[Federal Register Volume 68, Number 136 (Wednesday, July 16, 2003)]
[Proposed Rules]
[Pages 41967-41968]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-17955]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-07-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 the specified Eurocopter France (Eurocopter) model 
helicopters. This proposal would require operators to either 
temporarily or permanently secure the electrical bonding braid (bonding 
braid) that is installed on the left cyclic pitch control stick base 
within 10 hours time-in-service (TIS) and, if temporarily secured, 
installing a permanent attachment system for the bonding braid within 
500 hours TIS or 12 months, whichever occurs first. This proposal is 
prompted by a report of a bonding braid twisting around the attachment 
nut installed on the bolt that connects the roll channel torque link to 
the left-hand cyclic pitch control stick. The actions specified by this 
proposed AD are intended to prevent an unsecured bonding braid from 
restricting travel of the cyclic pitch control stick, and subsequent 
loss of control of the helicopter.

DATES: Comments must be received on or before September 15, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2003-SW-07-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, 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. 2003-SW-07-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    The Direction Generale De L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model EC 120 B helicopters. The DGAC 
advises that there was a report involving twisting of a bonding braid 
at the base of a cyclic stick that restricted movement of the cyclic 
pitch sticks.
    Eurocopter has issued Alert Telex No. 67A008, dated July 8, 2002, 
which specifies installing a clamp to position the bonding braid 
upwards and holding it against the cyclic pitch stick. DGAC classified 
this alert telex as mandatory and issued AD 2002-371-010(A), dated July 
24, 2002, 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, 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.
    The previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design registered in the 
United States. Therefore, the proposed AD would require, within 10 
hours TIS, temporarily or permanently securing the bonding braid using 
clamps, then, if not already accomplished, installing a permanent 
attachment system within 500 hours TIS or 12 months, whichever occurs 
first. Installing the permanent attachment system is a terminating 
action for the requirements of this AD. The actions would be required 
to be accomplished in accordance with the alert telex described 
previously.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. Because 
we have now included this

[[Page 41968]]

material in part 39, we no longer need to include it in each individual 
AD.
    The FAA estimates that this proposed AD would affect 80 helicopters 
of U.S. registry and the proposed actions would take approximately 0.5 
work hour per helicopter to accomplish the modification to temporarily 
secure the bonding braid, and 0.5 work hour to install a permanent 
attachment system. The average labor rate is $60 per work hour. 
Required parts would cost approximately $20 per helicopter. Based on 
these figures, we estimate the total cost impact of the proposed AD on 
U.S. operators to be $6,400 for the entire fleet, assuming that all 
operators install the temporary restraint, and subsequently, install 
the permanent restraint.
    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. 2003-SW-07-AD.

    Applicability: Model EC120B helicopters, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent an unsecured bonding braid from restricting travel of 
the cyclic pitch control stick, and subsequent loss of control of 
the helicopter, accomplish the following:
    (a) Within 10 hours time-in-service (TIS), temporarily secure 
the electrical bonding braid or install the permanent attachment 
system for the bonding braid in accordance with the Accomplishment 
Instructions, paragraph 2.B., of Eurocopter France Alert Telex No. 
67A008, dated July 8, 2002 (Alert Telex).
    (b) Within 500 hours TIS or 12 months, whichever occurs first, 
install the permanent attachment system for the bonding braid in 
accordance with the Accomplishment Instructions, paragraphs 2.B.2. 
and 2.B.3., of the Alert Telex.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Send the proposal to the Manager, Safety Management Group, FAA. 
Contact the Safety Management Group for information about previously 
approved alternative methods of compliance.

    Note: The subject of this AD is addressed in Direction Generale 
De L'Aviation (France) AD 2002-371-010(A), dated July 24, 2002.


    Issued in Fort Worth, Texas, on July 1, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-17955 Filed 7-15-03; 8:45 am]
BILLING CODE 4910-13-P