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contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

71483 

Vol. 77, No. 232 

Monday, December 3, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0520; Directorate 

Identifier 2002–NE–43–AD; Amendment 39– 

17273; AD 2012–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Turbomeca S.A. Arriel 1A, 1A1, 1A2, 

1B, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K, 

1K1, 1S, and 1S1 turboshaft engines. 

That AD currently requires initial and 

repetitive visual inspections for erosion 

caused by dust ingestion and, if 

necessary, cleaning of the gas generator 

(module M03). This new AD requires 

determining the engine history; 

performing a one-time visual inspection 

of the axial compressor for erosion; 

performing initial and repetitive 

cleaning of the gas generator hollow 

shaft; and replacing the rear bearing if 

the amount of dust collected during 

cleaning exceeds 8 grams. This AD also 

includes an optional terminating action. 

This AD was prompted by in-service 

experience which has shown that dust 

inside the gas generator hollow shaft 

may be found when the axial 

compressor wheel has less erosion than 

initially assessed. We are issuing this 

AD to prevent an unbalance of the gas 

generator rotating assembly, which may 

lead to gas generator rear bearing failure, 

and uncommanded engine shutdown. 

DATES: This AD is effective January 7, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 7, 2013. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: 33 05 59 74 40 00; telex: 570 

042; fax: 33 05 59 74 45 15. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Rose 

Len, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238– 

7199; email: rose.len@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–12–14, 

Amendment 39–13199 (68 FR 36900, 

June 20, 2003). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

July 25, 2012 (77 FR 43550). That NPRM 

proposed to require determining the 

engine history; performing a one-time 

visual inspection of the axial 

compressor for erosion; performing 

initial and repetitive cleaning of the gas 

generator hollow shaft; and replacing 

the rear bearing if the amount of dust 

collected during cleaning exceeds 8 

grams. That NPRM also included an 

optional terminating action. That NPRM 

also removed Turbomeca S.A. Arriel 1E 

and 1K turboshaft engines from the 

applicability section of the AD. The 1E 

engine is no longer in service. The 1K 

engine is not an FAA validated engine. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Ease Requirements When 

Barrier Filters Used Continuously 

Charles E. Greenberg requested that 

the FAA consider modifying the AD to 

accommodate operators of helicopters 

with barrier filter installations for the 

engine intakes. If operator records can 

show that specific serial number 

engines have always operated with 

filtered air, the requirement for cleaning 

the gas generator hollow shaft should be 

superseded by a requirement to 

maintain records of operation with 

barrier filter protection. The commenter 

stated that no dirt can be ingested by an 

engine downstream of the filter, as long 

as the barrier filter has never gone into 

bypass mode. 

We disagree. The FAA cannot 

anticipate all of the available barrier 

filter designs installed on helicopter 

models. Each barrier filter design and 

helicopter combination would require 

its own assessment of the filter’s use 

and effectiveness. We did not change 

the AD. 

However, the substantiated 

continuous use of a barrier filter may be 

proposed as an alternative method of 

compliance (AMOC) to this AD, using 

the standard AMOC request procedure. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 1,421 engines installed on 

helicopters of U.S. registry. We also 

estimate that it will take about 24 workhours per engine to inspect and clean 

the gas generator module. The average 

labor rate is $85 per work-hour. A 

replacement gas generator rear bearing 

would cost about $4,128 per engine and 

take about 8 work-hours to replace. 

Based on these figures, we estimate the 

cost of the AD on U.S. operators to be 

$2,898,840. 


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71484 Federal Register / Vol. 77, No. 232 / Monday, December 3, 2012 / Rules and Regulations 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, 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 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2003–12–14, Amendment 39–13199 (68 

FR 36900, June 20, 2003), and adding 

the following new AD: 

2012–24–03 Turbomeca S.A.: Amendment 

39–17273; Docket No. FAA–2012–0520; 

Directorate Identifier 2002–NE–43–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 7, 2013. 

(b) Affected ADs 

This AD supersedes AD 2003–12–14, 

Amendment 39–13199 (68 FR 36900, June 

20, 2003). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 

1D1, 1E2, 1K1, 1S, and 1S1 turboshaft 

engines that have not incorporated 

Turbomeca S.A. Modification TU360. 

(d) Unsafe Condition 

This AD was prompted by in-service 

experience showing that dust inside the gas 

generator hollow shaft may be found when 

the axial compressor wheel has less erosion 

than initially assessed. We are issuing this 

AD to prevent an unbalance of the gas 

generator rotating assembly, which may lead 

to deterioration of the gas generator rear 

bearing and uncommanded engine 

shutdown. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 50 engine hours after the 

effective date of this AD, determine the 

engine history and perform the maintenance 

actions at the specified schedules. Use 

paragraphs 1.A. and 2.A. through 2.C. of 

Turbomeca S.A. Alert Mandatory Service 

Bulletin (MSB) No. A292 72 0230, Version C, 

dated February 29, 2012 to perform the 

maintenance actions and to establish the 

cleaning schedule. 

(2) If during any of the cleanings, the dust 

weight collected inside the gas generator 

hollow shaft is more than 8 grams, replace 

the gas generator rear bearing before further 

flight. 

(3) After the effective date of this AD, if 

there are any changes in accordance with 

paragraph 1.A.(1)(a)1.3 of Turbomeca S.A. 

Alert MSB No. A292 72 0230, Version C, 

dated February 29, 2012, within 50 engine 

hours time-in-service after such a change, 

accomplish the actions as specified in 

paragraphs (e)(1) and (e)(2) of this AD. 

(4) After the effective date of this AD, do 

not install any gas generator (module M03) 

on an engine unless it is in compliance with 

this AD. 

(5) After the effective date of this AD, do 

not install any gas generator rear bearing that 

has operated on an engine with a hollow 

shaft that has been found to have a dust 

weight more than 8 grams. 

(f) Optional Terminating Action 

As optional terminating action to the 

repetitive actions in this AD, modify the 

engine by incorporating Turbomeca S.A. 

Modification TU360. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Rose Len, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238–7199; 

email: rose.len@faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0071, dated April 26, 2012, 

and Turbomeca S.A. Alert MSB No. A292 72 

0230, Version C, dated February 29, 2012, for 

related information. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Turbomeca S.A. Alert Mandatory 

Service Bulletin No. A292 72 0230, Version 

C, dated February 29, 2012. 

(ii) Reserved. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 05 59 

74 40 00; telex: 570 042; fax: 33 05 59 74 45 

15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

November 20, 2012. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–28839 Filed 11–30–12; 8:45 am] 

BILLING CODE 4910–13–P 


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