Airworthiness Directives; Lockheed Model L-1011-385-1 Series Airplanes

[Federal Register Volume 64, Number 10 (Friday, January 15, 1999)]
[Rules and Regulations]
[Pages 2556-2558]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-810]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-241-AD; Amendment 39-10994; AD 99-02-05]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011-385-1 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Lockheed Model L-1011-385-1 series airplanes, 
that requires modification of the power drive units and the lower drive 
sprocket assemblies of the galley lift system. This amendment 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 this 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: Effective February 19, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 19, 1999.

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. This information may be examined at the Federal 
Aviation

[[Page 2557]]

Administration (FAA), Transport Airplane Directorate, Rules Docket, 
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; 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-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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Lockheed Model L-1011-385-
1 series airplanes was published in the Federal Register on October 27, 
1998 (63 FR 57262). That action proposed to require modification of the 
power drive units and the lower drive sprocket assemblies of the galley 
lift system.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
both comments received.
    The 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 148 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 77 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 16 work 
hours per airplane to accomplish the required modification, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $1,797 per airplane. Based on these figures, the cost 
impact of the 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 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 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 adding the following new 
airworthiness directive:

99-02-05  Lockheed: Amendment 39-10994. 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.
    (e) The modification shall be done in accordance with Lockheed 
Service Bulletin 093-25-294, Revision 2, dated April 13, 1981, which 
contains the following list of effective pages:

[[Page 2558]]



------------------------------------------------------------------------
                                 Revision level
           Page No.              shown on page      Date shown on page
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1, 3..........................  2..............  April 13, 1981.
2, 4-13.......................  Original.......  June 29, 1979.
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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. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown 
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (f) This amendment becomes effective on February 19, 1999.

    Issued in Renton, Washington, on January 7, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-810 Filed 1-14-99; 8:45 am]
BILLING CODE 4910-13-P

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