[Federal Register Volume 63, Number 229 (Monday, November 30, 1998)]
[Proposed Rules]
[Pages 65718-65719]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31699]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-289-AD]
RIN 2120-AA64
Airworthiness Directives; Short Brothers Model SD3-60 SHERPA
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 all Short Brothers Model SD3-60
SHERPA series airplanes. This proposal would require a one-time visual
inspection to determine the part number of the power control cable
assemblies and pulleys of the engine controls; and replacement of the
power control cable assemblies and pulleys (as applicable) with new
parts, if necessary. This proposal is prompted by issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by the proposed AD are intended to
prevent breakage of the power control cable assemblies due to the
inflexible construction of the cable, which could result in loss of
engine power and consequent reduced controllability of the airplane.
DATES: Comments must be received by December 30, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-289-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 Short Brothers, Airworthiness & Engineering Quality, P.O.
Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. This
information may be examined at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
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 98-NM-289-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. 98-NM-289-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified the FAA that an unsafe
condition may exist on all Short Brothers Model SD3-60 SHERPA series
airplanes. The CAA advises that the existing power control cable
assemblies are subject to breakage, which is caused by the inflexible
construction of the cable. The manufacturer has introduced a more
flexible construction of the cable, which was incorporated during
production of the subject airplanes, however, the possibility does
exist that not all airplanes were modified. Breakage of the power
control cable assemblies due to the inflexible construction of the
cable, if not corrected, could result in loss of engine power and
consequent reduced controllability of the airplane.
[[Page 65719]]
Explanation of Relevant Service Information
The manufacturer has issued Service Bulletin SD3-60 SHERPA-76-1,
dated July 1998, which describes procedures for a one-time visual
inspection to determine the part number of the power control cable
assemblies and pulleys of the engine controls; and replacement of the
power control cable assemblies and pulleys (as applicable) with new
parts, if necessary. Accomplishment of the actions specified in the
service bulletin is intended to adequately address the identified
unsafe condition. The CAA classified this service bulletin as mandatory
and issued British airworthiness directive 004-07-98 in order to assure
the continued airworthiness of these airplanes in the United Kingdom.
FAA's Conclusions
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletin described previously.
Cost Impact
The FAA estimates that 28 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 15 work
hours per airplane to accomplish the proposed inspection, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the proposed inspection by this AD on U.S. operators is
estimated to be $25,200, or $900 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.
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:
Short Brothers, PLC: Docket 98-NM-289-AD.
Applicability: All Model SD3-60 SHERPA series airplanes,
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 breakage of the power control cable assemblies due to
the inflexible construction of the cable, which could result in loss
of engine power and consequent reduced controllability of the
airplane, accomplish the following:
(a) Within 1,200 flight hours after the effective date of this
AD, perform a one-time visual inspection to determine the part
number (P/N) of the power control cable assemblies and pulleys of
the engine controls, in accordance with Part A of the Accomplishment
Instructions of Shorts Service Bulletin SD3-60 SHERPA-76-1, dated
July 1998.
(1) If any power control cable assembly having P/N SD3-47-1091
or SD3-47-1094 is found, prior to further flight, replace the power
control cable assembly with a new power control cable assembly in
accordance with Part B of the Accomplishment Instructions of the
service bulletin.
(2) If any pulley having P/N C181605 is found, prior to further
flight, replace the pulley with a new pulley in accordance with Part
C of the Accomplishment Instructions of the service bulletin.
(b) As of the effective date of this AD, no person shall install
on the engine controls of any airplane a cable assembly having P/N
SD3-47-1091 or SD3-47-1094, or any pulley having P/N C181605.
(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, International Branch, ANM-116, FAA,
Transport 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, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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.
Note 3: The subject of this AD is addressed in British
airworthiness directive 004-07-98.
Issued in Renton, Washington, on November 20, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-31699 Filed 11-27-98; 8:45 am]
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