Airworthiness Directives; Dassault Model Falcon 2000EX Airplanes, 32417-32419 [E9-15855]

Download as PDF Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations Bulletin 777–27A0059, Revision 1, dated August 18, 2005; are considered acceptable for compliance with the corresponding actions specified in paragraphs (g), (h), and (i) of this AD. Credit for Hard-Time Replacement of HSTA (k) Any HSTA overhauled within the compliance times specified in paragraphs (g), (h), and (i) of this AD or before the effective date of this AD—as part of a ‘‘hard-time’’ replacement program that includes removal of the HSTA from the airplane and overhaul of the stabilizer ballscrew in accordance with original equipment manufacturer component maintenance manual instructions—meets the intent of one detailed inspection, one freeplay inspection, and one lubrication of the HSTA. Therefore, any such HSTA is considered acceptable for compliance with the initial accomplishment of the actions specified in paragraphs (g), (h), and (i) of this AD, and repetitions of those actions may be determined from the performance date of that overhaul. Parts Installation (l) As of the effective date of this AD, no person may install, on any airplane, a horizontal stabilizer trim actuator that is not in a ‘‘known serviceable condition’’ as defined in Note 6, section 3.A., of Boeing Alert Service Bulletin 777–27A0059, Revision 2, dated January 15, 2009; unless a detailed inspection, freeplay measurement, and lubrication of that actuator are performed in accordance with paragraphs (g), (h), and (i) of this AD, as applicable. sroberts on DSKD5P82C1PROD with RULES Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Kelly McGuckin, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6490; fax (425) 917–6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) 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. Material Incorporated by Reference (n) You must use Boeing Service Bulletin 777–27A0059, Revision 2, dated January 15, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1, fax 206–766– VerDate Nov<24>2008 16:30 Jul 07, 2009 Jkt 217001 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_ register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, WA, on June 24, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–15639 Filed 7–7–09; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0380; Directorate Identifier 2008–NM–153–AD; Amendment 39–15959; AD 2009–14–09] RIN 2120–AA64 Airworthiness Directives; Dassault Model Falcon 2000EX Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: An internal review of design data has shown that the web of the left hand side (LH) stringer 13 near frame 8 might have been improperly trimmed on a few aircraft. If not corrected, possible crack initiations could occur in the upper stringer web, and therefore could impair the structural strength of the adjacent door stop. This latent failure could ultimately lead to the loss of redundancy of the door stops, thereby affecting the structural integrity of the fuselage. * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 12, 2009. Frm 00029 Fmt 4700 The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 12, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion DEPARTMENT OF TRANSPORTATION PO 00000 32417 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 27, 2009 (74 FR 19027). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: An internal review of design data has shown that the web of the left hand side (LH) stringer 13 near frame 8 might have been improperly trimmed on a few aircraft. If not corrected, possible crack initiations could occur in the upper stringer web, and therefore could impair the structural strength of the adjacent door stop. This latent failure could ultimately lead to the loss of redundancy of the door stops, thereby affecting the structural integrity of the fuselage. Computational analysis has revealed a substantial reduced fatigue life for the stringer abutting onto the improperly trimmed web and has determined the need for an inspection and repair action no later than the first ‘‘C’’ check. To address this unsafe condition, the present Airworthiness Directive (AD) mandates an inspection and a conditional rework or replacement of the web of the LH stringer 13 between frames 7 and 8. Required actions include measuring the trimmed length of the web, inspecting for any sharp and unprotected edges of the web, and doing corrective actions if necessary. Corrective actions include reworking the web and applying protection to the web, or replacing the web, if improperly trimmed. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or E:\FR\FM\08JYR1.SGM 08JYR1 32418 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 12 products of U.S. registry. We also estimate that it will take about 1 workhour per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $960, or $80 per product. sroberts on DSKD5P82C1PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on VerDate Nov<24>2008 16:30 Jul 07, 2009 Jkt 217001 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 AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 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 AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–14–09 Dassault Aviation: Amendment 39–15959. Docket No. FAA–2009–0380; Directorate Identifier 2008–NM–153–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 12, 2009. Affected ADs (b) None. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Applicability (c) This AD applies to Dassault Model Falcon 2000EX airplanes, certificated in any category, serial numbers 102 through 124 inclusive. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: An internal review of design data has shown that the web of the left hand side (LH) stringer 13 near frame 8 might have been improperly trimmed on a few aircraft. If not corrected, possible crack initiations could occur in the upper stringer web, and therefore could impair the structural strength of the adjacent door stop. This latent failure could ultimately lead to the loss of redundancy of the door stops, thereby affecting the structural integrity of the fuselage. Computational analysis has revealed a substantial reduced fatigue life for the stringer abutting onto the improperly trimmed web and has determined the need for an inspection and repair action no later than the first ‘‘C’’ check. To address this unsafe condition, the present Airworthiness Directive (AD) mandates an inspection and a conditional rework or replacement of the web of the LH stringer 13 between frames 7 and 8. Required actions include measuring the trimmed length of the web, inspecting for any sharp and unprotected edges of the web, and doing corrective actions if necessary. Corrective actions include reworking the web and applying protection to the web, or replacing the web, if improperly trimmed. Actions and Compliance (f) Unless already done, do the following actions. (1) At the later of the times in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD: Perform a detailed visual inspection to detect any sharp and unprotected edges of the web of the LH stringer 13 between frames 7 and 8, and measure the trimmed length of the web, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin F2000EX–178, dated July 1, 2008. (i) Before the accumulation of 3,750 total flight cycles, or within 74 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French export certificate of airworthiness, whichever occurs first. (ii) Within 6 months after the effective date of this AD. (2) If, during the inspection and measurement required by paragraph (f)(1) of this AD, any sharp or unprotected edge is found, or if the trimmed length is 1.57 inches (40 mm) or greater, before further flight, do all applicable corrective actions, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin F2000EX–178, dated July 1, 2008. E:\FR\FM\08JYR1.SGM 08JYR1 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. 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, Transport Airplane Directorate, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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 FAAapproved 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. sroberts on DSKD5P82C1PROD with RULES Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2008–0143, dated July 31, 2008; and Dassault Mandatory Service Bulletin F2000EX–178, dated July 1, 2008; for related information. Material Incorporated by Reference (i) You must use Dassault Mandatory Service Bulletin F2000EX–178, dated July 1, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet https:// www.dassaultfalcon.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and VerDate Nov<24>2008 16:30 Jul 07, 2009 Jkt 217001 Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, WA, on June 25, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–15855 Filed 7–7–09; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0263; Directorate Identifier 2008–NM–137–AD; Amendment 39–15957; AD 2009–14–07] RIN 2120–AA64 Airworthiness Directives; Dassault Model Mystere-Falcon 20–C5, 20–D5, 20–E5, and 20–F5 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: This Airworthiness Directive (AD) is issued following the discovery of hot air leaks when operating the wing anti-icing system. The seals Part Number (P/N) MS29513–325, near the de-icing valves (12H1) and (12H2) in frame 33 area, do not have the proper temperature rating. The consequences, in the area of the hot air leak, are risks of ignition of potential hydraulic leaks. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 12, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 12, 2009. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, Frm 00031 Fmt 4700 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion BILLING CODE 4910–13–P PO 00000 32419 Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 26, 2009 (74 FR 13147). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: This Airworthiness Directive (AD) is issued following the discovery of hot air leaks when operating the wing anti-icing system. The seals Part Number (P/N) MS29513–325, near the de-icing valves (12H1) and (12H2) in frame 33 area, do not have the proper temperature rating. The consequences, in the area of the hot air leak, are risks of ignition of potential hydraulic leaks. The purpose of this AD is to verify that seals with correct temperature rating have been installed on Mystere-Falcon 20-()5 airplanes. The corrective action includes replacing the left and right seals near de-icing valves (12H1) and (12H2) in frame area 33. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Refer to Current Revision of the Service Bulletin Dassault Falcon Jet Corporation (Dassault) requests that we revise the NPRM to refer to Revision 1 of Dassault Mandatory Service Bulletin F20–766, dated June 24, 2008, in this AD. We referred to Dassault Service Bulletin F20–766, dated October 31, 2005, in the NPRM as the appropriate source of service information for doing the proposed requirements. We agree. Dassault Mandatory Service Bulletin F20–766, Revision 1, dated June 24, 2008, does not specify any additional action for airplanes on which the required actions have been accomplished in accordance with the original issue of Dassault Service Bulletin F20–766, dated October 31, 2005. Also, paragraph 1.D. of Dassault Mandatory Service Bulletin F20–766, E:\FR\FM\08JYR1.SGM 08JYR1

Agencies

[Federal Register Volume 74, Number 129 (Wednesday, July 8, 2009)]
[Rules and Regulations]
[Pages 32417-32419]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-15855]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0380; Directorate Identifier 2008-NM-153-AD; 
Amendment 39-15959; AD 2009-14-09]
RIN 2120-AA64


Airworthiness Directives; Dassault Model Falcon 2000EX Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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:

    An internal review of design data has shown that the web of the 
left hand side (LH) stringer 13 near frame 8 might have been 
improperly trimmed on a few aircraft.
    If not corrected, possible crack initiations could occur in the 
upper stringer web, and therefore could impair the structural 
strength of the adjacent door stop. This latent failure could 
ultimately lead to the loss of redundancy of the door stops, thereby 
affecting the structural integrity of the fuselage.
* * * * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective August 12, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 12, 
2009.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 27, 2009 (74 
FR 19027). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    An internal review of design data has shown that the web of the 
left hand side (LH) stringer 13 near frame 8 might have been 
improperly trimmed on a few aircraft.
    If not corrected, possible crack initiations could occur in the 
upper stringer web, and therefore could impair the structural 
strength of the adjacent door stop. This latent failure could 
ultimately lead to the loss of redundancy of the door stops, thereby 
affecting the structural integrity of the fuselage.
    Computational analysis has revealed a substantial reduced 
fatigue life for the stringer abutting onto the improperly trimmed 
web and has determined the need for an inspection and repair action 
no later than the first ``C'' check.
    To address this unsafe condition, the present Airworthiness 
Directive (AD) mandates an inspection and a conditional rework or 
replacement of the web of the LH stringer 13 between frames 7 and 8.

Required actions include measuring the trimmed length of the web, 
inspecting for any sharp and unprotected edges of the web, and doing 
corrective actions if necessary. Corrective actions include reworking 
the web and applying protection to the web, or replacing the web, if 
improperly trimmed. You may obtain further information by examining the 
MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or

[[Page 32418]]

on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 12 products of U.S. registry. 
We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $960, or $80 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); 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 AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-14-09 Dassault Aviation: Amendment 39-15959. Docket No. FAA-
2009-0380; Directorate Identifier 2008-NM-153-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
12, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Dassault Model Falcon 2000EX airplanes, 
certificated in any category, serial numbers 102 through 124 
inclusive.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

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

    An internal review of design data has shown that the web of the 
left hand side (LH) stringer 13 near frame 8 might have been 
improperly trimmed on a few aircraft.
    If not corrected, possible crack initiations could occur in the 
upper stringer web, and therefore could impair the structural 
strength of the adjacent door stop. This latent failure could 
ultimately lead to the loss of redundancy of the door stops, thereby 
affecting the structural integrity of the fuselage.
    Computational analysis has revealed a substantial reduced 
fatigue life for the stringer abutting onto the improperly trimmed 
web and has determined the need for an inspection and repair action 
no later than the first ``C'' check.
    To address this unsafe condition, the present Airworthiness 
Directive (AD) mandates an inspection and a conditional rework or 
replacement of the web of the LH stringer 13 between frames 7 and 8.

    Required actions include measuring the trimmed length of the 
web, inspecting for any sharp and unprotected edges of the web, and 
doing corrective actions if necessary. Corrective actions include 
reworking the web and applying protection to the web, or replacing 
the web, if improperly trimmed.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) At the later of the times in paragraphs (f)(1)(i) and 
(f)(1)(ii) of this AD: Perform a detailed visual inspection to 
detect any sharp and unprotected edges of the web of the LH stringer 
13 between frames 7 and 8, and measure the trimmed length of the 
web, in accordance with the Accomplishment Instructions of Dassault 
Mandatory Service Bulletin F2000EX-178, dated July 1, 2008.
    (i) Before the accumulation of 3,750 total flight cycles, or 
within 74 months since the date of issuance of the original French 
airworthiness certificate or the date of issuance of the original 
French export certificate of airworthiness, whichever occurs first.
    (ii) Within 6 months after the effective date of this AD.
    (2) If, during the inspection and measurement required by 
paragraph (f)(1) of this AD, any sharp or unprotected edge is found, 
or if the trimmed length is 1.57 inches (40 mm) or greater, before 
further flight, do all applicable corrective actions, in accordance 
with the Accomplishment Instructions of Dassault Mandatory Service 
Bulletin F2000EX-178, dated July 1, 2008.

[[Page 32419]]

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

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, Transport Airplane Directorate, 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: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal maintenance inspector 
(PMI) or principal avionics inspector (PAI), as appropriate, or 
lacking a principal inspector, your local Flight Standards District 
Office. The AMOC approval letter must specifically reference this 
AD.
    (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 European Aviation Safety Agency (EASA) 
Airworthiness Directive 2008-0143, dated July 31, 2008; and Dassault 
Mandatory Service Bulletin F2000EX-178, dated July 1, 2008; for 
related information.

Material Incorporated by Reference

    (i) You must use Dassault Mandatory Service Bulletin F2000EX-
178, dated July 1, 2008, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 
07606; telephone 201-440-6700; Internet https://www.dassaultfalcon.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, WA, on June 25, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-15855 Filed 7-7-09; 8:45 am]
BILLING CODE 4910-13-P
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