Federal Register / Vol. 80, No. 118 / Friday, June 19, 2015 / Rules and Regulations 35191 

[FR Doc. 2015–15194 Filed 6–18–15; 8:45 am] 

BILLING CODE 8070–01–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0266; Directorate 

Identifier 2015–NE–03–AD; Amendment 39– 

18185; AD 2015–12–10] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Pratt 

& Whitney Division (PW) PW6122A and 

PW6124A turbofan engines. This AD 

requires initial and repetitive borescope 

inspections (BSIs) of the high-pressure 

compressor (HPC) 7th stage integrally 

bladed (IB) rotor aft integral arm for 

cracks until replacement of the HPC 7th 

stage IB rotor using non-silver-plated 

nuts. This AD was prompted by reports 

of crack finds in the HPC 7th stage IB 

rotor. We are issuing this AD to prevent 

HPC 7th stage IB rotor fractures, which 

could lead to uncontained engine failure 

and damage to the airplane. 

DATES: This AD is effective July 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 6, 2015. 

We must receive comments on this 

AD by August 3, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Pratt & Whitney, 400 

Main St., East Hartford, CT 06108; 

phone: 860–565–8770; fax: 860–565– 

4503. 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. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

0266. 

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– 

0266; 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238– 

7199; email: wego.wang@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports of cracks in the 

PW6122A and the PW6124A HPC 7th 

stage IB rotor aft integral arm. The root 

cause is the presence of silver-plated 

nuts reacting with hot titanium in a high 

sulfur/high chlorine environment. This 

AD requires initial and repetitive BSIs 

of the HPC 7th stage IB rotor. This AD 

also requires, as terminating action, 

replacement of the HPC 7th stage IB 

rotor and HPC 7th stage IB rotor silverplated nuts with non-silver-plated nuts. 

This condition, if not corrected, could 

result in HPC 7th stage IB rotor 

fractures. We are issuing this AD to 

prevent HPC 7th stage IB rotor fractures, 

which could lead to uncontained engine 

failure and damage to the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed PW Engineering 

Authorization (EA) No. 15MM008, 

Revision A, dated March 24, 2015. We 

also reviewed PW Service Bulletin (SB) 

No. PW6ENG 72–46, dated March 5, 

2015. The EA describes procedures for 

BSIs of the HPC 7th stage IB rotor aft 

integral arm for cracks using the splitcase method. The SB describes removal 

and replacement of the HPC 7th stage IB 

rotor, removal of the HPC 7th stage IB 

rotor silver-plated nuts, and the 

installation of non-silver plated nuts. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires initial and repetitive 

BSIs of the HPC 7th stage IB rotor. This 

AD also requires as terminating action 

to replace the HPC 7th stage IB rotor and 

HPC 7th stage IB rotor silver-plated nuts 

with non-silver-plated nuts. 

FAA’s Justification and Determination 

of the Effective Date 

No domestic operators use this 

product. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–0266; Directorate Identifier 2015– 

NE–03–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will affect 0 

engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 8 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Based on these figures, we 


rmajette on DSK2TPTVN1PROD with RULES
35192 Federal Register / Vol. 80, No. 118 / Friday, June 19, 2015 / Rules and Regulations 

estimate the total cost of this AD to U.S. 

operators to be $0. 

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 

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, 

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): 

2015–12–10 Pratt & Whitney Division: 

Amendment 39–18185; Docket No. 

FAA–2015–0266; Directorate Identifier 

2015–NE–03–AD. 

(a) Effective Date 

This AD is effective July 6, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Division (PW) PW6122A and PW6124A 

turbofan engines with high-pressure 

compressor (HPC) 7th stage integrally bladed 

(IB) rotor, part number (P/N) 5495637, 

installed. 

(d) Unsafe Condition 

This AD was prompted by reports of crack 

finds in the HPC 7th stage IB rotor. We are 

issuing this AD to prevent HPC 7th stage IB 

rotor fractures, which could lead to 

uncontained engine failure and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 180 cycles after the effective 

date of this AD or within 6,500 cycles 

accumulated on the HPC 7th stage IB rotor, 

whichever occurs later, borescope inspect the 

HPC 7th stage IB rotor for cracks. Use 

Appendix 1, paragraphs 5 and 6 of PW 

Engineering Authorization 15MM008, 

Revision A, dated March 24, 2015, to do your 

inspection. Thereafter, repeat the inspection 

at every 1,000 cycles since last inspection. 

(2) If any crack is detected on the HPC 7th 

stage IB rotor, then before further flight, 

replace the HPC 7th stage IB rotor with a part 

eligible for installation. 

(f) Mandatory Terminating Action 

(1) At the next shop visit after the effective 

date of this AD: 

(i) Replace the affected HPC 7th stage IB 

rotor, P/N 5495637, with a new, zero-time, 

HPC 7th stage IB rotor, P/N 5495637, and 

(ii) Remove the HPC 7th stage IB rotor 

silver-plated nuts, P/N 4301682, and replace 

with non-silver-plated nuts. Use the 

Accomplishment Instructions of PW Service 

Bulletin No. PW6ENG 72–46, dated March 5, 

2015 to perform the removal and 

replacement. 

(g) Definition 

For the purposes 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 purposes of transportation 

without subsequent engine maintenance, is 

not an engine shop visit. 

(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. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

For more information about this AD, 

contact Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238–7199; 

email: wego.wang@faa.gov. 

(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 Division (PW) 

Engineering Authorization No. 15MM008, 

Revision A, dated March 24, 2015. 

(ii) PW Service Bulletin No. PW6ENG 72– 

46, dated March 5, 2015. 

(3) For PW service information identified 

in this AD, contact Pratt & Whitney, 400 

Main St., East Hartford, CT 06108; phone: 

860–565–8770; fax: 860–565–4503. 

(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 

June 9, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–14992 Filed 6–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0492; Directorate 

Identifier 2013–NM–134–AD; Amendment 

39–18187; AD 2015–12–12] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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