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(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Installation of Bonding Provisions

At the next scheduled opening of the fuel tanks after the effective date of this AD, but no later than 84 months after the effective date of this AD, install additional and improved bonding provisions in the fuel tanks, and do the applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Fokker Proforma Service Bulletin SBF28–28–058, dated January 9, 2014; and Fokker F28 Appendix Service Bulletin SBF28–28–058/APP01, dated July 15, 2014. (h) Revision of Maintenance or Inspection Program

Before further flight after completing the installation specified in paragraph (g) of this AD, or within 30 days after the effective date of this AD, whichever occurs later: Revise the airplane maintenance or inspection program, as applicable, by incorporating the fuel airworthiness limitation items and critical design configuration control limitations (CDCCLs) specified in paragraph 1.L.(1)(c) of Fokker Proforma Service Bulletin SBF28–28– 058, dated January 9, 2014. The initial compliance times for the tasks are at the latest of the times specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD.

(1) At the applicable time specified in Fokker Service Bulletin SBF28–28–050, Revision 3, dated December 11, 2014.

(2) Before further flight after completing the installation specified in paragraph (g) of this AD.

(3) Within 30 days after the effective date of this AD.

(i) No Alternative Actions, Intervals, and CDCCLs

After accomplishment of the revision required by paragraph (h) of this AD, no alternative actions ( e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD.
(j) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane 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 International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; 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) 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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Fokker B.V. Service’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.

(k) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0108, dated May 8, 2014, for related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–

2015–8467. (l) 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) Fokker F28 Appendix Service Bulletin SBF28–28–058/APP01, dated July 15, 2014.

(ii) Fokker Proforma Service Bulletin SBF28–28–058, dated January 9, 2014.

(iii) Fokker Service Bulletin SBF28–28– 050, Revision 3, dated December 11, 2014.

(3) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280–350; fax +31 (0)88–6280–111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.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 May 20,

2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–12595 Filed 6–16–16; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–8257; Directorate Identifier 2015–NE–36–AD; Amendment 39–**  **18555; AD 2016–12–06]**

**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. MAKILA 2A and MAKILA 2A1 turboshaft engines. This AD requires repetitive diffuser inspections and replacement of those diffusers that fail inspection. This AD was prompted by two occurrences of crack initiation on a ferrule of the diffuser. We are issuing this AD to prevent rupture of the ferrule of the diffuser, which could result in engine fire and damage to the helicopter.

**DATES :**  This AD becomes effective July 22, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 22, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Turbomeca S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 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–
8257. 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– 8257; 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


### 39546 Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations

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 March 11, 2016 (81 FR 12834) (‘‘the NPRM’’). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

Two occurrences of crack initiation were reported on a ferrule of diffuser part number (P/N) 0298210100, which propagated and led to the ferrule rupture. The investigation shows in both cases that the ruptured ferrule contacted and punctured the main fuel supply line, resulting in a fuel leak. This condition, if not detected and corrected, could lead to an engine fire, consequently triggering an uncommanded engine in flight shut down, possibly resulting in an emergency landing. Prompted by these occurrences, Turbomeca published Mandatory Service Bulletin (MSB) No. 298 72 2832 to provide repetitive inspection instructions.

This AD requires repetitive inspections of the affected diffuser and removal of those diffusers that fail the required inspection. 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–2015–8257.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM.

We increased the compliance time for repetitive inspection from 50 hours since last inspection to 300 hours since last inspection. We updated the revision number and date of Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. A298 72 2832 throughout this AD and changed the Credit for Previous Actions paragraph as a result of the MSB change.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

Turbomeca S.A. has issued Alert MSB No. A298 72 2832, Version C, dated April 15, 2016. The Alert MSB describes procedures for repetitive inspections of the affected diffuser and depending on findings, accomplishment of the corrective action(s). Costs of Compliance

We estimate that this AD affects 10 engines installed on helicopters of U.S. registry. We also estimate that it will take about 2 hours per engine to comply with this AD. 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 $1,700. 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):

2016–12–06 Turbomeca S.A.: Amendment 39–18555; Docket No. FAA–2015–8257; Directorate Identifier 2015–NE–36–AD.

(a) Effective Date

This AD becomes effective July 22, 2016.

(b) Affected ADs

None. (c) Applicability

This AD applies to Turbomeca S.A. MAKILA 2A and MAKILA 2A1 turboshaft engine models with a high-pressure gas generator module (M03) that has modification (mod) TU 52 installed.

(d) Reason

This AD was prompted by two occurrences of crack initiation on a ferrule of the diffuser, which propagated and led to the ferrule rupture. We are issuing this AD to prevent rupture of the ferrule of the diffuser, which could result in engine fire and damage to the helicopter.
(e) Actions and Compliance

Comply with this AD within the compliance times specified, unless already done.

(1) Borescope inspect the centrifugal diffuser ferrule, part number 0298210100, prior to the ferrule accumulating 700 hours, time since new or time since replacement or within 30 hours from the effective date of this AD, whichever is later. Use Accomplishment Instructions, paragraphs 2.4.1 through 2.4.2.2.1, of Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. 298 72 2832, Version C, dated April 15, 2016, to do the borescope inspections required by this AD.


### 39547 Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations

(2) Repeat the borescope inspection required by this AD every 300 hours since last inspection.

(3) If any crack, loss of contact between the ferrule and diffuser axial vane, or any contact between the injection manifold supply pipe and the diffuser ferrule is found, remove the diffuser case and replace the ferrule with a part eligible for installation.

(f) Credit for Previous Actions

You may take credit for the actions required by paragraph (e) of this AD if you performed those actions using Turbomeca S.A. MSB No. 298 72 2832, Version B, dated October 12, 2015 or earlier versions, before the effective date of this AD.
(g) 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.

(h) 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.

(2) Refer to MCAI European Aviation Safety Agency AD 2015–0209R1, dated April 20, 2016, 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 it in Docket No.
FAA–2015–8257.
(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) Turbomeca S.A. Alert MSB No. A298 72 2832, Version C, dated April 15, 2016.

(ii) Reserved. (3) For Turbomeca S.A. service information identified in this AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 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/ibrlocations.html. Issued in Burlington, Massachusetts, on June 10, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2016–14234 Filed 6–16–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0027; Directorate Identifier 2010–NM–127–AD; Amendment**  **39–18543; AD 2016–11–16]**

**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 equipped with Rolls-Royce Model RB211-Trent 800 engines. This AD was prompted by reports of thrust reverser (T/R) events related to thermal damage of the T/R inner wall. Depending on the airplane configuration, this AD requires a records review and applicable repetitive inspections, replacements, and installations of the T/R inner wall; and related investigative and corrective actions if necessary. This AD also requires installation of serviceable T/R halves, which would terminate the repetitive actions. This AD also requires revising the inspection or maintenance program by incorporating new airworthiness limitations. We are issuing this AD to detect and correct a degraded T/R inner wall panel. A degraded T/R inner wall panel could lead to failure of the T/R and adjacent components and their consequent separation from the airplane, which could result in a rejected takeoff (RTO) and cause asymmetric thrust and consequent loss of control of the airplane during reverse thrust operation. If a T/R inner wall overheats, separated components could cause structural damage to the airplane, damage to other airplanes, or possible injury to people on the ground.

**DATES :**  This AD is effective July 22,
2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 22, 2016. **ADDRESSES :**  For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206–544–5000, extension 1; fax: 206–766–5680; Internet: https:// www.myboeingfleet.com . You may view this referenced 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2011–
0027. 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–2011– 0027; 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 other information. The address for the Docket Office (phone: 800–647–5527) is Docket 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 :**  Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6501; fax: 425–917–6590; email: kevin.nguyen@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 777–200 and -300series airplanes equipped with RollsRoyce Model RB211-Trent 800 engines. The SNPRM published in the Federal Register on September 25, 2015 (80 FR 57744) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 20, 2011 (76 FR 3561) (‘‘the NPRM’’). The NPRM proposed to require repetitive inspections for degradation of T/R structure and sealant, and related investigative and corrective actions if