[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
