[Federal Register: March 24, 2008 (Volume 73, Number 57)]
[Rules and Regulations]
[Page 15395-15397]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24mr08-3]
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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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