13526 Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 

(e) Required Actions 

Within 10 hours time-in-service, replace 

the 3.2 mm rivets, part-number (P/N) 

21215DC3200J, of the RH and LH 

longitudinal beams Y350 of the bottom 

structure with 4.8 mm rivets, P/N 

21215DC4800J, as shown in Figures 2 and 3 

of Eurocopter Emergency Alert Service 

Bulletin No. 01.00.81, Revision 0, dated 

March 19, 2012. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2012–0046–E, dated 

March 21, 2012. You may view the EASA AD 

on the Internet at www.regulations.gov in 

Docket No. FAA–2013–0573. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5314: Fuselage Main, Keel. 

(i) 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 No. 01.00.81, Revision 0, dated 

March 19, 2012. 

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

Emergency Alert Service Bulletin No. 

01.00.81, Revision 0, dated March 19, 2012, 

is co-published as one document along with 

Eurocopter Emergency Alert Service Bulletin 

No. 01.00.46, Revision 0, dated March 19, 

2012, which is not incorporated by reference 

in this AD. 

(ii) Reserved. 

(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. 2014–04697 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–2013–0477; Directorate 

Identifier 2011–SW–015–AD; Amendment 

39–17780; AD 2014–05–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Type Certificate 

Previously Held by Eurocopter France) 

(Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2010–11– 

51 for Eurocopter France (Eurocopter) 

Model AS350B, BA, B1, B2, C, D, and 

D1 helicopters and Model AS355E, F, 

F1, F2, and N helicopters with certain 

part-numbered tail gearbox (TGB) 

control levers installed. AD 2010–11–51 

required repetitive visual inspections of 

the TGB control lever for a crack and 

replacing a cracked TGB control lever 

with an airworthy TGB control lever. 

This new AD retains the requirements of 

AD 2010–11–51 and also requires 

inspecting other areas of the TGB 

control lever not previously inspected 

and at additional inspection intervals. 

This AD was prompted by several 

reports of cracking in a TGB control 

lever. The actions of this AD are 

intended to prevent failure of the TGB 

control lever, loss of tail rotor control, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective April 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 15, 2014. 

ADDRESSES: For 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. 

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: 

Robert Grant, Aviation Safety Engineer, 

Rotorcraft Directorate, Safety 

Management Group, 2601 Meacham 

Blvd., Fort Worth, TX 76137, telephone 

817–222–5110, email robert.grant@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–11–51, 

Amendment 39–16396 (75 FR 50874, 

August 18, 2010). AD 2010–11–51 

applied to Eurocopter Model AS350B, 

BA, B1, B2, C, D, and D1 helicopters 

and Model AS355E, F, F1, F2, and N 

helicopters with certain part-numbered 

tail gearbox (TGB) control levers 

installed. The NPRM published in the 

Federal Register on June 17, 2013 (78 

FR 36129). The NPRM proposed to 

retain the requirements in AD 2010–11– 

51 to perform repetitive visual 

inspections in a certain area on each 

TGB control lever not marked with an 

‘‘X’’ and to replace a cracked part. Also, 

the NPRM proposed to require 

inspecting another area of each TGB 

control lever at additional intervals. The 

NPRM also proposed replacing 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 the applicability 

of the AD. The proposed requirements 

were intended to prevent failure of the 

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Federal Register / Vol. 79, No. 47 / Tuesday, March 11, 2014 / Rules and Regulations 13527 

TGB control lever, loss of tail rotor 

control, and subsequent loss of control 

of the helicopter. 

The NPRM was prompted by 

Emergency AD No. 2011–0038–E, dated 

March 4, 2011 (AD No. 2011–0038–E), 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for the Eurocopter Model 

AS350B, BA, BB, B1, B2, and D, and 

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

Emergency AD No. 2011–0038–E 

superseded EASA Emergency AD No. 

2010–0082–E, dated April 27, 2010 (AD 

No. 2010–0082–E). EASA advises that 

since issuing its Emergency AD No. 

2010–0082–E, Eurocopter found 

additional cracks opposite the required 

inspection area on the affected control 

levers. EASA Emergency AD No. 2011– 

0038–E retains the requirements of 

EASA Emergency AD No. 2010–082–E 

and adds repetitive inspections for the 

area opposite the control levers. 

Since we issued the NPRM, 

Eurocopter France changed its name to 

Airbus Helicopters. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 36129, June 17, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except for the name change 

previously described and correcting the 

date referenced for Revision 2 of the 

Eurocopter Emergency Alert Service 

Bulletin (EASB). These changes are 

consistent with the intent of the 

proposals in the NPRM (78 FR 36129, 

June 17, 2013) and will not increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Differences Between This AD and the 

EASA AD 

This AD differs from EASA 

Emergency AD No. 2011–0038–E as 

follows: 

• We include the Model AS350C and 

AS350D1 helicopters that may contain 

the affected TGB control lever. We do 

not include the Model AS350BB 

helicopter because it is not typecertificated in the United States. 

• We do not require an ‘‘after last 

flight’’of the day inspection. 

• We do not allow a pilot to inspect 

for a crack. 

• We do not require reworking 

noninstalled control levers. 

• We do not include a calendar 

compliance time for reworking the TGB 

control lever if there is not a crack. 

• We do not require you to contact 

Eurocopter (now Airbus Helicopters) if 

a crack is found during any inspection. 

Related Service Information 

Eurocopter issued one EASB, 

Revision 2, dated March 1, 2011, with 

four different numbers. EASB No. 

05.00.62 is for Model AS350 

helicopters; EASB No. 05.00.57 is for 

Model AS355 helicopters; EASB No. 

05.00.38 is for military Model AS550 

helicopters; and EASB No. 05.00.35 is 

for military Model AS555 helicopters. 

The military models are not typecertificated in the United States. The 

EASB specifies visually inspecting the 

TGB control lever for a crack at the last 

flight of each day, without exceeding 10 

flying hours between inspections. The 

EASB also specifies a rework procedure 

for affected TGB control levers, to be 

done within 660 flying hours and no 

later than June 30, 2011, indicated by 

marking the control lever with a letter 

‘‘X.’’ EASA classified this EASB as 

mandatory and issued AD No. 2011– 

0038–E to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

791 helicopters of U.S. registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. The inspections for a crack in 

the TGB control lever will take a 

minimal amount of time. Replacing a 

control lever will take about 3 work 

hours at an average labor rate of $85 per 

work hour. Required parts will cost 

about $2,103 per helicopter. Based on 

these figures, we estimate the total cost 

of the AD on U.S. operators to be $2,358 

per helicopter to replace the control 

lever. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 to the extent that it justifies 

making a regulatory distinction; 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 an economic 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: 

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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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