[Federal Register Volume 65, Number 84 (Monday, May 1, 2000)]
[Rules and Regulations]
[Pages 25280-25281]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-10286]



[[Page 25280]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-221-AD; Amendment 39-11706; AD 2000-08-20]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011-385 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 series airplanes, that 
requires modification of the high pressure bleed valve controller of 
each engine. This amendment is prompted by reports of failure of the 
bleed air system components such as the thermal compensators and bleed 
air ducts. The actions specified by this AD are intended to prevent 
such failures of the bleed air system components, which could result in 
high temperature air leaking into the cabin and/or cargo areas and 
could possibly require an emergency landing and evacuation.

DATES: Effective June 5, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 5, 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 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 
series airplanes was published in the Federal Register on October 6, 
1999 (64 FR 54232). That action proposed to require modification of the 
high pressure bleed valve controller of each engine.
    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 proposed rule.

Request to Specify Lockheed Service Bulletin Reference to Hamilton 
Standard Service Bulletin

    One commenter, the manufacturer, requests that the language in NOTE 
2 of the proposal be revised to reflect that the Lockheed Service 
Bulletin 093-36-065, dated February 9, 1999, specifically references 
Hamilton Standard Service Bulletin 36-1060 R1, dated March 1, 1997.
    The FAA concurs with the commenter's request and has revised NOTE 2 
of the final rule accordingly.

Request to Extend the Compliance Time

    One commenter, an airline operator, requests that the compliance 
time for the proposed modification be revised to coincide with a ``C'' 
check interval. The commenter states that the proposed compliance time 
of 14 months does not match its ``C'' check interval of 19 months. The 
commenter explains that it will incur an undue financial burden unless 
the compliance time is extended to 19 months since it is necessary to 
remove an airplane from service in order to accomplish the tasks 
associated with the proposal.
    The FAA does not concur. The modification of the bleed valve 
controller itself (installing the new check valve) can be accomplished 
previous to installation of the bleed valve controller on the airplane. 
The FAA estimates that the installation of the modified bleed valve 
controller will take 1 work hour to accomplish. If installation of the 
modified check valve is performed with the controller mounted on the 
engine, the installation can still be accomplished in approximately 2 
work hours. Therefore, the FAA considers that it is not necessary to 
accomplish the required modification during an extended downtime of a 
``C'' check. Therefore, it is unnecessary to revise the final rule.

Request to Revise the ``Differences'' Section

    One commenter, the manufacturer, requests that the FAA revise the 
``Differences Between Proposed Rule and Service Information'' section 
of the proposal to specify ``this proposed AD would require the 
modification of both high pressure bleed valve controller types to a 
later configuration (P/N 739084-4) with the installation of the 
restrictor check valve P/N 764898-2 or later.''
    The FAA acknowledges that the ``Differences Between Proposed Rule 
and Service Information'' section of the proposed AD, as revised by the 
commenter clarifies the intent of the proposed rule. However, since 
that section of the preamble does not reappear in the final rule, no 
change to the final rule is necessary.

Request to Specify Certain High Pressure Bleed Valve Controllers

    That same commenter, the manufacturer, requests that paragraph (b) 
of the proposal be revised to specify particular high pressure bleed 
valve controllers. The commenter suggests that the revised paragraph 
should read that ``No person shall install on any airplane a high 
pressure bleed valve controller, Hamilton Standard P/N 739084-2 or 
739084-3 (Lockheed P/N 672286-103 or 672286-105), unless it has been 
modified in accordance with this AD.'' The FAA concurs and has revised 
paragraph (b) of the final rule accordingly.

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 Model L-1011-385 series airplanes of 
the affected design in the worldwide fleet. The FAA estimates that 116 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 2 work hours per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Required 
parts will cost approximately $650 per airplane. Based on these 
figures, the cost impact of the AD on U.S. operators is estimated to be 
$89,320, or $770 per airplane.

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    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:

2000-08-20  Lockheed: Amendment 39-11706. Docket 99-NM-221-AD.

    Applicability: Model L-1011-385-1, -1-14, -1-15, and -3 series 
airplanes, equipped with high pressure bleed valve controller 
Hamilton Standard part number (P/N) 739084-2 or 739084-3 (Lockheed 
P/N 672286-103 or 672286-105); 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 failures of the bleed air system components, which 
could result in high temperature air leaking into the cabin and/or 
cargo areas and could possibly require an emergency landing and 
evacuation, accomplish the following:
    (a) Within 14 months after the effective date of this AD, modify 
the high pressure bleed valve controller of each engine in 
accordance with Lockheed Service Bulletin 093-36-065, dated February 
9, 1999.

    Note 2: Lockheed Service Bulletin 093-36-065, dated February 9, 
1999, references Hamilton Standard Service Bulletin 36-1060, 
Revision 1, dated March 1, 1977, as an additional source of service 
information for the modification of the high pressure bleed valve 
controller of each engine.

    (b) As of the effective date of this AD, no person shall install 
on any airplane a high pressure bleed valve controller having 
Hamilton Standard part number (P/N) 739084-2 or 739084-3 (Lockheed 
P/N 672286-103 or 672286-105), unless it has been modified in 
accordance with this AD.

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, 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.

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 093-36-065, dated February 9, 1999. 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, 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 June 5, 2000.

    Issued in Renton, Washington, on April 19, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-10286 Filed 4-28-00; 8:45 am]
BILLING CODE 4910-13-U