AD 2021-09-15 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes

Models named: 382, 382B, 382E, 382F, 382G, C-130A, C-130B, C-130BL, C-130E, C-130H. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, type certificated in any category; and Model C-130A, C-130B, C-130BL, C-130E, C-130H, C-130H-30, C-130J, C-130J-30, EC-130Q, HC-130H, KC-130H, NC-130B, NC-130, and WC-130H airplanes, type certificated in the restricted or amateur category. The restricted and amateur category airplanes were originally manufactured by Lockheed Martin Corporation/Lockheed Martin Aeronautics Company; current type certificate holders include, but are not limited to, those specified in paragraphs (c)(1) through (9) of this AD. (1) LeSEA Model C-130A airplanes, Type Certificate Data Sheet (TCDS) A34SO, Revision 1. (2) T.B.M, Inc. (transferred from Central Air Services, Inc.), Model C-130A airplanes, TCDS A39CE, Revision 3. (3) Western International Aviation, Inc., Model C-130A airplanes, TCDS A33NM. (4) USDA Forest Service Model C-130A airplanes, TCDS A15NM, Revision 4. (5) Snow Aviation International, Inc., Model C-130A airplanes, TCDS TQ3CH, Revision 1. (6) Heavylift Helicopter, Inc. (transferred from Hemet Valley Flying Service), Model C-130A, TCDS A31NM airplanes, Revision 1. (7) Heavylift Helicopters, Inc., Model C-130B airplanes, TCDS A35NM, Revision 1. (8) Hawkins & Powers Aviation, Inc., Model HP-C-130A airplanes, TCDS A30NM, Revision 1. (9) Coulson Aviation (USA), Inc., Model EC-130Q airplanes, TCDS T00019LA, Revision 2.

Comply with this AD within the compliance times specified, unless already done.

At the applicable compliance time specified in paragraph (g)(1) or (2) of this AD, do an eddy current surface scan for cracks of the center wing upper and lower forward corner fittings and fasteners, and do a torque check of the left and right outer-wing-to-center-wing front-beam-web-joint-splice-angle fasteners (including checking for any loose, sheared, broken, or missing fasteners), in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Alert Service Bulletin A382-57-99, Revision 1, dated February 17, 2021. If any cracking is found during the inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. If any loose fastener is found during the torque check, retorque the fastener before further flight, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Alert Service Bulletin A382-57-99, Revision 1, dated February 17, 2021. If any sheared, broken, or missing fastener is found during the torque check, replace the fastener before further flight. (1) For airplanes that have accumulated 2,500 or more flight hours as of the effective date of this AD: Within 90 days after the effective date of this AD. (2) For airplanes that have accumulated less than 2,500 flight hours as of the effective date of this AD: Within 270 days after the effective date of this AD.

This AD was prompted by a report of a crack found on the web attachment flange of the center wing upper forward corner fitting. The FAA is issuing this AD to address loose fasteners in a certain wing joint at the front beam web, which can cause internal load redistribution, and consequent cracked center wing upper and lower corner fittings and failed fasteners in those fittings, resulting in reduced structural integrity of the airplane and loss of control of the airplane.

None.