Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39545 

(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 


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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. 


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

(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 -300 

series 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 


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