AD 95-20-04 R1

This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, that 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. That AD originally was prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions specified in that AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes. This amendment corrects the compliance time for the initial inspection of each structurally significant detail (SSD).

The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of November 2, 1995 (60 FR 51713, October 3, 1995).

Final rule; correction.

95-20-04 R1 LOCKHEED: Amendment 39-9454. Docket 93-NM-219-AD. Revises AD 95-20-04, Amendment 39-9382.

Applicability: Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 series airplanes, certificated in any category.

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 use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent fatigue cracking that could compromise the structural integrity of these airplanes, accomplish the following:

(a) Within 12 months the effective date of this AD, incorporate a revision into the FAA-approved 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.

(1) The initial inspection for each SSD must be performed at the later of the times specified in paragraph (a)(1)(i) or (a)(1)(ii) of this AD:

(i) Within one repeat interval measured from a date 12 months after the effective date of this AD; or

(ii) Prior to the threshold specified in the Lockheed Document for that SSD.

(2) A 10 percent deviation from the repetitive interval specified in the Lockheed Document for that SSD is acceptable to allow for planning and scheduling time.

(3) If the Lockheed Document 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 the Lockheed Document 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 Appendix VI of the Lockheed Document provide acceptable methods for accomplishing the inspections required by this AD.

(b) If any cracking isfound in any SSD, prior to further flight, repair in accordance with paragraph (b)(1), (b)(2), or (b)(3) of this AD.

(1) In accordance with the applicable service bulletin referenced in Lockheed Document Number LG92ER0060, "L-1011-385 Series Supplemental Inspection Document," revised January 1994; or

(2) In accordance with the Structural Repair Manual; or

(3) In accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate.

(c) 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, 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 Lockheed Document. Information collection requirements contained in this regulation 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.

(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, FAA, Small Airplane Directorate. 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

(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.

(f) The incorporation of the revision and reporting requirements shall be done in accordance with Lockheed Document Number LG92ER0060, "L-1011-385 Series Supplemental Inspection Document," revised January 1994. This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of November 2, 1995 (60 FR 51713, October 3, 1995). Copies may be obtained from Lockheed Aeronautical Systems Support Company, Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at he FAA, Atlanta Aircraft Certification Office, Small Airplane Directorate, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This amendment is effective on November 2, 1995.

On September 20, 1995, the FAA issued AD 95-20-04, amendment 39-9382 (60 FR 51713, October 3, 1995), applicable to all Lockheed Model L-1011-385-1 series airplanes. That AD 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. That action was prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions required by that AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes.

Since the issuance of that AD, the FAA has received communications from an affected operator indicating confusion about the compliance time for accomplishing the inspections of each structurally significant detail(SSD). This operator points out that the AD specifies, first, that the inspections contained in the SID must be incorporated into the FAA-approved maintenance program within 12 months after the effective date of the AD. Second, the AD requires that the initial inspection of each SSD must be accomplished within one repeat interval after the effective date of the AD. The operator points out that this presents a problem in complying with the AD, since, in some cases, the initial inspection of an SSD may be required to be accomplished prior to the incorporation of the SID program into an operator's maintenance program.

The FAA has reviewed the compliance time specified in AD 95-20-04, and finds that it is indeed erroneous. It was the FAA's intent that the SID program be incorporated into the FAA-approved maintenance inspection program prior to the performance of any inspection contained in the SID. Therefore, the FAA has determined that it is appropriate to take action to correctparagraph (a)(1) of that AD to specify that the compliance time for performing the initial inspection of each SSD is within one repeat interval measured from a date 12 months after November 2, 1995 (the effective date of the AD). The FAA finds that this change will not compromise safety and is consistent with what the FAA had originally intended.

Action is taken herein to correct the error and to correctly add the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13). The effective date of the rule remains November 2, 1995.

The final rule is being reprinted in its entirety for the convenience of affected operators.

Since this AD merely corrects the compliance time for a previously-required action, it requires no additional work to be performed by affected operators. In light of this, the FAA has determined that it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary.

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Correction
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40101, 40113, 44701.

39.13 - [Amended]
2. Section 39.13 is amended by removing amendment 39-9382 (60 FR 51713, October 3, 1995), and by adding a new airworthiness directive (AD), amendment 39-9454, to read as follows: