65176 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1311; Directorate 

Identifier 2011–NM–204–AD; Amendment 

39–17636; AD 2013–22–04] 

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–8–102, 

–103, and –106 airplanes; and Model 

DHC–8–200, –300, and –400 series 

airplanes. This AD was prompted by 

reports of excessive wear found in the 

clevis (bolt) hole where the rod 

assembly attaches to the rudder/brake 

pedal bellcrank, due to prolonged 

fretting. This AD requires measuring the 

bellcrank clevis holes, inspecting for 

cracking of the bellcrank, and reworking the clevis holes with steel 

bushings, or replacing the bellcrank. We 

are issuing this AD to detect and correct 

a worn or cracked clevis hole, which 

could cause failure of the bellcrank on 

one side, with subsequent asymmetric 

braking and consequent runway 

excursion. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2012-1311; or in 

person at the 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. 

FOR FURTHER INFORMATION CONTACT: 

Luke Walker, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7363; 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 the specified products. The 

NPRM was published in the Federal 

Register on December 26, 2012 (77 FR 

75906). The NPRM proposed to correct 

an unsafe condition for the specified 

products. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, issued Canadian 

Airworthiness Directive CF–2011–32, 

dated August 15, 2011 (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 several in-service reports 

of excessive wear found in the bolt [clevis] 

hole where the rod assembly, Part Numbers 

(P/N) 82710795–001 or 82710024–003, is 

attached to the rudder/brake pedal bellcrank. 

An investigation revealed that the wear was 

attributed to prolonged fretting. 

Failure of the bellcrank on one side could 

lead to asymmetric braking and may lead to 

runway excursion. 

This [Canadian] directive mandates 

[measuring clevis holes for length, and, for 

certain bellcranks, doing a liquid penetrant 

inspection for cracking, and] the re-work [by 

installing steel bushings] or replacement of 

each bellcrank, P/N 82710022–001/–002, 

82710029–001/–002, 82710813–001/–002 

and 82710814–001/–002, found with a worn 

[or cracked] bolt hole. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

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

0002. 

Revised Service Information 

Bombardier, Inc. has issued Service 

Bulletin 84–27–55, Revision A, dated 

February 22, 2012. The NPRM (77 FR 

75906, December 26, 2012) referred to 

Bombardier Service Bulletin 84–27–55, 

dated June 15, 2011, in paragraphs (h) 

and (i) of the NPRM. In this final rule, 

we have revised the service bulletin 

references in those paragraphs 

accordingly, and have added new 

paragraph (j) to this final rule to give 

credit for actions done before the 

effective date of this AD in accordance 

with Bombardier Service Bulletin 84– 

27–55, dated June 15, 2011 (and 

redesignated subsequent paragraphs 

accordingly). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Allow Use of Serviceable 

Parts 

An anonymous commenter requested 

that the references to ‘‘new bellcrank’’ 

in the NPRM (77 FR 75906, December 

26, 2012) be changed to allow operators 

to install ‘‘serviceable’’ bellcranks (new 

bellcranks or ones that have been 

modified according to the applicable 

service information), thus giving equal 

safety, yet providing more flexibility 

and less recordkeeping for operators. 

We agree with the commenter’s 

request for the reasons given. We have 

revised paragraphs (g)(2), (h)(2), (h)(3), 

(h)(4), (i)(2), (i)(3), and (i)(4) of this AD 

by specifying to replace the bellcrank 

with a new bellcrank ‘‘or with a 

serviceable bellcrank with bushings 

having part number 82710297–101 

installed.’’ We have also clarified 

paragraphs (h)(1) and (i)(1) of this final 

rule by specifying to replace the 

bellcrank ‘‘with a new or with a 

serviceable bellcrank with bushings 

having part number 82710297–101 

installed.’’ 

Request To Add Eddy Current 

Inspection Option 

The same anonymous commenter 

requested that we include an eddy 

current inspection option in this final 

rule to agree with parallel actions 

specified in Bombardier Service 

Bulletin 84–27–55, Revision A, dated 

February 22, 2012. 

We agree with the commenter’s 

request because Bombardier added that 

inspection option in Bombardier Service 

Bulletin 84–27–55, Revision A, dated 

February 22, 2012. Accordingly, we 

have added the option in paragraphs (h) 

and (i) of this final rule. 

Request To Clarify Compliance Times 

The same anonymous commenter, in 

an incomplete request, stated that the 

replacement times in paragraph (h) of 

the NPRM (77 FR 75906, December 26, 

2012) do not sufficiently remove the 

identified unsafe condition. From the 

truncated statement, we cannot infer 

what part of paragraph (h) the 

commenter requested that we change. 

We have made no change to this final 

rule in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 


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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65177 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

75906, December 26, 2012) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 75906, 

December 26, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

178 products of U.S. registry. We also 

estimate that it will take 5 work-hours 

per product to comply with the basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. Based 

on these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$75,650, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 16 work-hours and require parts 

costing up to $2,532, for a cost of $3,892 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. We have no 

way of determining the number of 

products that may need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

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

0002; 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 MCAI, the 

regulatory evaluation, any 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: 

2013–22–04 Bombardier, Inc.: Amendment 

39–17636. Docket No. FAA–2012–1311; 

Directorate Identifier 2011–NM–204–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 5, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. 

airplanes, certificated in any category, as 

specified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes: Serial 

numbers 003 through 672 inclusive. 

(2) Model DHC–8–400, –401, and –402 

airplanes: Serial numbers 4003 through 4372 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by reports of 

excessive wear found in the clevis (bolt) hole 

where the rod assembly attaches to the 

rudder/brake pedal bellcrank, due to 

prolonged fretting. We are issuing this AD to 

detect and correct a worn or cracked clevis 

hole, which could cause failure of the 

bellcrank on one side, with subsequent 

asymmetric braking and consequent runway 

excursion. 

(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) Actions for Model DHC–8–100, –200, and 

–300 Series Airplanes 

For Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes: Within 

6,000 flight hours or 24 months after the 

effective date of this AD, whichever occurs 

first, inspect each bellcrank for cracking 

using liquid penetrant, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 8–27–111, dated 

June 15, 2011. 

(1) If no cracking is found: Before further 

flight, rework the bellcrank, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–27–111, dated 

June 15, 2011. 

(2) If any clevis hole is greater than 0.218 

inch (measured edge-to-edge), or if any 

cracking is found: 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 

8–27–111, dated June 15, 2011. 

(h) Actions for Certain Model DHC–8–400 

Series Airplanes 

For Model DHC–8–400, –401, and –402 

airplanes that have accumulated less than or 

equal to 15,000 total flight hours as of the 

effective date of this AD: Within 6,000 flight 

hours after the effective date of this AD, but 

not to exceed 15,600 total flight hours, 

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. 


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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 


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