Airworthiness Directive · Amendment 39-17670 · Fuselage
The Boeing Company Airplanes
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, as identified in Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012.
We are superseding Airworthiness Directive (AD) 2009-06-02, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series airplanes. AD 2009-06-02 required repetitive inspections for skin cracks at the shear tie end fastener locations of the fuselage frames, and repair of cracks if necessary. This new AD also requires repetitive inspections for skin cracks next to the shear tie on airplanes with certain existing repair doublers, and corrective actions if necessary. This AD also revises the applicability to include additional airplanes. This AD was prompted by additional cracking found on an airplane not affected by AD 2009-06-02. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin that can propagate and grow, and result in reduced structural integrity and sudden decompression of the airplane in flight.
At the applicable compliance time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, except as provided by paragraphs (i)(1) and (i)(2) of this AD, do an external detailed or high frequency eddy current (HFEC) inspection for skin cracks at specified shear tie end fastener locations of the fuselage frames, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. Repeat the external detailed or HFEC inspection thereafter at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012.
For any external repair doubler in the inspection area specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, that has an upper or lower fastener row that is common to a shear tie end fastener: At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, whichever occurs later, do an internal HFEC inspection for cracks in the skin next to the shear tie, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, except as required by paragraph (i)(3) of this AD. Do all corrective actions before further flight. Repeat the internal HFEC inspection thereafter at the time specified in Table 4 or Table 5 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, as applicable.
(1) Before further flight after an inspection required by paragraph (g) of this AD.
(2) Within 2,000 flight cycles after the effective date of this AD.
(1) Paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, specifies certain compliance times in terms of the effective date of AD 2009-06-02, Amendment 39-15838 (74 FR 11013, March 16, 2009). The effective date of AD 2009-06-02 is April 20, 2009.
(2) Where paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, specifies counting the compliance time “after the revision 1 date of this service bulletin,” this AD requires compliance within the applicable time after the effective date of this AD.
(3) Where Boeing Alert Service Bulletin 747-53A2682, Revision 1, dated May 24, 2012, specifies to contact Boeing for repair instructions, this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD.
