AD 2001-13-22 Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A Military), and -40 Series Airplanes; and Model MD-10-10F and MD-10-30F Series Airplanes

Models named: MD-10-10F, MD-10-30F series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes; and Model MD-10-10F and MD-10-30F series airplanes; as listed in McDonnell Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999; 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 (e)(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 prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane, accomplish the following: Inspection or Torque Verification, and Corrective Actions, if Necessary (a) Within 2 months after September 25, 2000, (the effective date of AD 2000-16-10, amendment 39-11866), do an ultrasonic inspection of the attaching bolts on the inboard and outboard support on the outboard flap assembly and on the outboard support on the inboard flap assembly to detect failed bolts, or verify the torque of the attaching bolts on the inboard support on the outboard flap, per McDonnell Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999. (1) If no failed bolt is found, repeat the ultrasonic inspection or torque verification every 6 months. (2) If any failed bolt is found, before further flight, replace the bolt and associated parts with a new Inconel bolt and new associated parts per the service bulletin, except as provided by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. Accomplishment of the replacement constitutes terminating action for the repetitive requirements of paragraph (a)(1) of this AD for that bolt. (i) If an Inconel bolt is not available for accomplishment of the replacement, replacement with a new H-11 steel bolt is acceptable provided that operators repeat the ultrasonic inspection or torque verification every 6 months until the requirements of paragraph (c) of this AD are accomplished. (ii) If a PLI washer is not available for accomplishment of the Inconel replacement, a new Inconel bolt can be temporarily installed without a new PLI washer provided that the bolt is torqued to the applicable value specified in the service bulletin. Within 6,000 flight hours after an Inconel bolt is torqued, replace the PLI washer with a new washer per the service bulletin. Torque Verification (b) For airplanes on which the verification of the torque of the attaching bolts on the inboard support on the outboard flap was done per paragraph (a) of this AD: Within 2 months after the effective date of this AD, verify the torque of the attaching bolts on the outboard support on the inboard and outboard flaps, per McDonnell Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999; and do the applicable action(s) specified in paragraph (a)(1) or (a)(2) of this AD. Bolt Replacement (c) Within 2 years after accomplishing the initial inspection required by paragraph (a) of this AD or the torque verification required by paragraphs (a) and (b) of this AD, do the action specified in paragraph (a)(2) of this AD for all H-11 bolts. Accomplishment of the replacement of all H-11 bolts with Inconcel bolts constitutes terminating action for the requirements of this AD. Spares (d) As of 2 years after the effective date of this AD, no person shall install, on any airplane, an H-11 steel bolt, part number 71658-8-44, 71658-7-44, 71658-7-54, 71658-7-56, 71658-7-29, 71658-9-31, 71658-9-34, 71658-9-38, 71658-9-41, 71658-10-41, 71658-7-26, 71658-7-27, or 71658-8-29, on the inboard or outboard flap assembly. Alternative Methods of Compliance (e)(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 per AD 2000-16-10, amendment 39-11866, are considered to be approved as alternative methods of compliance with this AD. Special Flight Permits (f) 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 (g) The actions shall be done in accordance with McDonnell Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999. This incorporation by reference of that document was approved previously by the Director of the Federal Register as of September 25, 2000 (65 FR 50621, August 21, 2000). Copies may be obtained from Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 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 (h) This amendment becomes effective on August 9, 2001. Issued in Renton, Washington, on June 27, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-16739 Filed 7-3-01; 8:45 am] BILLING CODE 4910-13-P