Airworthiness directives › 2016-16-10
AD 2016-16-10 Airworthiness Directives; The Boeing Company Airplanes
Models named: 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, except as provided by paragraphs (j)(1) and (j)(2) of this AD: Do the actions specified in paragraphs (g)(1) through (g)(5) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2862, Revision 1, dated July 24, 2015, except as required by paragraph (j)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (1) Do a detailed inspection for cracks and missing fasteners of the station 320 crown frame. (2) Do a surface high frequency eddy current (HFEC) inspection for cracks of the station 320 crown frame. (3) Do a surface HFEC inspection for cracks in the web and flange surfaces of the forward segment of window post number 3. (4) Do a detailed inspection for missing fasteners of the window upper sill. (5) Do a surface HFEC inspection for cracks of the window upper sill.
Unsafe condition
This AD was prompted by reports of fatigue cracks in the station 320 crown frame in window post number 3. We are issuing this AD to detect and correct fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill, which could result in an in-flight decompression and a loss of structural integrity of the fuselage.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1