42424 Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations 

(iv) If at least one lock washer tab is not 

aligned and bent flush with a nut flat surface 

and at least one lock washer tab is not 

aligned and bent flush with a flat surface of 

the clevis assembly, before further flight, 

replace the servo with an airworthy servo. 

(v) If any tab of the lock washer is not bent 

flush against either a flat surface of the nut 

or clevis assembly, bend the tab flush against 

a flat surface. 

(2) After accomplishing paragraphs (f)(1)(i) 

through (f)(1)(v), vibro-etch the letter ‘‘V’’ at 

the end of the part number on the data plate. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

(1) Bell Helicopter Alert Service Bulletins 

407–11–96 and 427–11–35, both Revision B 

and both dated August 29, 2011, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/ 

files/. You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada AD CF–2011–17R1, dated 

December 19, 2011. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6730, Rotorcraft Servo System. 

Issued in Fort Worth, Texas, on July 2, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17561 Filed 7–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1095; Directorate 

Identifier 2009–NE–40–AD; Amendment 39– 

17104; AD 2012–13–02] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Pratt & Whitney Division PW4074 

and PW4077 turbofan engines. That AD 

currently requires removing the 15th 

stage high-pressure compressor (HPC) 

disk within 12,000 cycles since new 

(CSN) or using a drawdown removal 

plan for disks that exceed 12,000 CSN. 

This new AD requires the same actions 

and clarifies that 15th stage HPC disks 

that have accumulated more than 9,865 

CSN require a borescope inspection 

(BSI) or eddy current inspection (ECI) of 

the disk outer rim front rail for cracks 

prior to accumulating 12,000 CSN. This 

AD was prompted by a request from an 

operator that we clarify our inspection 

schedule for 15th stage HPC disks that 

have accumulated more than 9,865, but 

less than 12,000 CSN, on the effective 

date of the AD. We are issuing this AD 

to prevent cracks from propagating into 

the disk bolt holes, which could result 

in a failure of the 15th stage HPC disk, 

uncontained engine failure, and damage 

to the airplane. 

DATES: This AD is effective August 23, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 8, 2011 (76 FR 

47056, August 4, 2011). 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; phone: 860–565–7700; fax: 

860–565–1605. You may review copies 

of the referenced service information at 

the FAA, Engine & Propeller Directorate, 

16 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; 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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7178; fax: 781– 

238–7199; email: ian.dargin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–14–07, 

Amendment 39–16742 (76 FR 47056, 

August 4, 2011). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

February 24, 2012 (77 FR 11017). That 

NPRM proposed to continue to require 

removing the 15th stage HPC disk 

within 12,000 CSN or using a 

drawdown removal plan for disks that 

exceed 12,000 CSN. That NPRM also 

proposed to clarify our inspection 

schedule for 15th stage HPC disks that 

have accumulated more than 9,865, but 

less than 12,000 CSN, on the effective 

date of the AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

United Airlines and The Boeing 

Company support the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

44 engines installed on airplanes of U.S. 

registry. Prorated parts life will cost 

about $66,000 per 15th stage HPC disk. 

Based on these figures, we estimate the 

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

be $2,904,000. The new requirements of 

this AD add no additional economic 

burden. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations 42425 

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, 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 

removing airworthiness directive (AD) 

2011–14–07, Amendment 39–16742 (76 

FR 47056, August 4, 2011), and adding 

the following new AD: 

2012–13–02 Pratt & Whitney Division: 

Amendment 39–17104; Docket No. 

FAA–2010–1095; Directorate Identifier 

2009–NE–40–AD. 

(a) Effective Date 

This AD is effective August 23, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–14–07, 

Amendment 39–16742 (76 FR 47056, August 

4, 2011). 

(c) Applicability 

This AD applies to Pratt & Whitney 

Division PW4074 and PW4077 turbofan 

engines with 15th stage high-pressure 

compressor (HPC) disks, part number (P/N) 

55H615, installed. 

(d) Unsafe Condition 

This AD results from multiple shop 

findings of cracked 15th stage HPC disks. We 

are issuing this AD to prevent cracks from 

propagating into the disk bolt holes, which 

could result in a failure of the 15th stage HPC 

disk, uncontained engine failure, and damage 

to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. To perform the inspections, use 

paragraph 1.A. or 1.B. of the 

Accomplishment Instructions ‘‘For Engines 

Installed on the Aircraft’’ or 1.A. or 1.B. of 

the Accomplishment Instructions ‘‘For 

Engines Removed from the Aircraft,’’ of Pratt 

& Whitney Service Bulletin PW4G–112–72– 

309, Revision 1, dated July 1, 2010. 

(1) For 15th stage HPC disks that have 

9,865 or fewer cycles since new (CSN) on the 

effective date of this AD, remove the disk 

from service before accumulating 12,000 

CSN. 

(2) For 15th stage HPC disks that have 

accumulated more than 9,865 CSN on the 

effective date of this AD, do one of the 

following: 

(i) Remove the disk from service at the next 

piece-part exposure, not to exceed 2,135 

cycles-in-service (CIS) after the effective date 

of this AD. 

(ii) Perform a borescope inspection (BSI) or 

eddy current inspection (ECI) of the front rail 

of the disk outer rim according to the 

following schedule: 

(A) Within 2,400 cycles-since-last 

fluorescent penetrant inspection or ECI, or 

(B) Within 1,200 cycles-since-last BSI, or 

(C) Before accumulating 12,000 CSN, or 

(D) Within 55 CIS after the effective date 

of this AD, whichever occurs latest. 

(3) If the BSI from paragraph (e)(2)(ii) of 

this AD indicates the presence of a crack in 

the disk outer rim front rail, but you cannot 

visually confirm a crack, perform an ECI 

within 5 CIS after the BSI. 

(4) If you confirm a crack in the front rail 

of the disk outer rim using any inspection 

method, remove the disk from service before 

further flight. 

(f) 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. 

(g) Related Information 

For more information about this AD, 

contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7178; fax: 781–238– 

7199; email: ian.dargin@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) Pratt & Whitney Service Bulletin PW4G– 

112–72–309, Revision 1, dated July 1, 2010, 

approved for IBR September 8, 2011. 

(ii) Reserved. 

(3) For Pratt & Whitney service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, CT 

06108; phone: 860–565–7700; fax: 860–565– 

1605. 

(4) You may review copies of the 

referenced service information at the FAA, 

Engine & Propeller Directorate, 16 New 

England Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may also review copies of the 

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/ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

June 19, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–17001 Filed 7–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0621; Airspace 

Docket No. 12–ASO–24] 

RIN 2120–AA66 

Amendment of Air Traffic Service 

(ATS) Routes in the Vicinity of Vero 

Beach, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This action amends the legal 

descriptions of Jet Routes J–45 and J–79, 

and VHF omnidirectional range (VOR) 


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