[Federal Register Volume 63, Number 66 (Tuesday, April 7, 1998)]
[Proposed Rules]
[Pages 16916-16918]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-8989]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-07-AD]
Airworthiness Directives; Eurocopter France Model AS 332C, L, L1,
and L2 Helicopters
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 Eurocopter France Model AS 332C,
L, L1, and L2 helicopters. This proposal would require visually
inspecting the intermediate gearbox-to-structure attachment stirrup
(stirrup) front tabs for cracks, and if a crack is discovered, removing
the intermediate gearbox and replacing it with an airworthy
intermediate gearbox; and inspecting for the conformity of the
attachment parts. This proposal is prompted by five reports of failure
of the two stirrup tabs. The actions specified by the proposed AD are
intended to prevent failure of the intermediate gearbox stirrup front
tabs, loss of anti-torque drive, and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before May 7, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-07-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand
Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-
3527. This information may be examined at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas.
FOR FURTHER INFORMATION CONTACT: Mr. Scott Horn, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5125, fax (817)
222-5961.
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 should 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 No. 98-SW-07-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, Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-07-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
Discussion
The Direction Generale De L'Aviation Civile (DGAC), which is the
airworthiness authority for France, recently notified the FAA that an
unsafe condition may exist on Eurocopter France Model AS 332C, L, L1,
and L2 helicopters with intermediate gearboxes, part number 332A35-0002
all dash numbers, 332A35-0010 all dash numbers, and 332A35-0011-01,
that have not been modified in accordance with MOD 0761049 or MOD
0761050. The DGAC advises that cracks have
[[Page 16917]]
been discovered on the stirrup, and mandates visually inspecting the
stirrup front tabs for cracks. If a crack is discovered, the DGAC
mandates removing the intermediate gearbox and replacing it with an
airworthy intermediate gearbox; and inspecting for the conformity of
the attachment parts.
Eurocopter France has issued Eurocopter France AS 332 Service
Bulletin No. 01.00.47 Revision No. 1, dated September 10, 1997. The
DGAC classified this service bulletin as mandatory and issued AD 96-
263-060(AB)R1 for Model AS 332C, L, and L1 helicopters, and AD 96-262-
004(AB)R1 for Model AS 332L2 helicopters, both dated November 5, 1997,
in order to assure the continued airworthiness of these helicopters in
France.
This helicopter 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other Eurocopter France Model AS 332C, L, L1, and
L2 helicopters of the same type design registered in the United States,
the proposed AD would require visually inspecting the stirrup front
tabs for cracks, and if a crack is discovered, removing the
intermediate gearbox and replacing it with an airworthy intermediate
gearbox; and inspecting for the conformity of the attachment parts. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
The FAA estimates that 4 helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately 0.25
work hours to inspect the tabs, and 3 work hours to inspect for
conformity, 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 $780.
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 a new airworthiness directive
to read as follows:
Eurocopter France: Docket No. 98-SW-07-AD.
Applicability: Model AS 332C, L, L1, and L2 helicopters, with
intermediate gearboxes (IGB), part numbers (P/N) 332A35-0002 all
dash numbers, 332A35-0010 all dash numbers, and 332A35-0011-01,
installed, except those IGBs modified in accordance with MOD 0761049
or MOD 0761050, certificated in any category.
Note 1: This AD applies to each helicopter 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 helicopters 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 helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the IGB-to-structure attachment stirrup
(stirrup) front tabs, loss of anti-torque drive, and subsequent loss
of control of the helicopter, accomplish the following:
(a) Before the first flight of each day, perform a visual
inspection of the stirrup front tabs for cracks in accordance with
paragraph 2.B1) of the Accomplishment Instructions in Eurocopter
France AS 332 Service Bulletin 01.00.47, Revision No. 1, dated
September 10, 1997 (SB). If a crack is found, remove the IGB and
replace it with an airworthy IGB before further flight. Completion
of the conformity procedure contained in paragraph 2.B.2.1.3) of the
SB is terminating action for the requirement of this AD to inspect
for cracks prior to the first flight of each day.
(b) Within 100 hours time-in-service (TIS), inspect the two
front attaching assemblies securing the stirrup of the IGB to the
angle bracket of the structure (attachment assembly) for thickness
of the stirrup front tabs in accordance with paragraph 2.B.2) of the
SB.
(1) If the attachment assembly meets the conformity requirements
of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB, reassemble
the attachment assembly in accordance with paragraph 2.B.2.1.3) of
the SB.
(2) If the attachment assembly does not meet the conformity
requirements of either paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB,
replace it with an attachment assembly which does meet the
conformity requirements of either of those paragraphs. Install the
attachment assembly hardware in accordance with 2.B.2.1.3) of the
SB.
(3) If a crack is discovered in the stirrup front tabs as a
result of the conformity inspection, remove the IGB and replace it
with an airworthy IGB before further flight.
(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, FAA, Rotorcraft Directorate,
Rotorcraft Standards Staff. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Rotorcraft Standards Staff.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(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 helicopter to a location where
the requirements of this AD can be accomplished.
Note 3: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile
[[Page 16918]]
(France) AD 96-263-060(AB)R1 for Eurocopter France (ECF) Model AS
332C, L, and L1 helicopters, and AD 96-262-004(AB)R1 for ECF Model
AS 332L2 helicopters, both dated November 5, 1997.
Issued in Fort Worth, Texas, on March 30, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-8989 Filed 4-6-98; 8:45 am]
BILLING CODE 4910-13-P
