[Federal Register Volume 60, Number 26 (Wednesday, February 8, 1995)]
[Proposed Rules]
[Pages 7480-7482]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3073]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-240-AD]
Airworthiness Directives; Lockheed Model 382 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Lockheed Model 382
series airplanes, that currently requires a revision to the Airplane
Flight Manual to require takeoff operation in accordance with revised
performance data. This action would require installation of certain
valve housings for the propeller [[Page 7481]] governor on the outboard
engines. This proposal is prompted by a report of a change that had
been incorporated into the propeller governor of these airplanes during
production, which altered the thrust decay characteristic of the
propeller when operating in an engine failure scenario. The actions
specified by the proposed AD are intended to ensure that the airplane
maintains adequate thrust decay characteristics in the event of
critical engine failure during takeoff.
DATES: Comments must be received by April 6, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-240-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 Aeronautical Systems Support Company, 2251 Lake
Park Drive, Smyrna, Georgia 30080. This information may be examined at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Atlanta Aircraft Certification Office, 1701
Columbia Avenue, Suite 2-160, College Park, Georgia.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
FAA, Flight Test Branch, ACE-160, Small Airplane Directorate, Atlanta
Aircraft Certification Office, Campus Building, 1701 Columbia Avenue,
Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-
7367; fax (404) 305-7348.
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 94-NM-240-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-103, Attention: Rules
Docket No. 94-NM-240-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On June 23, 1994, the FAA issued AD 94-14-09, amendment 39-8961 (59
FR 35236, July 11, 1994), applicable to certain Lockheed Model 382
series airplanes, to require a revision to the Airplane Flight Manual
(AFM) to require takeoff operation in accordance with revised
performance data. That action was prompted by a report of a change that
had been incorporated into the propeller governor of these airplanes
during production, which altered the thrust decay characteristic of the
propeller when operating in an engine failure scenario. The
requirements of that AD are intended to ensure that the airplane is
operated at sufficient speeds to mitigate the problems associated with
a faster thrust decay and to prevent the airplane from departing the
side of the runway.
In the preamble to AD 94-14-09, the FAA indicated that the AFM
revision required by that AD was considered to be only ``interim
action'' until a design change in the propeller governor was developed
to address the ground minimum control speed (Vmcg) characteristics. The
FAA also indicated that, once such a design change was developed,
approved, and available, the FAA would consider further rulemaking on
this subject.
The manufacturer recently has advised the FAA that it has been
unable to develop a new modification of the subject governors (which
have servo-type valve housing assemblies, having part number 714325-2,
-3, -5, -6, or -7) that would provide adequate thrust decay
characteristics. However, the manufacturer has advised that propeller
governors with valve housing assemblies having part number 714325-1,
which were manufactured before the line production change, do provide
adequate thrust decay characteristics. On the basis of the data
presented, the FAA finds that installation of these valve housing
assemblies having part number 714325-1 will ensure adequate thrust
decay characteristics in the event of a critical engine failure during
takeoff and, thus, will positively address the unsafe condition
presented by fast thrust decay. This proposed rulemaking follows from
that determination.
Since the problem associated with maintaining adequate thrust decay
characteristics of the propeller when operating in an engine failure
scenario is likely to exist or develop on other products of this same
type design, the proposed AD would supersede AD 94-14-09 to require
removal of any servo-type valve housing assembly, having part number
714325-2, -3, -5, -6, or -7 installed on any outboard engine, and
replacement of those assemblies with part number 714325-1. Replacement
would be required in accordance with Lockheed Document SMP-515C, Card
No. CO-135. The proposed compliance time of 24 months is considered
adequate to accomplish the replacement during normal maintenance
schedules, and also is considered to be ample time for obtaining
required parts. Installation of valve housing assemblies, having part
number 714325-1, would constitute terminating action for the takeoff
operation procedures required by AD 94-14-09; once the replacement is
accomplished, the previously required AFM revision could be removed.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this requirement.
There are approximately 112 Model 382, 382E, and 382G series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 18 [[Page 7482]] airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 8 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would cost
approximately $90,000 per airplane. Based on these figures, the total
cost impact of the proposed AD on U.S. operators is estimated to be
$1,628,640, or $90,480 per airplane.
The FAA has been advised that the only U.S. operator of Lockheed
Model 382 series airplanes has already equipped half of its fleet (9
airplanes) with the valve housing assembly that would be required by
this proposed rule. Therefore, the future economic cost of this rule on
U.S. operators is now only $814,320.
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.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8961 (59 FR
35236, July 11, 1994), and by adding a new airworthiness directive
(AD), to read as follows:
Lockheed: Docket 94-NM-240-AD. Supersedes AD 94-14-09, Amendment 39-
8961.
Applicability: Model 382, 382E, and 382G series airplanes;
equipped with a servo-type valve housing assembly, having part
number 714325-2, -3, -5, -6, or -7, installed on any outboard
engine; 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 use the authority
provided in paragraph (c) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To ensure that the airplane maintains adequate thrust decay
characteristics in the event of critical engine failure during
takeoff, accomplish the following:
(a) Within 60 days after August 10, 1994 (the effective date of
AD 94-14-09, amendment 39-8961), revise the Limitations and
Performance Data Sections of the FAA- approved Airplane Flight
Manual (AFM) to include information specified in Lockheed Airplane
Flight Manual Supplement 382-16, dated August 11, 1993, and operate
the airplane accordingly thereafter. The requirements of this
paragraph may be accomplished by inserting AFM Supplement 382-16
into the AFM.
(b) Within 24 months after the effective date of this AD,
replace the servo-type valve housing assemblies having part number
714325-2, -3, -5, -6, or -7, with part number 714325-1, on the
propeller governors installed on the outboard engines, in accordance
with Lockheed Document SMP-515C, Card No. CO-135. Replacement of
these assemblies with part number 714325-1, constitutes terminating
action for the requirements of paragraph (a) of this AD; once the
replacement is accomplished, the AFM revision may be removed.
Note 2: Propeller governors with servo-type valve housing
assemblies having part number 714325-2, -3, -5, -6, or -7, may be
retained or replaced with part number 714325-1 for use on the
inboard engine positions.
(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.
Issued in Renton, Washington, on February 2, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-3073 Filed 2-7-95; 8:45 am]
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