Airworthiness Directive · Amendment 39-17794 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012.
We are superseding airworthiness directive (AD) 2008-11-04 for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-11-04 required repetitive inspections for cracking in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, and corrective actions if necessary. This new AD reduces the inspection threshold for cracking in and around the galley service doorway hinge cutouts, adds inspections of certain repaired structure at the forward entry and galley service doorway upper and lower hinge cutouts, expands the inspection area at the forward entry and galley service doorway upper and lower hinge cutouts, and removes certain airplanes from the applicability. This AD was prompted by multiple reports of cracks in the skin and/or bear strap at the forward galley service doorway hinge cutouts, and multiple reports of cracking under the repairs installed at the hinge cutouts. We are issuing this AD to detect and correct such cracking, which could result in rapid decompression of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008). Except as provided by paragraph (h)(1) of this AD, at the applicable times specified in paragraph 1.E. “Compliance,” of Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, do external detailed, low frequency eddy current (LFEC), high frequency eddy current (HFEC), and HFEC rotary probe inspections, as applicable, for cracks in and around the upper and lower hinge cutouts of the forward entry and forward galley service doorways, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, except as provided by paragraphs (h)(2) and (i) of this AD. Do not exceed the applicable repetitive interval for the previous inspection, as specified in Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, as Option A or Option B. Repair any crack before further flight using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Accomplishment of the actions required by paragraph (j) of this AD terminates the requirements of this paragraph.
This paragraph restates the requirements of paragraphs (g) and (h) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008).
(1) Where Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, specifies a compliance time after the release date of that service bulletin, this AD requires compliance within the specified compliance time after June 25, 2008 (the effective date of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008)).
(2) Although Boeing Alert Service Bulletin 737-53A1200, dated April 13, 2006, specifies contacting Boeing for information about installing an optional preventive modification that would terminate the repetitive inspections specified in paragraph (g) of this AD, this AD requires that any terminating action be done by using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
This paragraph restates the optional terminating action specified paragraph (i) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008), with revised method of compliance language and removal of note 1 to paragraph (i) of this AD. The inspections specified in paragraph (g) of this AD may be terminated at areas repaired using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
Except as required by paragraph (l)(1) of this AD, at the applicable times specified in Paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Do an external and internal detailed inspection, HFEC inspection, and HFEC hole probe inspection, at the forward entry and galley service doorway upper and lower hinge cutouts for cracking in the skin, bonded doubler, bearstrap, and frame outer chord, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, except as required by paragraph (m) of this AD. Options provided in Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, for accomplishing the inspections are acceptable for compliance with the corresponding requirements of this paragraph. Repeat the applicable inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If any crack is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Accomplishment of the initial inspections terminates the requirements of paragraph (g) of this AD.
(1) For airplanes with any structural repair manual (SRM) repair specified in paragraphs (k)(1)(i) through (k)(1)(vii) of this AD installed, at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Do an external and internal detailed inspection, HFEC inspection, and LFEC inspection, at the forward entry and galley service doorway upper and lower hinge cutouts for cracking in the skin, bearstrap, and frame outer chord, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, except as required by paragraph (l)(2) of this AD. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If any crack is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
(i) Repair specified in Boeing 737-100/-200 SRM 53-30-03, Figure 21.
(ii) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 31.
(iii) Repair 5 specified in Boeing 737-300 SRM 53-10-01; Repair 5 specified in Boeing 737-400 SRM 53-10-01; or Repair 5 specified in Boeing 737-500 SRM 53-10-01; installed at the upper or lower hinge cutout.
(iv) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 20.
(v) Repair 6 specified in Boeing 737-300 SRM 53-10-01; Repair 6 specified in Boeing 737-400 SRM 53-10-01; or Repair 6 specified in Boeing 737-500 SRM 53-10-01.
(vi) Repair 8 specified in Boeing 737-300 SRM 53-10-01; Repair 8 specified in Boeing 737-400 SRM 53-10-01; or Repair 8 specified in Boeing 737-500 SRM 53-10-01.
(vii) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 32.
(2) For airplanes with any repair installed at the forward entry doorway or forward galley doorway, upper or lower hinge cutout, that does not meet the conditions specified in Note 10 of paragraph 3.A., “General Information,” of the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Except as required by paragraph (l) of this AD, at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, contact the Manager, Seattle ACO, FAA, for instructions, using the procedures specified in paragraph (p) of this AD, and do the actions required by the FAA.
(1) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, specifies a compliance time after the issue date of Boeing Service Bulletin 737-53A1200, Revision 1, dated July 7, 2011, this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, specifies to contact Boeing for further instructions, this AD requires contacting the Manager, Seattle Aircraft Certification Office (ACO), FAA, for instructions and doing the actions required by the FAA, using the procedures specified in paragraph (p) of this AD.
For Group 5 airplanes identified in Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Before further flight, contact the Manager, Seattle ACO, FAA, for instructions, using the procedures specified in paragraph (p) of this AD, and do the actions required by the FAA.
The inspections required by paragraph (j) of this AD may be terminated at areas with repairs installed prior to the effective date of this AD, provided the repairs meet the conditions specified in Note 10 of paragraph 3.A., “General Information,” of the Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012.
