Airworthiness Directive · Amendment 39-16978 · Fuselage
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
All Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes, certificated in any category.
We are superseding an existing airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes. That AD currently requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This new AD adds Model L-1011-385-3 airplanes to the applicability, changes certain inspection thresholds, adds three new structurally significant details (SSDs), and removes an SSD that has been addressed by a different AD. This AD was prompted by an evaluation by the manufacturer of usage and flight data that provided additional information about certain SSDs where fatigue damage is likely to occur. We are issuing this AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
This maintenance program revision is retained from AD 95-20-04 R1, Amendment 39-9454 (60 FR 63414, December 11, 1995): For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes: Within 12 months after November 2, 1995 (the effective date of AD 95-20-04 R1, Amendment 39-9454 (60 FR 63414, December 11, 1995)), incorporate a revision into the maintenance inspection program which provides for inspection(s) of the structurally significant details (SSD) defined in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994. Doing the revision required by paragraph (h) of this AD terminates the requirement to revise the maintenance inspections program specified in this paragraph. Doing the inspections required by paragraph (i) of this AD terminates the corresponding inspection requirements of this paragraph.
(1) The initial inspection for each SSD must be performed at the later of the times specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Within one repeat interval measured from November 2, 1996 (12 months after November 2, 1995).
(ii) Prior to the threshold specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, for that SSD.
(2) A 10 percent deviation from the repetitive interval specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, for that SSD is acceptable to allow for planning and scheduling time.
(3) If Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, specifies that inspection of any SSD be performed at every “C” check, those inspections must be performed at intervals not to exceed 5,000 hours time-in-service or 2,500 flight cycles, whichever occurs earlier.
(4) If Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, specifies either the initial inspection or the repetitive inspection intervals for any SSD in terms of flight hours or flight cycles, the inspection shall be performed prior to the earlier of the terms (whichever occurs first on the airplane: either accumulated number of flight hours, or accumulated number of flight cycles).
(5) The non-destructive inspection techniques referenced in Section VI., “Appendix,” of Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, provide acceptable methods for accomplishing the inspections required by paragraph (g) of this AD.
For all airplanes: Within 12 months after the effective date of this AD, incorporate a revision into the maintenance inspection program which provides for inspection(s) of the SSDs defined in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009. Doing this revision terminates the requirement to revise the maintenance inspection program as specified in paragraph (g) of this AD.
For all airplanes: Do all applicable inspections specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009. Do the initial inspection or next repetitive inspection at the applicable time specified in paragraphs (i)(1) and (i)(2) of this AD, except as provided by paragraphs (j), (k), and (l) of this AD. Repeat the inspections thereafter in accordance with the intervals and actions specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, except as provided by paragraphs (j), (k), and (l) of this AD. The non-destructive inspection techniques referenced in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, provide acceptable methods for accomplishing the inspections required by this AD. Doing the inspections required by this paragraph of this AD terminates the corresponding inspection requirements of paragraph (g) of this AD.
(1) For Model L-1011-385-3 airplanes; and for Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes on which the initial inspection required by paragraph (g) of this AD has not been accomplished before the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
(i) Within one repeat interval measured from a date 12 months after the effective date of this AD.
(ii) Before the threshold specified for that SSD in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009.
(2) For Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes on which the initial inspection required by paragraph (g) of this AD has been accomplished before the effective date of this AD: Do the next repetitive inspection at the earlier of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within the next repetitive inspection interval specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994, for that SSD.
(ii) Within one repeat interval measured from a date 12 months after the effective date of this AD; or within the next repetitive interval specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, for that SSD; whichever occurs later.
For all airplanes: A 10 percent deviation from the repetitive interval specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, for that SSD is acceptable to allow for planning and scheduling time.
For all airplanes: Where Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, specifies that inspection of any SSD be performed at every “C” check, those inspections must be performed at intervals not to exceed 5,000 flight hours or 2,500 flight cycles, whichever occurs earlier.
For all airplanes: Where Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009, specifies either the initial inspection or the repetitive inspection intervals for any SSD in terms of flight hours or flight cycles, the inspection must be performed prior to the earlier of the terms (whichever occurs first on the airplane: either accumulated number of flight hours, or accumulated number of flight cycles).
For all airplanes: There should be no repair or modification work done in the inspection area before the initial inspections required by paragraph (i) of this AD; any changes in the inspection area could affect the inspection procedure.
For all airplanes: If any cracking is found in any SSD during any inspection required by this AD, prior to further flight, repair in accordance with paragraph (n)(1), (n)(2), or (n)(3) of this AD:
(1) In accordance with the Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994; or revised April 2009. After doing the revision required by paragraph (h) of this AD, repair in accordance with Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009.
Note 1 to paragraph (n)(1) of this AD: Guidance on doing repairs in accordance with a “L-1011-385 Series Supplemental Inspection Document” specified in paragraph (n)(1) of this AD can be found in the applicable service bulletins identified in certain SSDs of the “L-1011-385 Series Supplemental Inspection Document” specified in paragraph (n)(1) of this AD.
(2) In accordance with Lockheed L-1011 Structural Repair Manual, Revision 80, dated December 15, 2009.
(3) In accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA.
For all airplanes: At the later of the times specified in paragraphs (o)(1) and (o)(2) of this AD, submit a report of the results (positive or negative) of the inspection(s) to Lockheed in accordance with Section V., Data Reporting System (DRS), of the applicable Lockheed Document specified in paragraph (o)(1) of this AD. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) Within 30 days after returning the airplane to service, subsequent to accomplishment of the inspection(s) specified in Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised January 1994; or Lockheed Document Number LG92ER0060, “L-1011-385 Series Supplemental Inspection Document,” revised April 2009.
(2) Within 30 days after the effective date of this AD.
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.
