AD 2008-23-01 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes

Models named: A318, A319, A320, A321. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category, except those airplanes on which Airbus Modification 36734 or 37508 has been incorporated in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Certain Requirements of AD 2006-12-02 Part and Serial Number Inspection (f) Within 10 days after July 3, 2006 (the effective date of AD 2006-12-02), inspect to determine the part number (P/N) and serial number (S/N) of each fuel tank boost pump installed in the wing and center fuel tanks. A review of maintenance records may be performed instead of the required inspection if the P/N and S/N of the fuel boost pump can be conclusively determined from that review. Airbus Mandatory Service Bulletin A320-28-1152, dated May 5, 2006; or Revision 01, dated July 17, 2006; is acceptable for complying with the requirements of this paragraph. Revisions to Airplane Flight Manual (AFM)/Maintenance Program P/N 568-1-27202-005 With S/Ns 6137 and Subsequent (g) For airplanes equipped with one or more Eaton Aerospace Limited (formerly FR-HITEMP Limited) fuel boost pumps, having P/N 568-1-27202-005 with S/N 6137 and subsequent: Prior to further flight after accomplishing the inspection required by paragraph (f) of this AD, do the actions specified in paragraphs (g)(1) and (g)(2), as applicable of this AD, until the modifications/replacements required by paragraph (j) of this AD have been done. (1) Revise the Limitations section of the Airbus A318/319/320/321 AFM (“the AFM”) and the FAA-approved maintenance program by incorporating the following. This may be accomplished by inserting copies of this AD into the AFM and the maintenance program. “Apply the following procedure at each fuel loading: Refueling: Before refueling, all pumps must be turned off, in order to prevent them from automatically starting during the refueling process. Ground fuel transfer: For all aircraft, do not start a fuel transfer from any wing tank, if it contains less than 700 kg (1,550 lb) of fuel. For A318, A319, and A320 aircraft with a center tank, do not start a fuel transfer from the center tank, if it contains less than 2,000 kg (4,500 lb) of fuel. If a tank has less than the required quantity, it is necessary to add fuel (via a transfer from another tank or refueling) to enable a transfer to take place. Defueling: For all aircraft, when defueling the wings, do not start the fuel pumps if the fuel quantity in the inner tank (wing tank for A321) is below 700 kg (1,550 lb). If the fuel on the aircraft is not sufficient to achieve the required fuel distribution, then transfer fuel or refuel the aircraft to obtain the required fuel quantity in the wing tank. For A318, A319, and A320 aircraft with a center tank, when performing a pressure defuel of the center tank, make sure that the center tank contains at least 2,000 kg (4,500 lb) of fuel. If it has less than the required quantity, then transfer fuel to the center tank. Defuel the aircraft normally, and turn OFF the center tank pumps immediately after the FAULT light on the corresponding pushbutton-switch comes on.” (2) For all airplanes equipped with a center tank (Modification 20024) excluding A321 models, revise the Limitations section of the Airbus A318/319/320/321 AFM (“the AFM”) to incorporate the changes specified in Airbus Temporary Revision (TR) 4.03.00/28, dated May 4, 2006; or 4.03.00/28, Issue 02, dated May 18, 2007. This may be accomplished by inserting a copy of the TR into the AFM. When general revisions of the AFM have been issued that incorporate the revisions specified in the TR, the copy of the TR may be removed from the AFM, provided the relevant information in the general revision is identical to that in TR 4.03.00/28, dated May 4, 2006; or 4.03.00/28, Issue 02, dated May 18, 2007. New Requirements of This AD Part and Serial Number Inspection (h) For all airplanes: Within 10 days after the effective date of this AD, inspect to determine the type and part number of each fuel tank boost pump installed in the wing and center fuel tanks. A review of maintenance records may be performed instead of the required inspection if the part number and serial number of the fuel boost pump can be conclusively determined from that review. Airbus Mandatory Service Bulletin A320-28-1159, dated January 8, 2007, is acceptable for complying with the requirements of this paragraph. Revisions to AFM/Maintenance Program: P/Ns 568-1-27202-001 and -002; and P/N 568-1-27202-005 With S/Ns Below 6137 (i) For airplanes equipped with one or more Eaton Aerospace Limited (formerly FR- HITEMP Limited) fuel boost pumps, having P/N 568-1-27202-001 or 568-1-27202-002; or P/N 568-1-27202-005 with any serial number below 6137: Before further flight after accomplishing the inspection required by paragraph (h) of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable, until the modifications/replacements required by paragraph (j) of this AD have been done. Terminating Action (j) For airplanes equipped with one or more Eaton Aerospace Limited (formerly FR-HITEMP Limited) fuel boost pumps, having P/N 568-1-27202-001, -002, or -005: Within 5,000 flight hours or 18 months, whichever occurs first after the effective date of this AD, modify or replace affected fuel boost pumps in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A320-28-1159, dated January 8, 2007. Modification or replacement of all affected fuel tank boost pumps on an airplane terminates the requirements of this AD, and the limitations required by paragraph (g) of this AD may be removed from the Airbus A318/319/320/321 AFM and the maintenance program for that airplane. Note 1: For additional sources of service information for the fuel pump modification/replacement, Airbus Mandatory Service Bulletin A320-28-1159, dated January 8, 2007, refers to EATON Service Bulletin 8410-28-05, dated October 2, 2006. Credit for Actions Done Using Alternative Service Information (k) Modification of a fuel pump before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A320-28-1153, dated May 5, 2006, is acceptable for compliance with the corresponding requirements of paragraph (j) of this AD, for that pump only. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, ATTN: Tim Dulin, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) AMOCs approved previously in accordance with AD 2006-12-02 are approved as AMOCs for the corresponding provisions of this AD. Related Information (m) European Aviation Safety Agency airworthiness directive 2007-0218, dated August 10, 2007, also addresses the subject of this AD. Material Incorporated by Reference (n) You must use the service information specified in Table 1 of this AD to perform the actions that are required by this AD, as applicable, unless the AD specifies otherwise. Table 1—All Material Incorporated by Reference Service information Revision/issue level Date Airbus Mandatory Service Bulletin A320-28-1152, including Appendix 01 Original May 5, 2006. Airbus Mandatory Service Bulletin A320-28-1152, including Appendix 01 Revision 01 July 17, 2006. Airbus Mandatory Service Bulletin A320-28-1159 Original January 8, 2007. Airbus Temporary Revision 4.03.00/28 Original May 4, 2006. Airbus Temporary Revision 4.03.00/28 to the Airbus A318/319/320/321 Airplane Flight Manual Issue 02 May 18, 2007. (1) The Director of the Federal Register approved the incorporation by reference of the documents specified in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 2—New Material Incorporated by Reference Service information Revision/issue level Date Airbus Mandatory Service Bulletin A320-28-1152, including Appendix 01 Original May 5, 2006. Airbus Mandatory Service Bulletin A320-28-1152, including Appendix 01 Revision 01 July 17, 2006. Airbus Mandatory Service Bulletin A320-28-1159 Original January 8, 2007. Airbus Temporary Revision 4.03.00/28 to the Airbus A318/319/320/321 Airplane Flight Manual Issue 02 May 18, 2007. (2) On July 3, 2006 (71 FR 34814, June 16, 2006), the Director of the Federal Register previously approved the incorporation by reference of Airbus Temporary Revision 4.03.00/28, dated May 4, 2006. (3) Contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on October 24, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-25997 Filed 11-13-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to prevent electrical arcing in the fuel tank boost pump motor, which, in the presence of a combustible air-fuel mixture in the pump, could result in an explosion and loss of the airplane.