[Federal Register: May 21, 2007 (Volume 72, Number 97)]
[Proposed Rules]
[Page 28456-28458]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21my07-4]
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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