Airworthiness Directives; Aerospatiale Model SN-601 (Corvette) Airplanes, 29086-29088 [E7-10046]

Download as PDF 29086 § 39.13 Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28257; Directorate Identifier 2007–NM–034–AD. Comments Due Date (a) The FAA must receive comments on this AD action by July 9, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 100, –200B, –200C, and –200F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747–53A2673, dated February 8, 2007. Unsafe Condition (d) This AD results from a report of a 2inch crack through the fuselage skin and internal bonded doubler at the cutout of the bulk cargo door light. We are issuing this AD to detect and correct cracks in the fuselage skin at the cutout of the bulk cargo door light, which could result in reduced structural integrity of the fuselage at the bulk cargo door and consequent rapid decompression of the fuselage. rmajette on PROD1PC67 with PROPOSALS Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections/Corrective Actions (f) Before the accumulation of 20,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later: Perform a high frequency eddy current (HFEC) inspection for cracks in the fuselage skin at the cutout of the bulk cargo door light, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2673, dated February 8, 2007. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. (1) If no crack is found: Repeat the inspection required by paragraph (f) of this AD at the time specified. (2) If any crack is found that is 2.0 inches or less in length from the edge of the light cutout forward lower corner: Before further flight, do all the corrective actions (including an additional HFEC inspection for cracks) in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Accomplishing Part 2 ends the repetitive inspections required by paragraph (f) of this AD. (3) If any crack is found during the inspection required by paragraph (f) of this AD that is more than 2.0 inches in total length from the edge of the light cutout forward lower corner, or is at a location other than the light cutout forward lower corner: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (g)(2) of this AD. VerDate Aug<31>2005 15:42 May 23, 2007 Jkt 211001 Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. (3) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on May 15, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10045 Filed 5–23–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28259; Directorate Identifier 2007–NM–024–AD] RIN 2120–AA64 Airworthiness Directives; Aerospatiale Model SN–601 (Corvette) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. 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: SUMMARY: Cracks have been evidenced on the nose landing gear LH (left-hand) and RH (righthand) hinge fittings due to stress corrosion on in-service aircraft. If undetected, they could lead to complete rupture of one or two of the fittings. The unsafe condition is collapse of the nose landing gear. The proposed AD PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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 June 25, 2007. 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: Mike Borfitz, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2677; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This 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 E:\FR\FM\24MYP1.SGM 24MYP1 Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules 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–2007–28259; Directorate Identifier 2007–NM–024–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 based on 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 Generale de l’Aviation Civile (DGAC), which is the aviation authority for France, has issued French Airworthiness Directive F–2004–169, dated October 27, 2004 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Cracks have been evidenced on the nose landing gear LH (left-hand) and RH (righthand) hinge fittings due to stress corrosion on in-service aircraft. If undetected, they could lead to complete rupture of one or two of the fittings. The unsafe condition is collapse of the nose landing gear. The MCAI requires repetitive inspections of the nose landing gear LH and RH hinge fittings for cracking, and replacing the hinge fitting with a new fitting if any cracking is found. You may obtain further information by examining the MCAI in the AD docket. rmajette on PROD1PC67 with PROPOSALS Relevant Service Information Airbus has issued SN–601 Corvette Service Bulletin 32–17, dated September 23, 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 This 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 the State of VerDate Aug<31>2005 15:42 May 23, 2007 Jkt 211001 Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This 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 highlighted in a Note within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 3 products of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,680, or $560 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 29087 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Aerospatiale: Docket No. FAA–2007–28259; Directorate Identifier 2007–NM–024–AD. Comments Due Date (a) We must receive comments by June 25, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Aerospatiale Model SN–601 (Corvette) airplanes, all serial numbers; certificated in any category. Subject (d) Landing gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Cracks have been evidenced on the nose landing gear LH (left-hand) and RH (right- E:\FR\FM\24MYP1.SGM 24MYP1 29088 Federal Register / Vol. 72, No. 100 / Thursday, May 24, 2007 / Proposed Rules hand) hinge fittings due to stress corrosion on in-service aircraft. If undetected, they could lead to complete rupture of one or two of the fittings. The unsafe condition is collapse of the nose landing gear. The MCAI requires repetitive inspections of the nose landing gear LH and RH hinge fittings for cracking, and replacing the hinge fitting with a new fitting if any cracking is found. has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first: Inspect the nose landing gear LH (left-hand) and RH (right-hand) hinge fittings for cracking, in accordance with the instructions of Airbus SN–601 Corvette Service Bulletin 32–17, dated September 23, 2004. (2) In case of finding one or several cracks, before further flight, replace the hinge fitting with a new hinge fitting in accordance with the instructions of Airbus SN–601 Corvette Service Bulletin 32–17, dated September 23, 2004. Repeat the requirements of paragraph (f)(1) of this AD thereafter at intervals not to exceed 3,600 flight hours or 36 months, whichever occurs first. (3) If no crack is detected, repeat the requirements of paragraph (f)(1) of this AD thereafter at intervals not to exceed 3,600 flight hours or 36 months, whichever occurs first. Issued in Renton, Washington, on May 15, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–10046 Filed 5–23–07; 8:45 am] FAA AD Differences rmajette on PROD1PC67 with PROPOSALS Note: This AD differs from the MCAI and/ or service information as follows: Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (f)(2) of this AD requires that you repair the cracks before further flight. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Mike Borfitz, Aerospace Engineer, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2677; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) VerDate Aug<31>2005 15:42 May 23, 2007 Jkt 211001 Related Information (h) Refer to MCAI French Airworthiness Directive F–2004–169, dated October 27, 2004; and Airbus SN–601 Corvette Service Bulletin 32–17, dated September 23, 2004; for related information. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28255; Directorate Identifier 2007–NM–023–AD] RIN 2120–AA64 Airworthiness Directives; Lockheed Model 1329 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Lockheed Model 1329 series airplanes. This proposed AD would require determining the part number on the steering cylinder assembly for the nose landing gear (NLG), determining the total flight cycles accumulated on the NLG steering cylinder assembly, repetitive replacement of the assembly, inspecting for missing tow turning limit markings, and performing corrective actions if necessary. This proposed AD results from reports of numerous failures of the NLG steering cylinder. We are proposing this AD to prevent the loss of hydraulic pressure and steering control. DATES: We must receive comments on this proposed AD by June 25, 2007. ADDRESSES: Use one of the following addresses to submit comments 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • 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. Contact Lockheed Martin Aircraft & Logistics Center, 120 Orion Street, Greenville, South Carolina 29605, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Hector Hernandez, Aerospace Engineer, Systems and Equipment Branch, ACE– 119A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone (770) 703–6069; fax (770) 703–6097. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28255; Directorate Identifier 2007–NM–023–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza E:\FR\FM\24MYP1.SGM 24MYP1

Agencies

[Federal Register Volume 72, Number 100 (Thursday, May 24, 2007)]
[Proposed Rules]
[Pages 29086-29088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10046]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28259; Directorate Identifier 2007-NM-024-AD]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model SN-601 (Corvette) 
Airplanes

AGENCY: Federal Aviation Administration (FAA), 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) 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:

    Cracks have been evidenced on the nose landing gear LH (left-
hand) and RH (right-hand) hinge fittings due to stress corrosion on 
in-service aircraft. If undetected, they could lead to complete 
rupture of one or two of the fittings.

The unsafe condition is collapse of the nose landing gear. 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 June 25, 2007.

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: Mike Borfitz, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2677; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Streamlined Issuance of AD

    The FAA is implementing a new process for streamlining the issuance 
of ADs related to MCAI. This 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

[[Page 29087]]

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-2007-
28259; Directorate Identifier 2007-NM-024-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 based on 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 G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the aviation authority for France, has issued French 
Airworthiness Directive F-2004-169, dated October 27, 2004 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Cracks have been evidenced on the nose landing gear LH (left-
hand) and RH (right-hand) hinge fittings due to stress corrosion on 
in-service aircraft. If undetected, they could lead to complete 
rupture of one or two of the fittings.

The unsafe condition is collapse of the nose landing gear. The MCAI 
requires repetitive inspections of the nose landing gear LH and RH 
hinge fittings for cracking, and replacing the hinge fitting with a new 
fitting if any cracking is found. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued SN-601 Corvette Service Bulletin 32-17, dated 
September 23, 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 This 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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This 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 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 3 products of U.S. registry. We also estimate that 
it would take about 7 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $1,680, or $560 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this 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:

Aerospatiale: Docket No. FAA-2007-28259; Directorate Identifier 
2007-NM-024-AD.

Comments Due Date

    (a) We must receive comments by June 25, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Aerospatiale Model SN-601 (Corvette) 
airplanes, all serial numbers; certificated in any category.

Subject

    (d) Landing gear.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Cracks have been evidenced on the nose landing gear LH (left-
hand) and RH (right-

[[Page 29088]]

hand) hinge fittings due to stress corrosion on in-service aircraft. 
If undetected, they could lead to complete rupture of one or two of 
the fittings.

The unsafe condition is collapse of the nose landing gear. The MCAI 
requires repetitive inspections of the nose landing gear LH and RH 
hinge fittings for cracking, and replacing the hinge fitting with a 
new fitting if any cracking is found.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 200 flight hours or 6 months after the effective date 
of this AD, whichever occurs first: Inspect the nose landing gear LH 
(left-hand) and RH (right-hand) hinge fittings for cracking, in 
accordance with the instructions of Airbus SN-601 Corvette Service 
Bulletin 32-17, dated September 23, 2004.
    (2) In case of finding one or several cracks, before further 
flight, replace the hinge fitting with a new hinge fitting in 
accordance with the instructions of Airbus SN-601 Corvette Service 
Bulletin 32-17, dated September 23, 2004. Repeat the requirements of 
paragraph (f)(1) of this AD thereafter at intervals not to exceed 
3,600 flight hours or 36 months, whichever occurs first.
    (3) If no crack is detected, repeat the requirements of 
paragraph (f)(1) of this AD thereafter at intervals not to exceed 
3,600 flight hours or 36 months, whichever occurs first.

FAA AD Differences

    Note: This AD differs from the MCAI and/ or service information 
as follows: Although the MCAI or service information allows further 
flight after cracks are found during compliance with the required 
action, paragraph (f)(2) of this AD requires that you repair the 
cracks before further flight.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Mike Borfitz, Aerospace Engineer, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2677; fax (425) 227-1149. Before using any approved AMOC 
on any airplane to which the AMOC applies, notify your 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI French Airworthiness Directive F-2004-169, 
dated October 27, 2004; and Airbus SN-601 Corvette Service Bulletin 
32-17, dated September 23, 2004; for related information.

    Issued in Renton, Washington, on May 15, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-10046 Filed 5-23-07; 8:45 am]
BILLING CODE 4910-13-P