[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73581-73583]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23827]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23004; Directorate Identifier 2005-NE-42-AD;
Amendment 39-14405; AD 2005-25-12]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Astazou XIV B and XIV H
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Turbomeca Astazou XIV B and XIV H turboshaft engines that have operated
with air intake noise suppressors. This AD requires ensuring proper
installation of air intake noise suppressors, and ultrasonically
inspecting 2nd stage axial compressor wheel blades operated in engines
with improperly installed intake noise suppressors. This AD results
from several reports of failure of 2nd stage axial compressor wheel
blades. We are issuing this AD to prevent failure of 2nd stage axial
compressor wheel blades, leading to in-flight engine shutdown and
autorotation landing.
DATES: Effective December 28, 2005. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of December 28, 2005.
We must receive any comments on this AD by February 13, 2006.
ADDRESSES: Use one of the following addresses to comment on this 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.
[[Page 73582]]
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, 40220 Tarnos, France; telephone 33 05 59 74 40
00, fax 33 05 59 74 45 15, for the service information identified in
this 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: The Direction Generale de L'Aviation Civile
(DGAC), which is the airworthiness authority for France, notified us
that an unsafe condition might exist on Turbomeca Astazou XIV B and XIV
H turboshaft engines that have operated with an air intake noise
suppressor. The DGAC advises that several cases of failure of 2nd stage
axial compressor wheel blades have occurred in service. An
investigation revealed that these failures result from aerodynamic-
induced stresses caused by improperly installed air intake noise
suppressors. An improperly installed air intake noise suppressor has
too great an angular position on the air intake casing. This in turn
results in downstream airflow turbulence causing high stresses in the
2nd stage axial compressor wheel blades.
Relevant Service Information
We have reviewed and approved the technical contents of Turbomeca
Alert Service Bulletin (ASB) No. A283 72 0800, dated February 5, 2004,
that describes instructions for ultrasonic inspection of 2nd stage
axial compressor wheel blades. The DGAC classified this alert service
bulletin as mandatory and issued AD F-2004-029, dated February 18,
2004, in order to ensure the airworthiness of these Astazou XIV B and
XIV H turboshaft engines in France.
Bilateral Airworthiness Agreement
These Astazou XIV B and XIV H turboshaft engines are manufactured
in France and 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. Under this bilateral airworthiness agreement, the DGAC kept
the FAA informed of the situation described above. We have examined the
findings of the DGAC, 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.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other Turbomeca Astazou XIV B and XIV H turboshaft engines
of the same type design. We are issuing this AD to prevent failure of
2nd stage axial compressor wheel blades, leading to in-flight engine
shutdown and autorotation landing. This AD requires:
Before further flight, ensuring proper installation of air
intake noise suppressors; and
For engines operated with improperly installed air intake
noise suppressors, removing the engine and performing an ultrasonic
inspection of 2nd stage axial compressor wheel blades, within 50 flight
hours or 6 months after the effective date of this AD, whichever occurs
first, and replacing blades that fail inspection.
You must use the service information described previously to perform
the removals, blade inspections, replacements, and installations
required by this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-23004;
Directorate Identifier 2005-NE-42-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
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 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 AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located 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 DMS receives them.
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 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.
[[Page 73583]]
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 a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Under 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
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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2005-25-12 Turbomeca: Amendment 39-14405. Docket No. FAA-2005-23004;
Directorate Identifier 2005-NE-42-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca Astazou XIV B and XIV H
turboshaft engines that have operated with air intake noise
suppressors. These engines are installed on, but not limited to,
single-engine Aerospatiale AS319B ``Alouette III'' and AS342J
``Gazelle'' helicopters.
Unsafe Condition
(d) This AD results from several reports of failure of 2nd stage
axial compressor wheel blades. We are issuing this AD to prevent
failure of 2nd stage axial compressor wheel blades, leading to in-
flight engine shutdown and autorotation landing.
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.
Ensure Proper Installation of Air Intake Noise Suppressors
(f) Before further flight, ensure proper installation of air
intake noise suppressors.
(g) You can find information on doing this in aircraft
maintenance manual (AMM) section 71-30-41 for Aerospatiale AS319B
helicopters, and in AMM section 71-61-401 for Aerospatiale AS342J
helicopters.
Engines That Operated With Improperly Installed Air Intake Noise
Suppressors
(h) For engines that operated with improperly installed air
intake noise suppressors:
(1) Perform an ultrasonic inspection of 2nd stage axial
compressor wheel blades, within 50 flight hours or 6 months after
the effective date of this AD, whichever occurs first, and replace
blades that fail inspection.
(2) Use 2.B.(1) through 2.B.(2)(b) of Turbomeca Alert Service
Bulletin No. A283 72 0800, dated February 5, 2004, to do the
inspection.
Alternative Methods of Compliance
(i) 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
(j) Direction Generale de L'Aviation Civile airworthiness
directive F-2004-029, dated February 18, 2004, also addresses the
subject of this AD.
Material Incorporated by Reference
(k) You must use Turbomeca Alert Service Bulletin No. A283 72
0800, dated February 5, 2004, to perform the removals, blade
inspections, replacements, and installations required by this AD.
The Director of the Federal Register approved the incorporation by
reference of this service bulletin in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Turbomeca, 40220 Tarnos, France;
telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of
this service information. You may review copies at the Docket
Management Facility; U.S. Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-
0001, on the internet at http://dms.dot.gov; 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/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-23827 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P