68764 Federal Register / Vol. 71, No. 228 / Tuesday, November 28, 2006 / Proposed Rules 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) For the serial numbers indicated below, 

within the next 100 hours time-in-service or 

12 months after the effective date of this AD, 

whichever occurs first, do the following 

actions, unless already done: 

(i) For airplane serial numbers 269 and 339 

and up, check the aircraft records to 

determine whether cylinder yoke part 

number ZOO.N7134732200 or the yokes in 

master cylinder assembly part number 

ZOO.N6068757280 (left hand side) and 

ZOO.N6068757281 (right hand side) have 

been replaced. This check can be done by an 

owner/operator holding at least a private 

pilot certificate as authorized by section 43.7 

of the Federal Aviation Regulations (14 CFR 

43.7). 

(A) If you can positively identify that 

master cylinder yoke part number 

ZOO.N7134732200 or the yokes in master 

cylinder assembly part number 

ZOO.N6068757280 (left hand side) and 

ZOO.N6068757281 (right hand side) have 

been replaced, then you must comply with 

paragraph (e)(1)(ii) of this AD. 

(B) If you can positively identify that 

master cylinder yoke part number 

ZOO.N7134732200 or the yokes in master 

cylinder assembly part number 

ZOO.N6068757280 (left hand side) and 

ZOO.N6068757281 (right hand side) have not 

been replaced, then make an entry in the 

aircraft records showing compliance with 

this AD per section 43.9 of the Federal 

Aviation Regulations (14 CFR 43.9). 

(ii) For all airplane serial numbers, unless 

the action is shown not to apply per 

paragraph (e)(1)(i)(B) of this AD, inspect for 

misalignment of the master cylinder yokes 

from their threaded pins, as instructed in the 

EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–136, ATA No. 32, 

dated December 2005, accomplishment 

instructions paragraph. 

(A) If a yoke is found satisfactory, proceed 

to its re-installation on aircraft. 

(B) If a yoke is found defective, prior to 

further flight, discard the yoke and install a 

new part number T700A324004810000 (or 

FAA-approved equivalent part number) yoke 

in accordance with EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

136, ATA No. 32, dated December 2005. 

(2) For all airplane serial numbers, as of the 

effective date of this AD, do not install part 

number ZOO.N7134732200 yokes or yokes in 

master cylinder assembly part number 

ZOO.N6068757280 (left hand side) and 

ZOO.N6068757281 (right hand side), unless 

EADS SOCATA TBM Aircraft Mandatory 

Service Bulletin SB 70–136, ATA No. 32, 

dated December 2005, is complied with. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) It does not allow interim use of yokes 

found defective during inspection. FAA 

policy is to replace defective parts on critical 

systems. 

(2) It applies to all serial numbers. This 

will assure that, if any of the airplanes had 

the affected part number yokes installed after 

delivery of the airplane, the unsafe condition 

is still addressed. It also will assure that any 

of the affected part number yokes are 

inspected per the AD and service bulletin 

before future installation of these parts. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Doug Rudolph, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4059; fax: (816) 

329–4090, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et.seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to European Aviation Safety 

Agency (EASA) AD No.: 2006–0189, dated 

July 4, 2006; and EADS SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70–

136, ATA No. 32, dated December 2005, for 

related information. 

Issued in Kansas City, Missouri, on 

November 20, 2006. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E6–20122 Filed 11–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26180; Directorate 

Identifier 2006–CE–59–AD] 

RIN 2120–AA64 

Airworthiness Directives; EADS 

SOCATA Model TBM 700 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 the 

products listed above. This proposed 

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 the discovery of propeller 

control cables with a defective 

crimping. Two cable ends were found 

uncrimped at the factory after an engine 

run-up test, and one cable end was also 

found uncrimped on the first 100 hour 

aircraft maintenance check. The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by December 28, 

2006. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone (816) 329–

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 


ycherry on PROD1PC61 with PROPOSALS
Federal Register / Vol. 71, No. 228 / Tuesday, November 28, 2006 / Proposed Rules 68765 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certified 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

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–2006–26180; Directorate Identifier 

2006–CE–59–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:// 

dms.dot.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 Direction Ge ́ne ́rale de l’Aviation 

Civile, which is the aviation authority 

for France, has issued French AD No. F–

2004–175, dated November 10, 2004, 

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

correct an unsafe condition for the 

specified products. The MCAI states the 

discovery of propeller control cables 

with a defective crimping. Two cable 

ends were found uncrimped at the 

factory after an engine run-up test, and 

one cable was also found uncrimped on 

the first 100-hour time-in-service 

aircraft maintenance check. If not 

corrected, an incorrect crimping of the 

propeller control lever cable could 

generate a decrease of the propeller 

revolutions per minute which could 

result in loss of power. As for the fuel 

control manual override, this condition 

has no consequence on operation. The 

MCAI requires you to check the batch 

number and/or replace the control 

cables. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

EADS SOCATA has issued EADS 

SOCATA TBM Aircraft Mandatory Alert 

Service Bulletin SB 70–123, ATA No. 

76, dated October 2004. 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 agreements 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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

described in a separate paragraph of the 

proposed AD. These requirements, if 

ultimately adopted, will take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 20 products of U.S. registry. 

We also estimate that it would take 

about 9 work-hours per product to 

comply with the proposed AD. The 

average labor rate is $80 per work-hour. 

Required parts would cost about $2,200 

per product. Where the service 

information lists required parts cost that 

are covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$58,400, or $2,920 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

roles 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 regulations 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulator 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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: 


ycherry on PROD1PC61 with PROPOSALS
68766 Federal Register / Vol. 71, No. 228 / Tuesday, November 28, 2006 / Proposed Rules 

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 § 13.13 by adding 

the following new AD: 

EADS SOCATA: Docket No. FAA–2006–

26180; Directorate Identifier 2006–CE–

59–AD. 

Comments Due Date 

(a) We must receive comments by 

December 28, 2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model TBM 700 

airplanes, serial numbers 285 through 304 

and 307, certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states the 

discovery of propeller control cables with a 

defective crimping. Two cable ends were 

found uncrimped at the factory after an 

engine run-up test, and one cable end was 

also found uncrimped on the first 100-hour 

time-in-service aircraft maintenance check. If 

not corrected, as incorrect crimping of the 

propeller control lever cable could generate 

a decrease of the propeller revolutions per 

minute which could result in loss of power. 

Actions and Compliance 

(e) Unless already done, within the next 50 

hours time-in-service (TIS), inspect for the 

batch number identification and replace 

defective control cables as necessary in 

accordance with the paragraph B. of the 

‘‘ACCOMPLISHMENT INSTRUCTIONS’’ of 

EADS SOCATA TBM Aircraft Mandatory 

Alert Service Bulletin SB 70–123, ATA No. 

76, dated October 2004. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(a) The requirement of paragraph 3.1 for 

the operational procedure was based on the 

urgency in November 2004. However, in 

November 2006, this action is not necessary. 

(2) For the requirement of paragraph 3.2, 

the seriousness of the condition warrants a 

compliance time of 50 hours TIS instead of 

25 hours TIS. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

FAA, ATTN: Albert J. Mercado, Aerospace 

Safety Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4119, fax: (816) 329–4090, has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR part 

39.19. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et.seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(g) Refer to MCAI Director Ge ́ne ́rale de l’

Aviation Civile Airworthiness Directive No. 

F–2004–175, dated November 10, 2004, and 

EADS SOCATA TBM Aircraft Mandatory 

Alert Service Bulletin SB 70–123, ATA No. 

76, dated October 2004, for related 

information. 

Issued in Kansas City, Missouri, on 

November 20, 2006. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–9429 Filed 11–27–06; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25926; Directorate 

Identifier 2000–CE–17–AD] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers & Harland Ltd. Models SC–7 

Series 2 and SC–7 Series 3 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

Airworthiness Directive (AD) 2003–17–

05, which applies to all Short Brothers 

& Harland Ltd. (Shorts) Models SC–7 

Series 2 and SC–7 Series 3 airplanes. 

AD 2003–17–05 currently establishes a 

technical service life for these airplanes 

and allows you to incorporate 

modifications, inspections, and 

replacements of certain life limited 

items to extend the life limits of these 

airplanes. Since we issued AD 2003–17–

05, Shorts Service Bulletin SB 51–51 

was revised to Revision 8, dated July 5, 

2006, and the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, issued an AD for 

the European Community to correct an 

unsafe condition for the specified 

product. AD 2003–17–05 contains 

conflicting information on the repetitive 

visual inspection requirement. 

Consequently, this proposed AD would 

retain the technical service life for these 

airplanes; would continue to allow 

modifications, inspections, and 

replacements of certain life limited 

items to extend the life limits of these 

airplanes; and would clarify the 

repetitive visual inspection requirement 

between one of the service bulletins and 

the maintenance program if an operator 

chooses to extend the life limit. The 

actions specified by this proposed AD 

are intended to clarify the inspection 

information to prevent failure of critical 

structure of the aircraft caused by 

fatigue. 

DATES: We must receive comments on 

this proposed AD by December 28, 

2006. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Short 

Brothers PLC, P.O. Box 241, Airport 

Road, Belfast BT3 9DZ Northern Ireland; 

telephone: +44 (0) 28 9045 8444; 

facsimile: +44 (0) 28 9073 3396. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number, ‘‘FAA–2006–25926; Directorate 


ycherry on PROD1PC61 with PROPOSALS