Airworthiness Directive · Amendment 39-18733 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 767-200 and -300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0267, Revision 1, dated August 4, 2016.
(2) Installation of Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01920se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead is subject to widespread fatigue damage (WFD). This AD requires replacing the aft pressure bulkhead with a new, improved aft pressure bulkhead, and doing related investigative and corrective actions if necessary. We are issuing this AD to prevent the unsafe condition on these products.
Before the accumulation of 60,000 total flight cycles, or within 36 months after the effective date of this AD, whichever occurs later, but not earlier than 37,500 total accumulated flight cycles: Replace the aft pressure bulkhead at Station 1582 of Section 48 with a new, improved aft pressure bulkhead, and perform all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0267, Revision 1, dated August 4, 2016; except as required by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the replacement in this paragraph terminates all requirements of the ADs identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
(1) AD 2004-05-16, Amendment 39-13511 (69 FR 10917, March 9, 2004).
(2) AD 2004-14-19, Amendment 39-13728 (69 FR 42549, July 16, 2004).
(3) AD 2009-06-19, Amendment 39-15856 (74 FR 12243, March 24, 2009).
If any defect (e.g., rifling, gouging, nicks, or burrs, or excessive surface roughness) is found in any fastener hole (other than normally produced during a typical reaming operation), during accomplishment of any inspection (related investigative actions) required by this AD, and Boeing Alert Service Bulletin 767-53A0267, Revision 1, dated August 4, 2016, specifies to contact Boeing for repair instructions: Before further flight, repair in accordance with the procedures specified in paragraph (k) of this AD.
Where Boeing Alert Service Bulletin 767-53A0267, Revision 1, dated August 4, 2016, specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified time after the effective date of this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
