Airworthiness Directive · Amendment 39-18515 · Fuselage
The Boeing Company Airplanes
(1) 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 Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracked antenna support channels, skin cracking underneath the number 2 very high frequency (VHF) antenna, and cracking in the frames attached to the internal support structure. This AD requires repetitive inspections to determine the condition of the skin and the internal support structure, and follow-on actions including corrective action as necessary. We are issuing this AD to detect and correct skin cracking of the fuselage. Such cracking could result in separation of the number 2 VHF antenna from the airplane and rapid depressurization of the cabin.
For airplanes identified as Group 1 in Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: Within 120 days after the effective date of this AD, inspect for cracking at the number 2 VHF antenna location, and do all applicable follow-on actions, using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
For airplanes identified as Groups 2 through 6, Configurations 1 through 3 in Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: Within 1,250 flight cycles after the effective date of this AD, do an external detailed inspection for cracking of the fuselage skin, as applicable, and do all applicable corrective actions, in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014. Thereafter, at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as required by paragraph (l)(1) of this AD: Do all applicable actions specified in paragraphs (h)(1) through (h)(4) of this AD.
(1) Repeat the Part 1 inspections specified in paragraph (h) of this AD until the accomplishment of paragraph (k)(1), (k)(2), or (k)(3) of this AD, as applicable.
(2) Inspect for cracking at the number 2 VHF antenna location using internal and external detailed inspections, internal and external high frequency eddy current (HFEC) inspections, and an HFEC open-hole inspection, as applicable, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014. Repeat the inspections until the accomplishment of paragraph (k)(2) or (k)(3) of this AD, as applicable.
(3) Repair any crack found, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as required by paragraph (l)(2) of this AD.
(4) Do a preventive modification, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as specified in paragraph (l)(2) of this AD. The accomplishment of this preventive modification terminates the inspections required by paragraphs (h), (h)(1), and (h)(2) of this AD.
For airplanes identified as Groups 3 through 6, Configuration 4, in Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014: At the applicable time specified in table 10 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, except as required by paragraph (l)(1) of this AD, do an external detailed inspection for cracking at the outer row of fasteners common to the internal repair doubler, and do an internal general visual inspection for cracking on the modified internal support structure of the number 2 VHF antenna, skin, and surrounding stringers, channel, and frames, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(1) If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(2) If no cracking is found, repeat the inspections at the time specified in table 10 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
Tables 7 through 9 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, specify post-repair and post-modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the repaired and modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance.
The following describes terminating action for the airplane groups and configurations, as identified in Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014.
(1) For airplanes in Group 2, Configuration 2; and Groups 3 through 6, Configuration 2: Accomplishment of the inspections specified in paragraph (h)(2) of this AD terminates the repetitive inspection requirements of paragraph (h)(1) of this AD.
(2) For airplanes in Group 2, Configuration 1; and Groups 3 through 6, Configurations 1, 2, and 3: Accomplishment of the repair specified in paragraph (h)(3) of this AD terminates the initial and repetitive inspections specified in paragraphs (h), (h)(1), and (h)(2) of this AD.
(3) For airplanes in Group 2, Configuration 1; and Groups 3 through 6, Configurations 1 and 3: Accomplishment of the preventive modification specified in paragraph (h)(4) of this AD terminates the initial and repetitive inspections specified in paragraphs (h), (h)(1), and (h)(2) of this AD.
(1) Where Boeing Special Attention Service Bulletin 737-53-1159, Revision 1, dated October 20, 2014, specifies a compliance time “after the Revision 1 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 737-53-1159, Revision 1, dated October 20, 2014, specifies to contact Boeing for appropriate action, and specifies that action as “RC” (Required for Compliance): Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
