Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines, 73579-73581 [05-23831]
Download as PDF
<![CDATA[
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
We are issuing this AD to prevent reduced
structural integrity of the engine mount,
which could result in possible separation of
an engine from the airplane.
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.
Determine Serial Number (S/N) and Inspect
if Necessary
(f) Within the applicable compliance time
specified in paragraph (f)(1), (f)(2), or (f)(3) of
this AD: Determine the serial number of the
engines installed on the airplane, as
identified in the table in paragraph 1.A.,
‘‘Effectivity,’’ of Dassault Service Bulletin
F2000–299, dated July 23, 2004; if any
affected serial number is found on any
engine, perform a borescope inspection to
verify that a spherical bearing is installed on
the attachment fitting of the front engine
mount by doing all the applicable actions
specified in the Accomplishment
Instructions of the service bulletin.
(1) For airplanes with any engine having
850 total landings or less as of the effective
date of this AD: Before the accumulation of
880 total landings on the engine.
(2) For airplanes with any engine having
more than 850 total landings, but 1,000 total
landings or less as of the effective date of this
AD: Within 1 month after the effective date
of this AD.
(3) For airplanes with any engine having
more than 1,000 total landings as of the
effective date of this AD: Within 10 landings
after the effective date of this AD.
Corrective Action
(g) If any spherical bearing is found
missing during the inspection required by
paragraph (f) of this AD: Before further flight,
repair according to a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
´ ´
FAA; or the Direction Generale de l’Aviation
Civile (or its delegated agent).
No Reporting Requirement
(h) This AD does not require submitting
reporting information to the manufacturer.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Related Information
(j) French airworthiness directive F–2004–
128, issued August 4, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(k) You must use Dassault Service Bulletin
F2000–299, dated July 23, 2004, to perform
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606,
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., room PL–401,
Nassif Building, Washington, DC; 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 the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23829 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–2005–22928; Directorate
Identifier 2005–NE–43–AD; Amendment 39–
14406; AD 2005–25–13]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 2B and 2B1 Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Turbomeca Arriel 2B and 2B1 turboshaft
engines without modification TU22
incorporated. This AD requires initial
and repetitive visual checks of the free
turbine shield for cracks. This AD
results from reports of several free
turbine shields found with large
circumferential cracks. We are issuing
this AD to prevent failure of the free
turbine shield, leading to engine
misalignment, in-flight engine
shutdown, emergency autorotation
landing, or accident.
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.
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
73579
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.
• 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 Arriel 2B and 2B1 turboshaft
engines without modification TU22
incorporated. The DGAC advises that on
several of these engines, large
circumferential cracks were found in the
free turbine shield at the blending
radius between the containment shield
and the rear flange. These cracks could
cause a loss of engine alignment during
maneuvering loads and lead to in-flight
engine shutdown.
ADDRESSES:
Relevant Service Information
We have reviewed and approved the
technical contents of Turbomeca Alert
Mandatory Service Bulletin No. A292 72
2821, dated June 27, 2005, that
describes procedures for visual checks
of the free turbine shield for cracks. The
DGAC classified this service bulletin as
mandatory and issued AD F–2005–162,
dated September 28, 2005, in order to
ensure the airworthiness of these Arriel
2B and 2B1 engines in France.
Bilateral Airworthiness Agreement
These Turbomeca Arriel 2B and 2B1
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
E:\FR\FM\13DER1.SGM
13DER1
73580
Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations
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 Arriel 2B and 2B1
turboshaft engines without modification
TU22 incorporated, of the same type
design. We are issuing this AD to
prevent failure of the free turbine shield,
leading to engine misalignment, inflight engine shutdown, emergency
autorotation landing, or accident. This
AD requires initial visual checks of the
free turbine shield for cracks within 10
operating hours of the effective date of
the AD, repetitive visual checks at
certain compliance intervals based on
shield condition, and replacement if
necessary. This AD also allows
incorporation of Turbomeca
modification TU22 as optional
terminating action to the required
repetitive visual checks. You must use
the service information described
previously to perform the actions
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–2005–22928; Directorate Identifier
2005–NE–43–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.
VerDate Aug<31>2005
16:47 Dec 12, 2005
Jkt 208001
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 Offices 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
PO 00000
Frm 00028
Fmt 4700
Sfmt 4700
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 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:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
2005–25–13 Turbomeca: Amendment 39–
14406. Docket No. FAA–2005–22928;
Directorate Identifier 2005–NE–43–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca Arriel 2B
and 2B1 turboshaft engines without
modification TU22 incorporated. These
engines are installed on, but not limited to,
Eurocopter France AS350B3 and EC130B4
helicopters.
Unsafe Condition
(d) This AD results from reports of several
free turbine shields found with large
circumferential cracks. We are issuing this
AD to prevent failure of the free turbine
shield, leading to engine misalignment, inflight engine shutdown, emergency
autorotation landing, or accident.
E:\FR\FM\13DER1.SGM
13DER1
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
]]>Agencies
[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73579-73581]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23831]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22928; Directorate Identifier 2005-NE-43-AD;
Amendment 39-14406; AD 2005-25-13]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 2B and 2B1 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 Arriel 2B and 2B1 turboshaft engines without modification
TU22 incorporated. This AD requires initial and repetitive visual
checks of the free turbine shield for cracks. This AD results from
reports of several free turbine shields found with large
circumferential cracks. We are issuing this AD to prevent failure of
the free turbine shield, leading to engine misalignment, in-flight
engine shutdown, emergency autorotation landing, or accident.
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.
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 Arriel 2B and 2B1
turboshaft engines without modification TU22 incorporated. The DGAC
advises that on several of these engines, large circumferential cracks
were found in the free turbine shield at the blending radius between
the containment shield and the rear flange. These cracks could cause a
loss of engine alignment during maneuvering loads and lead to in-flight
engine shutdown.
Relevant Service Information
We have reviewed and approved the technical contents of Turbomeca
Alert Mandatory Service Bulletin No. A292 72 2821, dated June 27, 2005,
that describes procedures for visual checks of the free turbine shield
for cracks. The DGAC classified this service bulletin as mandatory and
issued AD F-2005-162, dated September 28, 2005, in order to ensure the
airworthiness of these Arriel 2B and 2B1 engines in France.
Bilateral Airworthiness Agreement
These Turbomeca Arriel 2B and 2B1 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
[[Page 73580]]
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 Arriel 2B and 2B1 turboshaft engines without
modification TU22 incorporated, of the same type design. We are issuing
this AD to prevent failure of the free turbine shield, leading to
engine misalignment, in-flight engine shutdown, emergency autorotation
landing, or accident. This AD requires initial visual checks of the
free turbine shield for cracks within 10 operating hours of the
effective date of the AD, repetitive visual checks at certain
compliance intervals based on shield condition, and replacement if
necessary. This AD also allows incorporation of Turbomeca modification
TU22 as optional terminating action to the required repetitive visual
checks. You must use the service information described previously to
perform the actions 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-2005-22928;
Directorate Identifier 2005-NE-43-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 Offices 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.
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
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
2005-25-13 Turbomeca: Amendment 39-14406. Docket No. FAA-2005-22928;
Directorate Identifier 2005-NE-43-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft
engines without modification TU22 incorporated. These engines are
installed on, but not limited to, Eurocopter France AS350B3 and
EC130B4 helicopters.
Unsafe Condition
(d) This AD results from reports of several free turbine shields
found with large circumferential cracks. We are issuing this AD to
prevent failure of the free turbine shield, leading to engine
misalignment, in-flight engine shutdown, emergency autorotation
landing, or accident.
[[Page 73581]]
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 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
----------------------------------------------------------------------------------------------------------------
Crack locations using Re-check using paragraphs
Number of cracks: appendix 1 from MSB Crack length: (f)(1) and (f)(2) of this
A292 72 2821: AD, or replace:
----------------------------------------------------------------------------------------------------------------
(i) 0............................. Not Applicable....... Not Applicable............ Re-check shield within
500 N1 cycles.
(ii) 1............................ D-A.................. (A) Less than 170 mm...... Re-check shield within
100 N1 cycles.
(B) Between 170 mm and 200 Re-check shield daily.
mm.
(C) Greater than 200 mm... Replace shield before
further flight.
(iii) 1........................... A-B.................. (A) Less than 201 mm...... Re-check within 100
cycles.
(5:00 o'clock Area).. (B) Between 201 mm and 248 Re-check daily.
mm.
(C) Greater than 248 mm... Replace shield before
further flight.
(iv) 1............................ C-D.................. (A) Less than 297 mm...... Re-check within 100
cycles.
(8:00 o'clock Area).. (B) Between 297 mm and 366 Re-check daily.
mm.
(C) Greater than 366 mm... Replace shield before
further flight.
(v) 2............................. One in A-B and one in (A) Zone 1 using Appendix Re-check within 100
C-D. 3 of MSB A292 72 2821. cycles.
(B) Zone 2 using Appendix Re-check daily.
3 of MSB A292 72 2821.
(C) Zone 3 using Appendix Replace shield before
3 of MSB A292 72 2821. further flight.
(vi) 2............................ Either one or both in Any....................... Replace shield before
D-A. further flight.
(vii) 2........................... Both in A-B.......... Any....................... Replace shield before
further flight.
(viii) 2.......................... Both in C-D.......... Any....................... Replace shield before
further flight.
(ix) 3 or more.................... Any.................. Any....................... Replace shield before
further flight.
----------------------------------------------------------------------------------------------------------------
(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, 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. 05-23831 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P
