Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 20505 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Pratt & Whitney Canada Corp. (formerly 

Pratt & Whitney Canada Inc.): Docket 

No. FAA–2013–0197; Directorate 

Identifier 2013–NE–09–AD. 

(a) Comments Due Date 

We must receive comments by June 4, 

2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) PW118A, PW118B, PW119B, 

PW119C, PW123, PW123B, PW123C, 

PW123D, PW123E, PW123AF, PW124B, 

PW125B, PW126A, PW127, PW127E, 

PW127F, PW127G, and PW127M turboprop 

engines with a 1st stage power turbine (PT) 

blade part number (P/N) 3120973–01, P/N 

3120983–01, or P/N 3054053–01 installed 

that has a serial number listed in Table 1 of 

the Appendix of P&WC Service Bulletin No. 

PW100–72–21823, Revision 3, dated March 

8, 2013. 

(d) Reason 

This AD was prompted by reports of 

fractures of the 1st stage PT blade. We are 

issuing this AD to prevent fracture of the 1st 

stage PT blade, possible engine fire, and 

damage to the airplane. 

(e) Actions and Compliance 

Unless already done, within 60 months 

after the effective date of this AD or when the 

affected PT blades are at module level 

exposure, whichever occurs first, do one of 

the following: 

(1) Replace the affected 1st stage PT blade 

with a blade eligible for installation; or 

(2) Perform a one-time X-ray inspection of 

the affected 1st stage PT blades, using 

paragraph 3.F.(2) of the Accomplishment 

Instructions of P&WC Service Bulletin No. 

PW100–72–21823, Revision 3, dated March 

8, 2013. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install into any engine any 1st stage PT blade 

that has not passed the inspection required 

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

(g) Definition 

For the purpose of this AD, module level 

exposure is when the affected engine is 

inducted into the engine shop, the PT 

module is removed from the engine, and 

access is available to the necessary 

subassembly. 

(h) Credit for Previous Actions 

If before the effective date of this AD, you 

inspected the 1st stage PT blades using 

earlier versions of P&WC Service Bulletin No. 

PW100–72–21823, Revision 3, dated March 

8, 2013, you met the inspection requirements 

in paragraph (e) of this AD. 

(i) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to Transport Canada 

Airworthiness Directive CF–2013–02, dated 

January 22, 2013, and P&WC Service Bulletin 

No. PW100–72–21823, Revision 3, dated 

March 8, 2012, for related information. 

(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. 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 

March 29, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07934 Filed 4–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0143; Directorate 

Identifier 2013–NE–06–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 certain 

Rolls-Royce plc (RR) RB211–524B–02; 

–524B2–19; –524B3–02; –524B4–02; 

–524C2–19; –524D4–19; –524D4–B–19; 

–524D4–39; –535C–37; –535E4–37; 

–535E4–B–37, and –535E4–B–75 

turbofan engines, and all RB211– 

524G2–19; –524G3–19; –524H2–19; and 

–524H–36 turbofan engines. This 

proposed AD was prompted by the 

discovery of a cracked and distorted 

front combustion liner (FCL) metering 

panel, which was made from the wrong 

material. This proposed AD would 

require a one-time inspection of the FCL 

metering panel to determine if it was 

made from N75 material and replacing 

it with one made from C263 material if 

it was made from N75 material. We are 

proposing this AD to prevent hot gas 

burning through the engine casing, 

which could result in an under-cowl fire 

and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by June 4, 2013. 

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 proposed AD, contact Rolls-Royce 

plc, Corporate Communications, P.O. 

Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from https:// 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
20506 Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 

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; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (phone: 800–647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: robert.green@faa.gov; phone: 

781–238–7754; fax: 781–238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0143; Directorate Identifier 

2013–NE–06–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued mandatory 

continuing airworthiness information 

(MCAI) AD 2012–0215R1, dated January 

4, 2013, to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During investigation of a starting problem 

with an RB211–535E4–B–37 engine, the Fuel 

Spray Nozzles (FSNs) appeared misaligned 

and the engine was removed. Further 

investigation found that the FSNs were 

correctly positioned but that the Front 

Combustion Liner (FCL) metering panel 

(reference Engine Illustrated Parts Catalogue 

(EIPC) section 72–41–13, Figure/Item 02– 

324) was cracked and distorted. Laboratory 

investigation revealed that the FCL metering 

panel was made of N75 material rather than 

the specified C263 material. 

Rolls-Royce (RR) issued SB RB.211–72– 

7221 in 1984, to address the issue of cracking 

of FCL metering panels manufactured in N75 

material. SB RB.211–72–7221 replaces the 

FCL metering panel manufactured in N75 

material with one manufactured in C263 

material. The FCL metering panel in socalled Phase 2 combustors of the RB211– 

524G/H and RB211–535C/E4/E4–B series 

engines was specified in C263 material from 

engine type at entry into service. 

Based on these findings, it was determined 

that installation of N75 material FCL 

metering panels on an engine where C263 

was the intended material, may result in 

metering panel cracking and distortion. 

This condition, if not prevented, 

could result in hot gas burning through 

the engine casing, which could result in 

an under-cowl fire and damage to the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

RR Alert Non-Modification Service 

Bulletin (NMSB) No. RB.211–72– 

AG046, Revision 3, dated December 6, 

2012, and Alert NMSB No. RB.211–72– 

AG183, Revision 3, dated December 6, 

2012. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require a one-time 

inspection of the FCL metering panel to 

determine if it was made from N75 

material, and replacing it with one made 

from C263 material if it was made from 

N75 material. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 315 RR turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 11 hours per engine to inspect the 

FCL metering panel on-wing. The 

average labor rate is $85 per hour. 

Required parts cost about $108,887 per 

engine. We anticipate that 12 FCL 

metering panels will fail inspection. 

Based on these figures, we estimate the 

cost of the proposed AD on U.S. 

operators to be $1,601,169. 

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); and 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 20507 

(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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 AD: 

Rolls-Royce plc: Docket No. FAA–2013– 

0143; Directorate Identifier 2013–NE– 

06–AD. 

(a) Comments Due Date 

We must receive comments by June 4, 

2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to: 

(1) All Rolls-Royce plc (RR) RB211–524G2– 

19; –524G3–19; –524H2–19; and –524H–36 

turbofan engines. 

(2) RR RB211–524B–02; –524B2–19; 

–524B3–02; –524B4–02; –524C2–19; 

–524D4–19; –524D4–B–19; and –524D4–39 

that have incorporated RR Service Bulletin 

(SB) No. RB.211–72–7221, dated December 7, 

1984. 

(3) All RR RB211–535C–37; –535E4–37; 

–535E4–B–37, and –535E4–B–75 turbofan 

engines, except those engines that have 

incorporated RR SB No. RB.211–72–C230, 

dated November 16, 1999, or Revision 1, 

dated November 22, 2012. 

(4) This AD does not apply to engines 

listed in paragraphs (c)(1) through (c)(3): 

(i) That have installed a front combustion 

liner (FCL) metering panel delivered from RR 

after April 23, 2011; or 

(ii) That were inspected before the effective 

date of this AD using RR Alert NonModification Service Bulletin (NMSB) No. 

RB.211–72–AF572, dated October 15, 2007, 

or Revision 1, dated October 8, 2008, or 

Revision 2, dated April 2, 2009, or RR 

Repeater Technical Variance No. 75295, Issue 

1, dated April 20, 2007. 

(d) Reason 

This AD was prompted by the discovery of 

a cracked and distorted FCL metering panel, 

made from the wrong material. We are 

issuing this AD to prevent hot gas burning 

through the engine casing, which could 

result in an under-cowl fire and damage to 

the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) At the next engine shop visit or within 

625 flight cycles, whichever occurs first after 

the effective date of this AD, perform a onetime inspection of the FCL metering panel to 

determine if it was made from N75 material, 

and replace it if made from N75 material, 

with one made from C263 material. 

(2) To inspect RB211–524 series turbofan 

engines, use Section 3., Accomplishment 

Instructions, of Alert NMSB No. RB.211–72– 

AG183, Revision 3, dated December 6, 2012, 

except reporting requirement paragraph 2 of 

Appendices 1 and 2 of that Alert NMSB. 

(3) To inspect RB211–535 series turbofan 

engines, use Section 3., Accomplishment 

Instructions, of Alert NMSB No. RB.211–72– 

AG046, Revision 3, dated December 6, 2012, 

except reporting requirement paragraph 2 of 

Appendices 1 and 2 of that Alert NMSB. 

(f) Definitions 

For the purpose of this AD, a shop visit is 

the induction of an engine into the shop for 

maintenance or overhaul. The separation of 

engine flanges solely for the purposes of 

transporting the engine without subsequent 

engine maintenance does not constitute an 

engine shop visit. 

(g) 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. 

(h) 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; 

email: robert.green@faa.gov; phone: 781– 

238–7754; fax: 781–238 7199. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0215R1, dated January 4, 

2013, RR Alert NMSB No. RB.211–72– 

AG183, Revision 3, dated December 6, 2012, 

and Alert NMSB No. RB.211–72–AG046, 

Revision 3, dated December 6, 2012, for 

related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

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

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

civil_team.jsp, or download the publication 

from 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. 

Issued in Burlington, Massachusetts, on 

March 29, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07930 Filed 4–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0052; Directorate 

Identifier 2013–NE–02–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 

Rolls-Royce plc (RR) RB211–535E4–37, 

RB211–535E4–B–37, RB211–535E4–C– 

37, and RB211–535E4–B–75 turbofan 

engines. This proposed AD was 

prompted by RR updating the low-cyclefatigue life analysis for the low pressure 

turbine (LPT) stage 2 discs. This 

proposed AD would require removal of 

affected parts using a drawdown plan. 

We are proposing this AD to prevent 

LPT stage 2 disc failure, which could 

result in uncontained engine damage 

and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by June 4, 2013. 

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 AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; or download the 

publication from https:// 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS