Airworthiness directives › 2023-22-06
AD 2023-22-06 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Models named: 382, 382B, 382E, 382F, 382G, C-130A, C-130B, HP-C-130A, EC-130Q, C-130H. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the airplanes identified in paragraphs (c)(1) and (2) of this AD. (1) All Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category. (2) All airplanes specified in paragraphs (c)(2)(i) through (xi) of this AD, type certificated in the restricted category. (i) LeSEA Model C-130A airplanes (transferred from Central Air Services, Inc.), Type Certificate Data Sheet (TCDS) A34SO, Revision 1. (ii) T.B.M., Inc., Model C-130A airplanes, TCDS A39CE, Revision 3. (iii) Western International Aviation, Inc., Model C-130A airplanes, TCDS A33NM. (iv) USDA Forest Service Model C-130A airplanes, TCDS A15NM, Revision 4. (v) Snow Aviation International, Inc., Model C-130A airplanes, TCDS TQ3CH, Revision 1. (vi) International Air Response (transferred from Rogers Helicopters, Inc., and Heavylift Helicopters Inc.) Model C-130A airplanes, TCDS A31NM, Revision 3. (vii) Heavylift Helicopters, Inc., Model C-130B airplanes, TCDS A35NM, Revision 1. (viii) Hawkins & Powers Aviation, Inc., Model HP-C-130A airplanes, TCDS A30NM, Revision 1. (ix) Coulson Aviation (USA), Inc., Model EC-130Q and C-130H airplanes, TCDS T00019LA, Revision 4. (x) Lockheed-Georgia Company Model 282-44A-05 (C-130B) airplanes, TCDS A5SO. (xi) Surplus Model C-130A airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 35 days after the effective date of this AD, do the inspections specified in paragraphs (g)(1) and (2) of this AD, using a method approved in accordance with the procedures specified in paragraph (i) of this AD. If any cracked or severed engine truss mount upper lug is found, the engine truss mount must be replaced before further flight, using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (1) Do a one-time detailed visual inspection for cracking of the No. 1 and No. 4 engine truss mount upper lugs, lower surfaces, at outer wing station (OWS) 162 and OWS 197; and for severed engine truss mount upper lugs; at a total of four locations: two locations per engine mount, one mount assembly at each OWS. (2) Do a one-time borescope inspection for cracking of the No. 1 and No. 4 engine truss mount upper lug side surfaces, inboard and outboard, at OWS 162 and OWS 197; and for severed engine truss mount upper lugs; at a total of eight locations: two locations per engine truss mount lug, two lugs per engine, one mount assembly at each OWS. Note 1 to paragraph (g): Guidance for accomplishing the inspections and replacement can be found in Lockheed Martin Aeronautics Company Alert Service Bulletin A382-57-103, dated October 19, 2023.
Unsafe condition
This AD was prompted by reports of fatigue cracking of an upper lug of the engine truss mount, and by reports of cracks found prior to the initial inspection times required by AD 96-12-20. The FAA is issuing this AD to address such fatigue cracking. Fatigue cracking of a single engine truss mount upper lug could reduce the static strength of an engine mount to limit load, while cracking of both lugs can lead to separation of the engine, catastrophic structural damage, and loss of control of the airplane.
Affected ADs
This AD replaces AD 96-12-20, Amendment 39-9663 (61 FR 29279, June 10, 1996; corrected August 16, 1996 (61 FR 42549)) (AD 96-12-20).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1