Airworthiness directives › 2001-16-12
AD 2001-16-12 Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, -30, and -30F (KC-10A Military) Series Airplanes, and Model MD-10-10F and -30F Series Airplanes
Models named: Excluding, MD-10-10F series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
The following airplanes, certificated in any category: Model Excluding airplanes 1. DC-10-30 and -30F (KC-10A military) series airplanes, and MD-10-30F series airplanes On which bolt retainers have been installed on the engine mount per McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992, or on which the modification specified in McDonnell Douglas Service Bulletin DC10-71-159, dated September 6, 1995, or Revision 01, dated July 28, 1997, has been performed. 2. DC-10-10 and -15 series airplanes, and Model MD-10-10F series airplanes On which the modification specified in McDonnell Douglas Service Bulletin DC10-71-159, dated September 6, 1995, or Revision 01, dated July 28, 1997, 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 (d)(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.
Compliance
Required as indicated, unless accomplished previously. To prevent broken lockwires, which could result in loosening of the engine mount bolts, and consequent separation of the engine from the airplane, accomplish the following: Restatement of Requirements of AD 95-04-07 R2, Amendment 39-11354 (a) Within 120 days after March 17, 1995 (the effective date of AD 95-04-07 R1, amendment 39-9317), unless accomplished previously within the last 750 flight hours prior to March 17, 1995, perform a visual inspection to detect broken lockwires on the forward engine mount bolts on engines 1, 2, and 3, in accordance with McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995. (1) If no lockwire is found broken, repeat the inspection thereafter at intervals not to exceed 750 flight hours. (2) If any lockwire is found broken, prior to further flight: Check the torque of the bolt, install a new lockwire, and install a torque stripe on the bolt, in accordance with the alert service bulletin. Thereafter at intervals not to exceed 750 flight hours, perform a visual inspection to detect misalignment of the torque stripes, and repeat the inspection to detect broken lockwires, in accordance with the alert service bulletin. Terminating Actions (b) For Model DC-10-30 and -30F (KC-10A military) series airplanes, and Model MD-10-30F series airplanes: Within 18 months after the effective date of this AD, install retainers on the engine mount bolts of engine 1, 2, or 3 per the procedures depicted in Figure 6 of Revision 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, dated June 30, 1992; or modify the forward engine mount bolts for engine 1, 2, or 3, per McDonnell Douglas Service Bullletin DC10-71-159, dated September 6, 1995, or Revision 01, dated July 28, 1997. Accomplishment of the installation constitutes terminating action for the requirements of this AD for that engine. (c) For Model DC-10-10 and -15 series airplanes, and Model MD-10-10F series airplanes: Within 18 months after the effective date of this AD, modify the forward engine mount bolts for engine 1, 2, or 3, per McDonnell Douglas Service Bulletin DC10-71-159, dated September 6, 1995; or Revision 01, dated July 28, 1997. Accomplishment of the modification constitutes terminating action for the requirements of this AD for that engine. Alternative Methods of Compliance (d)(1) 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. 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. (2) Alternative methods of compliance, approved previously in accordance with AD 95-04-07 R2, amendment 39-11354, are approved as alternative methods of compliance with this AD. Special Flight Permits (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. Incorporation by Reference (f) The actions shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992; McDonnell Douglas Service Bulletin DC10-71-159, dated September 6, 1995, or McDonnell Douglas Service Bulletin DC10-71-159 RO1, Revision 01, dated July 28, 1997; and McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995; as applicable. (1) The incorporation by reference of McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992; McDonnell Douglas Service Bulletin DC10-71-159, dated September 6, 1995; and McDonnell Douglas Service Bulletin DC10-71-159 R01, Revision 01, dated July 28, 1997; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995, was approved previously by the Director of the Federal Register as of November 10, 1999 (64 FR 54202, October 6, 1999). (3) 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 (g) This amendment becomes effective on September 25, 2001. Issued in Renton, Washington, on August 13, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-20804 Filed 8-20-01; 8:45 am] BILLING CODE 4910-13-P
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