Airworthiness Directive · Amendment 39-14022 · the Cessna Aircraft Company Models 402C and 414A Airplanes
the Cessna Aircraft Company Models 402C and 414A Airplanes
Superseded. A later AD replaced this one: AD 2005-12-13. Comply with the one in force.
This AD affects Model 402C and 414A airplanes, all serial numbers, that:
(1) are certificated in any category; and
(2) do not incorporate a spar strap modification on each wing spar following the original release of (or a later FAA-approved revision to) Cessna Service Bulletin MEB02-5 and Cessna Service Kit SK402-47 (currently at MEB02-5 Revision 2 and SK402-47B).
The FAA is adopting a new airworthiness directive (AD) to supersede emergency AD 2005-05-51 and AD 2000-23-01 for The Cessna Aircraft Company (Cessna) Models 402C and 414A airplanes. This AD contains the same information as emergency AD 2005-05-52 and publishes the action in the Federal Register. It requires you to eddy current inspect the forward wing spars and visually inspect the aft and auxiliary spars. This AD is the result of extensive cracks found on three wing spars of the affected airplanes. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control of the airplane.
Visual Inspections for all Model 402C airplanes With Fewer than 15,000 Hours Total Time-in-service (TIS): Initially inspect upon accumulating 10,000 hours TIS on the airplane or at the next inspection that would have been required by AD 2000-23-01 or emergency AD 2005-05-51, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 110 hours TIS until accumulating 15,000 hours TIS:
(1) Perform both a visual external and internal inspection of the forward, aft, and auxiliary wing spars for cracks.
(2) Do these visual inspections following the Accomplishment Instructions section of Cessna Service Bulletin MEB99-3 (Model 402C), Revision 2, dated February 28, 2005.
(3) When doing the inspections, pay particular attention to the following areas:
(i) Just Outboard of the Engine Beam
(A) The main lower spar cap at Wing Station (WS) 114.
(B) The three rivets on both the inboard and outboard sides of WS 114 (total of six rivets) in the main lower spar cap as viewed from the access hole.
(C) The main spar web at WS 112.5.
(ii) Just Inboard of the Inboard Engine Beam
(A) The main lower spar cap between WS 80 and WS 89.
(B) The two attach bolts on the main spar just inboard of the WS 89.18 rib.
(f) Eddy Current and Visual Inspections: Perform eddy current inspections of the forward wing spars combined with visual inspections of the aft and auxiliary spars. Do these inspections following the Accomplishment Instructions section of Cessna Service Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7 (Model 414A), both at Revision 2 and both dated February 28, 2005.
| Affected airplanes | Eddy current and visual inspections | Repetitive Eddy current and visual inspection interval |
|---|---|---|
| (1) For Model 414A airplanes, serial numbers 414A001 through 414A0047 and 414A0049 through 414A0200 | At whichever of the following occurs later: • Upon accumulating 8,500 hours TIS on the airplanes; • At the next inspection that would have been required by emergency AD 2005-05-51 (required at intervals not to exceed 15 hours TIS); or • Within the next 2 days after the effective date of this AD (2 days after receipt for those who received emergency AD 200505-52) | Thereafter at intervals not to exceed 100 hours TIS. |
| (2) For the following airplanes that have 15,000 hours or more TIS or upon accumulating 15,000 hours TIS: | At whichever of the following occurs later: • Upon accumulting 15,000 hours TIS on the airplane; • At the next inspection that would have been required by emergency AD 2005-05-51 (required at intervals not to exceed 15 hours TIS); or • Within the next 2 days after effective date of this AD (2 days after receipt for those who received emergency AD 2005-05-52) | Thereafter at intervals not to exceed 100 hours TIS. |
| (i) All Model 402C airplanes. | ||
| (ii) Model 414A airplanes, serial numbers 414A0201 through 414A1212 |
Note: The Cessna service bulletins allow for either a visual inspection or eddy current inspection of the forward spars on all airplanes affected by this AD. Visual inspections of the forward spars do not satisfy the requirements of this AD for the airplanes referenced in paragraphs (f)(1) and (f)(2) of this AD. These airplanes must have the forward spars inspected using the eddy current methods specified in the Cessna service bulletins.
(g) Cracks Found: If you find any crack on any forward, aft, or auxiliary wing spar; or in surrounding structure such as spar webs or skins during any inspection required by this AD, before further flight do the following:
(1) Obtain an FAA-approved repair scheme from the Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800, facsimile: (316) 942-9006; and
(2) Incorporate this repair scheme.
(h) Reporting Requirement: As soon as possible, but no later than 24 hours after any inspection required by this AD and as defined below:
(1) Submit a report of inspection findings to the Manager, Wichita Aircraft Certification Office (ACO), by fax: (316) 946-4107.
(i) Include a report for “cracks found” or “no cracks found” on the initial inspection; and
(ii) Include a report only for “cracks found” on the repetitive inspections.
(2) The report must include your name and a contact phone number, the results of the findings, a description of any cracking found, the airplane serial number, and the total number of hours TIS on the airplane. The “Lower Wing Spars and Skin Inspection Report” included in Cessna Service Bulletin MEB99-3 and MEB00-7 may be utilized for this reporting requirement.
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.
Aircraft
