[Federal Register Volume 62, Number 138 (Friday, July 18, 1997)]
[Proposed Rules]
[Pages 38491-38493]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-18935]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-59-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011 Series Airplanes
Equipped With Rolls Royce Model RB211-22B Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Lockheed Model L-
1011 series airplanes, that currently requires various modifications
and corrective actions to prevent a potential fire hazard caused by
heat damage to the flex fuel feed line from an undetected gearbox fire.
In lieu of the various modifications and corrective actions, that AD
also provides for an optional terminating action (i.e., installation of
a vent air tube in the gear compartment and thickened gearbox housings)
for another existing AD. For airplanes on which that optional
terminating action has been accomplished, this action would require
accomplishment of the various modifications and corrective actions.
This proposal is prompted by a report indicating that, due to bearing
failure, an in-flight fire occurred on an airplane on which a thickened
gearbox housing was installed. The actions specified by the proposed AD
are intended to detect and correct bearing failure, which could lead to
a fire in the gearbox.
DATES: Comments must be received by August 25, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-59-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
The service information referenced in the proposed rule may be
obtained from Lockheed Aeronautical Systems Support Company, Field
Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna,
Georgia 30080. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the FAA, Atlanta Aircraft Certification Office, Campus Building, 1701
Columbia Avenue, Suite 2-160, College Park, Georgia.
FOR FURTHER INFORMATION CONTACT: Thomas B. Peters, Aerospace Engineer,
Systems and Flight Test Branch, ACE-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:
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,
[[Page 38492]]
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 96-NM-59-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-103, Attention: Rules
Docket No. 96-NM-59-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On March 25, 1987, the FAA issued AD 87-07-10, amendment 39-5597
(52 FR 10736, April 3, 1987), applicable to certain Lockheed Model L-
1011 series airplanes, equipped with Rolls Royce Model RB211-22B
engines. That AD currently requires various modifications and
corrective actions that constitute terminating action for AD 85-09-03,
amendment 39-5056 (50 FR 18553, May 3, 1985). (These various
modifications include installation of: a fire detector segment, a
modified gearbox breather duct, and a vent air tube in the gear
compartment.) In lieu of the various modifications and corrective
actions, that AD also provides for an optional terminating action
(i.e., installation of a vent air tube in the gear compartment and
installation of thickened gearbox housings) for the requirements of AD
85-09-03. AD 87-07-10 was prompted by reports of gearbox fires, which
were caused by failed bearings. The requirements of that AD are
intended to prevent a potential fire hazard, as a result of heat damage
to the flex fuel feed line from an undetected gearbox fire.
At the time of issuance of AD 87-07-10, the FAA had not received
any reports of bearing failure on Lockheed Model L-1011 series
airplanes equipped with Rolls Royce Model RB211-524 series engines on
which thickened gearbox housings were installed. Since Rolls Royce
Model RB211-22B engines are similar in design to Model RB211-524 series
engines, the FAA determined that installation of thickened housings on
Model RB211-22B engines would prevent bearing failure that could cause
a gearbox fire. Therefore, the FAA included the installation of such
housings as optional terminating action in AD 87-07-10.
Actions Since Issuance of Previous AD
Since the issuance of that AD, the FAA has received a report
indicating that an in-flight fire occurred in a thickened gearbox
housing on a Rolls Royce Model RB211-524 series engine installed on a
Lockheed Model L-1011 series airplane. (This housing was installed on
Model L-1011 series airplanes equipped with Rolls Royce Model RB211-22B
engines as an optional terminating action of AD 87-07-10.) In light of
this report, the FAA has determined that the optional terminating
action of AD 87-07-10 does not adequately preclude bearing failure, as
previously believed. Bearing failure, if not detected and corrected,
could lead to a fire in the gearbox.
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 supersede AD 87-07-10 to continue to require various
modifications and corrective actions, which constitute terminating
action for AD 85-09-03. For airplanes on which the optional terminating
action specified in AD 87-07-10 has been accomplished, this AD would
add a requirement to accomplish the various modifications and
corrective actions. The actions would be required to be accomplished in
accordance with the service bulletins described previously in AD 87-07-
10.
Other Relevant Rulemaking
The FAA has previously issued AD 94-03-10, amendment 39-8817 (59 FR
6535, February 11, 1994), which is applicable to certain Lockheed Model
L-1011 series airplanes equipped with Rolls Royce Model RB211-524
series engines. That AD requires modification of the high speed gearbox
of the engines. Operators should note that this proposed AD would not
affect the current requirements of AD 94-03-10.
Cost Impact
There are approximately 130 Lockheed Model L-1011 series airplanes
equipped with Rolls Royce Model RB211-22B engines of the affected
design in the worldwide fleet. The FAA estimates that 76 airplanes of
U.S. registry would be affected by this proposed AD.
The proposed installation of a fire detector segment would take
approximately 3 work hours per engine (3 engines per airplane) to
accomplish, at an average labor rate of $60 per work hour. Required
parts for Walter-Kidde systems would cost approximately $2,100 per
engine. Required parts for Graviner systems would cost approximately
$8,100 per engine. Based on these figures, the cost impact on U.S.
operators of the installation proposed by this AD is estimated to be
$6,840 per airplane (for Walter-Kidde systems), or $24,840 per airplane
(for Graviner systems).
The proposed modification would take approximately 6 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Required parts would cost approximately $10,000 per airplane. Based on
these figures, the cost impact on U.S. operators of the modification
proposed by this AD is estimated to be $787,360, or $10,360 per
airplane.
The proposed introduction of a vent air tube would take
approximately 3 work hours per engine (3 engines per airplane) to
accomplish, at an average labor rate of $60 per work hour. Required
parts would cost approximately $500 per engine. Based on these figures,
the cost impact on U.S. operators of the introduction of a vent air
tube proposed by this AD is estimated to be $155,040, or $2,040 per
airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 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
[[Page 38493]]
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 removing amendment 39-5597 (52 FR
10736, April 3, 1987), and by adding a new airworthiness directive
(AD), to read as follows:
Lockheed: Docket 96-NM-59-AD. Supersedes AD 87-07-10, Amendment 39-
5597.
Applicability: Model L-1011 series airplanes equipped with Rolls
Royce RB211-22B engines, certificated in any category.
Note 1: If an operator has accomplished the requirements of
paragraphs (a) and (b) of this AD on any affected airplane and,
subsequently, installs a different Model RB211-22B engine on that
airplane, the airplane and all installed engines are still subject
to the requirements of this AD.
Note 2: 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 (e) 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 detect and correct bearing failure, which could lead to a
fire in the gearbox, accomplish the following:
(a) Within 8,000 flight hours or 30 months after May 8, 1987
(the effective date of AD 87-07-10, amendment 39-5597), whichever
occurs first, accomplish the procedures specified in the
Accomplishment Instructions of the service bulletins listed in
paragraphs (a)(1) and (a)(2) of this AD.
(1) Lockheed Service Bulletin 093-26-036, dated April 1, 1986,
Installation of Fire Detector Segment; and
(2) Lockheed Service Bulletin 093-71-067, Revision 1, dated
April 1, 1986, Gearbox Breather Duct Modification.
(b) Within 8,000 flight hours or 30 months after May 8, 1987,
whichever occurs first, accomplish the procedures specified in the
Accomplishment Instructions of the service bulletins listed in
paragraphs (b)(1) and (b)(2) of this AD.
(1) Rolls Royce Service Bulletin RB.211-72-4666, Revision 3,
dated October 14, 1977, Introduction of Vent Air Tube in Gear
Compartment; and
(2) Rolls Royce Service Bulletin RB.211-72-8138, dated March 21,
1986, Installation of Additional No. 7 Fire Sensor.
(c) For airplanes on which Rolls Royce Service Bulletin RB.211-
72-4666, Revision 3, dated October 14, 1977, and Rolls Royce Service
Bulletin RB.211-72-3878, Revision 3, dated June 25, 1976, have been
accomplished in accordance with paragraph C of AD 87-07-10: Within
48 months or 16,000 flight hours after the effective date of this
AD, whichever occurs first, accomplish the actions specified in
paragraphs (a) and (b) of this AD.
(d) Accomplishment of the requirements of paragraphs (a) and (b)
of this AD; or accomplishment of the requirements of paragraph (c)
of this AD; constitutes terminating action for the requirements of
AD 85-09-03, amendment 39-5056. The AFM limitations required by AD
85-09-03 may be removed following accomplishment of the terminating
action.
(e) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(f) 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.
Issued in Renton, Washington, on July 11, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-18935 Filed 7-17-97; 8:45 am]
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