Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 1 of 20

A/C: MSN: 0533 A320-214-008

Compiled: G. Stemmer

Inspection of the rudder external surface 

The external surface of the rudder has to be inspected in defined areas for debonding. 

Inspect the Rudder S/N: TS1536 installed at MSN 0533 in the areas: 

RH Panel: Area B detailed on page 13 and adjacent pages as per Part II 

LH Panel: Area C detailed on page 13 and adjacent pages as per Part I 

This inspection has to be performed by Airbus staff only. 

The inspection results have to be reported immediately to Airbus to get further instructions 

(use the reporting sheet from page 9, use one reporting sheet for each inspection area). 

Send the inspection report with a referenced mail to: 

AIRTAC (Airbus Technical AOG Center) 

Customer Services 

AIRBUS Central Entity 

Phone: +33 (0)5 61 93 3400 (24 hour) 

Fax: +33 (0)5 61 93 3500 

Mailto: airtac@airbus.com

and 

Nicolas SEYNAEVE

Structure Engineer 

A380 & A318/A319/A320/A321 Structure Engineering Support

Customer Services - SEES5 

AIRBUS Central Entity

Phone: +33(0)5 61 93 34 38 

Fax: +33(0)5 61 93 36 14 

Mailto:nicolas.seynaeve@airbus.com

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 2 of 20

A/C: MSN: 0533 A320-214-008

Job preparation: 

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE 

IN POSITION BEFORE YOU START A TASK ON OR NEAR THE HORIZONTAL AND VERTICAL 

STABILIZERS (REFER TO AMM 55-40-00). 

NOTE: To achieve a full picture of the structural condition in the inspection area it is required 

to check in advance the aircraft documentation for any repairs performed by the operator in 

that area. If repairs in the inspection area are documented report to Airbus in order to check 

or adapt the inspection procedure.

- The aircraft must be in a Hangar or Dock providing accessibility to the complete 

rudder external surface. 

- Make sure that the aircraft is electrically grounded 

(Refer to A320 AMM 12-34-24 PB 200). 

- Make the horizontal and vertical stabilizer safe (Refer to A320 AMM subtask 

55-40-00-865-050 and 55-40-00-860-052). 

- Conditions and supplies needed for inspection: 

- Compressed air supply for ELCH test (only for Part II) 

- 16Amp 220V Power (or comparable 110V for 3600Watt) for Thermography 

 inspection. 

- Max. ambient temperature of 35°C for Thermography inspection. 

- For performing a manual tap test the noise in the hangar must be limited. 

- Get access to the rudder (if required by a platform or Cherry Picker) 

- Get access to the rudder front spar by opening the relevant trailing edge panel, 

verify and record Rudder S/N and P/N 

(the identification plate is located on the rudder front spar, see next page). 

- Record Aircraft FH & FC. 

Perform the inspections as per Part I and/or II

Job close up: 

- Make sure that the work areas are clean and clear of tools and other items of 

equipment. 

- Remove the control safety locks and warning notices, as necessary. 

- Put the horizontal and vertical stabilizers to operating condition. 

- Remove the access platforms, if used. 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 3 of 20

A/C: A320-214-008 MSN: 0533

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 4 of 20

A/C: MSN: 0533 A320-214-008

NDT Equipment list

All NDT equipment will be provided by Airbus. 

• ELCH

ELCH BT100 Version 2 and calibration block PN 99A554-07322-000 

• Tap Test

Mitsui Woodpecker WP632 preferred 

alternative: Tap Test Tool : PN 98A57103013000 

NOTE: Tap test tool PN 99A55209001000 (tap test hammer) not suitable for 

inspection of rudder skins. 

• Thermography

Airbus Kits PN 99A55407320000 

 & PN 99A55407321000 

• Vacuum Loss Inspection

Wood’s Power Grip TL3AMBNS 3" Concave Vacuum Cup with Indicator 

• Boroscope

 Equipment as detailed in Airbus instruction D55RP0828599 : 2.7mm, diameter 30° 

• X-Ray

Equipment as detailed in A320 NTM 51-10-10 

(only if available on customer side and requested by Airbus NDT specialist) 

Equipment list for the composite mechanic: 

All equipment will be provided by Airbus. 

Relevant tools and auxiliary materials for: 

• Cleaning 

• Drilling 

• Sanding 

• Resin and mixing Equipment 

• Syringes for resin injection 

• High Speed Tape 

• Adhesive Foil for Vacuum loss inspection 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 5 of 20

A/C: MSN: 0533 A320-214-008

Inspection instruction (Part I): 

NOTE: For structural details like core data and skin thickness see page 10 to 12. 

Inspect the external surface as defined on page 1 by the methods: 

 Mark and clean the inspection Area (with Solvent General Purpose (Mat No. 11-026) and lint 

free Cotton Cloth (Mat. No. 19-003)). 

 Perform Tap Test or Woodpecker as per A320 NTM 51-10-03 or NTM 51-10-19. 

 Perform IRT (Thermography) Inspection as per Airbus Instructions X5540RP0828668 (General procedure for thermographic inspection to detect trapped water in honeycomb structures 

mounted vertically). 

 Perform ELCH Inspection as per Airbus Instruction X51RP0828659 (General 

Procedure to Inspect Honeycomb Structures with ELCH). 

Apply a test grid of 50mm and maintain a distance from any edge or screw of 75mm. 

For calibration use Method 1 and apply the threshold values for: 

the area between trailing edge screws and trailing edge: 

(1) Yellow value: 0.3mm and (2) Red value: 0.4mm 

all other areas: 

(1) Yellow value: 0.25mm and (2) Red value: 0.35mm 

 CAUTION:

- If any kind of debonding was detected by the above inspections do not continue with the 

inspection. 

Document the inspection results using the report sheet on page 9, mark the 

inspection results with dimensions on the rudder surface and document by a photo. Send 

the report immediately to Airbus to get further instructions. 

- If no debonding was detected by the above inspections proceed with the Vacuum Loss Inspection. 

 For Vacuum Loss Inspection: 

- Prepare the surface (Position the adhesive foil, mark the grid of holes for 

inspection as per sketch). 

- Drill the inspection holes with diameter 1,5 mm through the outer skin only. 

WARNING: Drill penetration into the sandwich structure has to be limited to 

20mm to prevent inner skin damage. 

- Perform the Inspection as per Airbus Instructions D55RP0826329 (General 

Procedure to detect damage in Honeycomb Core Sandwich Structures by 

applying vacuum). 

- In case of indications perform damage size assessment in width direction as 

per instructions on page 7. 

- Document the inspection results using the report sheet on page 9. 

In case of findings mark the inspection results with dimensions on the rudder surface and 

document by a photo. 

When repairs with deviating dimensions as those presented by the inspection drawings or 

additional repairs performed by the operator are found these have to be included in the 

damage report with relevant dimensions. 

Close up: 

In case of no indication close the inspection holes by one of the procedures detailed on next page. 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 6 of 20

A/C: MSN: 0533 A320-214-008

Temporary inspection hole repair (Option I):

(1) Close the holes with high speed tape (Mat-No. 08-052) or self-adhesive patches 

ASNA2879A040 (which can become painted). 

This temporary repair has to be replaced by the permanent repair latest after 600 FC 

(FH not relevant). Correct cover application has to be ensured by visual re-inspection during the 

temporary period. 

Temporary inspection hole repair (Option II): 

(1) Prepare and dry the repair area (Refer to Chapter 51-77-11, Paragraph 4.M.(2)). 

(2) Prepare the laminating resin (Mat. No. 08-070, Refer to Chapter 51-77-11, Paragraph 6.B.(2) 

and 4.A.(3)). Warm up the mixed resin to a maximum of 45°C to achieve the required viscosity for injection. 

(3) Fill a syringe (max. tube diameter 1,0 mm) with the prepared adhesive, inject the adhesive 

through the hole in the skin into the cells of the honeycomb core. Start injection at the cell 

bottom and finish when resin is leaking out of the inspection hole. 

(4) Remove the syringe out of the hole and place immediately a piece of high speed tape (MatNo. 08-052) or self-adhesive patches ASNA2879A040 (which can 

become painted) on the repair area. 

(5) Cure the adhesive for a minimum of 6h at RT. 

If RT is below 18°C (65°F) perform resin gelation t est outside the repair area. After resin 

gelation plus 2h the aircraft can be released to operations again.

This temporary repair has to be finished by the final surface restoration (continue with permanent 

repair step (6)) latest after 4500 FC (FH not relevant).

Permanent inspection hole repair:

(1) Prepare and dry the repair area (Refer to Chapter 51-77-11, Paragraph 4.M.(2)). 

(2) Prepare the laminating resin (Mat. No. 08-070, Refer to Chapter 51-77-11, Paragraph 6.B.(2) 

and 4.A.(3)). Warm up the mixed resin to a maximum of 45°C to achieve the required viscosity for injection. 

(3) Fill a syringe (max. tube diameter 1,0 mm) with the prepared adhesive, inject the adhesive 

through the hole in the skin into the cells of the honeycomb core. Start injection at the cell 

bottom and finish when resin is leaking out of the inspection hole. 

(4) Remove the syringe out of the hole and place immediately a piece of sticky tape on the repair 

area. 

(5) Cure the adhesive for 12h at RT. If RT is below 18°C (65°F) perform resin gelation test outside the repair area. After resin gelation plus 4h continue with next step. 

(6) Remove the sticky tape from the repair area. 

(7) Inspect the repair (Refer to Chapter 51-77-10, Paragraph 5.). 

(8) Remove any resin remnants from the border area of the repair, use abrasive cloth. Start with 

280 grade and finish with 400 grade. 

(9) Clean the repair area with cleaning agent (Material No. 11-003 or 11-004 and refer to Chapter 51-77-11, Paragraph 4.E.). 

(10) Restore the surface protection (Refer to Chapter 51-75-12). 

All references as per A320 SRM Revision 01 AUG 2008.

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 7 of 20

A/C: A320-214-008 MSN: 0533

Damage assessment by Vacuum Loss Inspection: 

NOTE: For the inspections a normal paint condition and an adequate flat surface is 

expected. If intensive paint cracking or surface waviness is present a local surface 

polishing by sanding is advisable. For the sanding operation use cloth 280 or 400 

grade. By the sanding operation neither the surface primer nor the outer fabric layer 

should become effected. 

If the Vacuum Loss Inspection still reveals damage an Add-on inspection in midfield 

direction only must be performed to define the overall damage size. 

- For Add-on inspection 1 drill one additional row of inspection holes with a pitch 

of 25mm and one extra hole at each end of the row parallel to the detected 

leakage as per sketch below. Drill inspection holes with diameter 1,5 mm 

through the outer skin only. 

WARNING: Drill penetration into the sandwich structure has to be limited to 

20mm to prevent inner skin damage. 

- Perform Vacuum Loss Inspection (same procedure as applied for basic inspection), position the vacuum cup in a way that only one of the new holes is covered by the cup during each measurement. 

- If no extra leakage is found document the damage using the reporting sheet. 

- If more leakages are found proceed with Add-on inspection 2 (and if required 

further steps until the whole damage extend is detected) using the same procedure as detailed above. 

NOTE: The overall damage length and width is bounded by those rows of 

inspection holes which do not indicate a vacuum loss. 

 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 8 of 20

A/C: MSN: 0533 A320-214-008

Inspection instruction (Part II): 

NOTE: For structural details like core data and skin thickness see page 10 to 12. 

Inspect the external surface as defined on page 1 by the methods: 

 Mark and clean the inspection Area (with Solvent General Purpose (Mat No. 

11-026 and lint free Cotton Cloth (Mat. No. 19-003)). 

 Perform Tap Test or Woodpecker as per A320 NTM 51-10-03 or NTM 51-10-19. 

 Perform IRT (Thermography) Inspection as per Airbus Instruction X5540RP0828668 

(General procedure for thermographic inspection to detect trapped water in honeycomb structures mounted vertically). 

 Perform ELCH Inspection as per Airbus Instruction X51RP0828659 (General 

Procedure to Inspect Honeycomb Structures with ELCH). 

Apply a test grid of 50mm and maintain a distance from any edge or screw of 75mm. 

For calibration use Method 1 and apply the threshold values for: 

the area between trailing edge screws and trailing edge: 

(1) Yellow value: 0.3mm and (2) Red value: 0.4mm 

all other areas: 

(1) Yellow value: 0.25mm and (2) Red value: 0.35mm 

 In case of indication perform damage size assessment. 

 Document the inspection results using the report sheet on page 9. 

In case of findings mark the inspection results with dimensions on the rudder surface 

and document by a photo. 

When repairs with deviating dimensions as those presented by the inspection 

drawings or additional repairs performed by the operator are found these have to be 

included in the damage report with relevant dimensions. 

Close up: 

Clean the inspection Area (with Solvent General Purpose (Mat No. 11-026 and lint free 

Cotton Cloth (Mat. No. 19-003)) from any remnants of the US-Inspection. 

Complementary inspection methods (Part III): 

Complementary inspection methods are required only in case of unclear indication from 

Part I or Part II to identify the cause of the indication and to confirm the damage (Refer to 

NTM Para 8 “Acceptance Criteria”). 

 

 Boroscope inspection as per Airbus Instruction D55RP0828599 (General visual 

boroscop inspection for internal honeycomb core sandwich structures). 

 X-Ray inspection as per A320 NTM 51-10-10 Part 2 

(only if available on customer side and requested by Airbus NDT specialist) 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 9 of 20

A/C: MSN: 0533 A320-214-008

 

Inspection Report

Rudder Surface Inspection as per specific TD in area:

Aircraft type: Inspection date:

MSN: Operator:

Rudder S/N: FC:

Rudder P/N: FH:

Inspection method

Tap Test No findings Findings as detailed

Inspection by sketch* and photos

Thermography No findings Findings as detailed

Inspection by sketch* and photos

ELCH Inspection No findings Findings as detailed

by sketch* and photos

Vacuum Loss No findings Findings as detailed

Inspection by sketch* and photos

* use inspection sketches of the TD

as a submittal

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 10 of 20

A/C: A320-214-008 MSN: 0533

General Overview 

Core Blocks 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 11 of 20

A/C: MSN: 0533 A320-214-008

General Overview 

Core Blocks

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 12 of 20

A/C: A320-214-008 MSN: 0533

General Overview 

Outer Skin Thickness in Booster area 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 13 of 20

A/C: A320-214-008 MSN: 0533

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 14 of 20

A/C: MSN: 0533 A320-214-008

Inspection area B 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 15 of 20

A/C: A320-214-008 MSN: 0533

Inspection area B 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 16 of 20

A/C: A320-214-008 MSN: 0533

Inspection area B 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 17 of 20

A/C: A320-214-008 MSN: 0533

Inspection area B 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 18 of 20

A/C: MSN: 0533 A320-214-008

Inspection area C 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 19 of 20

A/C: A320-214-008 MSN: 0533

Inspection area C 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.
Technical Disposition Ref.: TD/K4/S2/27051/2009

Issue: B

Date: 25 Feb 2009 20 of 20

A/C: A320-214-008 MSN: 0533

Inspection area C 

Page:

Copyright Airbus S.A.S. 2009. All rights reserved.

This document contains Airbus S.A.S. (Societe par Actions Simplifiee) proprietary information and shall at all times remain the property of Airbus S.A.S.. 

No intellectual property right or license is granted by Airbus S.A.S. in connection with any information contained in it. It shall be treated as confidential, shall not be disclosed in whole or in part 

to any third party and shall not be duplicated in any manner, without Airbus S.A.S. prior written consent. This Technical Disposition (TD) only covers design aspects and excludes 

workmanship aspects. It has been prepared for a specific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis of the information supplied to Airbus. 

This TD is not to be used for any other aircraft or component or any other purposes than for which it was supplied without the written approval of Airbus.