AD 2009-23-04 Airworthiness Directives; Boeing Model 767 Airplanes

Models named: 767-200, -300, -300F, -400ER series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 767-200, -300, -300F, and -400ER series 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. Compliance Times for Initial Replacement (f) For each main tank fuel boost pump: At the latest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, do the actions specified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-28A0095 or 767-28A0096; both dated September 15, 2005; as applicable. (1) Within 96 months since the date of the first installation of the fuel boost pump or before the accumulation of 40,000 flight hours on the fuel boost pump, whichever comes first. (2) Within 96 months since the date of replacement of the feed-through connector, or before the accumulation of 40,000 flight hours on the fuel boost pump since the date of replacement of the feed-through connector, whichever comes first. (3) Within 24 months after the effective date of this AD. Replacement of Fuel Boost Pump Feed-Through Connector (g) At the compliance time specified in paragraph (f) of this AD: Replace the feed-through connector of each fuel boost pump as described in paragraph (g)(1) or (g)(2) of this AD. (1) Replace the fuel boost pump with a new fuel boost pump. (2) Replace the fuel boost pump with a modified and re-identified fuel boost pump having a new feed-through connector installed. Note 1: Replacing the feed-through connector of each fuel boost pump, as required by paragraph (g) of this AD, may be done in different fuel boost pumps at different times provided the compliance times required by paragraph (f) of this AD are met for each pump. Note 2: Boeing Alert Service Bulletins 767-28A0095 and 767-28A0096, both dated September 15, 2005, refer to Hamilton Sundstrand Alert Service Bulletin 5006003-28-A4, dated May 9, 2005, as a source of guidance for replacing the feed-through connector and re-identifying the fuel boost pump. Repetitive Replacements (h) Repeat the replacement required by paragraph (g) of this AD thereafter at intervals not to exceed the applicable times specified in paragraphs (h)(1) and (h)(2) of this AD: (1) For airplanes on which the replacement specified in paragraph (g)(1) of this AD is done: Within 96 months since the date of the first installation of the fuel boost pump or before the accumulation of 40,000 flight hours on the fuel boost pump, whichever comes first. (2) For airplanes on which the replacement specified in paragraph (g)(2) of this AD is done: Within 96 months since the date of replacement of the feed-through connector or before the accumulation of 40,000 flight hours on the fuel boost pump since the date of replacement of the feed-through connector, whichever comes first. Parts Installation (i) As of the effective date of this AD, no person may install a fuel boost pump on any airplane, unless that pump has a feed-through connector that meets the requirements of paragraphs (f) and (g) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to Judy Coyle, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6497; fax (425) 917-6590. Or, e-mail information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov . (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Material Incorporated by Reference (k) You must use Boeing Alert Service Bulletin 767-28A0095, dated September 15, 2005; or Boeing Alert Service Bulletin 767-28A0096, dated September 15, 2005; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com ; Internet https://www.myboeingfleet.com . (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (4) You may also review copies of the service information that is incorporated by reference 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 26, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-26585 Filed 11-6-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of cracking in the epoxy potting compound on the internal feed-through connector of the fuel boost pump in the area of the soldered wire connector lugs. We are issuing this AD to prevent a hazardous electrical path from the dry side to the wet side of the fuel boost pump through a cracked feed-through connector, or between pins or a pin and the shell on one side of the feed-through connector, which could create an ignition source on the wet side of the fuel boost pump or cause a fire in the fuel boost pump enclosure and lead to subsequent explosion of the fuel tank.