2928 Federal Register / Vol. 77, No. 13 / Friday, January 20, 2012 / Proposed Rules 

For the reasons discussed, 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); 

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. 

We prepared an economic 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, 

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 AD: 

Agusta S.P.A. Helicopters (Agusta): Docket 

No. FAA–2012–0013; Directorate 

Identifier 2010–SW–043–AD. 

(a) Applicability 

This AD applies to Agusta Model AB139 

and AW139 helicopters, with a generator 

control unit (GCU), part-number (P/N) 

1152550–3 installed; certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

potential fault in the overvoltage protection 

in GCUs currently installed on Model AB139 

and AW139 helicopters. We are proposing 

this AD to prevent failure of the overvoltage 

protection of the GCU, degraded performance 

of the electrical power generation and 

distribution systems, or fire, and subsequent 

loss of control of the helicopter. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(d) Requirements 

(1) Remove the No. 1 and No. 2 GCU, 

P/N 1152550–3. Do not install GCU, 

P/N 1152550–3, on any helicopter. 

(2) Modify the electrical connector A13P1 

(GCU #1) and A14P1 (GCU #2) by installing 

the wiring to the power distribution panel 

(PDP) for your serial-numbered helicopter as 

depicted in Figure 1 of Agusta Bollettino 

Tecnico No. 139–133, Revision A, dated 

March 17, 2009. 

(3) Using either GCU P/N 1152550–4 or 

GCU P/N 1152550–5, install a No. 1 and No. 

2 GCU that has the same part number. Having 

different part-numbered GCUs on the same 

helicopter is not approved. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, Rotorcraft Directorate, 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, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office, before operating any aircraft 

complying with this AD through an AMOC. 

(f) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (Italy) AD 

2009–0042, dated February 25, 2009. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2430 DC generating system. 

Issued in Fort Worth, Texas, on January 5, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1121 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–2012–0033; Directorate 

Identifier 2011–NM–086–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A310 series airplanes. 

This proposed 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). This proposed AD 

would require prohibiting in-flight use 

of the green EMPs; revising the airplane 

flight manual (AFM) limitations section; 

installing a placard in the cockpit 

overhead panel; doing a one-time 

general visual inspection for correct 

condition and installation of hydraulic 

pressure hoses, electrical conduits, 

feeder cables, and associated clamping 

devices; and corrective action if 

necessary. We are proposing 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. 

DATES: We must receive comments on 

this proposed AD by March 5, 2012. 

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. 

• 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, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

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 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 13 / Friday, January 20, 2012 / Proposed Rules 2929 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 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. 

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–2012–0033; Directorate Identifier 

2011–NM–086–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 we receive 

about this proposed AD. 

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 2011–0071, 

dated April 18, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

An operator reported an electrical arc and 

a large hydraulic haze in the left hand Main 

Landing Gear (LH MLG) wheel bay that 

occurred during ground operation. The 

analysis revealed that this occurrence is 

likely the result of chafing between hydraulic 

high pressure hose and electrical wiring of 

the Green Electrical Motor Pump (EMP). 

This condition, if not detected and 

corrected, and in combination with a system 

failure leading to the use of the Green EMPs 

in flight, could lead to an uncontrolled and 

undetected fire in the MLG bay. 

For the reasons explained above, this AD 

temporarily prohibits the in-flight use of 

green EMPs, by mandating an update of the 

Aeroplane Flight Manual (AFM) limitations 

section and installation of a placard in the 

cockpit overhead panel. This [EASA] AD 

requires also a one-time [general] visual 

inspection of hydraulic pressure hoses and 

electrical wiring of Green EMPs and 

corrective action(s), depending on findings. 

Corrective actions include repair or 

replacement of the hydraulic pressure 

hoses and electrical wiring with new 

hydraulic pressure hoses and electrical 

wiring. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued All Operators Telex 

A310–29A2101, Revision 01, dated 

April 12, 2011; and All Operators Telex 

A310–29A2102, dated April 12, 2011. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an 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 58 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $200 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$21,460, or $370 per product. 

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); 

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. 

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, 

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 AD: 

Airbus: Docket No. FAA–2012–0033; 

Directorate Identifier 2011–NM–086–AD. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
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