2930 Federal Register / Vol. 77, No. 13 / Friday, January 20, 2012 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by March 5, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29: Hydraulic Power. 

(e) Reason 

This AD was prompted by a report of an 

electrical arc and hydraulic haze in the wheel 

bay of the left-hand main landing gear (MLG) 

possibly resulting from chafing between the 

hydraulic high pressure hose and electrical 

wiring of the green electrical motor pump 

(EMP). We are issuing this AD to detect and 

correct chafing of hydraulic pressure hoses 

and electrical wiring of the green EMPs, 

which in combination with a system failure, 

could cause an uncontrolled and undetected 

fire in the MLG bay. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Installing Placard and Revising Airplane 

Flight Manual 

For all airplanes, as of the effective date of 

this AD, the in-flight use of green EMPs is 

prohibited. Before the next flight, do the 

actions specified in paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) Install in the cockpit on the hydraulic 

power overhead panel 427VU, a locally 

manufactured self-adhesive placard 

prohibiting the in-flight use of the green 

EMPs, in accordance with the instructions in 

Airbus All Operators Telex A310–29A2101, 

Revision 01, dated April 12, 2011 (for 

airplanes equipped with EATON (formerly 

VICKERS) hydraulic EMPs); or Airbus All 

Operators Telex A310–29A2102, dated April 

12, 2011 (for airplanes equipped with 

PARKER (formerly ABEX) hydraulic EMPs). 

(2) Revise the Limitations section of the 

applicable airplane flight manual (AFM) to 

prohibit the in-flight use of the green EMPs. 

Note 1: Inserting a copy of this AD into the 

AFM Limitations section is acceptable for 

complying with the requirement of paragraph 

(g)(2) of this AD. 

(h) Inspecting for Damage and Chafing 

Within 500 flight hours or 4 months after 

the effective date of this AD, whichever 

occurs first, do a one-time general visual 

inspection for correct condition (i.e., no 

damage and no chafing) and correct 

installation of the hydraulic pressure hoses, 

electrical conduits, feeder cables, and 

associated clamping devices at frame 54, as 

well as the electrical conduits and feeder 

cables underneath the clamps (including 

removal of the concerned clamps), in 

accordance with the instructions in Airbus 

All Operators Telex A310–29A2101, Revision 

01, dated April 12, 2011 (for airplanes 

equipped with EATON (formerly VICKERS) 

hydraulic EMPs); or Airbus All Operators 

Telex A310–29A2102, dated April 12, 2011 

(for airplanes equipped with PARKER 

(formerly ABEX) hydraulic EMPs). If any 

incorrect installation is found, before further 

flight, install the affected parts correctly, in 

accordance with Airbus All Operators Telex 

A310–29A2101, Revision 01, dated April 12, 

2011 (for airplanes equipped with EATON 

(formerly VICKERS) hydraulic EMPs); or 

Airbus All Operators Telex A310–29A2102, 

dated April 12, 2011 (for airplanes equipped 

with PARKER (formerly ABEX) hydraulic 

EMPs). 

(1) If any damage or chafing marks are 

found during the inspection required by 

paragraph (h) of this AD, before further flight, 

replace or repair the affected parts (hydraulic 

pressure hoses, electrical conduits, feeder 

cables, clamps, and spacer, if installed), in 

accordance with the instructions in Airbus 

All Operators Telex A310–29A2101, Revision 

01, dated April 12, 2011 (for airplanes 

equipped with EATON (formerly VICKERS) 

hydraulic EMPs); or Airbus All Operators 

Telex A310–29A2102, dated April 12, 2011 

(for airplanes equipped with PARKER 

(formerly ABEX) hydraulic EMPs). 

(2) Before further flight after compliance 

with the requirements of paragraph (h) of this 

AD, as applicable, remove the placard 

required by paragraph (g)(1) of this AD; and 

remove the revision of the Limitations 

section of the AFM, as required by paragraph 

(g)(2) of this AD; from the airplane and the 

AFM, respectively. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to Attn: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0071, dated April 18, 2011; 

Airbus All Operators Telex A310–29A2101, 

Revision 01, dated April 12, 2011; and 

Airbus All Operators Telex A310–29A2102, 

dated April 12, 2011; for related information. 

Issued in Renton, Washington, on January 

13, 2012. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–1131 Filed 1–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0010; Directorate 

Identifier 2012–NE–03–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 adopt a new 

airworthiness directive (AD) for all 

Turbomeca S.A. Arriel 2B and 2B1 

turboshaft engines. This proposed AD 

was prompted by the discovery of nonconformities of certain power turbine 

(PT) blade fir-tree roots. This proposed 

AD would require removing the affected 

PT blades from service on or before 

reaching a new reduced life limit for 

those certain PT blades. We are 

proposing this AD to prevent PT blade 

rupture, which could result in an 

uncommanded in-flight engine 

shutdown, forced autorotation landing, 

or accident. 

DATES: We must receive comments on 

this proposed AD by March 20, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

For service information identified in 

this proposed AD, contact Turbomeca, 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 13 / Friday, January 20, 2012 / Proposed Rules 2931 

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 Operations office 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 Operations 

office (phone: (800) 647–5527) is the 

same as the Mail address provided 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–2012–0010; Directorate Identifier 

2012–NE–03–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 

closing date and may amend this 

proposed AD based on 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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, 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). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0218, 

dated November 10, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During production of Arriel 2 Power 

Turbine (PT) wheels, Turbomeca has 

detected geometric non-conformities on 

blade fir-tree roots. The technical 

investigations carried out by Turbomeca have 

shown that this non-conformity is due to PT 

blade manufacturing and that only a limited 

number of PT blades are potentially affected. 

This situation, if not detected and 

corrected, may potentially lead to a reduction 

in the fatigue resistance of the PT blades, 

which can reduce their in service use limit. 

This reduction of fatigue resistance can 

potentially result in blade rupture, which 

could cause an uncommanded in-flight 

shutdown, ultimately leading to an 

emergency autorotation landing for a singleengine helicopter. 

To address this unsafe condition, 

Turbomeca has issued Turbomeca Mandatory 

Service Bulletin (MSB) A292 72 2842, 

Version A, in which the life limit of those PT 

blades is reduced to 5,000 Flight Cycles (FC). 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Turbomeca S.A. has issued 

Mandatory Service Bulletin No. A292 72 

2842, Version A, dated September 23, 

2011. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination 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 

AD 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 150 engines installed on 

helicopters of U.S. registry. We also 

estimate that it would take about 4 

work-hours per product to comply with 

this proposed AD. The average labor 

rate is $85 per work-hour. A prorated 

replacement M04 module would cost 

about $20,000 per engine. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$3,051,000. 

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 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; 

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 regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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, 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
2932 Federal Register / Vol. 77, No. 13 / Friday, January 20, 2012 / Proposed Rules 

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 adding 

the following new airworthiness 

directive (AD): 

Turbomeca S.A.: Docket No. FAA–2012– 

0010; Directorate Identifier 2012–NE– 

03–AD. 

(a) Comments Due Date 

We must receive comments by March 20, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Turbomeca S.A. Arriel 

2B and 2B1 turboshaft engines with at least 

one installed power turbine (PT) blade part 

number (P/N) 2 292 81 A01 0, serial numbers 

(S/Ns) 102782 through 120230 inclusive, or, 

S/Ns 120293 through 120390 inclusive. 

(d) Reason 

This AD was prompted by the detection of 

geometric non-conformities on PT blade firtree roots. We are issuing this AD to prevent 

PT blade rupture, which could result in an 

uncommanded in-flight engine shutdown, 

forced autorotation landing, or accident. 

(e) Actions and Compliance 

Unless already done, do the following 

actions within 5,000 flight cycles on the PT 

blades, or within one month after the 

effective date of this AD, whichever occurs 

later. 

(1) Replace the PT blades with PT blades 

eligible for installation; or 

(2) Replace the M04 module with an M04 

module having PT blades eligible for 

installation; or 

(3) Replace the PT wheel assembly with a 

PT wheel assembly having PT blades eligible 

for installation. 

(4) Guidance on the replacements specified 

in paragraphs (e)(1) through (e)(3) can be 

found in Turbomeca S.A. Mandatory Service 

Bulletin No. A292 72 2842, Version A, dated 

September 23, 2011. 

(f) Definition 

For the purposes of this AD, a PT blade 

eligible for installation is one not listed in 

paragraph (c) of this AD or, one listed in 

paragraph (c) of this AD with fewer than 

5,000 flight cycles. 

(g) Installation Prohibition 

From the effective date of this AD: 

(1) Do not install a PT blade as listed in 

paragraph (c) of this AD, that has 5,000 or 

more flight cycles, into any engine. 

(2) Do not install any engine with a PT 

blade as listed in paragraph (c) of this AD, 

that has 5,000 or more flight cycles, onto a 

helicopter. 

(h) 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. 

(i) 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 MCAI EASA Airworthiness 

Directive 2011–0218, dated November 10, 

2011, and Turbomeca S.A. Alert Service 

Bulletin No. A292 72 2842, Version A, dated 

September 23, 2011, for related information. 

(3) For service information identified in 

this AD, contact Turbomeca, 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 

January 13, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1129 Filed 1–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28059; Directorate 

Identifier 2007–NE–13–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all RR RB211-Trent 553–61, 553A2– 

61, 556–61, 556A2–61, 556B–61, 

556B2–61, 560–61, 560A2–61, 768–60, 

772–60, 772B–60, 875–17, 877–17, 884– 

17, 884B–17, 892–17, 892B–17, and 

895–17 turbofan engines. That NPRM 

proposed to supersede an existing AD 

that requires inspecting the 

intermediate-pressure (IP) compressor 

rotor shaft rear balance land for cracks, 

which could lead to engine failure. This 

action revises that NPRM by changing 

the optional terminating action for 

RB211-Trent 700 and RB211-Trent 800 

engines to mandatory terminating 

action. Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this supplemental NPRM by March 20, 

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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–245418 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp. You may review copies 

of the referenced service information at 

the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803. 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, 

MA; phone: (781) 238–7143; fax: (781) 

238–7199; email: alan.strom@faa.gov. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS