### 42005 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations

are consistent with the conservation plan during the last year of the contract.

* * * * *

(f) The eligible retired or retiring owner or operator and the eligible beginning, veteran, or socially disadvantaged farmer or rancher must agree to be jointly and severally responsible for complying with both the provisions of the Transition Incentives Program agreement and the provisions of this part, and must also agree to be jointly and severally responsible for any payment adjustments that may result from violations of the terms or conditions of the Transition Incentives Program agreement or this part.

**§§ 1410.1, 1410.2, 1410.3, 1410.6, 1410.8, 1410.10, 1410.11, 1410.22, 1410.32, 1410.33,**  **1410.40, 1410.41, 1410.43, 1410.50, 1410.51, 1410.60, 1410.61, and 1410.62 [Amended]** 

■ 54. In addition to the amendments set forth above, in 7 CFR part 1410, remove the word ‘‘CCC’’ each time it appears and add the words ‘‘the Deputy Administrator’’ in its place, in the following places:

■ a. In § 1410.1(g), (h), and (i);

■ b. In § 1410.2, in the definitions of ‘‘Agricultural commodity’’, ‘‘Commercial pond-raised aquaculture facility’’, ‘‘Field’’, ‘‘Field windbreak, shelterbelt, and/or living snowfence’’, ‘‘Offer’’, ‘‘Offeror’’, ‘‘Operator’’, ‘‘Perennial crop’’, and ‘‘Technical assistance’’;

■ c. In § 1410.3(b) and (d);

■ d. In § 1410.6(a)(2);

■ e. In § 1410.8(a);

■ f. In § 1410.10(b);

■ g. In § 1410.11(b) introductory text, (b)(1), (e), and (g);

■ h. In § 1410.22(e);

■ i. In § 1410.32(b)(3), (d) introductory text, and (f)(2);

■ j. In § 1410.33(d);

■ k. In § 1410.40(b) and (g);

■ l. In § 1410.41(b) and (c);

■ m. In § 1410.43;

■ n. In § 1410.50(a);

■ o. In § 1410.51(a)(1) and (c);

■ p. In § 1410.60(a);

■ q. In § 1410.61; and

■ r. In § 1410.62(h).

Val Dolcini, Administrator, Farm Service Agency, and Executive Vice President, Commodity Credit Corporation.
[FR Doc. 2015–17317 Filed 7–15–15; 8:45 am]

**BILLING CODE 3410–05–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0086; Directorate Identifier 2014–NM–191–AD; Amendment**  **39–18206; AD 2015–14–08]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Airbus Model A310–203 airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD was prompted by reports that side link clevis bolts of the front engine mount do not meet the design service goal (DSG) requirements on airplanes equipped with General Electric Company CF6– 80A3 engines. This AD requires repetitive replacement of all side link clevis engine mount bolts. We are issuing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.

**DATES :**  This AD becomes effective August 20, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 20, 2015.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0086or 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 Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: account.airworth-eas@airbus.com ; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
0086.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–2125; fax: 425–227–1149.

**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 all Airbus Model A310–203 airplanes. The NPRM published in the Federal Register on February 18, 2015 (80 FR 8575). The NPRM is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. The NPRM was prompted by reports that side link clevis bolts of the front engine mount do not meet the DSG requirements on airplanes equipped with General Electric Company CF6– 80A3 engines. The NPRM proposed to require repetitive replacement of all side link clevis engine mount bolts. We are issuing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014–0191, dated August 29, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A310–203 airplanes. The MCAI states:

During fatigue analysis performed in the scope of the Extended Service Goal, taking into account the certification loads and the new lift-off loads, Airbus determined that side link clevis engine mount bolts do not meet the Design Service Goal (DSG) requirements on aeroplanes equipped with CF6–80A3 engines.

This condition, if not corrected, could lead to failure of the front engine mount, possibly resulting in-flight separation of the engine from the aeroplane.

To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A310– 71–2038 to introduce a life limit on the side link clevis engine mount bolts.

For the reason described above, this [EASA] AD requires implementation of the new life limit and replacement of all side link clevis engine mount bolts that have exceeded the new limit.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/


### 42006 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations

#!documentDetail;D=FAA-2015-0086-
0003.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 8575, February 18, 2015) 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 (80 FR 8575, February 18, 2015) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 8575, February 18, 2015).

Related Service Information Under 1 CFR Part 51

We reviewed Airbus Service Bulletin A310–71–2038, including Appendices 01 and 02, dated April 8, 2014. The service information describes procedures for replacement of all side link clevis bolts on the CF6–80A3 frontengine mount and subsequent reidentification of the newly installed bolts with a cross (to differentiate them from the old ones). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section of this AD. Costs of Compliance

We estimate that this AD affects 13 airplanes of U.S. registry.

We also estimate that it will take about 142 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 cost about $2,900 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $194,610, or $14,970 per product. 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. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0086; 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):

2015–14–08 Airbus: Amendment 39–18206. Docket No. FAA–2015–0086; Directorate Identifier 2014–NM–191–AD.
(a) Effective Date

This AD becomes effective August 20,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to Airbus Model A310– 203 airplanes, certificated in any category, all manufacturer serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason

This AD was prompted by reports that side link clevis bolts of the front engine mount do not meet the Design Service Goal (DSG) requirements on airplanes equipped with General Electric Company CF6–80A3 engines. We are issuing this AD to prevent failure of the front engine mount, and consequent possible departure of the engine.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Repetitive Bolt Replacement

Within 18 months after the effective date of this AD, replace the side link clevis bolts, nuts, and bushings of the front engine mount on both engines, and re-identify the new installed bolts with a cross (to differentiate them from the old ones), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–71–2038, including Appendices 01 and 02, dated April 8, 2014. Repeat the replacement thereafter at intervals not to exceed 29 years.
(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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate


### 42007 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations

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 2014–0191, dated August 29, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-0086-0003.
(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 Service Bulletin A310–71–2038, including Appendices 01 and 02, dated April 8, 2014.

(ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ 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 July 2,
2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–17202 Filed 7–15–15; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD; Amendment 39–**  **18177; AD 2015–12–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Honeywell International Inc. Turboprop Engines** 

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

**ACTION :**  Final rule; correction.

**SUMMARY :**  The FAA is correcting an airworthiness directive (AD) that published in the Federal Register . That AD applies to all Honeywell International Inc. TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR turboprop engines with certain Honeywell part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, installed. The AD number in the document headings is incorrect. Additionally, the Amendment number in the regulatory text is incorrect. This document corrects these two errors. In all other respects, the original document remains the same.

**DATES :**  This final rule is effective on July 22, 2015. The effective date of AD 2015– 12–04, Amendment 39–18177 (80 FR 34534, June 17, 2015) remains July 22,
2015.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 :**  Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627–5246; fax: 562–627–5210; email: joseph.costa@ faa.gov.

**SUPPLEMENTARY INFORMATION :**  AD 2015– 12–04, Amendment 39–18177, 80 FR 34534, June 17, 2015), requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals.

As published, the AD number in the document headings is incorrect. Additionally, the Amendment number in the regulatory text of AD 2015–12–04 is incorrect.

No other part of the final rule has been changed.

The effective date of AD 2015–12–04 remains July 22, 2015. Correction of Non-Regulatory Text

In the Federal Register of June 17, 2015, AD 2015–12–04; Amendment 39– 18177 (80 FR 34534) is corrected as follows:

On page 34534, in the 2nd column, on line 6, change ‘‘2014–12–04’’ to ‘‘2015– 12–04’’. Correction of Regulatory Text

**§ 39.13 [Corrected]**

■ 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2006–15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006), and adding the following new AD:
2015–12–04 Honeywell International Inc.: Amendment 39–18177; Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD.
(a) Effective Date

This AD is effective August 20, 2015.
(b) Affected ADs

This AD replaces AD 2006–15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006).
(c) Applicability

This AD applies to all Honeywell International Inc. TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR turboprop engines with Honeywell part numbers (P/Ns) for Woodward fuel control unit (FCU) assemblies listed in Table 1 to paragraph (c) of this AD, installed.



### TABLE 

### 1 TO 

### PARAGRAPH 

### (C

### )—A FFECTED 

### FCU ASSEMBLY 

### P/N S

Group No. Engine FCU Assembly P/Ns

1 ..................... TPE331–1, –2, and –2UA ........................ P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, –34, and –35.