13528 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2010–11–51, Amendment 39–16396 (75 

FR 50874, August 18, 2010), and adding 

the following new AD: 

2014–05–07 Airbus Helicopters (Type 

Certificate Previously Held by 

Eurocopter France): Amendment 39– 

17780; FAA–2013–0477; Directorate 

Identifier 2011–SW–015–AD. 

(a) Applicability 

This AD applies to Model AS350B, BA, B1, 

B2, C, D, and D1 helicopters and Model 

AS355E, F, F1, F2, and N helicopters, with 

a tail gearbox (TGB) control lever, part 

number (P/N) 350A33–1058–00, P/N 

350A33–1058–01, P/N 350A33–1058–02, or 

P/N 350A33–1058–03, both with and without 

an ‘‘X’’ marked near the P/N, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the TGB control lever. This 

condition could result in failure of the TGB 

control lever, loss of tail rotor control, and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2010–11–51, 

Amendment 39–16396 (75 FR 50874, August 

18, 2010). 

(d) Effective Date 

This AD becomes effective April 15, 2014. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For helicopters with a lever not marked 

with an ‘‘X’’ near the P/N, within 10 hours 

time-in-service (TIS), and thereafter at 

intervals not to exceed 10 hours TIS, using 

a mirror and appropriate light source, 

visually inspect the TGB control lever for a 

crack as shown in area ‘‘A’’ of Figure 2 of 

Eurocopter Emergency Alert Service Bulletin 

No. 05.00.62, Revision 2, dated March 1, 

2011 (EASB No. 05.00.62), for Model AS350 

helicopters, and Eurocopter Emergency Alert 

Service Bulletin No. 05.00.57, Revision 2, 

dated March 1, 2011 (EASB No. 05.00.57), for 

Model AS355 helicopters. If there is a crack, 

before further flight, replace each cracked 

TGB control lever with a TGB control lever 

with a P/N not listed in paragraph (a) of this 

AD. 

(2) For Model AS355N helicopters, within 

110 hours TIS, or if the helicopter has 

reached 100 or more hours TIS, within the 

next 10 hours TIS, and thereafter at intervals 

not to exceed 110 hours TIS, using a mirror 

and appropriate light source, inspect each 

TGB control lever for a crack as shown in 

area ‘‘C’’ of Figure 8 of EASB No. 05.00.62 

or EASB No. 05.00.57, as applicable to your 

model helicopter. 

(3) Within 660 hours TIS, replace each 

TGB control lever with a reworked TGB 

control lever marked with an ‘‘X’’ near the P/ 

N or with a TGB control lever with a P/N not 

listed in paragraph (a) of this AD. 

(4) For all model helicopters except Model 

AS355N, within 660 hours TIS, or if the 

helicopter has reached 605 or more hours TIS 

within the next 55 hours TIS, and thereafter 

at intervals not to exceed 660 hours TIS, 

using a mirror and appropriate light source, 

inspect each TGB control lever for a crack as 

shown in area ‘‘C’’ of Figure 8 of EASB No. 

05.00.62 or EASB No. 05.00.57, as applicable 

to your model helicopter. 

(5) If there is a crack, before further flight, 

replace each cracked TGB control lever with 

a TGB control lever with a P/N not listed in 

paragraph (a) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Safety Management Group, 2601 

Meacham Blvd., Fort Worth, TX 76137, 

telephone (817) 222–5110, email 

robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Related Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2011–0038–E, dated 

March 4, 2011, and superseded EASA 

Emergency AD No. 2010–0082–E, dated April 

27, 2010. You may view the EASA AD on the 

Internet at http://www.regulations.gov in 

Docket No. FAA–2013–0477. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720 Tail Rotor Control System. 

(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 the AD specifies otherwise. 

(i) Eurocopter Emergency Alert Service 

Bulletin (EASB), No. 05.00.62, 

Revision 2, dated March 1, 2011. 

(ii) Eurocopter EASB No. 05.00.57, 

Revision 2, dated March 1, 2011. 

Note 1 to paragraph (j)(2): Eurocopter 

EASB No. 05.00.62, Revision 2, dated March 

1, 2011, and Eurocopter EASB No. 05.00.57, 

Revision 2, dated March 1, 2011, are copublished as one document along with 

Eurocopter EASB No. 05.00.38, Revision 2, 

dated March 1, 2011, and Eurocopter EASB 

No. 05.00.35, Revision 2, dated March 1, 

2011, which are not incorporated by 

reference in this AD. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on February 

26, 2014. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04729 Filed 3–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0798; Directorate 

Identifier 2013–NM–087–AD; Amendment 

39–17796; AD 2014–05–23] 

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 BD–100–1A10 

(Challenger 300) airplanes. This AD was 

prompted by multiple reports of erratic 

electrical status indications on the push 

button annunciators and the engine 

instrument and crew alerting system. 

Certain of those reported incidents 

resulted in the airplane experiencing a 

momentary loss of electrical power and 

loss of flight displays. This AD requires 

modification of the direct current power 

centers. We are issuing this AD to 

prevent loss of electrical power, which 

could result in the loss of flight displays 

and reduced controllability of the 

airplane. 

DATES: This AD becomes effective April 

15, 2014. 

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Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 13529 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0798; 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Systems and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone (516) 228–7301; 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 

BD–100–1A10 (Challenger 300) 

airplanes. The NPRM published in the 

Federal Register on September 25, 2013 

(78 FR 58965). The NPRM was 

prompted by multiple reports of erratic 

electrical status indications on the push 

button annunciators and the engine 

instrument and crew alerting system. 

Certain of those reported incidents 

resulted in the airplane experiencing a 

momentary loss of electrical power and 

loss of flight displays. The NPRM 

proposed to require modification of the 

direct current power centers. We are 

issuing this AD to prevent loss of 

electrical power, which could result in 

the loss of flight displays and reduced 

controllability of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–05, 

dated February 22, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

There have been multiple in-service 

reports of erratic electrical status indications 

on the Push Button Annunciators (PBA) and 

the Engine Instrument & Crew Alerting 

System (EICAS) while on-ground and during 

flight. Three of those reported incidents 

resulted in the aeroplane experiencing 

momentary loss of electrical power and loss 

of flight displays. 

The investigation revealed that improper 

insertion of a Printed Circuit Board (PCB) in 

a Direct Current Power Center (DCPC) may 

lead to erroneous electrical status indications 

on the PBAs and EICAS. The erroneous 

indications could mislead the pilots into 

turning off active generators and leading to 

partial or complete loss of electrical power. 

Loss of electrical power could result in the 

loss of flight displays and reduced 

controllability of the aeroplane. 

Further investigation determined that the 

design of the existing DCPC covers does not 

ensure that the PCBs will remain inserted 

into the motherboard of the DCPC. 

This [TCCA] AD mandates the 

modification of each DCPC to ensure that 

properly closed covers will retain the PCBs 

within the motherboards. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0798- 

0001. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 58965, September 25, 2013) 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 (78 FR 

58965, September 25, 2013) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 58965, 

September 25, 2013). 

Costs of Compliance 

We estimate that this AD affects 92 

airplanes of U.S. registry. 

We also estimate that it will take 

about 7 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 $1,568 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$198,996, or $2,163 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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-2013-0798; 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 

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13530 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 

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 AD: 

2014–05–23 Bombardier, Inc.: Amendment 

39–17796. Docket No. FAA–2013–0798; 

Directorate Identifier 2013–NM–087–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 15, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

certificated in any category, serial numbers 

20003 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical power. 

(e) Reason 

This AD was prompted by multiple reports 

of erratic electrical status indications on the 

push button annunciators and the engine 

instrument and crew alerting system. Certain 

of those reported incidents resulted in the 

airplane experiencing a momentary loss of 

electrical power and loss of flight displays. 

We are issuing this AD to prevent loss of 

electrical power, which could result in the 

loss of flight displays and reduced 

controllability 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) Direct Current Power Centers (DCPC) 

Modification 

For airplanes having serial numbers 20003 

through 20405 inclusive: Within 800 flight 

hours after the effective date of this AD or 

within 24 months after the effective date of 

this AD, whichever occurs first, modify the 

left-hand DCPC, right-hand DCPC, and 

auxiliary DCPC, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–24–23, dated November 

26, 2012. 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a DCPC having a part 

number specified in paragraphs (h)(1) 

through (h)(9) of this AD on any airplane, 

unless the DCPC serial number has a suffix 

‘‘R’’ beside the serial number. 

(1) 970GC02Y04. 

(2) 970GC02Y05. 

(3) 970GC02Y06. 

(4) 975GC02Y04. 

(5) 975GC02Y05. 

(6) 975GC02Y06. 

(7) 320GC03Y04. 

(8) 320GC03Y05. 

(9) 320GC03Y06. 

(i) 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, 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) 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 FAAapproved 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. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–05, dated 

February 22, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0798-0001. 

(k) 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 100–24–23, 

dated November 26, 2012. 

(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 February 

26, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04822 Filed 3–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0977; Directorate 

Identifier 2013–NM–190–AD; Amendment 

39–17795; AD 2014–05–22] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 717–200 

airplanes. This AD was prompted by 

multiple reports of cracking in the 

overwing frames. This AD requires 

repetitive inspections for cracking in the 

overwing frames, and corrective actions 

if necessary. We are issuing this AD to 

detect and correct such cracking, which 

could result in a severed frame and 

might increase the loading of adjacent 

frames, resulting in damage to the 

adjacent structure and consequent loss 

of structural integrity of the airplane. 

DATES: This AD is effective April 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 15, 2014. 

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