Airworthiness Directive · Amendment 39-16990 · Standard practices/structures
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, certificated in any category.
We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by a report of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their design service objective. This AD requires revising the maintenance inspection program to include inspections that will give no less than the required damage tolerance analysis for each principal structural element (PSE), doing repetitive inspections to detect cracks of all PSEs, and repairing cracked structure. We are issuing this AD to maintain the continued structural integrity of the fleet.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 12 months after the effective date of this AD, incorporate a revision into the maintenance inspection program that provides no less than the required damage tolerance assessment/analysis (DTA) for each structural significant item (SSI) listed in Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007. (The required inspection interval for each principal structural element (PSE) is listed in Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007.) The revision to the maintenance inspection program must include and must be implemented in accordance with the procedures in Section 5.0 (Damage Tolerance Analysis Methodology), Section 6.0 (Structural Inspection Requirements), and Section 7.0 (Discrepancy Reporting) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007. One report may be used to report findings for both the service difficulty report and this AD, provided the report refers to this AD and the PSE number for the inspection being accomplished when the discrepancy was found.
Note 1 to paragraphs (g) through (p) of this AD: Compliance with the requirements of this AD establishes compliance with section 121.1109(c)(1) of the Federal Aviation Regulations (14 CFR 121.1109(c)(1)).
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, except as provided by paragraphs (j) through (n) of this AD: Do the applicable initial inspections to detect cracks of all SSIs, in accordance with Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007. Repeat the applicable inspections thereafter at intervals not to exceed the “Recurring” intervals specified in Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, except as provided by paragraphs (l) through (n) of this AD.
(1) Before the applicable “Initial” threshold specified in Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007.
(2) Within 36 months after the effective date of this AD, or within one “Recurring” interval measured from 12 months after the effective date of the AD, whichever comes first.
Where Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, specifies the “Initial” threshold in years (since new), this AD requires compliance within the specified year since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness.
Where Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, specifies the “Initial” threshold as “Special Condition,” this AD requires compliance within 24 months after the effective date of this AD.
Where Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, specifies the “Initial” threshold and “Recurring” interval as “FS 1041 Fitting Replacement,” this AD requires compliance within 24 months after the effective date of this AD and thereafter at intervals not to exceed those specified in Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, concurrently with any FS 1041 fitting replacement.
Where Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, specifies the “Initial” threshold and “Recurring” interval as “Engine Change,” this AD requires compliance before further flight after the next engine change, and thereafter before further flight whenever the engines are changed.
Where Section 6.0 (Structural Inspection Requirements) of Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, specifies the “Initial” threshold and “Recurring” interval as “Aft Lord Mount Change,” this AD requires compliance before further flight after the next aft lord mount change (FS 1041 fitting change), and thereafter at intervals not to exceed those specified in Lockheed Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service Manual Publication (SMP), Supplemental Structural Inspection Document (SSID), SMP 515-C-SSID, Change 1, dated September 10, 2007, concurrently with any FS 1041 fitting replacement.
If any cracked structure is found during the inspections required by paragraph (i) of this AD, before further flight, repair the cracked structure using a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD.
Note 2 to paragraph (o) of this AD: Applicable existing FAA-approved repair procedures do not require further approval provided they have DTA-established inspection procedures and intervals previously approved by the FAA.
Note 3 to paragraph (o) of this AD: Operators may contact the Manager, Atlanta ACO, for information regarding the use of published service data approved by the FAA associated with the repairs specified in paragraph (o) of this AD.
Before any airplane that is subject to this AD and that has exceeded the applicable compliance times specified in paragraph (i) of this AD can be added to an air carrier's operations specifications, a program for the accomplishment of the inspections required by this AD must be established in accordance with paragraph (p)(1) or (p)(2) of this AD, as applicable.
(1) For airplanes that have been inspected in accordance with this AD: The inspection of each PSE must be done by the new operator in accordance with the previous operator's schedule and inspection method, or the new operator's schedule and inspection method, at whichever time would result in the earlier accomplishment for that PSE inspection. The compliance time for accomplishment of this inspection must be measured from the last inspection accomplished by the previous operator. After each inspection has been done once, each subsequent inspection must be performed in accordance with the new operator's schedule and inspection method.
(2) For airplanes that have not been inspected in accordance with this AD: The inspection of each PSE required by this AD must be done either before adding the airplane to the air carrier's operations specification, or in accordance with a schedule and an inspection method approved by the Manager, Atlanta ACO. After each inspection has been done once, each subsequent inspection must be done in accordance with the new operator's schedule.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
