[Federal Register Volume 64, Number 175 (Friday, September 10, 1999)]
[Proposed Rules]
[Pages 49113-49115]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23621]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-365-AD]
RIN 2120-AA64
Airworthiness Directives; Aerospatiale Model SN-601 (Corvette)
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 Aerospatiale Model SN-601
(Corvette) series airplanes. This proposal would require repetitive
inspections, and repair if necessary, of the locking indication system
of the drag strut jack on the main landing gear (MLG) to detect
corrosion and damage resulting from its operation. This proposal would
also require replacement of seals and backup rings with new parts. 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 failure of the
locking indication system of the drag strut jack on the MLG due to
corrosion. Such corrosion could prevent the MLG from locking and result
in the subsequent collapse of the MLG.
DATES: Comments must be received by October 12, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-365-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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex
03, France. 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.
[[Page 49114]]
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-365-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-365-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on all Aerospatiale Model SN-601 (Corvette) series
airplanes. The DGAC advises that one occurrence of corrosion has been
reported in the locking indication system of the drag strut jack on the
main landing gear (MLG). Such corrosion could cause failure of the
locking indication system of the drag strut jack, which could prevent
the MLG from locking and result in the subsequent collapse of the MLG.
Explanation of Relevant Service Information
Messier-Dowty, the manufacturer of the affected MLG, has issued
Technical Instruction No. 20403, Issue 2, dated March 1998, which
describes procedures for repetitive inspections to detect corrosion and
other damage, and repair if necessary, of the locking indication system
of the drag strut jack on the MLG. The Technical Instruction also
describes procedures for verification of the free displacement of the
plungers, replacement of damaged parts with new parts, and replacement
of all seals and back up rings with new parts. Accomplishment of the
actions specified in the technical instruction is intended to
adequately address the identified unsafe condition. The DGAC classified
this technical instruction as mandatory and issued French airworthiness
directive 98-179-021(B), dated May 6, 1998, in order to assure the
continued airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France 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 DGAC has kept the FAA informed
of the situation described above. The FAA has examined the findings of
the DGAC, 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 technical instruction described
previously.
Cost Impact
The FAA estimates that 2 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 inspection, and that the
average labor rate is $60 per work hour. The cost of required parts
would be minimal. Based on these figures, the cost impact of the
proposed AD on U.S. operators is estimated to be $960, or $480 per
airplane, per inspection cycle.
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:
Aerospatiale: Docket 98-NM-365-AD.
Applicability: All Model SN-601 (Corvette) 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 (b) 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 failure of the locking indication system of the drag
strut jack on the main landing gear (MLG) due to corrosion that
could prevent the MLG from locking and result in the subsequent
collapse of the MLG, accomplish the following:
(a) Within 3,600 flight hours or 36 months after the effective
date of this AD, whichever
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occurs first, perform a detailed visual inspection to detect certain
discrepancies of the locking indication system on the drag strut
jack on the MLG, in accordance with Messier-Dowty Technical
Instruction No. 20403, Issue 2, dated March 1998. Prior to
reassembling the parts, replace all the seals and backup rings with
new parts, in accordance with the Technical Instruction.
(1) If no corrosion is found on either plunger, prior to further
flight, inspect for the free displacement of both plungers, in
accordance with the Technical Instruction.
(i) If the displacement of both plungers is free without any
hard points, repeat the inspection required by paragraph (a) of this
AD thereafter at intervals not to exceed 72 months.
(ii) If the displacement of either plunger is not free, prior to
further flight, replace the plunger with a new plunger, in
accordance with the Technical Instruction. Repeat the inspection
required by paragraph (a) of this AD thereafter at intervals not to
exceed 72 months.
(2) If corrosion is found on either plunger, prior to further
flight, replace the plunger with a new plunger, in accordance with
the Technical Instruction. Repeat the inspection thereafter at
intervals not to exceed 72 months.
(3) If no corrosion, marking, binding, or peening is found on
any disassembled part removed from the stacking, other than the
plungers, repeat the inspection thereafter at intervals not to
exceed 72 months.
(4) If any corrosion, marking, binding or peening is found on
any disassembled parts removed from the stacking, other than the
plungers, prior to further flight, replace the part with a new part,
in accordance with the Technical Instruction. Repeat the inspection
thereafter at intervals not to exceed 72 months.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
Alternative Methods of Compliance
(b) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(c) 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 4: The subject of this AD is addressed in French
airworthiness directive 98-179-021(B), dated May 6, 1998.
Issued in Renton, Washington, on September 3, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23621 Filed 9-9-99; 8:45 am]
BILLING CODE 4910-13-P
