AD 2006-12-02 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 all Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Part and Serial Number Inspection (f) Within 10 days after the effective date of this AD, 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. For any airplane not equipped with any Eaton Aerospace Limited (formerly FR-HITEMP Limited) fuel pump having P/N 568-1-27202-005 with S/N 6137 and subsequent: No further action is required by this AD for that airplane except as described in paragraph (i) of this AD. Revisions to the Airplane Flight Manual (AFM) and the Maintenance Program (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) of this AD. (1) Revise the Limitations section of the Airbus A318/A319/A320/A321 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 (1550 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) Revise the Limitations section of the AFM to incorporate the changes specified in Airbus Temporary Revision (TR) 4.03.00/28, dated May 4, 2006. 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. Optional Terminating Action (h) Replacement of all subject fuel boost pumps on any airplane with boost pumps having a P/N other than P/N 568-1-27202-005; or with boost pumps, P/N 568-1-27202-005, having a S/N other than 6137 and subsequent; constitutes terminating action for this AD, and the limitations required by paragraph (g) of this AD may be removed from the AFM and the maintenance program for that airplane. Parts Installation (i) As of the effective date of this AD, no person may install a boost pump, P/N 568-1-27202-005, having S/N 6137 and subsequent, on any airplane. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) The European Aviation Safety Agency (EASA) emergency airworthiness directive 2006-0106-E, dated May 2, 2006, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Temporary Revision 4.03.00/28, dated May 4, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. (The approval date of Airbus Temporary Revision 4.03.00/28 is only indicated on page one of the document.) The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 June 7, 2006. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5425 Filed 6-15-06; 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 ensure that the flightcrew is aware of procedures to prevent the presence of a combustible air-fuel mixture in the fuel tank boost pump, which, in the event of electrical arcing in the pump motor, could result in an explosion and loss of the airplane.