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
9870 Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules 

Since we issued the existing AD, RRD 

has revised the approved published life 

limits of these parts to the same or 

higher limits as originally certified. 

DATES: We must receive comments on 

this proposed AD by April 23, 2012. 

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. 

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: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238– 

7199; email: mark.riley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD rescission. Send your 

comments to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2008–0224; Directorate Identifier 

2007–NE–44–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD rescission. 

We will consider all comments received 

by the closing date and may amend this 

proposed AD rescission 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 

rescission. 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 

On March 17, 2009, we issued AD 

2009–07–01 (74 FR 12086, March 23, 

2009). That AD requires reducing the 

published life limits of BR700–715 

turbofan engine HP turbine stage 1 

discs, P/Ns BRH20130 and BRH20131, 

and HP turbine stage 2 discs, P/Ns 

BRH19423 and BRH19427. 

Since we issued AD 2009–07–01 (74 

FR 12086, March 23, 2009), RRD has 

revised the approved published life 

limits of these HP turbine stage 1 discs 

to the same or higher limits as originally 

certified. The European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive Cancellation 

Notice 2007–0152–CN, dated December 

22, 2011. EASA stated in that 

Cancellation Notice that they have 

approved published life limits for the 

affected parts that are increased to the 

same or higher value as originally 

certified. We have evaluated the 

information provided by RRD and EASA 

and have determined that an unsafe 

condition no longer exists in these HP 

turbine stage 1 and stage 2 discs. 

FAA’s Determination and Requirements 

of This Proposed AD Rescission 

We are proposing this AD rescission 

of AD 2009–07–01 (74 FR 12086, March 

23, 2009) because we evaluated all 

information and determined that 

allowing the increase in the published 

part life limits is acceptable. This 

proposed AD would rescind AD 2009– 

07–01. 

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 a practice, method, 

or procedure necessary for safety in air 

commerce. 

Regulatory Findings 

We determined that this proposed AD 

rescission would not have federalism 

implications under Executive Order 

13132. This proposed AD rescission 

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 rescission of a 

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 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 rescission and placed 

it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 

rescinding airworthiness directive (AD) 

2009–07–01, Amendment 39–15860 (74 

FR 12086, March 23, 2009): 

Rolls-Royce Deutschland Ltd & Co KG 

(formerly BMW Rolls-Royce GmbH, 

formerly BMW Rolls-Royce Aero 

Engines): Docket No. FAA–2008–0224; 

Directorate Identifier 2007–NE–44–AD. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 34 / Tuesday, February 21, 2012 / Proposed Rules 9871 

(a) Comments Due Date 

We must receive comments by April 23, 

2012. 

(b) Affected ADs 

This AD rescinds AD 2009–07–01 (74 FR 

12086, March 23, 2009). 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1–30 

turbofan engines. 

Issued in Burlington, Massachusetts, on 

February 10, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–3864 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–2012–0143; Directorate 

Identifier 2011–NM–077–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 

airplanes. The existing AD currently 

requires revising the airworthiness 

limitations section (ALS) of the 

instructions for continued airworthiness 

for certain airplanes, and the FAAapproved maintenance program for 

certain other airplanes, to incorporate 

new limitations for fuel tank systems. 

Since we issued that AD, Fokker 

Services B.V. has revised a Fokker 70/ 

100 maintenance review board (MRB) 

document with revised limitations, 

tasks, thresholds, and intervals. This 

proposed AD would revise the 

maintenance program to incorporate the 

limitations, tasks, thresholds, and 

intervals specified in that Fokker MRB 

document. We are proposing this AD to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 6, 2012. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; email 

technicalservices.fokkerservices@

stork.com; Internet http://www.my

fokkerfleet.com. You may review copies 

of the referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, Washington. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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 (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

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–2012–0143; Directorate Identifier 

2011–NM–077–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 we receive 

about this proposed AD. 

Discussion 

On July 9, 2004, we issued AD 2004– 

15–08, Amendment 39–13742 (69 FR 

44586, July 27, 2004). This AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2004–15–08, 

Amendment 39–13742 (69 FR 44586, 

July 27, 2004): The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2011– 

0157, dated August 25, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Fokker Services have published issue 8 of 

report SE–623 dated 17 March 2011, which 

is part of the Airworthiness Limitations 

Section of the Instructions for Continued 

Airworthiness, referred to in Section 06, 

Appendix 1, of the Fokker 70/100 

Maintenance Review Board (MRB) document. 

The complete Airworthiness Limitations 

Section currently consists of: 

—Certification Maintenance Requirements 

(CMRs)—report SE–473, issue 8, 

—Airworthiness Limitation Items (ALIs) and 

Safe Life Items (SLIs)—report SE–623, 

issue 8, 

—Fuel ALIs and Critical Design 

Configuration Control Limitations 

(CDCCLs)—report SE–672, issue 2. 

The instructions contained in those reports 

have been identified as mandatory actions for 

continued airworthiness. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0046, which is superseded, and 

requires the implementation of the 

inspections and limitations as specified in 

the Airworthiness Limitation Section of the 

Instructions for Continued Airworthiness, 

referred to in Section 06, Appendix 1 of the 

Fokker 70/100 MRB document, reports SE– 

473, SE–623 and SE–672 at the abovementioned issues. 

You may obtain further information by 

examining the MCAI in the AD docket. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 


srobinson on DSK4SPTVN1PROD with PROPOSALS