Airworthiness Directive · Amendment 39-17362 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracks in the skin and surrounding structure under the number 3 very high frequency (VHF) antenna on the lower external surface of the airplane at buttock line 0.0, aft of the main landing gear wheel well. This AD requires inspecting for cracking and corrosion under the number 3 VHF antenna, and corrective actions if necessary; and, for certain airplanes, replacing bonded skin panels with solid skin panels if not previously accomplished. This AD also provides an optional preventive modification (which would terminate the inspection requirements for certain airplanes). We are issuing this AD to detect and correct cracks and corrosion of the skin and surrounding structure under the number 3 VHF antenna, which could result in separation of the antenna from the airplane, and rapid depressurization of the airplane.
Except as required by paragraph (j)(1) of this AD, at the applicable times specified in tables 1 through 9 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010: Do the applicable inspections (external detailed; external high frequency eddy current (HFEC); and internal detailed and HFEC) for cracks and corrosion in the skin, support, frames, stringers, or antenna, as applicable. Do the inspections in accordance with Parts 1, 3, 4, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, except as required by paragraphs (j)(2) and (j)(3) of this AD. Repeat the applicable inspections thereafter at the applicable times specified in tables 1 through 9 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, until the actions specified in paragraph (k) of this AD are done.
If any crack or corrosion is found during any inspection required by paragraph (g) of this AD: Repair before further flight, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, except as required by paragraphs (j)(2) and (j)(3) of this AD. Repair of any crack or corrosion terminates the repetitive inspection requirements of paragraph (g) of this AD for the repaired area only.
The post-repair/modification inspections specified in Part 8 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, are not required by this AD.
Note 1 to paragraph (i) of this AD: The damage tolerance inspections specified in Part 8 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The actions specified in Part 8 of the Accomplishment Instructions and corresponding figures of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, are not required by this AD.
(1) Where Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, 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) Where Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, specifies contacting Boeing for inspection or repair instructions: Do the applicable action using a method approved in accordance with the procedures specified in paragraph (n) of this AD.
(3) For Group 7 airplanes, as identified in paragraph 1.A., “Effectivity,” of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010: Use the applicable instructions for Group 2, Configuration 1, 2, or 3 airplanes, as identified in Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010.
For Groups 1, 2, 3, 4, 6, and 7 airplanes, as identified in Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010: Except as provided by paragraphs (j)(2) and (j)(3) of this AD, accomplishment of the preventive modification, including all applicable HFEC and detailed inspections for cracking or corrosion inside or outside the repair skin cutout area, in the frame fastener holes, or in the support channel; and all applicable repairs or replacements; as specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010, terminates the repetitive inspection requirements of paragraph (g) of this AD.
For Groups 2 and 7 airplanes, as identified in Boeing Special Attention Service Bulletin 737-53-1287, Revision 1, dated November 15, 2010: Before or concurrently with accomplishing the requirements of paragraph (g) of this AD, do the replacement of the bonded skin panels with solid skin panels, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737-53A1042, Revision 9, dated July 25, 1991, except as required by paragraph (j)(3) of this AD. The actions specified in paragraph (l) of this AD are also required by AD 90-06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990).
