file:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] ALL OPERATORS TELEX - ALL OPERATORS TELEX

SUBJECT: ATA 27 - ELEVATOR SERVOCONTROLS - DAMPING POSITION INSPECTION AND REPLACEMENT OF THE SOLENOID VALVES O-RING SEALS OUR REF: AOT A330-27A3129 REV 01 - DATED 16 JULY 2004 OUR PREVIOUS REF.: AOT A330-27A3129 DATED 24 JUNE 2004

0. REASON FOR REVISION THE AIM OF THIS REVISION IS TO INFORM OPERATORS THAT THE INFORMATION IN IPC 27-34-51 FIG 1 IS NOT CORRECT REGARDING THE PART NUMBER OF THE SEALS ITEM 130, 140 AND 150 TO BE INSTALLED ON ELEVATOR SERVOCONTROLS PN SC4800-2/-4/-7/-8. IPC 24-34-51 FIG 1 CORRECT PART NUMBERS FOR ITEMS 130, 140 AND 150 ARE: - ITEM 130: NAS1611-011 - ITEM 140: NAS1611-012 - ITEM 150: NAS1611-013 SEALS WITH PN MS28775-XXX ARE NOT QUALIFIED FOR HYDRAULIC SYSTEMS APPLICATIONS. THEIR INSTALLATION CAN LEAD TO THEIR COMPLETE DEGRADATION IN A SHORT-TIME AND THEREFORE, MUST NOT BE USED TO REPLACE THE SEALS IN SOLENOID VALVES. FAILURE OF THE SEAL MAY LEAD TO HYDRAULIC SYSTEM LOSS. 2 SYSTEMS ARE POTENTIALLY AFFECTED. AS A CONSEQUENCE, AIRBUS REQUESTS TO REMOVE THOSE SEALS IMMEDIATELY. THIS AOT WILL BE FOLLOWED BY A TELEGRAPHIC CN (CONSIGNE DE NAVIGABILITE). NOTE 1: SEAL REFERENCES FOR SERVOCONTROLS PN SC4800-7A/-9/- 10/-11 INDICATED IN IPC 27-34-51 FIG 1A ARE CORRECT. NOTE 2: AN IPC TEMPORARY REVISION WILL BE ISSUED WITHIN 3 WEEKS. THE REVISED PARAGRAPHS ARE INDICATED BY THE: **REV** MARKING.

1. AIRCRAFT AFFECTED ALL A330-200 IN-SERVICE AIRCRAFT.file:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] 2. REFERENCED DOCUMENTS **REV** REF.1: IPC 27-34-51-1/-1A ITEMS 80, 120, 130, 140, 150 / SOLENOID VALVE AND O-RING SEALS CAUTION : IPC 24-34-51 FIG 1 CORRECT PART NUMBERS FOR ITEMS 130, 140 AND 150 ARE: ITEM 130: NAS1611-011 ITEM 140: NAS1611-012 ITEM 150: NAS1611-013 - REF.2: OIT REF. 999.0066/04/BB REV 01 DATED 11 JUN 2004/ ELEVATOR SERVOCONTROL - ELEVATOR BLOCKED IN FULL PITCH DOWN POSITION DUE TO A DUAL FAILURE - REF.3: AMM 27-34-51-000-804 / REMOVAL OF THE ELEVATOR SERVOCONTROL UNIT SOLENOID VALVES - REF.4: AMM 27-34-51-400-804 / INSTALLATION OF THE ELEVATOR SERVOCONTROL UNIT SOLENOID VALVES - REF.5: AMM 27-34-00-710-802 / OPERATIONAL TEST OF THE ELEVATOR AND HYDRAULIC ACTUATION - REF.6: AMM 27-96-00-710-803 / OPERATIONAL TEST OF THE FCPC'S AND FCSC'S STANDBY SERVO-LOOPS ON PITCH CONTROL - REF.7: TFU 27.34.00.010 / ELEVATOR SERVOCONTROL-UNDUE DAMPING MODE / JUNE 2004

3. REASON 3.1. FACTS ON 11TH OF JUNE 2004, OPERATORS INFORMATION TELEX (OIT/REF.2) WAS ISSUED TO INFORM OF AN EVENT CONCERNING AN ELEVATOR STUCK IN FULL PITCH DOWN POSITION, WHEN THE DAMPING SERVOCONTROL FAILED TO CHANGE TO ACTIVE MODE.

3.2. INVESTIGATIONS EACH ELEVATOR IS EQUIPPED WITH TWO SERVOCONTROLS HAVING THREE OPERATING MODES: ACTIVE MODE, DAMPING MODE AND CENTERING MODE. THE MODE SELECTION FROM ACTIVE TO DAMPING IS ACHIEVED BY A SELECTOR VALVE INSTALLED INSIDE EACH SERVOCONTROL. THIS SELECTOR VALVE IS CONTROLLED BY TWO IDENTICAL SOLENOID VALVES (PN: EVP504 / REF.1 ITEM 120) INSTALLED ON THE SERVOCONTROL. EACH SOLENOID VALVE IS SEALED BY O-RING SEALS (REF.1 ITEMS 80, 130, 140, 150).file:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] DURING THE ABOVE DESCRIBED EVENT, THE SERVOCONTROL WAS UNABLE TO CHANGE FROM DAMPING TO ACTIVE MODE. THIS IS CONSIDERED TO BE DUE TO AN INTERNAL LEAKAGE CAUSED BY A CUT/WORN O-RING SEAL (REF.1 ITEM 140) ON ONE SOLENOID VALVE. A SAMPLING INSPECTION OF THESE SEALS ON IN-SERVICE AIRCRAFT AND A REVIEW OF THE SHOP FINDING HISTORY AT GOODRICH HIGHLIGHTED SIMILAR WORN SEALS ON A330-200 ELEVATOR SERVOCONTROLS WITH MORE THAN 3000 FC ONLY. 3.3. CONSEQUENCES THE INTERNAL LEAKAGE THROUGH THE O-RING SEAL (REF.ITEM 140) CAN RESULT IN THE MODE SELECTOR VALVE FAILING TO MOVE TO THE ACTIVE POSITION. THIS FAILURE CANNOT BE DETECTED BY THE FLIGHT CONTROL PRIMARY COMPUTERS PRE-SB A340-27-4101/4102 AND A330-27-3097/3098 AND WILL NOT BE ANNOUNCED TO THE FLIGHT CREW (REFER TO OIT REF.2).

3.4. AIM AIRBUS REQUESTS THAT A330-200 OPERATORS PERFORM A ONE-TIME INSPECTION AND REPLACEMENT OF THE O-RING SEALS INSTALLED ON THE TWO SOLENOID VALVES OF THE DAMPING ELEVATOR SERVOCONTROLS (POSITIONS 3CS1 AND 3CS2). **REV** DUE TO IPC 27-34-51 FIG 1 DISCREPANCY, AIRBUS REQUESTS OPERATORS TO COMPLY WITH THE FOLLOWING REQUIREMENT: IF: THE INSPECTION HAS ALREADY BEEN PERFORMED AS PER AOT A330 27A3129 DATED 24 JUNE 2004, AND, THE SEALS WHICH HAVE BEEN INSTALLED ARE PN MS28775-XXX OR A PN THAT CANNOT BE IDENTIFIED, THEN: THE SEALS ARE TO BE REPLACED BEFORE NEXT FLIGHT BY REF.1 SEALS PN NAS1611-XXX AS DESCRIBED HEREUNDER: ITEM 130: NAS1611-011 ITEM 140: NAS1611-012 ITEM 150: NAS1611-013.

4. SHORT-TERM ACTION 4.1. PLANNING AND MANPOWER ON THE SERVOCONTROLS INSTALLED AT DAMPING POSITIONS 3CS1 AND 3CS2, THIS INSPECTION AND REPLACEMENT HAS TO BEfile:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] PERFORMED PRIOR TO: - ACCUMULATION OF 3000 FLIGHT CYCLES: . SINCE INSTALLATION OF THE SOLENOID VALVE ON THE SERVOCONTROL, OR . BY THE SERVOCONTROL SINCE NEW, IF THE INSTALLATION DATE OF THE SOLENOID VALVES CANNOT BE DEFINED, OR - WITHIN 700 FH FROM THE ISSUANCE DATE OF THIS AOT, WHICHEVER OCCURS LATER.

THE COMPLETE ACTIONS REPRESENT 10 MAN-HOURS AND 5 HOURS ELAPSED TIME (TWO MECHANICS ARE REQUIRED).

4.2. DESCRIPTION 4.2.1. REMOVAL OF THE SOLENOID VALVES ON EACH AFFECTED ELEVATOR SERVOCONTROL, REMOVE THE TWO SOLENOID VALVES AS PER AMM 27-34-51-000-804 (REF.3). 4.2.2. INSPECTION OF THE O-RING SEALS VISUALLY INSPECT THE O-RING SEALS (REF.1 ITEMS 80, 130, 140, 150) OF THE SOLENOID VALVES, AND RECORD THEIR CONDITION (OK, WORN, CUT, EXTRUDED). IF POSSIBLE, TAKE PICTURES OF ANY DAMAGED SEALS WHILE THEY ARE STILL ON THE SOLENOID VALVE. 4.2.3. REPLACEMENT OF THE O-RING SEALS AND INSTALLATION OF THE SOLENOID VALVE CAUTION: EXTRACT OF AMM 20-29-00: 'DO NOT USE POINTED, SHARP OR METAL TOOLS TO REMOVE/INSTALL THE O-RING SEALS. SHARP EDGES CAN CAUSE DAMAGE TO THE GROOVES OR SEAL CONTACT SURFACES. USE SPOON-TYPE REMOVAL TOOLS OR A WEDGE-TYPE REMOVAL TOOL WITH A HOOK TO REMOVE/INSTALL THE O-RING SEALS.' REPLACE ALL THE O-RING SEALS (REF.1 ITEMS 80, 130, 140, 150) BY NEW ONES AND RE-INSTALL THE SOLENOID VALVES, AS PER AMM 27-34-51-400-804 (REF.4). 4.2.4. OPERATIONAL TEST OF THE ELEVATORS PERFORM THE OPERATIONAL TEST OF THE ELEVATOR AND HYDRAULIC ACTUATION, AS PER AMM 27-34-00-710-802 (REF.5).file:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] PERFORM THE OPERATIONAL TEST OF THE FCPC'S AND FCSC'S STANDBY SERVO-LOOPS ON PITCH CONTROL, AS PER AMM 27-96-00- 710-803 (REF.6) 4.2.5. REPORT THE FINDINGS TO AIRBUS **REV** FOLLOWING DATA MUST BE REPORTED TO AIRBUS: - INSPECTED AIRCRAFT: MSN, FLIGHT HOURS(FH), FLIGHT CYCLES(FC); - FOR EACH INSPECTED SERVOCONTROL : PART NUMBER (PN), SERIAL NUMBER (SN), FH, FC, POSITION ON AIRCRAFT (3CS1, 3CS2); - FOR EACH INSPECTED SOLENOID VALVE: PN, SN, FH, FC, CONDITION (OK, WORN, CUT, EXTRUDED,.) OF EACH INSPECTED O- RING SEAL (REF.1 ITEMS 80, 130, 140, 150); - PICTURES OF THE DAMAGED SEALS, IF AVAILABLE.

4.3. MATERIAL-TOOLING FOR EACH INSPECTED SERVOCONTROL: **REV** IPC 27-34-51-1/-1A ITEM 80 - PN NAS1611-112 - QTY 02 IPC 27-34-51-1/-1A ITEM 130 - PN NAS1611-011 - QTY 02 IPC 27-34-51-1/-1A ITEM 140 - PN NAS1611-012 - QTY 02 IPC 27-34-51-1/-1A ITEM 150 - PN NAS1611-013 - QTY 02 CAUTION: SEALS WITH PN MS28775-XXX MUST NOT BE USED TO REPLACE THE SEALS IN SOLENOID VALVES. IN CASE OF SPARE UNAVAILABILITY, ORDERS FOR SPARE O-RING SEALS SHOULD BE ADRESSED TO: GOODRICH AOG CONTACT: WORLDWIDE: TEL. +44/121.451.5904 FAX +44/121.451.6133 E-MAIL: aog.helpdesk@goodrich.com NORTH AMERICA: TEL. +1.800.735.7899 NO SPECIFIC TOOLING IS REQUIRED FOR THIS INSPECTION.

5. FURTHER ACTION THE REASON FOR THE DAMAGED SEAL IS STILL UNDER INVESTIGATION.file:///O|/ANMTAD/114/114%20Common/Electronic%20Working%20Files/2010/2010_170/AOT_27A3129_01.txt [9/10/2013 12:45:25 PM] A MODIFICATION OF THE SOLENOID VALVE OF THE SERVOCONTROL (DIFFERENT SEALING) IS BEING CONSIDERED. FURTHER INFORMATION WILL BE PROVIDED THROUGH TECHNICAL FOLLOW-UP 27.34.00.010 (TFU REF.7) DATED JUNE 2004.

6. AOT APPROVAL THE TECHNICAL CONTENT OF THIS AOT HAS BEEN APPROVED UNDER THE AUTHORITY OF FRENCH DGAC DESIGN ORGANISATION APPROVAL NUMBER F-JA.02.

7. REPORTING/ACKNOWLEDGEMENT OPERATORS ARE REQUESTED TO ACKNOWLEDGE RECEIPT OF THIS AOT TO: MR R. LASCOURS, SEQ, SITA CODE TLSBT7X, FAX NUMBER +33/(0)5.61.30.00.79 WITHIN 48 HOURS AFTER RECEIPT. THIS ACKNOWLEDGMENT CAN BE MADE THROUGH THE AIRBUS RCSR OFFICE WHEN AVAILABLE. FINDINGS FROM INSPECTIONS ARE TO BE SENT TO: AIRBUS CUSTOMER SERVICES, ENGINEERING AND TECHNICAL SUPPORT, ATTENTION: MR. C. HERVAGAULT, SEE53, PHONE +33/(0)5.62.11.75.29, FAX +33/(0)5.61.93.44.25. E-MAIL: cedric.hervagault@airbus.com QUESTIONS ABOUT THE TECHNICAL CONTENT OF THE AOT ARE ALSO TO BE ADDRESSED TO MR. C. HERVAGAULT. BEST REGARDS, J. GROTHER A330/A340 PROGRAM VICE PRESIDENT ENGINEERING AND TECHNICAL SUPPORT CUSTOMER SERVICES DIRECTORATE

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