2007-05-10: Steel lock rod/bar on both crew seat back cylinder lock assemblies

2007-05-10 Cessna Aircraft Company: Amendment 39-14971; Docket No. FAA-2006-25261; Directorate Identifier 2006-CE-38-AD. Effective Date (a) This AD becomes effective on April 11, 2007. Affected ADs (b) None. Applicability (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos. 172R ...... 17280001 through 17281262. 172S ...... 172S8001 through 172S9994. 182S ...... 18280001 through 18280944. 182T ....... 18280945 through 18281701. T182T .... T18208001 through T18208453. 206H ...... 20608001 through 20608250. T206H .... T20608001 through T20608570. Unsafe Condition (d) This AD results from reports of the crew seat back cylinder lock assembly failing at the aft end area and other cylinder lock assemblies found cracked. The actions specified in this AD are intended to prevent the crew seat cylinder lock assembly from bending, cracking, or failing. This failure could cause uncontrolled movement of the seat back, resulting in possible backward collapse during flight. Backward collapse of either crew seat back could result in an abrupt pitch-up if the affected crew member continues to hold on to the control yoke during this failure and could cause difficulty in exiting the airplane from an aft passenger seat after landing. Compliance (e) To address this problem, you must do the following, unless already done: (1) Airplanes that do not have Modification Kit MK172-25-10A or Modification Kit MK172-25-10B installed: Action Compliance Procedures For each crew seat (pilot and copilot), install Modification Kit MK172-25-10C or fabricate and install a steel lock rod/bar. For airplanes that have over 1,000 hours time-in-service (TIS) on the effective date of this AD: do the action within the next 4 months after April 11, 2007 (the effective date of this AD). For airplanes that have from 501 to 1,000 hours TISon the effective date of this AD: do the action within the next 8 months after April 11, 2007 (the effective date of this AD). For airplanes that have from 0 to 500 hours TIS on the effective date of this AD: do the action within the next 12 months after April 11, 2007 (the effective date of this AD). Follow Cessna Single Engine Service Bulletin SB04-25-01, Revision 4, dated December 26, 2006, for installing Modification Kit MK172-25-10C. Follow Cessna Single Engine Service Bulletin SB04-25-02, Revision 1, dated October 17, 2005, or Revision 2, dated June 5, 2006, for fabricating and installing a steel lock rod/bar. (2) Airplanes that have Modification Kit MK172-25-10A or Modification Kit MK172-25-10B installed: Action Compliance Procedures (i) For each crew seat (pilot and copilot), do an installation inspection. Within the next 30 days after April 11, 2007 (the effective date of this AD). Follow Cessna Single Engine Service Bulletin SB04-25-01, Revision 4, dated December 26, 2006. (ii) If you do not find any discrepancies during the inspection required in paragraph (e)(2)(i) of this AD, make a log book entry showing compliance with this AD and no further action is required. Before further flight after the inspection required in paragraph (e)(2)(i) of this AD. Follow Cessna Single Engine Service Bulletin SB04-25-01, Revision 4, dated December 26, 2006. (iii) If you find discrepancies during the inspection required in paragraph (e)(2)(i) of this AD, make all necessary corrective actions. Before further flight after the inspection required in paragraph (e)(2)(i) of this AD. Follow Cessna Single Engine Service Bulletin SB04-25-01, Revision 4, dated December 26, 2006. Note: Although not required for the airplanes affected by this AD, you may replace the steel lock rod/bar with Modification Kit MK172-25-10C. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Gary Park,Aerospace Engineer, 1801 Airport Road, Mid- Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4123; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (g) You must use Cessna Single Engine Service Bulletin SB04-25- 01, Revision 4, dated December 26, 2006; and Cessna Single Engine Service Bulletin SB04-25-02, Revision 1, dated October 17, 2005, or Revision 2, dated June 5, 2006, 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 Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, KS 67277; telephone: (316) 517-5800; fax: (316) 942-9006. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, 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/code_of_federal_regulations/ibr_locations.html .