N405DD
Registered owner: VINERIPE INC, CA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| Fargo Jet Center LLC (CTUA) | Certificate holder | — | Matched by certificate designator |
| UND AEROSPACE FOUNDATION | Operator | on 2009-07-23 | Operator named in NTSB report |
Accident & incident history
Operated by UND Aerospace Foundation (per NTSB report)
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
4 reports on file, 2006-08-24.
Part: BOLT — OVERTORQUED (RUDDER SYS)
DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTION INVESTIGATED PILOT COMPLAINT OF STIFF NOSEWHEEL STEERING. VERIFIED COMPLAINT, FOUND NOSEWHEEL STEERING STIFF AND LOUD POPPING NOISES COMING FROM COCKPIT UNDER FLOOR AREA WHEN TAXIED FROM COPILOTS POSITION. ACCESSED COCKPIT AREA RUDDER CONTROL SYSTEM AND FOUND PILOTS SIDE OB RUDDER CONTROL PUSHROD TO HAVE EXCESSIVE PLAY. UPON REMOVING OB PUSHROD ASSY. BEARINGS FELL OUT OF ROD END BEARING ASSY. FURTHER INVESTIGATION SHOWED PN 50-5244553 LT SIDE RUDDER BELLCRANK ASSY OPERATION TIGHT, FOUND PN 139909B47 PIVOT BOLT OVERTIGHTENED. ALSO FOUND LT TO RT RUDDER CONTROLS INTERCONNECT TUBE ATTACHING HARDWARE OVERTIGHTENED. (K)
Part: MOUNT — DISTORTED (RUDDER SERVO)
DURING FIRST SCHEDULED 1ST AND 2ND PHASE INSPECTIONS NOTED SQUEAKING AND METAL TO METAL CONTACT NOISES WHEN RUDDER MOVED SIDE TO SIDE. FOUND RUDDER SERVO CABLE RUBBING ON SMT-65 SERVO MOUNT CABLE DRUM COVER. REPLACED SMT-65 UNIT AND REINSTALLED, RIGGED SERVO CABLE. RUDDER OPERATIONS NOW NORMAL, AUTOPILOT OPERATIONAL CHECKS OK. SUSPECT SMT -65 SERVO MOUNT EITHER DISTORTED FROM PRIOR HANDLING OR NOT ASSEMBLED CORRECTLY. (K)
Part: FASTENER — OVERTORQUED (RUDDER SYS)
FOUND OTHER LT SIDE RUDDER CONTROL ATTACHING HARDWARE TIGHT OR OVERTIGHTENED. EXAMINED LT RUDDER CONTROL SYSTEM HARDWARE FOR SERVICEABILITY AND REINSTALLED AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED. REPLACED PILOT`S OB PUSHROD ASSY BEARINGS AND REINSTALLED. NOSEWHEEL STEERING AND RUDDER OPERATIONS FOUND NORMAL AFTER REASSEMBLY. SUSPECT HARDWARE POSSIBLY OVERTIGHTENED DURING INITIAL AC ASSY, AIRCRAFT WAS ALSO SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MFG. RECOMMENDED FURTHER INVESTIGATION BY MFG TO DETERMINE IF A ONE-TIME SB. (K)
Part: CONTROL CABLE — OUT OF ADJUST (ELEVATOR)
DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTIONS NOTED ELEVATOR CONTROL SYSTEM CABLE TENSIONS OUT OF MM SERVICE LIMITS. FOUND ELEVATOR NEUTRAL POSITIONS OUT OF LIMITS FOLLOWING CABLE TENSION ADJUSTMENTS (WITH FORWARD AND AFT RIG PINS INSTALLED). FOUND FORWARD BELLCRANK DOWN STOP BOLT CLEARANCE PAST SERVICE LIMIT AND ADJUSTED. FOUND ELEVATOR BOBWEIGHT CLEARANCE GAP EXCESSIVE. REQUIRED ADJUSTING THE FORWARD PUSHROD ASSY AND ADDING WASHERS TO OBTAIN BOBWEIGHT CLEARANCE WITHIN SERVICE LIMITS. AIRCRAFT HAD BEEN SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MANUFACTURE LOGBOOK RECORDS. RECOMMEND FOLLOW-UP INVESTIGATION BY MFG ON OTHER AC. (K)