Airworthiness Directive · Amendment 39-11971 · Cessna Aircraft Company Model 402C Airplanes
Cessna Aircraft Company Model 402C Airplanes
Superseded. A later AD replaced this one: AD 2005-05-51, AD 2005-05-52, AD 2005-12-12, AD 2005-12-13. Comply with the one in force.
Any Model 402C airplane, certificated in any category, that has a serial number that falls within one of the following ranges:
(1) 689;
(2) 402C0001 through 402C0125;
(3) 402C0201 through 402C0355;
(4) 402C0401 through 402C0528;
(5) 402C0601 through 402C0653; and
(6) 402C0801 through 402C1020.
This amendment supersedes Airworthiness Directive (AD) 99-11- 13, which currently requires inspecting (one-time) the forward, aft, and auxiliary wing spars for cracks on certain Cessna Aircraft Company (Cessna) Model 402C airplanes, and repairing any cracks found. AD 99- 11-13 also requires reporting the results of the inspection to the Federal Aviation Administration (FAA) to provide data to help us determine whether the inspection should be repetitive. After re- evaluating the fatigue analysis for the wing spars on the affected airplanes, we have determined that spar cap cracking is not an isolated condition and could continue to develop over the life of the affected airplanes. This AD retains the inspection required in AD 99-11-13, and will make the inspection repetitive. The actions specified by this AD are intended to detect and correct any cracks in the forward, aft, and auxiliary wing spars, which could result in reduced or loss of control of the airplane.
To address this problem, you must accomplish the following:
| Actions | Compliance times | Procedures |
|---|---|---|
| (1) Accomplish both an external and internal inspection of the forward, aft, and auxiliary wing spars for cracks | Initially inspect upon accumulating 10,000 hours total time-in-service (TIS) on the airplane or within the next 25 hours TIS after June 21, 1999 (the effective date of AD 99-11-13), whichever occurs later. Repetitively inspect thereafter within 110 hours TIS after the last inspection required by this AD or Ad 99-11-13, whichever is applicable, and thereafter at intervals not to exceed 110 hours TIS | Accomplish these inspections in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3, dated May 6, 1999. |
| (2) If any crack is found on any forward, aft, or auxiliary wing spar during any inspection required by this AD, accomplish the following: | ||
| (i) Obtain an FAA-approved repair scheme from the Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 941-7550, facsimile: (316) 942-9008; and | ||
| (ii) Incorporate this repair scheme | Prior to further flight after the inspection where the crack is found | Not applicable. |
Note 1: The 110-hour TIS interval repetitive inspection time is established to allow this action to be accomplished with regular maintenance. The FAA initially determined that 100-hour TIS intervals would provide the safety intent, but has since determined that the 110-hour TIS intervals would provide the same safety intent while providing a 10-percent time flexibility in scheduling to coincide with regular maintenance.
Note 2: The compliance times specified in Cessna Service Bulletin MEB99-3, dated May 6, 1999, are different than those required by this AD. The times in this AD take precedence over those in the service bulletin.
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.
