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

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/


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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 front 

engine 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 


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

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)—AFFECTED FCU ASSEMBLY P/NS

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. 


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