61720 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 

(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 part 39 of the Federal 

Aviation Regulations (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) 

2014–14–02], Amendment 39–17896 (79 

FR 39958, July 11, 2014), and adding the 

following new AD: 

2015–20–03 Pratt & Whitney Canada Corp.: 

Amendment 39–18281; Docket No. 

FAA–2013–1059; Directorate Identifier 

2013–NE–36–AD. 

(a) Effective Date 

This AD is effective November 18, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–14–02, 

Amendment 39–17896 (79 FR 39958, July 11, 

2014). 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) PW120, PW121, and PW121A 

turboprop engines with post SB 21610 

configuration; PW124B, PW127, PW127E, 

and PW127F turboprop engines with post SB 

21607 configuration; PW127E and PW127F 

turboprop engines with serial numbers (S/Ns) 

PCE–EB0366 and earlier; PW127G turboprop 

engines with S/Ns PCE–AX0275 and earlier; 

and PW127M turboprop engines with S/Ns 

PCE–ED0810 and earlier. 

(d) Unsafe Condition 

This AD was prompted by reports of fuel 

seepage past the metal-to-metal sealing 

surfaces of the fuel nozzle and fuel manifold 

flow adapter. We are issuing this AD to 

prevent in-flight fuel leakage, engine fire, 

damage to the engine, and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. Within 1,500 flight hours after the 

effective date of this AD, or at the next engine 

shop visit, whichever occurs first: 

(1) Remove the O-ring seal from the fuel 

manifold fitting, 

(2) Remove fuel manifold flow adapter, 

part numbers (P/Ns) 3059754–01, 3059757– 

01, and 3059760–01; and 

(3) Install a fuel nozzle gasket and fuel 

manifold flow adapter that are eligible for 

installation, in accordance with paragraphs 

3.A, 3.B, and 3.C of P&WC SB No. PW100– 

72–21861, dated November 21, 2014. 

(f) Installation Prohibition 

After the effective date of this AD, fuel 

manifold adapter, P/Ns 3059754–01, 

3059757–01, and 3059760–01, and fuel 

manifold gasket, P/N 3079354–01, are not 

eligible for installation in any engine. 

(g) Definition 

For the purpose of this AD, an engine shop 

visit is the induction of an engine into the 

shop for maintenance involving the 

separation of pairs of major mating engine 

flanges. The separation of engine flanges 

solely for the purpose of transportation 

without subsequent engine maintenance does 

not constitute an engine shop visit. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Barbara Caufield, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7146; fax: 781–238– 

7199; email: barbara.caufield@faa.gov. 

(2) Refer to MCAI Transport Canada AD 

CF–2014–41, dated November 26, 2014, for 

related 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–2013– 

1059. 

(j) 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) Pratt & Whitney Canada Corp. Service 

Bulletin (SB) No. PW100–72–21861, dated 

November 21, 2014. 

(ii) Reserved. 

(3) For Pratt & Whitney Canada Corp. 

service information identified in this AD, 

contact Pratt & Whitney Canada Corp., 1000 

Marie-Victorin Blvd., Longueuil, Quebec, 

Canada, J4G 1A1; phone: 800–268–8000; fax: 

450–647–2888; Web site: www.pwc.ca. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 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 

September 22, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25718 Filed 10–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0808; Directorate 

Identifier 2008–NE–18–AD; Amendment 39– 

18288; AD 2015–20–09] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directives (AD) 2001–18– 

06 and AD 2008–22–16, for all General 

Electric Company (GE) CT58 turboshaft 

engines. AD 2001–18–06 and AD 2008– 

22–16 required recalculating the lives of 

life-limited rotating parts using a 

repetitive heavy-lift (RHL) multiplying 

factor and removal from service of parts 

that exceed the recalculated cyclic or 

hourly life limit. This new AD would 

consolidate AD 2001–18–06 and AD 

2008–22–16, and further reduce the life 

capability of certain parts. This AD was 

prompted by recalculation of life for 

parts installed on engines used in 

Utility operations, and a reduced life for 

compressor spools in all operations. We 

are issuing this AD to prevent failure of 

life-limited rotating parts, uncontained 

part release, damage to the engine, and 

damage to the aircraft. 

DATES: This AD is effective November 

18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 18, 2015. 

ADDRESSES: For service information 

identified in this proposed AD, contact 

General Electric Company, GE Aviation, 

Room 285, One Neumann Way, 

Cincinnati, OH, 45215; phone: 513– 

552–3272; email: 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 61721 

aviation.fleetsupport@ge.com. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

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–2008– 

0808; 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 

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: 

Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7120; fax: 781–238–7199; email: 

chris.mcguire@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2001–18–06, 

Amendment 39–12432 (66 FR 47575, 

September 13, 2001, (‘‘AD 2001–18– 

06’’) and AD 2008–22–16, Amendment 

39–15712 (73 FR 63629, October 27, 

2008, (‘‘AD 2008–22–16’’). AD 2001–18– 

06 and AD 2008–22–16 applied to 

certain GE CT58 turboshaft engines. The 

NPRM published in the Federal 

Register on May 1, 2015 (80 FR 24852). 

The NPRM was prompted by GE 

updating the life limits of compressor 

spools. GE also updated the calculation 

method for the life consumption of 

compressor spools and of life-limited 

rotating parts flown in Utility 

operations. This update resulted in 

generally reduced lives for compressor 

spools and all other life-limited parts 

used in Utility operations. The NPRM 

proposed to consolidate AD 2001–18–06 

and AD 2008–22–16, and further reduce 

the life capability of certain parts. We 

are issuing this AD to prevent failure of 

life-limited rotating parts, uncontained 

part release, damage to the engine, and 

damage to the aircraft. 

Related Service Information Under 1 

CFR Part 51 

We reviewed GE CT58 Alert Service 

Bulletin (ASB) No. SB 72–A0162, 

Revision 16, dated January 7, 2015. The 

service information describes 

procedures for calculating life limits for 

the affected life-limited rotating parts. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or see ADDRESSES for 

other ways to access this service 

information. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request New Method for Determining 

Reduced Life Limits 

AAR Airlift Group (AAR) requested 

replacement of the current method for 

determining reduced life limits because 

current limits do not agree with 

operators field experience. AAR 

independent testing revealed that 

expired critical rotating parts showed no 

fatigue cracks. 

We disagree. FAA-approved life limits 

for rotating parts are specified to 

prevent fatigue crack initiation, using 

conservative analytical margins. The 

number of parts that AAR had inspected 

would not be sufficient to show a 

likelihood of part cracking consistent 

with FAA regulatory guidelines for 

rotating part life limits. We did not 

change this AD. 

Request Reassessment of Cost Impact 

AAR disagrees that the NPRM has 

minimal impact on their company. AAR 

stated that their cost per flight would 

increase and company revenue would 

be reduced. 

We agree that this AD will impose an 

economic impact to operators. How an 

operator absorbs or passes on the cost is 

left to the operator to determine. We did 

not change this AD. 

Clarification Requirements 

Since we issued the proposed AD, we 

discovered that ASB formatting 

discrepancies exist due to 

documentation changes implemented by 

GE. We changed paragraphs (e)(2), 

(e)(3), and (e)(4) to reflect the correct SB 

paragraph numbers. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 60 engines installed on aircraft of 

U.S. registry. The average pro-rated cost 

of the life-limited rotating parts is 

$20,000. 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 $8,715,000. 

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 have 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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, 


tkelley on DSK3SPTVN1PROD with RULES
61722 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 

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: 

■ a. Removing airworthiness directives 

(AD) 2001–18–06, Amendment 39– 

12432 (66 FR 47575, September 13, 

2001) (‘‘AD 2001–18–06’’); and AD 

2008–22–16, Amendment 39–15712 (73 

FR 63629, October 27, 2008) (‘‘AD 

2008–22–16’’), and 

■ b. Adding the following new AD: 

2015–20–09 General Electric Company: 

Amendment 39–18288; Docket No. 

FAA–2008–0808; Directorate Identifier 

2008–NE–18–AD. 

(a) Effective Date 

This AD is effective November 18, 2015. 

(b) Affected ADs 

This AD replaces AD 2001–18–06 and AD 

2008–22–16. 

(c) Applicability 

This AD applies to all General Electric 

Company (GE) CT58–100–2, CT58–110–1, 

CT58–110–2, CT58–140–1, and CT58–140–2 

turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by recalculation of 

life for parts installed on engines used in 

Utility operations, and a reduced life for 

compressor spools in all operations. We are 

issuing this AD to prevent failure of lifelimited rotating parts, uncontained part 

release, damage to the engine, and damage to 

the aircraft. 

(e) Compliance 

Do the actions required by this AD, unless 

already done. 

(1) Calculating Cyclic Life Consumption 

Re-calculate the cycles-since-new for all 

compressor spools, and for life-limited 

rotating parts other than compressor spools 

used in Utility operations. Use paragraphs 

3.A.(1) and 3.B.(1) in the Accomplishment 

Instructions of GE CT58 Alert Service 

Bulletin (ASB) No. SB 72–A0162, Revision 

16, dated January 7, 2015, to perform the 

calculations. 

(2) Removal of Compressor Spools 

After the effective date of this AD, remove 

compressor spools, part numbers (P/Ns) 

5124T94G02, 6010T57G04, 6010T57G07, and 

6010T57G08 from service, before reaching 

the life limits specified in paragraph 4.A., 

Appendix A, in GE CT58 ASB No. SB 72– 

A0162, Revision 16, dated January 7, 2015, 

as re-calculated per paragraph (e)(1) of this 

AD. 

(3) Removal of Rotating Parts Used in Utility 

Operations Other Than Compressor Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part 

used in Utility operations, other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD, that exceeds its 

life limit as re-calculated per paragraph (e)(1) 

of this AD. Use Tables I, II, III, and IV in 

paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE CT58 

ASB No. SB 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.D., 

Appendix A of this GE CT58 ASB, to 

determine when to remove these parts. 

(4) Removal of Rotating Parts Not Used in 

Utility Operations Other Than Compressor 

Spools 

After the effective date of this AD, remove 

from service any life-limited rotating part not 

used in Utility operations, other than the 

compressor spools with P/Ns listed in 

paragraph (e)(2) of this AD, that exceeds its 

life limit. Use Tables I, II, III, and IV in 

paragraphs 3.D. through 3.G. in the 

Accomplishment Instructions in GE CT58 

ASB No. SB 72–A0162, Revision 16, dated 

January 7, 2015, and paragraph 4.C., 

Appendix A of this GE CT58 ASB, to 

determine when to remove these parts. 

(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 

For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7120; fax: 781–238– 

7199; email: chris.mcguire@faa.gov. 

(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) General Electric Company (GE) CT58 

Alert Service Bulletin No. SB 72–A0162, 

Revision 16, dated January 7, 2015. 

(ii) Reserved. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, One 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, 12 

New England Executive Park, 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 

September 30, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25719 Filed 10–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3224; Directorate 

Identifier 2015–CE–026–AD; Amendment 

39–18290; AD 2015–20–11] 

RIN 2120–AA64 

Airworthiness Directives; SchemppHirth Flugzeugbau GmbH Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Schempp-Hirth Flugzeugbau GmbH 

Models Duo Discus and Duo Discus T 

powered sailplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as excessive load on the air 

brake system. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective November 

18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 18, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3224; or in person at 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 service information identified in 

this AD, contact Schempp-Hirth 

Flugzeugbau GmbH, Krebenstrasse 25, 

73230 Kirchheim/Teck, Germany; 

telephone: +49 7021 7298–0; fax: +49 

7021 7298–199; email: info@schempphirth.com; Internet: http:// 


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