AD 2009-04-04 Airworthiness Directives; Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, and 402B Airplanes

Makes named: cessna. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the following airplane models and serial numbers that are certificated in any category:   Models Serial Nos. 401 655 and 401-0001 through 401-0322. 401A 655 and 401A0001 through 401A0132. 401B 401B0001 through 401B0221. 402 402-0001 through 402-0322. 402A 402A0001 through 402A0129. 402B 402B0001 through 402B0122, 402B0201 through 402B0249, 402B0301 through 402B0455, 402B0501 through 402B0640, 402B0801 through 402B0935, 402B1001 through 402B1100, 402B1201 through 402B1250, and 402B1301 through 402B1384.

To address this problem, you must do the actions below using Cessna Service Bulletin MEB08-8, dated December 23, 2008, at the following compliance time, unless already done: Note 1: Cessna Service Bulletin MEB08-8, dated December 23, 2008, provides detailed instructions on measuring, inspecting, and replacing cracked parts, including how to handle two or more cracks in the same hole. (1) Within the next 10 hours time-in-service (TIS) after March 2, 2009 (the effective date of this AD) and, in addition, before further flight anytime the airplane experiences a “hard landing,” visually inspect the auxiliary wing spar near the location where the main landing gear trunnion is mounted for cracks. (2) If any crack is found during any inspection required by this AD that is 0.5 inch or more, before further flight after any such crack is found, replace the cracked parts. (3) If cracks are found during any inspection required by this AD that are less than 0.5 inch, do the following: (i) Repetitively thereafter inspect the cracks for length at intervals not to exceed 50 hours TIS and, before further flight, replace any part that has a crack length of 0.5 inch or more; and (ii) Replace the cracked part within 200 hours TIS after the original crack was found or within 12 months after the original crack was found, whichever occurs first. (4) If you find any cracks as a result of any inspection required by this AD, report the results to Cessna using the form in the service bulletin. Send a copy of this report to the FAA at the address specified in paragraph (f) of this AD. For the reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. Do the reporting requirement at whichever of the following that occurs later: (i) Within 10 days after the inspection; or (ii) Within the next 10 days after March 2, 2009 (the effective date of this AD). Note 2: The FAA considers this interim action. We will work with Cessna and evaluate the crack reports and all other information. Based on this information, we may initiate additional rulemaking action. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), 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: Adam Neubauer, Wichita ACO, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4156; fax: (316) 946-4107. 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. Material Incorporated by Reference (g) You must use Cessna Service Bulletin MEB08-8, dated December 23, 2008, 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, P.O. Box 7704, Wichita, Kansas 67277; telephone: (800) 423-7762 or (316) 517-6056; Internet: http://www.cessna.com . (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329-3768. (4) You may also review copies of the service information incorporated by reference for this AD 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 Kansas City, Missouri, on February 6, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-3016 Filed 2-17-09; 8:45 am] BILLING CODE 4910-13-P

This AD is the result of several reports of fatigue cracking on the affected airplanes in the auxiliary wing spar. We are issuing this AD to detect and correct such cracks, which, if not corrected, could result in failure of the wing auxiliary spar web and cause landing gear collapse during normal landing. This could lead to loss of control and passenger injury.