[Federal Register Volume 63, Number 14 (Thursday, January 22, 1998)]
[Proposed Rules]
[Pages 3273-3275]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-1428]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-07-AD]
Airworthiness Directives; Eurocopter France Model SA 330F, G, and
J 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 SA 330F,
G, and J helicopters. This proposal would require visually inspecting
the intermediate gearbox (IGB) fairing safety stop (safety stop) for
cracks, crazing, or edge wear, and if cracks, crazing, or edge wear
exceeds the established limits, replacing the safety stop; and,
inspecting to ensure that the inclined drive shaft fairing hinge pin is
properly locked. A terminating action is provided in the AD by
installing an additional safety stop on the IGB fairing. This proposal
is prompted by one report of an accident involving the loss of the
inclined drive shaft fairing. The actions specified by the proposed AD
are intended to prevent loss of the inclined drive shaft fairing and
impact with the tail rotor, and subsequent loss of control of the
helicopter.
DATES: Comments must be received by March 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 97-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. 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. Mike Mathias, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, 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
[[Page 3274]]
must submit a self-addressed, stamped postcard on which the following
statement is made: ``Comments to Docket No. 97-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. 97-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 SA 330F, G, and J
helicopters. The DGAC advises that there was one reported accident that
was caused by the loss of the inclined drive shaft fairing.
Eurocopter France has issued Eurocopter France SA 330 Service
Bulletin No. 54.20, Revision 1, dated February 27, 1996, which
specifies visually inspecting the safety stop for wear, cracks or
crazing, and determining if the edge has ruptured locally, and
replacing the safety stop. The DGAC classified this service bulletin as
mandatory and issued DGAC AD 96-095-076(B), dated April 24, 1996, 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 SA 330F, G, and J
helicopters of the same type design registered in the United States,
the proposed AD would require visually inspecting the safety stop for
cracks, crazing, or edge wear that exceeds the limits stated in Note II
of the Accomplishment Instructions of Eurocopter France SA 330 Service
Bulletin No. 54.20, Revision 1, dated February 27, 1996, and if cracks,
crazing, or edge wear exceeds the established limits, replacing the
safety stop; and, inspecting to ensure that the inclined drive shaft
fairing hinge pin is properly locked. Both inspections are required
within 7 calendar days after the effective date of the AD, and upon
completion of the last flight of each day. Installing an additional
safety stop (right-angle clip) on the IGB fairing within 60 calendar
days after the effective date of the AD is terminating action for the
requirements of this AD. The actions would be required to be
accomplished in accordance with the service bulletin described
previously.
The FAA estimates that 1 helicopter of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour to perform the inspection, and two work hours to install the
safety stop, and that the average labor rate is $60 per work hour.
Required parts would cost approximately $50 per helicopter. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $230.
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. 97-SW-07-AD.
Applicability: Model SA 330 F, G, and J helicopters,
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 (d) 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 loss of the inclined drive shaft fairing hinge pin
(hinge pin), that could result in loss of the inclined drive shaft
fairing, impact with the tail rotor, and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 7 calendar days after the effective date of this AD,
and thereafter, upon the completion of the last flight of each day,
visually inspect the intermediate gearbox (IGB) fairing safety stop
(safety stop) and the hinge pin in accordance with the
Accomplishment Instructions of Eurocopter France SA 330 Service
Bulletin No. 54.20, Revision 1, dated February 27, 1996.
(1) Inspect the IGB fairing safety stop, part number (P/N)
330A24-2086-20, for cracks or crazing, and edge wear that exceeds
the limits stated in Note II of the Accomplishment Instructions of
Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1,
dated February 27, 1996, and if cracks, crazing, or edge wear that
exceeds the established limits is detected, remove the safety stop
and replace it with an airworthy safety stop; and,
(2) Inspect the hinge pin to ensure it is properly locked.
(b) Within 60 calendar days after the effective date of this AD,
install an additional safety stop, P/N 330A24-2119-21, to prevent
the hinge pin from backing out of its hole in
[[Page 3275]]
case of a locking arm failure, in accordance with Accomplishment
Instructions of Eurocopter France SA 330 Service Bulletin No. 54.20,
Revision 1, dated February 27, 1996.
(c) Installation of an airworthy additional safety stop, P/N
330A24-2119-21, constitutes terminating action for the requirements
of this AD.
(d) 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, Rotorcraft Standards Staff,
Rotorcraft Directorate, FAA. 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.
(e) 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 (France) AD 96-095-076(B), dated April
24, 1996.
Issued in Fort Worth, Texas, on January 14, 1998.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-1428 Filed 1-21-98; 8:45 am]
BILLING CODE 4910-13-U
