FARGO JET CENTER LLC

Operated by FARGO JET CENTER LLC (per NTSB report)

TRIED FLYING N817PA MORNING OF MAY 7TH AND THE RIGHT SIDE DOESN'T COME OUT OF THE GROUND PITCH. DOING THE AUTO FEATHER TEST, THE RIGHT PROP WAS AT 1700 RPM. TRIED DOING THE GROUND IDLE STOP TEST AND THE RIGHT SIDE FAILED THAT TEST. COULDN'T GET IT TO SWITCH TO THE FLIGHT PITCH. MAINTENANCE DISCOVERED THAT THE GROUND IDLE SOLENOID DROPOUT SWITCH WAS MISSING THE LEVER TO ACTUATE THE MICROSWITCH. PER THE LOG ENTRY "REPLACED R/H ENGINE GROUND IDLE SOLENOID DROPOUT SWITCH LEVER, P/N: JS-151, IAW KING AIR B300 M/M 76-10-17. OPS CHECK GOOD."

AFTER DEPARTURE CLIMBING THRU 8000 FT MSL CREW HEARD A POPPING NOISE, NOTICED CO-PILOTS WINDSHIELD HAD CRACKED. NO EMERGENCY DECLARED, AC RETURNED TO AIRPORT. NO OTHER AIRCRAFT DAMAGE. TYPICAL WINDSHIELD FAILURE TOLAMINATED HEATED WINDSHIELD. (K)

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)

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)

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)

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)

THE AIRCRAFT WAS AT 33,000 FT WITH THE WINDSHIELD HEAT OFF, SPEED OF 290 KNOTS AND CABIN PRESSURIZED TO 6.5 PSI WHEN THE WINDSHIELD CRACKED. THEY WERE ALSO IN CLEAR AIR, WITH NO TURBULENCE. (GL21200500727)

PILOT REPORTED BLEED AIR WARNING INDICATION ON LEFT SIDE. TROUBLE SHOT AND FOUND EVA TUBING MELTED BELOW HEAT DUCT. DISCOVERED EARLIER REPAIR (WITHIN 1O HOURS) OF RIGHT SIDE TUBING 2 INCHES FROM LATEST FAILURE. TUBING IS COMING IN CONTACT WITH DUCT AND MELTING. ANOTHER STANDOFF IS REQUIRED TO MAINTAIN TUBING CLEARANCE NOTED IN MM. 1683 HOURS TOTAL TIME

PILOT CALLED IN AND REPORTED FLUCTUATION OF FUEL AND TORQUE INDICATION ON RIGHT ENGINE. RETURNED TO BASE AND MONITORED ENGINE PARAMETERS, SHUT DOWN RIGHT ENGINE WHEN UNABLE TO CONTROL TORQUE SETTINGS. ON INSPECTION FOUND BEARING FAILED ON FUEL CONTROL UNIT, WAS THE FRONT BEARING ON DRIVESHAFT,PN 2525501. TEARDOWN REPORTED BEARING WASHED OUT/ LUBRICANT WAS LOST THROUGH SEAL.

PILOT SELECTED GEAR DOWN, NO RESPONSE. PERFORMED MANUAL GEAR EXTENSION AND LANDED AIRCRAFT. TROUBLESHOT GEAR DOWN CIRCUIT, FOUND ATTACHING SCREENS FOR GEAR DOWN RELAY IN LANDING. GEAR CONTROL BOX HAD COME LOOSE. RE-SECURED RELAY AND PERFORMED GEAR RETRACTION, CHECK OK. GEAR MOTOR CONTROL BOX WAS REPLACED 12-7-93, ACFT TT: 6,446.4 HRS WITH OVERHAULED UNIT. (X)