Airworthiness Directive · Amendment 39-18619 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 767-200 and -300 series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE_AML.pdf) 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 all 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 web to pressure chord joint is subject to widespread fatigue damage (WFD). This AD requires repetitive high frequency eddy current (HFEC) inspections of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, for any crack, and repair of cracks. We are issuing this AD to detect and correct cracks in the aft pressure bulkhead web. Such cracking could result in the loss of structural integrity of the airplane.
Except as required by paragraph (h) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015, perform a surface high frequency eddy current (HFEC) inspection for cracking of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015. For this AD, Group 2, Configuration 2, as specified in Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015, includes airplanes with the aft pressure bulkhead replaced as specified in Boeing Alert Service Bulletin 767-53A0267. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015.
Where Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015, specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Although Boeing Alert Service Bulletin 767-53A0268, dated April 1, 2015, specifies to contact Boeing for repair instructions, and specifies that action as “RC” (Required for Compliance), this AD requires repair as specified in this paragraph. Installation of a repair terminates the inspections required by paragraph (g) of this AD in the area covered by the repair only.
