[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73579-73581]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23831]
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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.
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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 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, 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 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 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
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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:
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(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.
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(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 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. 05-23831 Filed 12-12-05; 8:45 am]
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