This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

9868 

Vol. 77, No. 34 

Tuesday, February 21, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1045; Directorate 

Identifier 2011–NE–32–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. 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 

Honeywell International Inc. models 

TFE731–4, –4R, –5, –5R, –5AR, and 

–5BR series turbofan engines. This 

proposed AD was prompted by a report 

of a rim/web separation of a first stage 

low-pressure turbine (LPT1) rotor 

assembly. This proposed AD would 

require replacing affected LPT1 rotor 

assemblies with LPT1 rotor assemblies 

eligible for installation. We are 

proposing this AD to prevent 

uncontained disk separation, leading to 

fuel tank penetration, fire, personal 

injury, and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by April 23, 2012. 

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 Honeywell 

Engines and Systems Technical 

Publications and Distribution, M/S 

2101–201, P.O. Box 52170, Phoenix, AZ 

85072–2170, phone: 602–365–2493 

(General Aviation), 602–365–5535 

(Commercial Aviation), fax: 602–365– 

5577 (General Aviation and Commercial 

Aviation). You may review copies of the 

referenced 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 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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210: email: 

joseph.costa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–1045; Directorate Identifier 2011– 

NE–32–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 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 proposed AD. 

Discussion 

We received a report of a rim/web 

separation on an LPT1 rotor disk, part 

number (P/N) 3075446–2, in a TFE731– 

5BR engine. The crack propagated in 

sustained peak strain low-cycle-fatigue, 

and accumulated 762 cycles-in-service 

(CIS) before failure. The current 

published life limit for this part is 

10,000 CIS. The most probable cause for 

this separation was due to LPT1 blade 

walking. This condition, if not 

corrected, could result in an 

uncontained disk separation, fuel tank 

penetration, fire, personal injury, and 

damage to the airplane. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

replacing affected LPT1 rotor assemblies 

with improved design LPT1 rotor 

assemblies that are eligible for 

installation. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 1,550 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 1 

work-hour per engine to perform the 

proposed actions at next access and 165 

work-hours per unscheduled engine 

disassembly, and that the average labor 

rate is $85 per work-hour. Replacement 

parts would cost about $175,000 per 

engine. Based on these figures, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $35,195,488 

per year. 

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: 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules 9869 

‘‘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, 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): 

Honeywell International Inc. (formerly 

AlliedSignal Inc., formerly Garret 

Turbine Engine Company): Docket No. 

FAA–2011–1045; Directorate Identifier 

2011–NE–32–AD. 

(a) Comments Due Date 

We must receive comments by April 23, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to Honeywell 

International Inc. model TFE731–5 series 

engines, with a first stage low-pressure 

turbine (LPT1) rotor assembly, part number 

(P/N) 3075184–2, 3075184–3, or 3075184–4, 

installed. 

(2) This AD also applies to Honeywell 

International Inc. models TFE731–5AR and 

–5BR series engines, with a first stage LPT1 

rotor assembly, P/N 3075447–1, 3075447–2, 

3075447–4, 3075713–1, 3075713–2, 

3075713–3, or 3074748–5, installed. 

(3) This AD also applies to Honeywell 

International Inc. models TFE731–4, –4R, 

–5AR, –5BR, and –5R series turbofan engines, 

with an LPT1 rotor assembly, P/N 3074748– 

4, 3074748–5, 3075447–1, 3075447–2, 

3075447–4, 3075713–1, 3075713–2, or 

3075713–3, installed. 

(d) Unsafe Condition 

This AD was prompted by a report of a 

rim/web separation of an LPT1 rotor 

assembly. We are issuing this AD to prevent 

uncontained disk separation, leading to fuel 

tank penetration, fire, personal injury, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Engines Installed in Dassault-Aviation 

Falcon 20 and Construcciones Aeronauticas, 

S.A. (CASA) 101 Airplanes 

(1) Remove the LPT1 rotor assembly at the 

next access to the LPT1 rotor assembly or at 

the next major periodic inspection, not to 

exceed 2,600 hours-in-service since last 

major periodic inspection, or 8 years after the 

effective date of this AD, whichever occurs 

first. 

(2) Install an LPT1 rotor assembly that is 

eligible for installation. 

(g) Engines Not Installed in DassaultAviation Falcon 20 or CASA 101 Airplanes 

(1) Remove the LPT1 rotor assembly at the 

next core zone inspection, not to exceed 

5,100 hours-in-service since last core zone 

inspection, or at the next time the LPT1 rotor 

disc is removed for cause, or 8 years after the 

effective date of this AD, whichever occurs 

first. 

(2) Install an LPT1 rotor assembly that is 

eligible for installation. 

(h) Definitions 

(1) For the purpose of this AD, ‘‘next 

access’’ is when the low-pressure tie rod is 

unstretched. 

(2) For the purpose of this AD, an LPT1 

rotor assembly ‘‘eligible for installation’’ is an 

LPT1 rotor assembly not having a P/N listed 

in this AD. 

(i) Installation Prohibition 

After the effective date of this AD, if the 

rotor assembly must be replaced as specified 

in paragraph (f)(1) or (g)(1) of this AD, do not 

install any LPT1 rotor assembly listed by P/ 

N in paragraphs (c)(1), (c)(2), and (c)(3) of 

this AD, into any engine. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures in 

14 CFR 39.19 to request an AMOC. 

(k) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210: email: joseph.costa@faa.gov. 

(2) Honeywell International Inc. Service 

Bulletin (SB) No. TFE731–72–3768, SB No. 

TFE731–72–3769, and SB No. TFE731–72– 

3770, pertain to the subject of this AD. 

Contact Honeywell Engines and Systems 

Technical Publications and Distribution, 

M/S 2101–201, P.O. Box 52170, Phoenix, AZ 

85072–2170, phone: 602–365–2493 (General 

Aviation), 602–365–5535 (Commercial 

Aviation), fax: 602–365–5577 (General 

Aviation and Commercial Aviation), for a 

copy of this service information. 

(3) You may review copies of the 

referenced 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 

February 3, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–3861 Filed 2–17–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0224; Directorate 

Identifier 2007–NE–44–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (RRD) 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM); rescission. 

SUMMARY: We propose to rescind an 

airworthiness directive (AD) for RRD 

BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 turbofan engines. 

The existing AD resulted from the need 

to reduce the published life limits of 

high-pressure (HP) turbine stage 1 discs, 

part numbers (P/Ns) BRH20130 and 

BRH20131, and HP turbine stage 2 

discs, P/Ns BRH19423 and BRH19427. 


srobinson on DSK4SPTVN1PROD with PROPOSALS