Airworthiness Directives; Bombardier Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes, 63587-63590 [E9-28554]

Download as PDF Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A320– 111, –211, –212, –214, –231, –232, and –233 series airplanes, certificated in any category, all certified models, all serial numbers, equipped with Hamilton Sundstrand (formerly Dowty) Ram Air Turbine (RAT) Ejection Jack, Model ERPS13EJ, part number (P/N) 114160004A or 114160005, except those airplanes on which Airbus modification 27189 was done in production or Airbus Service Bulletin A320–29–1100 was done in service, and on which Airbus modification 28413 was not done in production. Subject (d) Air Transport Association (ATA) of America Code 29: Hydraulic Power. jlentini on DSKJ8SOYB1PROD with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: An A320 operator experienced difficulties in extending the RAT during a deployment testing. During the trouble shooting, the Ejection Jack of the RAT was removed and investigated. The investigation identified excessive wear of the uplock segments against the inner cylinder of the Ejection Jack, due to an incorrect blend radius of the inner cylinder. This problem was determined to be caused during the previous rework of the Ejection Jack and was possibly due to the incomplete requirements contained within the Component Maintenance Manual (CMM). This Ejection Jack failure may prevent the effective deployment and use of the RAT in emergency conditions. This AD therefore mandates the replacement of an Ejection Jack that has been previously reworked in accordance with the incomplete CMM requirements. This will restore the reliability of the Ejection Jack of the RAT. The implementation of this modification was originally managed by an Airbus monitoring campaign. However, the rate of installation of the corrective action by operators has not met the predicated [sic] target. As such and to ensure continued compliance with the certification requirements, it is considered necessary to require compliance by means of an AD. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 12 months after the effective date of this AD, identify the serial number of the installed ejection jack of the RAT, in accordance with Accomplishment Instructions of Airbus Service Bulletin A320– 29–1136, dated February 20, 2007. If the serial number is included in the affected batch identified in the service bulletin, before further flight, replace the ejection jack of the VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 RAT with a modified or reworked ejection jack, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–29–1136, dated February 20, 2007. (2) As of the effective date of this AD, no person may install a RAT Ejection Jack Model ERPS13EJ, P/N 114160004A or 114160005, on any airplane unless the ejection jack has been modified or reworked in accordance with Airbus Service Bulletin A320–29–1136, dated February 20, 2007. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: While the European Aviation Safety Agency AD 2008–0199, dated November 5, 2008, applies to Airbus Model A318, A319, and A321 series airplanes, this AD does not list these models for reasons explained in the Comments section of this AD. 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: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. (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 Airworthiness Directive 2008– 0199, dated November 5, 2008; and Airbus Service Bulletin A320–29–1136, dated February 20, 2007; for related information. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A320–29–1136, excluding Appendix 01, dated February 20, 2007, 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 PO 00000 Frm 00057 Fmt 4700 Sfmt 4700 63587 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// www.airbus.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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 19, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28556 Filed 12–3–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0565; Directorate Identifier 2008–NM–217–AD; Amendment 39–16112; AD 2009–24–18] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2A12 (CL–601) and CL– 600–2B16 (CL–601–3A, CL–601–3R, and CL–604) 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: * * * [I]ncidents of throttle jam and engine shutdowns, caused by premature wear of the rack and pinion mechanism of part number (P/N) 2100140–005 and –007 Engine Throttle Control Gearbox (ETCG), installed on Bombardier CL–601 and 604 aircraft. * E:\FR\FM\04DER1.SGM * * 04DER1 * * 63588 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 8, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 8, 2010. ADDRESSES: You may examine the AD docket on the Internet at http:// 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: Rocco Viselli, Aerospace Engineer, Airframe and Mechanical Systems, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7331; fax (516) 794–5531. 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 June 23, 2009 (74 FR 29632). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: There have been various reported incidents of throttle jam and engine shutdowns, caused by premature wear of the rack and pinion mechanism of part number (P/N) 2100140– 005 and –007 Engine Throttle Control Gearbox (ETCG), installed on Bombardier CL–601 and 604 aircraft. Bombardier issued service bulletins (SB) 601–0583 (CL601/601–3A, –3R) and 604–76– 004 (CL 604), introducing periodic inspection of the affected ETCG rack and pinion mechanisms for wear. Subject inspection requirement tasks have now been incorporated into the applicable CL601 and CL604 Time Limits Maintenance Checks (TLMCs) through Temporary Revisions (TR), TR 5–236 (for CL601), TR 5– 236 (for CL601–3A & –3R) and TR 5–2–40 (for CL604). jlentini on DSKJ8SOYB1PROD with RULES The required action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new repetitive functional tests of the ETCG. 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 on the determination of the cost to the public. VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 New Note We have added Note 1 to this AD to clarify compliance with section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)). Updated Contact Information We have updated paragraph (g)(1) of this AD to provide the appropriate contact information to use when submitting requests for approval of an alternative method of compliance (AMOC). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 377 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 $30,160, 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 PO 00000 Frm 00058 Fmt 4700 Sfmt 4700 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 http:// 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. E:\FR\FM\04DER1.SGM 04DER1 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–24–18 Bombardier, Inc. (Formerly Canadair): Amendment 39–16112. Docket No. FAA–2009–0565; Directorate Identifier 2008–NM–217–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 8, 2010. the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (g)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Subject (d) Air Transport Association (ATA) of America Code 76: Engine controls. Affected ADs (b) None. Applicability (c) This AD applies to all Bombardier Model CL–600–2A12 (CL–601) and CL–600– 2B16 (CL–601–3A, CL–601–3R, and CL–604) airplanes, certificated in any category. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in Reason (e) The mandatory continuing airworthiness information (MCAI) states: There have been various reported incidents of throttle jam and engine shutdowns, caused by premature wear of the rack and pinion mechanism of part number (P/N) 2100140– 005 and –007 Engine Throttle Control Gearbox (ETCG), installed on Bombardier CL–601 and 604 aircraft. Bombardier issued service bulletins (SB) 601–0583 (CL601/601–3A, –3R) and 604–76– 63589 004 (CL 604), introducing periodic inspection of the affected ETCG rack and pinion mechanisms for wear. Subject inspection requirement tasks have now been incorporated into the applicable CL601 and CL604 Time Limits Maintenance Checks (TLMCs) through Temporary Revisions (TR), TR 5–236 (for CL601), TR 5– 236 (for CL601–3A & –3R) and TR 5–2–40 (for CL604). The required action is revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new repetitive functional tests of the ETCG. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 30 days after the effective date of this AD: Revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating the applicable task in the TR listed in Table 1 of this AD. TABLE 1—TEMPORARY REVISIONS TO THE AIRWORTHINESS LIMITATIONS SECTION Use Canadair Challenger Temporary Revision— For Bombardier model— CL–600–2A12 (CL–601) airplanes. CL–600–2B16 (CL–601–3A, and CL–601–3R) airplanes. CL–600–2B16 (CL–604) airplanes. Dated— To the Airworthiness Limitations section of— 5–236 July 25, 2008 .............. 5–236 March 22, 2007 ........... 5–2–40 July 28, 2008 .............. Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601–5. Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601A–5. Section 5–10–40 of Chapter 5 of the Canadair Challenger CL–604 Time Limits/Maintenance Checks. (2) For the new TLMC tasks identified in Canadair Challenger Temporary Revision 5– 236, dated July 25, 2008; Temporary Revision 5–2–40, dated July 28, 2008; and Temporary Revision 5–236, dated March 22, 2007: Initial compliance with the new TLMC tasks must be carried out in accordance with the phasein schedule detailed in the Canadair Challenger TRs 5–236 and TR 5–2–40, as applicable, after the effective date of this AD. Thereafter, except as provided by paragraph (g)(1) of this AD, no alternative TLMC task intervals may be used. (3) When information in a TR specified in paragraph (f)(1) has been included in the general revisions of the applicable Airworthiness Limitations section, the TR may be removed from that Airworthiness Limitations section of the Instruction for Continued Airworthiness. FAA AD Differences jlentini on DSKJ8SOYB1PROD with RULES Note 2: 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, New York Aircraft Certification Office, ANE–170, 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: Program Manager, Continuing Operational Safety, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228– 7300; fax 516–794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your 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 Canadian Airworthiness Directive CF–2008–32R2, dated November 17, 2008, and the service information identified in Table 2 of this AD for related information. TABLE 2—REFERENCED SERVICE INFORMATION Canadair Challenger Temporary Revision— Dated— To the Airworthiness Limitations section of— 5–236 .............................. July 25, 2008 ............... Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601–5. VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 PO 00000 Frm 00059 Fmt 4700 Sfmt 4700 E:\FR\FM\04DER1.SGM 04DER1 63590 Federal Register / Vol. 74, No. 232 / Friday, December 4, 2009 / Rules and Regulations TABLE 2—REFERENCED SERVICE INFORMATION—Continued Canadair Challenger Temporary Revision— Dated— To the Airworthiness Limitations section of— 5–236 .............................. March 22, 2007 ............ 5–2–40 ............................ July 28, 2008 ............... Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601A–5. Section 5–10–40 of Chapter 5 of the Canadair Challenger CL–604 Time Limits/Maintenance Checks. Material Incorporated by Reference (i) You must use the applicable service information contained in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. TABLE 3—MATERIAL INCORPORATED BY REFERENCE Canadair Challenger Temporary Revision— Dated— To the Airworthiness Limitations section of— 5–236 .............................. July 25, 2008 ............... 5–236 .............................. March 22, 2007 ............ 5–2–40 ............................ July 28, 2008 ............... Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601–5. Section 5–10–30 of Chapter 5 of the Canadair Challenger Time Limits/Maintenance Checks, PSP 601A–5. Section 5–10–40 of Chapter 5 of the Canadair Challenger CL–604 Time Limits/Maintenance Checks. (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 ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road, West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com; Internet http:// www.bombardier.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: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 19, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28554 Filed 12–3–09; 8:45 am] jlentini on DSKJ8SOYB1PROD with RULES BILLING CODE 4910–13–P VerDate Nov<24>2008 17:09 Dec 03, 2009 Jkt 220001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0553; Directorate Identifier 2008–NM–199–AD; Amendment 39–16111; AD 2009–24–17] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–200B, 747–200C, 747–200F, and 747SR Series Airplanes SUMMARY: We are issuing a new airworthiness directive (AD) for certain Boeing Model 747–100, 747–100B, 747– 200B, 747–200C, 747–200F, and 747SR series airplanes. This AD requires a onetime general visual inspection for missing fasteners in certain stringer-tostringer clip joints at the station (STA) 760 through STA 940 frames, and related investigative and corrective actions if necessary. This AD results from a report of broken and cracked frame shear ties, cracks on the frame doubler and frame web, and missing fasteners in the stringer (S) –10L stringer-to-stringer clip joint at the STA 820 frame. We are issuing this AD to detect and correct missing fasteners in the stringer-to-stringer clip joints, which could result in shear tie and skin cracks and rapid in-flight decompression of the airplane. Frm 00060 Fmt 4700 Sfmt 4700 ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207; telephone 206–544–9990; fax 206–766– 5682; e-mail DDCS@boeing.com; Internet https:// www.myboeingfleet.com. Examining the AD Docket AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. PO 00000 DATES: This AD is effective January 8, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 8, 2010. You may examine the AD docket on the Internet at http:// www.regulations.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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6449; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: E:\FR\FM\04DER1.SGM 04DER1

Agencies

[Federal Register Volume 74, Number 232 (Friday, December 4, 2009)]
[Rules and Regulations]
[Pages 63587-63590]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28554]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0565; Directorate Identifier 2008-NM-217-AD; 
Amendment 39-16112; AD 2009-24-18]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2A12 (CL-601) 
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) 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:

    * * * [I]ncidents of throttle jam and engine shutdowns, caused 
by premature wear of the rack and pinion mechanism of part number 
(P/N) 2100140-005 and -007 Engine Throttle Control Gearbox (ETCG), 
installed on Bombardier CL-601 and 604 aircraft.
* * * * *


[[Page 63588]]


We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective January 8, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 8, 
2010.

ADDRESSES: You may examine the AD docket on the Internet at http://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: Rocco Viselli, Aerospace Engineer, 
Airframe and Mechanical Systems, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7331; fax (516) 794-5531.

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 June 23, 2009 (74 FR 
29632). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    There have been various reported incidents of throttle jam and 
engine shutdowns, caused by premature wear of the rack and pinion 
mechanism of part number (P/N) 2100140-005 and -007 Engine Throttle 
Control Gearbox (ETCG), installed on Bombardier CL-601 and 604 
aircraft.
    Bombardier issued service bulletins (SB) 601-0583 (CL601/601-3A, 
-3R) and 604-76-004 (CL 604), introducing periodic inspection of the 
affected ETCG rack and pinion mechanisms for wear.
    Subject inspection requirement tasks have now been incorporated 
into the applicable CL601 and CL604 Time Limits Maintenance Checks 
(TLMCs) through Temporary Revisions (TR), TR 5-236 (for CL601), TR 
5-236 (for CL601-3A & -3R) and TR 5-2-40 (for CL604).

The required action is revising the Airworthiness Limitations Section 
of the Instructions for Continued Airworthiness to incorporate new 
repetitive functional tests of the ETCG. 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 on the determination of 
the cost to the public.

New Note

    We have added Note 1 to this AD to clarify compliance with section 
91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)).

Updated Contact Information

    We have updated paragraph (g)(1) of this AD to provide the 
appropriate contact information to use when submitting requests for 
approval of an alternative method of compliance (AMOC).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

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 377 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 $30,160, 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 http://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.

[[Page 63589]]

Sec.  39.13  [Amended]

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

2009-24-18 Bombardier, Inc. (Formerly Canadair): Amendment 39-16112. 
Docket No. FAA-2009-0565; Directorate Identifier 2008-NM-217-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
8, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Bombardier Model CL-600-2A12 (CL-601) 
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes, 
certificated in any category.

    Note 1:  This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (g)(1) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued operational safety of the airplane.

Subject

    (d) Air Transport Association (ATA) of America Code 76: Engine 
controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    There have been various reported incidents of throttle jam and 
engine shutdowns, caused by premature wear of the rack and pinion 
mechanism of part number (P/N) 2100140-005 and -007 Engine Throttle 
Control Gearbox (ETCG), installed on Bombardier CL-601 and 604 
aircraft.
    Bombardier issued service bulletins (SB) 601-0583 (CL601/601-3A, 
-3R) and 604-76-004 (CL 604), introducing periodic inspection of the 
affected ETCG rack and pinion mechanisms for wear.
    Subject inspection requirement tasks have now been incorporated 
into the applicable CL601 and CL604 Time Limits Maintenance Checks 
(TLMCs) through Temporary Revisions (TR), TR 5-236 (for CL601), TR 
5-236 (for CL601-3A & -3R) and TR 5-2-40 (for CL604).

The required action is revising the Airworthiness Limitations 
Section of the Instructions for Continued Airworthiness to 
incorporate new repetitive functional tests of the ETCG.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 30 days after the effective date of this AD: Revise 
the Airworthiness Limitations section of the Instructions for 
Continued Airworthiness by incorporating the applicable task in the 
TR listed in Table 1 of this AD.

                      Table 1--Temporary Revisions to the Airworthiness Limitations Section
----------------------------------------------------------------------------------------------------------------
                                         Use Canadair
                                          Challenger                                    To the Airworthiness
        For Bombardier model--             Temporary             Dated--              Limitations section of--
                                          Revision--
----------------------------------------------------------------------------------------------------------------
CL-600-2A12 (CL-601) airplanes........           5-236  July 25, 2008............  Section 5-10-30 of Chapter 5
                                                                                    of the Canadair Challenger
                                                                                    Time Limits/Maintenance
                                                                                    Checks, PSP 601-5.
CL-600-2B16 (CL-601-3A, and CL-601-3R)           5-236  March 22, 2007...........  Section 5-10-30 of Chapter 5
 airplanes.                                                                         of the Canadair Challenger
                                                                                    Time Limits/Maintenance
                                                                                    Checks, PSP 601A-5.
CL-600-2B16 (CL-604) airplanes........          5-2-40  July 28, 2008............  Section 5-10-40 of Chapter 5
                                                                                    of the Canadair Challenger
                                                                                    CL-604 Time Limits/
                                                                                    Maintenance Checks.
----------------------------------------------------------------------------------------------------------------

     (2) For the new TLMC tasks identified in Canadair Challenger 
Temporary Revision 5-236, dated July 25, 2008; Temporary Revision 5-
2-40, dated July 28, 2008; and Temporary Revision 5-236, dated March 
22, 2007: Initial compliance with the new TLMC tasks must be carried 
out in accordance with the phase-in schedule detailed in the 
Canadair Challenger TRs 5-236 and TR 5-2-40, as applicable, after 
the effective date of this AD. Thereafter, except as provided by 
paragraph (g)(1) of this AD, no alternative TLMC task intervals may 
be used.
    (3) When information in a TR specified in paragraph (f)(1) has 
been included in the general revisions of the applicable 
Airworthiness Limitations section, the TR may be removed from that 
Airworthiness Limitations section of the Instruction for Continued 
Airworthiness.

FAA AD Differences

    Note 2:  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, New 
York Aircraft Certification Office, ANE-170, 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: Program Manager, 
Continuing Operational Safety, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your 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 Canadian Airworthiness Directive CF-2008-32R2, 
dated November 17, 2008, and the service information identified in 
Table 2 of this AD for related information.

                 Table 2--Referenced Service Information
------------------------------------------------------------------------
                                                    To the Airworthiness
 Canadair Challenger Temporary       Dated--        Limitations section
          Revision--                                        of--
------------------------------------------------------------------------
5-236.........................  July 25, 2008....  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601-5.

[[Page 63590]]

 
5-236.........................  March 22, 2007...  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601A-5.
5-2-40........................  July 28, 2008....  Section 5-10-40 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    CL-604 Time Limits/
                                                    Maintenance Checks.
------------------------------------------------------------------------

Material Incorporated by Reference

    (i) You must use the applicable service information contained in 
Table 3 of this AD to do the actions required by this AD, unless the 
AD specifies otherwise.

               Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
                                                    To the Airworthiness
 Canadair Challenger Temporary       Dated--        Limitations section
          Revision--                                        of--
------------------------------------------------------------------------
5-236.........................  July 25, 2008....  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601-5.
5-236.........................  March 22, 2007...  Section 5-10-30 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    Time Limits/
                                                    Maintenance Checks,
                                                    PSP 601A-5.
5-2-40........................  July 28, 2008....  Section 5-10-40 of
                                                    Chapter 5 of the
                                                    Canadair Challenger
                                                    CL-604 Time Limits/
                                                    Maintenance Checks.
------------------------------------------------------------------------

    (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 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road, West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.crj@aero.bombardier.com; Internet http://www.bombardier.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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 19, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-28554 Filed 12-3-09; 8:45 am]
BILLING CODE 4910-13-P