Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 57007 

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): 

2012–18–09 Bell Helicopter Textron 

Canada (BHTC): Amendment 39–17185; 

Docket No. FAA–2012–0337; Directorate 

Identifier 2010–SW–090–AD. 

(a) Applicability 

This AD applies to BHTC Model 407 

helicopters, serial numbers 53000 through 

53990, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

incorrect torque value of the tailboom 

attachment bolt (bolt) specified in the BHTC 

Model 407 Maintenance Manual and applied 

during manufacturing, which exceeds the 

torque range recommended for the bolts. This 

condition could result in an over-torque of 

the bolt, bolt failure, loss of the tailboom, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 22, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

(1) For helicopters with 7000 hours or less 

time-in-service (TIS), at the next 600 hours 

scheduled inspection, or 90 days, whichever 

comes first; and for helicopters with more 

than 7000 hours TIS, within 150 hours TIS 

or 90 days, whichever comes first, replace the 

tailboom-attachment hardware (attachment 

hardware) as follows: 

(i) Remove the left upper bolt, washers, 

and nut. 

(ii) Install a new bolt, part number (P/N) 

NAS627–30; washer, P/N 140–007–29S25E6; 

washer(s), P/N NAS1149G0732P; and new 

nut, P/N 42FLW–720 in accordance with 

paragraphs 2.a) through paragraph 3.e) of the 

‘‘Accomplishment Instructions: Replacement 

of tailboom attachment bolts and nuts’’ 

section and Figure 2 in the BHTC Alert 

Service Bulletin No. 407–10–93, Revision A, 

dated August 30, 2010 (ASB). 

(iii) Remove the opposite right upper bolt, 

washers, and nut, and accomplish the 

requirements in paragraph (e)(1)(ii) of this 

AD. 

(iv) Remove the left lower bolt, washers, 

and nut. 

(v) Install a new bolt, (P/N) NAS626–26; 

washer, P/N 140–007–25S22E6; washer(s), P/ 

N NAS1149G0663P; and new nut, P/N 

42FLW–624 in accordance with paragraphs 

6.a) through 7.e) of the ‘‘Accomplishment 

Instructions: Replacement of tailboom 

attachment bolts and nuts’’ section and 

Figure 2 in the ASB. 

(vi) Remove the right lower bolt, washers, 

and nut, and accomplish the requirements in 

paragraph (e)(1)(v) of this AD. 

(2) After installation of the new attachment 

hardware, at intervals of not less than 1 hour 

TIS but not exceeding 5 hours TIS, determine 

the torque of each nut until the torque 

stabilizes at each attachment location, 

referring to Figure 2 of the ASB. Apply the 

minimum specified torque of the range, plus 

the minimum acceptable tare torque of 14 

inch/lbs (1.58 Nm) for the upper nuts, and 

9.5 inch/lbs (1.07 Nm) for the lower nuts. 

(3) At intervals not to exceed 300 hours 

TIS, determine the torque of each of the four 

attachment nuts, referring to Figure 2 of the 

ASB. Apply the minimum specified torque of 

the range plus the minimum acceptable tare 

torque of 14 inch/lbs (1.58 Nm) for the upper 

nuts, and 9.5 inch/lbs (1.07 Nm) for the lower 

nuts. If the proper torque has not been 

retained since the last torque determination, 

remove and inspect the tailboom assembly 

for damage, corrosion, improper assembly, 

and condition. If the tailboom assembly is 

airworthy, replace the attachment hardware 

in accordance with the requirements in 

paragraphs (e)(1)(i) through (e)(1)(vi) and 

determine that the torque has stabilized in 

accordance with paragraph (e)(2) of this AD. 

Replace any unairworthy tailboom assembly 

with an airworthy tailboom assembly. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: 817– 

222–5961; email: sharon.y.miles@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. 

(g) Additional Information 

The subject of this AD is addressed in the 

Transport Canada Civil Aviation (TCCA) AD 

CF–2010–33, dated September 30, 2010. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Rotorcraft tailboom. 

(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) Bell Helicopter Textron Canada Limited 

Alert Service Bulletin No. 407–10–93, 

Revision A, dated August 30, 2010. 

(ii) Reserved. 

(3) 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/. 

(4) You may review a copy of this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. For information on the 

availability of this material at the FAA, call 

(817) 222–5110. 

(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 Fort Worth, Texas, on August 30, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–22038 Filed 9–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0217; Directorate 

Identifier 2009–NE–23–AD; Amendment 39– 

17194; AD 2012–18–17] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division 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 (Pratt & 

Whitney) PW4052, PW4056, PW4060, 

PW4062, PW4062A, PW4074, PW4077, 

PW4077D, PW4084D, PW4090, 

PW4090–3, PW4152, PW4156A, 

PW4158, PW4164, PW4168, PW4168A, 

PW4460, and PW4462 turbofan engines. 

That AD currently requires initial and 

repetitive fluorescent penetrant 

inspections (FPI) for cracks in the blade 

loading and locking slots of the highpressure compressor (HPC) drum rotor 

disk assembly rear drum. This new AD 

requires the same actions, requires 

replacement of the 13th, 14th, and 15th 

stage HPC seals with redesigned HPC 

seals as an additional action, and adds 

an optional terminating action to the 

repetitive inspection requirements by 

allowing replacement of the entire HPC 

drum rotor disk assembly with a 

redesigned HPC drum rotor disk 

assembly. This AD was prompted by 

Pratt & Whitney developing a 

redesigned HPC drum rotor disk 

assembly for certain affected engine 

models. We are issuing this AD to 

prevent failure of the HPC drum rotor 

disk assembly, which could lead to an 


tkelley on DSK3SPTVN1PROD with RULES
57008 Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 

uncontained engine failure, and damage 

to the airplane. 

DATES: This AD is effective October 22, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 22, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 18, 2010 (75 FR 

55459, September 13, 2010). 

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 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; 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: 

James Gray, Aerospace Engineer, Engine 

& Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7742; fax: 781– 

238–7199; email: james.e.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–18–13, 

Amendment 39–16427 (75 FR 55459, 

September 13, 2010). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

May 24, 2012 (77 FR 30926). That 

NPRM proposed to retain all of the 

requirements of AD 2010–18–13. That 

NPRM also proposed to require 

replacement of the 13th, 14th, and 15th 

stage HPC seals with redesigned seals 

and add an optional terminating action 

to the repetitive inspection requirement 

by allowing replacement of the HPC 

drum rotor disk assembly with a 

redesigned HPC drum rotor disk 

assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

In Agreement With the Proposed AD 

The Boeing Company and FedEx 

Express are in agreement with the 

proposed AD. 

Request To Allow for Previous Credit 

FedEx Express requested that we 

allow credit for prior compliance with 

the AD actions. 

We do not agree. The proposed AD 

already allows credit for prior 

compliance in paragraph (e), which 

states to comply within the compliance 

times specified unless already done. We 

did not change the AD. 

Request To Reference the Latest 

Revisions of Two Service Bulletins 

(SBs) 

United Airlines, Korean Air, and 

Atlas Air, requested that we reference 

the latest revisions of two SBs which 

were revised since the proposed AD was 

issued. 

We agree. We now reference Pratt & 

Whitney SB No. PW4ENG 72–816, 

Revision 1, dated June 12, 2012, and 

Pratt & Whitney SB No. PW4G–100–72– 

240, Revision 1, dated June 12, 2012, in 

the AD. 

Request To Revise Paragraph (g) 

United Airlines requested that we 

change paragraph (g) of the proposed 

AD to only require use of paragraphs 

1.A. through 1.C. of the 

Accomplishment Instructions of SB No. 

PW4ENG 72–816 since additional 

paragraphs of the SB are not needed to 

comply with the AD. 

We agree. We changed paragraphs 

(g)(1) and (g)(2) to only require use of 

paragraphs 1.A through 1.C. of that SB 

to comply with the AD. 

Request To Add Previously Approved 

Alternate Methods of Compliance 

(AMOCs) 

Japan Airlines and Korean Air 

requested that we add the previously 

approved AMOCs to the AD. The 

commenters referenced two previously 

approved AMOCs related to taking 

credit for the inspections required by 

AD 2005–25–09 (70 FR 73358, 

December 12, 2005), and use of the disk 

replacement repair included in the 

PW4000 Engine Cleaning Inspection 

and Repair (CIR) Manual to return noncracked stages of the drum rotor disk 

assembly to service. 

We do not agree. We did not list the 

previously approved AMOCs in the 

proposed AD because paragraph (j) of 

the proposed AD already allows use of 

previously approved AMOCs to 

paragraph (f) of the existing AD. 

Paragraph (f) was specified because the 

content of this paragraph did not change 

in the proposed AD supersedure. We 

did not change the AD. 

Request To Revise Paragraph (f)(2) 

Atlas Air requested that we revise 

paragraph (f)(2) of the proposed AD to 

remove only the cracked disk in the 

HPC drum rotor disk assembly from 

service. The commenter stated that 

currently paragraph (f)(2) requires the 

entire drum rotor disk assembly to be 

removed from service if a crack is 

found. The commenter believes it would 

be acceptable to remove from service 

only the cracked disk in the drum rotor 

disk assembly and use the repair in the 

PW4000 Engine CIR manual to replace 

it with a serviceable disk. 

We partially agree. We agree that an 

acceptable level of safety would be 

maintained by returning the other stages 

of the drum rotor disk assembly to 

service if they were not cracked, if the 

cracked stages of the HPC drum rotor 

disk assembly were replaced by new 

disks per the disk replacement repairs 

in the PW4000 Engine CIR manual. We 

do not agree with revising the proposed 

AD because this is already an approved 

global AMOC covered under paragraph 

(j) of the proposed AD. We did not 

change the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

Costs of Compliance 

We estimate that this AD will affect 

911 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 1 work-hour per engine 

to perform an inspection using an 

average labor rate of $85 per work-hour. 

We estimate that there are 770 PW4000– 

94′′ and PW4000–100′′ engines that will 

require replacement of 13th, 14th, and 

15th stage HPC seals, at a parts cost of 

$3,000 per engine. No additional labor 

is assumed when the replacement is 

done at piece-part exposure of the HPC 

drum rotor disk assembly. The 

replacement parts cost of the redesigned 

HPC drum rotor disk assembly is 

$630,000. Based on these figures, we 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 57009 

estimate that the total cost of the AD to 

U.S. operators will be $2,387,435. 

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, 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) 

2010–18–13, Amendment 39–16427 (75 

FR 55459, September 13, 2010), and 

adding the following new AD: 

2012–18–17 Pratt & Whitney Division: 

Amendment 39–17194; Docket No. 

FAA–2010–0217; Directorate Identifier 

2009–NE–23–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 22, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–18–13, 

Amendment 39–16427 (75 FR 55459, 

September 13, 2010). 

(c) Applicability 

This AD applies to the following Pratt & 

Whitney Division (Pratt & Whitney) turbofan 

engines: 

(1) PW4000–94′′ engine models PW4052, 

PW4056, PW4060, PW4062, PW4062A, 

PW4152, PW4156A, PW4158, PW4460, and 

PW4462, including those models with any 

dash number suffix, with a high-pressure 

compressor (HPC) drum rotor disk assembly 

listed in Table 1 to paragraph (c) of this AD 

installed. 

(2) PW4000–100′′ engine models PW4164, 

PW4168, and PW4168A, with a HPC drum 

rotor disk assembly listed in Table 1 to 

paragraph (c) of this AD installed. 

(3) PW4000–112′′ engine models PW4074, 

PW4077, PW4077D, PW4084D, PW4090, and 

PW4090–3, with a HPC drum rotor disk 

assembly listed in Table 1 to paragraph (c) of 

this AD installed. 

TABLE 1 TO PARAGRAPH (c)—AFFECTED HPC DRUM ROTOR DISK ASSEMBLIES

Engine models Affected HPC drum rotor disk assembly part numbers 

PW4000–94′′ ................................... 50H936; 50H936–002; 53H923–01; 53H923–001; 53H973–01; 53H973–001; 54H803–01; 54H803–001; 

54H803–002; 56H013–01; 56H013–001; 58H236–01 

PW4000–100′′ ................................. 53H973–01; 53H973–001; 54H803–01; 54H803–001; 54H803–002; 56H013–01; 56H013–001; 58H236–01 

PW4000–112′′ ................................. 55H722–01; 55H410–01; 57H010–01; 57H210–01; 57H610–01; 57H910–01 

(d) Unsafe Condition 

This AD was prompted by Pratt & Whitney 

developing a redesigned HPC drum rotor disk 

assembly for certain affected engine models. 

We are issuing this AD to prevent failure of 

the HPC drum rotor disk assembly, which 

could lead to an uncontained engine failure, 

and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Local Fluorescent Penetrant Inspection 

(1) Perform a local fluorescent penetrant 

inspection for cracks in the HPC drum rotor 

disk assembly rear drum blade loading and 

locking slots of the specific stages of the HPC 

drum rotor disk assemblies from which any 

of the blades are removed as specified in 

Table 2 to paragraph (f) of this AD. 

TABLE 2 TO PARAGRAPH (f)—COMPLIANCE TIMES AND SERVICE BULLETINS BY ENGINE MODEL

For engine model Inspect whenever . . . To inspect, use . . . 

PW4074, PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3.

Any of the HPC 13th or 14th stage blades are 

removed during a shop visit.

Paragraphs 1.A. through 1.B. of the Accomplishment Instructions of PW4G–112–72– 

264, Revision 2, dated February 23, 2010. 

PW4164, PW4168, and PW4168A .................... Any of the HPC 13th, 14th, or 15th stage 

blades are removed during a shop visit.

Paragraphs 1.A. through 1.C of the Accomplishment Instructions of PW4G–100–72– 

186, Revision 1, dated September 2, 2004. 

PW4052, PW4056, PW4060, PW4062, 

PW4062A, PW4152, PW4156A, PW4158, 

PW4460, and PW4462.

Any of the HPC 13th, 14th, or 15th stage 

blades are removed during a shop visit.

Paragraphs 1.A. through 1.C. of the Accomplishment Instructions of PW4ENG 72–796, 

dated June 11, 2009. 


tkelley on DSK3SPTVN1PROD with RULES
57010 Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 

(2) Remove from service any HPC drum 

rotor disk assembly rear drum found with a 

crack in any of the blade loading and locking 

slots. 

(g) Replacement of 13th, 14th, and 15th HPC 

Seals 

At the next piece-part exposure of the HPC 

drum rotor disk assembly after the effective 

date of this AD: 

(1) Replace the 13th, 14th, and 15th stage 

HPC seals with redesigned HPC seals of 

engines listed in paragraph (c)(1) of this AD 

in accordance with paragraphs 1.A through 

1.C of the Accomplishment Instructions of 

Pratt & Whitney Service Bulletin (SB) No. 

PW4ENG 72–816, Revision 1, dated June 12, 

2012. 

(2) Replace the 13th, 14th, and 15th stage 

HPC seals with redesigned HPC seals of 

engines listed in paragraph (c)(2) of this AD 

in accordance with paragraphs 1.A through 

1.C of the Accomplishment Instructions of 

Pratt & Whitney SB No. PW4G–100–72–240, 

Revision 1, dated June 12, 2012. 

(h) Optional Terminating Action 

As optional terminating action to the 

repetitive inspection requirements of this 

AD: 

(1) Replace the HPC drum rotor disk 

assembly of engines listed in paragraph (c)(1) 

of this AD with a redesigned HPC drum rotor 

disk assembly in accordance with the 

Accomplishment Instructions of Pratt & 

Whitney SB No. PW4ENG 72–817, dated 

December 7, 2011. 

(2) Replace the HPC drum rotor disk 

assembly of engines listed in paragraph (c)(2) 

of this AD with a redesigned HPC drum rotor 

disk assembly in accordance with the 

Accomplishment Instructions of Pratt & 

Whitney SB No. PW4G–100–72–241, dated 

November 15, 2011. 

(i) Definition 

For the purpose of this AD, piece-part 

exposure means that the HPC drum rotor disk 

assembly is removed from the engine and 

completely disassembled. 

(j) 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. AMOCs approved previously in 

accordance with AD 2010–18–13, 

Amendment 39–16427 (75 FR 55459, 

September 13, 2010) are approved as AMOCs 

for the corresponding requirements in 

paragraph (f) of this AD. 

(k) Related Information 

For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7742; fax: 781–238– 

7199; email: james.e.gray@faa.gov. 

(l) 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. 

(3) The following service information was 

approved for IBR on October 22, 2012. 

(i) Pratt & Whitney Service Bulletin No. 

PW4G–100–72–240, Revision 1, dated June 

12, 2012. 

(ii) Pratt & Whitney Service Bulletin No. 

PW4G–100–72–241, dated November 15, 

2011. 

(iii) Pratt & Whitney Service Bulletin No. 

PW4ENG 72–816, Revision 1, dated June 12, 

2012. 

(iv) Pratt & Whitney Service Bulletin No. 

PW4ENG 72–817, dated December 7, 2011. 

(4) The following service information was 

approved for IBR on October 18, 2010 (75 FR 

55459, September 13, 2010). 

(i) Pratt & Whitney Service Bulletin No. 

PW4G–100–72–186, Revision 1, dated 

September 2, 2004. 

(ii) Pratt & Whitney Service Bulletin No. 

PW4G–112–72–264, Revision 2, dated 

February 23, 2010. 

(iii) Pratt & Whitney Service Bulletin No. 

PW4ENG 72–796, dated June 11, 2009. 

(5) 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. 

(6) 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. 

(7) 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 4, 2012. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–22534 Filed 9–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–1407; Airspace 

Docket No. 11–AGL–25] 

RIN 2120–AA66 

Modification of Area Navigation 

(RNAV) Route Q–62; Northeast United 

States 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies area 

navigation (RNAV) route Q–62 by 

extending it further west and 

incorporating two additional navigation 

fixes. The route extension links two 

RNAV Standard Terminal Arrival 

Routes (STARs) serving the Chicago 

O’Hare International Airport, IL, 

terminal area with the high altitude 

route. The FAA is taking this action to 

increase National Airspace System 

(NAS) efficiency and enhance flight 

safety as aircraft transition from the en 

route airway structure to the terminal 

area airspace phase of flight. 

DATES: Effective date 0901 UTC, 

November 15, 2012. 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: 

Colby Abbott, Airspace, Regulations and 

ATC Procedures Group, Office of 

Airspace Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On Monday, February 6, 2012, the 

FAA published in the Federal Register 

a notice of proposed rulemaking to 

modify RNAV route Q–62 in Northeast 

United States by extending it further 

west (77 FR 5733). Interested parties 

were invited to participate in this 

rulemaking proceeding by submitting 

written comments on this proposal to 

the FAA. No comments were received. 

The Rule 

The FAA is amending Title 14, Code 

of Federal Regulations (14 CFR) part 71 

by extending high altitude RNAV route 

Q–62 to the west to include the WATSN 

and DAIFE fixes. This action links the 

WATSN and HALIE RNAV STARs 

serving Chicago O’Hare International 

Airport, IL, with the high altitude route 

and establishes a seamless transition for 

westbound air traffic from the New York 

metropolitan area into the Chicago 

O’Hare International Airport, IL, 

terminal area. Additionally, this action 

reduces ATC system complexity, air 

traffic controller and pilot workload, 

voice communication requirements, and 

aircraft fuel consumption. It also 

expands the use of RNAV within the 

NAS. 

High altitude RNAV routes are 

published in paragraph 2006 of FAA 

Order 7400.9W dated August 8, 2012, 

and effective September 15, 2012, which 

is incorporated by reference in 14 CFR 

71.1. The RNAV route listed in this 

document will be subsequently 

published in the Order. 


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