Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 69037 

FAA–2014–0256; Directorate Identifier 

2013–NM–214–AD. 

(a) Effective Date 

This AD is effective December 26, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200LR, –300, –300ER, and 777F 

series airplanes, certificated in any category, 

as identified in Boeing Special Attention 

Service Bulletin 777–27–0115, dated May 22, 

2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of dual 

pitch rate sensor (PRS) failures causing the 

primary flight computers to transition from 

primary mode to secondary mode, resulting 

in autopilot disconnects. We are issuing this 

AD to prevent a dual PRS failure that could 

cause an automatic disengagement of the 

autopilot and autoland, which may prevent 

continued safe flight and landing if 

disengagement occurs at low altitude and the 

flight crew is unable to safely assume control 

and execute a go-around or manual landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 60 months after the effective date 

of this AD, inspect to determine the part 

numbers of all four PRSs, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–27– 

0115, dated May 22, 2013. For airplanes in 

group 1, as identified in Boeing Special 

Attention Service Bulletin 777–27–0115, 

dated May 22, 2013: A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the PRS 

can be conclusively determined from that 

review. 

(h) Replacement 

If any PRS having P/N 402875–05–01 is 

found during the inspection required by 

paragraph (g) of this AD: Before further flight, 

replace with a PRS having P/N 402875–03– 

01, in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–27–0115, dated May 22, 

2013. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a PRS having P/N 

402875–05–01 on any airplane. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(k) Related Information 

For more information about this AD, 

contact Douglas Tsuji, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6546; fax: 425–917– 

6590; email: douglas.tsuji@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 777–27–0115, dated May 22, 2013. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26831 Filed 11–19–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0489; Directorate 

Identifier 2014–NM–048–AD; Amendment 

39–18022; AD 2014–23–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by a 

report indicating that inboard and 

outboard hydraulic lines of the brakes 

were found connected to the incorrect 

ports on the swivel assembly of the 

main landing gear (MLG). This AD 

requires modifying the MLG by 

installing a new bracket on the left and 

right lower aft-wing planks. We are 

issuing this AD to prevent incorrect 

installation of the brake hydraulic lines, 

which could cause the brakes and the 

anti-skid system to operate incorrectly, 

and consequent catastrophic failure of 

the airplane during a high-speed 

rejected takeoff. 

DATES: This AD becomes effective 

December 26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 26, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0489 or in 

person at the Docket 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. 

For service information identified in 

this AD, contact contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 


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69038 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7303; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes. The NPRM published in 

the Federal Register on August 4, 2014 

(79 FR 45135). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–10, 

dated February 12, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. The MCAI states: 

Cases of inboard and outboard hydraulic 

brake lines connected to the incorrect port of 

the swivel assembly on the main landing gear 

were found in service, including a runway 

overrun event. Cross-connected brake 

hydraulic lines can cause the brakes and/or 

the anti-skid system to operate incorrectly. 

During a high speed rejected take-off, 

inability for the brakes to operate correctly 

could be catastrophic. 

This [Canadian] AD mandates the 

modification to prevent inadvertent crossconnection of the inboard and outboard 

hydraulic brake lines. 

The required action in this AD 

includes installing a new bracket on the 

left and right lower aft-wing planks of 

the MLG. You may examine the MCAI 

in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0489- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 45135, August 4, 2014) 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 this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

45135, August 4, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 45135, 

August 4, 2014). 

Costs of Compliance 

We estimate that this AD affects 526 

airplanes of U.S. registry. 

We also estimate that it will take 

about 6 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $375 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $465,510, or 

$885 per product. 

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 that 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; 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0489; 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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2014–23–06 Bombardier, Inc.: Amendment 

39–18022. Docket No. FAA–2014–0489; 

Directorate Identifier 2014–NM–048–AD. 

(a) Effective Date 

This AD becomes effective December 26, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report 

indicating that inboard and outboard 

hydraulic lines of the brakes were found 

connected to the incorrect ports on the 

swivel assembly of the main landing gear 

(MLG). We are issuing this AD to prevent 

incorrect installation of the brake hydraulic 

lines, which could cause the brakes and the 

anti-skid system to operate incorrectly, and 

consequent catastrophic failure of the 

airplane during a high-speed rejected takeoff. 


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Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 69039 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 6,600 flight hours after the effective 

date of this AD, but no later than 36 months 

after the effective date of this AD: Modify the 

MLG by installing a new bracket on the left 

and right lower aft-wing planks, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–32–110, dated December 19, 2013. 

(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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–10, dated 

February 12, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0489-0002. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 601R–32– 

110, dated December 19, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26985 Filed 11–19–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0472; Directorate 

Identifier 2013–SW–040–AD; Amendment 

39–18018; AD 2014–23–02] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters (Type Certificate 

Currently Held by AgustaWestland 

S.p.A.) (Agusta) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Agusta Model A109E, A109K2, A119, 

and AW119 MKII helicopters. This AD 

requires repetitively performing a 

magnetic particle inspection of the 

Gleason crown for a crack. This AD was 

prompted by a report of a crack that was 

found on a Gleason crown, which if not 

detected, could cause damage to or loss 

of the main rotor drive and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective December 

26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 26, 2014. 

ADDRESSES: For service information 

identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: 

Maurizio D’Angelo; telephone 39–0331– 

664757; fax 39–0331–664680; or at 

http://www.agustawestland.com/

technical-bullettins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

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 AD, the European 

Aviation Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 16, 2014, at 79 FR 41462, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Agusta Model A109E, A109K2, A119, 

and AW119 MKII helicopters with a 

main transmission, part number (P/N) 

109–0400–03–103, 109–0400–05–103, 

and 109–0400–03–109, with a Gleason 

crown, P/N 109–0403–07–103, installed. 

The NPRM proposed to require, for 

main transmissions with 2,400 or more 

hours time-in-service (TIS), performing 

repetitive magnetic particle inspections 

of the Gleason crown for a crack. If there 

is a crack, the NPRM proposed replacing 

the Gleason crown assembly before 

further flight. The NPRM also proposed 

to prohibit installing a Gleason crown, 

P/N 109–0403–07–103, or a Gleason 

crown assembly, P/N 109–0401–27–101 

or P/N 109–0401–27–109, on any 

helicopter. The proposed requirements 

were intended to detect a crack, which 

could cause damage to or loss of the 

main rotor drive and subsequent loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2013–0118, dated June 3, 2013, issued 

by EASA, which is the Technical Agent 


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