DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-201 5-7490; Directorate Identifier 2015-NE-40-AD] 

RIN 2120-AA64 

Ainvorthincss Directives; Turbomcca S.A. Turboshaft Engines 

AGENCY: federal Aviation Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking (NPRM). 

[4910-13-Pl 

SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain 

Turbomeca S.A. Astazou XIV B and H turboshaft engines. This proposed AD was 

prompted by a report of a crack on the 3rd stage turbine wheel. This proposed AD would 

require a one-time inspection of the front surface of the 3rd stage turbine for a groove. We 

are proposing this AD to prevent cracks in the 3rd stage turbine wheel, failure of the 

engine, in-llight shutdown, and loss of control of the helicopter. 

DATES: We must receive comments on this proposed AD by [INSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

ADDRESSES: You may send comments by any of the following methods: 

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Docket Management Facility, U.S. Department ofTranspor1ation, 1200 

New Jersey Avenue SE., West Building Ground Floor, Room W12- 140, Washington, DC 

20590-000 I. 
• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., 

Monday through Friday, except f-ederal holidays. 

• Fax: 202-493-225 1. 

For service information identified in this proposed AD, contact Turbomeca S.A., 

40220 Tamos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. You may 

view this service information at the FAA, Engine & Propeller Directorate, 1200 District 

A venue, Burlington, MA. For information on the availability of this materi al at the FAA, 

ca11781-238-7 125. 

Examining the AD Docket 

You may examine the AD docket on the Internet at http://www.rcgulations.gov by 

searching for and locating Docket No. F AA-20 15-7490; or in person at the Docket 

Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 

holidays. The AD docket contains this proposed AD, the mandatory continuing 

airworthiness information (MCAI), the regulatory evaluation, any comments received, 

and other information. The address for the Docket Office (phone: 800-647-5527) is in the 

ADDRESSES section. Comments will be avail able in the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781-238-7134; fax: 78 1-238-7199; email: 

wcgo.wang@ faa.gov. 

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SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any writlen relevant data, views, or arguments about this 

NPRM. Send your comments to an add ress listed under the ADDRESSES section. 

Include "Docket No. FAA-20 15-7490: Directorate Identifier 2015-NE-40-AD" at the 

beginning of your comments. We specifically invite comments on the overall regulatory, 

economic, environmental, and energy aspects of this NPRM. We will consider all 

comments received by the closing date and may amend this NPRM based on those 

cornments. 

We will post all comments we receive, without change, to 

http://www.regulations.gov, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact with FAA personnel 

concerni ng this NPRM. 

Discussion 

The European Aviation Safety Agency (EASA), which is the Technical Agent for 

the Member States of the European Community, has issued EASA AD 20 15-0223, elated 

November 16, 2015 (refeiTed to hereinafter as " the MCAI"), to correct an unsafe 

condition for the specified products. The MCAI states: 

During the overhaul of an ASTAZOU XIV engine, a crack was 

detected on the front face of the third stage turbine wheel between 

two balanci ng lugs. The cause of the crack is probably linked to a 

geometric singularity, likely caused by the transformation 

operation aimed at introducing expansion slots between the blades 

duri ng embodiment ofTurbomeca mod AB 173. Although there is 

only one known case of this type of crack, and although it was 

detected, the possibility exists that additional parts have the same 

geometric singularity. 

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This condition, if not detected and coJTected, may lead to fai lure of 

a turbine blade and its associated piece of rim, possibly resulting in 

an uncommanded in-flight shut-down and/or release of high energy 

debris. 

You may obtain further information by examining the MCAI in the AD docket on 

the Internet at http://www.regulations.gov by searching for and locating Docket No. 

F AA-20 15-7490. 

Related Service Information under 1 CFR Part 51 

Turbomeca S./\. has issued Service Bulletin (SB) No. 283 72 0811 , Version A, 

elated August 25,2015. The SB describes procedures for inspection ofthc 3rd stage 

turbine wheel. This service information is reasonably available because the interested 

parties have access to it through their normal course of business or by the means 

identified in the ADDRESSES section ofthis NPRM. 

FAA's Determination and Requirements of This Proposed AD 

This product has been approved by the aviation authority of france, and is 

approved for operation in the United States. Pursuant to our bilateral agreement with the 

European Community, EASA has notified us of the unsafe condition described in the 

MCAI and service information referenced above. We are proposing this NPRM because 

we evaluated all information provided by EASA and determined the unsafe condition 

exists and is likely to exist or develop on other products of the same type design. This 

NPRM would require inspecting the front surface of the 3rd stage turbine for a groove. 

Costs of Compliance 

We estimate that this proposed AD affects 9 engines installed on helicopters of 

U.S. registry. We also estimate that it would take about 5 hours per engine to comply 

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with this proposed AD. The average labor rate is $85 per hour. Based on these figures, 

we estimate the cost of this proposed AD on U.S. operators to be $3,825. 

Authority for This Rulemaking 

Title 49 of the United States Code specifies the f-AA's authority to issue rules on 

aviation safety. Subtitle I, section I 06, describes the authority of the r AA 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 Vll , 

Part A, Subpart IIJ, Section 44 70 I: General requirements." Under that section, Congress 

charges the FAA with promoting safe f1ight of civil aircraft in air commerce by 

prescribing regulations for practices, methods, and procedures the Administrator finds 

necessary for safety in a ir 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 

identi tied in this rulemaking action. 

Regulatory Findings 

We determined that this proposed AD would not have federalism implications 

under Executive Order 13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a "significant regulatory action" under Executive Order 12866, 

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(2) Is not a "significant rule" under the DOT Regulatory Policies and Procedures 

(44 FR 11034, february 26, 1979), 

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation safe ty, Incorporation by reference, Safety. 

The Proposed Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA 

proposes to amend 14 CFR part 39 as follows: 

PART 39 - AIRWORTHINESS DIRECT IVES 

l. The authority citation for part 39 continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113,44701. 

§ 39.13 [Amended! 

2. The FAA amends§ 39.1 3 by adding the fo llowing new airworthiness directi ve 

(AD): 

Turbomeca S.A.: Docket No. F AA-20 15-7490; Directorate Identifier 20 15-NE-40-AD. 

(a) Comments Due Date 

We must receive comments by (INSERT DATE 60 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

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(c) pplic tbili ty 

This AD applies to all Astazou XIV Band XIV H turboshaft engines with 3rd 

stage turbi ne wheel, part number (PIN) 0 265 25 700 0 or P/N 0 265 25 706 0, installed, if 

the engine incorporates Turbomeca modification AB- 173 or AB-208. 

(d) Reason 

This AD was prompted by a report of a crack on the 3rd stage turbine wheel. We 

are issuing this AD to prevent cracks in the 3rd stage turbine wheel, fa ilure of the engine, 

in-flight shutdown, and loss of control of the helicopter. 

(e) Actions and Compliance 

Comply with this AD within the compliance times specified, unless already clone. 

(1) At the next piece part exposure of the 3rd stage turbine wheel or within I ,000 

engine hours after the effective date of this AD whichever comes first, perform a onetime inspection for a groove on the front surface of the 3rd stage turbi ne wheel. Use 

Accomplishment Instructions, paragraph 4.4.2, ofTurbomeca S.A. Service Bulletin (SB) 

No. 283 72 0811 , Version A, elated August 25, 2015 to perform the inspection. 

(2) Ifthe 3rd stage turbine wheel passes inspection required by paragraph (e)( I) of 

this AD, no further action is required. 

(3) lfthe 3rd stage turbine wheel fails inspection req uired by paragraph (e)(l) of 

this AD, remove the part and replace with a part eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not insta ll any 3rd stage tu rbine wheel, PIN 

0 265 25 700 0 or P/N 0 265 25 706 0, unless it was inspected per the Accomplishment 

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Instructions, paragraph 4.4.2, ofTurbomeca S.A. SB No. 283 72 0811 , Version A, dated 

August 25, 2015. 

(g) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, FAA, may approve AMOCs for this 

AD. Usc the procedures found in 14 CFR 39. 19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(h) Related Information 

( I) For more inf01mation about this AD, contact Wego Wang, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803; phone: 781-238-7134; fax: 781-238-7199; 

email: wego.wang@faa.gov. 

(2) Refer to MCAT European Aviation Safety Agency AD 2015-0223, dated 

November 16, 2015, for more information. You may examine the MCAl in the AD 

docket on the Internet at http://W\.vw.regulations.gov by searching for and locating it in 

Docket No. F AA-20 15-7490. 

(3) Turbomeca S.A. SB No. 283 72 08 11 , Version A, dated August 25,20 15, can 

be obtained fi·om Turbomeca S.A., using the contact information in paragraph (h)(4) of 

this proposed AD. 

(4) For service information identified in this proposed AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. 

(5) You may view this service information at the FAA, Engine & Propeller 

Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of 

this material at the F i\A, call 781-238-7 125. 

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Issued in Burlington, Massachusetts, on January 27, 2016. 

Coll een M. D' Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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