Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37779 

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 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. 

Adoption of the 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 Amendment 39–16836 (76 FR 

68299, November 4, 2011), and adding 

the following new airworthiness 

directive (AD): 

2012–12–21 Eurocopter Deutschland 

GMBH: Amendment 39–17101; Docket 

No. FAA–2012–0659; Directorate 

Identifier 2011–SW–061–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 

C–2 helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

excessively high reverse current flow when 

switching off a generator during flight, which 

could make the remaining generator fail and 

result in a complete electrical power system 

failure and subsequent loss of control of the 

helicopter. 

(c) Other Affected ADs 

This AD supersedes AD 2011–21–13, 

Amendment 39–16836 (76 FR 68299, 

November 4, 2011). 

(d) 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. 

(e) Required Action 

Within 30 days: 

(1) Remove the specified temporary pages 

from the following sections of the rotorcraft 

flight manual (RFM) RFM BK 117 C–2: 

(i) ‘‘Emergency and Malfunction 

Procedures’’: pages 3–3 and 3–4, and 

(ii) ‘‘Performance Data’’: page 5–7. 

(2) Remove diodes CR10007 and CR10008 

from the generator relays in the left-hand and 

right-hand After Junction Boxes, respectively, 

in accordance with the Accomplishment 

Instructions, paragraphs 3.B.2.(a) through 

3.B.2.(d), and as depicted in Figures 1 and 2, 

of Eurocopter Alert Service Bulletin ASB 

MBB BK117 C–2–24A–008 Revision 1, dated 

August 29, 2011. 

(3) Test the DC Power system for proper 

operation. 

(4) Do not install an After Junction Box on 

any helicopter, unless the After Junction Box 

has been modified in accordance with the 

requirements of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Safety Management Group, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5114, email: 

george.schwab@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR 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. 

(g) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency AD No. 

2011–0162, dated August 30, 2011. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2435: Starter Generator. 

(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) Eurocopter Alert Service Bulletin ASB 

MBB BK117 C–2–24A–008 Revision 1, dated 

August 29, 2011. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, telephone 

(972) 641–0000 or (800) 232–0323, fax (972) 

641–3775, or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(5) You may also 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on June 14, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–15325 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0013; Directorate 

Identifier 2010–SW–043–AD; Amendment 

39–17090; AD 2012–12–10] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model AB139 and 

AW139 helicopters with a certain 

generator control unit (GCU), to require 

replacing each affected GCU with an 

airworthy GCU. This AD was prompted 

by laboratory tests which revealed a 

potential fault in the overvoltage 

protection on a certain part-numbered 

GCU. The actions are intended to 

prevent failure of the overvoltage 

protection of the GCU, degraded 

performance of the electrical power 

generation and distribution systems, a 

fire, and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective July 30, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 30, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39–0331–711133; 

fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 


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37780 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

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 AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Mark Wiley, Aerospace Engineer, FAA, 

Regulations and Policy Group, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5134; fax (817) 

222–5961; email mark.wiley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 20, 2012, at 77 FR 2926, 

the Federal Register published our 

Notice of Proposed Rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 to include an AD that 

would apply to Agusta Model AB139 

and AW139 helicopters, with a GCU, 

part-number (P/N) 1152550–3, installed. 

That NPRM proposed to require, within 

6 months, removing the No. 1 and No. 

2 GCU, P/N 1152550–3, modifying the 

electrical connectors A13P1 and A14P1 

by installing wiring to the power 

distribution panel, and installing a No. 

1 and No. 2 GCU with P/N 1152550–4 

or 1152550–5. Both GCUs must have 

identical P/Ns on the same helicopter. 

The proposed requirements were 

intended to prevent failure of the 

overvoltage protection of the GCU, 

degraded performance of the electrical 

power generation and distribution 

systems, a fire, and subsequent loss of 

control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2009– 

0042, dated February 25, 2009 (AD 

2009–0042), to correct an unsafe 

condition for the Agusta Model AB139 

and AW139 helicopters, all serial 

numbers (S/Ns) except S/Ns 31002, 

31003, 31004, and 31007. EASA advises 

that laboratory tests performed on a new 

GCU model under development have 

shown a potential fault in the 

overvoltage protection of currently 

installed GCUs, P/N 1152550–3. EASA 

also advises that this condition, if not 

corrected, could adversely affect the 

helicopter’s electrical power generation 

and distribution system functionalities. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, the EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by the EASA and determined 

that an unsafe condition exists and is 

likely to exist or develop on other 

helicopters of these same type designs. 

We have determined that air safety and 

the public interest require adopting the 

AD requirements as proposed, except 

for a typographical correction in the 

Related Service Information paragraph 

of the NPRM, which referred to the 

EASA AD as ‘‘2009–0048’’ instead of 

‘‘2009–0042.’’ This change is consistent 

with the intent of the proposals in the 

NPRM and will not increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD does not apply to 

certain serial-numbered Model AB139 

and AW139 helicopters, whereas this 

AD applies to all serial-numbered 

Model AB139 and AW139 helicopters. 

Related Service Information 

Agusta S.p.A. issued Mandatory 

Bollettino Tecnico No. 139–133, Rev. A, 

dated March 17, 2009 (BT), for Model 

AB139 and AW139 helicopters, S/Ns 

31005 up to S/N 31143, except for S/Ns 

31007, 31037, 31038, 31094; S/N 31112; 

S/Ns 31146 up to S/N 31148; S/N 

31155; S/Ns 31201 up to S/N 31218; and 

S/Ns 41001 up to S/N 41022, except S/N 

41007; with a GCU, P/N 1152550–3. 

This BT specifies, within 6 months from 

receipt of the BT, removing GCU, P/N 

1152550–3, modifying electrical 

connector A13P1 and A14P1, and 

replacing each GCU with an airworthy 

GCU, P/N 1152550–4 or 1152550–5, to 

improve electrical power generation and 

distribution system functionalities. 

EASA classified this BT as mandatory 

and issued AD 2009–0042 to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

72 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. We estimate that it will 

take about 4 work-hours to perform the 

required actions of this AD per 

helicopter at an average labor rate of $85 

per work-hour, and required parts will 

cost about $42,384 per helicopter. Based 

on these figures, we estimate the cost to 

be $42,724 per helicopter and the total 

cost impact of the AD for U.S. operators 

to be $3,076,128. 

According to the Agusta service 

information some of the costs of this AD 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by Agusta. Accordingly, we 

have included all costs in our cost 

estimate. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 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 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37781 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this 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. 

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 adding 

the following new airworthiness 

directive (AD): 

2012–12–10 Agusta S.p.A. Helicopters: 

Amendment 39–17090; Docket No. 

FAA–2012–0013; Directorate Identifier 

2010–SW–043–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. (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. This condition 

could result in 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) Effective Date 

This AD becomes effective July 30, 2012. 

(d) 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. 

(e) Required Actions 

(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 No. 1) and A14P1 (GCU No. 2) by 

installing the wiring to the power 

distribution panel (PDP) for your serialnumbered helicopter as depicted in Figure 1 

of Agusta Bollettino Tecnico No. 139–133, 

Rev. 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. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Mark Wiley, 

Aerospace Engineer, FAA, Regulations and 

Policy Group, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5134; fax (817) 222– 

5961; email mark.wiley@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR 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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2009–0042, dated February 25, 2009. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2430, DC generating system. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 10, 2012. 

(i) Agusta Bollettino Tecnico No. 139–133, 

Rev. A, dated March 17, 2009. 

(4) For service information identified in 

this AD, contact Agusta Westland, Customer 

Support & Services, Via Per Tornavento 15, 

21019 Somma Lombardo (VA) Italy, Attn: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(5) You may review a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137 or 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/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on June 8, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–14797 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1412; Directorate 

Identifier 2011–NM–158–AD; Amendment 

39–17088; AD 2012–12–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300 series airplanes. This AD was 

prompted by reports of cracked retract 

actuator fuse pins that can fail earlier 

than the previously determined safe life 

limit of the pins. A fractured retract 

actuator fuse pin can cause the main 

landing gear to extend without 

restriction and attempt to lock into 

position under high dynamic loads. 

This AD requires an inspection for the 

part number of the fuse pin, and 

replacement of the pin if necessary. We 

are issuing this AD to prevent structural 

damage to the side and drag brace lock 

assemblies, which could result in 

landing gear collapse during 

touchdown, rollout, or taxi. 

DATES: This AD is effective July 30, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 30, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 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, 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 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 


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