Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78699 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0603; Directorate 

Identifier 2009–SW–079–AD; Amendment 

39–17706; AD 2013–25–10] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial-numbered Bell Helicopter Textron 

Canada Limited (BHTC) Model 206L, 

206L–1, 206L–3, and 206L–4 helicopters 

with a certain tailboom upper left 

attachment fitting (fitting). This AD 

requires inspecting the fitting for a crack 

and other conditions. This AD was 

prompted by the manufacturer revising 

and extending the 100 hour time-inservice (TIS) inspection requirements 

for the fitting. The actions of this AD are 

intended to detect a crack, loose rivet, 

corrosion, or any other damage, which 

could lead to loss of the tailboom and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective January 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of January 31, 2014. 

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. 

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 foreign 

authority’s AD, any incorporated-byreference 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: 

Sharon Miles, Aerospace Engineer, 

FAA, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5110; 

email: sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 12, 2013, at 78 FR 41886, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

add an AD that would apply to BHTC 

Model 206L, 206L–1, 206L–3, and 

206L–4 helicopters with an upper left 

attachment fitting part number 206– 

032–409–001 installed. The NPRM 

proposed to require within 100 hours 

TIS and thereafter at intervals not 

exceeding 110 hours TIS, inspecting the 

upper left tailboom attachment fitting 

for a crack, corrosion, damage, or a loose 

rivet. If there is a crack or corrosion or 

damage beyond acceptable limits, the 

NPRM proposed to require replacing the 

upper left tailboom attachment fitting. If 

there is corrosion or damage within 

acceptable limits, the NPRM proposed 

to require repairing the fitting. If there 

is a loose rivet, the NPRM proposed to 

require replacing the loose rivet. The 

proposed requirements were intended to 

detect a crack, loose rivet, corrosion, or 

any other damage, which could lead to 

loss of the tailboom and subsequent loss 

of control of the helicopter. 

The NPRM was prompted by AD No. 

CF–2009–41, dated November 16, 2009, 

issued by Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada. TCCA issued AD 

No. CF–2009–41 to correct an unsafe 

condition for certain 206L series 

helicopters, specifically: Model 206L, 

serial number (S/N) 45004 through 

45153, and 46601 through 46617; Model 

206L–1, S/N 45154 through 45790; 

Model 206L–3, S/N 51001 through 

51612; and Model 206L–4, all S/Ns. 

TCCA advises that AD No. CF–2009–41 

was prompted by a new airworthiness 

limitation for the fitting that requires an 

inspection of fitting part number 203– 

032–409–001 at each 100-hour or 

annual inspection. The TCCA AD 

requires inspecting the fitting, and 

replacing or repairing it if necessary, in 

accordance with the Accomplishment 

Instructions of BHTC Alert Service 

Bulletin (ASB) 206L–09–158, Revision 

A, dated August 31, 2009 (ASB 206L– 

09–158 Revision A). TCCA further states 

that incorporating this inspection into 

the applicable maintenance manual 

revision constitutes terminating action 

to TCCA AD No. CF–2009–41. The 

actions in TCCA AD No. CF–2009–41 

are intended to detect a crack in a 

tailboom attachment fitting, which 

could result in loss of the tailboom and 

subsequent loss of control of the 

helicopter. 

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 41886, July 12, 2013). 

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 a recurring 

inspection every 100 hours, while this 

AD requires the inspection at intervals 

not to exceed 110 hours to align with 

the Bell ASB. 

Related Service Information 

We reviewed ASB 206L–09–158, 

Revision A for certain serial-numbered 

Model 206L, L–1, L–3, and L–4 

helicopters with certain tailboom 

assemblies installed. The ASB requires 

an inspection of the fitting for a crack, 

loose rivets, corrosion, and damage at 

each 100-hour or annual inspection. If 

there is a crack, the ASB specifies 

replacing the fitting with an airworthy 

fitting. If there is a loose rivet, the ASB 

specifies replacing the rivet with an 

airworthy rivet. If the fitting has 

corrosion or mechanical damage, the 

ASB specifies determining if the 

corrosion or mechanical damage is 

within acceptable limits. If the corrosion 

or mechanical damage is within 

acceptable limits, the ASB specifies 

repairing the damage in accordance 

with the instructions contained in the 

ASB. If the damage is not within 

acceptable limits, the ASB specifies 

replacing the fitting with an airworthy 


tkelley on DSK3SPTVN1PROD with RULES
78700 Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 

fitting. TCCA classified this ASB as 

mandatory and issued AD No. CF– 

2009–41 to ensure the continued 

airworthiness of these helicopters. 

Since that time, BHTC has issued ASB 

206L–09–158, Revision B, dated June 1, 

2011, for all Model 206L series 

helicopters. Revision B of the ASB 

changes the recurring inspection 

interval from every 100 flight hours to 

every 110 flight-hours. 

Costs of Compliance 

We estimate that this AD affects 783 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

At an average labor rate of $85 per workhour, inspecting the fitting requires 

about 1 work-hour, for a cost per 

helicopter of $85 and a total cost to U.S. 

operators of $66,555 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs or replacements 

that would be required based on the 

results of the proposed inspection. We 

have no way of determining the number 

of aircraft that might need these repairs 

or replacements. Repairing a damaged 

fitting requires about 8 work-hours and 

required parts cost about $10, for a cost 

per helicopter of $690. Replacing a 

fitting which is damaged beyond the 

allowable repair limits requires about 8 

work-hours and required parts cost 

about $793, for a cost per helicopter of 

$1,473. Replacing a loose rivet requires 

about 1 work-hour, and required parts 

cost about $1, for a cost per helicopter 

of $86. 

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): 

2013–25–10 Bell Helicopter Textron 

Canada (BHTC): Amendment 39–17706; 

Docket No. FAA–2013–0603; Directorate 

Identifier 2009–SW–079–AD. 

(a) Applicability 

This AD applies to BHTC Model 206L, 

206L–1, 206L–3, and 206L–4 helicopters 

with an upper left attachment fitting part 

number 206–032–409–001 installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a tailboom attachment fitting, which 

could result in loss of the tailboom and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective January 31, 

2014. 

(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) At the next 100-hour inspection, and 

thereafter at intervals not to exceed 110 hours 

time-in-service, inspect each tailboom upper 

left attachment fitting (fitting) for a crack, a 

loose rivet, corrosion, or damage as depicted 

in Figure 2 of BellAlert Service Bulletin 

206L–09–158, Revision B, dated June 1, 2011 

(ASB 206L–09–158). 

(2) If there is a crack, corrosion, or damage 

beyond the acceptable limits of Figure 2 of 

ASB 206L–09–158, before further flight, 

replace the fitting with an airworthy fitting. 

(3) If there is corrosion or damage within 

the acceptable limits of Figure 2 of ASB 

206L–09–158, before further flight, repair the 

fitting as described in the Accomplishment 

Instructions, Part I, paragraphs 5.b.(1) 

through 5.b.(6), of ASB 206L–09–158. 

(4) If there is a loose rivet, before further 

flight, replace the loose rivet with an 

airworthy rivet. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aerospace Engineer, FAA, Regulations and 

Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone: (817) 222– 

5122; fax: (817) 222–5961; email: 

sharon.y.miles@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 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2009–41, dated November 16, 2009. 

You may view the TCCA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0603. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302: Rotorcraft Tailboom. 

(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 Alert Service Bulletin 206L–09– 

158, Revision B, dated June 1, 2011. 

(ii) Reserved. 


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Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations 78701 

(3) For Bell 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 December 

5, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–30186 Filed 12–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0421; Directorate 

Identifier 2013–NM–003–AD; Amendment 

39–17701; AD 2013–25–05] 

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 certain 

The Boeing Company Model 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by fuel system 

reviews conducted by the manufacturer. 

This AD requires, depending on 

airplane configuration, replacing fuel 

pump power control relays with new 

relays having a ground fault interrupter 

(GFI) feature, installing ground studs 

and a bonding jumper, doing certain 

bonding resistance measurements, and 

changing the GFI relay position. This 

AD also requires revising the 

maintenance program to incorporate 

certain airworthiness limitations. We 

are issuing this AD to prevent damage 

to the fuel pumps caused by electrical 

arcing that could introduce an ignition 

source in the fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD is effective January 31, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 31, 2014. 

ADDRESSES: For 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. 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. 

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 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6482; 

fax: 425–917–6590; email: 

georgios.roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on May 16, 2013 (78 FR 28764). 

The NPRM proposed to require, 

depending on airplane configuration, 

replacing fuel pump power control 

relays with new relays having a ground 

fault interrupter (GFI) feature, installing 

ground studs and a bonding jumper, 

doing certain bonding resistance 

measurements, and changing the GFI 

relay position. The NPRM also proposed 

to require revising the maintenance 

program to incorporate certain 

airworthiness limitations. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 28764, 

May 16, 2013) and the FAA’s response 

to each comment. 

Support for the NPRM 

Boeing concurred with the content of 

the proposed rule. 

Request To Include Certain Instructions 

and Delete Certain Step 

All Nippon Airways (ANA) requested 

that we include instructions for the 

removal and installation of certain relay 

sockets, and for removal of paint on the 

mounting panel under Step 5 of Figure 

5 of Boeing Alert Service Bulletin 737– 

28A1212, Revision 2, dated October 18, 

2012. ANA stated that without removal 

of the paint on the mounting panel, the 

required bonding resistance 

measurements cannot be obtained. In 

addition, ANA requested that we delete 

step 6 of Figure 5 of Boeing Alert 

Service Bulletin 737–28A1212, Revision 

2, dated October 18, 2012, which 

describes removal of paint around the 

relay cutout. ANA stated that paint 

removal around the relay cutout is not 

needed since the relay sockets are 

mounted to the cutout area of the panel 

and the relays are a spacer-mounted 

type. 

We disagree with providing 

additional instructions that would 

expand the scope of this final rule, 

requiring additional notice and 

comment. We find that delaying this 

action would be inappropriate in light 

of the urgency of the identified unsafe 

condition. Operators should note that a 

general AMOC, which was requested by 

Boeing on behalf of all operators, has 

been issued for AD 2011–12–09, 

Amendment 39–16716 (76 FR 33988, 

June 10, 2011). The AMOC provides 

essentially the same relief as that 

requested by the commenter. Once this 

final rule is effective, we may issue a 

similar AMOC. Any person may request 

approval of an alternative method of 

compliance (AMOC) under the 

provisions of paragraph (l) of this AD for 

procedures that help them meet the 

bonding resistance requirements. We 

have not changed this final rule in this 

regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 


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