AD 99-08-22 Airworthiness Directives; McDonnell Douglas Model DC-10 Series Airplanes and KC-10 (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-10 (military) airplanes, as listed in McDonnell Douglas Alert Service Bulletin DC10-55A028, dated April 27, 1998; 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 (c) 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 fatigue cracking of the rear spar cap of the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer, and consequent reduced controllability of the airplane, accomplish the following: (a) Prior to the accumulation of 18,000 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later: Perform a penetrant inspection or a high frequency eddy current inspection to detect fatigue cracking of the rear spar cap of the horizontal stabilizer, in accordance with McDonnell Douglas Alert Service Bulletin DC10-55A028, dated April 27, 1998. Note 2: Accomplishment of a penetrant inspection or a high frequency eddy current inspection to detect fatigue cracking of the rear spar cap of the horizontal stabilizer, in accordance with McDonnell Douglas Comtwx DC-10-COM-0047/SFY, dated December 11, 1997, prior to the effective date of this AD, is acceptable for compliance with the initial inspection requirements required by paragraph (a) of this AD. (1) If no cracking is detected, repeat the inspection thereafter at intervals not to exceed 2,200 landings until accomplishment [[Page 18804]] of the requirements of paragraph (b) of this AD. (2) If any cracking is detected, prior to further flight, repair in accordance with the alert service bulletin. Repeat the inspection thereafter at intervals not to exceed 2,200 landings until accomplishment of the requirements of paragraph (b) of this AD. (b) Within 5 years after the effective date of this AD or prior to the accumulation of 18,000 total landings, whichever occurs later: Perform a penetrant inspection or a high frequency eddy current inspection to detect fatigue cracking of the rear spar cap of the horizontal stabilizer, in accordance with McDonnell Douglas Alert Service Bulletin DC10-55A028, dated April 27, 1998. (1) If no cracking is detected, prior to further flight, perform the preventive modification of the rear spar cap of the horizontal stabilizer, in accordance with the alert service bulletin. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (2) If any cracking is detected, prior to further flight, repair, and perform the preventive modification of the rear spar cap of the horizontal stabilizer, in accordance with the alert service bulletin. Accomplishment of the modification constitutes terminating action for the requirements of this AD. Alternative Methods of Compliance (c) 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 Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. 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 3: 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 (d) 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. Incorporation by Reference (e) The actions shall be done in accordance with McDonnell Douglas Alert Service Bulletin DC10-55A028, dated April 27, 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 The Boeing Company, Douglas Products 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. (f) This amendment becomes effective on May 21, 1999. Issued in Renton, Washington, on April 7, 1999. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-9253 Filed 4-15-99; 8:45 am] BILLING CODE 4910-13-P