2005-12-13: Forward wing spars

2005-12-13 Cessna Aircraft Company: Amendment 39-14129; Docket No. FAA-05-21177; Directorate Identifier 2005-CE-26-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 22, 2005. Are Any Other ADs Affected by This Action? (b) Yes. This AD supersedes AD 2005-05-52; Amendment 39-14022. What Airplanes Are Affected by This AD? (c) This AD affects Models 402C and 414A, all serial numbers, that are certificated in any category. What is the Unsafe Condition Presented in This AD? (d) This AD is the result of fatigue cracks found in the lower wing spar caps. We are issuing this AD to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. What Must I Do To Address This Problem? (e) Modification of the Wing Spars: (1) For Cessna Model 414A airplanes, serial numbers 414A0001 through 414A0047 and 414A0049 through 414A0200, incorporate a spar strap modification on each wing (Cessna Multi-Engine Service Kit SK402-47B, dated August 2, 2003), following Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, unless Cessna Multi-Engine Service Kit SK402-47, SK402-47A, or SK402-47B has already been done. The above modifications terminate the repetitive inspection requirements of AD 2005-05-52: If you have equal to or more than But less than Modification of the lower Wing Spar Cap compliance times (i) 12,000 hours time-in-service (TIS) Not Applicable Within 400 hours TIS after June 22, 2005 (the effective date of this AD). (ii) 9,000 hours TIS on the wing or wing spar 12,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD). (iii) 0 hours TIS on the wing or wing spar; 9,000 hours TIS At whichever of the following occurs later: Upon accumulating 9,000 hours TIS or Within 800 hours TIS after June22, 2005 (the effective date of this AD). (2) For Cessna Model 402C airplanes, all serial numbers; and Model 414A airplanes, serial numbers 414A0201 through 414A1212, incorporate a spar strap modification on each wing (Cessna Multi- Engine Service Kit SK402-47B, dated August 2, 2003), following Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, unless Cessna Multi-Engine Service Kit SK402-47, SK402-47A, or SK402-47B has already been done. The above modifications terminate the repetitive inspection requirements of AD 2005-05-52: If you have equal to or more than But less than Modification of the lower Wing Spar Cap compliance times (i) 20,000 hours TIS Not Applicable Within 400 hours TIS after June 22, 2005 (the effective date of this AD). (ii) 15,000 hours TIS on the wing or wing spar 20,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD). (iii) 0 hours TIS on the wing or wing spar 15,000 hours TIS At whichever of the following occurs later: Upon accumulating 15,000 hours TIS on the wing or wing spar; or Within 800 TIS after June 22, 2005 (the effective date of this AD). (f) Repetitive Inspection of the Wing Spar: Until the modification in paragraph (e)(1) and (e)(2) of this AD is done, continue the repetitive eddy current inspections of the forward wing spars combined with visual inspections of the aft and auxiliary spars as mandated by AD 2005-05-52. Do these inspections following the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7 (Model 414A), both at Revision 2 and both dated February 28, 2005. The modification required in paragraph (e)(1) and (e)(2) of this AD terminates the repetitive inspection requirements of AD 2005-05-52. Affected airplanes Eddy current and visual inspections Repetitive Eddy current and visual inspection interval (1) For Model 414A airplanes, serial numbers 414A0001 through 414A0047 and 414A0049 through 414A0200. At whichever of the following occurs later: Upon accumulating 8,500 hours TIS on the airplane; At the next inspection that would have been required by emergency AD 2005 05 51 (required at intervals not to exceed 15 hours TIS); or. Within the next 2 days after the March 21, 2005 (the effective date of AD 2005 05 52) (2 days after receipt for those who received this AD as an emergency AD) Thereafter at intervals not to exceed 100 hours TIS. (2) For the following airplanes that have 15,000 hours or more TIS or upon accumulating 15,000 hours TIS: (i) All Model 402C airplanes. (ii) Model 414A airplanes, serial numbers 414A0201 through 414A1212. At whichever of the following occurs later: Upon accumulating 15,000 hours TIS on the airplane; At the next inspection that would have been required by emergency AD 2005 05 51 (required at intervals not to exceed 15 hours TIS); or Within the next 2 days after March 21, 2005 (the effective date of AD 2005 05 52) (2 days after receipt for those who received this AD as an emergency AD). Thereafter at intervals not to exceed 100 hours TIS. (g) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records positively show the TIS of the wings or wing spars, then initially inspect and modify at applicable wing or wing spar times in paragraphs (e)(1), (e)(2), and (f) of this AD. (h) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records cannot positively show the TIS of the wings or wing, then inspect and modify within 400 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (i) For all Cessna Models 402C and 414A airplanes with Cessna Service Kit SK402-47, SK402-47A, or SK402-47B incorporated, inspect and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspect following the procedures in Cessna Model 402C and 414A Supplemental Inspection Document (SID), Inspection ID 57-10-16 (compliance times in this AD take precedence over the compliance times in the SID): Initially upon accumulating 12,500 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 500 hours TIS. You may request an alternative method of compliance to adjust the compliance times for these inspections by following the procedures in 14 CFR 39.19 and this AD. (j) Wing Spar Replacement if Cracks Found During any Inspection Required by this AD: Prior to further flight, replace the wing spar with a new wing spar or a used wing spar where wing or wing spar hours TIS can be positively identified. Do not install used wings spars when you are not able to positively identify total wing or wing spar hours TIS. (k) Reporting Requirement: Report any cracks you find within 10 days after the cracks are found or within 10 days after June 22, 2005 (the effective date of this AD), whichever occurs later. Do not report if no cracks are found. Include in your report the aircraft serial number, aircraft TIS, wing spar cap TIS, crack location and size, corrective action taken, and a point of contact name and phone number. Send your report to Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946- 4125; facsimile: (316) 946-4107. May I Request an Alternative Method of Compliance? (l) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Wichita Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (m) You must do the actions required by this AD following the instructions in Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, and Service Kit SK402-47B, dated August 2, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517- 5800; facsimile: (316) 942-9006. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http:// www. archives.gov/ federal_register/code_of_federal_regulations/ibr_locations. html or call (202) 741- 6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-05-21177; Directorate Identifier 2005-CE-26-AD.