[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