Airworthiness Directive · Amendment 39-19835 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 737 series airplanes, certificated in any category, except for Model 737-100, -200, -200C, -300, -400, and -500 series airplanes.
(2) Installation of Supplemental Type Certificate (STC) ST00830SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a “change in product” alternative method of compliance (AMOC) approval request, per 14 CFR 39.17, is not necessary to comply with the requirements of this AD.
The FAA is adopting a new airworthiness directive (AD) for The Boeing Company Model 737 series airplanes, except for Model 737-100, - 200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of separation of the lower aft wing-to-body fairing panel 194E ("fairing panel 194E") during flight, due to worn or damaged nutplates on the support structure. This AD requires repetitive inspections for discrepancies of fairing panel 194E, wheel well panel 193D, and support structure, and related investigative and corrective actions if necessary. This AD also requires rework of the panels and support structure, which terminates the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For airplanes with an original airworthiness certificate or an original export certificate of airworthiness dated on or before the effective date of this AD, except as specified in paragraph (g)(2) of this AD: Within 24 months after the effective date of this AD, do a general visual inspection for discrepancies of fairing panel 194E, wheel well panel 193D, and support structure, and do all applicable related investigative and corrective actions, in accordance with Part 1 and Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012. All applicable related investigative and corrective actions must be done before further flight. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles.
(2) For airplanes having line numbers 3533 and subsequent that have not altered the type design since the issuance of an original airworthiness certificate or an original export certificate of airworthiness, an external visual inspection of fairing panel 194E and wheel well panel 193D may be used to verify the correct panel configuration, provided it can be determined that fairing panel 194E, wheel well panel 193D, and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012. If the external inspection shows that fairing panel 194E, wheel well panel 193D, and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, then the repetitive inspections required by paragraph (g)(1) of this AD are terminated.
(3) For airplanes having line numbers 3533 and subsequent with an original airworthiness certificate or an original export certificate of airworthiness dated on or before the effective date of this AD: If the initial inspection required by paragraph (g)(1) of this AD shows that fairing panel 194E, wheel well panel 193D, and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, then the repetitive inspections required by paragraph (g)(1) of this AD are terminated. The requirements of paragraph (i) of this AD continue to apply.
(4) Repairs to fairing panel 194E, wheel well panel 193D, or the support structure that do not affect the number or type of fasteners necessary for the post-reworked configuration may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the remaining requirements can be done and the airplane can be put back in an airworthy condition.
For airplanes with an original airworthiness certificate or an original export certificate of airworthiness dated on or before the effective date of this AD: Within 72 months after the effective date of this AD, do the actions required by paragraph (h)(1) or (2) of this AD, as applicable. Accomplishing the actions in paragraph (h)(1) or (2) of this AD terminates the repetitive inspections required by paragraph (g)(1) of this AD. The requirements of paragraph (i) of this AD continue to apply.
(1) Rework fairing panel 194E, wheel well panel 193D, and the support structure, including accomplishment of all applicable related investigative actions and repair, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012. All applicable related investigative actions and repairs must be done before further flight.
(2) Verify that fairing panel 194E, wheel well panel 193D, and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012.
(1) For airplanes with an original airworthiness certificate or an original export certificate of airworthiness dated after the effective date of this AD: As of the effective date of this AD, no person may install a fairing panel 194E on any airplane identified in paragraph (c) of this AD, unless fairing panel 194E, wheel well panel 193D, and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012.
(2) For airplanes with an original airworthiness certificate or an original export certificate of airworthiness dated on or before the effective date of this AD: As of the effective date of this AD, a fairing panel l94E with or without the post-reworked configuration may be installed on any airplane, provided that the repetitive inspections and all applicable related investigative and corrective actions required by paragraph (g)(1) of this AD are accomplished.
(3) For airplanes on which the terminating action required by paragraph (h) of this AD has been done: As of the effective date of this AD, no person may install a fairing panel 194E on any airplane identified in paragraph (c) of this AD unless fairing panel 194E, wheel well panel 193D and the support structure have the number and type of attachments specified in the post-reworked configuration of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012.
(1) If any action(s) in Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, cannot be accomplished as specified therein, those action(s) must be accomplished using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
(2) Where figure 5 of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, includes note (b), but does not specify what steps that note applies to, for this AD, apply note (b) to steps 8 and 10 of figure 5 of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012.
(3) Where note (a) to figure 5 of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, specifies to clean “per abrasive cleaning method CM5” and refers to “SWPM 20-20-00,” for this AD use “cleaning procedure 3” and refer to “SWPM 20-20-00.”
(4) Where note (a) to figure 5 of Boeing Special Attention Service Bulletin 737-53-1307, dated January 12, 2012, specifies to clean “per solvent cleaning method CM3,” and refers to “SWPM 20-20-00,” for this AD use “cleaning procedure 5” and refer to “SWPM 20-20-00.”
