17390 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 

for MILC as specified in the 2014 Farm 

Bill to begin receiving payments. During 

the period (referred to as the ‘‘relief 

period’’) beginning April 14, 2014, 

through the close of business on May 

30, 2014, producers with existing MILC 

contracts may select a different 

production start month for FY 2014 by 

completing and submitting form CCC– 

580M ‘‘Milk Income Loss Contract 

Extension (MILC) Modification’’ to FSA. 

For producers with new dairy 

operations that began operation before 

April 14, 2014, FSA will accept 

applications (form CCC–580 ‘‘Milk 

Income Loss Contract (MILC)’’) during 

the relief period. Regular start month 

selection provisions specified in 7 CFR 

1430.205, ‘‘Selection of Starting 

Month,’’ will not apply during the relief 

period. After the relief period ends, 

beginning June 2, 2014, all production 

start month changes for new and 

existing MILC participants must be 

made according to regular start month 

selection provisions as specified in 7 

CFR 1430.205. 

September 2013 was the last eligible 

month for MILC payments under the 

Food, Conservation, and Energy Act of 

2008 (the 2008 Farm Bill, Pub. L. 110– 

246) as extended by the American 

Taxpayer Relief Act of 2012 (Pub. L. 

112–240). The payment rate determined 

for October through December 2013 and 

January 2014, the first four months of 

FY 2014, is zero. Payments for 

subsequent months of FY 2014 will be 

determined as data becomes available. 

The payment rate for MILC is adjusted 

upward when the National Average 

Dairy Feed Ration Cost exceeds certain 

levels. Beginning February 1, 2014, and 

ending on the termination date for 

MILC, if the National Average Dairy 

Feed Ration Cost for a month is greater 

than $7.35 per hundredweight, the 

payment rate for that month will be 

increased by 45 percent of the 

percentage by which the National 

Average Dairy Feed Ration Cost exceeds 

$7.35 per hundredweight. 

DIPP 

The 2014 Farm Bill extended DIPP 

through September 30, 2018 with no 

changes. Through DIPP, FSA issues 

payments to dairy producers for losses 

incurred because they were required to 

remove their milk production from 

commercial markets due to the presence 

of certain chemical or toxic residues. 

Acreage Reporting 

As a condition of eligibility for all 

commodity program and marketing loan 

program benefits specified in Subtitle A 

and Subtitle B of Title I of the 2014 

Farm Bill, producers on farms must 

annually submit acreage reports of all 

cropland on the farm. The report of 

acreage must include the producer or 

producers’ shares and comply with the 

existing regulations specified in 7 CFR 

part 718. 

Payment Eligibility and Payment Limit 

Requirements 

The 2014 Farm Bill modifies the 

payment limit and adjusted gross 

income (AGI) eligibility provisions, 

which are currently specified in 7 CFR 

Part 1400. Beginning with the 2014 crop 

year, the total amount of payments 

received, directly and indirectly, by a 

person or legal entity (except joint 

ventures or general partnerships) for 

Price Loss Coverage, Agricultural Risk 

Coverage, marketing loan gains, and 

loan deficiency payments (other than for 

peanuts), is limited to no more than 

$125,000 annually. A person or legal 

entity that receives, directly or 

indirectly, payments for peanuts has a 

separate $125,000 payment limit for 

those payments. The NAP payment 

limit also increases to $125,000 per 

year. The combined payment limit for 

three of the four disaster programs 

(Livestock Indemnity Program, 

Livestock Forage Disaster Program, and 

Emergency Assistance for Livestock, 

Honey Bees, and Farm-Raised Fish) is 

also increased to $125,000; a separate 

$125,000 limit applies to the Tree 

Assistance Program. 

The 2014 Farm Bill simplifies and 

modifies the average AGI eligibility 

provisions. Producers whose total (farm 

plus nonfarm) average AGI for the 3 tax 

years preceding the most recent 

complete tax year exceeds $900,000 are 

not eligible to receive benefits from 

most programs administered by FSA 

and the Natural Resources Conservation 

Service (NRCS). Previous average AGI 

provisions specified in the 2008 Farm 

Bill had different eligibility limits for 

certain programs based on average farm 

AGI and, for some programs, on average 

nonfarm AGI. 

The AGI and payment limit eligibility 

restrictions from the 2014 Farm Bill 

apply to the 2014 crop, fiscal, or 

program year for payment limits which 

encompass the 2010, 2011, and 2012 tax 

years for purposes of calculating the 

average AGI, and will be implemented 

immediately. The regulations in 7 CFR 

part 1400 will be amended at a later 

date through rulemaking to reflect the 

changes required by the 2014 Farm Bill. 

Environmental Review 

FSA has determined that, in 

accordance with the 7 CFR 799.9(d), 

Environmental Quality and Related 

Environmental Concerns—Compliance 

with the National Environmental Policy 

Act, implementing the regulations of the 

Council on Environmental Quality (40 

CFR parts 1500–1508), continuation of 

these programs as mandated by the 2014 

Farm Bill, will not significantly affect 

the quality of the human environment. 

Therefore, no environmental assessment 

or environmental impact statement will 

be prepared. 

Signed at Washington, DC, on March 25, 

2014. 

Juan M. Garcia, 

Executive Vice President, Commodity Credit 

Corporation and Administrator, Farm Service 

Agency. 

[FR Doc. 2014–06991 Filed 3–27–14; 8:45 am] 

BILLING CODE 3410–05–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0171; Directorate 

Identifier 2014–NM–038–AD; Amendment 

39–17812; AD 2014–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8 

airplanes. This AD requires repetitive 

functional checks of the nose and main 

landing gear, and corrective actions if 

necessary. This AD also provides 

optional terminating action for the 

repetitive functional checks. This AD 

was prompted by a report that the 

emergency downlock indication system 

(EDIS) had given a false landing gear 

down-and-locked indication. We are 

issuing this AD to detect and correct a 

false down-and-locked landing gear 

indication, which, on landing, could 

result in possible collapse of the landing 

gear. 

DATES: This AD becomes effective April 

14, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 14, 2014. 

We must receive comments on this 

AD by May 12, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 


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Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17391 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone: 416–375–4000; fax: 

416–375–4539; email thd.qseries@

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. 

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– 

0171; or in person at the Docket 

Operations office 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. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, 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) 228–7318; 

fax: (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, issued Canadian 

Airworthiness Directive CF–2014–11, 

dated February 13, 2014 (the Mandatory 

Continuing Airworthiness Information, 

referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

During an in-service event where the 

landing gear control panel indicated an 

unsafe nose landing gear, the flight crew 

observed that all three green lights were 

illuminated on the emergency downlock 

indication system. The nose landing gear was 

not down and locked, and collapsed during 

landing. 

Investigation found ambient light and 

wiring shorts can lead to incorrect 

illumination of the green lights on the 

emergency downlock indication system. 

This [TCCA] AD mandates the functional 

check of the nose and main landing gear 

alternate indication phototransistors and the 

modification of the emergency downlock 

indication system. 

The unsafe condition is a false downand-locked landing gear indication, 

which, on landing, could result in 

possible collapse of the landing gear. 

This AD provides the modification as 

optional terminating action for the 

repetitive functional checks of the 

alternate indication phototransistors of 

the nose and main landing gear. You 

may examine the MCAI on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0171. 

Relevant Service Information 

Bombardier has issued the following 

service bulletins. 

• Bombardier Service Bulletin 8–32– 

173, Revision A, dated December 17, 

2012. 

• Bombardier Service Bulletin 8–32– 

176, Revision A, dated February 22, 

2013. 

• Bombardier Service Bulletin 8–32– 

177, dated October 9, 2013. 

• Bombardier Service Bulletin 8–33–56, 

Revision A, dated February 22, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Difference Between This AD and the 

MCAI or Service Information 

Canadian Airworthiness Directive 

CF–2014–11, dated February 13, 2014, 

requires modification of the EDIS. We 

have determined that this EDIS 

modification would eliminate the need 

for the functional checks of the alternate 

indication phototransistors of the nose 

and main landing gear required by this 

AD. Therefore, this final rule provides 

for the modification as an optional 

terminating action for the functional 

checks. However, we are considering 

further rulemaking to require the 

modification on all affected airplanes. 

FAA’s 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 ambient light and wiring 

shorts can lead to incorrect illumination 

of the green lights on the EDIS. This 

condition could lead to the landing gear 

not being down and locked, and 

consequent landing gear collapse during 

landing. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0171; 

Directorate Identifier 2014–NM–038– 

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 based on 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. 

Costs of Compliance 

We estimate that this AD affects 85 

airplanes of U.S. registry. 

We also estimate that it will take 

about 3 work-hours 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. 


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17392 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 

operators to be $21,675, or $255 per 

product, per inspection cycle. 

We estimate that it would take up to 

40 work-hours per product to do the 

optional terminating action provided in 

this AD. Parts would cost up to 

$19,436.00 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be up to $1,941,060, 

or $22,836 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. 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

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): 

2014–06–08 Bombardier, Inc.: Amendment 

39–17812. Docket No. FAA–2014–0171; 

Directorate Identifier 2014–NM–038–AD. 

(a) Effective Date 

This AD becomes effective April 14, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–101, –102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes, certificated 

in any category, serial numbers 003 through 

672 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report that the 

emergency downlock indication system had 

given a false landing gear down-and-locked 

indication. We are issuing this AD to detect 

and correct a false down-and-locked landing 

gear indication, which, on landing, could 

result in possible collapse of the landing 

gear. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Functional Check 

Within 600 flight hours or 100 days, 

whichever occurs first after the effective date 

of this AD: Perform a functional check of the 

alternate indication phototransistors of the 

nose and main landing gear; and do all 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–32–173, 

Revision A, dated December 17, 2012. Do all 

applicable corrective actions before further 

flight. Repeat the functional check thereafter 

at intervals not to exceed 600 flight hours or 

100 days, whichever occurs first, until 

accomplishment of the applicable actions 

specified in paragraph (h) of this AD. 

(h) Optional Terminating Action 

Accomplishment of the applicable actions 

specified in paragraphs (h)(1) through (h)(3) 

of this AD terminates the requirements of 

paragraph (g) of this AD. 

(1) For airplanes configured as described in 

Modsum 8/1519: Incorporate Modsum 

8Q101968, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–33–56, Revision A, dated 

February 22, 2013. 

(2) For airplanes configured as described in 

Modsum 8/0235, 8/0461, and 8/0534: 

Incorporate Modsum 8Q101955, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–176, Revision A, dated February 22, 

2013. 

(3) For airplanes not configured as 

described in Modsum 8/0534: Incorporate 

Modsum 8Q101969, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–177, dated October 9, 

2013. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 8–32–173, dated October 28, 

2011, which is not incorporated by reference 

in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–33–56, dated 

February 11, 2013, which is not incorporated 

by reference in this AD. 

(3) This paragraph provides credit for 

actions required by paragraph (h)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–32–176, dated 

February 11, 2013, which is not incorporated 

by reference in this AD. 

(j) 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. 


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Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Rules and Regulations 17393 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). You are required to 

ensure the product is airworthy before it is 

returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–11, dated 

February 13, 2014, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating Docket No. FAA–2014–0171. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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 Service Bulletin 8–32–173, 

Revision A, dated December 17, 2012. 

(ii) Bombardier Service Bulletin 8–32–176, 

Revision A, dated February 22, 2013. 

(iii) Bombardier Service Bulletin 8–32–177, 

dated October 9, 2013. 

(iv) Bombardier Service Bulletin 8–33–56, 

Revision A, dated February 22, 2013. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone: 416–375–4000; fax: 416–375– 

4539; email: thd.qseries@

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/ibrlocations.html. 

Issued in Renton, Washington, on March 

19, 2014. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06636 Filed 3–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1019; Directorate 

Identifier 2013–CE–038–AD; Amendment 

39–17810; AD 2014–06–06] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

SOCATA Model TBM 700 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 landing gear 

actuator rod and piston becoming 

unscrewed during operation and the 

landing gear actuator ball joint 

becoming uncrimped. We are issuing 

this AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective May 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

1019; 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 SOCATA—Direction 

des Services—65921 Tarbes Cedex 9— 

France; telephone +33 (0) 62 41 7300, 

fax +33 (0) 62 41 76 54, or for North 

America: SOCATA NORTH AMERICA, 

7501 South Airport Road, North Perry 

Airport, Pembroke Pines, Florida 33023; 

telephone: (954) 893–1400; fax: (954) 

964–4141; email: mysocata@

socata.daher.com; Internet: http://

mysocata.com. 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 SOCATA Model TBM 700 airplanes. 

That NPRM was published in the 

Federal Register on December 4, 2013 

(78 FR 72834). That 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 maintenance check, possible 

unscrewing of rod and piston during 

operation was detected on a landing gear 

actuator. Investigation showed that this was 

likely caused by maintenance operation not 

conforming with the procedure described in 

the SOCATA maintenance manual. 

Moreover, following in-service landing 

gear collapse, uncrimping of a right hand 

main landing gear (MLG) actuator ball joint 

was detected. Investigation revealed a 

manufacturing non-conformity of some 

actuator rod end assemblies. 

These conditions, if not detected and 

corrected, could lead to MLG or nose landing 

gear (NLG) failure during landing or roll-out 

and consequent damage to the aeroplane and 

injury to occupants. 

To address this potential unsafe condition, 

SOCATA issued Service Bulletin (SB) 70– 

197–32 to require a one-time inspection of 

the landing gear actuator piston/rod and SB 

70–206–32 to require a one-time inspection 

of the landing gear actuator ball joint 

centering and, depending on findings, 

accomplishment of corrective actions. 

SOCATA also developed modification 70– 

0334–32, embodied in production to secure 

rod/piston assembly through addition of a 

pin and to reduce retraction/extension 

indication failure through improvement of 

switch kinematics. These modified actuators 

have a new part number (P/N). 

For the reasons described above, this AD 

requires a one-time inspection of the landing 

gear actuators piston/rod and ball joint 

centering and, depending on findings, 

accomplishment of applicable corrective 

actions. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1019- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 


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