Airworthiness Directive · Amendment 39-18100 · 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, certificated in any category, as identified in Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014.
We are adopting a new airworthiness directive (AD) for certain 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. This AD was prompted by reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. This AD requires repetitive inspections of the fuselage skin of the MED 1 cutout for cracking, and repair if necessary; and also provides an optional terminating modification, including post-repair or post-modification fuselage skin inspections for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane.
Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014: Do a detailed inspection and a surface high frequency eddy current inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. Do all applicable corrective actions before further flight. Repeat the inspections of the applicable MED 1 cutout thereafter at the applicable intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. Accomplishing the corrective actions required by this paragraph terminates the repetitive inspection requirements of this paragraph.
For airplanes on which no crack is found during the initial inspections required by paragraph (g) of this AD: Installing the preventive modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, terminates the repetitive inspections required by paragraph (g) of this AD.
For airplanes on which the corrective actions required by paragraph (g) of this AD have been done, or airplanes that have installed the preventive modification specified in paragraph (h) of this AD: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, do a detailed inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the fuselage skin at the applicable MED 1 cutout thereafter at the intervals specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014.
(1) Where paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, specifies a compliance time “after the Original issue date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, specifies to contact 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.
