Airworthiness Directive · Amendment 39-16355 · Fuselage
The Boeing Company Model 747-100, -200B, and -200F Series Airplanes
This AD applies to The Boeing Company Model 747-100, 747-200B, and 747-200F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009.
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-100, 747-200B, and -200F series airplanes. That AD currently requires inspections to detect cracking in the upper row of fasteners holes of the skin lap joints in the fuselage lower lobe, and repair if necessary. This new AD reduces the maximum interval of the post-modification inspections. This AD results from reports of fatigue cracking on modified airplanes. We are issuing this AD to detect and correct fatigue cracking in the longitudinal lap joints of the fuselage lower lobe, which could lead to the rapid decompression of the airplane and the inability of the structure to carry fail-safe loads.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Perform an external high frequency eddy current inspection to detect cracks in the upper row of fasteners in the modified lap joints in accordance with Boeing Service Bulletin 747-53A2267, Revision 3, dated March 26, 1992; or Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009; at the time specified in paragraph (g)(1) or (g)(2) or (g)(3) of this AD, as applicable. As of the effective date of this AD, only Revision 4 may be used.
(1) For locations on airplanes on which the full modification required by AD 90-06-06, Amendment 39-6490, has been accomplished in accordance with Revision 2 of Boeing Service Bulletin 747-53A2267, dated March 29, 1990; or Revision 3, dated March 26, 1992; or Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009: Prior to the accumulation of 10,000 flight cycles after accomplishment of the full modification.
(2) For locations on airplanes on which the full modification required by AD 90-06-06 has been accomplished in accordance with Boeing Service Bulletin 747-53A2267, dated March 28, 1986; or Revision 1, dated September 25, 1986: Prior to the accumulation of 7,000 flight cycles after accomplishment of the full modification.
(3) For locations on airplanes on which the optional modification has been accomplished in accordance with Boeing Service Bulletin 747-53A2267, Revision 2, dated March 29, 1990, or Revision 3, dated March 26, 1992; or Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009: Prior to the accumulation of 7,000 flight cycles after accomplishment of the optional modification.
If no cracking is detected during the inspection required by paragraph (g) of this AD, repeat the inspection required by paragraph (g) of this AD at the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, and thereafter at intervals not to exceed 1,000 flight cycles.
(1) Within 3,000 flight cycles after the last inspection required by paragraph (g) of this AD.
(2) Within 1,000 flight cycles after the last inspection required by paragraph (g) of this AD or 500 flight cycles after the effective date of this AD, whichever occurs later.
(i) If any cracking is detected during any inspection required by paragraph (g) of this AD, prior to further flight, repair in accordance with Section 53-30-03 of the Boeing 747 Structural Repair Manual (SRM); or Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009; except as required by paragraph (j) of this AD; and repeat the inspection required by paragraph (g) of this AD at the times specified in paragraph (i)(1) of this AD. As of the effective date of this AD, use only Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009.
(1) As of the effective date of this AD: If the repair specified in the Boeing 747 SRM does not include removing the lap joint and the upper row of countersunk fasteners, repeat the inspection required by paragraph (g) of this AD at the earlier of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, and thereafter at intervals not to exceed 1,000 flight cycles.
(i) Within 3,000 flight cycles after the last inspection required by paragraph (g) of this AD.
(ii) Within 1,000 flight cycles after the last inspection required by paragraph (g) of this AD, or within 500 flight cycles after the effective date of this AD, whichever occurs later.
(2) If the repair specified in the Boeing 747 SRM includes removing the lap joint and the upper row of countersunk fasteners, such repair constitutes terminating action for the inspection requirements of this AD. To “remove” means to trim out all three fastener rows of the overlapping skin common to the lap joint.
If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March 26, 2009, specifies contacting Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
