ALERT OPERATORS TRANSMI SSI ON - ALERT OPERATORS TRANSMI SSI ON

SUBJECT: ATA 27 - Wing Tip Brake (WTB) loss of braking function OUR REF.: A27L001 - 12 rev 01 dated 27 April 2012. OUR PREVI OUS REF.: A27L 001 - 12 dated 26 April 2012. 0. REASON FOR REVISI ON 1) This revision has been sent to an enlarged distribution list as the first issue did not reach all affected operators; 2) Chapter 7 has been modified to add acknowledgement instruction. The revised paragraphs are indicated b y: **BEG.REV** and **END.RE V**. 1. AIRCRAFT AFFECTED All A330 - 200/ - 200F/ - 300 and A340 - 200/ - 300/ - 500/ - 600 in - service aircraft fitted with Wing Tip Brake (WTB) PN 1007A0000 - 03, PN 1007A0000 - 04 or PN 1007A0000 - 05. 2. REFERENCED DOCUMENTATION 2.1 Appendix Appendix A: Reporting Sh eet reference RS - SEEL6 - 2012 - 735701 2.2 References

- Ref.1: Operator Information Telex (OIT) SE 999.0106/10 - "ATA 27 - Wing Tip Brakes - Loss Of Braking Function"

- Ref.2: All Operator Telex (AOT) A330 - 27A3174/A340 - 27A4172 - "ATA 27 - Wing Tip Brakes - Anticipated Check Of WTB/POB Braking Performance"

- Ref.3: Technical Follow - Up (TFU) 27.50.00.010 - "Wing Tip Brake - Lo ss of Braking Function"

- Ref.4. Aircraft Maintenance Manual (AMM) task 27 - 51 - 00 - 710 - 801 - "Flap - Operational Test of the Wing Tip Brake/Pressure - Off - Brake (POB)"

- Ref.5: AMM task 27 - 81 - 00 - 710 - 801 - "Slat - Operational Test of the WTB/POB"

- Ref.6: Maintenance Planning Document (MPD) revision April 01/2012 Task 275400 - 14 - 1 - "Operational Check of Flap WTB/POB performance" / Maintenance Review Board Report (MRBR) task 27.50.00/14- Ref.7: MPD revision April 01/2012 Task 278000 - 10 - 1 - "Operational Check of Slat

WTB/POB performance" / MRBR task 27.80.00/10

- Ref.8: Airbus Service Bulletin (SB) A330 - 27 - 3183 / A340 - 27 - 4179 - "Flight Controls - Replace Wing Tip Brake Standard A03 or A04 or A05 by Standard A06"

- Ref.9: AMM task 27 - 51 - 51 PB 401 - "Brake - Wing Tip - Removal/Installation"

- Ref.10: AMM task 27 - 81 - 51 PB 401 - "Brake - Wing Tip - Removal/Installation"

- Ref.11: Airbus SB A330 - 27 - 3189/A340 - 27 - 4184 - "Flight Controls - Replace Wing Tip Brake Standard A06 By

Standard B01"

- Ref.12: Illustrated Parts Catalog (IPC) - figure 27 - 51 - 51/ figure 27 - 81 - 51 - "Brake - Wing Tip" 3. REASON This AOT supersedes AOT Ref.2, which requested an anticipated one - time application of the operational test of Wing Tip Brake (WTB) Pressure - Off - Brake (POB) on the slat and flap systems. Due to the findings from Ref.2 AOT, the present AOT requests a repetitive application of that operational test at a shorter interval tha n Ref.6 & 7 in order to ensure a reliable operation of the flap and slat WTB until a reliable PN is installed at all four WTB positions. 3.1 FACTS While performing the Ref.4 and Ref.5 tasks called by MPD/MRBR Ref.6 and Ref.7, an operator identified that the four WTB required replacement after failing the test. Strip examinations in shop confirmed that the four WTB had lost their braking capability due to brake plates being heavily worn out. The four affected WTB were PN 1007A0000 - 05. 3.2 CONSEQUENCES WTB are designed to stop and hold the mechanical transmission of slats and flaps in some specific failure cases. In such events, the Slat Flap Control Computers (SFCC) de - energize their WTB solenoids. This cuts the hydraulic pressure off, leading to brak es application. Loss of the WTB braking function can result in the inability of the flap or slat sy stem to be stopped and held in position, as required during operation in case of failure. 3.3 AIM The aim of this AOT is to ensure a reliable operation of the flap and slat WTB b y:

- Identifying potentially

defective units.

- Performing repetitive tests Ref.4 & Ref.5 at every 1000FH until replacement of all WTB PN 1007A0000 - 03, - 04 or - 05 by WTB PN 1007A0000 - 06 or 1007B0000 - 01.

- Replacing all WTB PN 1007A0000 - 03, - 04 or - 05 within 26 months from AOT receipt.3.4 INVESTIGAT ION

Analysis of the WTB returned from service has revealed that WTB fitted with brake plates supplied by

Jurid (WTB PN 1007A0000 - 03, - 04 or - 05) are subject to premature wear. Note: WTB fitted with Miba brake plates (PN 1007A0000 - 06 or 1007B0000 - 01) have not shown similar signs of premature wear. This has been confirmed b y a fleet sampling on high time WTB PN 1007A0000 - 06 and 1007B0000 - 01. This failure mode cannot be detected in normal operation, but can be detected during the Operational Test of the WTB/POB (AMM Ref.4 and Ref.5). 4. SHORT TERM ACTION 4.1 PLANNING AND MANPOWER 4.1.1 ACCOMPLI SHMENT TIMESCALE The following actions need to be performed, as per paragraph 4.2, on all affected aircraft:

- Within 30 days from receipt of this AOT, identify the aircraft equipped with WTB PN 1007A0000 - 03, - 04 or - 05.

- Within 90 days from receipt of this AOT, report results of the identification to Airbus.

- Within 1000 FH since previous acco mplishment of MPD/MRBR tasks ref.6 and ref.7 or since first flight of the aircraft, as applicable, or within 30 days from receipt of this AOT, whichever occurs later o Do the operational test of the slat and flap WTB/POB in accordance with AMM tasks ref . 4 and ref. 5.

- Every 1000 FH, until replacement of all WTB PN 1007A0000 - 03, 1007A0000 - 04 and 1007A0000 - 05, repeat the operational test of the slat and flap WTB/POB in accordance with AMM tasks Ref. 4 and Ref. 5.

- In case of findings: o Replace the failed WTB before further flight. o Report findings to Airbus within 90 days.

- Within 26 months from AOT receipt, replace all WTB PN 1007A0000 - 03, 1007A0000 - 04 and 1007A0000 - 05. 4.1.2 MANPOWER The estimated time to perform AMM Ref.4 and Ref.5 is:

- 2 man - hours- 1 hour elapsed time

with an additional 4 man - hours in case a WTB requires replacement. 4.2 DESCRIPTION 4.2.1 IDENTIFICATION OF AFFECTED AIRCRAFT Within 30 days from receipt of this AOT: a) Identify

all aircraft fitted with at least one WTB PN 1007A0000 - 03, 1007A0000 - 04 or 1007A0000 - 05. The two following procedures are approved for the identification:

- Use the data from operators' approved records

- Read the data b y visual inspection on aircraft Within 90 days from receipt of this AOT: b) Report each aircraft configuration to Airbus through the reporting sheet in Annex A. 4.2.2 REPETITIVE OPERATIONNAL TEST OF WTB/POB PERFORMANCE On all affected aircraft, the following procedure shall be applied: a) If onl y WTB PN 1007A0000 - 06 or 1007 B0000 - 01 is installed on the aircraft (flap and slat systems), no further action is required b y this AOT. b) If at least one WTB PN 1007A0000 - 03, 1007A0000 - 04 or 1007A0000 - 05 is installed on the flap s ys tem (FIN 5060CV or 5138CV), within 1000 FH since previous accomplishment of MPD/MRBR task Ref.6 or since first flight of the aircraft, as applicable, or within 30 days from receipt of this AOT, whichever occurs later; and thereafter at intervals not to exceed 1000 FH, do the Operational Test of the WTB/POB as per AMM Ref.4.

- If an operational test fails:

- BEFORE FURTHER FLIGHT, replace the faulty WTB b y a serviceable WTB unit in accordance with instructions of i) or ii) as follows: i) Installation of PN 1007A0000 - 06 or 1007B0000 - 01: o For pre - MOD 43 512 aircraft, install WTB PN 1007A0000 - 06 as per SB Ref.8 or WTB PN 1007B0000 - 01 as per SB Ref.11. o For post - MOD 43512 aircraft, replace the WTB through AMM Ref.9 to recover the original aircraft delivery

configuration. SB Ref.11 can be embodied to in stall WTB PN 1007B0000 - 01. ii) Installation of PN 1007A0000 - 03 or PN 1007A0000 - 04 or PN 1007A0000 - 05 as per AMM Ref. 9 is authorized on pre - MOD 43512 aircraft provided that the replacement flap WTB is successfull y tested on aircraft as per AMM Ref.4.

- Report findings to Airbus within 90 day s.c) If at least one WTB PN 1007A0000 - 03, 1007A0000 - 04 or PN 1007A0000 - 05 is installed

on the slat system (FIN 5120CW or 5060CW), within 1000 FH since previous accomplishment of MPD/MRBR task ref.7 or since first f light of the aircraft, as applicable, or within 30 days from receipt of this AOT, whichever occurs later; and thereafter at intervals not to exceed 1000 FH, do the Operational Test of the WTB/POB as per AMM Ref.5.

- If an operational test fails:

- BEFORE FURTHER FLIGHT, replace the faulty WTB b y a serviceable WTB unit in accordance with instructions of i) or ii) as follows: i) Installation of PN 1007A0000 - 06 or 1007B0000 - 01: o For pre - MOD 43512 aircraft, install WTB PN 1007A0000 - 06 as per SB Ref.8 or WTB PN 1007B0000 - 01 as per SB Ref.11. o For post - MOD 43512 aircraft, replace the WTB through AMM Ref.10 to recover the original aircraft delivery

configuration. SB Ref.11 can be embodied to install WTB PN 1007B0000 - 01. ii) Installation of PN 1007A0000 - 03 or PN 1007A0000 - 04 or PN 1007A0000 - 05 as per AMM Ref.10 is authorized on pre - MOD 43512 aircraft provided that the replacement slat WTB is successfull y tested on aircraft as per AMM Ref.5.

- Report the findings to Airbus within 90 day s. Note: A Servi ceable WTB unit is defined as a part having:

- P/N 1007A0000 - 06 (preferred P/N) or

- P/N 1007B0000 - 01 (preferred P/N) or

- Only on pre - MOD 43512 aircraft, P/N 1007A0000 - 03 or P/N 1007A0000 - 04 or P/N 1007A0000 - 05 which has been successfull y tested on aircra ft after its installation as per AMM Ref.4 or Ref.5 (P/N to be used exceptionally in case of spare shortage). 4.2.3 WTB REPLACEMENT Within 26 months from receipt of this AOT: Replace all remaining WTB PN 1007A0000 - 03, 1007A0000 - 04 or 1007A0000 - 05 by WTB PN 1007A0000 - 06, depending on aircraft configuration:

- For pre - MOD 43512 aircraft, install WTB PN 1007A0000 - 06 as per SB Ref.8.

- For post - MOD 43512 aircraft, replace the WTB through AMM Ref.9 or AMM Ref.10 to recover the original aircraft delivery conf iguration. Installation of a WTB PN 1007B0000 - 01 as per SB Ref.11 instead of a WTB PN 1007A0000 - 06 is an acceptable means to comply with this AOT, as these units are 2 - way interchangeable as per IPC Ref.12. Once all WTB PN 1007A0000 - 03, 1007A0000 - 04 or 1 007A0000 - 05 have been replaced on an aircraft b y PN 1007A0000 - 06 or PN 1007B0000 - 01:- The MPD/MRBR Ref.6 and Ref.7 interval is restored for the accomplishment of the

Operational Test of the WTB/POB.

- No further action is required. 4.3 SPARES AND TOOLIN G No specific tooling is required to perform the actions described in this AOT. Spare WTB units have been positioned in Singapore, Europe and the USA, in order to reduce delivery lead - time. Orders for spare WTB should be addressed to: GOODRICH AOG CONTACT: Worldwide: tel. +44/121.451.5904 Fax +44/121.451.6133 E - mail: 24 - 7@goodrich.com North America: tel. +1/800.735.7899 Due to the limited number of available spares, the following rules will apply for spares delivery : a) For paragraph 4.2.2, spares wil l be delivered upon request when a WTB is confirmed faulty during the test, b) For paragraph 4.2.3, Goodrich will organize a retrofit campaign of WTB PN 1007A0000 - 03, - 04 and - 05 , which Airbus will supervise. An Airbus Retrofit Information L etter (RIL) wil l cover this retrofit. 5. FOLLOW - UP PLAN Follow - up of this AOT will be ensured b y means of TFU Ref.3. 6. AOT APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.031. It is anticipated that this AOT will be rendered mandatory by the Airworthiness Authorities. 7. REPORTI

NG/ACKNOWLEDGEMENT BEG REV* Operators are requested to acknowledge receipt of this AOT within 48 hours after receipt to: BONNET Laétitia E - mail:laetitia.bonnet@airbus.com Fax number +33 ( 0)5 67 19 12 05 END REV*Questions about this AOT and inspection results with or without findings shall be sent to

Airbus Customer Services Engineering within 90 days after AOT application, to the attention of: HERVAGAULT, Cédric, SEEL 6 Phone: +33 (0)5 6 2 11 75 29 Fax number +33 (0)5 67 19 12 05 E - mail: cedric.hervagault@airbus.com Best Regards, Jean - Luc MOUYSSET Philippe GOURDON VI CE PRESIDENT ENGINEERING SUPPORT VI CE PRESIDENT A330/A340 PROGRAMME CUSTOMER SERVI CES CU STOMER SERVI CES