[Federal Register Volume 72, Number 97 (Monday, May 21, 2007)]
[Proposed Rules]
[Pages 28456-28458]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-9708]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28229; Directorate Identifier 2006-SW-23-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC130 B4 
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 (Eurocopter) Model EC 130 B4 helicopters, 
with certain twist grip assemblies installed. This proposal would 
require inspecting the pilot and co-pilot collective levers for proper 
bonding between the twist grip drive tubes and the control pinions and 
if debonding is present, replacing the collective levers before further 
flight. This proposal is prompted by one incident in which the engine 
remained at idle speed although the twist grip had been turned to the 
flight position. The actions specified by this proposed AD are intended 
to detect debonding between the twist grip drive tubes and the control 
pinions on the pilot and co-pilot collective levers to prevent loss of 
cockpit throttle control of the engine, and subsequent loss of control 
of the helicopter.

DATES: Comments must be received on or before July 20, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: 202-493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You may get the service information identified in this proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28229, Directorate Identifier 2006-SW-23-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed rulemaking. Using the search 
function of our docket Web site, you can find and read the comments to 
any of our dockets, including the name of the individual who sent or 
signed the comment. You may review the DOT's complete Privacy Act 
Statement in the Federal Register published on April 11, 2000 (65 FR 
19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of 
Transportation Nassif Building in Room PL-401 at 400 Seventh Street, 
SW., Washington, DC. Comments will be available in the AD docket 
shortly after the DMS receives them.

Discussion

    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on Eurocopter Model EC 130 B4 helicopters, 
with a twist grip assembly, part number (P/N) 350A27520900, 
350A27520901, 350A27520902, or 350A27520903, with a serial number below 
64, installed on the pilot's side, and a twist grip assembly, P/N 
350A27521201, with a serial number below 67, installed on the co-
pilot's side. EASA advises that analysis of an incident that occurred 
during autorotation training revealed a failure of the twist grip drive 
tube and control pinion bonded attachment. The engine remained at idle 
rating although the twist grip had been turned back to the flight 
position. The manufacturer states that the autorotation procedure 
continued without damage to the helicopter, which landed safely. The 
failure has been attributed to non-compliant surface preparation during 
manufacture.
    Eurocopter, an EADS Company, has issued Alert Service Bulletin 
EC130 No. 76A001, dated February 10, 2006, which specifies a check by 
use of a twist grip adjusting gauge of the bonding between the twist 
grip drive tube and the control pinion on both the pilot and co-pilot 
collective levers. If the twist grip twists under a load on the 
adjusting gauge of 35N, the collective lever must be replaced. EASA 
classified this service bulletin as mandatory and issued AD No. 2006-
0079, dated April 3, 2006, 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 
section 21.29 of the Federal Aviation

[[Page 28457]]

Regulations (14 CFR 21.29) and the applicable bilateral agreement. 
Under this agreement, EASA has kept the FAA informed of the situation 
described above. We have examined EASA's findings, evaluated all 
pertinent information, and determined that AD action is necessary for 
products of this type design that are certificated for operation in the 
United States.
    This 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 110 
hours time-in-service (TIS) or 4 months, whichever occurs first, or 
before the installation of a collective lever with an affected twist 
grip assembly on a helicopter, inspecting the bonding between the twist 
grip drive tube and the control pinion on both the pilot and co-pilot 
collective levers. If debonding is present, replacing the collective 
lever with an airworthy collective lever that has been inspected in 
accordance with paragraph (a) of this proposed AD, or a collective 
lever with a twist grip assembly that is not listed in the 
Applicability of this proposed AD is required before further flight. 
The actions would be required to be accomplished by following the 
specified portions of the alert service bulletin described previously.
    We estimate that this proposed AD would affect 73 helicopters of 
U.S. registry. The debonding inspection would take approximately 0.25 
work hour per helicopter and replacing a collective lever would take 
approximately 2 work hours, at an average labor rate of $80 per work 
hour. If replacement is necessary, required parts would cost 
approximately:
     $8,651 for a co-pilot twist grip assembly, P/N 
350A27521201;
     $12,542 for a pilot twist grip assembly, P/N 350A27520903;
     $5 for a clamp, P/N ASNA0021;
     $2 for a bolt, P/N 22125BC050014L; and
     $1 for a nut, P/N 22431BC050L.

    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $10,271, assuming one co-pilot 
twist grip assembly is replaced in one helicopter, that the twist grip 
adjusting gage (tool) and spring scale needed are on-site and 
available, that the co-pilot twist grip assembly is not covered by 
warranty, and no pilot twist grip assembly will need to be replaced. 
The manufacturer has indicated that parts are covered by warranty up to 
1,000 hours or 2 years after the purchase of a new helicopter, however 
it was indicated that labor is not covered by a warranty.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, this proposed 
AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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. FAA-2007-28229; Directorate Identifier 
2006-SW-23-AD.

    Applicability: Model EC130 B4 helicopters, with a twist grip 
assembly, part number (P/N) 350A27520900, 350A27520901, 
350A27520902, or 350A27520903, with a serial number below 64, 
installed on the pilot's side, and a twist grip assembly, P/N 
350A27521201, with a serial number below 67, installed on the co-
pilot's side, certificated in any category.
    Compliance: Required within 110 hours time-in-service (TIS) or 4 
months, whichever occurs first, and before installing a replacement 
collective lever with an affected twist grip assembly, unless 
accomplished previously.
    To detect a reduced bonding strength of the control pinion on 
the pilot and co-pilot collective lever drive tubes, which could 
lead to failure of a twist grip drive tube and control pinion bonded 
attachment, resulting in loss of engine throttle control and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Inspect the pilot and co-pilot collective levers for proper 
bonding between the twist grip drive tubes and the control pinions 
in accordance with paragraphs 2.B.1. and 2.B.2. of the 
Accomplishment Instructions, in Eurocopter, an EADS Company, Alert 
Service Bulletin EC130 No. 76A001, dated February 10, 2006, except 
you are neither required to contact the manufacturer nor return a 
non-compliant collective lever.
    (b) If a twist grip turns when applying the 35N load to the 
twist grip, before further flight, replace the collective lever with 
an airworthy collective lever that has been inspected in accordance 
with paragraph (a) of this AD, or a collective lever with a twist 
grip assembly that is not listed in the Applicability of this AD.
    (c) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, FAA, ATTN: Ed Cuevas, 
Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety 
Management Group, Fort Worth, Texas 76193-0111, telephone (817) 222-
5355, fax (817) 222-5961, for information about previously approved 
alternative methods of compliance.

    Note: The subject of this AD is addressed in EASA (France) AD 
2006-0079, dated April 3, 2006.



[[Page 28458]]


    Issued in Fort Worth, Texas, on May 7, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-9708 Filed 5-18-07; 8:45 am]
BILLING CODE 4910-13-P