AD 2000-17-10

[Federal Register Volume 65, Number 171 (Friday, September 1, 2000)]
[Rules and Regulations]
[Pages 53157-53158]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-22122]



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Federal Register / Vol. 65, No. 171 / Friday, September 1, 2000 / 
Rules and Regulations

[[Page 53157]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-314-AD; Amendment 39-11884; AD 2000-17-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Lockheed Model L-1011-385 series airplanes, that 
requires 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 amendment 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 this 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: Effective October 6, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 6, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion 
Street, Greenville, South Carolina 29605. This information may be 
examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, 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, 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 all Lockheed Model L-1011-385 
series airplanes was published in the Federal Register on November 22, 
1999 (64 FR 63755). That action proposed to 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter supports the proposal.

Request To Extend the Compliance Time

    Two commenters support the intent of the proposed AD, but request 
that the compliance time for the proposed modification be extended from 
24 months, as specified in the proposal, to 36 months. One of the 
commenters states that in-service statistics indicate that the rate at 
which the unsafe condition (i.e., fire burn through from the high speed 
gear box) arises occurs on the order of 10<SUP>-</SUP>\7\ per airplane 
flying hour. The other commenter contends that, because of the low risk 
of the identified unsafe condition occuring and the average airplane 
usage, safety would not be compromised by extending the compliance 
time.
    The FAA does not concur with the commenters' requests to extend the 
compliance time. In developing an appropriate compliance time for this 
action, the FAA considered not only the degree of urgency associated 
with addresssing the subject unsafe condition, but the practical aspect 
of accomplishing the work necessary to perform the modifications 
(estimated at 24 work hours in the proposal). In consideration of these 
items, the FAA has determined that 24 months represents an appropriate 
interval of time allowable wherein the modfications can be accomplished 
during scheduled maintenance intervals for the majority of affected 
operators, and an acceptable level of safety can be maintained.

Since the Issuance of the Proposal

    In the proposed rule, the FAA inadvertently estimated the cost for 
accomplishing the modifications as $7,790 per airplane, or $911,430 for 
the affected fleet. Those costs actually reflect the estimated cost of 
workshours for the airplane but only the parts costs for one engine, 
rather than for three engines. Additionally, the proposed rule 
contained a typographical error on the estimated cost of the parts. 
Instead of $6,350, the correct estimate is $6,320 per engine. The FAA 
has, therefore, revised this final rule to reflect the correct 
estimated costs of $2,386,800, or $20,400 per airplane.

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 with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

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 
will be affected by this AD, that it will take approximately 8 work 
hours per engine, or 24 work hours per airplane to accomplish the 
required modifications. The FAA estimates that the average

[[Page 53158]]

labor rate is $60 per work hour. Required parts will cost approximately 
$6,320 per engine, or $18,960 per airplane. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $2,386,800, 
or $20,400 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2000-17-10 Lockheed: Amendment 39-11884. 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. 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).

    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 
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.

Incorporation by Reference

    (e) The actions shall be done in accordance with Lockheed 
Service Bulletin 093-77-059, dated February 25, 1998; or Lockheed 
Service Bulletin 093-77-059, Revision 1, dated February 2, 1999. 
Revision 1 of Lockheed Service Bulletin 093-077-059, contains the 
following list of effective pages:

------------------------------------------------------------------------
                           Revision level shown
      Page  number               on page            Date shown on page
------------------------------------------------------------------------
1, 4....................  1....................  February 2, 1999.
2, 3, 5-9...............  Original.............  February 25, 1998.
------------------------------------------------------------------------

    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 Martin Aircraft & 
Logistics Center, 120 Orion Street, Greenville, South Carolina 
29605. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
FAA, 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 October 6, 2000.

    Issued in Renton, Washington, on August 24, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-22122 Filed 8-31-00; 8:45 am]
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