AD 2010-14-02 Airworthiness Directives; Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) Airplanes

This AD applies to Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes; certificated in any category; serial numbers 5408 through 5665 inclusive.

Unless already done, do the following actions. (1) Within 400 flight hours after the effective date of this AD, inspect to determine the part number of the installed ADG and accomplish the actions required by paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the ADG can be conclusively determined from that review. (i) If the part number of the ADG is 604-90800-23 (Hamilton Sundstrand part number 1711405), the strut wall thickness is within specification and no further action is required by this paragraph. (ii) If the part number of the ADG is 604-90800-1, -17 or -19 (Hamilton Sundstrand part number in the 761339 series), inspect to determine the ADG serial number and do the applicable action required by paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C) of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection if the serial number of the ADG can be conclusively determined from that review. (A) If the serial number of the ADG is 2000 or higher, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (B) If the serial number of the ADG is in the range 0101 through 1999 inclusive, and the symbol 24-3 is marked in the serial number block of the identification plate, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (C) If the serial number of the ADG is in the range 0101 through 1999 inclusive, and the symbol 24-3 is not marked in the serial number block of the identification plate, inspect to determine the serial number of the strut and generator housing assembly and do the applicable action required by paragraph (f)(1)(ii)(C)( 1 ) or (f)(1)(ii)(C)( 2 ) of this AD, as applicable. Note 1: Guidance on serial number location can be found in Figure 1, Sheet 1, of Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, Revision 3, dated March 12, 2009. ( 1 ) If the serial number of the strut and generator housing assembly is in the range 0001 through 2503 inclusive, the fluorescent penetrant inspection specified in paragraph (f)(2) of this AD is required. For airplanes on which an unscheduled in-flight or on-ground ADG deployment has occurred after accomplishing the actions required by this paragraph, do the actions required by paragraph (f)(5), (f)(6), or (f)(7) of this AD, as applicable. ( 2 ) If the serial number of the strut and generator housing assembly is 2504 or higher, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (2) For airplanes having a strut and generator housing assembly identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD, except for airplanes with serial numbers 5611 through 5665 on which Bombardier conducted the initial fluorescent penetrant inspection prior to aircraft delivery and on which the ADG has not been replaced since aircraft delivery: Within 400 flight hours after the effective date of this AD, do a fluorescent penetrant inspection of the ADG strut, and replace the ADG, as applicable, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. Accomplishing the requirements in paragraph (f)(4) of this AD is required for airplanes on which each ADG has been inspected in accordance with this paragraph. (3) Accomplishment of the fluorescent penetrant inspection before the effective date of this AD in accordance with the applicable service information identified in Table 1 of this AD is acceptable for compliance with the requirements of paragraph (f)(2) of this AD. Table 1—Acceptable Service Information Document Revision Date Bombardier Alert Service Bulletin A604-24-017 Original May 6, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Original April 14, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 1 April 19, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 2 November 14, 2006. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 3 March 12, 2009. Note 2: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, the fluorescent penetrant inspection is referred to as a “penetrant check.” (4) As of the effective date of this AD, for airplanes on which the inspection required by paragraph (f)(2) of this AD has been done and on which a scheduled ADG operational test is performed: Before further flight after each test, do a fluorescent penetrant inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (5) As of the effective date of this AD, for airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled in-flight ADG deployment occurs: Before further flight after each deployment, do a general visual inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.B., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. [If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph.] The general visual inspection required by this paragraph is not required if the fluorescent penetrant inspection required by paragraph (f)(6) of this AD is performed before further flight. (6) For airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled in-flight ADG deployment occurs: Within 3 days or 10 hours time-in-service, whichever comes first, after each deployment, perform a fluorescent penetrant inspection of the ADG strut, and replace the ADG, as applicable, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (7) For airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled on-ground ADG deployment task is done: Before further flight after each deployment, do a general visual inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.B., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (8) For airplanes identified in paragraphs (f)(1)(ii)(A), (f)(1)(ii)(B), and (f)(1)(ii)(C)( 2 ) of this AD: Within 400 flight hours after the effective date of this AD, re-identify the ADG, in accordance with the Accomplishment Instructions in Bombardier Service Bulletin 604-24-019, dated October 1, 2007. Following re-identification, no further action is required by this paragraph. Note 3: Paragraph (f)(8) of this AD is applicable only if required by paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C)( 2 ) of this AD. The strut wall thickness of the ADGs specified in these paragraphs is not below specification. (9) As of the effective date of this AD, no person may install an ADG having part number 604-90800-1, -17, or -19 (Hamilton Sundstrand part number in the 761339 series) on any airplane if the serial number of the ADG is in the range 0101 through 1999 strut and the serial number of the generator housing assembly is in the range 0001 through 2503. Note 4: The Bombardier CL-604 Illustrated Parts Catalog specifies that, for an ADG with a Hamilton Sundstrand part number in the 761339 series, future procurement is to be an ADG with Hamilton Sundstrand part number 1711405. (10) Although Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Service Bulletin 604-24-019, dated October 1, 2007; specify submitting certain information to the manufacturer, this AD does not require that submission. FAA AD Differences Note 5: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (f)(10) of this AD specifies that such submittal is not required. 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 (ACO), 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, Continued Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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. Related Information (h) Refer to MCAI Canadian Airworthiness Directive CF-2009-24, dated May 19, 2009; Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Bombardier Service Bulletin 604-24-019, dated October 1, 2007; for related information. Material Incorporated by Reference (i) You must use Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Bombardier Service Bulletin 604-24-019, dated October 1, 2007; as applicable; 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 Bombardier, Inc., 400 Côte-Vertu Road West, Dorval, Québec 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. (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 June 17, 2010. Robert D. Breneman, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-15818 Filed 6-30-10; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) Within 400 flight hours after the effective date of this AD, inspect to determine the part number of the installed ADG and accomplish the actions required by paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the ADG can be conclusively determined from that review. (i) If the part number of the ADG is 604-90800-23 (Hamilton Sundstrand part number 1711405), the strut wall thickness is within specification and no further action is required by this paragraph. (ii) If the part number of the ADG is 604-90800-1, -17 or -19 (Hamilton Sundstrand part number in the 761339 series), inspect to determine the ADG serial number and do the applicable action required by paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C) of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection if the serial number of the ADG can be conclusively determined from that review. (A) If the serial number of the ADG is 2000 or higher, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (B) If the serial number of the ADG is in the range 0101 through 1999 inclusive, and the symbol 24-3 is marked in the serial number block of the identification plate, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (C) If the serial number of the ADG is in the range 0101 through 1999 inclusive, and the symbol 24-3 is not marked in the serial number block of the identification plate, inspect to determine the serial number of the strut and generator housing assembly and do the applicable action required by paragraph (f)(1)(ii)(C)( 1 ) or (f)(1)(ii)(C)( 2 ) of this AD, as applicable. Note 1: Guidance on serial number location can be found in Figure 1, Sheet 1, of Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, Revision 3, dated March 12, 2009. ( 1 ) If the serial number of the strut and generator housing assembly is in the range 0001 through 2503 inclusive, the fluorescent penetrant inspection specified in paragraph (f)(2) of this AD is required. For airplanes on which an unscheduled in-flight or on-ground ADG deployment has occurred after accomplishing the actions required by this paragraph, do the actions required by paragraph (f)(5), (f)(6), or (f)(7) of this AD, as applicable. ( 2 ) If the serial number of the strut and generator housing assembly is 2504 or higher, the strut wall thickness is within specification and only re-identification is required. Do the actions required by paragraph (f)(8) of this AD. (2) For airplanes having a strut and generator housing assembly identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD, except for airplanes with serial numbers 5611 through 5665 on which Bombardier conducted the initial fluorescent penetrant inspection prior to aircraft delivery and on which the ADG has not been replaced since aircraft delivery: Within 400 flight hours after the effective date of this AD, do a fluorescent penetrant inspection of the ADG strut, and replace the ADG, as applicable, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. Accomplishing the requirements in paragraph (f)(4) of this AD is required for airplanes on which each ADG has been inspected in accordance with this paragraph. (3) Accomplishment of the fluorescent penetrant inspection before the effective date of this AD in accordance with the applicable service information identified in Table 1 of this AD is acceptable for compliance with the requirements of paragraph (f)(2) of this AD. Table 1—Acceptable Service Information Document Revision Date Bombardier Alert Service Bulletin A604-24-017 Original May 6, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Original April 14, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 1 April 19, 2005. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 2 November 14, 2006. Hamilton Sundstrand Service Bulletin ERPS10AG-24-3 Revision 3 March 12, 2009. Note 2: In Hamilton Sundstrand Service Bulletin ERPS10AG-24-3, the fluorescent penetrant inspection is referred to as a “penetrant check.” (4) As of the effective date of this AD, for airplanes on which the inspection required by paragraph (f)(2) of this AD has been done and on which a scheduled ADG operational test is performed: Before further flight after each test, do a fluorescent penetrant inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (5) As of the effective date of this AD, for airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled in-flight ADG deployment occurs: Before further flight after each deployment, do a general visual inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.B., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. [If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph.] The general visual inspection required by this paragraph is not required if the fluorescent penetrant inspection required by paragraph (f)(6) of this AD is performed before further flight. (6) For airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled in-flight ADG deployment occurs: Within 3 days or 10 hours time-in-service, whichever comes first, after each deployment, perform a fluorescent penetrant inspection of the ADG strut, and replace the ADG, as applicable, in accordance with paragraphs 2.A., 2.C., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (7) For airplanes identified in paragraph (f)(1)(ii)(C)( 1 ) of this AD on which an unscheduled on-ground ADG deployment task is done: Before further flight after each deployment, do a general visual inspection of the ADG strut for cracks, and replace the ADG if any crack is found, in accordance with paragraphs 2.A., 2.B., and 2.D. of the Accomplishment Instructions in Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007. If the ADG is replaced by an ADG with part number 604-90800-23 (Hamilton Sundstrand part number 1711405), no further action is required by this paragraph. (8) For airplanes identified in paragraphs (f)(1)(ii)(A), (f)(1)(ii)(B), and (f)(1)(ii)(C)( 2 ) of this AD: Within 400 flight hours after the effective date of this AD, re-identify the ADG, in accordance with the Accomplishment Instructions in Bombardier Service Bulletin 604-24-019, dated October 1, 2007. Following re-identification, no further action is required by this paragraph. Note 3: Paragraph (f)(8) of this AD is applicable only if required by paragraph (f)(1)(ii)(A), (f)(1)(ii)(B), or (f)(1)(ii)(C)( 2 ) of this AD. The strut wall thickness of the ADGs specified in these paragraphs is not below specification. (9) As of the effective date of this AD, no person may install an ADG having part number 604-90800-1, -17, or -19 (Hamilton Sundstrand part number in the 761339 series) on any airplane if the serial number of the ADG is in the range 0101 through 1999 strut and the serial number of the generator housing assembly is in the range 0001 through 2503. Note 4: The Bombardier CL-604 Illustrated Parts Catalog specifies that, for an ADG with a Hamilton Sundstrand part number in the 761339 series, future procurement is to be an ADG with Hamilton Sundstrand part number 1711405. (10) Although Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Service Bulletin 604-24-019, dated October 1, 2007; specify submitting certain information to the manufacturer, this AD does not require that submission. FAA AD Differences Note 5: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (f)(10) of this AD specifies that such submittal is not required. 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 (ACO), 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, Continued Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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. Related Information (h) Refer to MCAI Canadian Airworthiness Directive CF-2009-24, dated May 19, 2009; Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Bombardier Service Bulletin 604-24-019, dated October 1, 2007; for related information. Material Incorporated by Reference (i) You must use Bombardier Alert Service Bulletin A604-24-017, Revision 01, dated January 15, 2007; and Bombardier Service Bulletin 604-24-019, dated October 1, 2007; as applicable; 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 Bombardier, Inc., 400 Côte-Vertu Road West, Dorval, Québec 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. (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 June 17, 2010. Robert D. Breneman, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-15818 Filed 6-30-10; 8:45 am] BILLING CODE 4910-13-P