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Airworthiness Directives; Lockheed Model L-1011 Series Airplanes

Document Details

Information about this document as published in the Federal Register.

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Start Preamble

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Final rule.

SUMMARY:

This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires modifications of the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. That AD was prompted by reports of an undetected fire breaching the high speed gearbox (HSGB) case on certain Rolls Royce engines installed on in-service airplanes due to lack of an internal fire detection system within the HSGB. The actions specified by that AD are intended to prevent undetected fires originating within the HSGB from breaching the Start Printed Page 44031HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire. This action removes certain airplanes from the applicability of the existing AD.

DATES:

Effective September 26, 2001.

The incorporation by reference of Lockheed Service Bulletin 093-77-059, dated February 25, 1998; and Lockheed Service Bulletin 093-77-059, Revision 1, dated February 2, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of October 6, 2000 (65 FR 53157, September 1, 2000).

ADDRESSES:

The service information referenced in this AD may be obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion Street, Greenville, South Carolina 29605. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Linda Haynes, Aerospace Engineer, ACE-116A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone (770) 703-6063; fax (770) 703-6097.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by revising AD 2000-17-10, amendment 39-11884 (65 FR 53157, September 1, 2000), which is applicable to Lockheed Model L-1011-385 series airplanes, was published in the Federal Register on April 26, 2001 (66 FR 20954). The action proposed to continue to require modifications of the engine turbine cooling air panel at the flight engineer/second officer's console, pilot's caution and warning light panel on the main instrument panel, and monitoring system for the engine turbine air temperature. That action also proposed to remove certain airplanes from the applicability of the existing AD.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion

The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact

There are approximately 54 Model Lockheed Model L-1011-385 series airplanes of the affected design in the worldwide fleet. The FAA estimates that 29 airplanes of U.S. registry will be affected by this AD, that it will take approximately 8 work hours per engine (3 engines per airplane) to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will cost approximately $6,320 per engine, or $18,960 per airplane. Based on these figures, the cost impact of this AD on U.S. operators is estimated to be $591,600 or $20,400 per airplane.

The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact

The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

Start List of Subjects

List of Subjects in 14 CFR Part 39

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Adoption of the Amendment

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Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (

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PART 39—AIRWORTHINESS DIRECTIVES

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1. The authority citation for part 39 continues to read as follows:

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Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. Section 39.13 is amended by removing amendment 39-11884 (

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2000-17-10 R1 Lockheed: Amendment 39-12378. Docket 2000-NM-369-AD. Revises AD 2000-17-10, Amendment 39-11884.

Applicability: Model L-1011-385 series airplanes equipped with Rolls Royce Model RB211-524 series engines, 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 request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent undetected fires originating within the high speed gearbox (HSGB) from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, accomplish the following:

Restatement of Requirements of AD 2000-17-10

Modification

(a) Within 24 months after October 6, 2000 (the effective date of AD 2000-17-10, amendment 39-11884), accomplish the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD, in accordance with Lockheed Service Bulletin 093-77-059, dated February 25, 1998; or Revision 1, dated February 2, 1999.

(1) Modify the engine turbine cooling air panel at the flight engineer/second officer's console.

(2) Modify the pilot's caution and warning light panel on the main instrument panel.

(3) Modify the monitoring system for the engine turbine air temperature.

Note 2:

Lockheed Service Bulletin 093-77-059 refers to Rolls Royce Service Bulletins RB.211-72-C178, dated March 20, 1998; and Start Printed Page 44032RB.211-77-C144, dated August 7, 1998; as additional sources of service information for accomplishment of the modification of the monitoring system for the engine turbine air temperature.

Alternative Methods of Compliance

(b) 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 Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office (ACO).

Note 3:

Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.

Special Flight Permits

(c) 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.

Incorporation by Reference

(d) The actions shall be done in accordance with Lockheed Service Bulletin 093-77-059, dated February 25, 1998; or Lockheed Service Bulletin 093-77-059, Revision 1, dated February 2, 1999. This incorporation by reference was approved previously by the Director of the Federal Register as of October 6, 2000 (65 FR 53157, September 1, 2000). Copies may be obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion Street, Greenville, South Carolina 29605. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

(e) This amendment becomes effective on September 26, 2001.

Start Signature

Issued in Renton, Washington, on August 15, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 01-21101 Filed 8-21-01; 8:45 am]

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