AD 2010-05-12 Airworthiness Directives; Bombardier Model DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201, and DHC-8-202 Series Airplanes

Models named: DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201, DHC-8-202 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Bombardier Model DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201, and DHC-8-202 series airplanes; certificated in any category; serial numbers 003 through 663 inclusive.

Unless already done, do the following actions. (1) For airplanes on which Bombardier Modification 8/0024 has not been done: Within 18 months after the effective date of this AD, perform a functional check of the dielectric properties of the fuel tank skin between Yw171.20 and Yw261.00 of the upper and lower wing for aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (2) For airplanes on which Bombardier Modification 8/0024 has been done: Within 18 months after the effective date of this AD, perform a functional check of the dielectric properties of the fuel tank skin between Yw171.20 and Yw261.00 of the upper wing for aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (3) If the functional check required by paragraph (f)(1) or (f)(2) of this AD indicates that the aluminum-loaded primer and aluminum-loaded enamel coating have been properly applied, as defined in the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009: Before further flight, restore the protective finish on the areas where the surface finish was removed for the functional check, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (4) If the functional check required by paragraph (f)(1) or (f)(2) of this AD indicates that the aluminum-loaded primer and aluminum-loaded enamel coating have not been applied or have not been properly applied, as defined in the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009: Perform the actions required by paragraphs (f)(4)(i), (f)(4)(ii), and (f)(4)(iii) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (i) Before further flight, strip the affected wing skin surfaces to bare metal and apply alodine coating to those areas, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (ii) Within 90 flight hours after performing the actions required by paragraph (f)(4)(i) of this AD, and thereafter at intervals not to exceed 90 flight hours: Perform a detailed visual inspection of the stripped areas for any sign of corrosion or deterioration of the protective alodine coating, and re-apply the protective alodine coating, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (iii) Within 3 months after performing the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable: Paint the affected wing skin surfaces with aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (5) Accomplishment of the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable, before the effective date of this AD, in accordance with Bombardier Service Bulletin 8-57-46, dated September 29, 2008, is acceptable for compliance with the corresponding requirements of this AD. (6) Accomplishment of the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable, in accordance with AD 2008-13-09, Amendment 39-15572, is acceptable for compliance with the corresponding requirements of this AD, provided the actions are done within the applicable compliance times specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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, 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), 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 Canadian Airworthiness Directive CF-2009-05, dated January 29, 2009; and Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009; for related information. Material Incorporated by Reference (i) You must use Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bombardier, Inc., 400 Côte-Vertu Road West, Dorval, Québec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail thd.qseries@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 February 24, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-4652 Filed 3-8-10; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions. (1) For airplanes on which Bombardier Modification 8/0024 has not been done: Within 18 months after the effective date of this AD, perform a functional check of the dielectric properties of the fuel tank skin between Yw171.20 and Yw261.00 of the upper and lower wing for aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (2) For airplanes on which Bombardier Modification 8/0024 has been done: Within 18 months after the effective date of this AD, perform a functional check of the dielectric properties of the fuel tank skin between Yw171.20 and Yw261.00 of the upper wing for aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (3) If the functional check required by paragraph (f)(1) or (f)(2) of this AD indicates that the aluminum-loaded primer and aluminum-loaded enamel coating have been properly applied, as defined in the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009: Before further flight, restore the protective finish on the areas where the surface finish was removed for the functional check, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (4) If the functional check required by paragraph (f)(1) or (f)(2) of this AD indicates that the aluminum-loaded primer and aluminum-loaded enamel coating have not been applied or have not been properly applied, as defined in the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009: Perform the actions required by paragraphs (f)(4)(i), (f)(4)(ii), and (f)(4)(iii) of this AD, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (i) Before further flight, strip the affected wing skin surfaces to bare metal and apply alodine coating to those areas, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (ii) Within 90 flight hours after performing the actions required by paragraph (f)(4)(i) of this AD, and thereafter at intervals not to exceed 90 flight hours: Perform a detailed visual inspection of the stripped areas for any sign of corrosion or deterioration of the protective alodine coating, and re-apply the protective alodine coating, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (iii) Within 3 months after performing the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable: Paint the affected wing skin surfaces with aluminum-loaded primer and aluminum-loaded enamel coating, in accordance with Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009. (5) Accomplishment of the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable, before the effective date of this AD, in accordance with Bombardier Service Bulletin 8-57-46, dated September 29, 2008, is acceptable for compliance with the corresponding requirements of this AD. (6) Accomplishment of the actions required by paragraph (f)(1) or (f)(2) of this AD, as applicable, in accordance with AD 2008-13-09, Amendment 39-15572, is acceptable for compliance with the corresponding requirements of this AD, provided the actions are done within the applicable compliance times specified in this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, 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, 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. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), 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 Canadian Airworthiness Directive CF-2009-05, dated January 29, 2009; and Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009; for related information. Material Incorporated by Reference (i) You must use Bombardier Service Bulletin 8-57-46, Revision A, dated February 6, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Bombardier, Inc., 400 Côte-Vertu Road West, Dorval, Québec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-7401; e-mail thd.qseries@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 February 24, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-4652 Filed 3-8-10; 8:45 am] BILLING CODE 4910-13-P