[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.
----------------------------------------------------------------------------------------------------------------

    (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]
BILLING CODE 4910-13-P