This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

38613 

Vol. 80, No. 129 

Tuesday, July 7, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0499; Directorate 

Identifier 2013–SW–061–AD; Amendment 

39–18198; AD 2015–13–11] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada (BHTC) 

Model 430 helicopters to require 

inspecting the tail rotor control tube 

assembly (control tube) and either 

repairing or replacing the control tube. 

This AD was prompted by two reports 

of failure of the control tube bonded 

clevis. The actions of this AD are 

intended to prevent failure of a control 

tube bonded clevis, which could lead to 

failure of the control tube and 

subsequent loss of helicopter control. 

DATES: This AD is effective August 11, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 11, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or 

at http://www.bellcustomer.com/files/. 

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. It is also available 

on the Internet at http://

www.regulations.gov in Docket No. 

FAA–2014–0499. 

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 Transport 

Canada Civil Aviation (TCCA) 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: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 30, 2014, at 79 FR 44147, 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 

BHTC Model 430 Helicopters, serial 

number 49001 through 49121, with 

control tube part number (P/N) 430– 

001–007–101 installed. The NPRM 

proposed to require inspecting the 

control tube and either repairing or 

replacing it. The proposed requirements 

were intended to prevent failure of a 

control tube bonded clevis, which could 

lead to failure of the control tube and 

subsequent loss of helicopter control. 

The NPRM was prompted by 

Canadian AD No. CF–2013–30, dated 

October 7, 2013, issued by TCCA, which 

is the aviation authority for Canada, to 

correct an unsafe condition for BHTC 

Model 430 helicopters with control tube 

P/N 430–001–007–101. TCCA advises of 

two failures of the control tube bonded 

clevis caused by cracking from control 

tube oscillation. TCCA states that this 

situation, if not corrected, could result 

in the loss of control of the helicopter. 

TCCA AD No. CF–2013–30 

consequently requires a one-time 

inspection of the control tube for 

damage and contacting BHTC for 

evaluation of the control tube if the 

damage exceeds allowable limits. If the 

tube is not damaged, the damage is 

within allowable limits, or BHTC 

Engineering determines the control tube 

can be returned to service, TCCA AD 

No. CF–2013–30 requires modifying the 

tube according to BHTC’s service 

information. TCCA AD No. CF–2013–30 

also requires replacing control tubes, P/ 

N 430–001–007–101, with control tube, 

P/N 430–001–007–105, no later than 12 

months from the effective date of its AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(79 FR 44147, July 30, 2014). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCCA, its 

technical representative, has notified us 

of the unsafe condition described in the 

TCCA AD. We are issuing this AD 

because we evaluated all information 

provided by TCCA 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. 

Differences Between This AD and the 

TCCA AD 

The TCCA AD requires submitting 

sketches of a control tube damaged 

beyond defined limits to BHTC for 

evaluation. BHTC then determines if the 

control tube can be returned to service. 

We make no such requirement in this 

AD. 

Related Service Information Under 1 

CFR Part 51 

Bell Helicopter Alert Service Bulletin 

(ASB) No. 430–13–51, dated September 

3, 2013, states that BHTC received two 

reports of control tube, P/N 430–001– 

007–101, failing because the clevis 

failed due to fatigue caused by control 

tube oscillation. ASB No. 430–13–51 

specifies a one-time inspection of 

control tube assembly, P/N 430–001– 

007–101, to verify if the tube has 

chaffing damage and indicated that a 


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38614 Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations 

mandatory replacement would follow 

when sufficient parts became available. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Other Related Service Information 

We reviewed Bell Helicopter 

Technical Bulletin 430–04–35, Revision 

B, dated March 20, 2009, which 

recommends that control tube, P/N 430– 

001–007–101, be replaced with control 

tube, P/N 430–001–007–105, if damage 

exists. On June 12, 2014, Bell issued 

Revision A to ASB No. 430–13–51, 

which set a compliance date of 

September 30, 2014, to remove control 

tube, P/N 430–001–007–101. 

Costs of Compliance 

We estimate that this AD affects 5 

helicopters of U.S. Registry and that 

labor costs average $85 a work hour. 

Based on these estimates, we expect the 

following costs: 

• The cost of inspecting the control 

tube is minimal. 

• Repairing the control tube requires 

2 work-hours for a labor cost of $170. 

• Replacing control tube, P/N 430– 

001–007–101, with control tube, P/N 

430–001–007–105, requires 3 workhours for a labor cost of $255. Parts cost 

$3,974 for a total cost per helicopter of 

$4,229. 

According to manufacturer’s service 

information, 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 by the manufacturer. 

Accordingly, 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 

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: 

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): 

2015–13–11 Bell Helicopter Textron 

Canada: Amendment 39–18198; Docket 

No. FAA–2014–0499; Directorate 

Identifier 2013–SW–061–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada (BHTC) Model 430 Helicopters, serial 

number 49001 through 49121, with control 

tube assembly (control tube), part number (P/ 

N) 430–001–007–101 installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue failure of a tail rotor control tube 

bonded clevis. This condition could result in 

failure of the tail rotor control tube and 

subsequent loss of helicopter control. 

(c) Effective Date 

This AD becomes effective August 11, 

2015. 

(d) 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. 

(e) Required Actions 

(1) Within 50 hours time-in-service (TIS), 

visually inspect each control tube for any 

damage, for any damage to the clevis, and to 

determine whether the clevis is correctly 

bonded to the control tube. 

(i) If a control tube and clevis have no 

damage or damage within acceptable limits 

and the clevis is correctly bonded to the 

control tube, repair the control tube by 

applying tape in accordance with the 

Accomplishment Instructions, Paragraph 5, 

of Bell Helicopter Alert Service Bulletin 430– 

13–51, dated September 3, 2013. 

(ii) If the control tube or clevis is damaged 

beyond acceptable limits or if the clevis is 

not correctly bonded to the control tube, 

replace control tube, P/N 430–001–007–101, 

with control tube, P/N 430–001–007–105. 

(2) Within 250 hours TIS, replace each 

control tube, P/N 430–001–007–101, with 

control tube, P/N 430–001–007–105. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Fuller, 

Senior Aviation Safety Engineer, Safety 

Management Group, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matthew.fuller@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 

(1) Bell Helicopter Technical Bulletin 430– 

04–35, Revision B, dated March 20, 2009, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information, 

contact Bell Helicopter Textron Canada 

Limited, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or at 

http://www.bellcustomer.com/files/. You may 

view this service information at FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2013–30, dated October 7, 2013. You 

may view the TCCA AD on the Internet at 


srobinson on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 129 / Tuesday, July 7, 2015 / Rules and Regulations 38615 

http://www.regulations.gov in Docket No. 

FAA–2014–0499. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Control 

(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) Bell Helicopter Alert Service Bulletin 

430–13–51, dated September 3, 2013. 

(ii) Reserved. 

(3) For Bell Helicopter Textron Canada 

Limited service information identified in this 

AD, contact Bell Helicopter Textron Canada 

Limited, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or at 

http://www.bellcustomer.com/files/. 

(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 June 24, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–16469 Filed 7–6–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0569; Directorate 

Identifier 2014–NM–047–AD; Amendment 

39–18199; AD 2015–14–01] 

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 DHC–8–400 

series airplanes. This AD was prompted 

by a report of loose bolts that are 

intended to secure the translating door 

crank assembly to the outside handle 

shaft. This AD requires a detailed 

inspection for loose bolts on the aft 

translating door crank assembly, and 

removal and reinstallation of the bolts. 

We are issuing this AD to prevent loose 

bolts from falling out. If both bolts 

become loose or fall out after the door 

is closed and locked, the door cannot be 

opened from inside or outside, which 

could impede evacuation in the event of 

an emergency. 

DATES: This AD becomes effective 

August 11, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 11, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0569; 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., QSeries 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. 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. It is also available on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0569. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; 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 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

August 15, 2014 (79 FR 48105). The 

NPRM was prompted by a report of 

loose bolts that are intended to secure 

the translating door crank assembly to 

the outside handle shaft. The NPRM 

proposed to require a detailed 

inspection for loose bolts on the aft 

translating door crank assembly, and 

removal and reinstallation of the bolts. 

We are issuing this AD to prevent loose 

bolts from falling out. If both bolts 

become loose or fall out after the door 

is closed and locked, the door cannot be 

opened from inside or outside, which 

could impede evacuation in the event of 

an emergency. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–08, 

dated February 10, 2014 (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 was one in-service report where the 

bolts securing the translating door crank 

assembly to the outside handle shaft were 

found loose. It was also found on another 

translating door that sealant was missing on 

these bolts. If both bolts become loose or fall 

out after the door is closed and locked, the 

door cannot be opened from inside or 

outside. 

The aft entry translating door and aft 

service translating door are classified as 

emergency exits. The inability to open an 

emergency exit could impede evacuation in 

the event of an emergency. 

This [Canadian] AD mandates the 

inspection of the translating door crank 

assemblies for loose bolts, as well as 

appropriate rectification [removal and 

reinstallation of the bolts]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0569- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The following presents the comment 

received on the NPRM (79 FR 48105, 

August 15, 2014), and the FAA’s 

response to the comment. 

Request To Remove Certain 

Requirements From the NPRM (79 FR 

48105, August 15, 2014) 

Horizon Air requested that the job setup and close-out procedures included in 

Part A–INSPECTION, and Part B– 

RECTIFICATION, of the 

Accomplishment Instructions of 

Bombardier Service Bulletin 84–52–75, 

Revision A, dated July 11, 2013, be 

removed as requirements in the NPRM 

(79 FR 48105, August 15, 2014). The 

commenter noted that only the 

procedures included in paragraph B. 


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