65178 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than 

or equal to 0.218 inch: Within 6,000 flight 

hours after the effective date of this AD, but 

not to exceed 15,600 total flight hours, 

rework the bellcrank, or replace the bellcrank 

with a new bellcrank or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(2) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.218 

inch, but is less than or equal to 0.248 inch: 

Within 6,000 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(3) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.248 

inch, but is less than or equal to 0.278 inch: 

Within 1,200 flight hours after doing the 

measurement/inspection required by 

paragraph (h) of this AD, replace the 

bellcrank with a new bellcrank, or with a 

serviceable bellcrank with bushings having 

part number 82710297–101 installed, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, Revision A, dated February 22, 

2012. 

(4) If any cracking is found, or if any clevis 

hole edge-to-edge length exceeds 0.278 inch: 

Before further flight, replace the bellcrank 

with a new bellcrank, or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(i) Actions for Certain Other Model DHC–8– 

400 Series Airplanes 

For Model DHC–8–400, –401, and –402 

airplanes that have accumulated more than 

15,000 total flight hours as of the effective 

date of this AD: Within 600 flight hours after 

the effective date of this AD, measure the 

edge-to-edge length of the clevis holes of 

each bellcrank, and inspect each bellcrank 

for cracking using liquid penetrant or eddy 

current inspection method; in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than 

or equal to 0.218 inch: Within 1,200 flight 

hours after the effective date of this AD, 

rework the bellcrank, or replace the bellcrank 

with a new bellcrank or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(2) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 

0.218, inch but is less than or equal to 0.248 

inch: Within 6,000 flight hours after the 

effective date of this AD, replace the 

bellcrank with a new bellcrank, or with a 

serviceable bellcrank with bushings having 

part number 82710297–101 installed, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, Revision A, dated February 22, 

2012. 

(3) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.248 

inch, but is less than or equal to 0.278 inch: 

Within 1,200 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(4) If any cracking is found, or any clevis 

hole edge-to-edge length exceeds 0.278 inch: 

Before further flight, replace the bellcrank 

with a new bellcrank, or with a serviceable 

bellcrank with bushings having part number 

82710297–101 installed, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (h) and (i) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(k) 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, New York 

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 FAA-approved 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2011–32, dated 

August 15, 2011, for related information. The 

MCAI can be found in the AD docket on the 

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

#!documentDetail;D=FAA-2012-1311-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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) Bombardier Service Bulletin 8–27–111, 

dated June 15, 2011. 

(ii) Bombardier Service Bulletin 84–27–55, 

Revision A, dated February 22, 2012. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

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. 

(4) You may review copies of the 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 

September 30, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25305 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0526; Directorate 

Identifier 2008–SW–14–AD; Amendment 

39–17633; AD 2013–22–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Model 206L–4 and 407 helicopters. This 

AD requires replacing or reworking 

certain aft bearing caps. This AD was 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65179 

prompted by the manufacture of certain 

freewheel aft bearing caps without a 

lubrication channel to allow oil flow 

into the aft bearing support assembly. 

The actions of this AD are intended to 

prevent failure of the freewheel unit and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, Texas 76101, telephone 

(817) 280–3391, fax (817) 280–6466. 

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 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: Eric 

Haight, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Policy Group, Fort Worth, Texas 76137, 

telephone (817) 222–5110, email: 

eric.haight@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 20, 2013, at 78 FR 37158, 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 Bell 

Model 206L–4 and 407 helicopters. The 

NPRM proposed to require, within 50 

hours time-in-service (TIS), removing 

and disassembling the freewheel 

assembly, replacing the sprag, retainer, 

and the aft seal, and visually inspecting 

the remaining freewheel part details for 

a missing channel. Also, the NPRM 

proposed to require, if the channel is 

missing, before further flight, replacing 

the cap assembly with an airworthy cap 

or reworking and reidentifying the 

existing cap by using a vibrating stylus 

to add the letter ‘‘R’’ to the serial 

number of the reworked cap. The 

proposed actions were prompted by the 

manufacture of certain freewheel aft 

bearing caps without a lubrication 

channel to allow oil flow into the aft 

bearing support assembly. The proposed 

requirements were intended to prevent 

failure of the freewheel unit and 

subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

CF–2004–17R1, dated February 11, 2005 

(AD No. CF–2004–17R1), issued by 

TCAA, which is the aviation authority 

for Canada. AD No. CF–2004–17R1 

requires replacing or reworking 

freewheel assemblies on the Bell Model 

206L–4 and 407 helicopters. TCAA 

advises of a manufacturing oversight 

where a lubrication channel was not 

machined into the aft bearing cap of 

some freewheel units to allow oil flow 

into the aft bearing support assembly. 

TCAA states that lack of lubrication may 

adversely affect the durability and 

potentially the function of the freewheel 

unit. 

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 37158, June 20, 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, TCAA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are issuing this AD because we 

evaluated all information provided by 

TCAA 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 

TCAA AD 

This AD differs from the TCAA AD as 

follows: 

• We do not use a calendar time, 

which has already passed. 

• We require all affected helicopters 

to comply within 50 hours TIS; the 

TCAA AD has different compliance 

times as stipulated by the calculated 

average engine start cycle count 

identified in the applicable alert service 

bulletin (ASB), and a 300-hour TIS 

terminating action for modifying all 

affected helicopters. 

• We do not require referencing 

compliance with the ASBs as does the 

TCAA AD, and we do not require you 

to provide an affected cap for rework to 

Bell Tennessee nor require the original 

cap to be reworked by Bell Tennessee. 

• We do not require any action on 

‘‘spare’’ parts not installed on a 

helicopter but would require, before 

installing any replacement bearing 

support assembly, ensuring that the 

rework has been done. 

Related Service Information 

Bell has issued ASB No. 206L–04–129 

for the Model 206L–4 and ASB No. 407– 

04–66 for the Model 407, both Revision 

A, and both dated December 1, 2004, 

which specify identifying the affected 

freewheel aft bearing caps. The ASBs 

provide separate procedures, depending 

on whether helicopters are ‘‘not 

exclusively used for training’’ or 

‘‘exclusively used for training,’’ for 

replacing or reworking the freewheel 

cap assembly and replacing the output 

shaft, part number (P/N) 406–040–517– 

101, and sprag and retainer, P/N 406– 

040–580–103. TCCA classified these 

ASBs as mandatory and issued AD No. 

CF–2004–17R to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate there are 212 Model 

206L–4 helicopters and 540 Model 407 

helicopters of U.S. registry; however, we 

estimate that only 80 helicopters are 

affected by this AD. We estimate that 

operators may incur the following costs 

in order to comply with this AD: It will 

take about 16 work hours to replace the 

freewheel unit for all the affected parts 

at an average labor rate of $85 per work 

hour. Required parts will cost about 

$21,600 per helicopter. Based on these 

figures, we estimate the total cost per 

helicopter will be $22,900, and the total 

cost of the AD on U.S. operators will be 

$1,836,800. 

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 


wreier-aviles on DSK5TPTVN1PROD with RULES
65180 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and 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): 

2013–22–01 Bell Helicopter Textron 

Canada: Amendment 39–17633; Docket 

No. FAA–2013–0526; Directorate 

Identifier 2008–SW–14–AD. 

(a) Applicability 

This AD applies to Model 206L–4 and 407 

helicopters, with a freewheel aft bearing cap 

(cap), part number (P/N) 406–040–509–101, 

with a serial number with a prefix of ‘‘A-’’ 

and Nos. 1833 through 1912, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

certain caps being manufactured without a 

lubrication channel to allow oil flow into the 

aft bearing support assembly, which could 

result in failure of the freewheel unit and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective December 5, 

2013. 

(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 

Within 50 hours time-in-service (TIS): 

(1) Remove and disassemble each 

freewheel assembly. 

(2) Replace the sprag and retainer (item 7), 

the output shaft (item 10), and the aft seal 

(item 3), as depicted in Figure 2 of Bell Alert 

Service Bulletin (ASB) No. 206L–04–129 for 

the Model 206L–4 and ASB No. 407–04–66 

for the Model 407, both Revision A, and both 

dated December 1, 2004. 

(3) Visually inspect the remaining 

freewheel part details for a missing channel. 

(4) If the channel is missing, replace or 

rework the cap assembly by following the 

instructions depicted in Figure 3 of ASB 

206L–04–129 or ASB 407 04–66, as 

applicable for your model helicopter. Using 

a vibrating stylus, mark the letter ‘‘R’’ at the 

end of the serial number on the cap 

assembly. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Eric Haight, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

Fort Worth, Texas 76137, telephone (817) 

222–5110, email: eric.haight@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–2004–17R1, dated February 11, 2005. 

You may view the TCCA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0526. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6300: Main Rotor Drive System. 

(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 (ASB) No. 

206L–04–129, Revision A, dated December 1, 

2004. 

(ii) Bell ASB No. 407–04–66, Revision A, 

dated December 1, 2004. 

(3) For Bell service information identified 

in this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, Texas 76101, 

telephone (817) 280–3391, fax (817) 280– 

6466. 

(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 October 1, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–25310 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0401; Directorate 

Identifier 2012–SW–047–AD; Amendment 

39–17606; AD 2013–19–24] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–08– 

51 for MD Helicopters, Inc. (MDHI), 

Model 369A, 369D, 369E, 369H, 369HE, 

369HM, 369HS, 369F and 369FF 

helicopters with certain MDHI or 

Helicopter Technology Company (HTC) 

tail rotor blades installed. AD 2003–08– 

51 required reducing the retirement life 

of each tail rotor blade (blade), 

performing a one-time visual inspection 

of each blade’s pitch horn (pitch horn) 

for a crack or corrosion, and replacing 

any cracked blade or any blade that has 

exceeded its retirement life with an 


wreier-aviles on DSK5TPTVN1PROD with RULES