AD 2010-14-18 Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines

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 767-54A0101, Revision 5, dated June 29, 2010.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Note 1: Notwithstanding any inspection done in accordance with AD 2005-19-23, inspect within the compliance times specified in this AD. Initial Inspection (g) At the applicable time specified in paragraph (h) of this AD: Do the actions specified in either paragraph (g)(1) or (g)(2) of this AD. (1) Do a detailed inspection for cracking of the 8 aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and a surface high frequency eddy current (HFEC) inspection for cracking of the closeout angle that covers the 2 aft-most fasteners in the lower tang of the midspar fitting, in accordance with Part 1, “Detailed Inspection of Midspar Fitting and Surface High Frequency Eddy Current (HFEC) Inspection of Closeout Angle,” of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010. (2) Do an open-hole HFEC inspection for cracking of each fastener hole, inspect to determine the size of each fastener hole, and do all applicable related investigative and corrective actions, in accordance with Part 2, “Open Hole HFEC Inspection,” of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, except as required by paragraphs (m) and (n) of this AD, and except as provided by paragraph (p) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, do the actions specified in paragraph (g) of this AD. (1) For airplanes on which an inspection (any Part 1 or Part 2 inspection) has not been done in accordance with any service bulletin listed in Table 1 of this AD as of the effective date of this AD: Prior to the accumulation of 8,000 total flight cycles, or within 90 days after the effective date of this AD, whichever occurs later, do the actions specified in paragraph (g) of this AD. Table 1—Service Bulletins Service Bulletin Revision Date Boeing Alert Service Bulletin 767-54A0101 4 February 10, 2005. Boeing Alert Service Bulletin 767-54A0101 5 June 29, 2010. Boeing Service Bulletin 767-54A0101 2 January 10, 2002. Boeing Service Bulletin 767-54A0101 3 September 5, 2002. (2) For airplanes on which any inspection (any Part 1 or Part 2 inspection) has been done in accordance with any service bulletin listed in Table 1 of this AD as of the effective date of this AD: Within 400 flight cycles after doing the most recent inspection or within 90 days after the effective date of this AD, whichever occurs later, do the actions specified in paragraph (g) of this AD. Repetitive Inspections (i) If, during any detailed and surface HFEC inspection specified by paragraph (g)(1) of this AD, no cracking is found, do the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Repeat the inspections specified in paragraph (g)(1) of this AD thereafter at intervals not to exceed 400 flight cycles. (2) Within 400 flight cycles after doing the most recent inspections specified in paragraph (g)(1) of this AD, do the actions specified in paragraph (g)(2) of this AD and repeat thereafter at intervals not to exceed 6,000 flight cycles. (j) If, during the actions specified by paragraph (g)(2) of this AD, the terminating action specified in Part 4 of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, is not done, do the actions specified in either paragraph (j)(1) or (j)(2) of this AD. (1) Within 6,000 flight cycles after doing the actions specified in paragraph (g)(2) of this AD, do the inspections specified in paragraph (g)(1) of this AD and repeat the inspections thereafter at intervals not to exceed 400 flight cycles. (2) Repeat the actions specified in paragraph (g)(2) of this AD thereafter at intervals not to exceed 6,000 flight cycles. Corrective Actions for Inspections Done per Paragraph (g)(1) of This AD (k) If, during any inspection specified by paragraph (g)(1) of this AD, any crack is found in the midspar fitting tangs, before further flight, do the actions specified in paragraph (k)(1) or (k)(2) of this AD. (1) Do the terminating action specified in Part 4 of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, except as required by paragraph (m) of this AD. Accomplishment of this paragraph terminates the requirements of this AD. (2) Replace the midspar fitting of the strut with a new part, or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Within 8,000 flight cycles after doing the replacement, do the actions specified in either paragraph (k)(2)(i) or (k)(2)(ii) of this AD. (i) Do the inspections specified in paragraph (g)(1) of this AD and repeat the inspections thereafter at intervals not to exceed 400 flight cycles. (ii) Do the actions specified in paragraph (g)(2) of this AD and repeat the actions thereafter at intervals not to exceed 6,000 flight cycles. (l) If, during any surface HFEC inspection specified by paragraph (g)(1) of this AD, any crack is found in the closeout angle, before further flight, do the open-hole HFEC inspection for cracking and all applicable related investigative and corrective actions, in accordance with Part 2, “Open Hole HFEC Inspection,” and step 4.b.(2) of Part 1, “Detailed Inspection of Midspar Fitting and Surface High Frequency Eddy Current (HFEC) Inspection of Closeout Angle,” of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, except as required by paragraphs (m) and (n) of this AD, and except as provided by paragraph (p) of this AD. If the terminating action specified in Part 4 of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, is not done, do the actions specified in either paragraph (l)(1) or (l)(2) of this AD. (1) Within 6,000 flight cycles after doing the actions specified in paragraph (l) of this AD, do the inspections specified in paragraph (g)(1) of this AD and repeat the inspections thereafter at intervals not to exceed 400 flight cycles. (2) Within 6,000 flight cycles after doing the actions specified in paragraph (l) of this AD, do the actions specified in paragraph (g)(2) of this AD, and repeat the actions thereafter at intervals not to exceed 6,000 flight cycles. Service Bulletin Exceptions (m) Where Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, specifies that the manufacturer may be contacted for disposition of repair conditions: Before further flight, accomplish the repair using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (n) If, during any open-hole HFEC inspection required by paragraph (g)(2) or (l) of this AD, any crack is found in the midspar fitting and the hole size is 0.5322 inch, before further flight, do the terminating action specified in paragraph (k)(1) of this AD. Optional Terminating Action (o) Doing the terminating action specified in Part 4 of the Work Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, terminates the requirements of this AD. Note 2: Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, refers to the Boeing service bulletins in Table 2 of this AD as additional sources of guidance for doing the terminating action in paragraphs (k) and (o) of this AD. Table 2—Additional Sources of Guidance Boeing Service Bulletin Revision level Date Title 767-54-0052 Original June 11, 1992 Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection and Replacement. 767-54-0061 2 November 23, 1999 Nacelles/Pylons—Wing-to-Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement. 767-54-0069 2 August 31, 2000 Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—Fuse Pin Replacement and Wing Rework. 767-54-0072 Original March 13, 1997 Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, Rework or Replacement. 767-54-0080 1 May 9, 2002 Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle Strut and Wing Structure Modification. 767-54-0081 1 February 7, 2002 Nacelles/Pylons—General Electric Powered Airplanes—Nacelle Strut and Wing Structure Modification. 767-54A0062 6 November 5, 2009 Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and Replacement. 767-54A0074 1 April 24, 2008 Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. 767-54A0094 2 February 7, 2002 Nacelles/Pylons—Strut—to—Wing Attachment—Diagonal Brace Inspection/Rework/Replacement. 767-57-0063 1 November 30, 2000 Wings—Side Load Underwing Fitting —Inspection/Rework. Note 3: Certain service bulletins referenced in Table 2 of this AD are related to the ADs listed in Table 3 of this AD. Table 3—Other Relevant Rulemaking AD Applicability Related Boeing Service Bulletin AD requirement AD 2000-07-05, amendment 39-11659 Certain Boeing Model 767 series airplanes 767-54A0094 Repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut; follow-on actions, if necessary; and terminating action for the repetitive inspections. AD 2004-16-12, amendment 39-13768 Certain Boeing Model 767-200, -300, and -300F series airplanes powered by Pratt & Whitney engines or General Electric engines 767-54-0069, 767-54-0080, 767-54-0081, and 767-54A0094 Modification of the nacelle strut and wing structure. AD 2009-20-09, amendment 39-16032 Certain Boeing Model 767-200, -300, and -300F series airplanes 767-54A0074 Repetitive inspections for fatigue cracking and corrosion of the upper link fuse pin of the nacelle struts, and related investigative and corrective actions if necessary. AD 2010-03-08, amendment 39-16192 Certain Boeing Model 767-200, -300, and -300F series airplanes 767-54A0062, 767-54-0069 Repetitive detailed and eddy current inspections to detect cracks of certain midspar fuse pins, and corrective action if necessary. Optional Corrective Action for Paragraph (g)(2) or (l) of This AD (p) In lieu of doing the related investigative and corrective actions required by paragraph (g)(2) or (l) of this AD, before further flight, replace the midspar fitting of the strut with a new part, or repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Within 8,000 flight cycles after doing any replacement, do the actions specified in either paragraph (p)(1) or (p)(2) of this AD. (1) Do the inspections specified in paragraph (g)(1) of this AD and repeat the inspections thereafter at intervals not to exceed 400 flight cycles. (2) Do the actions specified in paragraph (g)(2) of this AD and repeat the actions thereafter at intervals not to exceed 6,000 flight cycles. Terminating Action Accomplished per Previous Issues of Service Bulletin (q) Doing the terminating action specified in Part 4 of the Work Instructions of any service bulletin listed in Table 4 of this AD before the effective date of this AD is acceptable for compliance with the requirements of this AD. Table 4—Credit Service Bulletins for Terminating Action Service Bulletin Revision Date Boeing Alert Service Bulletin 767-54A0101 Original September 23, 1999. Boeing Alert Service Bulletin 767-54A0101 4 February 10, 2005. Boeing Service Bulletin 767-54A0101 1 February 3, 2000. Boeing Service Bulletin 767-54A0101 2 January 10, 2002. Boeing Service Bulletin 767-54A0101 3 September 5, 2002. Alternative Methods of Compliance (AMOCs) (r)(1) The Manager, Seattle Aircraft Certification Office, 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: 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. Information may be e-mailed 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. (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. Material Incorporated by Reference (s) You must use Boeing Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 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 July 9, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-17611 Filed 7-21-10; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks in the midspar fitting tangs. The Federal Aviation Administration is issuing this AD to detect and correct fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine.