This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

72834 

Vol. 78, No. 233 

Wednesday, December 4, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1019; Directorate 

Identifier 2013–CE–038–AD] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

SOCATA Model TBM 700 airplanes. 

This proposed AD results from 

mandatory continuing airworthiness 

information (MCAI) originated 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 proposed AD to require actions to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by January 21, 2014. 

ADDRESSES: You may send comments 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 proposed 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 review 

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. 

Examining the AD Docket 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–1019; Directorate Identifier 

2013–CE–038–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2013–0227, dated September 23, 2013 

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

correct an unsafe condition for the 

specified products. 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. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2013–1019. 

Relevant Service Information 

SOCATA has issued DAHER– 

SOCATA Mandatory Service Bulletin 

SB 70–197, dated April 2013; and 

DAHER–SOCATA Mandatory Service 


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Federal Register / Vol. 78, No. 233 / Wednesday, December 4, 2013 / Proposed Rules 72835 

Bulletin SB 70–206, dated April 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 the Proposed 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 495 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $84,150, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours for each main 

landing gear and 3 work-hours for the 

nose landing gear, and require parts 

costing $100 for each rod and assembly. 

We have no way of determining the 

number of products that may need these 

actions. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 AD: 

SOCATA: Docket No. FAA–2013–1019; 

Directorate Identifier 2013–CE–038–AD. 

(a) Comments Due Date 

We must receive comments by January 21, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to SOCATA TBM 700 

airplanes, all serial numbers, certificated in 

any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated 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 the 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 detect and correct 

discrepancies in the pistons/rods and the ball 

joint centering of the nose landing gear and 

main landing gear, which could result in 

landing gear failure and lead to damage of the 

airplane and occupant injury. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) through (f)(4) of this AD on 

any airplane with the landing gear actuators 

part number (P/N) T700A3230050000, P/N 

T700A323005000000, or P/N 

T700A323005300000 installed: 

(1) Within the next 8 months after the 

effective date of this AD, perform a detailed 

visual inspection (DVI) of the pistons and 

rods of the nose landing gear (NLG) and left 

hand (LH) and right hand (RH) main landing 

gear (MLG) actuators and measure the 

distance following the Accomplishment 

Instructions paragraphs (A)(1) through (A)(4) 

in DAHER–SOCATA Mandatory Service 

Bulletin SB 70–197, dated April 2013. 

(2) Within the next 8 months after the 

effective date of this AD, perform a DVI of 

the ball joint centering of the NLG and LH 

and RH MLG actuators and measure the ball 

joint mismatch following the 

Accomplishment Instructions paragraphs (A) 

through (C) in DAHER–SOCATA Mandatory 

Service Bulletin SB 70–206, dated April 

2013. 

(3) If during any inspection required in 

paragraphs (f)(1) or (f)(2) of this AD any 

discrepancy is found, before further flight, 

replace the affected actuator or rod end 

assembly if applicable with an airworthy part 

following the Accomplishment Instructions 

in paragraph (A)(5) through (A)(10) and 

paragraph (B) of DAHER–SOCATA 

Mandatory Service Bulletin SB 70–197, dated 

April 2013; and/or paragraph (D) and (E) of 

DAHER–SOCATA Mandatory Service 

Bulletin SB 70–206, dated April 2013. 

(4) As of the effective date of this AD, do 

not install on any airplane a landing gear 

actuator P/N T700A3230050000, P/N 

T700A323005000000, or P/N 

T700A323005300000, unless it is found to be 

in compliance with the inspection 

requirements of paragraphs (f)(1) and (f)(2) of 

this AD. The landing gear actuator must be 

installed when doing these inspections. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: 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. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 


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appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0227, dated 

September 23, 2013 for related information. 

You may examine the MCAI on the Internet 

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

for and locating it in Docket No. FAA–2013– 

1019. For service information related to 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 review 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. 

Issued in Kansas City, Missouri, on 

November 27, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–29006 Filed 12–3–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0977; Directorate 

Identifier 2013–NM–190–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 717–200 

airplanes. This proposed AD was 

prompted by multiple reports of 

cracking in the overwing frames. This 

proposed AD would require repetitive 

inspections for cracking in the overwing 

frames, and corrective actions if 

necessary. We are proposing this AD to 

detect and correct such cracking, which 

could result in a severed frame and 

might increase the loading of adjacent 

frames, resulting in damage to the 

adjacent structure and consequent loss 

of structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 21, 2014. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https://

www.myboeingfleet.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; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street 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: Eric 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, Los 

Angeles Aircraft Certification Office 

(ACO), FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5348; fax: 562–627– 

5210; email: eric.schrieber@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0977; Directorate Identifier 2013– 

NM–190–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

We received multiple reports of 

cracking in the overwing frames on 

Boeing Model 717 airplanes. The 

airplanes had accumulated between 

18,235 and 36,208 total flight hours, and 

between 11,991 and 45,091 total flight 

cycles. The cracks, caused by fatigue, 

originated in the upper radius of the 

frame inboard tab just below the floor. 

This condition, if not corrected, could 

result in a severed frame, which might 

increase the loading of adjacent frames 

and result in damage to the adjacent 

structure and consequent loss of 

structural integrity of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 717–53A0036, dated August 12, 

2013. For information on the procedures 

and compliance times, see this service 

information at http://regulations.gov by 

searching for Docket No. FAA–2013– 

0977. 

FAA’s Determination 

We are proposing 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 the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 


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