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

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,


### 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.


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

(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 informationidentified 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 ofAppendix 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.