Airworthiness Directive · Amendment 39-18567 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC) [STC ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.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 airplanes. This AD was prompted by a determination that certain splice plate locations of the aft pressure bulkhead web are hidden and cannot be inspected using existing manufacturer service information. This AD requires repetitive open-hole high frequency eddy current (HFEC) inspections for cracking of the aft pressure bulkhead web. We are issuing this AD to detect and correct cracking in the aft pressure bulkhead web, which could result in rapid airplane decompression and loss of structural integrity.
At the applicable times specified in Table 1 and Table 2 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0266, dated April 20, 2015, except as required by paragraph (i) of this AD: Do an open-hole high frequency eddy current (HFEC) inspection for cracking in the aft pressure bulkhead web at STA 1582, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0266, dated April 20, 2015, except as required by paragraph (h) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at intervals not to exceed 12,000 flight cycles.
If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 767-53A0266, dated April 20, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair the crack in accordance with the procedures specified in paragraph (j) of this AD. Accomplishing a reinforcing repair terminates the inspections required by paragraph (g) of this AD in the area under the repair only.
Where Boeing Alert Service Bulletin 767-53A0266, dated April 20, 2015, 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.
