5902 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 

under the criteria of the Regulatory 

Flexibility Act. 

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): 

2015–02–15 Quest Aircraft Design, LLC: 

Amendment 39–18082; Docket No. 

FAA–2015–0099; Directorate Identifier 

2014–CE–039–AD. 

(a) Effective Date 

This AD is effective February 19, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Quest Aircraft Design, 

LLC Model KODIAK 100 airplanes, all serial 

numbers, that are: 

(1) Equipped with elevators with serial 

numbers 0001 through 0149; and 

(2) certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5522; Elevator Skins. 

(e) Unsafe Condition 

This AD was prompted by a report that 

fatigue cracks were found in the lower 

elevator skins. We are issuing this AD to 

correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (j) of this AD, unless already done. 

(g) Inspect the Elevator Skins for Cracking 

At or before reaching 1,500 hours time in 

service (TIS) on the elevator or within the 

next 25 hours TIS after February 19, 2015 

(the effective date of this AD), whichever 

occurs later, inspect the top and bottom of 

the elevator for cracking in the forward 

inboard end of the trailing edge skin, aft of 

the spar. Do the inspection following section 

4. of Quest Aircraft Field Service Instruction, 

Elevator Doubler Installation, Elevator Serial 

Numbers 0001 through 0149, Report No. FSI– 

106, Revision 02, not dated, as specified in 

Quest Aircraft KODIAK Mandatory Service 

Bulletin SB 14–09, Revision 1, dated 

December 11, 2014. 

Note 1 to paragraph (g) of this AD: Quest 

Aircraft Field Service Instruction, Elevator 

Doubler Installation, Elevator Serial Numbers 

0001 through 0149, Report No. FSI–106, 

Revision 02, not dated, references Advisory 

Circular 43.13–1B, Section 2. The reference 

should state Advisory Circular 43.13–1B, 

chapter 5, section 2. You may find Advisory 

Circular 43.13–1B on the Internet at http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgAdvisoryCircular.nsf/0/99C827

DB9BAAC81B86256B4500596C4E?Open

Document&Highlight=43.13-1b. 

(h) Install Doublers 

If no cracking was found during the 

inspection required in paragraph (g) of this 

AD, before further flight after the inspection, 

install doublers. Do the installation following 

section 5.1 of Quest Aircraft Field Service 

Instruction, Elevator Doubler Installation, 

Elevator Serial Numbers 0001 through 0149, 

Report No. FSI–106, Revision 02, not dated, 

as specified in Quest Aircraft KODIAK 

Mandatory Service Bulletin SB 14–09, 

Revision 1, dated December 11, 2014. 

(i) Repair Cracked Elevator Skins and Install 

Doublers 

If cracking was found during the 

inspection required in paragraph (g) of this 

AD, before further flight after the inspection, 

repair the cracks and install doublers, except 

as specified in paragraph (j). Do the repair 

and installation following section 5.2 of 

Quest Aircraft Field Service Instruction, 

Elevator Doubler Installation, Elevator Serial 

Numbers 0001 through 0149, Report No. FSI– 

106, Revision 02, not dated, as specified in 

Quest Aircraft KODIAK Mandatory Service 

Bulletin SB 14–09, Revision 1, dated 

December 11, 2014. 

(j) Cracked Elevator Skins That Exceed 

Service Bulletin Repair Limits 

If the cracking found during the inspection 

required in paragraph (g) of this AD exceeds 

the repair specified in paragraph (i) of this 

AD, before further flight, obtain an FAAapproved repair method from Quest Aircraft 

by contacting the Manager, Seattle Aircraft 

Certification Office (ACO), FAA, as specified 

in paragraph (k) of this AD. To use a repair 

method approved by the Manager of the 

Seattle ACO, the approval letter must 

specifically reference this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) of this AD. 

(2) 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. 

(l) Related Information 

For more information about this AD, 

contact Jason Deutschman, Aerospace 

Engineer, Seattle Aircraft Certification Office, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057; phone: (425) 917–6595; 

fax: (425) 917–6590; email: 

jason.deutschman@faa.gov. 

(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) Quest Aircraft KODIAK Mandatory 

Service Bulletin SB 14–09, Revision 1, dated 

December 11, 2014. 

(ii) Quest Aircraft Field Service 

Instruction, Elevator Doubler Installation, 

Elevator Serial Numbers 0001 through 0149, 

Report No. FSI–106, Revision 02, not dated. 

(3) For Quest Aircraft service information 

identified in this AD, contact Quest Aircraft 

Design, LLC, 1200 Turbine Drive, Sandpoint, 

Idaho 83864; telephone: (208) 263–1111; toll 

free: (866) 263–1112; fax: (208) 263–1511; 

CustomerService@QuestAircraft.com; 

www.questaircraft.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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/ibr-locations.html. 

Issued in Kansas City, Missouri, on January 

16, 2015. 

Kelly A. Broadway, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01196 Filed 2–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0446; Directorate 

Identifier 2013–NM–077–AD; Amendment 

39–18069; AD 2015–02–02] 

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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 5903 

Bombardier, Inc. Model CL–215–6B11 

(CL–215T Variant), and CL–215–6B11 

(CL–415 Variant) airplanes. This AD 

was prompted by a report that, during 

a routine inspection, corrosion was 

discovered on the lower bearing of the 

rudder upper torque tube. This AD 

requires applying grease to the bearing; 

doing a general visual inspection of the 

expelled old grease for any 

contaminants, metal wear, and 

indication of corrosion, and replacing 

the bearing if necessary; and revising 

the maintenance or inspection program, 

as applicable, to incorporate the rudder 

spring tab operational test and a check 

of the rudder spring tab operation into 

the daily inspection. We are issuing this 

AD to prevent corroded bearings, which 

could result in a partial or total loss of 

axial support. 

DATES: This AD becomes effective 

March 11, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 11, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0446 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., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE 171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; 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 

CL–215–6B11 (CL–215T Variant), and 

CL–215–6B11 (CL–415 Variant) 

airplanes. The NPRM published in the 

Federal Register on July 15, 2014 (79 FR 

41145). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–08, 

dated March 12, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

215–6B11 (CL–215T Variant), and CL– 

215–6B11 (CL–415 Variant) airplanes. 

The MCAI states: 

During a routine inspection, corrosion was 

discovered on the Rudder Upper Torque 

Tube Lower bearing, part number (P/N) 

DAT48–64A. Corroded bearings may 

eventually result in a partial or total loss of 

axial support. 

As such, Bombardier has issued Service 

Bulletin (SB) 215–A3171 Rev. 1 and SB 215– 

A4452 Rev. 1, which provide instructions to 

refresh the lubrication in the bearing in order 

to inspect for corrosion and/or contaminants 

in the existing grease. These SBs will also 

incorporate an operational check to the 50 

hour maintenance scheduled tasks, and a test 

of the Rudder Spring Tab operation into the 

Daily inspection or the aircrew Preflight 

Check. 

Required actions include applying 

grease to the bearing, doing a general 

visual inspection of the expelled old 

grease for any contaminants, metal 

wear, and indication of corrosion, and 

replacing the bearing if necessary; 

revising the maintenance or inspection 

program, as applicable, to incorporate 

the rudder spring tab operational test; 

and revising the maintenance or 

inspection program, as applicable, to 

incorporate a check of the rudder spring 

tab operation into the daily inspection. 

You may examine the MCAI in the AD 

docket on the Internet at http://www.

regulations.gov/#!documentDetail;D=

FAA-2014-0446-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 41145, July 15, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

41145, July 15, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 41145, 

July 15, 2014). 

Related Service Information 

Bombardier, Inc. has issued 

Bombardier Alert Service Bulletin 215– 

A3171, Revision 1, dated January 25, 

2012, and Bombardier Alert Service 

Bulletin 215–A4452, Revision 1, dated 

January 3, 2012. This service 

information describes applying grease to 

the bearing; doing a general visual 

inspection of the expelled old grease for 

any contaminants, metal wear, and 

indication of corrosion, and replacing 

the bearing if necessary; and revising 

the maintenance or inspection program, 

as applicable, to incorporate the rudder 

spring tab operational test and a check 

of the rudder spring tab operation into 

the daily inspection. You can find this 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0446. 

Costs of Compliance 

We estimate that this AD affects 5 

airplanes of U.S. registry. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will be 

negligible. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $850, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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. 


tkelley on DSK3SPTVN1PROD with RULES
5904 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2014-0446; 

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 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 airworthiness 

directive (AD): 

2015–02–02 Bombardier, Inc.: Amendment 

39–18069. Docket No. FAA–2014–0446; 

Directorate Identifier 2013–NM–077–AD. 

(a) Effective Date 

This AD becomes effective March 11, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Bombardier, Inc. 

airplanes, certificated in any category, 

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

this AD. 

(1) Model CL–215–6B11 (CL–215T Variant) 

airplanes, serial numbers 1056 through 1125 

inclusive. 

(2) Model CL–215–6B11 (CL–415 Variant) 

airplanes, serial numbers 2001 through 2990 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a report that, 

during a routine inspection, corrosion was 

discovered on the lower bearing of the rudder 

upper torque tube. We are issuing this AD to 

prevent corroded bearings, which could 

result in a partial or total loss of axial 

support. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Lubrication of the Rudder Upper Torque 

Tube Bearing 

Within 3 months after the effective date of 

this AD, apply grease to the bearing, and do 

a general visual inspection of the expelled 

old grease for any contaminants (i.e. ashes, 

dust, and algae), metal wear, and indication 

of corrosion, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A3171, Revision 

1, dated January 25, 2012 (for Model CL– 

215–6B11 (CL–215T Variant) airplanes); or 

Bombardier Alert Service Bulletin 215– 

A4452, Revision 1, dated January 3, 2012 (for 

Model CL–215–6B11 (CL–415 Variant) 

airplanes). If any contaminants (i.e., ashes, 

dust, and algae), metal wear, or indication of 

corrosion are found, before further flight, 

replace the bearing with a new bearing, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3171, Revision 1, dated 

January 25, 2012 (for Model CL–215–6B11 

(CL–215T Variant) airplanes); or Bombardier 

Alert Service Bulletin 215–A4452, Revision 

1, dated January 3, 2012 (for Model CL–215– 

6B11 (CL–415 Variant) airplanes). Repeat the 

inspection, thereafter, before and after each 

fire season or at intervals not to exceed 6 

months, whichever occurs first. 

Note 1 to paragraph (g) of this AD: It is 

suggested that paragraph (g) of this AD be 

carried out in conjunction with AD 2009–05– 

04, Amendment 39–15828 (74 FR 8860, 

February 27, 2009), as the task and task 

intervals are in the same general area. 

(h) Operational Test 

Within 30 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, to 

incorporate the rudder spring tab operational 

test, in accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3171, Revision 1, dated 

January 25, 2012 (for Model CL–215–6B11 

(CL–215T Variant) airplanes); or Bombardier 

Alert Service Bulletin 215–A4452, Revision 

1, dated January 3, 2012 (for Model CL–215– 

6B11 (CL–415 Variant) airplanes). 

(i) Daily Maintenance Procedure Check 

Within 30 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, to 

incorporate a check of the rudder spring tab 

operation into the daily inspection, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A3171, Revision 1, dated 

January 25, 2012 (for Model CL–215–6B11 

(CL–215T Variant) airplanes); or Bombardier 

Alert Service Bulletin 215–A4452, Revision 

1, dated January 3, 2012 (for Model CL–215– 

6B11 (CL–415 Variant) airplanes). 

(j) No Alternative Actions and Intervals 

After accomplishment of the maintenance 

or inspection program revision required by 

paragraphs (h) and (i) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (k)(1) of this AD. 

(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, NY 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–08, dated 

March 12, 2013, for related information. This 

MCAI may be found in the AD docket on the 

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

!documentDetail;D=FAA-2014-0446-0002. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations 5905 

(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 this AD specifies otherwise. 

(i) Bombardier Alert Service Bulletin 215– 

A3171, Revision 1, dated January 25, 2012. 

(ii) Bombardier Alert Service Bulletin 215– 

A4452, Revision 1, dated January 3, 2012. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this 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/ibr-locations.html. 

Issued in Renton, Washington, on January 

12, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01187 Filed 2–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0540; Directorate 

Identifier 2014–NE–10–AD; Amendment 39– 

18074; AD 2015–02–07] 

RIN 2120–AA64 

Airworthiness Directives; Lycoming 

Engines Reciprocating Engines (Type 

Certificate previously held by Textron 

Lycoming Division, AVCO Corporation) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial number (S/N) Lycoming Engines 

reciprocating engines. This AD was 

prompted by propeller governor shaft 

set screws coming loose due to 

improper installation. We are issuing 

this AD to prevent the propeller 

governor shaft set screw from coming 

loose, causing damage to the engine and 

damage to the airplane. 

DATES: This AD is effective March 11, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 11, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Lycoming 

Engines, 652 Oliver Street, 

Williamsport, PA 17701; phone: 800– 

258–3279; fax: 570–327–7101; Internet: 

www.lycoming.com/Lycoming/

SUPPORT/TechnicalPublications/

ServiceBulletins.aspx. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call 781– 

238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0540; 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 

Document 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: 

Norm Perenson, Aerospace Engineer, 

New York Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: 516–228– 

7337; fax: 516–794–5531; email: 

norman.perenson@faa.gov. 

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 S/N Lycoming Engines 

reciprocating engines. The NPRM 

published in the Federal Register on 

September 11, 2014 (79 FR 54218). The 

NPRM was prompted by events of 

propeller governor shaft set screws 

coming loose due to improper 

installation. If the set screws come 

loose, the engine may lose oil resulting 

in damage to the engine and damage to 

the airplane. The NPRM proposed to 

require application of Loctite 290, or 

equivalent, to the threads of the 

propeller governor shaft set screw at 

each installation of the set screw in 

addition to the peening of crankcase 

hole threads. We are issuing this AD to 

prevent the propeller governor shaft set 

screw from coming loose, causing 

damage to the engine and damage to the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 54218, September 11, 2014) or on the 

determination of the cost to the public. 

We did however; find that we 

directed the use of LocTite 290, a 

commercial product by brand name. We 

changed the AD to remove the 

requirement to use any particular brand 

like LocTite 290, from this AD. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information 

We reviewed Lycoming Engines 

Service Instruction No. 1343B, dated 

June 15, 2007. The service instruction 

describes procedures for application of 

sealant for the propeller governor shaft 

set screw and the peening of crankcase 

hole threads. You can find this 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0540. 

Costs of Compliance 

We estimate that this AD will affect 

about 2,330 engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 0.1 hours 

per engine to comply with this AD. The 

average labor rate is $85 per hour. 

Prorated parts life will cost about $1 per 

engine. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $22,135. 

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 


tkelley on DSK3SPTVN1PROD with RULES