Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations 37171 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–15057 (72 FR 

27953, May 18, 2007), and adding the 

following new AD: 

2014–13–05 British Aerospace Regional 

Aircraft: Amendment 39–17880; Docket 

No. FAA–2014–0241; Directorate 

Identifier 2014–CE–008–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 5, 2014. 

(b) Affected ADs 

This AD supersedes AD 2007–10–16, 

Amendment 39–15057 (72 FR 27953, May 18, 

2007). 

(c) Applicability 

This AD applies to British Aerospace 

Regional Aircraft Jetstream Model 3201 

airplanes, all serial numbers, certificated in 

any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 5: Time Limits. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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 the need to 

incorporate revisions to the Airworthiness 

Limitations section of the Instructions for 

Continued Airworthiness (ICA). We are 

issuing this AD to enforce compliance with 

these requirements in order to maintain 

airworthiness. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) and (f)(2) of this AD: 

(1) As of August 5, 2014 (the effective date 

of this AD), replace each component before 

exceeding the applicable life limit and 

complete all applicable maintenance tasks 

within the thresholds and intervals as 

specified in Chapter 05–10–05, 

Airworthiness Limitations, of the British 

Aerospace Jetstream 3200 Series Aircraft 

Maintenance Manual, Revision, 29, dated 

December 15, 2012. 

(2) You may comply with the requirements 

in paragraph (f)(1) of this AD by 

incorporating British Aerospace Jetstream 

3200 Series Aircraft Maintenance Manual, 

Revision 29, Airworthiness Limitations, 

Chapter 05–10–05, dated December 15, 2012, 

into the Airworthiness Limitations section of 

your ICA and complying with that program. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4138; fax: (816) 329– 

4090; email: taylor.martin@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to European Aviation Safety Agency 

(EASA) AD No.: 2014–0044, dated February 

24, 2014. You may examine the MCAI on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0241-0002. 

(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) Chapter 05–10–05, Airworthiness 

Limitations, of the British Aerospace 

Jetstream 3200 Series Aircraft Maintenance 

Manual, Revision, 29, dated December 15, 

2012. 

(ii) Reserved. 

(3) For British Aerospace Regional Aircraft 

service information identified in this AD, 

contact BAE Systems (Operations) Limited, 

Customer Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone: +44 

1292 675207; fax: +44 1292 675704; email: 

RApublications@baesystems.com; Internet: 

http://www.baesystems.com/Businesses/

RegionalAircraft/. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on June 

20, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–15136 Filed 6–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1009; Directorate 

Identifier 2013–NE–35–AD; Amendment 39– 

17855; AD 2014–11–05] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboprop 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Pratt & Whitney Canada Corp. (P&WC) 

turboprop engines. This AD requires 

installing a reinforcement liner to the 

power turbine (PT) containment ring 

and, for certain PT containment rings, 

adding scallops. This AD was prompted 

by in-service events involving the 

perforation of engine cases as a result of 

the liberation of PT blades and the 

fracture/displacement of the PT 

containment ring. We are issuing this 

AD to prevent uncontained engine 

failure and damage to the airplane. 

DATES: This AD becomes effective 

August 5, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 5, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, 

J4G 1A1; phone: 800–268–8000; fax: 

450–647–2888; Internet: www.pwc.ca. 

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–2013– 

1009; 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. 


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37172 Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations 

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, 12 New England 

Executive Park, 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 January 7, 2014 (79 FR 763). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

There have been in-service events 

involving the perforation of PT6A small 

series engine cases as a result of the loss of 

integrity of Power Turbine (PT) Containment 

Rings under failure loads. Perforation of 

engine cases has been seen to result from the 

liberation of PT blades and from fracture/

displacement of the PT Containment Ring 

itself. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Add Engine Models to the 

List of Applicable Engines 

Friend Aircare requested that we add 

the engine models listed in P&WC 

Service Bulletin (SB) No. 12076, 

Revision 3, dated January 17, 1992, to 

the applicability of this AD because that 

SB requires the same modification to the 

PT containment ring assembly. 

We agree. We revised paragraph (c) of 

this AD by adding certain serial 

numbers of the following P&WC engine 

models: PT6A–11, PT6A–11AG, PT6A– 

15AG, PT6A–110, PT6A–112, and 

PT6A–121. We revised paragraph (e) of 

this AD to specify use of either P&WC 

SB No. 12076, Revision 3, dated January 

17, 1992; or P&WC SB No. PT6A–72– 

A1427, Revision 3, dated January 27, 

2012, as applicable. We revised 

paragraph (f) of this AD by adding credit 

for corrective actions taken in 

accordance with P&WC SB No. 12076, 

Revision 2, dated April 24, 1991, or 

earlier versions. 

Request To Exclude Engines Used on 

Single-Engine Aircraft 

Reabe Spraying Services, Inc. 

requested that we exclude from 

applicability engines used on singleengine aircraft, or aircraft where the 

engine has nothing alongside of it that 

would sustain damage from release of 

debris. 

We disagree. We consider the 

uncontained release of engine hardware 

to be an unsafe condition. We did not 

change this AD. 

Request To Withdraw the NPRM 

Dynamic Aviation requested that the 

FAA withdraw the NPRM (79 FR 763, 

January 7, 2014). Dynamic Aviation has 

not experienced any PT disk blade 

failure in 16 years and 800,000 flight 

hours. 

We disagree. There have been inservice events involving the perforation 

of PT6A series engine cases as a result 

of the loss of integrity of the PT 

containment rings under failure loads. 

Perforation of engine cases has been 

seen to result from the liberation of PT 

blades and from fracture/displacement 

of the PT containment ring itself. We 

consider the release of engine hardware 

to be an unsafe condition. This AD 

requires the incorporation of P&WC SB 

No. 12076, Revision 3, dated January 17, 

1992, or P&WC SB No. PT6A–72– 

A1427, Revision 3, dated January 27, 

2012, as applicable, to prevent 

uncontained events. We did not change 

this AD. 

Requests To Extend the Period of 

Compliance 

Dynamic Aviation requested that we 

change the compliance time from within 

24 months after the effective date of this 

AD, to within 36 to 48 months after the 

effective date of this AD. Dynamic 

Aviation said the extended compliance 

period would better allow the complete 

modification of all engines. 

Ameriflight LLC requested that we 

reconsider the period of compliance to 

allow a longer, more realistic timeframe 

for compliance. 

We agree. The compliance period can 

be increased without an appreciable risk 

effect. We revised paragraph (e)(2) of 

this AD to read, ‘‘Within 48 months 

after the effective date of this AD, 

modify the existing PT containment 

ring.’’ 

Request To More Accurately Estimate 

the Time Required To Modify an Engine 

Several entities requested that the 

estimated time and costs of compliance 

for completing the requirements of this 

AD more accurately reflect the actual 

time required to modify an engine. 

We agree. In the NPRM (79 FR 763, 

January 7, 2014), we based our estimate 

of 3 hours to modify an engine on 

original equipment manufacturer 

service information. Further analysis 

indicates this estimate is inadequate. 

We increased the estimated hours 

required to modify an engine from 3 

hours to 20 hours. 

Conclusion 

We reviewed the available data, 

including the comments received, 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. 

Costs of Compliance 

We estimate that this AD affects 1,000 

engines installed on airplanes of U.S. 

registry. We estimate that it will take 

about 20 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Required parts cost about 

$1,655 per engine. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $3,355,000. 

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 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 


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Federal Register / Vol. 79, No. 126 / Tuesday, July 1, 2014 / Rules and Regulations 37173 

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): 

2014–11–05 Pratt & Whitney Canada Corp.: 

Amendment 39–17855; Docket No. 

FAA–2013–1009; Directorate Identifier 

2013–NE–35–AD. 

(a) Effective Date 

This AD becomes effective August 5, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) turboprop engines as follows: 

all model PT6A–20, PT6A–20A, PT6A–20B, 

PT6A–25, PT6A–28, PT6A–34B, PT6A–36, 

and PT6A–135 engines; model PT6A–11 

engines, serial number (S/N) PC–E10539 and 

earlier; PT6A–11AG, S/N PC–E10224 and 

earlier; PT6A–15AG engines, S/N earlier than 

PC–E14089; model PT6A–21 engines, S/N 

PCE–25361 and earlier; model PT6A–25A 

engines, S/N PCE–48757 and earlier; model 

PT6A–25C engines, S/N PCE–26258 and 

earlier; model PT6A–27 engines, S/N PCE– 

42523 and earlier as well as all engines 

converted to PT6A–27; model PT6A–34 

engines, S/N PCE–57303 and earlier as well 

as all engines converted to PT6A–34; model 

PT6A–34AG engines, S/N PCE–57312 and 

earlier as well as all engines converted to 

PT6A–34AG; model PT6A–110 engines, S/N 

PC–E15052 and earlier; model PT6A–112 

engines, S/N earlier than PC–E12563; model 

PT6A–114 engines, S/N PCE–17218 and 

earlier; and model PT6A–135A engines, S/N 

PCE–35089 and earlier. 

(d) Reason 

This AD was prompted by in-service 

events involving the perforation of engine 

cases as a result of the liberation of power 

turbine (PT) blades and the fracture/

displacement of the PT containment ring. We 

are issuing this AD to prevent uncontained 

engine failure and damage to the airplane. 

(e) Actions and Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) Within 48 months after the effective 

date of this AD, modify the existing PT 

containment ring. Use paragraph 2, 

Accomplishment Instructions, of P&WC 

Service Bulletin (SB) No. 12076, Revision 3, 

dated January 17, 1992, or paragraph 3, 

Accomplishment Instructions, P&WC SB No. 

PT6A–72–A1427, Revision 3, dated January 

27, 2012, as applicable, to make the 

modification. 

(f) Credit for Previous Actions 

If you modified the PT containment ring 

before the effective date of this AD using 

P&WC SB No. 12076, Revision 2, dated April 

24, 1991, or earlier versions, or P&WC SB No. 

PT6A–72–A1427, Revision 2, dated April 3, 

1990, or earlier versions, you have met the 

requirements of this AD. 

(g) 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. 

(h) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7754; fax: (781) 238–7199; 

email: robert.green@faa.gov. 

(2) Refer to MCAI Transport Canada Civil 

Aviation AD CF–2013–33R1, dated 

November 14, 2013, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1009-0003. 

(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) Pratt & Whitney Canada (P&WC) Corp. 

Service Bulletin (SB) No. PT6A–72–A1427, 

Revision 3, dated January 27, 2012. 

(ii) P&WC, Inc. SB No. 12076, Revision 3, 

dated January 17, 1992. 

(3) For P&WC service information 

identified in this AD, contact Pratt & Whitney 

Canada Corp., 1000 Marie-Victorin, 

Longueuil, Quebec, Canada, J4G 1A1; phone: 

800–268–8000; fax: 450–647–2888; Internet: 

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 

May 22, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–14955 Filed 6–30–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2014–0154; Airspace 

Docket No. 14–ACE–1] 

Establishment of Class E Airspace; 

Steele, MO 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace at Steele, MO. Controlled 

airspace is necessary to accommodate 

new Area Navigation (RNAV) Standard 

Instrument Approach Procedures at 

Steele Municipal Airport. The FAA is 

taking this action to enhance the safety 

and management of Instrument Flight 

Rule (IFR) operations at the airport. 

DATES: Effective date: 0901 UTC, April 

30, 2015. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR Part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: Raul 

Garza, Jr., Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone 817–321– 

7654. 

SUPPLEMENTARY INFORMATION: 

History 

On April 22, 2014, the FAA published 

in the Federal Register a notice of 

proposed rulemaking (NPRM) to 

establish Class E airspace for the Steele, 

MO, area, creating controlled airspace at 

Steele Municipal Airport (79 FR 22457) 

Docket No. FAA–2014–0154. Interested 

parties were invited to participate in 

this rulemaking effort by submitting 


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