AD 2010-22-01 Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes

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

This AD applies to The Boeing Company Model 767-200, -300, and -300F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008.

Comply with this AD within the compliance times specified, unless already done. Restatement of Requirements of AD 2009-20-09, With Revised Credit Provisions in Paragraph (I) of This AD Initial and Repetitive Inspections/Investigative and Corrective Actions (g) Inspect the upper link fuse pin of the nacelle struts for fatigue cracking and corrosion at the applicable time specified in Table 1 of this AD. Do the applicable inspection by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008; and do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection at intervals not to exceed 3,000 flight cycles or 24 months, whichever is first, until the requirements of paragraph (h) of this AD have been done. Table 1—Compliance Times Engine type At the later of: Initial inspection threshold Grace period JT9D 14,000 total flight cycles Within 3,000 flight cycles or 18 months after November 5, 2009 (the effective date of AD 2009-20-09), whichever is first. CF6-80A 24,000 total flight cycles Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. PW4000 8,000 total flight cycles Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. CF6-80C2 10,000 total flight cycles Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. RB211 24,000 total flight cycles Within 3,000 flight cycles or 18 months after November 5, 2009, whichever is first. Note 1: The upper link inspections can be done with the pylon and/or engine in any position. Note 2: In paragraph 3.B, Steps 4.b.(1)(a) and 4.b.(2)(b)(2){a} of the Accomplishment Instructions of Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008, the procedures specify to apply two layers of Boeing Material Specification (BMS) 10-11 primer to the inside surface of the fuse pin if no crack indication is found. However, two layers of primer are only necessary to touch up bare areas on the fuse pin if no crack indication is found. Terminating Action in AD 2000-19-09, Amendment 39-11910, and AD 2004-16-12, Amendment 39-13768 (h) Accomplishment of the modification specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, terminates the inspections required by paragraph (g) of this AD. (1) For Model 767 series airplanes powered by Rolls-Royce RB211 series engines, as identified in AD 2000-19-09: Modification of the nacelle strut and wing structure, as required by paragraphs (a) and (b) of AD 2000-19-09. (2) For Model 767-200, -300, and -300F series airplanes powered by Pratt & Whitney and General Electric engines, as identified in AD 2004-16-12: Modification of the nacelle strut and wing structure, as required by paragraphs (a), (b), (d), and (e) of AD 2004-16-12. Credit for Inspection Done Using Previous Service Information (i) Inspection of the fuse pins before November 5, 2009, in accordance with Boeing Service Bulletin 767-54-0074, dated March 27, 1997, is acceptable for compliance with the inspections required by paragraph (g) of this AD, except that operator's equivalent procedures are not allowed. New Requirements of This AD Optional Terminating Action for Inspections (j) Replacement of the fuse pins with new fuse pins (not serviceable fuse pins), in accordance with Boeing Service Bulletin 767-54-0074, dated March 27, 1997; or Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008; terminates the repetitive inspections of the fuse pins required by paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (k)(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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your Principal Maintenance Inspector or Principal Avionics Inspector, as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. AMOCs that specified using new pins (not serviceable pins) approved previously in accordance with AD 2009-20-09, Amendment 39-16032, are approved as AMOCs for the corresponding provisions of paragraph (h) of this AD. Related Information (l) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 917-6590. Material Incorporated by Reference (m) You must use Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating actions specified in this AD, you must use Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008; or Boeing Service Bulletin 767-54-0074, dated March 27, 1997; to perform those actions, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767-54-0074, dated March 27, 1997, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April 24, 2008, on November 5, 2009 (74 FR 50692, October 1, 2009). (3) 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. (4) 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. (5) 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 an NARA facility, 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 6, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-26224 Filed 10-19-10; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by two reports of cracked upper link fuse pins. We are issuing this AD to prevent fatigue cracking or corrosion of the upper link fuse pin, which could result in failure of the fuse pin and consequent reduced structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane during flight.