[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Proposed Rules]
[Pages 6883-6885]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3580]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-52-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC120B 
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 EC120B helicopters. This 
proposal would require inspecting the attachment of the bolted 
assemblies of the cyclic pitch flight control torque tube (torque tube) 
for an appropriate locking device. If a bolted assembly is single-
locked, the proposed AD would require, if necessary, tightening the 
self-locking nuts at certain intervals and modifying the torque tube 
after a certain time. This proposal is prompted by the discovery that 
some of the attachments of the torque tube were fastened with a single-
locking device instead of the intended double-locking device. The 
actions specified by this proposed AD are intended to prevent 
separation of the cyclic pitch stick yokes from the torque tube, loss 
of cyclic control, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before April 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-52-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.

FOR FURTHER INFORMATION CONTACT: Richard Monschke, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort 
Worth, Texas 76193-0110, 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 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,

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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-52-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-52-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 EC120B helicopters. The DGAC advises 
that the design fails to provide double-locking of the attachment pins 
of the cyclic pitch stick yokes to the torque tube.
    ECF has issued Alert Service Bulletin No. 67A003, dated August 2, 
2001 (ASB), which specifies inspecting single-locking devices within 50 
hours time-in-service (TIS) and modifying single-locking devices to 
make them double locking within 500 hours TIS or 24 months, whichever 
occurs first. The DGAC classified this ASB as mandatory and issued AD 
2001-373-008(A), dated August 22, 2001, to ensure 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 
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 
helicopter models of the same type design registered in the United 
States. Therefore, the proposed AD would require determining whether 
the attachment of the bolted assembly of the torque tube is a single or 
double-locking device. If the bolted assembly is single-locked, the 
proposed AD would require repetitively inspecting and, if necessary, 
tightening the self-locking nuts to a specified torque. The proposed AD 
would also require modifying the torque tube to provide double locking 
for the attachment pins of the cyclic pitch stick yokes to the torque 
tube after a specified time interval. The actions would be required to 
be accomplished in accordance with the ASB described previously except 
for the compliance time allowed before the torque tube modification is 
required. The DGAC and the manufacturer specify modifying the torque 
tube within 500 hours time-in-service (TIS) or 24 months, whichever 
occurs first. However, the FAA has determined that, due to the 
seriousness of this unsafe condition, the torque tube must be modified 
within the next 250 hours TIS or 12 months, whichever occurs first.
    The FAA estimates that 44 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately 5 work 
hours per helicopter to accomplish the proposed actions, and that the 
average labor rate is $60 per work hour. Required parts would cost 
approximately $195. Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $21,780.
    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-52-AD.

    Applicability: Model EC120B helicopters, serial numbers 1001 
through 1029 inclusive, 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 (e) 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 separation of the cyclic pitch stick yokes from the 
cyclic pitch flight control torque tube (torque tube), loss of 
cyclic control, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Within 50 hours time-in-service (TIS), determine whether 
each attachment of the bolted assembly of the torque tube 
(attachment) has a single or double-locking device in accordance 
with the Accomplishment Instructions, paragraph 2.B.1., of 
Eurocopter France Alert Service Bulletin No. 67A003, dated August 2, 
2001 (ASB).
    (1) If the attachment has a double-locking device (a castellated 
self-locking nut with a cotter pin), no further action is required 
by this AD.
    (2) If the attachment has a single-locking device (castellated 
nut without a cotter pin or a self-locking nut only), in accordance 
with the Accomplishment Instructions, paragraph 2.B.1., of the ASB, 
before further flight:

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    (i) Torque each nut to 0.4 to 0.5 mdaN (36 to 44 inch-lbs), and
    (ii) Apply a slippage mark on the nut and torque tube.
    (b) At intervals not to exceed 50 hours TIS, inspect the 
attachment for movement of the locking device indicated by a 
misalignment of the slippage mark.
    (1) If no movement has occurred, record the inspection.
    (2) If movement has occurred, replace, retorque, and reapply the 
slippage mark to the nut in accordance with the Accomplishment 
Instructions, paragraph 2.B.2., of the ASB.
    (c) Within 250 hours TIS or 12 months, whichever occurs first, 
modify the torque tube in accordance with the Accomplishment 
Instructions, paragraph 2.B.3., of the ASB.
    (d) Modifying the torque tube in accordance with paragraph (c) 
of this AD is terminating action for the requirements of this AD.
    (e) 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.

    (f) 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 2001-373-008(A), dated 
August 22, 2001.


    Issued in Fort Worth, Texas, on January 29, 2002.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-3580 Filed 2-13-02; 8:45 am]
BILLING CODE 4910-13-U