4648 Federal Register / Vol. 77, No. 20 / Tuesday, January 31, 2012 / Rules and Regulations 

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 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this 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. 

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 AD: 

2012–02–12 Bombardier, Inc.: Amendment 

39–16935. Docket No. FAA–2012–0037; 

Directorate Identifier 2012–NM–003–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 15, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes; 

certificated in any category; serial numbers 

4095 through 4391 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

(e) Reason 

This AD was prompted by multiple reports 

of the loss of certain alternating current (AC) 

systems caused by a burnt AC power wire 

bundle. We are issuing this AD to prevent the 

loss of ice protection systems for the angle of 

attack vanes, pitot probes, engine inlets, and 

windshields, and consequent loss of or 

misleading airspeed indication and increased 

workload for the flight crew, which could 

lead to loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection and Corrective Actions 

Within 400 flight hours or 60 days, 

whichever occurs first, after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) Do a detailed inspection of the affected 

AC power wire bundle for damage (any 

foreign object damage (FOD), damage due to 

sharp bends and kinking or deterioration, 

insulation cracking, evidence of heat damage 

to the insulation, and chafing) and do all 

applicable repairs, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–24–52, dated November 

22, 2011. Do all applicable repairs before 

further flight. 

(2) Segregate the AC power wire bundle 

into two bundles and install Teflon tubing, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–24–52, dated November 22, 2011. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to Attn: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone (516) 228–7300; fax (516) 794– 

5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–46, dated December 20, 

2011; and Bombardier Service Bulletin 84– 

24–52, dated November 22, 2011; for related 

information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Bombardier Service Bulletin 84–24–52, 

dated November 22, 2011. 

(2) For Bombardier, Inc. service 

information identified in this AD, contact 

Bombardier, Inc., Q–Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone (416) 

375–4000; fax (416) 375–4539; email 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

23, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–1993 Filed 1–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0994; Directorate 

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

16934; AD 2012–02–11] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–535 Series Turbofan 

Engine 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 


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Federal Register / Vol. 77, No. 20 / Tuesday, January 31, 2012 / Rules and Regulations 4649 

all RR RB211–535E4–37, –535E4–B–37, 

–535E4–B–75, and –535E4–C–37 

turbofan engines. That AD currently 

requires performing initial and 

repetitive visual and fluorescent 

penetrant inspections (FPI) of the lowpressure (LP) turbine stage 1, 2, and 3 

discs to detect cracks in the discs. This 

new AD continues to require those 

inspections and changes the definition 

of a shop visit to be less restrictive. This 

AD was prompted by our finding that 

the definition of shop visit in the 

existing AD was too restrictive. We are 

issuing this AD to revise the definition 

of shop visit and to detect cracks in the 

LP turbine stage 1, 2, and 3 discs, which 

could result in an uncontained release 

of LP turbine blades and damage to the 

airplane. 

DATES: This AD is effective March 6, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; phone: 011 44 

1332 242424, fax: 011 44 1332 249936; 

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

contact/civil_team.jsp, or download the 

publication from https:// 

www.aeromanager.com. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7143; fax: (781) 

238–7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–11–08, 

amendment 39–16707 (76 FR 30529, 

May 26, 2011). That AD applies to the 

specified products. The NPRM was 

published in the Federal Register on 

October 25, 2011 (76 FR 65997). That 

NPRM proposed to continue to require 

performing an initial FPI on the LP 

turbine stage 1, 2, and 3 discs at the next 

engine shop inspection after the 

effective date of that AD. That NPRM 

also continued to require repetitive 

inspections at each engine shop visit 

after accumulating 1,500 cycles since 

last inspection of the LP turbine stage 1, 

2, and 3 discs. That NPRM also 

proposed to change the definition of a 

shop visit to be less restrictive. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 65997, October 25, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects about 

588 RB211–535 series turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it will take about 

30 work-hours per product to comply 

with this AD. The average labor rate is 

$85 per work-hour. No parts are 

required. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $1,499,400. 

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) 

2011–11–08, Amendment 39–16707 (76 

FR 30529, May 26, 2011, and adding the 

following new AD: 

2012–02–11 Rolls-Royce plc: Amendment 

39–16934; Docket No. FAA–2009–0994; 

Directorate Identifier 2009–NE–39–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 6, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–11–08, 

Amendment 39–16707 (76 FR 30529, May 26, 

2011). 

(c) Applicability 

This AD applies to Rolls-Royce plc RB211– 

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

–535E4–C–37 turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by our 

determination that the definition of ‘‘shop 

visit’’ in the existing AD is too restrictive, in 


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4650 Federal Register / Vol. 77, No. 20 / Tuesday, January 31, 2012 / Rules and Regulations 

that it would require operators to inspect 

more often than required to ensure safety. We 

are issuing this AD to revise the definition of 

shop visit and to detect cracks in the lowpressure (LP) turbine stage 1, 2, and 3 discs, 

which could result in an uncontained release 

of LP turbine blades and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Initial Inspection Requirements 

At the next engine shop visit after the 

effective date of this AD, perform a visual 

and a fluorescent penetrant inspection of the 

LP turbine stage 1, 2, and 3 discs. 

(2) Repeat Inspection Requirements 

At each engine shop visit after 

accumulating 1,500 cycles since the last 

inspection of the LP turbine stage 1, 2 and 

3 discs, repeat the inspections specified in 

paragraph (e)(1) of this AD. 

(3) Remove Cracked Discs 

If you find cracks, remove the disc from 

service. 

(f) Definitions 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is induction of an engine into the 

shop for any purpose where: 

(1) All the blades are removed from the 

high-pressure (HP) compressor discs and the 

HP turbine disc, or 

(2) All the blades are removed from the 

intermediate pressure turbine disc. 

(g) 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. 

(h) Related Information 

(1) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7143; fax: (781) 

238–7199; email: alan.strom@faa.gov, for 

more information about this AD. 

(2) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0244, dated November 9, 2009, and RollsRoyce plc Alert Service Bulletin No. RB.211– 

72–AG272 for related information. Contact 

Rolls-Royce plc, P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; phone: 011 44 1332 

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

http://www.rollsroyce.com/contact/ 

civil_team.jsp, for a copy of this service 

information or download the publication 

from https://www.aeromanager.com. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

January 25, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1954 Filed 1–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0068; Directorate 

Identifier 2010–NE–05–AD; Amendment 39– 

16930; AD 2012–02–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (ADs) 

for General Electric Company (GE) CF6– 

45 and CF6–50 series turbofan engines 

with certain low-pressure turbine (LPT) 

rotor stage 3 disks installed. The 

existing ADs currently require 

inspections of high-pressure turbine 

(HPT) and LPT rotors, engine checks, 

and vibration surveys. This new AD 

retains the requirements of the two ADs 

being superseded, adds an optional LPT 

rotor stage 3 disk removal after a failed 

HPT blade borescope inspection (BSI) or 

a failed engine core vibration survey, 

establishes a new lower life limit for the 

affected LPT rotor stage 3 disks, and 

requires removing these disks from 

service at times determined by a 

drawdown plan. This AD was prompted 

by the determination that a new lower 

life limit for the LPT rotor stage 3 disks 

is necessary. We are issuing this AD to 

prevent critical life-limited rotating 

engine part failure, which could result 

in an uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective March 6, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 22, 2011 (76 FR 6323, 

February 4, 2011). 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, GE-Aviation, Room 

285, 1 Neumann Way, Cincinnati, OH 

45215, phone: (513) 552–3272; email: 

geae.aoc@ge.com. 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 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: 

Tomasz Rakowski, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7735; fax: (781) 238– 

7199; email: tomasz.rakowski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–02–07, 

Amendment 39–16580 (76 FR 6323, 

February 4, 2011) and AD 2011–18–01, 

Amendment 39–16783 (76 FR 52213, 

August 22, 2011). Those ADs apply to 

the specified products. The NPRM 

published in the Federal Register on 

October 19, 2011 (76 FR 64844). That 

NPRM proposed to retain the 

requirements of AD 2011–02–07 and AD 

2011–18–01, except that reporting to the 

FAA would no longer be required and 

there would be an optional LPT rotor 

stage 3 disk removal after a failed HPT 

blade BSI or a failed engine core 

vibration survey. That NPRM also 

proposed to establish a new lower life 

limit for the LPT rotor stage 3 disk part 

numbers listed in Table 1 of the 

proposed AD, and proposed to require 

removing these disks from service at 

times determined by a drawdown plan. 

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. 

Support for the NPRM as Written 

One commenter, The Boeing 

Company, supports the NPRM (76 FR 

64844, October 19, 2011) as written. 


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