AD 2001-06-02 Airworthiness Directives; McDonnell Douglas Model DC-8 Series Airplanes

Models named: DC-8 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-8 series airplanes, as listed in McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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) 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 prevent reduced structural integrity of the left or right wing due to metal fatigue failure of the front spar lower cap, accomplish the following: Note 2: This AD will affect the inspections, corrective actions, and reports required by AD 93-01-15, amendment 39-8469 (58 FR 5576, January 22, 1993), for Principal Structural Elements (PSE) 57.08.021 and 57.08.022 of the DC-8 Supplemental Inspection Document (SID). Note 3: Where there are differences between this AD and the referenced service bulletin, the AD prevails. Eddy Current Inspection (a) For Model DC-8-10 through DC-8-50, inclusive, DC-8-61, -61F, -71, and -71F series airplanes, equipped with left or right wing front spar lower cap, part number (P/N) 5597838-1 or -2; not modified per any of the McDonnell Douglas DC-8 service bulletins listed in Table 1 of this AD: Do an eddy current inspection to detect cracks of the lower front spar caps of the wings at the attachment holes of the leading edge assembly between stations Xfs=515.000 and Xfs=526.760, per McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997; at the time specified in either paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable. Table 1 is as follows: Table 1.—Applicable Service Bulletins for Preventative Modification. Service bulletin Revision level Date 57-90 Original Oct. 3, 1983. 57-90 1 June 16, 1988. 57-90 2 March 1, 1991. 57-90 3 March 25, 1992. 57-90 4 March 3, 1995. DC8-57-090 05 June 16, 1997. Note 4: Eddy current inspections done before the effective date of this AD per McDonnell Douglas DC-8 Service Bulletin 57-90, Revision 1, dated June 16, 1988; Revision 2, dated March 1, 1991; Revision 3, dated March 25, 1992; or Revision 4, dated March 3, 1995; are considered acceptable for compliance with the requirements of paragraph (a) of this AD. (1) For airplanes on which the immediately preceding inspection was conducted using eddy current techniques per AD 86-20-08 before the effective date of this AD: Inspect within 3,600 flight hours or 3 years after accomplishment of the last eddy current inspection, whichever occurs first. (2) For airplanes on which the immediately preceding inspection was conducted visually per AD 86-20-08 before the effective date of this AD: Inspect within 3,200 flight hours or 2 years after accomplishment of the last visual inspection, whichever occurs first. (3) For airplanes on which a visual or eddy current inspection or the modification required by AD 86-20-08 has not been done: Inspect before the accumulation of 30,000 total flight hours, or within 200 flight hours after the effective date of this AD. (b) For airplanes other than those identified in paragraph (a) of this AD; not modified per any of the McDonnell Douglas DC-8 service bulletins listed in Table 1 of this AD: Within 3,200 flight hours or 2 years after the effective date of this AD, whichever occurs first, do the eddy current inspection specified in paragraph (a) of this AD. Repetitive Inspections (c) If no crack is detected during any inspection required by this AD, repeat the eddy current inspection every 3,600 flight hours or 3 years, whichever occurs first. Repair (d) If any crack is detected during any inspection required this AD, before further flight, do the action specified in either paragraph (d)(1) or (d)(2) of this AD, as applicable. (1) For cracks within the limits specified in Conditions 2 through 6, inclusive, Table 1 of paragraph 3.B.4 of the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997: Modify the lower front spar cap per McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997. Accomplishment of the modification constitutes compliance with the requirements paragraphs (c) and (e) of this AD. (2) For cracks that exceed the limits specified in Conditions 2 through 6, inclusive, Table 1 of paragraph 3.B.4 of the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997: Repair per a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Preventative Modification (e) Before the accumulation of 100,000 total flight hours, modify the lower front spar cap per paragraph 3.B.2.B of the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997. Accomplishment of the modification constitutes compliance with the requirements paragraphs (a) and (b) of this AD and terminates the repetitive inspection requirements of paragraph (c) of this AD. Note 5: Modification of the lower front spar cap accomplished before the effective date of this AD per McDonnell Douglas DC-8 Service Bulletin 57-90, dated October 3, 1993; Revision 1, dated June 16, 1988; Revision 2, dated March 1, 1991; Revision 3, dated March 25, 1992; or Revision 4, dated March 3, 1995; is considered acceptable for compliance with the requirements of paragraph (e) of this AD. (f) Accomplishment of the modification required by paragraph B. of AD 90-16-05, amendment 39-6614 (55 FR 31818, August 6, 1990) (which references “DC-8 Aging Aircraft Service Action Requirements Document” (SARD), McDonnell Douglas Report MDC K1579, Revision A, dated March 1, 1990, as the appropriate source of service information for accomplishing the modification) constitutes compliance with paragraphs (a), (b), and (e) of this AD and terminates the repetitive inspection requirements of paragraph (c) of this AD. Follow-On Inspection (g) Within 32,900 flight hours after accomplishment of the modification specified in paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this AD, or within 2 years after the effective date of this AD, whichever occurs later, perform an inspection to detect cracks in the area specified in paragraph (a) of this AD, and corrective actions, if necessary; per a method approved by the Manager, Los Angeles ACO. (1) Modification required by paragraph (d)(1) of this AD; (2) Modification required by paragraph (e) of this AD; (3) Modification specified in paragraph D. of AD 86-20-08; or (4) Modification required by paragraph B. of AD 90-16-05. Certain Actions Constitute Compliance With AD 90-16-05 (h) Accomplishment of the eddy current inspection(s) required by this AD constitutes compliance with the inspections required by paragraph A. of AD 90-16-05, as it pertains to McDonnell Douglas DC-8 Service Bulletin 57-90, Revision 2, dated March 1, 1991. Accomplishment of the eddy current inspection(s) does not terminate the remaining requirements of AD 90-16-05, as it applies to other service bulletins. Operators are required to continue to inspect and/or modify per the other service bulletins listed in that AD. Alternative Methods of Compliance (i) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles 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. Note 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (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) Except as provided by paragraphs (d)(2) and (g) of this AD, the actions shall be done in accordance with McDonnell Douglas Service Bulletin DC8-57-090, Revision 05, dated June 16, 1997. This incorporation by reference was approved 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: Technical Publications Business Administration, Dept. C1-L51 (2-60). Copies may be inspected at the FAA, 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 April 27, 2001. Issued in Renton, Washington, on March 12, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-6645 Filed 3-22-01; 8:45 am] BILLING CODE 4910-13-U