Airworthiness Directive · Amendment 39-17094 · Fuselage
The Boeing Company Airplanes
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 767-53A0228, dated July 28, 2011.
Note 1 to paragraph (c) of this AD: Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$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 certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit. This AD requires repetitive inspections for cracking, corrosion damage, and any other irregularity of the lower main sill inner chord and surrounding structure, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking on the lower main sill inner chord of the hatch opening of the overwing emergency exit, which could result in reduced structural integrity of the hatch opening of the overwing emergency exit and consequent rapid decompression of the airplane.
Within the applicable compliance time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, except as provided by paragraph (i)(3) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the lower main sill inner chord around body station (STA) 883.5; a detailed inspection for cracking, corrosion damage, and any other irregularity, of the lower main sill inner chord and surrounding structure around STA 883.5; and a detailed inspection for cracking, corrosion damage, or other irregularity, of the lower main sill inner chord and surrounding structure around STA 903.5; as applicable; and do all applicable repairs; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, except as required by paragraphs (i)(1) and (i)(2) of this AD. Do all applicable repairs before further flight. Repeat the applicable inspections thereafter within the applicable times and intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011. Doing a structural repair specified in paragraph (h) of this AD, terminates the inspections for that location only.
Doing a structural repair (doubler installation) in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, terminates the inspections required by paragraph (g) of this AD for that location only.
(1) If any cracking, corrosion damage, or other irregularity is found during any inspection required by this AD, and Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking, corrosion damage, or other irregularity, using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(2) Where Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, specifies that the sequence of steps to do the actions can be changed, this AD does not allow the sequence of steps to be changed for the inspection and repair; however, the open-up and close-up steps may be done in any practical order.
(3) Where Boeing Alert Service Bulletin 767-53A0228, dated July 28, 2011, 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.”
