[Federal Register Volume 67, Number 157 (Wednesday, August 14, 2002)]
[Proposed Rules]
[Pages 52896-52898]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20518]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-34-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA-365N, SA-
365N1, AS-365N2, and AS 365 N3 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Eurocopter France (ECF) Model SA-365N, SA-365N1, AS-365N2, and 
AS 365 N3 helicopters. This proposal would require inspecting the 9-
degree frame (frame) for the correct edge distance of the two 
attachment holes for the reinforced latch support and for a crack and 
repairing the frame if necessary. This proposal is prompted by the 
detection of a fatigue crack on the left-hand (LH) side of the frame 
during maintenance. The actions specified by this proposed AD are 
intended to prevent failure of the frame due to a crack at the latch 
support, loss of a passenger door, damage to the rotor system, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-34-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

[[Page 52897]]


FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, 
Texas 76193-0110, telephone (817) 222-5490, 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 document 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 mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-34-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. 2001-SW-34-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on ECF Model SA-365N, SA-365N1, AS-365N2, and AS 
365 N3 helicopters incorporating MOD 0753B31. The DGAC advises of the 
discovery of a crack on the left-hand side of the frame.
    ECF has issued AS 365 Alert Service Bulletin No. 53.00.42, dated 
January 31, 2001, which specifies measuring the edge distance of the 
attachment holes for the reinforced latch support of the frame, 
inspecting for a crack, and installing a repair on the frame or stop-
drilling the crack, and monitoring the crack for continued growth. The 
DGAC classified this service bulletin as mandatory and issued AD No. 
2001-060-052(A), dated February 21, 2001, to ensure the continued 
airworthiness of these helicopters in France.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral 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.
    This unsafe condition is likely to exist or develop on other ECF 
model helicopters of the same type design registered in the United 
States. Therefore, the proposed AD would require, within 50 hours time-
in-service, inspecting the frame at the two attachment holes for the 
latch support for the correct edge distance and for a crack and 
repairing the frame if necessary. The actions would be required to be 
accomplished in accordance with the service bulletin described 
previously.
    The FAA estimates that 45 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 3 work 
hours to visually inspect all helicopters and 8 work hours to repair an 
estimated 10 helicopters to correct edge distance only and 12 work 
hours to repair edge distance and cracks for an estimated 5 
helicopters, and that the average labor rate is $60 per work hour. 
Required parts would cost approximately $200 assuming a repair is 
necessary for 15 helicopters. Based on these figures, the total cost 
impact of the proposed AD on U.S. operators is estimated to be $19,500.
    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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. 2001-SW-34-AD.

    Applicability: Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 
helicopters, with MOD 0753B31 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 
otherwise 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 request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the frame due to a crack at the latch 
support, loss of a passenger door, damage to the rotor system, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 50 hours time-in-service, inspect each 9-degree frame 
(frame) by measuring the edge distance at the two 5.2 mm (0.205 
inch)

[[Page 52898]]

diameter attachment holes for the latch support for the passenger 
door in accordance with the Accomplishment Instructions, paragraph 
2.B.1., of Eurocopter France AS 365 Alert Service Bulletin 53.00.42, 
dated January 31, 2001 (ASB). Inspect the area around the attachment 
holes for a crack.
    (1) If the edge distance of both attachment holes is equal to or 
more than 8 mm (0.315 inch) and no crack is present, no action is 
required by this AD.
    (2) If the edge distance is less than 8 mm and no crack is 
present, before further flight, install a reinforcing plate in 
accordance with the Accomplishment Instructions paragraph 2.B.2. of 
the ASB. Accomplishing the requirements of paragraph 2.B.2. of the 
ASB constitutes terminating action for the requirements of this AD.
    (3) If there is a crack, before further flight, stop-drill the 
crack with a 3-millimeter diameter hole and repair the frame in 
accordance with the Accomplishment Instructions, paragraph 2.B.3 of 
the ASB. Accomplishing the requirements of paragraph 2.B.3. of the 
ASB constitutes terminating action for the requirements of this AD.
    (b) 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, Regulations Group, 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, Regulations Group.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Regulations Group.

    (c) Special flight permits may be issued in accordance with 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 No. 2001-060-052(A), dated 
February 21, 2001.


    Issued in Fort Worth, Texas, on August 5, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-20518 Filed 8-13-02; 8:45 am]
BILLING CODE 4910-13-P