Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11565 

(f) Borescope Inspections 

(1) Borescope-inspect to verify the 

presence of a retaining ring securing the PT 

baffle located near the second stage PT disk, 

as follows: 

(i) For engines with 2,200 PT cycles or 

more on the effective date of this AD, inspect 

within 100 operating hours or 150 PT cycles, 

whichever occurs first. 

(ii) For engines with more than 1,400 PT 

cycles but fewer than 2,200 PT cycles on the 

effective date of this AD, inspect within 250 

operating hours, 350 PT cycles, or before 

exceeding 2,350 PT cycles, whichever occurs 

first. 

(iii) For engines with 1,400 PT cycles or 

fewer on the effective date of this AD, inspect 

within 500 operating hours, 750 PT cycles, or 

before exceeding 1,750 PT cycles, whichever 

occurs first. 

(2) Thereafter, repetitively borescopeinspect to verify the presence of the retaining 

ring securing the PT baffle located near the 

second stage PT disk, on or before an 

additional 600 flight hours or 900 PT cycles, 

whichever occurs first. 

(3) Use P&WC Alert SB No. PT6C–72– 

A41060, Revision 3, dated October 11, 2012, 

paragraphs 3.A.(1) through 3.A.(6) to do the 

borescope inspections required by this AD. 

(4) If the retaining ring is missing or the PT 

baffle is out of position, then remove the 

engine from service before further flight. 

(g) Optional Terminating Action 

Performing the engine improvement 

modifications in P&WC SB No. PT6C–72– 

41056, Revision 5, dated January 17, 2013, 

paragraphs 3.A. through 3.C.(12) and 3.E.(1) 

through 3.E.(15), is an optional terminating 

action to the repetitive inspections required 

by this AD. 

(h) Credit for Previous Actions 

(1) If you performed the initial borescope 

inspection before the effective date of this AD 

using P&WC Special Instruction No. 45– 

2011R2, dated July 27, 2011, or P&WC Alert 

SB No. PT6C–72–A41060, dated August 12, 

2011, or Revision 1, dated September 29, 

2011, or Revision 2, dated February 10, 2012, 

you met the requirements of paragraph (f)(1) 

of this AD. 

(2) If you performed the engine 

modification before the effective date of this 

AD using P&WC SB No. PT6C–72–41056, 

dated April 1, 2011, or Revision 1, dated June 

17, 2011, or Revision 2, dated October 6, 

2011, or Revision 3, dated February 3, 2012, 

or Revision 4, dated February 13, 2012, you 

met the requirements of this AD and no 

further action is required. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(j) Related Information 

(1) For more information about this AD, 

contact James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: james.lawrence@faa.gov; phone: 781– 

238–7176; fax: 781–238–7199. 

(2) Refer to Transport Canada AD CF– 

2012–24, dated August 2, 2012, for related 

information. 

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

Alert Service Bulletin (SB) No. PT6C–72– 

A41060, Revision 3, dated October 11, 2012. 

(ii) P&WC SB No. PT6C–72–41056, 

Revision 5, dated January 17, 2013. 

(3) For 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; Web site: http:// 

www.pwc.ca. 

(4) 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. 

(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 

February 1, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–03266 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0942; Directorate 

Identifier 2012–NE–24–AD; Amendment 39– 

17355; AD 2013–03–21] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial number Pratt & Whitney Canada 

Corp. PW206B, PW206B2, PW206C, 

PW207C, PW207D, PW207D1, 

PW207D2, and PW207E turboshaft 

engines. This AD was prompted by the 

discovery that certain power turbine 

(PT) disks were made to specific heat 

codes that may not achieve the 

maximum in-service life. This AD 

requires re-identification of the PT disk 

to a part number (P/N) with a lower life 

limit. We are issuing this AD to prevent 

possible uncontained PT disk failure 

and loss of helicopter control. 

DATES: This AD becomes effective 

March 26, 2013. The Director of the 

Federal Register approved the 

incorporation by reference of a certain 

publication listed in this AD as of 

March 26, 2013. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7176; fax: 781–238– 

7199; email: james.lawrence@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 7, 2012 (77 FR 

66767). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information states: 

Certain power turbine (PT) disks, part 

number (P/N) 3044188–01, made to specific 

heat codes may not achieve the established 

maximum in-service life when installed in 

Turbomachinery Assembly P/N 3058588. The 

PT disk in-service life for engines using this 

specific PT disk and compressor turbine (CT) 

vane combination is reduced when operated 

in a particular temperature and speed 

environment. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 66767, November 7, 2012). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed (77 FR 66767, November 7, 

2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 83 engines installed on 


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11566 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 

helicopters of U.S. registry. We also 

estimate that it will take about 4 hours 

per engine to comply with this AD. The 

average labor rate is $85 per hour. 

Prorated parts life will cost about 

$8,900. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $766,920. 

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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 street address for 

the Docket Operations office (phone: 

800–647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 AD: 

2013–03–21 Pratt & Whitney Canada Corp.: 

Amendment 39–17355; Docket No. 

FAA–2012–0942; Directorate Identifier 

2012–NE–24–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) model PW206B, PW206B2, 

PW206C, PW207C, PW207D, PW207D1, 

PW207D2, and PW207E turboshaft engines. 

(d) Reason 

This AD was prompted by the discovery 

that certain power turbine (PT) disks, part 

number (P/N) 3044188–01, made to specific 

heat codes that may not achieve the 

established maximum in-service life when 

installed in Turbomachinery Assembly P/N 

3058588. The PT disk in-service life for 

engines using this specific PT disk and 

compressor turbine vane combination is 

reduced when operated in a particular 

temperature and speed environment. We are 

issuing this AD to prevent possible 

uncontained PT disk failure and loss of 

helicopter control. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) Affected PT Disks Installed With 

Turbomachinery Assembly P/N 3058588 

Installation 

(1) For any PT disk P/N 3044188–01 that 

is listed by serial number (S/N) in Table 1 of 

P&WC Alert Service Bulletin (ASB) No. 

PW200–72–A28311, Revision 2, dated July 

24, 2012, and, that is installed or that had 

previously been installed with 

Turbomachinery Assembly P/N 3058588 

installation, do the following: 

(i) Remove the PT disk P/N 3044188–01 

from service before it reaches 10,000 cyclessince-new (CSN). 

(ii) Re-identify the PT disk to P/N 

3072542–01, at the next engine shop visit, 

not to exceed 10,000 CSN on the PT disk, 

before reinstalling it in any engine. Use 

paragraphs 3.B.(1) through 3.B.(1)(b)4 of the 

Accomplishment Instructions of P&WC ASB 

No. PW200–72–A28311, Revision 2, dated 

July 24, 2012, to do the re-identification. 

(iii) After re-identification of the PT disk to 

P/N 3072542–01, retain the total cycles 

accumulated as P/N 3044188–01. The cycles 

remaining on the re-identified P/N 3072542– 

01 PT disk must be calculated using the 

difference between the published life limit of 

P/N 3072542–01 and the total number of 

cycles accumulated as P/N 3044188–01. The 

maximum in-service life of PT disk, P/N 

3072542–01, is 10,000 CSN. 

(2) After the effective date of this AD, do 

not install any PT disk, P/N 3044188–01, that 

is listed in Table 1 of P&WC ASB No. 

PW200–72–A28311, Revision 2, dated July 

24, 2012, in any engine with Turbomachinery 

Assembly P/N 3058588 installation, unless 

the PT disk has been re-identified to P/N 

3072542–01. Use paragraphs 3.B.(1) through 

3.B.(1)(b)4 of the Accomplishment 

Instructions of P&WC ASB No. PW200–72– 

A28311, Revision 2, dated July 24, 2012, to 

do the PT disk re-identification. 

(g) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

You may take credit for the reidentification of the PT disk that is required 

by this AD if you performed the reidentification before the effective date of this 

AD using P&WC ASB No. PW200–72– 

A28311, dated March 1, 2012, or P&WC ASB 

No. PW200–72–A28311, Revision 1, dated 

March 22, 2012. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7176; fax: 781–238–7199; 

email: james.lawrence@faa.gov. 

(2) Refer to Transport Canada AD CF– 

2012–23, dated July 26, 2012, for related 

information. 

(3) The Engine Maintenance Manual 

(EMM) Temporary Revisions (TRs) listed in 

Table 1 to paragraph (i)(3) of this AD pertain 

to the subject of this AD. 


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Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11567 

TABLE 1 TO PARAGRAPH (I)(3)—EMM 

TRS

EMM P/Ns: TR Nos.: 

3071602 ................................. AL–3, AL–4 

3043612 ................................. AL–12, AL– 

13 

3043322 ................................. AL–16 

3039732 ................................. AL–18, AL– 

19 

3038324 ................................. AL–20 

(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. Alert 

Service Bulletin No. PW200–72–A28311, 

Revision 2, dated July 24, 2012. 

(ii) Reserved. 

(3) For 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; Web site: 

www.pwc.ca. 

(4) 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. 

(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 

February 7, 2013. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–03412 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0986; Directorate 

Identifier 2012–NM–077–AD; Amendment 

39–17357; AD 2013–03–23] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP (Type Certificate 

Previously Held by Israel Aircraft 

Industries, Ltd.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace LP (Type 

Certificate Previously Held by Israel 

Aircraft Industries, Ltd.) Model 

Gulfstream G150 airplanes. This AD was 

prompted by a review that determined 

that the runway slope and anti-ice 

corrections to V1 and take-off distances 

in the Gulfstream G150 Airplane Flight 

Manual (AFM) were presented in a nonconservative manner. This AD requires 

revising the performance section of the 

AFM to include procedures to advise 

the flightcrew of certain runway slope 

and anti-ice corrections and take-off 

distance values. We are issuing this AD 

to prevent the use of published nonconservative data, which could result in 

the inability to meet the required takeoff performance, with consequent 

hazard to safe operation during 

performance-limited take-off operations. 

DATES: This AD becomes effective 

March 26, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 26, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1503; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 20, 2012 (77 FR 

58323). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

This [Israeli] AD mandates revised 

limitations in the G150 AFM, pertaining to 

the Performance Section. Each operator must 

incorporate Temporary Rev. 3 to the G150 

AFM. 

The unsafe condition is the use of 

published non-conservative data, which 

could result in the inability to meet the 

required take-off performance, with 

consequent hazard to safe operation 

during performance-limited take-off 

operations. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 58323, September 20, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

58323, September 20, 2012) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 58323, 

September 20, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

56 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $4,760, or $85 per product. 

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 


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