Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes, 66889-66891 [E6-19443]

Download as PDF Federal Register / Vol. 71, No. 222 / Friday, November 17, 2006 / Proposed Rules must also show that a lightning strike on a composite fan blade will not result in a hazardous condition to the aircraft and that the engine will continue to meet the requirements of § 33.75. Therefore, due to the close similarity of the GEnx model series fan blade design to the previously certified GE90 model series fan blade design, the FAA is proposing to issue similar special conditions as part of the type certification basis for the GEnx engine models in lieu of direct compliance to § 33.94(a)(1). These special conditions define the additional requirements that the Administrator considers necessary to establish a level of safety equivalent to that which would be established by direct compliance to the airworthiness standards of § 33.94(a)(1). Type Certification Basis Under 14 CFR 21.17, GE must show that the GEnx series turbofan engine models meet the requirements of the applicable provisions of § 21.21 and part 33. The FAA has determined that the applicable airworthiness regulations in part 33 do not contain adequate or appropriate safety standards for the GEnx series turbofan engine models because of its novel and unusual fan blade design features. Therefore, these special conditions are prescribed under the provisions of 14 CFR 11.19 and § 21.16, and will become part of the type certification basis of the GEnx engine in accordance with 14 CFR 21.17(a)(2). As discussed above, these special conditions apply only to the GEnx series turbofan engine models. If the type certificate for those models is amended later to include any other models that incorporate the same novel or unusual design features, these special conditions would also apply to the other models under the provisions of 14 CFR 21.101(a)(1). Novel or Unusual Design Features The GEnx–1B54, –1B58, –1B64, –1B67, –70B, –1B70/72, –1B70/75, –72B and –75B engine models will incorporate the following novel or unusual design features: fan blades to be manufactured using carbon graphite composite material that incorporates metal leading and training edges. jlentini on PROD1PC65 with PROPOSAL Applicability As discussed above, these special conditions apply only to the GEnx– 1B54, –1B58, –1B64, –1B67, –70B, –1B70/72, –1B70/75, –72B and –75B turbofan engine models. If GE applies later for a change to the type certificate to include another model incorporating the same novel or unusual fan blade VerDate Aug<31>2005 16:07 Nov 16, 2006 Jkt 211001 design features, these special conditions would apply to that model as well. Conclusion This action affects only the carbon fiber composite fan blade design features on the GEnx series turbofan engine models. It is not a rule of general applicability, and it affects only the General Electric Company which has applied to the FAA for certification of these fan blade design features. List of Subjects in 14 CFR Part 33 Air transportation, Aircraft, Aviation safety, Safety. The authority citation for these special conditions continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701– 44702, 44704. The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the GEnx series turbofan engines. 1. In lieu of the fan blade containment test with the fan blade failing at the outermost retention groove as specified in § 33.94(a)(1), complete the following requirements: (a) Conduct an engine fan blade containment test with the fan blade failing at the inner annulus flow path line. (b) Substantiate by test and analyses, or other methods acceptable to the Administrator, that a minimum material properties fan disk and fan blade retention system can withstand without failure a centrifugal load equal to two times the maximum load which the retention system could experience within approved engine operating limitations. The fan blade retention system includes the portion of the fan blade from the inner annulus flow path line inward to the blade dovetail, the blade retention components, and the fan disk and fan blade attachment features. (c) Using a procedure approved by the Administrator, establish an operating limitation that specifies the maximum allowable number of start-stop stress cycles for the fan blade retention systems. The life evaluation shall include the combined effects of high cycle and low cycle fatigue. If the operating limitation is less than 100,000 cycles, that limitation must be specified in Chapter 5 of the Engine Manual Airworthiness Limitation Section. (d) Substantiate that, during the service life of the engine, the total probability of the occurrence of a hazardous engine effect defined in § 33.75 due to an individual blade PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 66889 retention system failure resulting from all possible causes will be extremely improbable, with a cumulative calculated probability of failure of less than 10¥9 per engine flight hour. (e) Substantiate by test or analysis that not only will the engine continue to meet the requirements of § 33.75 following a lightning strike on the composite fan blade structure, but that the lightning strike will also not cause damage to the fan blades that would prevent continued safe operation of the affected engine. (f) Account for the effects of in-service deterioration, manufacturing variations, minimum material properties, and environmental effects during the tests and analyses required by paragraphs (a), (b), (c), (d), and (e) of these special conditions. (g) Propose fleet leader monitoring and field sampling programs for the GEnx engine fan blades that will monitor the effects of usage on fan blade and retention system integrity. The sampling program should use the experience gained on current GE90 engine model monitoring programs, and must be approved by the FAA prior to certification of the GEnx engine models. Issued in Burlington, Massachusetts on November 7, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–9230 Filed 11–16–06; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26166; Directorate Identifier 2006–CE–58–AD] RIN 2120–AA64 Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 cracks on a vertical E:\FR\FM\17NOP1.SGM 17NOP1 66890 Federal Register / Vol. 71, No. 222 / Friday, November 17, 2006 / Proposed Rules stabilizer attachment fitting due to corrosion, have been found on an aircraft in service. 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 18, 2006. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https:// 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: https:// www.regulations.gov. Follow the instructions for submitting comments. jlentini on PROD1PC65 with PROPOSAL Examining the AD Docket You may examine the AD docket on the Internet at https://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 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.-certificated products. VerDate Aug<31>2005 16:07 Nov 16, 2006 Jkt 211001 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–2006–26166; Directorate Identifier 2006–CE–58–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 https:// 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. 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. Discussion ´ ´ The Direction generale de l’aviation civile (DGAC), which is the aviation authority for France, has issued French AD No F–2003–366 R1, dated November 24, 2004 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states cracks on a vertical stabilizer attachment fitting due to corrosion have been found on an aircraft in service. This MCAI requires you to inspect the vertical stabilizer attachment fittings and bolts for cracks or corrosion and, if necessary, repair or replace the damaged parts. 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 Service Bulletin SB 70–104, Amendment 1, ATA No. 55, dated August 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 agreement with this State of PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 205 products of U.S. registry. We also estimate that it would take about 4 work-hours per product to comply with the proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $3,000 per product. Where the service information lists required parts costs 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 $680,600, or $3,320 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 E:\FR\FM\17NOP1.SGM 17NOP1 Federal Register / Vol. 71, No. 222 / Friday, November 17, 2006 / Proposed Rules Applicability 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. (c) This AD applies to SOCATA TBM 700 airplanes, serial numbers 1 through 308, plus the serial number 310, certificated in any category. Note 1: This AD does not apply to airplanes in which both modifications No. MOD70–127–55 and MOD70–129–53 have been factory installed. Regulatory Findings Reason 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 Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. (d) The mandatory continuing airworthiness information (MCAI) states cracks on a vertical stabilizer attachment fitting due to corrosion, have been found on an aircraft in service. 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: 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: jlentini on PROD1PC65 with PROPOSAL EADS SOCATA: Docket No. FAA–2006– 26166; Directorate Identifier 2006–CE– 58–AD Comments Due Date (a) We must receive comments by December 18, 2006. Affected ADs (b) None. VerDate Aug<31>2005 16:07 Nov 16, 2006 Jkt 211001 66891 Related Information ´ ´ (g) Refer to Direction generale de l’aviation civile (DGAC) AD No F–2003–366 R1, dated November 24, 2004; and EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–104, Amendment 1, ATA No. 55, dated August 2004, for related information. Issued in Kansas City, Missouri, on November 9, 2006. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–19443 Filed 11–16–06; 8:45 am] BILLING CODE 4910–13–P Actions and Compliance (e) Unless already done, do the following actions. (1) Within the next 600 hours time-inservice (TIS) or at the next annual inspection, whichever occurs first after the effective date of this AD, inspect vertical stabilizer attachment fittings and bolts for cracks or corrosion and if necessary repair or replace the damaged part and then apply a corrosion protection reinforcement, following EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70–104, Amendment 1, ATA No. 55, dated August 2004. (2) Repeat the actions of paragraph (e)(1) every 1,200 hours TIS or every 2 annual inspections whichever occurs first after the effective date of this AD, following EADS SOCATA Service Bulletin SB 70–104, Amendment 1, ATA No. 55, dated August 2004. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. 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 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 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. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26234; Directorate Identifier 2006–CE–64–AD] RIN 2120–AA64 Airworthiness Directives; EADS SOCATA Model TBM 700 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 loose rivets on frames C18 BIS and C19, which could result in a reduced structural integrity of the tail area. 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 18, 2006. You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://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, ADDRESSES: E:\FR\FM\17NOP1.SGM 17NOP1

Agencies

[Federal Register Volume 71, Number 222 (Friday, November 17, 2006)]
[Proposed Rules]
[Pages 66889-66891]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19443]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26166; Directorate Identifier 2006-CE-58-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 cracks on a vertical

[[Page 66890]]

stabilizer attachment fitting due to corrosion, have been found on an 
aircraft in service. 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 18, 
2006.

ADDRESSES: You may send comments by any of the following methods:
     DOT Docket Web Site: Go to https://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: https://www.regulations.gov. 
Follow the instructions for submitting comments.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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 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.-certificated 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-
26166; Directorate Identifier 2006-CE-58-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 https://
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 g[eacute]n[eacute]rale de l'aviation civile (DGAC), 
which is the aviation authority for France, has issued French AD No F-
2003-366 R1, dated November 24, 2004 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states cracks on a vertical stabilizer attachment fitting due to 
corrosion have been found on an aircraft in service. This MCAI requires 
you to inspect the vertical stabilizer attachment fittings and bolts 
for cracks or corrosion and, if necessary, repair or replace the 
damaged parts. 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 Service 
Bulletin SB 70-104, Amendment 1, ATA No. 55, dated August 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 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.

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 205 products of U.S. registry. We also estimate that 
it would take about 4 work-hours per product to comply with the 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $3,000 per product. Where the service 
information lists required parts costs 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 $680,600, 
or $3,320 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

[[Page 66891]]

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); and
    3. 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.
    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:

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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

EADS SOCATA: Docket No. FAA-2006-26166; Directorate Identifier 2006-
CE-58-AD

Comments Due Date

    (a) We must receive comments by December 18, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to SOCATA TBM 700 airplanes, serial numbers 
1 through 308, plus the serial number 310, certificated in any 
category.

    Note 1: This AD does not apply to airplanes in which both 
modifications No. MOD70-127-55 and MOD70-129-53 have been factory 
installed.

Reason

    (d) The mandatory continuing airworthiness information (MCAI) 
states cracks on a vertical stabilizer attachment fitting due to 
corrosion, have been found on an aircraft in service.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Within the next 600 hours time-in-service (TIS) or at the 
next annual inspection, whichever occurs first after the effective 
date of this AD, inspect vertical stabilizer attachment fittings and 
bolts for cracks or corrosion and if necessary repair or replace the 
damaged part and then apply a corrosion protection reinforcement, 
following EADS SOCATA TBM Aircraft Mandatory Service Bulletin SB 70-
104, Amendment 1, ATA No. 55, dated August 2004.
    (2) Repeat the actions of paragraph (e)(1) every 1,200 hours TIS 
or every 2 annual inspections whichever occurs first after the 
effective date of this AD, following EADS SOCATA Service Bulletin SB 
70-104, Amendment 1, ATA No. 55, dated August 2004.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: No differences.

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 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 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 Direction g[eacute]n[eacute]rale de l'aviation 
civile (DGAC) AD
    No F-2003-366 R1, dated November 24, 2004; and EADS SOCATA TBM 
Aircraft Mandatory Service Bulletin SB 70-104, Amendment 1, ATA No. 
55, dated August 2004, for related information.

    Issued in Kansas City, Missouri, on November 9, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-19443 Filed 11-16-06; 8:45 am]
BILLING CODE 4910-13-P