Airworthiness Directive · Amendment 39-17775 · Fuselage
The Boeing Company Airplanes
Superseded. A later AD replaced this one: AD 2014-18-02. Comply with the one in force.
(1) This AD applies to The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category, line numbers 1 through 3132 inclusive.
(2) Installation of Supplemental Type Certificate (STC) ST01920SE (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 ST01920SE 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 superseding Airworthiness Directive (AD) 2002-10-11, which applied to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2002-10-11 required repetitive inspections for cracking and corrosion of the aft pressure bulkhead, and corrective actions if necessary; and, for certain airplanes, enlargement of frame chord drain holes, and repetitive inspections of the frame chord drain path for debris, and corrective actions if necessary. This new AD specifies a drain path inspection for all airplanes. For certain airplanes, this new AD reduces the repetitive inspection interval; and adds repetitive inspections of the frame chord drain path for obstructions and debris, and corrective actions if necessary. This AD was prompted by three reports of severe corrosion in the area affected by AD 2002-10-11. We are issuing this AD to detect and correct corrosion or cracking of the aft pressure bulkhead, which could result in loss of the aft pressure bulkhead web and stiffeners, and consequent rapid decompression of the airplane.
This paragraph restates the requirements of paragraph (a) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with clarification of the drain path inspection. For Model 737 series airplanes having line numbers (L/N) 1 through 929 inclusive, with more than 20,000 hours time-in-service or 7 years since date of manufacture, whichever occurs first: Within 120 days after January 20, 1986 (the effective date of AD 84-20-03 R1, Amendment 39-5183 (50 FR 51235, December 16, 1985)), unless already accomplished within 21 months before January 20, 1986, visually inspect the body station (BS) 1016 pressure bulkhead, including inspecting for cracking and corrosion of the pressure bulkhead, and for debris in the drain path in the chord frame, according to Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision 2, dated July 13, 1984; or Revision 3, dated June 8, 2000. Remove any obstruction to the drain hole in the frame chord and replace any deteriorated leveling compound as noted in Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision 2, dated July 13, 1984; or Revision 3, dated June 8, 2000. Treat the area of inspection with corrosion inhibitor BMS 3-23, or equivalent. After the effective date of this AD, use only Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, to do the actions required by this paragraph.
This paragraph restates the requirements of paragraph (b) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised service bulletin requirements. For airplanes identified in paragraph (g) of this AD: Within 1 year after January 20, 1986 (the effective date of AD 84-20-03 R1, Amendment 39-5183 (50 FR 51235, December 16, 1985)), accomplish the drain hole enlargement as shown in Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision 2, dated July 13, 1984; or Revision 3, dated June 8, 2000. After the effective date of this AD, use only Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, to do the actions required by this paragraph.
This paragraph restates the requirements of paragraph (c) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised compliance methods. If cracking or corrosion is found during any inspection required by paragraph (g) or (j) of this AD: Before further flight, repair according to paragraph (i)(1) or (i)(2) of this AD, as applicable.
(1) If the inspection was done before the effective date of this AD: Repair according to Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision 2, dated July 13, 1984; or Revision 3, dated June 8, 2000; or according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(2) If the inspection was done on or after the effective date of this AD: Repair using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
This paragraph restates the requirements of paragraph (d) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised actions. For airplanes identified in paragraph (g) of this AD: Repeat the visual inspections and corrosion inhibitor treatment specified in paragraph (g) of this AD at intervals not to exceed 2 years. Accomplishment of the initial aft pressure bulkhead inspection required by paragraph (k) of this AD terminates the inspection required by this paragraph.
This paragraph restates the requirements of paragraph (e) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised terminating action. Do a detailed inspection for cracking or corrosion of the aft pressure bulkhead at BS 1016 (including the forward and aft sides of the pressure web, forward and aft sides of the pressure chord, pressure chord radius, forward and aft sides of the angle stiffener, forward and aft chord, stringer end fitting, system penetration doublers, channel stiffeners and fasteners, “Z” stiffeners and fasteners, and fasteners common to the pressure chord and pressure web), according to Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. Do this inspection at the applicable time shown in paragraph (k)(1), (k)(2), or (k)(3) of this AD.
(1) For airplanes on which an inspection has previously been done according to the requirements of paragraph (g) of this AD: Do the inspection within 2 years since the most recent inspection according to paragraph (g) or (j) of this AD, as applicable. For the airplanes identified in paragraph (g) of this AD, accomplishment of the inspection required by paragraph (k) of this AD terminates the inspections for cracking and corrosion required by paragraph (j) of this AD.
(2) For airplanes having L/Ns 930 through 1042 inclusive, on which an inspection has not previously been done according to paragraph (g) of this AD: Do the inspection within 2 years after June 27, 2002 (the effective date AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002)).
(3) For airplanes having L/Ns 1043 through 3132 inclusive, on which an inspection has not previously been done according to paragraph (g) of this AD: Do the inspection within 6 years since the airplane's date of manufacture, or within 2 years after June 27, 2002 (the effective date AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002)), whichever occurs later.
This paragraph restates the requirements of paragraph (f) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised compliance times. Repeat the inspection in paragraph (k) of this AD at the applicable time shown in paragraph (l)(1) or (l)(2) of this AD.
(1) For airplanes having L/Ns 1 through 1042 inclusive: Repeat the inspection thereafter at intervals not to exceed 2 years.
(2) For airplanes having L/Ns 1043 through 3132 inclusive: Repeat the inspection thereafter within 2 years since the last inspection or within 120 days after the effective date of this AD, whichever occurs later.
This paragraph restates the requirements of paragraph (g) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with revised repair requirements. If any corrosion or cracking is found during any inspection according to paragraph (k) or (l) of this AD: Do the applicable action specified in paragraph (m)(1) or (m)(2) of this AD.
(1) If the inspection was done prior to the effective date of this AD: Before further flight, repair according to Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. Exception: If corrosion or cracking of the web and stiffeners is outside the limits specified in Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, or if corrosion or cracking is found in any structure not covered by the repair instructions in Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, before further flight, repair according to a method approved by the Manager, Seattle ACO, or per data meeting the type certification basis of the airplane approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
(2) On or after the effective date of this AD, if any corrosion or cracking is found during any inspection required by this AD: Before further flight, repair the corrosion or cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD.
For airplanes having L/N 1 through 3132 inclusive: Within 2 years since the last inspection in accordance with paragraph (k) of this AD or within 2 years after the effective date of this AD, whichever occurs later: Do a general visual inspection of the drain path in the chord frame for debris, in accordance with Figure 2, Steps 1 through 6, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. Remove any obstruction to the drain hole in the frame chord and replace any deteriorated leveling compound. Treat the area of inspection with corrosion inhibitor BMS 3-23, or equivalent, as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. Repeat the actions required by this paragraph at intervals not to exceed 2 years. Do all actions required by this paragraph in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. For the purposes of this AD, a general visual inspection is a visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.
For airplanes having L/Ns 1043 through 3132 inclusive: In lieu of performing the first inspection after the effective date of this AD required by paragraph (l)(2) of this AD, operators may do the actions specified in this paragraph. Within 2 years from the most recent aft pressure bulkhead inspection done as specified in the service information identified in paragraph (o)(1), (o)(2), or (o)(3) of this AD, or within 120 days after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking or corrosion of the aft side of the aft pressure bulkhead at BS 1016 (including the aft sides of the pressure web, aft sides of the pressure chord, pressure chord radius, aft chord, stringer end fitting, system penetration doublers, and fasteners common to the pressure chord and pressure web), in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000. If any corrosion or cracking is found: Before further flight, repair the corrosion or cracking using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Repeat the inspection thereafter at intervals not to exceed 90 days for a period not to exceed 2 years, until the actions required by paragraph (l)(2) of this AD are accomplished.
(1) Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated September 2, 1983.
(2) Boeing Alert Service Bulletin 737-53A1075, Revision 2, dated July 13, 1984.
(3) Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000.
