Airworthiness directives › 2013-09-10
AD 2013-09-10 Airworthiness Directives; The Boeing Company Airplanes
Models named: 737-100, -200, -200C, -300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(1) This AD applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE ( http://rgl.faa.gov/regulatory_and_guidance_library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se ) 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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (a) of AD 2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000), with revised service information. Within 1 year or 4,500 flight cycles after May 16, 2000 (the effective date of AD 2000-07-06), whichever occurs later, perform an HFEC inspection to detect cracking of the lower corners (forward and aft) of the door frame of the forward cargo door, in accordance with Figure 4 or Figure 23, of Section 51-00-00, of Part 6, of Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, dated August 5, 1997, as applicable; or Procedure 4 or Procedure 23, of Section 51-00-00, of Part 6, of Boeing 737 Nondestructive Test (NDT) Manual, D6-37239, Revision 108, dated November 15, 2012; as applicable. Note 1 to paragraphs (g), (h), (i), and (j) of this AD: Accomplishment of Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31, 1994, does not supersede the requirements of AD 90-06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990). (1) If no cracking is detected, repeat the HFEC inspection thereafter at intervals not to exceed 4,500 flight cycles, until the requirements of paragraph (i) of this AD have been accomplished. (2) If any cracking is detected during any inspection required by paragraph (g) of this AD, prior to further flight, accomplish the requirements of paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, which constitute terminating action for the repetitive inspections required by paragraph (g)(1) of this AD. (i) Accomplish the requirements of paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this AD, and install a cross beam repair and reinforcement modification of the cross beam, in accordance with Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31, 1994. (A) Repair the door frame of the forward cargo door in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), Transport Airplane Directorate, FAA; or in accordance with data meeting the type certification basis of the airplane approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make such findings. For a repair or modification method to be approved by the Manager, Seattle ACO, as required by this paragraph, and paragraphs (g)(2)(ii), (h)(2), (h)(3)(ii), and (i)(2) of this AD, the Manager's approval letter must specifically reference this AD. (B) Replace the door frame of the forward cargo door with a new door frame, in accordance with Boeing Service Bulletin 737-52-1100, Revision 2, dated March 31, 1994. (ii) Modify the repaired or replaced door frame of the forward cargo door, in accordance with a method approved by the Manager, Seattle ACO, or in accordance with data meeting the type certification basis of the airplane approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Seattle ACO, to make those findings.
Unsafe condition
This AD was prompted by additional reports of fatigue cracking in the radius of the lower frames and in the lower number 5 cross beam of the forward cargo door. We are issuing this AD to prevent fatigue cracking of the lower corners of the door frame and number 5 cross beam of the forward cargo door, which could result in rapid depressurization of the airplane.
Affected ADs
This AD supersedes AD 2000-07-06, Amendment 39-11660 (65 FR 19302, April 11, 2000).
Read the original on the Federal Register →
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