3306 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

(2) For Model BD–700–1A10 airplanes, 

serial numbers 9381 and 9432 through 9476 

inclusive: Bombardier Service Bulletin 700– 

52–6007, dated March 29, 2012. 

(3) For Model BD–700–1A11 airplanes, 

serial numbers 9127 through 9383 inclusive, 

9389 through 9400 inclusive, 9404 through 

9431 inclusive, and 9998: Bombardier 

Service Bulletin 700–1A11–52–019, dated 

March 29, 2012. 

(4) For Model BD–700–1A11 airplanes, 

serial numbers 9386, 9401, and 9445 through 

9474 inclusive: Bombardier Service Bulletin 

700–52–5007, dated March 29, 2012. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–25, dated 

August 21, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0081-0002. 

(j) 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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 700–1A11– 

52–019, dated March 29, 2012. 

(ii) Bombardier Service Bulletin 700–52– 

042, dated March 29, 2012. 

(iii) Bombardier Service Bulletin 700–52– 

5007, dated March 29, 2012. 

(iv) Bombardier Service Bulletin 700–52– 

6007, dated March 29, 2012. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this 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. 

(5) You may view this service information 

that is incorporated by reference 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 Renton, Washington, on 

December 31, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00371 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0669; Directorate 

Identifier 2013–SW–038–AD; Amendment 

39–18373; AD 2016–01–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (AHD) 

(previously Eurocopter Deutschland 

GmbH) Model MBB–BK 117 A–1, A–3, 

A–4, B–1, B–2, C–1, and C–2 

helicopters. This AD requires an initial 

and recurring inspection of the N2 

control arm and, depending on the 

outcome of the inspection, repairing or 

replacing the N2 control arm. This AD 

was prompted by a report of a heavily 

corroded and broken N2 control arm. 

The actions of this AD are intended to 

detect corrosion, a crack, or a scratch in 

the N2 control arm, which could lead to 

failure of the N2 control arm, a drop in 

rotor speed, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 25, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, Texas 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2015–0669 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, the European 

Aviation Safety Agency (EASA) 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: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 24, 2015, at 80 FR 15530, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to AHD Model MBB–BK 117 A–1, A–3, 

A–4, B–1, B–2, C–1, and C–2 

helicopters. The NPRM proposed to 

require repetitive visual inspections of 

the N2 control arm for corrosion, a 

crack, and a scratch. The NPRM also 

proposed to require repairing any N2 

control arm with corrosion or a scratch 

less than 0.020 inch in depth and 

replacing any N2 control arm with 

exfoliation corrosion, a crack, or with 

corrosion or a scratch 0.020 inch or 

greater in depth. The proposed 

requirements were intended to detect 

corrosion, a crack, or a scratch in the N2 

control arm, which could lead to failure 

of the N2 control arm, a drop in rotor 


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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3307 

speed, and subsequent loss of control of 

the helicopter. 

The NPRM was prompted by AD No. 

2013–0154, dated July 22, 2013, issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for the Eurocopter Deutschland GmbH 

(now AHD) Model MBB–BK117 A–1, A– 

3, A–4, B–1, B–2, C–1, and C–2 

helicopters. EASA advises of an 

incident with a Model MBB–BK117 C– 

2 helicopter that dropped rotor speed 

(RPM) within the green range and could 

not be recovered to nominal value 

because of a heavily corroded and 

broken N2 control arm. EASA advises 

that under certain flight conditions and 

power demands, a broken N2 control 

arm can cause a significant and nonrecoverable drop in RPM. As a result, 

EASA AD No. 2013–0154 requires an 

initial and repetitive inspection of the 

N2 control arm for corrosion, damage, 

and scratches, and depending on the 

outcome of the inspection, repairing or 

replacing the N2 control arm. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

alternative method of compliance for a 

helicopter of foreign design. We have 

revised the contact information 

throughout this final rule to reflect the 

new address and new email address. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (80 FR 15530, March 24, 2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, 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 EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except for the minor editorial 

changes described above. These changes 

are consistent with the intent of the 

proposals in the NPRM (80 FR 15530, 

March 24, 2015) and will not increase 

the economic burden on any operator 

nor increase the scope of this AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD allows a 

noncumulative tolerance of 3 months in 

the compliance time for the initial 

inspection on helicopters with less than 

2 years from the date of first flight and 

for the repetitive inspections, and this 

AD does not. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter issued ASB MBB–BK117– 

60A–126 for Model MBB–BK 117 A–1, 

A–3, A–4, B–1, B–2, and C–1 

helicopters, and ASB MBB–BK117 C–2– 

76A–005 for Model MBB–BK 117 C–2 

helicopters, both Revision 0, and both 

dated June 24, 2013. The Eurocopter 

ASBs specify inspecting the N2 control 

arm for corrosion, damage, and 

scratches and, depending on the 

outcome of the inspection, either 

repairing or replacing the affected parts. 

The Eurocopter ASBs also specify 

performing the inspection with each 12 

month inspection until the N2 

inspection requirements are 

incorporated into the aircraft 

maintenance manual. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 441 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

Labor costs are estimated at $85 per 

work-hour. Inspecting the N2 control 

arm requires about one work-hour for an 

estimated cost of $85 per helicopter and 

$37,485 for the U.S. fleet per inspection 

cycle. Repairing the N2 control arm 

requires about four work-hours for an 

estimated labor cost of $340. Replacing 

the N2 control arm requires about three 

work-hours for an estimated labor cost 

of $255. Parts to replace the N2 control 

arm for Model MBB–BK 117 A–1, A–3, 

A–4, B–1, B–2, and C–1 helicopters cost 

about $2,743 for a total estimated cost 

of $2,998. Parts to replace the N2 

control arm for a Model MBB–BK 117 

C–2 helicopter cost about $4,500 for a 

total estimated cost of $4,755. 

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 

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): 

2016–01–14 Airbus Helicopters 

Deutschland GmbH (AHD) (Previously 


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3308 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

Eurocopter Deutschland GmbH):

Amendment 39–18373; Docket No. 

FAA–2015–0669; Directorate Identifier 

2013–SW–038–AD. 

(a) Applicability 

This AD applies to AHD Model MBB–BK 

117 A–1, A–3, A–4, B–1, B–2, C–1, and C– 

2 helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion, a crack, or a scratch on an N2 

control arm. This condition could lead to 

failure of the N2 control arm, resulting in a 

reduction in rotor speed and subsequent loss 

of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2016. 

(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 

For helicopters that have not reached 2 

years from the date of first flight, within 1 

year or before reaching 2 years from the date 

of first flight, whichever occurs first; and for 

helicopters that have reached or exceeded 2 

years from the date of first flight, within 50 

hours TIS: 

(1) Visually inspect each N2 control arm 

for corrosion, a crack, and a scratch as 

depicted in Figure 1 of Eurocopter Alert 

Service Bulletin (ASB) MBB–BK117–60A– 

126 or ASB MBB–BK117 C–2–76A–005, both 

Revision 0, and both dated June 24, 2013, as 

applicable to your model helicopter. 

(i) If an N2 control arm has corrosion or a 

scratch less than 0.5 millimeter (mm) (0.020 

inch) in depth, before further flight, remove 

the corrosion and repair the scratch. 

(ii) If an N2 control arm has any exfoliation 

corrosion, a crack, or has corrosion or a 

scratch 0.5 mm (0.020 inch) or greater in 

depth, before further flight, replace the N2 

control arm. 

(2) Thereafter, perform the requirements in 

paragraph (e)(1) of this AD at intervals not to 

exceed 12 months. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-AMOC-Requests@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. 2013–0154, dated July 22, 2013. You may 

view the EASA AD on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2015–0669. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Engine Controls, 7600. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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–BK117–60A–126, Revision 0, dated 

June 24, 2013. 

(ii) Eurocopter ASB MBB–BK117 C–2– 

76A–005, Revision 0, dated June 24, 2013. 

(3) For Eurocopter service information 

identified in this final rule, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone (972) 

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

3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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 Fort Worth, Texas, on January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00658 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1935; Directorate 

Identifier 2014–SW–008–AD; Amendment 

39–18374; AD 2016–01–15] 

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. This AD requires 

visually inspecting certain subfloor 

frames for a crack. This AD was 

prompted by reports of cracks on inservice helicopters. The actions of this 

AD are intended to detect or prevent a 

crack in the subfloor frame, which could 

result in failure of the pilot and co-pilot 

pedal support frame and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 25, 2016. 

ADDRESSES: For service information 

identified in this rule, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: 

Maurizio D’Angelo; telephone 39–0331– 

664757; fax 39–0331–664680; or at 

http://www.agustawestland.com/

technical-bulletins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1935 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, the European Aviation 

Safety Agency (EASA) 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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5110; email robert.grant@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 5, 2015, at 80 FR 32072, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 


jstallworth on DSK7TPTVN1PROD with RULES