[Federal Register Volume 60, Number 211 (Wednesday, November 1, 1995)]
[Proposed Rules]
[Pages 55491-55495]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-26999]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-SW-04-AD]
Airworthiness Directives; Societe Nationale Industrielle
Aerospatiale and Eurocopter France Model AS 350B, BA, B1, B2, and D,
and Model AS 355E, F, F1, F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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[[Page 55492]]
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Societe Nationale Industrielle
Aerospatiale and Eurocopter France (Eurocopter France) Model AS 350B,
BA, B1, B2, and D and Model AS 355E, F, F1, F2, and N helicopters,
without an autopilot installed. This proposal would require a visual
inspection to determine whether the cyclic pitch change control rod
(rod) end fittings were safetied, and removal and replacement of the
rod if the rod end fittings were not safetied. This proposal is
prompted by a manufacturer's report that some of the rod end fittings
had not been safetied at the factory. The actions specified by the
proposed AD are intended to prevent loss of tightening torque on the
adjustment nuts of the rod, shifting of the neutral point of the cyclic
stick, reduction in the amount of available movement of the cyclic
stick in the roll axis, and subsequent reduction in the controllability
of the helicopter.
DATES: Comments must be received by January 2, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 95-SW-04-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.
FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, 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. 95-SW-04-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 Assistant Chief Counsel, Attention: Rules
Docket No. 95-SW-04-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, has notified the FAA that an unsafe
condition may exist on Eurocopter France Model AS 350B, BA, B1, B2, and
D and Model AS 355E, F, F1, F2, and N helicopters, without an autopilot
installed. The DGAC advises that the manufacturer discovered that some
rod end fittings have not been safetied at the factory.
Eurocopter France has issued Eurocopter Service Bulletin No. 01.38,
dated June 26, 1994, for the Model AS 355 series helicopters, and
Eurocopter Service Bulletin No. 01.42, dated June 28, 1994, for the
Model AS 350 series helicopters, which specifies a visual inspection to
determine whether the rod end fittings have been safetied;
reinstallation of the forward lower fairing if the rod end fittings
have been safetied, and removal and replacement of the rod with an
airworthy rod and reinstallation of the forward lower fairing if the
rod end fittings have not been safetied. The DGAC classified this
service bulletin as mandatory and issued AD 94-179-051(B) and AD 94-
180-069(B), both dated August 3, 1994, 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 350B, BA, B1, B2,
and D and Model AS 355E, F, F1, F2, and N helicopters without an
autopilot installed, of the same type design registered in the United
States, the proposed AD would require a visual inspection to confirm
that the rod end fittings are safetied in accordance with the
manufacturer's service information, and removal and replacement of the
rod, if necessary.
The FAA estimates that 498 helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately one-
fourth of a work hour per helicopter to inspect the rod end fittings,
and 1 work hour to remove and reinstall the rod, if necessary, and that
the average labor rate is $60 per work hour. Required parts would be
provided by the manufacturer. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be $37,350.
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.
[[Page 55493]]
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), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
Societe Nationale Industrielle Aerospatiale and Eurocopter France:
Docket No. 95-SW-04-AD.
Applicability: Model AS 350B, BA, B1, B2, and D, and Model AS
355E, F, F1, F2, and N helicopters, with cyclic pitch change control
rod, part number (P/N) 704A34-113-279, installed, and without an
autopilot installed, 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 tightening torque on the adjustment nuts of
the cyclic pitch change control rod, shifting of the neutral
position of the cyclic stick, reduction in the amount of available
movement of the cyclic stick in the roll axis, and subsequent
reduction in the controllability of the helicopter, accomplish the
following:
(a) Within 100 hours time-in-service (TIS) after the effective
date of this AD, remove the forward lower fairing and visually
inspect the cyclic pitch change control rod (rod), P/N 704A34-113-
279, to determine whether the end fittings have been safetied (see
Figure 1, Detail 1, tabs bent around the adjustment nut).
(b) If the visual inspection indicates that the rod end fittings
have been safetied, reinstall the forward lower fairing.
(c) If the visual inspection indicates that the rod end fittings
have not been safetied (see Figure 1, Detail 2, tabs not bent around
the adjustment nut), accomplish the following in accordance with the
applicable maintenance manual:
(1) Immobilize the cyclic control.
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(2) Remove the rod and replace it with an airworthy rod on which
the rod end fittings have been safetied.
(3) Reinstall the forward lower fairing.
(4) Verify proper operation of the cyclic control.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Rotorcraft Standards Staff, FAA,
Rotorcraft Directorate. 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.
Issued in Fort Worth, Texas, on October 23, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-26999 Filed 10-31-95; 8:45 am]
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