AD 2002-07-06 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; and C-9 Airplanes

Models named: DC-9-10, -20, -30, -40, -50 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 airplanes; certificated in any category; equipped with a floor level hinged (ventral) door of the aft pressure bulkhead; as listed in McDonnell Douglas Service Bulletin DC9-53-137, Revision 07, dated February 6, 2001; except for those airplanes on which the modification required by paragraph (d) or (e) of AD 96-10-11, amendment 39-9618, or paragraph K. of AD 85-01-02 R1, amendment 39-5241, has been done. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (i)(1) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To detect and correct fatigue cracks in the corners and upper center of the door cutout of the aft pressure bulkhead, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane, accomplish the following: Visual and X-Ray Inspection (a) For airplanes on which the modification has NOT been accomplished per paragraph (g) of this AD: Except as provided by paragraph (h) of this AD, prior to the accumulation of 15,000 total landings, or within 4,000 landings after the effective date of this AD, whichever occurs later, do a visual inspection and an x-ray inspection to detect cracks of the upper and lower corners and upper center of the door cutout of the aft pressure bulkhead, per McDonnell Douglas Service Bulletin DC9-53-137, Revision 07, dated February 6, 2001. No Crack Detected: Repetitive Inspections (b) If no crack is detected during any inspection required by paragraph (a) of this AD, do the action specified in either paragraph (b)(1) or (b)(2) of this AD per paragraph 3.B. “Work Instructions” of McDonnell Douglas Service Bulletin DC9-53-137, Revision 07, dated February 6, 2001, as applicable: (1) If interim preventive repairs have been performed per the service bulletin; AD 85-01-02 R1 or AD 96-10-11: Do a visual inspection and an eddy current inspection at the times specified in the service bulletin. Repeat the applicable repetitive inspections at intervals not to exceed the times specified in the service bulletin, until accomplishment of the action required by paragraph (d) or (g) of this AD; or (2) If interim preventive repairs have NOT been performed per the service bulletin, do either paragraph (b)(2)(i) or (b)(2)(ii) of this AD: (i) Before further flight, install an interim preventive repair identified in Conditions I through XLIII inclusive, excluding Conditions XXI, XXXVII, and XXXVIII (not used at this time), per the service bulletin. At the times specified in the service bulletin, do a visual inspection and an eddy current inspection. At intervals not to exceed the times specified in the service bulletin, repeat the visual and eddy current inspections until accomplishment of the action specified in paragraph (d) or (g) of this AD; or (ii) At intervals not to exceed the times specified in the service bulletin, repeat the visual inspection and x-ray inspection required by paragraph (a) of this AD, until accomplishment of the action specified in paragraph (d) or (g) of this AD. Any Crack Detected: Corrective Actions and Repetitive Inspections (c) If any crack is detected during any inspection required by paragraph (a) or (b) of this AD, do the actions specified in paragraphs (c)(1) and (c)(2) of this AD per McDonnell Douglas Service Bulletin DC9-53-137, Revision 07, dated February 6, 2001. (1) Before further flight, do the applicable corrective actions (i.e., modification of the bulkhead; trim forward facing flange; stop drill ends of cracks; install repair kit; replacement of cracked part with new parts; and install additional doublers) identified in Conditions I through XLIII inclusive, excluding Conditions XXI, XXXVII, and XXXVIII (not used at this time), of the Accomplishment Instructions of the service bulletin; and (2) At the times specified in the Accomplishment Instructions of the service bulletin, do the applicable repetitive inspections, until accomplishment of the action specified in paragraph (d) or (g) of this AD. Concurrent Requirements (d) Except as provided by paragraph (h) of this AD, modify the ventral aft pressure bulkhead structure by accomplishing all actions specified in the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 53-165, Revision 3, dated May 3, 1989, per the service bulletin; at the applicable time specified in paragraph (d)(1), (d)(2), or (d)(3) of this AD. Note 2: Modification before the effective date of this AD per McDonnell Douglas DC-9 Service Bulletin 53-165, dated January 31, 1983; Revision 1, dated February 20, 1984; or Revision 2, dated August 29, 1986; is considered acceptable for compliance with the requirements of paragraph (d) of this AD. (1) For airplanes on which the bulkhead modification specified in McDonnell Douglas DC-9 Service Bulletin 53-139, dated September 26, 1980, or Revision 1, dated April 30, 1981, has been done, except as provided by paragraph (d)(3) of this AD: Modify within 15,000 landings after accomplishment of the bulkhead modification, or within 4,000 landings after the effective date of this AD, whichever occurs later. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (b) and (c)(2) of this AD. (2) For airplanes on which the production equivalent of the modification specified in paragraph (d)(1) of this AD has been done before delivery, except as provided by paragraph (d)(3) of this AD: Modify before the accumulation of 15,000 total landings, or within 4,000 landings after the effective date of this AD, whichever occurs later. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (b) and (c)(2) of this AD. (3) For airplanes listed in McDonnell Douglas DC-9 Service Bulletin 53-165, Revision 3, dated May 3, 1989, that are specified in paragraph (e) of this AD: Modify in conjunction with the requirements of paragraph (e) of this AD, or within 18 months after accomplishment of the requirements of paragraph (e) of this AD. Modification: Ventral Aft Pressure Bulkhead (e) For Model DC-9-30 and “50 series airplanes, and C-9 airplanes, as listed in McDonnell Douglas DC-9 Service Bulletin 53-157, Revision 1, dated January 7, 1985: Except as provided by paragraph (h) of this AD, within 18 months after the effective date of this AD, modify the ventral aft pressure bulkhead per the service bulletin. Note 3: Modification before the effective date of this AD per McDonnell Douglas DC-9 Service Bulletin 53-157, dated August 11, 1981, is considered acceptable for compliance with the requirements of paragraph (e) of this AD. Compliance with AD 85-01-02 R1 (f) Accomplishment of the visual and x-ray inspections required by paragraph (a) of this AD constitutes terminating action for the repetitive inspection requirements of AD 85-01-02 R1. Terminating Modification (g) Accomplishment of the modification (reference McDonnell Douglas DC-9 Service Bulletin 53-166) required by paragraph (d) or (e) of AD 96-10-11 (which references “DC-9/MD-80 Aging Aircraft Service Action Requirements Document” (SARD), McDonnell Douglas Report No. MDC K1572, Revision A, dated June 1, 1990; or Revision B, dated January 15, 1993; as the appropriate source of service information for accomplishing the modification) terminates the repetitive inspection requirements of paragraphs (b) and (c) of this AD. Exception to Inspections and Modifications (h) As of the effective date of this AD, the inspections and modifications required by this AD do NOT need to be done during any period that the airplane is operated without cabin pressurization and a placard is installed in the cockpit in full view of the pilot that states the following: “OPERATION WITH CABIN PRESSURIZATION IS PROHIBITED.” Alternative Methods of Compliance (AMOC) (i)(1) An AMOC or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. (2) AMOCs approved previously in accordance with AD 85-01-02 R1, amendment 39-4978; or AD 96-10-11, amendment 39-9618; are approved as AMOCs for paragraph (a) or (c) of this AD, as appropriate. (3) An AMOC for any inspection required by paragraph (a) or (c) of this AD that provides an acceptable level of safety may be used per data meeting the type certification basis of the airplane approved by a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Los Angeles ACO, to make such findings. Note 4: Information concerning the existence of approved AMOCs with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permit (j) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (k) The actions shall be done in accordance with McDonnell Douglas Service Bulletin DC9-53-137, Revision 07, dated February 6, 2001; McDonnell Douglas DC-9 Service Bulletin 53-165, Revision 3, dated May 3, 1989; and McDonnell Douglas DC-9 Service Bulletin 53-157, Revision 1, dated January 7, 1985; as applicable. This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (l) This amendment becomes effective on May 14, 2002. Issued in Renton, Washington, on March 28, 2002. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-8279 Filed 4-8-02; 8:45 am] BILLING CODE 4910-13-P