### 4764 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations

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):

2015–02–17 Airbus: Amendment 39–18084. Docket No. FAA–2015–0078; Directorate Identifier 2014–NM–235–AD.

(a) Effective Date

This AD becomes effective February 13,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers.

(1) Airbus Model A330–201, –202, –203, –223, –223F, –243, and –243F airplanes.

(2) Airbus Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes.
(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical Power.

(e) Reason

This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the constant speed motor/generator (CSM/G) during slat/flap extension when only one engine is running. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Revise Airplane Flight Manual (AFM)

Within 15 days after the effective date of this AD, revise the Emergency Procedures section of the Airbus A330 AFM to include the information in the applicable Airbus temporary revision (TR) specified in paragraph (g)(1) or (g)(2) of this AD. This may be done by inserting a copy of the applicable TR specified in paragraph (g)(1) or (g)(2) of this AD into the AFM. Operate the airplane according to the procedures in the applicable TR. When the information in the applicable TR has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revision is identical to that in the TR, and the TR may be removed.

(1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7,
2014.

(2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7,
2014.
(h) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. 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, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(i) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0281, dated December 22, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0078. (j) 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) Airbus A330/A340 Airplane Flight Manual (AFM) Temporary Revision TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7,
2014.

(ii) Airbus A330/A340 AFM Temporary Revision TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.

(3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com ; Internet http://www.airbus.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/ibrlocations.html

.

Issued in Renton, Washington, on January 9, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–01178 Filed 1–28–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0683; Directorate Identifier 2010–NE–25–AD; Amendment 39–**  **18065; AD 2015–02–01]**

**RIN 2120–AA64**

**Airworthiness Directives; Technify Motors GmbH (Type Certificate**  **Previously Held by Thielert Aircraft Engines GmbH) Reciprocating Engines** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are superseding airworthiness directive (AD) 2011–23– 01 for all Technify Motors GmbH (TMG) models TAE 125–01 and TAE 125–02– 99 reciprocating engines with certain part number (P/N) and serial number (S/ N) clutch assemblies installed. AD 2011–23–01 required replacement of certain P/N and S/N clutch assemblies. This AD requires the same actions but


### 4765 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations

expands the population of affected P/N and S/N clutch assemblies. This AD was prompted by an additional report of a clutch assembly that malfunctioned due to disk springs that received a nonconforming heat treatment process. We are issuing this AD to prevent failure of the clutch assembly, whichcould lead to failure of the engine, inflight shutdown, and loss of control of the airplane.

**DATES :**  This AD is effective February 13,
2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 13, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 22, 2011 (76 FR 68636, November 7, 2011).

We must receive any comments on this AD by March 16, 2015.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Technify Motors GmbH, Platanenstrasse 14, D–09356 Sankt Egidien, Germany; phone: +49– 37204–696–0; fax: +49–37204–696–55; email: info@centurion-engines.com . 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–2010– 0683; 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 mandatory continuing airworthiness information, regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7120; fax: (781) 238–7199; email: Chris.McGuire@faa.gov

. **SUPPLEMENTARY INFORMATION :** 
Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2010–0683; Directorate Identifier 2010– NE–25–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.

Discussion

On August 16, 2010, we issued AD 2010–18–02, Amendment 39–16415 (75 FR 52240, August 25, 2010), (‘‘AD 2010– 18–02’’), for certain Thielert Aircraft Engines GmbH (TAE) (previous certificate holder) models TAE 125–01 and TAE 125–02–99 reciprocating engines. AD 2010–18–02 resulted from reports of engine in-flight shutdowns. Preliminary investigation showed that nonconforming disc springs used in a certain production batch of the clutch caused the shutdowns. AD 2010–18–02 required replacement of certain clutch assemblies.

On October 19, 2011, we superseded AD 2010–18–02, issuing AD 2011–23– 01, Amendment 39–16852 (76 FR 68636, November 7, 2011), for certain TAE models TAE 125–01 and TAE 125– 02–99 reciprocating engines. AD 2011– 23–01 required replacement of certain P/N and S/N clutch assemblies due to clutch failure. AD 2011–23–01 resulted from TAE identifying additional clutch assemblies with nonconforming disc springs.

Actions Since AD 2011–23–01 Was Issued

Since we issued AD 2011–23–01, Amendment 39–16852 (76 FR 68636, November 7, 2011), we received an additional report of a malfunctioning clutch assembly. Investigation found that the same unsafe condition exists on approximately 40 additional S/N clutch assemblies that have nonconforming disk springs. Those additional nonconforming disc springs are identified in TMG Service Bulletin No. TM TAE 125–0021, Revision 2, dated October 13, 2014.

FAA’s Determination

We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs.
AD Requirements

This AD requires, for engines with affected clutch assemblies with more than 100 hours time since new (TSN), replacement of affected clutch assemblies before further flight. This AD also requires, for those engines with affected clutch assemblies that have accumulated less than 100 hours TSN, replacement of affected clutch assemblies before accumulating 100 hours TSN.
FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because TMG identified additional clutch assemblies with nonconforming disc springs and the need for operators to comply with some of the AD actions before further flight. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance

We estimate that this AD will affect about 111 engines installed on airplanes of U.S. registry. We also estimate that it will take about 16 hours per engine to perform the clutch assembly replacement. The average labor rate is $85 per hour. Required parts will cost about $1,796. Based on these figures, we


### 4766 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations

estimate the cost of the AD on U.S. operators to be $350,316.
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

This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866,

(2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and

(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
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 part 39 of the Federal Aviation Regulations (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 removing airworthiness directive (AD) 2011–23–01, Amendment 39–16852 (76 FR 68636, November 7, 2011), and adding the following new AD: 2015–02–01 Technify Motors GmbH (Type Certificate previously held by Thielert Aircraft Engines GmbH): Amendment 39–18065; Docket No. FAA–2010–0683; Directorate Identifier 2010–NE–25–AD.
(a) Effective Date

This AD is effective February 13, 2015.
(b) Affected ADs

This AD supersedes AD 2011–23–01, Amendment 39–16852 (76 FR 68636, November 7, 2011).
(c) Applicability

This AD applies to Technify Motors GmbH (TMG) models TAE 125–01 and TAE 125– 02–99 reciprocating engines, with a clutch assembly part number (P/N) listed in paragraphs (c)(i) through (c)(v) of this AD, and with a serial number (S/N) listed in either TMG Service Bulletin (SB) No. TM TAE 125–0021, Revision 2, dated October 13, 2014, or Thielert Aircraft Engines GmbH (TAE) SB No. TM TAE 125–1011 P1, Revision 2, dated August 31, 2011, installed. (i) P/N 02–7210–11001R11 (ii) P/N 02–7210–11001R11–AT (iii) P/N 02–7210–11001R13 (iv) P/N 05–7211–K006001 (v) P/N 05–7211–K006002
(d) Unsafe Condition

This AD was prompted by TMG identifying 40 additional S/N clutch assemblies with nonconforming disk springs for TMG TAE 125–01 reciprocating engines. We are issuing this AD to prevent failure of the clutch assembly, which could lead to failure of the engine, in-flight shutdown, and loss of control of the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.

After the effective date of this AD: (1) For engines with affected clutch assemblies that have accumulated 100 hours time since new (TSN) or more, replace the clutch assembly before further flight.

(2) For engines with affected clutch assemblies that have accumulated less than 100 hours TSN, replace the clutch assembly before accumulating 100 hours TSN.
(f) Installation Prohibition

After the effective date of this AD, do not install onto any airplane any engine having a clutch assembly, P/N 02–7210–11001R11, P/N 02–7210–11001R11–AT, P/N 02–7210– 11001R13, P/N 05–7211–K006001, or P/N 05–7211–K006002, installed, that has an S/N listed in TMG SB No. TM TAE 125–0021, Revision 2, dated October 13, 2014, or in TAE SB No. TM TAE 125–1011 P1, Revision 2, dated August 31, 2011.
(g) Credit for Previous Actions

If before the effective date of this AD you replaced an affected clutch assembly with a clutch assembly not listed in this AD, or with one not listed in either TMG SB No. TM TAE 125–0021, Revision 2, dated October 13, 2014, or TAE SB No. TM TAE 125–1011 P1, Revision 2, dated August 31, 2011, then you met the requirements of paragraph (e) of this AD and no further action is required to comply with this AD.
(h) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov.
(i) Related Information

(1) For more information about this AD, contact Christopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7120; fax: (781) 238– 7199; email: Chris.McGuire@faa.gov.

(2) Refer to MCAI European Aviation Safety Agency AD 2014–0232, dated October 22, 2014 and corrected on November 4, 2014, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2010–
0683. (j) 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.

(3) The following service information was approved for IBR on February 13, 2015.

(i) Technify Motors GmbH (TMG) Service Bulletin (SB) No. TM TAE 125–0021, Revision 2, dated October 13, 2014.

(ii) Reserved. (4) The following service information was approved for IBR on November 22, 2011.

(i) Thielert Aircraft Engines GmbH (TAE) SB No. TM TAE 125–1011 P1, Revision 2, dated August 31, 2011.

(ii) Reserved. (5) For TMG and TAE service information identified in this AD, contact Technify Motors GmbH, Platanenstrasse 14, D–09356 Sankt Egidien, Germany; phone: +49–37204– 696–0; fax: +49–37204–696–55; email: info@ centurion-engines.com.

(6) You may view this service information at 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.

(7) You may view this service information at the National Archives and Records


### 4767 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations

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 Burlington, Massachusetts, on January 8, 2015. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2015–00991 Filed 1–28–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0876; Directorate Identifier 2014–CE–032–AD; Amendment**  **39–18076; AD 2015–02–09]**

**RIN 2120–AA64**

**Airworthiness Directives; Costruzioni Aeronautiche Tecnam srl Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking found in the engine exhaust pipe. We are issuing this AD to require actions to address the unsafe condition on these products.

**DATES :**  This AD is effective March 5,
2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 5, 2015.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0876; or in person at 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 service information identified in this AD, contact Costruzioni Aeronautiche Tecnam Airworthiness Office, Via Maiorise–81043 Capua (CE) Italy; telephone: +39 0823 997538; fax: +39 0823 622899; email: technical.support@tecnam.com; Internet: http://www.tecnam.com/ Customer-Care/Service-Bulletins.aspx. You may view this referenced service information at the 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.

**FOR FURTHER INFORMATION CONTACT :**  Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to add an AD that would apply to Costruzioni Aeronautiche Tecnam srl Model P2006T airplanes. The NPRM was published in the Federal Register on October 29, 2014 (79 FR 64347). The NPRM proposed to correct an unsafe condition for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI states:

During a pre-flight inspection of a P2006T aeroplane, which included the opening of engine nacelle, a crack was found on the engine exhaust pipe Part Number (P/N) 26–
7–1800–1.

This condition, if not detected and corrected, could lead to engine damage, possibly resulting in damage to the aeroplane and injury to the occupants.

To address this potential unsafe condition, Costruzioni Aeronautiche TECNAM issued Service Bulletin (SB) SB 170–CS–Ed 1 Rev1.

For the reason described above, this AD requires a one-time inspection of the affected engine exhaust pipes and, depending on findings, replacement.
The MCAI can be found in the AD docket on the Internet at: http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0876-
0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 the 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 64347, October 29, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM.

Relative Service Information

We reviewed Costruzioni Aeronautiche TECNAM Service Bulletin No. SB 170–CS-Ed 1, Rev 1, dated September 25, 2014. The service bulletin describes procedures for inspecting and replacing (as necessary) the engine exhaust pipes. You can find this service information on the Internet
at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0876. Costs of Compliance

We estimate that this AD will affect 10 products of U.S. registry. We also estimate that it would take about .5 work-hour 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 on U.S. operators to be $425, or $42.50 per product.

In addition, we estimate that any necessary follow-on actions would take about .5 work-hour and require parts costing $343, for a cost of $385.50 per product. We have no way of determining the number of products that may need these actions. Paperwork Reduction Act

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue