[Federal Register Volume 64, Number 193 (Wednesday, October 6, 1999)]
[Proposed Rules]
[Pages 54232-54234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25933]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-221-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011-385 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 
series airplanes. This proposal would require modification of the high 
pressure bleed valve controller of each engine. This proposal 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 the proposed 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: Comments must be received by November 22, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-221-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 Martin Aircraft & Logistics Center, 120 Orion 
Street, Greenville, South Carolina 29605. This information

[[Page 54233]]

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 99-NM-221-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. 99-NM-221-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of failures of the bleed air system 
components, such as the thermal compensators and bleed air ducts, on 
certain Lockheed Model L-1011-385 series airplanes. Investigation 
revealed that during a selection of the anti-ice mode, a sudden 
overpressure spike condition of the bleed air system can occur. This 
overpressure spike condition is caused when the engine high pressure 
bleed valve is opened rapidly by its controller. This overpressure has 
contributed to failures of the bleed air system components. Such 
failures of the bleed air system components, if not corrected, could 
result in high temperature air leaking into the cabin and/or cargo 
areas and could possibly require an emergency landing and evacuation.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed Service Bulletin 093-36-
065, dated February 9, 1999, which describes procedures for 
modification of the high pressure bleed valve controller of each 
engine. The modification involves the installation of a specific 
restrictor check valve into the high pressure bleed valve controller of 
each engine. Accomplishment of the action specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.
    The Lockheed service bulletin references Hamilton Standard Service 
Bulletin 36-1060, Revision 1, dated March 1, 1977, as an additional 
source of service information for accomplishing the modification.

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 type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously, except as discussed below.

Differences Between Proposed Rule and Service Information

    Operators should note that the Lockheed service bulletin (described 
previously) provides service information for accomplishing the 
modification of the high pressure bleed valve controller with the 
installation of Hamilton Standard restrictor check valve part number 
(P/N) 764898-2 in the high pressure bleed valve controller P/N 739084-
3. However, this proposed AD would be applicable to those airplanes 
that are equipped with high pressure bleed valve controller P/N 739084-
2 or 739084-3. The high pressure bleed valve controller P/N 739084-2 
has no restrictor check valve installed, and the bleed valve controller 
P/N 739084-3 has a restrictor check valve installed that occasionally 
causes an inability to supply bleed augmentation. To reduce the 
probability of either a rupture of the bleed air system or the 
inability to deliver additional bleed, this proposed AD would require 
the modification of both high pressure bleed valve controller types to 
the latest configuration (P/N 739084-4) with the installation of the 
restrictor check valve P/N 764898-2.

Cost Impact

    There are approximately 235 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
2 work hours per airplane to accomplish the proposed replacement, and 
that the average labor rate is $60 per work hour. Required parts would 
cost approximately $650 per airplane. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $89,320, 
or $770 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.

[[Page 54234]]

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 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: Hamilton Standard has issued 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, 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.
    Issued in Renton, Washington, on September 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25933 Filed 10-5-99; 8:45 am]
BILLING CODE 4910-13-U