Airworthiness Directives; Turbomeca Astazou XIV B and XIV H Turboshaft Engines, 73581-73583 [05-23827]
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Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
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.
Visual Checks
(f) Within 10 operating hours after the
effective date of this AD:
(1) Visually check the free turbine shield
for cracks using 2.A. through 2.D.(2) of
73581
Turbomeca Mandatory Service Bulletin
(MSB) A292 72 2821, dated June 27, 2005.
(2) Replace the free turbine shield or
establish a repetitive check interval using the
criteria in the following Table 1:
TABLE 1.—FREE TURBINE SHIELD CHECK, DISPOSITION CRITERIA
Number of cracks:
Crack locations using
appendix 1 from MSB
A292 72 2821:
(i) 0 ..............................
(ii) 1 .............................
Not Applicable ............
D–A ............................
(iii) 1 .............................
A–B .............................
(5:00 o’clock Area) .....
(iv) 1 ............................
C–D ............................
(8:00 o’clock Area) .....
(v) 2 .............................
One in A–B and one
in C–D.
(vi) 2 ............................
(vii) 2 ............................
(viii) 2 ...........................
(ix) 3 or more ...............
Either one or both in
D–A.
Both in A–B ................
Both in C–D ................
Any .............................
(3) You may treat multiple cracks adjacent
to each other as a single crack by using the
length measured between the two extremities
of the cracks.
(4) Single cracks that span two locations
must use the location that yields the most
conservative re-check interval or replacement
requirement.
Optional Terminating Action
(g) Incorporation of Turbomeca
modification TU22 terminates the repetitive
visual checks required by this AD.
Alternative Methods of Compliance
(h) 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
(i) Direction Generale de L’Aviation Civile
AD F–2005–162, dated September 28, 2005,
also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Turbomeca Mandatory
Service Bulletin A292 72 2821, dated June
27, 2005, to perform the actions 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,
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
Re-check using paragraphs (f)(1) and (f)(2) of
this AD, or replace:
Crack length:
Not Applicable .................................................
(A) Less than 170 mm ....................................
(B) Between 170 mm and 200 mm ................
(C) Greater than 200 mm ...............................
(A) Less than 201 mm ....................................
(B) Between 201 mm and 248 mm ................
(C) Greater than 248 mm ...............................
(A) Less than 297 mm ....................................
(B) Between 297 mm and 366 mm ................
(C) Greater than 366 mm ...............................
(A) Zone 1 using Appendix 3 of MSB A292
72 2821.
(B) Zone 2 using Appendix 3 of MSB A292
72 2821.
(C) Zone 3 using Appendix 3 of MSB A292
72 2821.
Any ..................................................................
Re-check shield within 500 N1 cycles.
Re-check shield within 100 N1 cycles.
Re-check shield daily.
Replace shield before further flight.
Re-check within 100 cycles.
Re-check daily.
Replace shield before further flight.
Re-check within 100 cycles.
Re-check daily.
Replace shield before further flight.
Re-check within 100 cycles.
Any ..................................................................
Any ..................................................................
Any ..................................................................
Replace shield before further flight.
Replace shield before further flight.
Replace shield before further flight.
on the Internet at https://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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
December 5, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–23831 Filed 12–12–05; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
Re-check daily.
Replace shield before further flight.
Replace shield before further flight.
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 inflight 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
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
E:\FR\FM\13DER1.SGM
13DER1
73582
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
• 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 aerodynamicinduced 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
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
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 inflight 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 https://
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
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
https://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.
E:\FR\FM\13DER1.SGM
13DER1
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
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
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
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
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
the compliance times specified unless the
actions have already been done.
DEPARTMENT OF TRANSPORTATION
Ensure Proper Installation of Air Intake
Noise Suppressors
Federal Aviation Administration
(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
Authority: 49 U.S.C. 106(g), 40113, 44701.
73583
(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 https://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: https://www.archives.gov/federalregister/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
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
14 CFR Part 39
[Docket No. FAA–2005–22290; Directorate
Identifier 2005–NM–129–AD; Amendment
39–14407; AD 2005–25–14]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
(Jetstream) Model 4101 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all BAE
Systems (Operations) Limited
(Jetstream) Model 4101 airplanes. This
AD requires modifying the wiring of the
starter-generator terminal block. This
AD results from a report of total
electrical failure just as the airplane
landed. We are issuing this AD to
prevent total electrical failure and
consequent reduced controllability of
the airplane.
DATES: This AD becomes effective
January 17, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of January 17, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, room PL–401,
Washington, DC.
Contact British Aerospace Regional
Aircraft American Support, 13850
Mclearen Road, Herndon, Virginia
20171, for service information identified
in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
E:\FR\FM\13DER1.SGM
13DER1
]]>Agencies
[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73581-73583]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23827]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 https://
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
https://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 https://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:
https://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
