AD 2010-26-01 Airworthiness Directives; The Boeing Company Model 777-200 Series Airplanes

Models named: 777-200 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to The Boeing Company Model 777-200 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 777-78A0066, Revision 2, dated April 8, 2010.

Comply with this AD within the compliance times specified, unless already done. Installation of Insulation Blanket (g) Within 60 months or 4,500 flight cycles after the effective date of this AD, whichever is first: Install a new insulation blanket on the latch beam firewall of each T/R half by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 777-78A0066, Revision 2, dated April 8, 2010. Credit for Actions Accomplished in Accordance With Previous Service Information (h) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 777-78A0066, dated June 5, 2008; or Boeing Service Bulletin 777-78A0066, Revision 1, dated March 12, 2009; are acceptable for compliance with the corresponding requirements of paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (i)(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 Attn: Margaret Langsted, Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 917-6500; 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 (j) You must use Boeing Alert Service Bulletin 777-78A0066, Revision 2, dated April 8, 2010, 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. (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 December 3, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-31384 Filed 12-15-10; 8:45 am] BILLING CODE 4910-13-P

This AD results from an in-flight shutdown due to an engine fire indication; an under-cowl engine fire was extinguished after landing. The cause of the fire was uncontained failure of the starter in the engine core compartment; the fire progressed into the latch beam cavity and was fueled by oil from a damaged integrated drive generator oil line. We are issuing this AD to prevent a fire from entering the cowl or strut area, which could weaken thrust reverser (T/R) parts and result in reduced structural integrity of the T/R, possible separation of T/R parts during flight, and consequent damage to the airplane and injury to people or damage to property on the ground.