AD 98-26-22 Airworthiness Directives; McDonnell Douglas Model DC-10 Series Airplanes and KC-10A (Military) Airplanes

Models named: DC-10 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-10 series airplanes and KC-10A (military) airplanes, as listed in McDonnell Douglas Alert Service Bulletin DC10-57A137, dated July 31, 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 (d) 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 cracking of the lower cap of the wing rear spar, which could result in reduced structural integrity of the airplane, accomplish the following: (a) Conduct an eddy current surface inspection to detect cracking of the lower cap of the wing rear spar, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin DC10-57A137, dated July 31, 1997, or Revision 01, dated May 26, 1998; at the later of the times specified in paragraphs (a)(1) and (a)(2) of this AD. Thereafter, repeat this inspection at intervals not to exceed 1,500 landings, except as provided by paragraph (c) of this AD. (1) Prior to the accumulation of 7,000 total landings, or within 18 months after the effective date of this AD, whichever occurs later. Or (2) Within 1,500 landings after the accomplishment of the inspection of Principal Structural Elements 57.10.007 and 57.10.008, in accordance with AD 95-23-09, amendment 39-9429. (b) If any crack is found during any inspection required by paragraph (a) of this AD, accomplish paragraph (b)(1) or (b)(2) of this AD, as applicable. (1) Except as provided by paragraph (c) of this AD, for any crack identified in Condition 2 or Condition 3 of McDonnell Douglas Alert Service Bulletin DC10-57A137, Revision 01, dated May 26, 1998: Prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate; or accomplish the permanent repair of the spar cap in accordance with Revision 01 of the alert service bulletin, and repeat the eddy current surface inspection required by paragraph (a) of this AD thereafter at the times specified in Revision 01 of the alert service bulletin for that repaired spar cap. (2) For any crack identified in Condition 4 of McDonnell Douglas Alert Service Bulletin DC10-57A137, Revision 01, dated May 26, 1998: Accomplish either paragraph (b)(2)(i), or paragraphs (b)(2)(ii) and (b)(2)(iii) of this AD. (i) Prior to further flight, repair in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (ii) Prior to further flight, temporarily repair the spar cap in accordance with Revision 01 of the alert service bulletin. Repeat the eddy current surface inspection required by paragraph (a) of this AD thereafter at the applicable times specified in the alert service bulletin for that repaired spar cap, until accomplishment of paragraph (b)(3)(iii) of this AD. (iii) At the applicable time specified in the alert service bulletin, permanently repair the crack in accordance with Revision 01 of the alert service bulletin. Accomplishment of the permanent repair constitutes terminating action for the repetitive eddy current surface inspection requirements of paragraph (b)(2)(ii) of this AD. Within 10,000 landings following accomplishment of the permanent repair, repeat the eddy current surface inspection required by paragraph (a) of this AD thereafter at the applicable times specified in Revision 01 of the alert service bulletin for that permanently repaired spar cap. (c) For airplanes on which no crack (Condition 1) or any crack that is specified in Condition 2 of McDonnell Douglas Alert Service Bulletin DC10-57A137, Revision 01, dated May 26, 1998, is detected: Accomplishment of the preventative modification specified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD, in accordance with Revision 01 of the alert service bulletin, constitutes terminating action for the repetitive inspection requirements of paragraph (a) of this AD. (1) Remove existing sealant as required. (2) Remove affected taper-lok fasteners. (3) Ream holes to remove taper. (4) Cold work affected holes. (5) Perform an eddy current inspection using the open hole technique to detect cracks inside the holes. If any crack is detected, prior to further flight, repair in accordance with a method approved by Manager, Los Angeles ACO. (6) Install new fasteners. (d) 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. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (e) Special flight permits may be issued in accordance with sections 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. (f) Certain actions shall be done in accordance with McDonnell Douglas Alert Service Bulletin DC10-57A137, dated July 31, 1997, or McDonnell Douglas Alert Service Bulletin DC10-57A137, Revision 01, dated May 26, 1998. 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, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, 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. (g) This amendment becomes effective on February 2, 1999. Issued in Renton, Washington, on December 17, 1998. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-34095 Filed 12-28-98; 8:45 am] BILLING CODE 4910-13-P