[Federal Register Volume 62, Number 128 (Thursday, July 3, 1997)]
[Rules and Regulations]
[Pages 35951-35953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-17278]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-06-AD; Amendment 39-10065, AD 97-14-07]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011 Series Airplanes 
Equipped With Rolls-Royce Model RB211-524 Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Lockheed Model L-1011 series airplanes, 
that currently requires several modifications of the engine high speed 
gearboxes. This amendment requires that a new modification be installed 
in lieu of one of those previously required. This amendment is prompted 
by a report indicating that one of the currently required modifications 
is not completely effective because it can create interference problems 
between the fireloop and a fuel line. The actions specified by this AD 
are intended to reduce the possibility of a fire in the high speed gear 
boxes, and to ensure that any fire which may occur is readily detected 
by the flight crew.

DATES: Effective August 7, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 7, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Aeronautical Systems Support Company (LASSC), 
Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, 
Smyrna, Georgia 30080; and Rolls-Royce plc, Technical Publications 
Department, P.O. Box 17, Parkside, Coventry CV1 2LZ, England. 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, 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.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-

[[Page 35952]]

116A, FAA, Small Airplane Directorate, Atlanta Aircraft Certification 
Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College 
Park, Georgia 30337-2748; telephone (404) 305-7367; fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 94-03-10, 
amendment 39-8817 (59 FR 6535, February 11, 1994), which is applicable 
to certain Lockheed Model L-1011 series airplanes, was published in the 
Federal Register on March 26, 1997 (62 FR 14363). The action proposed 
to continue to require installation of a new vent tube in the high 
speed gearbox on the number 1, 2, and 3 engines, and modification of 
the breather duct of the high speed gearbox on the number 2 engine. The 
action also proposed to continue to require the installation of an 
additional fire detection system on the high speed gearbox on the 
number 1, 2, and 3 engines; however, it would require that the 
installation be accomplished in accordance with the revised service 
bulletin, described previously, which incorporates the new routing 
procedures. This proposed requirement would mean that operators who 
already have complied with the installation required by AD 94-03-10 
must perform additional procedures relative to rerouting the 
installation assembly.

Explanation of Changes Made to the Proposal

    The FAA has revised NOTE 2 and NOTE 3 of the proposed AD to 
reference the exact effective date (i.e., March 14, 1994) of AD 94-03-
10. The FAA finds that the phrase ``prior to the effective date of this 
AD,'' which appeared in the proposal, could be misinterpreted to mean 
the effective date of this final rule rather than the effective date of 
AD 94-03-10.

Consideration of Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    Both commenters support the proposed rule.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 92 Lockheed Model L-1011 series airplanes 
of the affected design in the worldwide fleet. The FAA estimates that 
28 airplanes of U.S. registry will be affected by this AD.
    The installation of a new vent tube in the high speed gear box, 
which is currently required by AD 94-03-10, takes approximately 3 work 
hours per airplane to accomplish, at an average labor rate of $60 per 
work hour. Required parts are estimated to cost $500 per airplane. 
Based on these figures, the cost impact of this action on U.S. 
operators is estimated to be $19,040, or $680 per airplane.
    The modification of the breather duct on the high speed gearbox on 
the number 2 engine, which is currently required by AD 94-03-10, 
requires approximately 6 work hours to accomplish, at an average labor 
rate of $60 per work hour. Required parts are estimated to cost $10,000 
per airplane. Based on these figures, the cost impact of this action on 
U.S. operators is estimated to be $290,080, or $10,360 per airplane.
    The installation of the additional fire detecting loop in 
accordance with the revised Lockheed service bulletin will require 
approximately 9 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. If the airplane is equipped with a 
Walter Kidde fire detection system, required parts are estimated to 
cost $2,100 per airplane. If the airplane is equipped with a Graviner 
fire detection system, required parts are estimated to cost $8,100 per 
airplane. Based on these figures, the cost impact of this requirement 
on U.S. operators is estimated to be between $73,920 and $241,920 for 
the fleet, or between $2,640 and $8,640 per airplane.
    The cost impact figures discussed above are 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. However, the FAA has been advised 
that at least 19 airplanes of U.S. registry already have been modified 
to incorporate the breather duct on the high speed gearbox on the 
number 2 engine. Therefore, the future cost impact of this AD is 
reduced by at least $196,840.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 39-8817 (59 FR 
6535, February 11, 1994), and by adding a new airworthiness directive 
(AD), amendment 39-10065, to read as follows:

97-14-07 Lockheed: Amendment 39-10065. Docket 97-NM-06-AD. 
Supersedes AD 94-03-10, Amendment 39-8817.

    Applicability: Model L-1011 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 
otherwise 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 (c) of 
this AD.

[[Page 35953]]

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 reduce the possibility of a fire in the engine high speed 
gearbox, and to ensure that, if a fire occurs, it is readily 
detected by the flight crew, accomplish the following:
    (a) Within 16,000 flight hours or 48 months after March 14, 
1994, (the effective date of AD 94-03-10, amendment 39-8817), 
whichever occurs first, accomplish both paragraphs (a)(1) and (a)(2) 
of this AD:
    (1) Install a new vent tube in the gear compartment of the high 
speed gearbox on the number 1, number 2, and number 3 engines, in 
accordance with Rolls-Royce Service Bulletin RB.211-72-4666, 
Revision 4, dated May 16, 1986.

    Note 2: Installation of a new vent tube prior to March 14, 1994, 
in accordance with Rolls-Royce Service Bulletin RB.211-72-4666, 
Revision 3, dated October 14, 1977, is considered acceptable for 
compliance with this AD.

    (2) Modify the breather duct of the high speed gearbox on the 
number 2 engine in accordance with Lockheed Service Bulletin 093-71-
067, Revision 2, dated December 12, 1988.

    Note 3: Modification of the breather duct prior to March 14, 
1994, in accordance with Lockheed Service Bulletin 093-71-067, 
Revision 1, dated April 1, 1986, is considered acceptable for 
compliance with this AD.

    (b) Install an additional fire detection system on the high 
speed gearbox on the number 1, number 2, and number 3 engines in 
accordance with paragraph (b)(1), (b)(2), (b)(3) of this AD, as 
applicable:
    (1) For airplanes on which an additional fire detection system 
has not been installed: Within 6,000 flight hours or 18 months after 
the effective date of this AD, whichever occurs first, install the 
system in accordance with Lockheed Service Bulletin 093-26-039, 
Revision 1, dated April 10, 1996.
    (2) For airplanes on which an additional fire detection system 
has been installed prior to the effective date of this AD and in 
accordance with Lockheed Service Bulletin 093-26-039, dated November 
11, 1992: Within 6,000 flight hours or 18 months after the effective 
date of this AD, whichever occurs first, modify the system in 
accordance with Lockheed Service Bulletin 093-26-039, Revision 1, 
dated April 10, 1996.
    (3) For airplanes on which an additional fire detection system 
has been installed prior to the effective date of this AD and in 
accordance with Lockheed Service Bulletin 093-26-039, Revision 1, 
dated April 10, 1996: No further action is required by this 
paragraph.
    (c)(1) 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, 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: 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (2) Alternative methods of compliance, approved previously in 
accordance with AD 94-03-10, amendment 39-8817, are approved as 
alternative methods of compliance with this AD.
    (d) 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.
    (e) The actions shall be done in accordance with Rolls-Royce 
Service Bulletin RB.211-72-4666, Revision 4, dated May 16, 1986; 
Lockheed Service Bulletin 093-71-067, Revision 2, dated December 12, 
1988; and Lockheed Service Bulletin 093-26-039, Revision 1, dated 
April 10, 1996. Rolls-Royce Service Bulletin RB.211-72-4666, 
Revision 4, dated May 16, 1986, contains the following list of 
effective pages:

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                                       Revision                         
                                        level                           
              Page No.                 shown on     Date shown on page  
                                         page                           
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1-4.................................          4  May 16, 1986.          
4A, 6A, 10..........................       none  August 26, 1977.       
5, 6, 7-9, Supplement Page 2........          2  August 26, 1977.       
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    This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Copies may be obtained from Lockheed Aeronautical Systems Support 
Company (LASSC), Field Support Department, Dept. 693, Zone 0755, 2251 
Lake Park Drive, Smyrna, Georgia 30080; and Rolls-Royce plc, Technical 
Publications Department, P.O. Box 17, Parkside, Coventry CV1 2LZ, 
England. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 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.
    (f) This amendment becomes effective on August 7, 1997.

    Issued in Renton, Washington, on June 26, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-17278 Filed 7-2-97; 8:45 am]
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