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

Issue: B Date: 25 Feb 2009 1 of 20 A/C: MSN: 0533 A320-214-008 G. Stemmer Compiled:



### Inspection of the rudder external surface The external surface of the rudder has to be inspec ted in defined areas for debonding. Inspect the Rudder S/N: TS1536 installed at MSN 053 3 in the areas: RH Panel: Area B detailed on page 13 and adjacent p ages as per Part II LH Panel: Area C detailed on page 13 and adjacent p ages as per Part I This inspection has to be performed by Airbus staff only. The inspection results have to be reported immediat ely to Airbus to get further instructions (use the reporting sheet from page 9, use one repor ting sheet for each inspection area).
Send the inspection report with a referenced mail t o:
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 Su pport 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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 conditi on 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 do cumented 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 grounde d (Refer to A320 AMM 12-34-24 PB 200).

- Make the horizontal and vertical stabilizer safe (R efer 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 Par t 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 o f tools and other items of equipment.

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

- Put the horizontal and vertical stabilizers to oper ating 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 3 of 20 A/C: MSN: 0533 A320-214-008 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 pr ovided by Airbus.

• ELCH ELCH BT100 Version 2 and calibration block PN 99A55 4-07322-000 • Tap Test Mitsui Woodpecker WP632 preferred alternative: Tap Test Tool : PN 98A57103013000 NOTE: Tap test tool PN 99A55209001000 (tap test ham mer) 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 wi th Indicator • Boroscope Equipment as detailed in Airbus instruction D55RP0 828599 : 2.7mm, diameter 30° • X-Ray Equipment as detailed in A320 NTM 51-10-10 (only if available on customer side and requested b y Airbus NDT specialist)
Equipment list for the composite mechanic: All equi pment 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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 ski n thickness see page 10 to 12. Inspect the external surface as defined on page 1 b y the methods:

 Mark and clean the inspection Area (with Solvent Ge neral Purpose (Mat No. 11-026) and lint free Cotton Cloth (Mat. No. 19-003)).  Perform Tap Test or Woodpecker as per A320 NTM 51-1 0-03 or NTM 51-10-19.  Perform IRT (Thermography) Inspection as per Airbus Instructions X5540RP0828668 (General procedure for thermographic inspection to dete ct trapped water in honeycomb structures mounted vertically).  Perform ELCH Inspection as per Airbus Instruction X 51RP0828659 (General Procedure to Inspect Honeycomb Structures with ELCH ). Apply a test grid of 50mm and maintain a distance f rom any edge or screw of 75mm. For calibration use Method 1 and apply the threshol d 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 sh eet on page 9, mark the inspection results with dimensions on the rudder su rface and document by a photo. Send the report immediately to Airbus to get further ins tructions.

- If no debonding was detected by the above inspectio ns proceed with the Vacuum Loss Inspection.  For Vacuum Loss Inspection:

- Prepare the surface (Position the adhesive foil, ma rk the grid of holes for inspection as per sketch).

- Drill the inspection holes with diameter 1,5 mm thr ough 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 D 55RP0826329 (General Procedure to detect damage in Honeycomb Core Sandwi ch Structures by applying vacuum).

- In case of indications perform damage size assessme nt in width direction as per instructions on page 7.



### - Document the inspection results using the report sh eet on page 9. In case of findings mark the inspection results wit h dimensions on the rudder surface and document by a photo. When repairs with deviating dimensions as those pre sented by the inspection drawings or additional repairs performed by the operator are fo und 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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. 0 8-052) or self-adhesive patches ASNA2879A040 (which can become painted). This temporary repair has to be replaced by the per manent 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 Chapt er 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 im mediately 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 op erations again. This temporary repair has to be finished by the fin al surface restoration (continue with permanent repair step (6)) latest after 4500 FC (FH not relev ant). 

### Permanent inspection hole repair: (1) Prepare and dry the repair area (Refer to Chapt er 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 im mediately a piece of sticky tape on the repair area. (5) Cure the adhesive for 12h at RT. If RT is below18°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 (Mate rial No. 11-003 or 11-004 and refer to Chapter 51-77-11, Paragraph 4.E.). (10) Restore the surface protection (Refer to Chapt er 51-75-12). A ll references as per A320 SRM R e vision 01 AUG 2008. Page:

Copyright Airbus S.A.S. 2009. All rights reserved. This document contains Airbus S.A.S. (Societe par A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 7 of 20 A/C: MSN: 0533 A320-214-008



### 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 requiredfurther 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 ski n thickness see page 10 to 12. Inspect the external surface as defined on page 1 b y the methods:

 Mark and clean the inspection Area (with Solvent Ge neral Purpose (Mat No. 11-026 and lint free Cotton Cloth (Mat. No. 19-003) ).  Perform Tap Test or Woodpecker as per A320 NTM 51-1 0-03 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 X 51RP0828659 (General Procedure to Inspect Honeycomb Structures with ELCH ). Apply a test grid of 50mm and maintain a distance f rom any edge or screw of 75mm. For calibration use Method 1 and apply the threshol d 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 assessmen t.  Document the inspection results using the report sh eet on page 9. In case of findings mark the inspection results wit h dimensions on the rudder surface and document by a photo. When repairs with deviating dimensions as those pre sented by the inspection drawings or additional repairs performed by the ope rator are found these have to be included in the damage report with relevant dimensi ons. Close up: Clean the inspection Area (with Solvent General Pur pose (Mat No. 11-026 and lint free Cotton Cloth (Mat. No. 19-003)) from any remnants o f 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 indi cation and to confirm the damage (Refer to NTM Para 8 “Acceptance Criteria”).

 Boroscope inspection as per Airbus Instruction D55R P0828599 (General visual boroscop inspection for internal honeycomb core san dwich structures).  X-Ray inspection as per A320 NTM 51-10-10 Part 2 (only if available on customer side and requested b y Airbus NDT specialist) Page:

Copyright Airbus S.A.S. 2009. All rights reserved. This document contains Airbus S.A.S. (Societe par A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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 are a:

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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 10 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 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 12 of 20 A/C: MSN: 0533 A320-214-008



### 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

I ssue: B Date: 25 Feb 2009 13 of 20 A/C: MSN: 0533 A320-214-008 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 15 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

I ssue: B Date: 25 Feb 2009 16 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

I ssue: B Date: 25 Feb 2009 17 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 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 A ctions Simplifiee) proprietary information and shal l at all times remain the property of Airbus S.A.S.

. No intellectual property right or license is grante d by Airbus S.A.S. in connection with any informati on contained in it. It shall be treated as confiden tial, shall not be disclosed in whole or in part to any third party and shall not be duplicated in a ny manner, without Airbus S.A.S. prior written cons ent. This Technical Disposition (TD) only covers de sign aspects and excludes workmanship aspects. It has been prepared for a spe cific aircraft or components, based on the original Airbus Type Certificate, and solely on the basis o f 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

I ssue: B Date: 25 Feb 2009 19 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

I ssue: B Date: 25 Feb 2009 20 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.