Federal Register / Vol. 80, No. 76 / Tuesday, April 21, 2015 / Proposed Rules 22137 

$28,765 per engine. Based on these 

figures, we estimate the cost of this 

proposed AD on U.S. operators to be 

$34,205. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

(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), 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

GE Aviation Czech s.r.o. (Type Certificate 

previously held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.): 

Docket No. FAA–2015–0625; Directorate 

Identifier 2015–NE–09–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain serial number 

(S/N) GE Aviation Czech s.r.o. M601E–11, 

M601E–11A, and M601F turboprop engine 

models, with gas generator turbine (GGT) 

blade, part number (P/N) M601–3372.6 or 

M601–3372.51, installed, as follows: 

(1) Model M601E–11: S/Ns 862001, 

863008, 894018, 034005, 034006, 034007, 

034008, 041003, and 042002. 

(2) Model M601E–11A: S/Ns 042003, 

042004, 044001, 044002, and 961001. 

(3) Model M601F: S/Ns 024001, 002001, 

003001, 024001, 934001, 934002, 961001. 

(d) Reason 

This AD was prompted by the 

determination that certain GGT blades are 

susceptible to blade failure. These blades are 

identified as blade P/Ns M601–3372.6 and 

M601–3372.51, and are installed on an 

engine S/N identified in paragraph (c) of this 

AD. We are issuing this AD to prevent GGT 

blade failure, which could lead to engine 

failure and loss of the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. After the effective date of this AD: 

(1) Do not return to service any affected 

engine with GGT blade, P/N M601–3372.6 or 

M601–3372.51, installed, after 300 hours 

time in service or six months, whichever 

occurs first, after the effective date of this 

AD. 

(2) If the affected engines are subsequently 

disassembled or overhauled, the non-shot 

peened GGT blades, P/N M601–3372.6 or 

M601–3372.51, are not eligible for 

installation in any other engine after removal. 

(f) 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. 

(g) 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 European Aviation 

Safety Agency AD 2015–0015, dated January 

30, 2015, for more information. You may 

examine the MCAI in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2015–0625. 

(3) GE Aviation Czech s.r.o. Alert Service 

Bulletin (ASB) No. M601E–11/30, dated 

December 23, 2014, which is co-published as 

one document with M601D–1/31, M601Z/29, 

and M601T/24, and ASB No. M601E–11/31, 

M601E–11A/18, M601F/28, dated December 

23, 2014, which is co-published as one 

document with M601D–1/32, M601Z/30, 

M601E/61, M601T/25, M601FS/12, M601F– 

22/25, M601F–32/23, and M601E–21/28, are 

not incorporated by reference in this AD. The 

ASBs can be obtained from GE Aviation 

Czech s.r.o. using the contact information in 

paragraph (g)(4) of this proposed AD. 

(4) For service information identified in 

this proposed AD, contact GE Aviation Czech 

s.r.o., Beranovy ́ch 65, 199 02 Praha 9— 

Letnˇ any, Czech Republic; phone: +420 222 

538 111; fax: +420 222 538 222. 

(5) 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. 

Issued in Burlington, Massachusetts, on 

April 7, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–09002 Filed 4–20–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0363; Directorate 

Identifier 2014–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Rolls-Royce plc (RR) RB211 Trent 

768–60, 772–60, and 772B–60 turbofan 

engines. The NPRM proposed to require 


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22138 Federal Register / Vol. 80, No. 76 / Tuesday, April 21, 2015 / Proposed Rules 

inspection of the fan case low-pressure 

(LP) fuel tubes and clips and the fuel oil 

heat exchanger (FOHE) mounts and 

hardware. The NPRM was prompted by 

fuel leaks caused by damage to the fan 

case LP fuel tube. This supplemental 

action revises the NPRM by expanding 

inspections and corrective actions, 

correcting a part number (P/N) and the 

costs of compliance, reducing the 

applicability, providing another method 

to comply with certain requirements, 

and giving credit for certain previous 

actions. We are proposing this SNPRM 

to prevent failure of the fan case LP fuel 

tube, which could lead to an in-flight 

engine shutdown, loss of thrust control, 

and damage to the airplane. 

DATES: We must receive comments by 

June 22, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this SNPRM, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE24 8BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; 

Internet: https://www.aeromanager.com. 

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–2014– 

0363; 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 proposed 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 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this SNPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0363; Directorate Identifier 2014– 

NE–08–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this SNPRM. We will 

consider all comments received by the 

closing date and may amend this 

SNPRM based on 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 with FAA 

personnel concerning this SNPRM. 

Discussion 

We issued an 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 July 3, 2014 (79 FR 37965). 

The NPRM proposed to require 

inspection of the fan case LP fuel tubes 

and clips and the FOHE mounts and 

hardware. 

Related Service Information under 1 

CFR Part 51 

We reviewed RR Alert NonModification Service Bulletin (NMSB) 

No. RB.211–73–AH522, Revision 2, 

dated July 18, 2014; RR NMSB No. 

RB.211–73–AH837, initial issue, dated 

September 9, 2014; and RR NMSB No. 

RB.211–73–G848, Revision 3, dated 

June 12, 2014. This service information 

describes procedures for inspecting, and 

replacing if required, the fan case LP 

fuel tube and clips, and the FOHE 

mounts and hardware. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or see ADDRESSES for other 

ways to access this service information. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the NPRM (79 FR 

37965, July 3, 2014), RR received reports 

of additional failures of clips associated 

with the LP fuel tube occurring prior to 

the next inspection as required by the 

NPRM. RR published NMSB No. 

RB.211–73–AH837, initial issue, dated 

September 9, 2014, to provide 

instructions for additional specific 

visual inspections, at shorter intervals, 

of the upper clip attaching feature and 

the bracket holding this clip to the oil 

tank and, based on inspection results, 

instructions for corrective actions. The 

European Aviation Safety Agency 

(EASA) also issued EASA AD 2014– 

0243, dated November 6, 2014, and 

EASA AD 2014–0243R1, dated 

December 10, 2014, which mandate 

additional inspections and corrective 

actions, grant credit for certain prior 

inspections, allow a certain in-shop 

inspection to serve in lieu of a required 

visual inspection, and state that 

replacing parts as a result of the 

inspections required by those EASA 

ADs, and as described in paragraphs 

(e)(1), (e)(2), and (e)(3) of this AD, are 

not terminating action. We reviewed 

EASA’s changes and concluded that 

they are necessary to correct the unsafe 

condition this SNPRM addresses. We 

incorporate EASA’s changes into 

paragraphs (e)(1) and (e)(4) of this 

SNPRM. 

In addition to these changes, we made 

other changes. 

Since we issued the NPRM (79 FR 

37965, July 3, 2014), we found that we 

referenced a non-existent fan case LP 

fuel tube P/N in the NPRM. Specifically, 

fan case LP fuel tube, P/N FW535776, 

does not exist. We changed paragraph 

(e)(3) of this SNPRM to eliminate the 

non-existent part number, replacing it 

with the correct one for the fan case LP 

fuel tube, P/N FW53576. 

We also found that we did not include 

in our cost estimate an estimate of the 

number of engines that we expect will 

fail the proposed inspections. We 

revised our cost estimate in this SNPRM 

by adding an estimate of the number of 

engines that we expect will fail 

inspection, and the cost of replacement 

parts. 

We also found that we did not 

provide adequate information to 

identify the applicable engines affected 

by this AD. We changed the 

Applicability paragraph to specify that 

certain engine models outfitted with fan 

case LP fuel tube, P/N FW53576, when 

installed by incorporating either RR 

production modification 73–F343, or RR 

Service Bulletin (SB) No. RB.211–73– 

F343, Revision 4, dated May 26, 2011, 

are affected by this SNPRM. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 


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Federal Register / Vol. 80, No. 76 / Tuesday, April 21, 2015 / Proposed Rules 22139 

AD. We received no comments on the 

NPRM (79 FR 37965, July 3, 2014). 

FAA’s Determination 

We are proposing this SNPRM 

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. Certain changes 

described above expand the scope of the 

NPRM (79 FR 37965, July 3, 2014). As 

a result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

the NPRM, except as discussed in the 

Actions Since Previous NPRM was 

Issued paragraph. 

Costs of Compliance 

We estimate that this proposed AD 

affects about 50 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 6 

hours per engine to comply with this 

proposed AD. The average labor rate is 

$85 per hour. We also estimate that 25 

of the engines will fail the inspection 

proposed by this AD. Required parts 

cost about $4,031 per engine. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $126,275. 

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), 

(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): 

Rolls-Royce plc: Docket No. FAA–2014– 

0363; Directorate Identifier 2014–NE– 

08–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RB211 Trent 768–60, 772–60, and 772B–60 

turbofan engines, if fitted with fuel tube, part 

number (P/N) FW53576, which was 

incorporated through RR production 

modification 73–F343 or which were 

modified in service in accordance with RR 

Service Bulletin (SB) No. RB.211–73–F343, 

Revision 4, dated May 26, 2011, or earlier 

versions. 

(d) Reason 

This AD was prompted by fuel leaks 

caused by damage to the fan case lowpressure (LP) fuel tube. We are issuing this 

AD to prevent failure of the fan case LP fuel 

tube, which could lead to an in-flight engine 

shutdown, loss of thrust control, and damage 

to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 800 flight hours (FH) after the 

effective date of this AD, and thereafter at 

intervals not to exceed 800 FH, inspect the 

clip at the uppermost fan case LP fuel tube 

clip position, CP4881, and support bracket, 

P/N FW26692. Use Accomplishment 

Instructions, paragraph 3.A, of RR NonModification Service Bulletin (NMSB) No. 

RB.211–73–AH837, initial issue, dated 

September 9, 2014, or paragraph 3.A. or 3.B. 

of RR NMSB No. RB.211–73–AH522, 

Revision 2, dated July 18, 2014, or earlier 

versions, to do your inspection. 

(i) If the clip at the uppermost clip 

position, CP4881, fails inspection, replace 

the clip with a part eligible for installation 

and, before further flight, inspect the fan case 

LP fuel tube, P/N FW53576, for fretting, and 

clips for cracks or failure, according to 

Accomplishment Instructions, paragraph 3.A. 

of RR NMSB No. RB.211–73–AH837, initial 

issue, dated September 9, 2014, or paragraph 

3.A. or 3.B. of RR NMSB No. RB.211–73– 

AH522, Revision 2, dated July 18, 2014, or 

earlier versions. 

(ii) If the support bracket, P/N FW26692, 

fails inspection, replace the bracket before 

further flight with a part eligible for 

installation and inspect the fan case LP fuel 

tube, P/N FW53576, and clips for cracks or 

failure. 

(2) Within 4,000 FH since new or 800 FH, 

whichever occurs later, after the effective 

date of this AD, and thereafter at intervals not 

to exceed 4,000 FH, inspect the fan case LP 

fuel tube, P/N FW53576, and clips, and the 

fuel oil heat exchanger (FOHE) mounts and 

hardware, for damage, wear, or fretting. Use 

paragraph 3.A. or 3.B., Accomplishment 

Instructions, of RR Alert NMSB No. RB.211– 

73–AH522, Revision 2, dated July 18, 2014, 

or earlier versions, to do the inspection. 

(i) If the fan case LP fuel tube, P/N 

FW53576, fails inspection, before further 

flight, replace the fuel tube and clips with 

parts eligible for installation. 

(ii) If any FOHE mount or hardware shows 

signs of damage, wear, or fretting, replace the 

damaged part before further flight with a part 

eligible for installation. 

(3) At each shop visit after the effective 

date of this AD, inspect the fan case LP fuel 

tubes, P/Ns FW26589, FW36335, FW26587, 

FW53577, and FW53576, and clips, and the 

FOHE mounts and hardware, for damage, 

wear, or fretting. Use paragraphs 3.B.(1) and 

3.B.(2) of RR Alert NMSB No. RB.211–73– 

AH522, Revision 2, dated July 18, 2014, or 

earlier versions, to do the inspection. 

(i) If any fan case LP fuel tube fails 

inspection, replace the fuel tube and clips 

before further flight with parts eligible for 

installation. 

(ii) If any FOHE mount or hardware shows 

signs of damage, wear, or fretting, replace the 

damaged part before further flight with a part 

eligible for installation. 

(4) If you replace any fan case LP fuel tube, 

clip, or FOHE mount or hardware as a result 


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22140 Federal Register / Vol. 80, No. 76 / Tuesday, April 21, 2015 / Proposed Rules 

of the inspections of paragraphs (e)(1), (e)(2), 

or (e)(3) of this AD, you must still continue 

to perform the repetitive inspections of 

paragraphs (e)(1), (e)(2), and (e)(3) of this AD. 

(5) Any reports requested in the NMSB 

accomplishment instructions referenced in 

paragraphs (e)(1), (e)(2), and (e)(3) of this AD 

are not required by this AD. 

(f) Credit for Previous Actions 

If, before the effective date of this AD, you 

performed the inspections and corrective 

actions required by paragraph (e)(2) of this 

AD using RR NMSB No. RB.211–73–G848, 

Revision 3, dated June 12, 2014, or earlier 

versions, you met the initial inspection 

requirements of paragraph (e)(2) of this AD. 

(g) Definitions 

For the purposes of this AD: 

(1) 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, except that the 

separation of engine flanges solely for the 

purposes of transportation without 

subsequent engine maintenance is not an 

engine shop visit. 

(2) The fan case LP fuel tubes and clips, 

and the FOHE mounts and hardware, are 

eligible for installation if they have passed 

the inspection requirements of paragraphs 

(e)(1), (e)(2), and (e)(3) of this AD. 

(h) 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. You may email your 

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

(i) Related Information 

(1) 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. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0243R1, dated 

December 10, 2014 for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=FAA2014-0363. 

(3) RR Alert NMSB No. RB.211–73–AH522, 

Revision 2, dated July 18, 2014, and earlier 

versions; RR NMSB No. RB.211–73–AH837, 

initial issue, dated September 9, 2014; and 

RR NMSB No. RB.211–73–G848, Revision 3, 

dated June 12, 2014, and earlier versions; 

which are not incorporated by reference in 

this AD, can be obtained from Rolls-Royce 

plc, using the contact information in 

paragraph (i)(4) of this proposed AD. 

(4) For service information identified in 

this proposed AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 31, 

Derby, England, DE24 8BJ; phone: 011–44– 

1332–242424; fax: 011–44–1332–249936; 

email: http://www.rolls-royce.com/contact/

civil_team.jsp; Internet: https://

www.aeromanager.com. 

(5) 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. 

Issued in Burlington, Massachusetts, on 

April 7, 2015. 

Ann C. Mollica, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–09001 Filed 4–20–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1130; Directorate 

Identifier 2015–NE–04–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all Pratt 

& Whitney (PW) PW4164–1D, PW4168– 

1D, PW4168A–1D and PW4170 engines, 

and certain PW4164, PW4168, and 

PW4168A turbofan engines. This 

proposed AD was prompted by fuel 

nozzle-to-fuel supply manifold interface 

fuel leaks. This proposed AD would 

require inspecting fuel nozzles for signs 

of leakage, replacing hardware as 

required, and torqueing to specified 

requirement. We are proposing this AD 

to prevent fuel leaks which could result 

in engine fire and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

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–2014– 

1130; 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 proposed 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: 

Katheryn Malatek, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7747; fax: 781–238– 

7199; email: katheryn.malatek@faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this NPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–1130; Directorate Identifier 2015– 

NE–04–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

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 NPRM. 

Discussion 

We received reports of four fuel 

nozzle leaks in service and an 

additional six fuel nozzle leaks found 

during shop visits. The root cause is 

inadequate torque of the fuel nozzle-tofuel supply manifold B-nuts for the 

temperatures that the fuel nozzles 

experience. This condition, if not 

corrected, could result in engine fire 

and damage to the airplane. 


tkelley on DSK3SPTVN1PROD with PROPOSALS