[Federal Register Volume 61, Number 61 (Thursday, March 28, 1996)]
[Rules and Regulations]
[Pages 13655-13659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7494]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-SW-04-AD; Amendment 39-9552; AD 96-07-03]


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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
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, that requires a visual inspection to determine whether the 
cyclic pitch change control rod (rod) end fittings were safetied, and 
removal

[[Page 13656]]

and replacement of the rod if the rod end fittings were not safetied. 
This amendment 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 this 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.

EFFECTIVE DATE: Effective May 2, 1996.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to Eurocopter France Model AS 350B, 
BA, B1, B2, and D, and Model AS 355E, F, F1, F2, and N helicopters, 
without an autopilot installed, was published in the Federal Register 
on November 1, 1995 (60 FR 55491). That action proposed to require a 
visual inspection to confirm that the rod end fittings are safetied, 
and removal and replacement of the rod, if necessary.
    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 Direction Generale De 
L'Aviation Civile, which is the airworthiness authority for France, 
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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. However, 
a note has been inserted at the end of paragraph (c) to alert the 
reader that a Eurocopter Service Bulletin has been issued that pertains 
to the requirements of this AD. The FAA has determined that air safety 
and the public interest require the adoption of the rule with the noted 
change.
    The FAA estimates that 498 helicopters of U.S. registry will be 
affected by this AD, that it will 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 will be 
provided by the manufacturer. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $37,350.
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from 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.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

    AD 96-07-03 Societe Nationale Industrielle Aerospatiale and 
Eurocopter France: Amendment 39-9552. 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.
    (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.
    
[[Page 13657]]

    (4) Verify proper operation of the cyclic control.

    Note 2: 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, pertain to this subject.

    (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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

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    (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.
    (f) This amendment becomes effective on May 2, 1996.

    Issued in Fort Worth, Texas, on March 20, 1996.
Daniel P. Salvano,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-7494 Filed 3-27-96; 8:45 am]
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