[Federal Register Volume 60, Number 106 (Friday, June 2, 1995)]
[Rules and Regulations]
[Pages 28715-28716]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-13505]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-240-AD; Amendment 39-9255; AD 95-12-05]
Airworthiness Directives; Lockheed Model 382 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes 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
amendment requires installation of certain valve housings for the
propeller governor on the outboard engines. This amendment 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 this AD are intended to
ensure that the airplane maintains adequate thrust decay
characteristics in the event of critical engine failure during takeoff.
DATES: Effective July 3, 1995.
The incorporation by reference of Lockheed Airplane Flight Manual
Supplement 382-16, dated August 11, 1993, as listed in the regulations,
was approved previously by the Director of the Federal Register as of
August 10, 1994 (59 FR 35236, July 11, 1994).
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Aeronautical Systems Support Company (LASSC),
Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive,
Smyrna, Georgia 30080. 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, Small Airplane Directorate,
Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park,
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,
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 94-14-09,
amendment 39-8961 (59 FR 35236, July 11, 1994), which is applicable to
certain Lockheed Model 382 series airplanes, was published in the
Federal Register on February 8, 1995 (60 FR 7480). The action proposed
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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
There are approximately 112 Model 382, 382E, and 382G series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 18 airplanes of U.S. registry will be affected by this
AD, that it will take approximately 8 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 $90,000 per
airplane. Based on these figures, the total cost impact of the 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 will be required by
this rule. Therefore, the future economic cost of this rule on U.S.
operators is now only $814,320.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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. 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), amendment 39-9255, to read as follows:
95-12-05 Lockheed: Amendment 39-9255. 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 [[Page 28716]] 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.
(e) The AFM revision shall be done in accordance with Lockheed
Airplane Flight Manual Supplement 382-16, dated August 11, 1993. The
incorporation by reference of this document was approved previously
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51 as of August 10, 1994 (59 FR 35236, July
11, 1994). Copies may be obtained from Lockheed Aeronautical Systems
Support Company (LASSC), Field Support Department, Dept. 693, Zone
0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Atlanta Aircraft
Certification Office, Small Airplane Directorate, Campus Building,
1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
(f) This amendment becomes effective on July 3, 1995.
Issued in Renton, Washington, on May 26, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-13505 Filed 6-1-95; 8:45 am]
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