Airworthiness Directive · Amendment 39-16579 · Fuselage
The Boeing Company Model 767-300 Series Airplanes
This AD applies to The Boeing Company Model 767-300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for cracks in the fuselage skin and backup structure at the lower VHF antenna cutout at station 1197 + 99 between stringers 39 left and 39 right, and corrective actions if necessary. Certain repairs terminate certain inspection requirements. This AD was prompted by reports of cracking found in the section 46 fuselage lower skin around the periphery of the VHF antenna baseplate at station 1197 + 99. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin and internal backup structure, which could result in rapid decompression of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Inspect for cracks in the fuselage skin and backup structure at the lower VHF antenna cutout at station 1197 + 99, between stringers 39L and 39R, by doing an external detailed inspection, with the antenna removed, of the fuselage structure at the lower aft VHF antenna cutout, and an internal detailed inspection of the backup structure. Do the inspections in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009. Do the inspections at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, except as required by paragraphs (h) and (i) of this AD.
(1) If no crack is found, repeat the external detailed inspection, without removing the antenna, at intervals not to exceed 3,000 flight cycles.
(2) If any crack is found in the fuselage skin, repair before further flight, in accordance with Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009. Accomplishment of this repair terminates the repetitive external detailed inspections of the fuselage skin required by this AD.
(3) If any crack is found in the backup structure, before further flight, repair or replace the cracked part(s), in accordance with Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009.
Where Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified time after the effective date of this AD.
(i) The internal detailed inspection specified in Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, and required by paragraph (g) of this AD must be done at the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) Before the accumulation of 25,000 total flight cycles.
(2) At the applicable time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) If any fuselage skin crack is found during the external detailed inspection required by paragraph (g) of this AD: Within 3,000 flight cycles after the effective date of this AD.
(ii) If no fuselage skin crack is found during the external detailed inspection required by paragraph (g) of this AD: Within 6,000 flight cycles after the effective date of this AD.
