2005-12-12: Right and left wing spar lower cap areas

2005-12-12 Cessna Aircraft Company: Amendment 39-14128; Docket No. FAA-05-21176; Directorate Identifier 2005-CE-25-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 79-10-15; Amendment 39-3711. What Airplanes Are Affected by This AD? (c) This AD affects Models 401, 401A, 401B, 402, 402A, 402B, 411, and 411A, 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) Repetitive Inspection and Modification of the Wing Spars: (1) For Cessna Models 411 and 411A airplanes that do notincorporate Cessna Service Kit SK411-56, SK411-56A, SK411-56B, or SK411-59, maintain the repetitive inspections required by AD 79-10- 15, Amendment 39-3711, and do the actions below. You may terminate the repetitive inspections of AD 79-10-15 after you incorporate the modification using the service information in paragraph (h)(2) of this AD: If you have equal to or more than But less than Then initially inspect and modify using the service information in paragraph (h)(2) of this AD, and reinspect as specified in paragraph (e)(3) of this AD (i) 18,000 hours time-in-service (TIS) on the wing or wing spar. Not applicable Within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (ii) 12,000 hours TIS on the wing or wing spar 18,000 hours TIS Within 200 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (iii) 10,000 hours TIS on the wing or wing spar 12,000 hours TIS Within400 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (iv) 5,500 hours TIS on the wing or wing spar 10,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (v) 0 hours TIS on the wing or wing spar 5,500 hours TIS At whichever of the following occurs later: Upon accumulating 5,500 hours TIS on the wing or wing spar; or Within 800 TIS after June 22, 2005 (the effective date of this AD), unless already done. (vi) 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)(i) through (e)(1)(v) of this AD. (vii) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbookrecords cannot positively show the TIS of the wings or wing spars, then inspect and modify within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (2) For Cessna Models 401, 401A, 401B, 402, 402A, and 402B airplanes that do not incorporate Cessna Service Kit SK402-36, SK402-36A, SK402-36B, SK402-36C, SK402-46, or SK402-46A, maintain the repetitive inspections required by AD 79-10-15, Amendment 39-3711, and do the actions below. You may terminate the repetitive inspections of AD 79-10-15 after you incorporate the modification using the service information in paragraph (h)(1) of this AD: If you have equal to or more than But less than Then initially inspect and modify using the service information in paragraph (h)(1) of this AD, and reinspect as specified in paragraph (e)(4) of this AD (i) 18,000 hours TIS on the wing or wing spar Not applicable Within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (ii) 12,000 hours TIS on the wing or wing spar 18,000 hours TIS Within 200 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (iii) 10,000 hours TIS on the wing or wing spar 12,000 hours TIS Within 400 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (iv) 6,500 hours TIS on the wing or wing spar 10,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (v) 0 hours TIS on the wing or wing spar . 6,500 hours TIS At whichever of the following occurs later: Upon accumulating 6,500 hours TIS on the wing or wing spar; or Within 800 TIS after June 22, 2005 (the effective date of this AD), unless already done. (vi) 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)(2)(i) through (e)(2)(v) of this AD. (vii) 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 spars, then inspect and modify within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (3) For all Cessna Models 411 and 411A airplanes with Cessna Service Kit SK411-56, SK411-56A, SK411-56B, or SK411-59 incorporated, inspect in the following areas and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspection areas and procedures are defined in the Cessna Model 411 Supplemental Inspection Document (SID): (i) Area "A" (Inspection ID 57-10-11): Initially upon accumulating 5,500 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 2,500 hours TIS. (ii) Area "B" (Inspection ID 57-10-12): Initially upon accumulating 5,500 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 1,000 hours TIS. (iii) Area "C" (Inspection ID 57-10-08): Upon accumulating 20,000 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 2,000 hours TIS. (4) For all Cessna Models 401, 401A, 401B, 402, 402A, and 402B airplanes with Cessna Service Kit SK402-36, SK402-36A, SK402-36B, SK402-36C, SK402-46, or SK402-46A incorporated, inspect in the following areas and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspection areas and procedures are defined in the Cessna Models 401 and 402 SID (compliance times in this AD take precedence over the compliance times in the SID): (i) Area "A" (Inspection ID 57-10-11): Initially upon accumulating 15,000 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 5,000 hours TIS. (ii) Area "B" (Inspection ID 57-10-12): Initially upon accumulating 7,500 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 not to exceed 5,000 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. (iii) Area "C" (Inspection ID 57-10-08): Upon accumulating 20,000 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 2,500 hours TIS. (f) Wing Spar Replacement if Cracks Found During any Inspection Required by this AD: (1) 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. (2) After replacement, initially inspect at the applicable time in paragraphs (e)(1)(i) through (e)(1)(vii) or (e)(2)(i) through(e)(2)(vii) of this AD and repetitively inspect at the times specified in paragraphs (e)(3)(i) through (e)(3)(iii) or (e)(4)(i) through (e)(4)(iii) of this AD. (g) 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. (h) Service Information to Perform the Actions of this AD: (1) Original issue dated September 24, 2001, and Revision 1, dated December 22, 2003, of both Cessna Multi-engine Service Bulletin MEB01-06 and Service Kit SK402-46A; and (2) Original issue dated September 24, 2001, of both Cessna Multi-engine Service Bulletin MEB01-07 and Service Kit SK411-59. May I Request an Alternative Method of Compliance? (i) 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? (j) You must do the actions required by this AD following the instructions in Cessna Multi-Engine Service Bulletin MEB01-6 and Service Kit SK402-46, both dated September 24, 2001; Cessna Multi- Engine Service Bulletin MEB01-6, Revision 1 and Service Kit SK402-46A, both dated December 22, 2003; and Cessna Multi-Engine Service Bulletin MEB01-7 and Service Kit SK411-59, both dated September 24, 2001. 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 theDocket 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-05-21176; Directorate Identifier 2005-CE-25-AD.