43550 Federal Register / Vol. 77, No. 143 / Wednesday, July 25, 2012 / Proposed Rules 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1294, dated March 31, 2011, 

specifies to do the action after the original 

issue date of that service bulletin, this AD 

requires the compliance time after the 

effective date of this AD. 

(3) Where the Condition column of table 1 

of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 737–53– 

1294, dated March 31, 2011, specifies a 

condition as of the original issue date of that 

service bulletin, this AD specifies the 

condition as of the effective date of this AD. 

(4) Note 1 of paragraph 3.A. of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1294, dated March 31, 2011, is to be 

disregarded when accomplishing the actions 

required by this AD. 

(j) Post-Repair Inspections 

The post-repair inspections, specified in 

Table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

737–53–1294, dated March 31, 2011, are not 

required by this AD. 

Note 1 to paragraph (j) of this AD: The 

damage tolerance inspections specified in 

Table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

737–53–1294, dated March 31, 2011, may be 

used in support of compliance with Section 

121.1109(c)(2) or 129.109(c)(2) of the Federal 

Aviation Regulations (14 CFR 121.1109(c)(2) 

or 14 CFR 129.109(c)(2)). The corresponding 

actions specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1294, dated March 

31, 2011, are not required by this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, it may be emailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

Aircraft Certification Office (ACO) to make 

those findings. For a repair method to be 

approved, the repair must meet the 

certification basis of the airplane and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6450; fax: 425–917–6590; 

email: alan.pohl@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on July 17, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18147 Filed 7–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0520; Directorate 

Identifier 2002–NE–43–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Turbomeca S.A. Arriel 

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

1D1, 1E, 1E2, 1K, 1K1, 1S, and 1S1 

turboshaft engines. The existing AD 

currently requires initial and repetitive 

visual inspections for erosion caused by 

dust ingestion and, if necessary, 

cleaning of the gas generator (module 

M03). Since we issued that AD, inservice experience has shown that dust 

inside the gas generator hollow shaft 

may be found when the axial 

compressor wheel has less erosion than 

initially assessed. This proposed AD 

would require determining the engine 

history, a one-time visual inspection of 

the axial compressor for erosion, initial 

and repetitive cleaning of the gas 

generator hollow shaft, and replacement 

of the rear bearing if the amount of dust 

collected during cleaning exceeds 8 

grams. This proposed AD also includes 

an optional terminating action. We are 

proposing 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: We must receive comments on 

this proposed AD by September 24, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33 05 59 74 40 

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

review copies of the referenced 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0520; Directorate Identifier 

2002–NE–43–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 143 / Wednesday, July 25, 2012 / Proposed Rules 43551 

closing date and may amend this 

proposed AD because of those 

comments. 

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 we receive 

about this proposed AD. 

Discussion 

On June 13, 2003, we issued AD 

2003–12–14, Amendment 39–13199 (68 

FR 36900, June 20, 2003), 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 requires initial and repetitive 

visual inspections for ingestive erosion 

and, if necessary, cleaning of the 

module M03. That AD resulted from 

reports from the manufacturer of an 

unbalance due to accumulation of dust 

in the gas generator hollow shaft. We 

issued that 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. 

Actions Since Existing AD Was Issued 

Since we issued AD 2003–12–14, 

Amendment 39–13199 (68 FR 36900, 

June 20, 2003), in-service experience 

has shown that dust inside the gas 

generator hollow shaft may be found 

when the axial compressor wheel has 

less erosion than initially assessed. 

Also, since we issued that AD, 

Turbomeca S.A. has developed an 

improvement of the gas generator 

hollow shaft (Modification TU360), 

which makes the engine less susceptible 

to dust ingestion. This proposed AD 

would have optional terminating action 

to the inspections and cleaning, by the 

incorporation of Modification TU360. 

Also, since we issued AD 2003–12–14, 

the European Aviation Safety Agency 

(EASA) issued AD 2012–0071, dated 

April 26, 2012, to address the 

conditions and improvements just 

described in the European Community. 

This proposed AD would remove 

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 

and was incorrectly included in AD 

2003–12–14. 

Relevant Service Information 

We reviewed Turbomeca S.A. Alert 

Mandatory Service Bulletin (MSB) No. 

A292 72 0230, Version C, dated 

February 29, 2012. The Alert MSB 

describes procedures for the 

determination of the engine history, a 

one-time visual inspection of the axial 

compressor for erosion, to define the 

initial cleaning of the gas generator 

hollow shaft, and the interval for 

repetitive cleaning of the shaft. The 

referenced service bulletin also 

describes the criteria for replacement of 

the rear bearing if dust is found. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require the 

following: 

• Determining the engine history; and 

• Performing a one-time visual 

inspection of the axial compressor for 

erosion, and initial and repetitive 

cleaning of the gas generator hollow 

shaft; and 

• Replacing the gas generator rear 

bearing before further flight if the dust 

collected during any cleaning inside the 

gas generator hollow shaft exceeds 8 

grams; and 

• 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-inservice after such a change, accomplish 

the actions required by this AD; and 

• After the effective date of the AD, 

do not install a module M03 on an 

engine unless it is in compliance with 

the requirements in this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 1,421 engines 

installed on helicopters of U.S. registry. 

We also estimate that it would take 

about 24 work-hours 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 

proposed AD on U.S. operators to be 

$2,898,840. 

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 

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 that the proposed 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), 

(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. 

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 

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: 

Turbomeca S.A.: Docket No. FAA–2012– 

0520; Directorate Identifier 2002–NE– 

43–AD. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
43552 Federal Register / Vol. 77, No. 143 / Wednesday, July 25, 2012 / Proposed Rules 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by September 24, 2012. 

(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 

paragraph (e)(1) and (e)(2) in 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. 

(3) For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33 05 59 74 40 00; 

fax: 33 05 59 74 45 15. You may review 

copies of the referenced 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. 

Issued in Burlington, Massachusetts, on 

July 20, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–18155 Filed 7–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0681; Directorate 

Identifier 2008–NE–13–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Turbomeca S.A. Arriel 

1E2, 1S, and 1S1 turboshaft engines. 

The existing AD currently requires a one 

time inspection and torque check of a 

certain 3-way union plug installed on 

all fuel control units (FCUs). Since we 

issued that AD, the applicability has 

been reduced to certain FCUs and the 

referenced service bulletin has been 

updated with additional detailed 

information to identify the noncompliant ‘‘red disk’’ plug. This 

proposed AD would still require a one 

time inspection and torque check of the 

3-way union plug, would require 

replacement of the plug before further 

flight if it is found to be non-compliant, 

and would prohibit installation of FCUs 

that have not passed the 3-way union 

plug inspection and torque check. We 

are proposing this AD to prevent fuel 

leaks, which could result in a fire and 

damage to the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 24, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 

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

Friday, except Federal holidays. 

For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33 05 59 74 40 

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

review copies of the referenced 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2008–0681; Directorate Identifier 

2008–NE–13–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS