Airworthiness Directive · Amendment 39-15810 · Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, and 402B Airplanes
Cessna Aircraft Company Models 401, 401A, 401B, 402, 402A, and 402B Airplanes
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. |
The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, and 402B airplanes. This AD requires an inspection of the auxiliary wing spar near the location where the main landing gear trunnion is mounted for cracks; immediate replacement if cracks of 0.5 inch or more are found; repetitive inspections with replacement at a later time as long as cracks of less than 0.5 inch are found; and a report to the FAA and Cessna if any cracks are found. This AD results from 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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
