Airworthiness directives › 2016-06-07
AD 2016-06-07 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 all 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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Except as specified in paragraphs (h)(1) and (h)(2) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013: Do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, except as specified in paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the applicable intervals specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013. The repetitive interval for the inspection of Area 2 specified in table 1 in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, is 1,000 flight cycles. In table 2 and table 3 in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013, the date “January 27, 2005,” is the effective date of AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23, 2004); and the date “May 10, 2005,” is the effective date of AD 2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005; corrected May 25, 2005 (70 FR 29940)). (1) Do an external detailed inspection for cracks of the top and sidewall panel webs of the NWW (specified as Area 1 and Area 2 in Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013). (2) Do internal detailed and surface high frequency eddy current (HFEC) inspections for cracks of the sidewall panel and top panel stiffeners of the NWW (specified as Area 3 in Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013). (3) Do an external detailed and ultrasonic testing (UT) inspection for cracks of the top and sidewall panel webs of the NWW (specified as Area 1 and Area 2 in Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 2013).
Unsafe condition
This AD was prompted by multiple reports of cracking in the nose wheel well (NWW) top panel and side panel webs and stiffeners. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage.
Affected ADs
This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (“AD 2006-22-15”).
Read the original on the Federal Register →
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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