[Federal Register Volume 64, Number 224 (Monday, November 22, 1999)]
[Proposed Rules]
[Pages 63755-63757]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-30371]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-314-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Lockheed Model L-1011-385
series airplanes. This proposal would 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. This proposal is 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 the
proposed AD are intended to prevent undetected fires originating within
the HSGB from breaching the HSGB case, which could result in engine
damage and increased difficulty in extinguishing a fire.
DATES: Comments must be received by January 6, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-314-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Lockheed Martin Aircraft & Logistics
[[Page 63756]]
Center, 120 Orion Street, Greenville, South Carolina 29605. This
information may be examined at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small
Airplane Directorate, Atlanta Aircraft Certification Office, One Crown
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia.
FOR FURTHER INFORMATION CONTACT: Thomas Peters Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane
Directorate, 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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-314-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-314-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports of an undetected fire breaching the
high speed gear box (HSGB) case on Rolls Royce Model RB211-22B and -524
series engines installed on all Lockheed Model L-1011-385 series
airplanes due to lack of an internal fire detection system within the
HSGB. Investigation has revealed that an internal failure (i.e.,
principally bearing failure) in the engine HSGB induces combustion of
the lubricating oil in the gearbox. This fire can eventually burn
through the gearbox housing, which is the first point where it becomes
detectable with the current fire detection system. After shutting down
the engine subsequent to a fire warning, the windmilling engine core
will still supply sufficient air to the HSGB to sustain combustion.
Undetected HSGB fires due to lack of an internal fire detection system
within the HSGB, could result in engine damage and increased difficulty
in extinguishing a fire.
Other Relevant Rulemaking
On June 26, 1997, the FAA issued AD 97-14-07, amendment 39-10065
(62 FR 35951, July 3, 1997), applicable to certain Lockheed Model L-
1011 series airplanes equipped with Rolls Royce RB211-524 engines, to
require various modifications and corrective actions to prevent a
potential fire hazard from an undetected gearbox fire.
On April 21, 1998, the FAA issued AD 98-09-23, amendment 39-10504
(63 FR 23382, April 29, 1998), applicable to certain Lockheed Model L-
1011 series airplanes equipped with Rolls Royce RB211-22B engines, to
require various modifications and corrective actions to prevent a
potential fire hazard from an undetected gearbox fire.
However, this proposed AD would not affect the current requirements
of those previously issued AD's.
Explanation of Relevant Service Information
The FAA has reviewed and approved Lockheed Service Bulletin 093-77-
059, dated February 25, 1998, and Revision 1, dated February 2, 1999.
The service bulletin describes procedures for modifications to 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. The modification to the engine turbine cooling air panel
involves installation of a HSGB overheat (OVHT) marker. The
modification to the pilot's caution and warning light panel on the main
instrument panel involves renaming the pilot's caution and warning
light panel ``TURB AIR OVHT ENG 1'' indicator light to ``TURB AIR /
HSGB ENG 1'', ``TURB AIR OVHT ENG 2'' to ``TURB AIR / HSGB ENG 2,'' and
``TURB AIR OVHT ENG 3'' to ``TURB AIR / HSGB ENG 3.'' The modification
to the monitoring system for the engine turbine air temperature
involves installation of a revised breather duct assembly for the HSGB;
installation of two overheat detectors in the gearbox breather duct
assembly; wiring modifications to the fancase/A-frame to engine core
services loom assembly; installation of a spiral anti-chafe sleeve over
the modified fancase/A-frame; and installation of additional clipping
brackets for the wiring modifications. Accomplishment of the actions
specified in the service bulletin is intended to adequately address the
identified unsafe condition.
Lockheed Service Bulletin 093-77-059 refers to Rolls Royce Service
Bulletins RB.211-72-C178, dated March 20, 1998; and RB.211-77-C144,
dated August 7, 1998; as additional sources of service information for
accomplishment of the modification to the monitoring system for the
engine turbine air temperature.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
Lockheed Service Bulletin 093-77-059 described previously.
Cost Impact
There are approximately 235 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
24 work hours per airplane to accomplish the proposed modifications,
and that the average labor rate is $60 per work hour.
Required parts would cost approximately $6,350 per airplane. Based
on these figures, the cost impact of the proposed AD on U.S. operators
is estimated to be $911,430, or $7,790 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed 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 proposed herein would not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of
[[Page 63757]]
power and responsibilities among the various levels of government.
Therefore, in accordance with Executive Order 12612, it is determined
that this proposal would not have sufficient federalism implications to
warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 adding the following new
airworthiness directive:
Lockheed: Docket 98-NM-314-AD.
Applicability: All Model L-1011-385 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 request approval for an
alternative method of compliance in accordance with paragraph (c) 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:
Modification
(a) Within 24 months after the effective date of this AD,
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
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.
Spares
(b) As of the effective date of this AD, no person shall install
on any airplane, an engine turbine cooling air panel assembly, part
number 1559672, or a pilot's caution and warning light panel
assembly on the main instrument panel, unless it has been modified
in accordance with paragraphs (a)(1) and (a)(2) of this AD, as
applicable.
Alternative Methods of Compliance
(c) 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 Aircraft Certification Office (ACO), FAA, Small
Airplane Directorate.
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
(d) Special flight permits may be issued in accordance with
Secs. 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.
Issued in Renton, Washington, on November 16, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-30371 Filed 11-19-99; 8:45 am]
BILLING CODE 4910-13-P
