[Federal Register Volume 62, Number 193 (Monday, October 6, 1997)]
[Proposed Rules]
[Pages 52053-52055]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-26377]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-106-AD]
Airworthiness Directives; Short Brothers Model SD3-60 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
series airplanes. This proposal would require repetitive inspections to
detect corrosion and/or wear of the top and bottom shear decks of the
left and right stub wings in the area of the forward pintle pin of the
main landing gear (MLG), and repair, 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 detect and correct corrosion and/or
wear of the top and bottom shear decks of the left and right stub wings
in the area of the forward pintle pin of the MLG, which could result in
failure of the MLG to extend or retract.
DATES: Comments must be received by November 5, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-106-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 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: Gary Lium, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1112; fax (425) 227-1149.
[[Page 52054]]
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 97-NM-106-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. 97-NM-106-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 series
airplanes. The CAA advises that it has received reports of corrosion
and/or wear of the top and bottom shear decks of the left and right
stub wings in the area of the forward pintle pin of the main landing
gear (MLG). The corrosion and/or wear was attributed to migration of
the retaining pin of the forward pintle pin of the MLG due to loss of
the retaining pin's circlip. Such corrosion or wear of the top and
bottom shear decks of the left and right stub wings in the area of the
forward pintle pin of the MLG, if not detected and corrected in a
timely manner, could result in failure of the MLG to extend or retract.
Explanation of Relevant Service Information
Short Brothers has issued Service Bulletin SD360-53-42, dated
September 1996, which describes procedures for repetitive inspections
to detect corrosion and/or wear of the top and bottom shear decks of
the left and right stub wings in the area of the forward pintle pin of
the MLG, and repair, if necessary. For airplanes on which certain
depths of corrosion or wear is detected, the service bulletin describes
procedures for a visual inspection to detect any discrepancy of the
pintle pin and sleeve. The CAA classified this service bulletin as
mandatory and issued British airworthiness directive 005-09-96 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 Sec. 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, the
proposed AD would require repetitive inspections to detect and correct
corrosion and/or wear of the top and bottom shear decks of the left and
right stub wings in the area of the forward pintle pin of the MLG, and
repair of any corrosion and/or wear. Those actions are required to be
accomplished in accordance with the service bulletin described
previously.
Differences Between the Proposal and the related CAA AD
Operators should note that for certain depths of corrosion and/or
wear detected that require an inspection of the pintle pin and sleeve,
this AD requires the repair of any discrepancy of the pintle pin or
sleeve to be accomplished in accordance with a method approved by the
FAA.
Cost Impact
The FAA estimates that 88 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 13 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
total cost impact of the proposed AD on U.S. operators is estimated to
be $68,640, or $780 per airplane.
The total 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:
[[Page 52055]]
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 97-NM-106-AD.
Applicability: All Model SD3-60 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
otherwise 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) of this AD 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 prevent failure of the main landing gear (MLG) to extend or
retract due to corrosion and/or wear of the left and right stub
wings in the area of the forward pintle pin of the MLG, accomplish
the following:
(a) Within 90 days after the effective date of this AD, conduct
an inspection for corrosion of the top and bottom shear decks of the
left and right stub wings in the area of the forward pintle pin of
the MLG, and measure the retaining pin holes of the pintle pin for
wear; in accordance with Part A. of the Accomplishment Instructions
of Short Brothers Service Bulletin SD360-53-42, dated September
1996.
(1) If any corrosion, wear, or measurement of the holes for the
retaining pin of the pintle pin is found that is within the limits
specified in Part A. of the Accomplishment Instructions of the
service bulletin, prior to further flight, repair the discrepancy in
accordance with the service bulletin. Thereafter, repeat the
inspection required by paragraph (a) of this AD at intervals not to
exceed 6 months.
(2) If any corrosion, wear, or measurement of the holes for the
retaining pin of the pintle pin is found that is beyond the limits
specified in Part A. of the Accomplishment Instructions of the
service bulletin, prior to further flight, perform the actions
required by paragraph (a)(2)(i) and (a)(2)(ii) of this AD.
(i) Remove the corrosion and install bushings on the upper and
lower shear webs in the retaining pin holes for the pintle pin in
accordance with Part B. (left MLG) and/or Part C. (right MLG), as
applicable, of the Accomplishment Instructions of the service
bulletin.
(ii) Perform a visual inspection of the pintle pin and the
sleeve for any discrepancy, in accordance with Part B. and/or Part
C., as applicable, of the Accomplishment Instructions of the service
bulletin.
(A) If no discrepancy is detected, the pintle pin and the sleeve
of the pintle pin may be returned to service.
(B) If any discrepancy of the pintle pin and sleeve is detected,
prior to further flight, repair the pintle pin and sleeve in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(b) Removal of corrosion and installation of bushings in
accordance with Part B. and/or Part C., as applicable, of the
Accomplishment Instructions of Short Brothers Service Bulletin
SD360-53-42, dated September 1996, constitutes terminating action
for the repetitive inspection requirements of this AD.
(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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
Special flight permits may be issued in accordance with
Secs. 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 005-09-96.
Issued in Renton, Wash., on September 30, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-26377 Filed 10-3-97; 8:45 am]
BILLING CODE 4910-13-U
