### 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 thisAD, 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


### 5903 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations

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 Co

ˆ te-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.


### 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.


### 5905 Federal Register / Vol. 80, No. 23 / Wednesday, February 4, 2015 / Rules and Regulations

(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 Co ˆ teVertu 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