65198 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(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 

MDHI Alert Service Bulletin SB900–116R1, 

dated April 9, 2010, which supersedes MDHI 

Alert Service Bulletin SB SB900–116, dated 

February 24, 1010, neither of which is 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact MDHI, Attn: Customer 

Support Division, 4555 E. McDowell Rd., 

Mail Stop M615, Mesa, AZ 85215–9734, 

telephone (800) 388–3378, fax (480) 346– 

6813, or at http://www.mdhelicopters.com. 

You may review copies of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas. 

(h) Subject 

Joint Aircraft System Component: 6210: 

Main rotor blade retention bolts. 

Issued in Fort Worth, Texas, on September 

27, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25702 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–2012–0594; Directorate 

Identifier 2012–NM–019–AD; Amendment 

39–17641; AD 2013–22–09] 

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, 

–401, and –402 airplanes. This AD was 

prompted by reports of movement of the 

rudder pedals being impeded due to 

corrosion of the trunnion shaft of the 

rudder feel trim unit (RFTU). This AD 

requires an inspection to determine if 

certain RFTUs are installed, an 

operational check for signs of seizure of 

affected parts, repetitive lubrication of 

certain RFTUs, and replacement of the 

RFTU if necessary. Installing 

replacement RFTUs having conformal 

bushings terminates the repetitive 

lubrication requirements. We are issuing 

this AD to detect and correct any sign 

of rough movement or seizure of the 

trunnion shaft and its bushing, which 

could cause a rudder control jam or a 

large and rapid alternating rudder input 

leading to a structural failure of the 

vertical fin. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication 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-2012-0594 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: 

Cesar Gomez, 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– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to the specified 

products. The SNPRM was published in 

the Federal Register on March 12, 2013 

(78 FR 15655). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM), which published in the 

Federal Register on June 12, 2012 (77 

FR 34874). The NPRM and the SNPRM 

both proposed to correct an unsafe 

condition for the specified products. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–02R1, 

dated October 12, 2012 (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 reported incidents 

on DHC–8 Series 400 aeroplanes where the 

movement of the rudder pedals has been 

impeded. An investigation showed that the 

Rudder Feel Trim Unit (RFTU) trunnion shaft 

was corroded. The root cause of the corrosion 

was a quality escape where cadmium plating 

on the trunnion bushing within the RFTU 

assembly was not removed. Corrosion on the 

shaft and in the trunnion bushing seized the 

trunnion and caused difficulties in 

controlling the rudder movement. 

This condition, if not corrected, could 

cause a rudder control jam or a large and 

rapid alternating rudder input leading to a 

structural failure of the vertical fin. 

This [TCCA] Airworthiness Directive (AD) 

is issued [inspect to determine serial number, 

an operational check for seizure, repetitive 

lubrication and] to replace the affected 

RFTUs to limit the possibility of binding and 

replace the affected RFTUs with units that 

have been reworked with conformal bushings 

to terminate the lubrication requirements. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2012-0594- 

0006. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Revise Compliance Time for 

Operational Check 

Horizon Air (Horizon) requested that 

paragraph (g)(2) of the SNPRM (78 FR 

15655, March 12, 2013) be revised to 

allow operators that perform a review of 

airplane maintenance records, in lieu of 

visually inspecting the serial number of 

the RFTU, time to schedule the 

operational check specified by 

paragraph (g)(2) of the SNPRM. Horizon 

stated that the compliance time ‘‘before 

further flight’’ specified in paragraph 

(g)(2) of the SNPRM would immediately 

ground aircraft. 

We agree with Horizon’s request. We 

have revised the compliance time in 

paragraph (g)(2) of this final rule to ‘‘200 

flight hours or 2 months, whichever 

occurs first after the effective date of 

this AD’’ for performing the operational 

check specified in that paragraph. 

Explanation of Changes Made to This 

AD 

We have revised paragraph (h) of this 

final rule to specify that installing 

replacement RFTUs having conformal 

bushings terminates the repetitive 

lubrication requirements of paragraph 


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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65199 

(g)(2)(ii) of this final rule for the affected 

RTFU. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We have determined that these changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

15655, March 12, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 15655, 

March 12, 2013). 

Costs of Compliance 

We estimate that this AD affects 83 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection, Replacement, Lubrication.5 work-hours × $85 per hour 

= $425 per inspection, replacement, and lubrication 

cycle.

$0 $425 per inspection, replacement, and lubrication cycle.$35,275 inspection, replacement, and lubrication cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ................................................................. 17 work-hours × $85 per hour = $1,445 ...................... $0 $1,445 

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. 

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 AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2012-0594; 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: 

2013–22–09 Bombardier, Inc.: Amendment 

39–17641. Docket No. FAA–2012–0594; 

Directorate Identifier 2012–NM–019–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. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

(S/N) 4001, 4003 and subsequent, equipped 

with rudder feel trim unit (RFTU) part 

number (P/N) 399500–1007. 


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65200 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

movement of the rudder pedals being 

impeded due to corrosion of the trunnion 

shaft of the RFTU. We are issuing this AD to 

detect and correct any sign of rough 

movement or seizure of the trunnion shaft 

and its bushing, which could cause a rudder 

control jam or a large and rapid alternating 

rudder input leading to a structural failure of 

the vertical fin. 

(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) Inspection, Replacement, and Lubrication 

Within 200 flight hours or two months 

after the effective date of this AD, whichever 

occurs first: Inspect the RTFU to determine 

whether the serial number is in the range 

from S/N 0008 through 0509 inclusive 

without a suffix ‘B,’ in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–60, dated July 12, 

2012. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the serial number of the RFTU 

can be conclusively determined from that 

review. 

(1) If the RFTU’s serial number is not in 

the range from S/N 0008 through 0509 

inclusive, or if the serial number has a suffix 

‘B,’ no further action is required for this 

paragraph. 

(2) If the RFTU’s serial number is in the 

range from S/N 0008 through 0509 inclusive, 

including those with a suffix ‘A,’ but not 

including those with suffix ‘B’: Within 200 

flight hours or 2 months, whichever occurs 

first after the effective date of this AD, 

perform an operational check of the RFTU for 

any sign of rough movement or seizure of the 

trunnion or center shaft, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–60, dated 

July 12, 2012. 

(i) If rough movement or seizure of the 

RFTU trunnion or center shaft is found: 

Before further flight, replace the RFTU with 

a new or serviceable RFTU, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–60, dated 

July 12, 2012. 

(ii) If no rough movement or seizure of the 

RFTU trunnion or center shaft is found: 

Before further flight, lubricate the RFTU, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–60, dated July 12, 2012. Repeat the 

lubrication of the RFTU at intervals not to 

exceed 600 flight hours or 3 months, 

whichever occurs first, until the RFTU is 

replaced with a unit that has a serial number 

outside the affected range or a serial number 

with a suffix ‘B.’ 

(h) Replacement 

For airplanes having an RFTU identified in 

paragraph (g)(2) of this AD: Except as 

required by paragraph (g)(2)(i) of this AD, 

within 5,000 flight hours or 3 years after the 

effective date of this AD, whichever occurs 

first, replace all affected RFTUs with units 

that have a serial number outside the range 

from S/Ns 0008 through 0509 inclusive, or 

that have a serial number with a suffix ‘B,’ 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–60, dated July 12, 2012. Installing 

replacement RFTUs having conformal 

bushings terminates the repetitive lubrication 

requirements of paragraph (g)(2)(ii) of this 

AD for the affected RTFU. 

(i) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an RFTU P/N 399500– 

1007 with a serial number from S/N 0008 

through 0509 inclusive, including serial 

numbers with suffix ‘A,’ on any airplane, 

except that RFTUs having a serial number 

with suffix ‘B’ may be installed. 

(j) 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. 

(k) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2012–02R1, dated October 12, 

2012, for related information, which can be 

found in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2012-0594-0006. 

(l) 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 84–27–60, 

dated July 12, 2012. 

(ii) Reserved. 

(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 October 

18, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25629 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–2013–0490; Directorate 

Identifier 2008–SW–004–AD; Amendment 

39–17611; AD 2013–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bell Model 407 helicopters. This AD 

requires installing a placard beneath the 

NR/NP dual tachometer and revising the 

limitations section of the rotorcraft 

flight manual (RFM). This AD was 

prompted by several incidents of third 

stage engine turbine wheel failures, 

which were caused by excessive 

vibrations at certain engine speeds 

during steady-state operations. These 

actions are intended to alert pilots to 

avoid certain engine speeds during 

steady-state operations, prevent failure 

of the third stage engine turbine, engine 

power loss, 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 


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