[Federal Register: November 4, 2005 (Volume 70, Number 213)]
[Proposed Rules]
[Page 67099-67101]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04no05-11]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22364; Directorate Identifier 2005-NE-26-AD]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 1B, 1D and 1D1
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for Turbomeca Arriel 1B, 1D and 1D1 turboshaft engines. This proposed
AD would require inspecting the 2nd stage nozzle guide vanes (NGV2) for
wall thickness. This proposed AD results from one instance of a
fractured 2nd stage turbine blade followed by an uncommanded engine
shutdown. We are proposing this AD to detect and prevent perforation of
the NGV2 that could cause fracture of a turbine blade that could result
in an uncommanded engine in-flight shutdown.
DATES: We must receive any comments on this proposed AD by January 3,
2006.
[[Page 67100]]
ADDRESSES: Use one of the following addresses to comment 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 20590-0001.
Fax: (202) 493-2251.
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.
Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74
40 00, fax 33 05 59 74 45 15, for the service information identified in
this proposed AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22364;
Directorate Identifier 2005-NE-26-AD'' in the subject line 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 AD. Using the search function of the
DMS web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). 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 AD Docket
You may examine the docket that contains the proposal, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Offices between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is on the plaza level of the Department of Transportation
Nassif Building at the street address stated in ADDRESSES. Comments
will be available in the AD docket shortly after the docket office
receives them.
Discussion
The Direction Generale de L'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified us that an unsafe
condition might exist on certain Turbomeca S.A. Arriel 1B, 1D and 1D1
turboshaft engines. The affected engines are those modified to TU 202,
except those having NGV2 vanes with serial numbers or specific marks
identified in Turbomeca Mandatory Service Bulletin (MSB) No. 292 72
0231, Update No. 5, dated July 22, 2004. The DGAC advises that in order
to detect and prevent a possible perforation of the NGV2, they are
requiring inspection of the NGV2 for wall thickness. Perforation of the
NGV2 could cause an aerodynamic wake upstream of the 2nd stage turbine.
Such a wake could lead to the fracture of a 2nd stage turbine blade
followed by an uncommanded engine in-flight shutdown. On a single-
engine helicopter, this in-flight shutdown could lead to an emergency
landing by autorotation or an accident.
Relevant Service Information
We have reviewed and approved the technical contents of Turbomeca
MSB No. 292 72 0231, Update No. 5, dated July 22, 2004, that describes
procedures for removing each vane of the NGV2, checking the vane
thickness, and replacing the NGV2 if the vane thickness is below the
defined criteria. The DGAC classified this MSB as mandatory and issued
airworthiness directive No. F-2004-088 R1, dated August 4, 2004, in
order to ensure the airworthiness of these NGV2 vanes in France.
FAA's Determination and Requirements of the Proposed AD
These engines, manufactured in France, are type-certificated for
operation in the United States under the provisions of section 21.29 of
the Federal Aviation Regulations (14 CFR 21.29) and the applicable
bilateral airworthiness agreement. In keeping with this bilateral
airworthiness agreement, the DGAC kept us informed of the situation
described above. We have examined the DGAC's findings, 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. For this reason, we are proposing this AD, which would
require inspection of the NGV2 wall thickness. The proposed AD would
require you to use the service information described previously to
perform these actions.
Costs of Compliance
There are about 2,000 Turbomeca Arriel 1B, 1D and 1D1 turboshaft
engines of the affected design in the worldwide fleet. We estimate that
this proposed AD would affect 571 engines installed on helicopters of
U.S. registry. We also estimate that it would take about 0.5 work hours
per engine to perform the proposed actions, and that the average labor
rate is $65 per work hour. No parts are required. Based on these
figures, we estimate the total cost of the proposed AD to U.S.
operators to be $18,558.
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.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. 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
[[Page 67101]]
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. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Turbomeca: Docket No. FAA-2005-22364; Directorate Identifier 2005-
NE-26-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 3,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca Arriel 1B, 1D and 1D1 certain
turboshaft engines, modified to TU 202. These engines are installed
on, but not limited to, Eurocopter France AS350A, AS350B, AS350B1,
and AS350B2 helicopters.
Unsafe Condition
(d) This AD results from one instance of a fractured 2nd stage
turbine blade followed by an uncommanded engine shutdown. We are
issuing this AD to detect and prevent perforation of the NGV2 that
could cause fracture of a turbine blade that could result in an
uncommanded engine in-flight shutdown.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Inspect 2nd Stage Nozzle Guide Vanes (NGV2)
(f) At the next shop visit or the next accessibility of the NGV2
after the effective date of this AD, whichever occurs first, check
the thickness of the material on each NGV2 using the Instructions to
be Incorporated of Turbomeca Mandatory Service Bulletin (MSB) No.
292 72 0231, Update No. 5, dated July 22, 2004. Replace the NGV2 if
the vane thickness is below the defined criteria.
(g) Inspections carried out before the effective date of this
AD, using an earlier update of MSB No. 292 72 0231, are acceptable
alternatives to the requirements of this AD.
(h) Information regarding NGV2's that have already had the
actions required by this AD done and are exempt from the inspections
using paragraph (e) of this AD can be found in MSB No. 292 72 0231,
Update No. 5, dated July 22, 2004.
Definitions
(i) For the purposes of this AD the following definitions apply:
(1) A shop visit is defined as introduction of the engine into a
shop for the purposes of deep maintenance and the separation of a
major mating flange.
(2) Accessibility of the NGV2 is defined as removal of the NGV2
from the engine regardless of the location or reason for removal.
Alternative Methods of Compliance (AMOCs)
(j) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(k) DGAC airworthiness directive No. F-20040-088 R1 also
addresses the subject of this AD.
Issued in Burlington, Massachusetts, on October 31, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-22007 Filed 11-3-05; 8:45 am]
BILLING CODE 4910-13-P