[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:
------------------------------------------------------------------------
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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