[Federal Register Volume 63, Number 207 (Tuesday, October 27, 1998)]
[Proposed Rules]
[Pages 57262-57263]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-28667]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-241-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385-1 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 certain Lockheed Model L-1011-385-
1 series airplanes. This proposal would require modification of the
power drive units and the lower drive sprocket assemblies of the galley
lift system. This proposal is prompted by a report indicating that, due
to fatigue cracking, the primary and secondary drive shafts of the
galley lift failed and caused the galley lift to drop to the lower
level, injuring a flight attendant. The actions specified by the
proposed AD are intended to prevent such fatigue cracking of the
primary and secondary drive shafts, which could result in complete
fracturing of the secondary shaft; such fracturing could allow the
galley lift to drop to the bottom of the shaft, and could result in
possible injury to crewmembers.
DATES: Comments must be received by December 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-241-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 (LASSC),
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, 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-241-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-241-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that the primary and
secondary drive shafts of the lower galley lift failed on a Lockheed L-
1011-385-1 series airplane. This failure resulted in the galley lift
dropping to the lower level, and consequent injury to a flight
attendant. This incident was caused by undetected fatigue cracking of
the secondary shaft. Such fatigue cracking, if not detected and
corrected in a timely manner, could result in complete fracturing of
the secondary shaft, which could allow the galley lift to drop to the
bottom of the shaft, and possible injury to crewmembers.
Explanation of Relevant Service Information
The FAA has reviewed and approved Lockheed Service Bulletin 093-25-
294, Revision 2, dated April 13, 1981, which describes procedures for
modification of the power drive units and the lower drive sprocket
assemblies of the galley lift system. The modification includes
reworking and reidentifying the (left and right) power drive units and
the lower drive sprocket assemblies. Accomplishment of the actions
specified in the Lockheed service bulletin is intended to adequately
address the identified unsafe condition.
The Lockheed service bulletin references Lear Siegler, Inc.,
Service Bulletins 21192-25-08, Revision 1, dated October 19, 1979;
21192-25-09 dated August 17, 1979; and 65806-25-03, dated June 9, 1979;
as additional sources of service information for the modification of
the power drive units and the lower drive sprocket assemblies.
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
[[Page 57263]]
type design, the proposed AD would require accomplishment of the
actions specified in the Lockheed service bulletin described
previously, except as described below.
Differences Between the Proposed Rule and Service Bulletin
Operators should note that, although the referenced Lockheed
service bulletin specifies that the spare power drive units and the
lower drive sprocket assemblies of the galley lift system are not
affected by this modification, this proposed AD would require such
spares of the galley lift system to be modified in accordance with this
AD prior to installation onto the galley lift system.
Cost Impact
There are approximately 148 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 77 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
16 work hours per airplane to accomplish the proposed modification, and
that the average labor rate is $60 per work hour. Required parts would
cost approximately $1,797 per airplane. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$212,289, or $2,757 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 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-241-AD.
Applicability: Model L-1011-385-1, L-1011-385-1-14, and L-1011-
385-1-15 series airplanes, equipped with lower deck galleys;
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 fatigue cracking of the primary and secondary drive
shafts, which could result in complete fracturing of the secondary
shaft, and consequent dropping of the galley lift to the bottom of
the shaft and possible injury to crewmembers, accomplish the
following:
(a) Within 18 months after the effective date of this AD, modify
the power drive units and the lower drive sprocket assemblies of the
galley lift system in accordance with Lockheed Service Bulletin 093-
25-294, Revision 2, dated April 13, 1981.
Note 2: The Lockheed service bulletin references Lear Siegler,
Inc., Service Bulletins 21192-25-08, Revision 1, dated October 19,
1979; 21192-25-09, dated August 17, 1979; and 65806-25-03, dated
June 9, 1979; as additional sources of service information for
modification of the power drive units and the lower drive sprocket
assemblies.
(b) As of the effective date of this AD, no person shall install
on any airplane a power drive unit of the galley lift system having
Lockheed part number (P/N) 671980-191 (Lear Siegler P/N 21192-004)
or a lower drive sprocket assembly having Lockheed P/N 671980-171
(Lear Siegler P/N 65806-313) unless it has been modified in
accordance with this AD.
(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 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.
(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.
Issued in Renton, Washington, on October 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-28667 Filed 10-26-98; 8:45 am]
BILLING CODE 4910-13-P