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@A318/A319/A320/A321SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51
MANDATORY MANDATORY MANDATORYATA SYSTEM: 27
TITLE: FLIGHT CONTROLS - ELAC SYSTEM - RESTORE ELAC2 AND THSMOTOR 1 POWER SUPPLY (SB ONLY)
MODIFICATION No.: 39998P11410 39999P11411
This page transmits Revision No.02 of Service Bulletin No.A320-27-1199
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
This Service Bulletin has been accomplished at Revision No. 01 on aircraft MSN 3480 to validate itscontent.
Compliance becomes Mandatory
CHANGES
SUMMARYREASON/DESCRIPTION/OPERATIONALCONSEQUENCES
REASON UPDATED R
GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED RMATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE
UPDATEDR
EFFECTIVITY OPERATOR LIST UPDATED RMANPOWER MANPOWER UPDATED RAPPENDICES APPENDICES UPDATED RPLANNING INFORMATIONEFFECTIVITY EFFECTIVITY RELATED INFORMATION
UPDATEDR
Material Effectivity MATERIAL EFFECTIVITY UPDATEDMATERIAL SET UPDATED
R
REASONHistory HISTORY UPDATED R
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on themass, balance, structural strength, reliability, operational characteristics affecting theairworthiness of the product. All other changes are major changes.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
This Service Bulletin is published for all operators of A320 aircraft.
Under emergency electrical configuration (electrical power achieved by emergency electrical generatorCSMG (Constant Speed Motor Generator) driven by the RAT (Ram Air Turbine)), only ELAC1 andSEC1 are operative among the Flight Control computer.
In the original design of the Single Aisle (SA) A/C family, the RAT was not efficient enough with NLGextended to provide Blue hydraulic pressure and to energize the emergency electrical generator CSMG.
In order to provide better aircraft controllability and redundancy, a set of wiring and relays was installedto energize the ELAC2 and THS Motor 1 through the battery under emergency electrical configurationas soon the NLG is extended. Taking benefit of the enhanced RAT installed later on SA aircraft,the ELAC2 and THS Motor 1 supply logic has been simplified. Logic has been simplified and isno more activated when NLG is extended. This has been introduced by Mod. No. 38310P10576(FLIGHT CONTROLS -ELAC SYSTEM - IMPROVE ELECTRICAL INSTALLATION OF ELAC2 ANDTHS MOTOR 1 POWER SUPPLY) in 2007. This modification aimed at removing temporized relays44CE, 46CE and 64CE (which embed electronic devices that make them more fragile), thus improvingthe ELAC2 and THS Motor 1 supply logic robustness.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
However, it has been identified that this modification affects the roll controllability in case of emergencyelectrical configuration combined with a dual G +Y hydraulic loss. In this extremely remote situation, onA320 aircraft, the roll control would be only provided by the left aileron with landing gear extended.
This Service Bulletin recommends to restore the aircraft configuration before the application of the Mod.No. 38310P10576.
This modification will permit, in case of an emergency electrical configuration combined with a dual G+Y hydraulic loss arises on the A320 aircraft, to restore the availability of the right aileron upon landinggear extension.
Accomplishment of this Service Bulletin implies some changes in the procedure given in AMM Task27-96-00-710-018 that is called as per MPD 27-90-00 (400FH or 80DY). Until the AMM is accordinglyupdated (after the SB Reporting Sheet receipt and AMM update processing), Airbus ask operatorsto use the testing procedure embedded in this Service Bulletin at SUBTASK 271199-710-003 001Operational test of the Logics that activate the ELAC 1 and 2 and SEC 1 STBY PWR SPLY .
GENERAL EVALUATION
EVALUATION TABLECOMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO
POTENTIAL AD YES A/C OPERATION AFFECTED NORELIABILITY AFFECTED NO PAX COMFORT AFFECTED NOCOST SAVING NO ETOPS AFFECTED NOSTRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO
NOTE (1): Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLEMATERIAL SET QTY PER
A/CPRICE PERA/C (USD)
MAIN PARTS
Kit 271199A01R01 1 3,370.00 Bundle, relays
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
62X AAR ABY ADH AEE AFL AFR AIJ AVA AXM AZA BAW BHPCCA CEB CES CSC CSZ DKH EIN FFT IGO JBU JST KNE KZRLAN LBT LTU MDL PAL RNV SBI TAI TAM VLG VRD WAU WZZ
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU NoneOEB NoneAOT NoneSIL None
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEXFRANCETel : (33) 5 61 93 33 33Telex : AIRBU 530526FFax : (33) 5 61 93 42 51
MANDATORY MANDATORY MANDATORYATA SYSTEM: 27
TITLE: FLIGHT CONTROLS - ELAC SYSTEM - RESTORE ELAC2 AND THSMOTOR 1 POWER SUPPLY (SB ONLY)
MODIFICATION No.: 39998P11410 39999P11411
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain theproperty of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection withany information contained in it. It is delivered on the express condition that said document and theinformation contained in it shall be treated as confidential, shall not be used for any purpose other thanthat for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shallnot be duplicated in any manner (except for the purposes of performing the tasks described hereunderand provided that any recipient of such document shall comply with the conditions herein), withoutAIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE: This modification is applicable by Service Bulletin only.
NOTE: This Service Bulletin has been validated on A320 aircraft MSN3480.
NOTE: This Service Bulletin is only applicable on Aircraft on which Mod.No. 38310P10576 (FLIGHT CONTROLS - ELAC SYSTEM IMPROVEELECTRICAL INSTALLATION OF ELAC2 AND THS MOTOR 1 POWERSUPPLY) is embodied.
The Operator/MSN relationship is provided for information only and is correct at the timeof issue in accordance with the information available to AIRBUS. Any future changesresulting from transfer of an aircraft from one operator to another will not be reflected inthis list unless the Service Bulletin is revised for another reason.
**CONF 001Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as astandard configuration.
(6) Material Effectivity
MATERIAL QTY PER A/C SEE NOTESKit 271199A01R01 1
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
This Service Bulletin is published for all operators of A320 aircraft.
Under emergency electrical configuration (electrical power achieved by emergencyelectrical generator CSMG (Constant Speed Motor Generator) driven by the RAT (RamAir Turbine)), only ELAC1 and SEC1 are operative among the Flight Control computer.
In the original design of the Single Aisle (SA) A/C family, the RAT was not efficientenough with NLG extended to provide Blue hydraulic pressure and to energize theemergency electrical generator CSMG.
In order to provide better aircraft controllability and redundancy, a set of wiring andrelays was installed to energize the ELAC2 and THS Motor 1 through the batteryunder emergency electrical configuration as soon the NLG is extended. Taking benefitof the enhanced RAT installed later on SA aircraft, the ELAC2 and THS Motor 1supply logic has been simplified. Logic has been simplified and is no more activatedwhen NLG is extended. This has been introduced by Mod. No. 38310P10576 (FLIGHTCONTROLS -ELAC SYSTEM - IMPROVE ELECTRICAL INSTALLATION OF ELAC2AND THS MOTOR 1 POWER SUPPLY) in 2007. This modification aimed at removingtemporized relays 44CE, 46CE and 64CE (which embed electronic devices that makethem more fragile), thus improving the ELAC2 and THS Motor 1 supply logic robustness.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
However, it has been identified that this modification affects the roll controllability in caseof emergency electrical configuration combined with a dual G +Y hydraulic loss. In thisextremely remote situation, on A320 aircraft, the roll control would be only provided bythe left aileron with landing gear extended.
(2) Objective/Action
This Service Bulletin recommends to restore the aircraft configuration before theapplication of the Mod. No. 38310P10576.
(3) Advantages
This modification will permit, in case of an emergency electrical configuration combinedwith a dual G +Y hydraulic loss arises on the A320 aircraft, to restore the availability ofthe right aileron upon landing gear extension.
(4) Operational/Maintenance Consequences
Accomplishment of this Service Bulletin implies some changes in the procedure given inAMM Task 27-96-00-710-018 that is called as per MPD 27-90-00 (400FH or 80DY). Untilthe AMM is accordingly updated (after the SB Reporting Sheet receipt and AMM updateprocessing), Airbus ask operators to use the testing procedure embedded in this ServiceBulletin at SUBTASK 271199-710-003 001 Operational test of the Logics that activatethe ELAC 1 and 2 and SEC 1 STBY PWR SPLY .
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 271199-831-801-001: Modification
(1) Modify the wiring in Electronics Racks 80VU and 188VU
(2) Modify the Wiring in Electronics Racks 83VU and 84VU
(3) Modify the wiring in Electronics Rack 93VU
(4) Modify the wiring in zone 120
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin has been rendered mandatory by the issue of anAirworthiness Directive (AD) published by the European Aviation Safety Agency (EASA).The AD must be used as the reference document for the mandatory accomplishmenttimescale.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
Approved under EASA Design Organisation Approval No. EASA 21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not ofAIRBUS origin, and which affects the content of this Service Bulletin, the operator isresponsible for obtaining approval by its airworthiness authority for any adaptation necessarybefore incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost todo the work. These estimates assume that the work will be done by experienced personnel,and may need to be revised upwards to suit operator’s circumstances. The estimates do notinclude the time to prepare, plan or inspect the work. Manufacture and procurement of partsand tools, drying times for paints, sealants, etc., and general administration work are also notincluded.
Modify the wiring in Electronics Racks 80VU and188VU
24.00
Modify the Wiring in Electronics Racks 83VU and84VU
7.00
Modify the wiring in Electronics Rack 93VU 5.00
Modify the wiring in zone 120 12.00
Tests 4.00Close-Up 2.00
TOTAL MANHOURS 56.00ELAPSED TIME (HOURS) 37.00
NOTE: For details of elapsed time assumptions, Refer to Appendix 01
H. WEIGHT AND BALANCE
The weight and balance estimates given in this Service Bulletin are based on theManufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition ofMEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.
Manufacturers Empty Weight +0.308 KG (+0.6790 LB)Effect on Balance +2.883 KGM (+20.852 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
Kit 271199A01R01 Customers with aircraft shown in theeffectivity of this Service Bulletin should senda purchase order to AIRBUS. Quote thenumber of this Service Bulletin. The addressis:AIRBUS Material, Logistics and SuppliersWeg beim Jaeger 150 D22335 HamburgGermanyFor ordering by internet:http://spares.airbus.comFor ordering modification kits by fax: +49 4050 76 25 90For ordering of single spares by fax: +49 4050 76 40 13
(2) Price and Availability
Kit 271199A01R01Cost 3,370.00 USD
Availability 90 calendar days from receipt of order
The Kit availability given above is the standard lead time from the date of your purchaseorder. If you require Kits before this time, please include a retrofit planning schedule withyour order so that we can try to comply with your requirements.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will provide the material at no charge for orders placed before Dec. 31st 2011.AIRBUS will also credit the manhours indicated in this Service Bulletin at the operator’sagreed in-house warranty labor rate for claims received not later than 90 days aftercompletion of the last affected aircraft of your fleet.
C. LIST OF COMPONENTS
Kit 271199A01R01
ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEENOTES
1 MS21042L04 9 NUT2 E0219ASXXV 3 BASE (1) (2)
3 E0217XXV0250A 3 RELAY (2)
D9000095024895 1 BundleD9100095008795 1 Placard
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
ITEM NEW PART N˚ QTY (UM) KEYWORD ITEM OLD PART N˚ INT SEENOTES
NSA935401-03 150 TIENSA935401-10 125 TIE
NOTE: If you find part numbers of hardware components in the related kit(s) whichyou cannot identify in the LIST OF COMPONENTS of this Service Bulletin,refer to Standards Manual (SM). The SM will give you the correct part numberto part number relationship.
NOTE (1): PN E0219ASXXV will be supplied through PN E0219AS.
NOTE (2): For the polarization, refer to ESPM 20-46-50.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
None
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONSINCLUDED IN THE REFERENCED PROCEDURES.
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEPELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLYAND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCEWORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DOTHIS:
PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; ASNECESSARY ON WIRING AND COMPONENTS.
REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHERCONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATIONAND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
Task Associated Data
Zone120 121 125 127 128From 128 to 127From 131 to 132
NOTE: For the Circuit Breakers location, refer to the Circuit Breaker DataTable (Refer to AMM 24-50-00, Page Block 001).
PANEL DESIGNATION FIN LOCATION SEENOTES
49VU ANTI ICE/PROBES/AOA/1 4DA1 04 D49VU ANTI ICE/PROBES/PHC/1 2DA1 03 D49VU ANTI ICE/PROBES/PITOT/1 3DA1 02 D122VU ANTI ICE/WINDOWS/R 4DG2 14 W122VU ANTI ICE/WHC/2 5DG2 13 W122VU ANTI ICE/WINDOWS/L 4DG1 14 X122VU ANTI ICE/WHC/1 5DG1 13 X122VU ANTI ICE/PROBES/PHC/3 2DA3 16 Y122VU ANTI ICE/PROBES/2/TAT 1DA2 15 Y122VU ANTI ICE/PROBES/2/PITOT 3DA2 14 Y122VU ANTI ICE/PROBES/2/AOA 4DA2 13 Y122VU ANTI ICE/PROBES/2/PHC 2DA2 12 Y122VU ANTI ICE/PROBES/2/STATIC 5DA2 11 Y122VU ANTI ICE/PROBES/3/PITOT 3DA3 16 Z122VU ANTI ICE/PROBES/3/AOA 4DA3 15 Z122VU ANTI ICE/PROBES/3/STATIC 5DA3 14 Z122VU ANTI ICE/PROBES/1/STATIC 5DA1 13 Z122VU ANTI ICE/PROBES/1/TAT 1DA1 12 Z
(7) Subtask 271199-710-003-001 - Operational test of the Logics that activate theELAC 1 and 2 and SEC 1 STBY PWR SPLY
ACTION RESULT5. On the CAPT and F/O side, onthe side sticks:
- move at the same time the twosticks around their axis.
You can heard an aural announcement: DUAL INPUTOn the glareshield panels 130VU and 131VU, on the SIDESTICK PRIORITY CAPT and the SIDE STICK PRIORITY F/Oannunciators:
- the green CAPT and F/O legends flash at the same time.
6. At the same time:
- on the CAPT side, push and holdfor less than 30 seconds thetakeover and priority pushbuttonswitch
- on the F/O side, move the sidestick to the left, then release it tothe neutral position.
You can heard an aural warning.On the F/O side, on the glareshield panel 130VU:
- the red arrow of the SIDE STICK PRIORITY F/O annunciatorcomes on.
On the CAPT side, on the glareshield panel 131VU:
- the green CAPT legend comes on.
7. On the CAPT side:
- release the takeover and prioritypushbutton switch.
8. At the same time:
- on the F/O side, push and holdfor less than 30 seconds thetakeover and priority pushbuttonswitch
- on the CAPT side, move the sidestick to the left, then release it tothe neutral position.
You can heard an aural warning.On the CAPT side, on the glareshield panel 131VU:
- the red arrow of the SIDE STICK PRIORITY CAPT annunciatorcomes on.
On the F/O side, on the glareshield panel 130VU:
- the green F/O legend comes on.
9. On the F/O side:
- release the takeover and prioritypushbutton switch.
10. On the CAPT side:
- move the side stick to the leftuntil it touches the stop.
On the lower ECAM display unit:
- the L/AIL index moves to the upper stop,
- the R/AIL index moves to the lower stop,
- the spoiler surfaces are retracted.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
- give the orders below one afterthe other and keep the side stickin each position for 3 seconds:
. full nose up
. full nose down
. full right turn
. full left turn
- move the side stick back to theneutral position.
On the lower ECAM display unit, on the F/CTL page:
- the indexes of the elevators and spoilers 2 and 5 move inrelation to the side stick orders.
16. On the F/O side:
- give the orders below one afterthe other and keep the side stickin each position for 3 seconds:
. full nose up
. full nose down
. full right turn
. full left turn
- move the side stick back to theneutral position.
On the lower ECAM display unit, on the F/CTL page:
- the indexes of the elevators and spoilers 2 and 5 move inrelation to the side stick orders.
17. Set the pitch-trim control wheelto the 10 UP position.
18. On the overhead panel 24VU:
- release and push again the SEC2 pushbutton switch.
After approximately five seconds, the pitch-trim control wheelgoes back automatically to the 0 position.On the lower ECAM display unit, on the F/CTL page:
- the PITCH TRIM indicator shows 0 DEG plus or minus 0.3.
19. Set the pitch-trim control wheelto the 3 DN position.
20. On the overhead panel 24VU:
- release and push again the SEC2 pushbutton switch.
After approximately five seconds, the pitch-trim control wheelgoes back automatically to the 0 position.On the lower ECAM display unit, on the F/CTL page:
- the PITCH TRIM indicator shows 0 DEG plus or minus 0.3.
21. On the overhead panel 23VU:
- push the ELAC 1 and SEC 1pushbutton switches.
On the overhead panel 23VU:
- the OFF legends of the ELAC 1 and SEC 1 pushbuttonswitches go off.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
- give the orders below one afterthe other and keep the side stickin each position for 3 seconds:
. full nose up
. full nose down
. full right turn
. full left turn
- move the side stick back to theneutral position.
On the lower ECAM display unit, on the F/CTL page:
- the indexes of the elevators and spoilers 2, 3 and 4 move inrelation to the side stick orders.
30. Set the pitch-trim control wheelto the 10 UP position.
31. On the overhead panel 23VU:
- release and push again the SEC1 pushbutton switch.
After approximately five seconds, the pitch-trim control wheelgoes back automatically to the 0 position.On the lower ECAM display unit, on the F/CTL page:
- the PITCH TRIM indicator shows 0 DEG plus or minus 0.3.
32. Set the pitch-trim control wheelto the 3 DN position.
33. On the overhead panel 23VU:
- release and push again the SEC1 pushbutton switch.
After approximately five seconds, the pitch-trim control wheelgoes back automatically to the 0 position.On the lower ECAM display unit, on the F/CTL page:
- the PITCH TRIM indicator shows 0 DEG plus or minus 0.3.
34. Open the CB 15CE1 and15CE2.
On the upper ECAM display unit:
- the F/CTL ELAC 1 FAULT and F/CTL ELAC 2 FAULTmessages come into view.
35. On the CAPT or F/O side:
- give the orders below one afterthe other:
. full nose up
. full nose down
. full right turn
. full left turn
- move the side stick back to theneutral position.
On the lower ECAM display unit, on the F/CTL page:
- the indexes of the elevators and spoilers 2, 3 and 4 move inrelation to the side stick orders.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
NOTE: For the Circuit Breaker location, refer to the Circuit Breaker Data Table(Refer to AMM 24-50-00, Page Block 001).
(a) Remove the safety clips and tags and close these circuit breakers:
PANEL DESIGNATION FIN LOCATION SEENOTES
122VU ANTI ICE/PROBES/1/TAT 1DA1 12 Z122VU ANTI ICE/PROBES/2/TAT 1DA2 15 Y49VU ANTI ICE/PROBES/PHC/1 2DA1 03 D122VU ANTI ICE/PROBES/2/PHC 2DA2 12 Y122VU ANTI ICE/PROBES/PHC/3 2DA3 16 Y49VU ANTI ICE/PROBES/PITOT/1 3DA1 02 D122VU ANTI ICE/PROBES/2/PITOT 3DA2 14 Y122VU ANTI ICE/PROBES/3/PITOT 3DA3 16 Z
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
122VU ANTI ICE/PROBES/2/AOA 4DA2 13 Y122VU ANTI ICE/PROBES/3/AOA 4DA3 15 Z122VU ANTI ICE/WINDOWS/L 4DG1 14 X122VU ANTI ICE/WINDOWS/R 4DG2 14 W122VU ANTI ICE/PROBES/2/STATIC 5DA2 11 Y122VU ANTI ICE/PROBES/3/STATIC 5DA3 14 Z122VU ANTI ICE/WHC/1 5DG1 13 X122VU ANTI ICE/WHC/2 5DG2 13 W49VU ANTI ICE/PROBES/AOA/1 4DA1 04 D122VU ANTI ICE/PROBES/1/STATIC 5DA1 13 Z
TITLE: FLIGHT CONTROLS - ELAC SYSTEM - RESTORE ELAC2 AND THSMOTOR 1 POWER SUPPLY (SB ONLY)
MODIFICATION No.: 39998P11410 39999P11411
Please complete the appropriate item (A or B):A - SB WILL BE embodied YES/NO (if NO please comment)If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) ofembodiment:
B - SB HAS BEEN embodied on aircraft:
Operator comments:
From Airline:Name/Title:Signature: Date:
If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior tonext normal revision or prior to SB embodiment, please indicate required service(s):Either: Modification Operational Impact (MOI), if available YES/NOOr : Intermediate revision YES/NO
Important Information: This SB will only be incorporated in your maintenance and operationaldocumentation if this sheet is returned to Airbus and signed by a duly authorised representative. Withthe next feasible revision, this will result in
- Updating of maintenance documentation to show pre and post SB data.- Updating of maintenance and operational documentation to show post SB data after embodiment.
If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automaticallyinclude them in the manual revisions. Refer to SIL 00-037 for detailed information.
Please return this completed sheet to:
AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE
Attn: SDC32 Technical Data and Documentation ServicesFAX: (+33) 5 61 93 28 06e-mail: [email protected] via your Resident Customer Support Office.
Alternatively, SB lists via letters or fax are also accepted.
DATE: Nov 09/09 SERVICE BULLETIN No.: A320-27-1199
Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported datathat you provide us will be used to analyse areas of difficulties and to take corrective action to furtherimprove the quality of our Service Bulletins.We thank you for the time you have taken in completing this form.
(Please rate on a scale of 1 to 4, with 4 being the highest score)
- Quality rating of this SB 4 3 2 1
- Quality rating of the Accomplishment Instructions 4 3 2 1
- Quality rating of the Illustrations 4 3 2 1
- Is this SB easy to understand ? Y / N
If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give ashort description of the issue.
Planning Material Instructions
X Effectivity X Kit content X Preparation
X Reason X List of Materials Operator Supplied X Mod/Inspection
X Manpower X Industry support X Test
X References X Re-identification X Close-Up
X Publication X Tooling X Illustrations
Comments:
Operator: Date:
Name/Title:
Please return this form to:
AIRBUSCUSTOMER SERVICES DIRECTORATE1 Rond Point Maurice Bellonte31707 BLAGNAC CEDEX FRANCE