Airworthiness directives › 2012-26-04
AD 2012-26-04 Airworthiness Directives; The Boeing Company Airplanes
Models named: 757-200, -200PF, -200CB series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model 757-200, -200PF, and -200CB series airplanes; certificated in any category; line numbers 1 through 1048 inclusive; powered by Rolls-Royce engines.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the one-time inspection and repair required by paragraph (g) of AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008), with optional inspection method and revised service information. For airplanes identified in paragraphs (g)(1) and (g)(2) of this AD: Within 90 days after August 24, 2007 (the effective date of AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9, 2007)), do a high frequency eddy current (HFEC) inspection for cracking of the four critical fastener holes in the horizontal flange and, before further flight, do all applicable repairs, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June 27, 2007; Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010; or Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011; except as required by paragraph (i)(3) of this AD. As of the effective date of this AD, only Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, may be used to accomplish the actions required by this paragraph. Doing an ultrasonic inspection for cracking of the fasteners, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010; or Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011; is an acceptable method of compliance with the HFEC inspection requirement of this paragraph. (1) Airplanes on which findings on the horizontal or vertical fasteners or the shims led to a rejection of any fastener during the actions specified in Boeing Alert Service Bulletin 757-54A0047, dated November 13, 2003; or Boeing Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005. (2) Airplanes that had equivalent findings prior to the actions specified in Boeing Alert Service Bulletin 757-54A0047, dated November 13, 2003, except for findings on airplanes identified as Group 1, Configuration 2, in Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June 27, 2007, that were prior to the incorporation of Boeing Service Bulletin 757-54-0035.
Unsafe condition
This AD was prompted by reports of loose fasteners and cracks at the joint common to the aft torque bulkhead and strut-to-diagonal brace fitting, and one report of such damage occurring less than 3,000 flight cycles after the last inspection. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.
Affected ADs
This AD supersedes AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008).
Read the original on the Federal Register →
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