Airworthiness Directives; Dassault Model Falcon 2000 Airplanes Equipped With CFE Company CFE738-1-1B Turbofan Engines, 73577-73579 [05-23829]

Download as PDF 73577 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations Effective Date (a) This AD becomes effective January 17, 2006. the Federal Aviation Administration amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Affected ADs (b) This AD supersedes AD 2004–15–02, Amendment 39–13736. 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–13736 (69 FR 44925, August 12, 2004) and by adding a new airworthiness directive, Amendment 39–14404, to read as follows: I 2005–25–11 Rolls-Royce plc: Amendment 39–14404. Docket No. 2003–NE–38–AD. Applicability (c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 884B–17, Trent 892–17, Trent 892B–17, and Trent 895–17 turbofan engines, with low pressure (LP) compressor fan blades, part number FW18548 installed. These engines are installed on, but not limited to, Boeing 777 series airplanes. Unsafe Condition (d) This AD results from a number of new production LP compressor blades found with surfaces formed outside of design intent. We are issuing this AD to prevent possible multiple uncontained LP compressor fan blade failure, due to cracking in the blade root caused by increased stresses in the shear key slots. 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. Actions Required for LP Compressor Fan Blades (f) Replace LP compressor fan blades with new or previously reworked LP compressor blades before accumulating the specified cycles-since-new (CSN) in the following Table 1, or rework the existing blades as specified in paragraph (g) of this AD. TABLE 1.—LP COMPRESSOR FAN BLADE REPLACEMENT OR REWORK SCHEDULE Airplane maximum gross weight (times 1,000 pounds) Boeing 777 Series: ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... ....................................................................................................................... (g) Rework LP compressor fan blades at or before accumulating the specified CSN in Table 1 of this AD. Follow paragraphs 3.B.(1) through 3.B.(22) of Accomplishment Instructions of RR service bulletin (SB) No. RB.211–72–E044, Revision 2, dated October 8, 2004, to do the blade rework. (h) For engines moved between configurations, calculate the cycles remaining using either of the following: (1) Subtract the total CSN from the most limiting configuration’s limit from Table 1 of this AD; or (2) Calculate the cycles remaining using the following equation:  X X  X X r = Lc 1 −  1 + 2 + 3 + .....        L1 L 2 L3 Where: Xr = Cycles remaining in current configuration. Lc = Cyclic limit of current configuration from Table 1 of this AD. Xn = Cycles accumulated in configuration n. Ln = Cyclic limit in configuration n from Table 1 of this AD. (i) Information on the source life of the cycle limits in Table 1 of this AD can be found in RR Alert SB No. RB.211–72–AE055, Revision 3, dated May 28, 2004. VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 660, 632.5 656 648 632.5 632.5 555 545 535 506 –884, –892, –884B –892, –895 –892, –892B –892B –892 –884 –877 –875 –875 Replace or rework LP compressor fan blades before accumulating: 2,400 2,400 3,200 3,200 4,100 4,100 4,100 4,100 4,100 CSN. CSN. CSN. CSN. CSN. CSN. CSN. CSN. CSN. Alternative Methods of Compliance (j) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Issued in Burlington, Massachusetts, on December 5, 2005. Carlos Pestana, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–23834 Filed 12–12–05; 8:45 am] Material Incorporated by Reference (k) You must use Rolls-Royce plc Service Bulletin No. RB.211–72–E044, Revision 2, dated October 8, 2004, to perform the blade rework required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332–242424; fax: 011–44–1332–245418. You can review a copy at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. BILLING CODE 4910–13–P Related Information (l) CAA airworthiness directive G–2004– 030, dated December 23, 2004, and RR Alert SB No. RB.211–72–AE055, Revision 4, dated December 9, 2004, pertain to the subject of this AD. PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22560; Directorate Identifier 2005–NM–061–AD; Amendment 39–14408; AD 2005–25–15] RIN 2120–AA64 Airworthiness Directives; Dassault Model Falcon 2000 Airplanes Equipped With CFE Company CFE738–1–1B Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain E:\FR\FM\13DER1.SGM 13DER1 ER13DE05.008</GPH> –300 –200 –200 –200 –200 –200 –200 –200 –200 RB211 Trent Engine Model 73578 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738– 1–1B turbofan engines. This AD requires determining the serial number of the engines installed on the airplane, inspecting any affected engine to verify that a spherical bearing is installed on the attachment fitting of the engine mount, and corrective action if necessary. This AD results from a report of a missing spherical bearing on the attachment fitting of the front engine mount on an in-service airplane, and subsequent damage and abnormal fatigue of the attachment fitting. We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane. DATES: This AD becomes effective January 17, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 17, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (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 level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply certain Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738–1–1B turbofan engines. That NPRM was published in the Federal Register on September 30, VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 2005 (70 FR 57217). That NPRM proposed to require determining the serial number of the engines installed on the airplane, inspecting any affected engine to verify that a spherical bearing is installed on the attachment fitting of the engine mount, and corrective action if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have changed this AD to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Costs of Compliance This inspection affects about 7 airplanes of U.S. registry. The inspection will take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $910, or $130 per airplane. 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 have determined that this AD will not have federalism implications under Executive Order 13132. This AD will PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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. See the ADDRESSES section for a location to examine the regulatory evaluation. 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–25–15 Dassault Aviation: Amendment 39–14408. Docket No. FAA–2005–22560; Directorate Identifier 2005–NM–061–AD Effective Date (a) This AD becomes effective January 17, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Dassault Model Falcon 2000 airplanes, certificated in any category; equipped with CFE Company CFE738–1–1B turbofan engines. Unsafe Condition (d) This AD results from a report of a missing spherical bearing on the attachment fitting of the front engine mount on an inservice airplane, and subsequent damage and abnormal fatigue of the attachment fitting. E:\FR\FM\13DER1.SGM 13DER1 Federal Register / Vol. 70, No. 238 / Tuesday, December 13, 2005 / Rules and Regulations We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane. 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. Determine Serial Number (S/N) and Inspect if Necessary (f) Within the applicable compliance time specified in paragraph (f)(1), (f)(2), or (f)(3) of this AD: Determine the serial number of the engines installed on the airplane, as identified in the table in paragraph 1.A., ‘‘Effectivity,’’ of Dassault Service Bulletin F2000–299, dated July 23, 2004; if any affected serial number is found on any engine, perform a borescope inspection to verify that a spherical bearing is installed on the attachment fitting of the front engine mount by doing all the applicable actions specified in the Accomplishment Instructions of the service bulletin. (1) For airplanes with any engine having 850 total landings or less as of the effective date of this AD: Before the accumulation of 880 total landings on the engine. (2) For airplanes with any engine having more than 850 total landings, but 1,000 total landings or less as of the effective date of this AD: Within 1 month after the effective date of this AD. (3) For airplanes with any engine having more than 1,000 total landings as of the effective date of this AD: Within 10 landings after the effective date of this AD. Corrective Action (g) If any spherical bearing is found missing during the inspection required by paragraph (f) of this AD: Before further flight, repair according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, ´ ´ FAA; or the Direction Generale de l’Aviation Civile (or its delegated agent). No Reporting Requirement (h) This AD does not require submitting reporting information to the manufacturer. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F–2004– 128, issued August 4, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Dassault Service Bulletin F2000–299, dated July 23, 2004, to perform VerDate Aug<31>2005 16:47 Dec 12, 2005 Jkt 208001 the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 2, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–23829 Filed 12–12–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22928; Directorate Identifier 2005–NE–43–AD; Amendment 39– 14406; AD 2005–25–13] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. This AD requires initial and repetitive visual checks of the free turbine shield for cracks. This AD results from reports of several free turbine shields found with large circumferential cracks. We are issuing this AD to prevent failure of the free turbine shield, leading to engine misalignment, in-flight engine shutdown, emergency autorotation landing, or accident. DATES: Effective December 28, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 28, 2005. We must receive any comments on this AD by February 13, 2006. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 73579 Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7175; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition might exist on Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. The DGAC advises that on several of these engines, large circumferential cracks were found in the free turbine shield at the blending radius between the containment shield and the rear flange. These cracks could cause a loss of engine alignment during maneuvering loads and lead to in-flight engine shutdown. ADDRESSES: Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Alert Mandatory Service Bulletin No. A292 72 2821, dated June 27, 2005, that describes procedures for visual checks of the free turbine shield for cracks. The DGAC classified this service bulletin as mandatory and issued AD F–2005–162, dated September 28, 2005, in order to ensure the airworthiness of these Arriel 2B and 2B1 engines in France. Bilateral Airworthiness Agreement These Turbomeca Arriel 2B and 2B1 turboshaft engines are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the E:\FR\FM\13DER1.SGM 13DER1

Agencies

[Federal Register Volume 70, Number 238 (Tuesday, December 13, 2005)]
[Rules and Regulations]
[Pages 73577-73579]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23829]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22560; Directorate Identifier 2005-NM-061-AD; 
Amendment 39-14408; AD 2005-25-15]
RIN 2120-AA64


Airworthiness Directives; Dassault Model Falcon 2000 Airplanes 
Equipped With CFE Company CFE738-1-1B Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain

[[Page 73578]]

Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738-
1-1B turbofan engines. This AD requires determining the serial number 
of the engines installed on the airplane, inspecting any affected 
engine to verify that a spherical bearing is installed on the 
attachment fitting of the engine mount, and corrective action if 
necessary. This AD results from a report of a missing spherical bearing 
on the attachment fitting of the front engine mount on an in-service 
airplane, and subsequent damage and abnormal fatigue of the attachment 
fitting. We are issuing this AD to prevent reduced structural integrity 
of the engine mount, which could result in possible separation of an 
engine from the airplane.

DATES: This AD becomes effective January 17, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 17, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New 
Jersey 07606, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply certain Dassault Model 
Falcon 2000 airplanes equipped with CFE Company CFE738-1-1B turbofan 
engines. That NPRM was published in the Federal Register on September 
30, 2005 (70 FR 57217). That NPRM proposed to require determining the 
serial number of the engines installed on the airplane, inspecting any 
affected engine to verify that a spherical bearing is installed on the 
attachment fitting of the engine mount, and corrective action if 
necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

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

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have changed this AD to clarify the appropriate procedure for 
notifying the principal inspector before using any approved AMOC on any 
airplane to which the AMOC applies.

Costs of Compliance

    This inspection affects about 7 airplanes of U.S. registry. The 
inspection will take about 2 work hours per airplane, at an average 
labor rate of $65 per work hour. Based on these figures, the estimated 
cost of the AD for U.S. operators is $910, or $130 per airplane.

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2005-25-15 Dassault Aviation: Amendment 39-14408. Docket No. FAA-
2005-22560; Directorate Identifier 2005-NM-061-AD

Effective Date

    (a) This AD becomes effective January 17, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Dassault Model Falcon 2000 airplanes, 
certificated in any category; equipped with CFE Company CFE738-1-1B 
turbofan engines.

Unsafe Condition

    (d) This AD results from a report of a missing spherical bearing 
on the attachment fitting of the front engine mount on an in-service 
airplane, and subsequent damage and abnormal fatigue of the 
attachment fitting.

[[Page 73579]]

We are issuing this AD to prevent reduced structural integrity of 
the engine mount, which could result in possible separation of an 
engine from the airplane.

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.

Determine Serial Number (S/N) and Inspect if Necessary

    (f) Within the applicable compliance time specified in paragraph 
(f)(1), (f)(2), or (f)(3) of this AD: Determine the serial number of 
the engines installed on the airplane, as identified in the table in 
paragraph 1.A., ``Effectivity,'' of Dassault Service Bulletin F2000-
299, dated July 23, 2004; if any affected serial number is found on 
any engine, perform a borescope inspection to verify that a 
spherical bearing is installed on the attachment fitting of the 
front engine mount by doing all the applicable actions specified in 
the Accomplishment Instructions of the service bulletin.
    (1) For airplanes with any engine having 850 total landings or 
less as of the effective date of this AD: Before the accumulation of 
880 total landings on the engine.
    (2) For airplanes with any engine having more than 850 total 
landings, but 1,000 total landings or less as of the effective date 
of this AD: Within 1 month after the effective date of this AD.
    (3) For airplanes with any engine having more than 1,000 total 
landings as of the effective date of this AD: Within 10 landings 
after the effective date of this AD.

Corrective Action

    (g) If any spherical bearing is found missing during the 
inspection required by paragraph (f) of this AD: Before further 
flight, repair according to a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its 
delegated agent).

No Reporting Requirement

    (h) This AD does not require submitting reporting information to 
the manufacturer.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (j) French airworthiness directive F-2004-128, issued August 4, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use Dassault Service Bulletin F2000-299, dated July 
23, 2004, to perform the actions that are required by this AD, 
unless the AD specifies otherwise. The Director of the Federal 
Register approved the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Dassault 
Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606, for a 
copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street, SW., room PL-401, Nassif Building, Washington, DC; 
on the internet at http://dms.dot.gov; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at the NARA, call (202) 741-6030, or 
go to http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23829 Filed 12-12-05; 8:45 am]
BILLING CODE 4910-13-P