19024 Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations 

(2) Strip coating, inspect, and recoat the 

teeth of the rotating CDP seal, P/N 

1669M73P02. Use paragraph 3.C.(2) of GE 

Service Bulletin (SB) CF6–80E1 S/B 72–0529, 

Revision 01, dated August 21, 2015 to do the 

strip coating, inspecting, and recoating, as 

follows: 

(i) For engines that have had stationary 

CDP seal, P/N 1347M28G02, replaced or 

stationary CDP seal honeycomb repaired; 

strip coating, inspect, and recoat the teeth of 

the rotating CDP seal at the next engine shop 

visit. 

(ii) For engines that have not had 

stationary CDP seal, P/N 1347M28G02, 

replaced or stationary CDP seal honeycomb 

repaired; strip coating, inspect, and recoat 

the teeth of the rotating CDP seal at the next 

part exposure of the rotating CDP seal. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any rotating CDP seal, P/N 

1669M73P02, that has not had its seal teeth 

recoated using procedures specified in ESM 

72–31–10, REPAIR 002 of GE CF6–80E1 

(GEK99376) Engine Manual, Revision 42, 

dated March 15, 2014, into any engine. 

(g) Definitions 

(1) For the purpose of this AD, exposure of 

the rotating CDP seal is defined as removal 

of the compressor rear frame from the highpressure compressor (HPC) module. 

(2) For the purpose of this AD, an engine 

shop visit is defined as the induction of an 

engine into the shop for maintenance 

involving the separation of any major mating 

engine flanges, except that the separation of 

engine flanges solely for the following 

purposes is not considered a shop visit: 

(i) Transportation without subsequent 

engine maintenance. 

(ii) Removing the turbine rear frame (TRF) 

for repair of TRF cracking. 

(iii) Removing the top or bottom HPC case, 

or both, for HPC airfoil maintenance. 

(iv) Removing only the accessory gearbox 

and/or transfer gearbox. 

(v) Replacing the high-pressure turbine 

(HPT) stage 1 blades per CF6–80E1 SB 72– 

0504 ‘‘Quick-Turn Workscope Procedure to 

Replace CF6–80E1 Stage 1 HPT Blades’’. 

(3) For the purpose of this AD, a stationary 

CDP seal is replaced if at any previous shop 

visit, the seal has been removed and a 

different seal is installed. 

(h) Credit for Previous Action 

You may take credit for the actions that are 

required by paragraph (e) of this AD if the 

actions were performed before the effective 

date of this AD using the procedures in ESM 

72–31–10, REPAIR 002 of the GE CF6–80E1 

(GEK99376) Engine Manual, Revision 42, 

dated March 15, 2014, or earlier versions. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Herman Mak, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7147; fax: 781–238–7199; email: 

herman.mak@faa.gov. 

(k) 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) General Electric Company Service 

Bulletin CF6–80E1 S/B 72–0529, Revision 01, 

dated August 21, 2015. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(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 

March 16, 2016. 

Ann C. Mollica, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07377 Filed 4–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5193; Directorate 

Identifier 2015–NE–35–AD; Amendment 39– 

18464; AD 2016–07–19] 

RIN 2120–AA64 

Airworthiness Directives; Technify 

Motors GmbH Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Technify Motors GmbH (type certificate 

previously held by Thielert Aircraft 

Engines GmbH) TAE 125–02–99 and 

TAE 125–02–114 reciprocating engines. 

This AD requires removal of affected 

fuel feed pumps. This AD was prompted 

by reports of in-flight shutdowns on 

TAE 125–02 engines. We are issuing 

this AD to prevent failure of the fuel 

feed pump, damage to the engine, and 

damage to the airplane. 

DATES: This AD becomes effective May 

9, 2016. 

ADDRESSES: For service information 

identified in this AD, contact Technify 

Motors GmbH, Platanenstrasse 14, D– 

09356 Sankt Egidien, Germany; phone: 

+49–37204–696–0; fax: +49–37204– 

696–2912; email: support@

continentaldiesel.de. 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– 

5193. 

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– 

5193; 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: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@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 January 4, 2016 (81 FR 27). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

In-flight shut down occurrences have been 

reported on aeroplanes equipped with TAE 

125–02 engines. The initial results of the 

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Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations 19025 

investigations showed that a defective fuel 

feed pump was the probable cause of the 

engine failure. 

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– 

5193. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 27, January 4, 2016). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information 

Technify Motors GmbH has issued 

Operation & Maintenance Manual, CD– 

135/CD–155, OM–02–02, Issue 4, 

Revision No. 5, dated September 18, 

2015. The service information describes 

procedures for removing and replacing 

the fuel feed pump. 

Costs of Compliance 

We estimate that this AD affects 190 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 0.5 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Pro-rated cost of 

the life limit reduction is about $160 per 

part. Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $38,475. 

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): 

2016–07–19 Technify Motors GmbH (Type 

Certificate previously held by Thielert 

Aircraft Engines GmbH): Amendment 

39–18464; Docket No. FAA–2015–5193; 

Directorate Identifier 2015–NE–35–AD. 

(a) Effective Date 

This AD becomes effective May 9, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Technify Motors 

GmbH TAE 125–02–99 and TAE 125–02–114 

reciprocating engines with a fuel feed pump, 

part number (P/N) 05–7312–K0073xx, or P/ 

N 05–7312–K0133xx, where ‘‘xx’’ can be any 

number, installed. 

(d) Reason 

This AD was prompted by reports of inflight shutdowns on TAE 125–02 engines. We 

are issuing this AD to prevent failure of the 

fuel feed pump, damage to the engine, and 

damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. Remove from service each affected fuel 

feed pump before it exceeds 600 operating 

hours (OH) time in service (TIS) or within 

110 OH after the effective date of this AD, 

whichever occurs later. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install onto any engine, any fuel feed pump, 

P/N 05–7312–K0073xx or P/N 05–7312– 

K0133xx, where ‘‘xx’’ can be any number, if 

the fuel feed pump has 600 hours or more 

TIS. If TIS of a fuel feed pump is unknown 

or has exceeded 600 hours TIS, then the fuel 

feed pump is not eligible for installation. 

Rebuilt, overhauled, or repaired fuel feed 

pumps or fuel feed pumps that lack a serial 

number, are not eligible for installation. 

(g) Related Information 

(1) For more information about this AD, 

Philip Haberlen, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & Propeller 

Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7770; fax: 781–238–7199; email: 

philip.haberlen@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0189, dated 

September 21, 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 it in Docket No. FAA–2015–5193. 

(3) For service information identified in 

this AD, contact Technify Motors GmbH, 

Platanenstrasse 14, D–09356 Sankt Egidien, 

Germany; phone: +49–37204–696–0; fax: 

+49–37204–696–2912; email: support@

continentaldiesel.de. 

(4) 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. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

March 25, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–07376 Filed 4–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

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