonding and adhesive compound (masking tape) (Material No.08−074) to the rubbing strip and to the adjacent area to give anunmasked area of 3 mm (0.118 in) thru 5 mm (0.197 in) from thesealant, refer to Figure 214 sheet 2.

(o) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the unmasked repair area, refer to Figure 214, sheet2.

(p) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).



Apr 01/15

Rubbing Strip − Permanent RepairFigure 214 (sheet 1)



Apr 01/15

Rubbing Strip − Permanent RepairFigure 214 (sheet 2)



Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS ONLY APPLICABLE AFTER MODIFICATION55884D46413.

CAUTION: THIS TEMPORARY REPAIR MUST BE REPLACED BY A PERMANENT REPAIR WITH�IN 30 MONTHS (FC AND FH NOT RELEVANT). REFER TO PARAGRAPH 4.P.FOR WEAR RESISTANT PAINT PERMANENT REPAIR.

O. Wear Resistant Paint − Temporary Repair


NOTE: This temporary repair is applicable for damage to the wear resis�tant paint of the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 216




− Bonding and Adhesive Com�pound (Self Adhesive Alu�minum Tape)












Apr 01/15


(b) Remove the damaged wear resistant paint.






(g) To build up the damaged area of the wear resistant paint, it isnecessary to prepare three layers of bonding and adhesive com�pound (self adhesive aluminum tape) (Material No. 08−052), referto Figure 215, sheet 2.

(h) Position the prepared bonding and adhesive compound (self adhe�sive aluminum tape) (Material No. 08−052) to the repair area,refer to Figure 215, sheet 2. The strips must be laid in thedirection of the flap drive (direction of the flap travel).

(i) Smooth out the layers from the center to remove air andwrinkles.

NOTE: Repeat this step after each layer is applied.

NOTE: If the position of the bonding and adhesive compound (selfadhesive aluminum tape) (Material No. 08−052) is not corrector if there is any indication of air bubbles, remove theall strips and fix again.

(j) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).



Apr 01/15

Wear Resistant Paint − Temporary RepairFigure 215 (sheet 1)



Apr 01/15

Wear Resistant Paint − Temporary RepairFigure 215 (sheet 2)



Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS ONLY APPLICABLE AFTER MODIFICATION55884D46413.

P. Wear Resistant Paint − Permanent Repair


NOTE: For wear resistant paint damage you can do a partial repair or acomplete repair to the wear resistant paint area as necessary.

NOTE: This permanent repair is applicable for damage to the wear resis�tant paint of the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 217




1 Wear Resistant Paint AR BAC707 In Accordance toAIMS04−04−027











Apr 01/15

(a) Mark the repair area according to Figure 216 and cover the adja�cent area with bonding and adhesive compound (masking tape) (Ma�terial No. 08−074) as necessary depending on the type of repair(partial repair or complete repair). This will help you to pro�tect adjacent skin surface.

(b) Remove the damaged wear resistant paint.


NOTE: For cleaning with cleaning agent (methyl−ethyl−ketone) (Ma�terial No.11−003) or cleaning agent (trichloroethane methylchloroform) (Material No.11−004) use paper or pure−cottoncloths only. Do not use fabrics containing synthetic mate�rials. Synthetics are dissolved by cold solvents and forman oil film which produces a nonadhesive surface.




(g) Apply the wear resistant paint (item 1) on the repair area asnecessary depending on the type of repair (partial repair orcomplete repair).

(h) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).



Apr 01/15

Wear Resistant Paint − Permanent RepairFigure 216



Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS APPLICABLE BEFORE AND AFTER MODIFICATION55884D46413.

Q. Repair of Rubbing Plate − Bonded Permanent Repair


NOTE: This permanent repair is applicable for damage to the bonded rub�bing plate of the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 218




Apr 01/15



1 Rubbing Plate AR Refer to Figure 217− Bonding and Adhesive Com�

pound (Acrylic PressureSensitive Tape)











− Material No. 16−018, refer toChapter 51−35−00

− Emery cloth AR Grade 240, Local Purchase


NOTE: This is a typical repair to be carried out on detached or tornrubbing plate.

(a) Mark the repair area in accordance with Figure 217.

(b) Remove damaged rubbing plate and sealant up to normal interfacesusing wooden spatula.


NOTE: For cleaning with cleaning agent (methyl−ethyl−ketone) (Ma�terial No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004) use paper or pure−cottoncloths only. Do not use fabrics containing synthetic mate�rials. Synthetics are dissolved by cold solvents and forman oil film which produces a nonadhesive surface.

(d) Prepare new rubbing plate (item 1) according to the original.

(e) Roughen mating surface of new rubbing plate (item 1) using emerycloth (grade 240).

(f) Clean the new rubbing plate (item 1) with cleaning agent (methyl−ethyl−ketone) (Material No. 11−003) or cleaning agent (trichloroe�thane methyl chloroform) (Material No. 11−004).



Apr 01/15

(g) If you are using bonding and adhesive compound (acrylic pressuresensitive tape) (adhesive film) (Material No. 08−066), installthe rubbing plate (item 1) with (adhesive film) as follows:

1 Cut the amount of bonding and adhesive compound (acrylic pres�sure sensitive tape) (Material No. 08−066) necessary for therubbing plate (item 1) approximately 20 mm (0.787 in) longer.

2 Remove the release paper from one side of the bonding andadhesive compound (acrylic pressure sensitive tape) (adhesivefilm) (Material No. 08−066) and apply the adhesive film immedi�ately to the mating surface of the rubbing plate (item 1). En�sure that the adhesive film is correctly positioned and free ofair bubbles.

NOTE: The adhesive film must be positioned to cover the rubbingplate (item 1) exactly. The width of the adhesive filmmust be the same as the width of the rubbing plate (item1).

3 Remove the release paper from the other side of the adhesivefilm.

4 Install the rubbing plate (item 1) to the inboard flap. Smoothout from the center to remove air.

NOTE: If any position of the rubbing plate (item 1) is notcorrect or if there is any indication of air bubbles, theentire rubbing strip must be removed and reaffixed.

(h) If you are using sealant (corrosion inhibiting brush consistency)(Material No. 09−013), install the rubbing plate (item 1) withsealant as follows:

1 Apply an even coat of sealant (corrosion inhibiting brush con�sistency) (Material No. 09−013) 0.25 mm (0.01 in) thick to bothmating surfaces.

2 Install the rubbing plate (item 1) to the inboard flap. Smoothout from the center to remove air.

3 Apply a uniform and constant pressure to the rubbing plate(item 1) with a vacuum bag or other suitable means. If a vacu�um bag is used, maintain a pressure of between 0.4 and 0.6 bar(5.8 and 9.66 psi).

NOTE: Let the sealant cure according to manufacturers instruc�tion.

NOTE: If position of the rubbing strip is not correct or ifbubbles appear, the entire rubbing strip must be removedand reaffixed.

(i) Seal the edges of the rubbing plate (item 1) with sealant (cor�rosion inhibiting brush consistency) (Material No. 09−013), refer



Apr 01/15

to Figure 217. Let sealant (corrosion inhibiting brush consisten�cy) (Material No. 09−013) cure according to manufacturersinstruction.

(j) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003) or cleaning agent (trichloroethane methylchloroform) (Material No. 11−004).

(k) Apply bonding and adhesive compound (masking tape) (Material No.08−074) to the rubbing plate (item 1) to give an unmasked areaof 3 mm (0.118 in) ± 1 mm (0.039 in) on the trailing edge and 5mm (0.197 in) ± 1 mm (0.039 in) on the upper surface, refer toFigure 217, sheet 2.

(l) Apply structure paint (polyurethane finish paint) (Material No.16−018) to the unmasked repair area, refer to Figure 217, sheet2.

(m) Remove all bonding and adhesive compound (masking tape) (MaterialNo. 08−074).



Apr 01/15

Repair of Rubbing Plate − BondedFigure 217 (sheet 1)



Apr 01/15

Repair of Rubbing Plate − BondedFigure 217 (sheet 2)



Apr 01/15


CAUTION: THIS REPAIR INFORMATION IS APPLICABLE BEFORE AND AFTER MODIFICATION55884D46413.

R. Repair of Rubbing Plate − Riveted Permanent Repair


NOTE: This permanent repair is applicable for damage to the riveted rub�bing plate of the inboard flap as follows:


A330−200

020, 021, 022, 023, 024, 025,026, 027, 050, 051, 052, 053,054, 055, 056, 057, 058, 059,060, 061

A330−300000, 001, 002, 003, 004, 010,011, 012, 013, 014, 020, 022,024, 025, 050, 051, 052, 053


Table 219




1 Rubbing Plate AR Refer to Figure 218− Sealant (Corrosion Inhibit�




Chapter 51−35−00− Structure Paint (Polyure�

thane Finish Paint)− Material No. 16−018, refer to



NOTE: This is a typical repair to be carried out on detached or tornrubbing plate.

(a) Drill out the rivets from the damaged rubbing plate.

(b) Detach the damaged rubbing plate and remove sealant from the re�pair area using a wooden spatula.



Apr 01/15

(c) Clean the repair area using cleaning agent (methyl−ethyl−ketone)(Material No. 11−003).

(d) Prepare the new rubbing plate (item 1) according to the originaland adapt to the flap contour.

(e) Transfer the existing fastener holes to the new rubbing plate(item 1) and drill the required diameter.

NOTE: For fastener hole and drill data, refer to Chapter51−44−11.

(f) Make the countersinks for the fasteners, refer to Chapter51−46−11.

(g) Deburr all rivet holes.

(h) Clean the rubbing plate (item 1) and the repair area with clean�ing agent (methyl−ethyl−ketone) (Material No. 11−003).

(i) Apply sealant (corrosion inhibiting brush consistency) (MaterialNo. 09−013) to the contacting surface of the rubbing plate (item1), refer to Chapter 51−76−11.

(j) Position the rubbing plate (item 1) and install the applicablerivets, refer to Figure 218 sheet 1, 2 and 3.

(k) Install all rivets wet with sealant (corrosion inhibiting brushconsistency) (Material No. 09−013), refer to Chapter 51−76−11.

NOTE: It is important that all rivets are installed within thework life of the sealant (corrosion inhibiting brush con�sistency) (Material No. 09−013). If this is not possible,install every third rivet within the work life of the seal�ant (corrosion inhibiting brush consistency) (Material No.09−013). For work life of the sealant (corrosion inhibitingbrush consistency) refer to the manufacturers instruction.

(l) Seal the edges of the rubbing plate (item 1) with sealant (cor�rosion inhibiting brush consistency), (Material No. 09−013), referto Chapter 51−76−11.

(m) Clean the repair area with cleaning agent (methyl−ethyl−ketone)(Material No. 11−003).

(n) Apply structure paint (polyurethane finish paint) (Material No.16−018) according to Figure 218, sheet 3.



Apr 01/15

Repair of Rubbing Plate − RivetedFigure 218 (sheet 1)



Apr 01/15


57-54!00!201 a330 - inboard flap rt repair

Documents

repair area

repair effectivity

repair instructions

repair scheme

damage repair data recording

applicable paragraph

metallic materials

composite materials