[Federal Register Volume 73, Number 57 (Monday, March 24, 2008)]
[Rules and Regulations]
[Pages 15395-15397]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-5494]


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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; 
Amendment 39-15434; AD 2008-06-22]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC130 B4 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Eurocopter France (Eurocopter) Model EC 130 B4 
helicopters, with certain twist grip assemblies installed, that 
requires 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 amendment 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 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: Effective April 28, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 28, 2008.

ADDRESSES: You may get the service information identified in this AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://www.regulations.gov or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on May 21, 2007 (72 FR 28456). That action proposed to 
require, within 110 hours time-in-service (TIS) or 4 months, whichever 
occurs first, or before installing a collective lever with an affected 
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 lever. If debonding is present, replacing the collective 
lever before further flight was proposed.
    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 
speed although the twist grip had been turned back to the flight 
position. The autorotation procedure continued to the ground without 
damage to the helicopter. 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 lever. EASA classified this service bulletin as mandatory 
and issued AD No. 2006-0079, dated April

[[Page 15396]]

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 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, France, through the EASA, has kept the 
FAA informed of the situation described above. The FAA has examined the 
findings of the EASA, 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.
    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. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that this AD will affect 73 helicopters of U.S. 
registry. The debonding inspection will take approximately 0.25 work 
hours per helicopter and replacing a collective lever will take 
approximately 2 work hours at an average labor rate of $80 per work 
hour. If replacement is necessary, required parts will cost 
approximately:
     $8,651 for a co-pilot twist grip assembly, part number (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 this 
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, and 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 indicated 
that labor is not covered by a warranty.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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 an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

    2008-06-22 Eurocopter France: Amendment 39-15434. 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 on a 
helicopter, 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, ATTN: Ed Cuevas, 
Aviation Safety Engineer, Rotorcraft Directorate, FAA, Fort Worth, 
Texas 76193-0111, telephone (817) 222-5355, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (d) The inspection and replacement, if necessary, shall be done 
in accordance with the specified portions of Eurocopter, an EADS 
Company, Alert Service Bulletin EC130 No. 76A001, dated February 10, 
2006. The Director of the Federal Register approved this 
incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Copies may be obtained from American Eurocopter 
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, 
telephone (972) 641-3460, fax (972) 641-3527. Copies may be 
inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

[[Page 15397]]

    (e) This amendment becomes effective on April 28, 2008.

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


    Issued in Fort Worth, Texas, on March 10, 2008.
Mark R. Schilling,
Acting Manager, Rotocraft Directorate, Aircraft Certification Service.
[FR Doc. E8-5494 Filed 3-21-08; 8:45 am]
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