Federal Register / Vol. 81, No. 26 / Tuesday, February 9, 2016 / Rules and Regulations 6753 

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 

removing Airworthiness Directive (AD) 

2014–13–01, Amendment 39–17875 (79 

FR 36635, June 30, 2014), and adding 

the following new AD: 

2016–03–05 Airbus Helicopters 

Deutschland GmbH: Amendment 39– 

18392; Docket No. FAA–2016–2843; 

Directorate Identifier 2015–SW–003–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 C– 

2 and MBB–BK 117 D–2 helicopters with a 

Goodrich hoist damper unit, part number (P/ 

N) 44307–480, 44307–480–1, or 44307–480– 

2 installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

uncommanded detachment of the external 

hoist damper unit, which could result in loss 

of an external load or person from the 

helicopter hoist, resulting in injury to 

persons being lifted by the hoist. 

(c) Affected ADs 

This AD supersedes AD 2014–13–01, 

Amendment 39–17875 (79 FR 36635, June 

30, 2014). 

(d) Effective Date 

This AD becomes effective February 24, 

2016. 

(e) 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. 

(f) Required Actions 

Before the next hoist operation, comply 

with paragraph (f)(1), (f)(2), or (f)(3) of this 

AD: 

(1) Replace the split retainers and reidentify each hoist damper unit in 

accordance with the Accomplishment 

Instructions, paragraph 3.B.1, of Airbus 

Helicopters Emergency Alert Service Bulletin 

(ASB) No. ASB MBB–BK117 C–2–85A–041, 

Revision 4, dated February 12, 2015, or 

Emergency ASB No. ASB MBB–BK117 D–2– 

85A–002, Revision 1, dated February 12, 

2015, as applicable to your model helicopter; 

or 

(2) Replace each hoist damper unit with a 

unit that has been repaired as required by 

paragraph (f)(1) of this AD; or 

(3) Deactivate the rescue hoist system. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: David N. 

Hatfield, Aviation Safety Engineer, Safety 

Management 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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2015–0019R1, dated February 13, 2015. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2016– 

2843. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2500, Cabin Equipment/Furnishings. 

(j) 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) Airbus Helicopters Emergency Alert 

Service Bulletin (ASB) No. ASB MBB–BK117 

C–2–85A–041, Revision 4, dated February 12, 

2015. 

(ii) Airbus Helicopters Emergency ASB No. 

ASB MBB–BK117 D–2–85A–002, Revision 1, 

dated February 12, 2015. 

(3) For Airbus Helicopters service 

information identified in this final rule, 

contact Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://www.airbus

helicopters.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 29, 

2016. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2016–02233 Filed 2–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3805; Directorate 

Identifier 2015–NE–28–AD; Amendment 39– 

18389; AD 2016–03–02] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Turbomeca S.A. ARRIEL 2C, 2C1, 2C2, 

2S1, and 2S2 turboshaft engines with 

modification TU34 or TU34A installed. 

This AD requires inspecting the torque 

conformation box (TCB) for correct 

resistance values and removing TCBs 

that fail inspection before further flight. 

This AD was prompted by TCB failures. 

We are issuing this AD to prevent 

failure of the TCB, loss of engine thrust 

control, and damage to the helicopter. 

DATES: This AD becomes effective 

March 15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 15, 2016. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 

59 74 45 15. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

3805. 

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– 

3805, or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

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6754 Federal Register / Vol. 81, No. 26 / Tuesday, February 9, 2016 / Rules and Regulations 

except Federal holidays. The AD docket 

contains this AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7772; fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on November 5, 2015 (80 FR 

68475). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several cases of torque conformation box 

(TCB) failures have been reported on engines 

incorporating mod TU34 or mod TU34A. 

Investigation concluded that these failures 

were caused by cracks on soldered joints of 

TCB resistors. 

This condition, if not corrected, could lead 

to limited power availability in a One Engine 

Inoperative (OEI) case, possibly resulting in 

reduced control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 68475, November 5, 2015). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

Turbomeca S.A. has issued 

Mandatory Service Bulletin (MSB) No. 

292 72 2860, Version A, dated July 15, 

2015. The MSB describes procedures for 

checking TCB resistance values. 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 of 

this final rule. 

Costs of Compliance 

We estimate that this AD affects 300 

engines installed on helicopters of U.S. 

registry. We estimate that it would take 

about 1 hour to perform an inspection. 

We also estimate that 20% of these 

engines would fail the inspection and 

require TCB removal, which would take 

about 1 hour. The average labor rate is 

$85 per hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $30,600. 

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 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 this AD: 

(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. 

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): 

2016–03–02 Turbomeca S.A.: Amendment 

39–18389; Docket No. FAA–2015–3805; 

Directorate Identifier 2015–NE–28–AD. 

(a) Effective Date 

This AD becomes effective March 15, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Turbomeca S.A. 

ARRIEL 2C, 2C1, 2C2, 2S1, and 2S2 

turboshaft engines with modification TU34 

or TU34A installed. 

(d) Reason 

This AD was prompted by torque 

conformation box (TCB) failures. We are 

issuing this AD to prevent failure of the TCB, 

loss of engine thrust control, and damage to 

the helicopter. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 600 engine flight hours (EFHs) 

or 6 months after the effective date of this 

AD, whichever occurs first, check the 

resistance values on the TCB. Use 

Accomplishment Instructions, paragraph 

2.3.2 of Turbomeca S.A. Mandatory Service 

Bulletin 292 72 2860, Version A, dated July 

15, 2015, to do the inspection. Repeat this 

inspection every 600 EFHs since last 

inspection. 

(2) Remove before further flight any TCB 

that fails the inspection required by 

paragraph (e)(1) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7772; fax: 781–238–7199; email: 

brian.kierstead@faa.gov. 

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Federal Register / Vol. 81, No. 26 / Tuesday, February 9, 2016 / Rules and Regulations 6755 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0177, dated August 

25, 2015, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–3805. 

(h) 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) Turbomeca S.A. Mandatory Service 

Bulletin No. 292 72 2860, Version A, dated 

July 15, 2015. 

(ii) Reserved. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; fax: 33 (0)5 59 74 45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may 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/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

February 2, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–02477 Filed 2–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3778; Directorate 

Identifier 2015–NE–27–AD; Amendment 39– 

18391; AD 2016–03–04] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211–535E4–37, 

RB211–535E4–B–37, and RB211– 

535E4–C–37 turbofan engines. This AD 

requires recalculating the cyclic life for 

certain engine life-limited rotating parts 

and removing those parts that have 

exceeded their cyclic life limit within 

specified compliance times. This AD 

was prompted by a review of 

operational data that determined certain 

RR RB211–535E4–37 engines have been 

operated to a more severe flight profile 

than is consistent with the flight profile 

used to establish the cyclic life limits for 

the rotating parts. We are issuing this 

AD to prevent failure of life-limited 

rotating parts, uncontained parts 

release, damage to the engine, and 

damage to the airplane. 

DATES: This AD becomes effective 

March 15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 15, 2016. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE24 8BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http://

www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://

customers.rolls-royce.com/public/

rollsroycecare. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

3778. 

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– 

3778; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on November 4, 2015 (80 FR 

68284). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A review of operational flight data has 

revealed that some RB211–535 engines may 

have been operated beyond the flight profile 

(FP) assumed by the operator when 

establishing the operational limits (life 

limits) within which the corresponding 

critical parts are allowed to remain installed. 

This condition, if not corrected, may lead 

to critical part failure, possibly resulting in 

release of high energy debris, damage to the 

aeroplane and/or injury to the occupants. 

To preclude failure of an engine lifelimited part, the MCAI specifies, and 

this AD would require, recalculating the 

cyclic life for certain parts and removing 

from service those parts that have 

exceeded their cyclic life limit within 

specified compliance times. This AD 

would establish a new default Flight 

Profile G for RR RB211–535E4–37 

engine life-limited parts. If, however, 

operators meet the requirements of 

Appendix 6 of RR Alert NonModification Service Bulletin (NMSB) 

No. RB.211–72–AH972, Revision 3, 

dated August 28, 2015, they may 

operate to Flight Profile A or B. You 

may obtain further information by 

examining the MCAI in the AD docket 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3778. 

Related Service Information Under 1 

CFR Part 51 

We reviewed RR Alert NMSB No. 

RB.211–72–AH972, Revision 3, dated 

August 28, 2015. The Alert NMSB 

describes a new flight profile, provides 

procedures for the consumed cyclic life 

corrections for prior operation of 

affected parts, and provides the removal 

from service recommendations for parts 

that have exceeded their cyclic life 

limit. 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 of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

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