AD 2008-11-11 Airworthiness Directives; Viking Air Limited Model DHC-2 Series Airplanes

Models named: DHC-2 Mk. I, DHC-2 Mk. II, DHC-2 Mk. III. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes, all serial numbers, certificated in any category.

Unless already done, do the following: (1) For airplanes with cracks that have been previously repaired with stop-drilled holes: Within the next 12 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), replace the tailplane front spar following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992. (2) For airplanes with lightening holes (without modification 2/466): Within the next 200 hours time-in-service (TIS) after December 15, 1992 (the compliance date retained from AD 92-24-02), visually inspect the front spar web in the area of the lightening holes for cracks between the pickup brackets. (i) If cracks are found, before further flight, incorporate Modification 2/466: installation of tailplane front spar without lightening holes, following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; or Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. (ii) If cracks are not found, within the next 24 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), incorporate Modification 2/466: installation of tailplane front spar without lightening holes, following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; or Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. Note 1: Modification 2/466, installation of tailplane front spar without lightening holes, is referenced in AD 92-24-02 and Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; and Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. Accomplishment of AD 92-24-02 or this AD incorporates modification 2/466. (3) For the following airplanes: Within the next 24 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), do the following: (i) For airplanes having serial numbers (S/Ns) 1 through 100: Install longer pick-up brackets (modification 2/436) following deHavilland Technical News Sheet B55, dated August 1, 1952. Note 2: Modification 2/436 was incorporated at manufacture on airplanes beginning with S/N 101. Other airplanes may have incorporated this modification in the field. (ii) For airplanes having S/N 1 through 317: Install a gusset plate on the rear face at each of the pick-up brackets (modification 2/758) following deHavilland Technical News Sheet B55, dated August 1, 1952. Note 3: Modification 2/758 was incorporated at manufacture on airplanes beginning with S/N 318. Other airplanes may have incorporated this modification in the field. (4) For all airplanes: Within 200 hours time-in-service (TIS) after July 23, 2008 (the effective date of this AD) and repetitively thereafter at intervals not to exceed every 24 months, remove the tailplane front spar pick-up brackets and do a fluorescent penetrant inspection of the tailplane front spar web for cracks in the area of the pick-up brackets following Appendix A of Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. (5) For all airplanes: If during any of the inspections required in paragraph (f)(4) of this AD cracks are found, before further flight, replace the tailplane front spar following Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. The 24-month repetitive fluorescent penetrant inspection is still required. Note 4: The replacement and modifications required by this AD do not terminate the 24-month repetitive fluorescent penetrant inspection required by paragraph (f)(4) of this AD. (6) For all airplanes: If any cracks are found as a result of the inspections required by this AD, use the following contact information to report your results: Viking Air Limited, Technical Support, 9574 Hampden road, Sidney, British-Columbia, Canada, V8L 5V5; telephone: regional 250-656-7227, North America 1-800-0663-8444, or international 1-800-6727-6727; fax: 250-656-0673; e-mail: technical.support@vikingair.com. FAA AD Differences Note 5: 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, 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: Pong Lee, Aerospace Engineer, FAA, New York Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228-7324; fax: (516) 794-5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 Transport Canada AD CF-1991-42R1, dated March 13, 2007; and Viking DHC-2 Beaver Service Bulletin No. 2/47, Revision E, dated January 23, 2007, for related information. Material Incorporated by Reference (i) You must use Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; deHavilland Technical News Sheet B55, dated August 1, 1952; and Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 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 Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) On December 15, 1992 (57 FR 53254, November 9, 1992), the Director of the Federal Register previously approved the incorporation by reference of deHavilland Technical News Sheet B55, dated August 1, 1952; and Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992. (3) For service information identified in this AD, contact Viking Air Limited, 9574 Hampden Road, Sidney, B.C., Canada V8L 5V5 or R.W. Martin, Inc., 37552 Winchester Road, Hangar 20, Murrieta, California 92563. (4) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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/ibr-locations.html . Issued in Kansas City, Missouri, on June 10, 2008. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-13478 Filed 6-17-08; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following: (1) For airplanes with cracks that have been previously repaired with stop-drilled holes: Within the next 12 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), replace the tailplane front spar following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992. (2) For airplanes with lightening holes (without modification 2/466): Within the next 200 hours time-in-service (TIS) after December 15, 1992 (the compliance date retained from AD 92-24-02), visually inspect the front spar web in the area of the lightening holes for cracks between the pickup brackets. (i) If cracks are found, before further flight, incorporate Modification 2/466: installation of tailplane front spar without lightening holes, following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; or Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. (ii) If cracks are not found, within the next 24 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), incorporate Modification 2/466: installation of tailplane front spar without lightening holes, following Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; or Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. Note 1: Modification 2/466, installation of tailplane front spar without lightening holes, is referenced in AD 92-24-02 and Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; and Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. Accomplishment of AD 92-24-02 or this AD incorporates modification 2/466. (3) For the following airplanes: Within the next 24 calendar months after December 15, 1992 (the compliance date retained from AD 92-24-02), do the following: (i) For airplanes having serial numbers (S/Ns) 1 through 100: Install longer pick-up brackets (modification 2/436) following deHavilland Technical News Sheet B55, dated August 1, 1952. Note 2: Modification 2/436 was incorporated at manufacture on airplanes beginning with S/N 101. Other airplanes may have incorporated this modification in the field. (ii) For airplanes having S/N 1 through 317: Install a gusset plate on the rear face at each of the pick-up brackets (modification 2/758) following deHavilland Technical News Sheet B55, dated August 1, 1952. Note 3: Modification 2/758 was incorporated at manufacture on airplanes beginning with S/N 318. Other airplanes may have incorporated this modification in the field. (4) For all airplanes: Within 200 hours time-in-service (TIS) after July 23, 2008 (the effective date of this AD) and repetitively thereafter at intervals not to exceed every 24 months, remove the tailplane front spar pick-up brackets and do a fluorescent penetrant inspection of the tailplane front spar web for cracks in the area of the pick-up brackets following Appendix A of Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. (5) For all airplanes: If during any of the inspections required in paragraph (f)(4) of this AD cracks are found, before further flight, replace the tailplane front spar following Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007. The 24-month repetitive fluorescent penetrant inspection is still required. Note 4: The replacement and modifications required by this AD do not terminate the 24-month repetitive fluorescent penetrant inspection required by paragraph (f)(4) of this AD. (6) For all airplanes: If any cracks are found as a result of the inspections required by this AD, use the following contact information to report your results: Viking Air Limited, Technical Support, 9574 Hampden road, Sidney, British-Columbia, Canada, V8L 5V5; telephone: regional 250-656-7227, North America 1-800-0663-8444, or international 1-800-6727-6727; fax: 250-656-0673; e-mail: technical.support@vikingair.com. FAA AD Differences Note 5: 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, 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: Pong Lee, Aerospace Engineer, FAA, New York Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228-7324; fax: (516) 794-5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 Transport Canada AD CF-1991-42R1, dated March 13, 2007; and Viking DHC-2 Beaver Service Bulletin No. 2/47, Revision E, dated January 23, 2007, for related information. Material Incorporated by Reference (i) You must use Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992; deHavilland Technical News Sheet B55, dated August 1, 1952; and Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 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 Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) On December 15, 1992 (57 FR 53254, November 9, 1992), the Director of the Federal Register previously approved the incorporation by reference of deHavilland Technical News Sheet B55, dated August 1, 1952; and Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September 4, 1992. (3) For service information identified in this AD, contact Viking Air Limited, 9574 Hampden Road, Sidney, B.C., Canada V8L 5V5 or R.W. Martin, Inc., 37552 Winchester Road, Hangar 20, Murrieta, California 92563. (4) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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/ibr-locations.html . Issued in Kansas City, Missouri, on June 10, 2008. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-13478 Filed 6-17-08; 8:45 am] BILLING CODE 4910-13-P