[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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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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