AD 2002-19-14 Airworthiness Directives; Lockheed C-130A Airplanes, Type Certificated in the Restricted Category

Models named: C-130A, HP-C-130A. Read the applicability below — it usually turns on serial or part numbers too.

Including, but not limited to, all of the following Lockheed C-130A airplanes, type certificated in the restricted category: Central Air Service, Inc., Model C-130A airplanes, Type Certificate Data Sheet (TCDS) No. A39CE, Revision 2; Hawkins & Powers Aviation, Inc., Model HP-C-130A airplanes, TCDS No. A30NM, Revision 1; Hemet Valley Flying Service Model C-130A airplanes, TCDS No. A31NM, Revision 0; LeSEA Model C-130A airplanes, TCDS No. A34SO, Revision 0; Snow Aviation International, Inc., Model C-130A airplanes, TCDS No. TQ3CH, Revision 1; United States Department of Agriculture (USDA) Forest Service Model C-130A airplanes, TCDS No. A15NM, Revision 4; Western International Aviation, Inc., Model C-130A airplanes, TCDS No. A33NM, Revision 0; and Any other surplus Military C-130A airplanes. 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 in the left- and right-side lower skin panels and stringers of the center wing, which could result in structural failure of the wings and consequent loss of control of the airplane, accomplish the following: Inspection (a) Within 4 days after the effective date of this AD, do the actions specified in paragraphs (a)(1) and (a)(2) of this AD per a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. (1) Do an inspection to detect cracks at fastener holes in the left- and right-side lower skin panels and stringers of the center wing between wing stations 41.0 and 71.0. The inspection procedures must be sufficiently reliable to determine the location and orientation of cracks that are very small, perhaps less than 0.10 inch in length. (2) Develop repetitive inspection intervals that prevent crack growth from exceeding the minimum residual strength required to support ultimate load on the affected structure. The repetitive inspection intervals must be based on a damage-tolerance assessment of the wing panels and stringers and be approved by the Manager, Atlanta ACO. Guidance for damage tolerance procedures may be found in Advisory Circular (AC) 25.571-1C, dated April 29, 1998. Thereafter, do the inspection approved per paragraph (a)(1) of this AD at the intervals approved per this paragraph. (b) If any crack is detected during any inspection required by this AD, before further flight, do the action(s) specified in paragraph (b)(1) or (b)(2) of this AD. (1) Replace the cracked part with a new part and continue to inspect per paragraph (a) of this AD. (2) Repair and inspect at new intervals based on a damage-tolerance assessment of the wing panels and stringers, per a method approved by the Manager, Atlanta ACO. The repair must include a damage-tolerance assessment as noted above, in addition to an analysis showing static strength capability in compliance with the certification basis of the airplane. Guidance for damage tolerance procedures may be found in Advisory Circular (AC) 25.571-1C, dated April 29, 1998. Reporting Requirement (c) Within 10 days after accomplishing the initial inspection required by paragraph (a)(1) of this AD, submit a report of the inspection results (both positive and negative) to the Manager, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; fax (770) 703-6097. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ) and have been assigned OMB Control Number 2120-0056. As a minimum, the report must include: (1) Airplane manufacturer's serial number(s); (2) Time-in-service of airplane; (3) Applicable TCDS; (4) Description of usage under which the restricted category was issued (see 14 CFR part 21.25(b)); (5) Part numbers and time-in-service of damaged and undamaged parts; and Note 2: Reports of “rehabed” wings indicate that wing panels and stringers may have been replaced. (6) Diagram(s) showing the location and orientation of cracks, and if available, the length of cracks. Alternative Methods of Compliance (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, Atlanta ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. 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. Effective Date (f) This amendment becomes effective on September 26, 2002. Issued in Renton, Washington, on September 20, 2002. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-24416 Filed 9-23-02; 12:24 pm] BILLING CODE 4910-13-P