[Federal Register Volume 66, Number 163 (Wednesday, August 22, 2001)]
[Rules and Regulations]
[Pages 44030-44032]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21101]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-369-AD; Amendment 39-12378; AD 2000-17-10 R1]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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

[[Page 44031]]

HSGB 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.

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.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-11884 (65 FR 
53157, September 1, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12378, to read as follows:

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

[[Page 44032]]

RB.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.

    Issued in Renton, Washington, on August 15, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21101 Filed 8-21-01; 8:45 am]
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