N184UX
Registered owner: ALPINE AVIATION INC, UT (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
AFTER DESCENDING AND LEVELING OFF LEFT ENGINE TORQUE NOT RISISNG PROPERLY AND INCORRECT ENGINE CONTROL/FEEL, PILOT NOTICED IMPROPER PWOER OUT OF LEFT ENGINE AND DECLARED EMERGENCY DUE TO PARITAL POWER ON LEFT ENGINE. PILOT WAS CLEARED TO LAND. LANDED SAFELY AND HAD NO OTHER ISSUES.
NORMAL START, NORMAL RUNNUP. ADVANCED POWER ON RWY 28R AND MANIPULATED POWER LEVERS TO MATCH TORQUES. ROTATED AT VR AND NOTICED AN ABNORMAL SPLIT IN THE POSITION OF THE POWER LEVERS. SCANNED THE ENGINE INSTRUMENTS FOR ANY ABNORMALITIES AND FOUND THE LEFT ENGINE ITT TO BE SLIGHTLY HIGHER THAN THE RIGHT ENGINE, THE TORQUE ON THE LEFT ENGINE WAS LOWER THAN THE RIGHT ENGINE AND THE TURBINE RPM WAS SIGNIFICANTLY HIGHER THAN THE RIGHT ENGINE. CONTINUED CLIMB TO PATTERN ALTITUDE AND UTILIZING BOTH ENGINES. INFORMED TOWER OF INTENT TO RETURN TO THE FIELD FOR ENGINE ABNORMALITY. IN THE DOWNWIND AND AT OR ABOVE PATTERN ALTITUDE, AGAIN CONFIRMED THE ABNORMAL ENGINE CONDITIONS AND REDUCED THE POWER ON THE LEFT ENGINE IN LEVEL FLIGHT. EXECUTED ENGINE SHUTDOWN IN FLIGHT TO PREVENT FURTHER DAMAGE TO LEFT ENGINE AND COMPLETED THE REMAINDER OF THE NON-MEMORY ITEMS IN THE CHECKLIST. COMPLETED AN UNEVENTFUL LANDING WITH THE LEFT ENGINE SECURED AND FEATHERED. MADE A LEFT TURN OFF ON TAXIWAY ECHO AND SHUT THE AIRCRAFT DOWN AFTER THE HOLD SHORT LINE.SHUT DOWN THE AIRCRAFT AND EDWARDS JET CENTER TOWED THE AIRCRAFT BACK TO THE UPS RAMP TO OFF-LOAD CARGO ONBOARD.
PILOT REPORTED THAT THE LEFT PROPELLER SEEMS LIKE IT TRIES TO AUTOFEATHER FURING FINAL. MAINTENANCE R & R THE BETA ARM LEVER IAW BMM 61-20-00 STEP 2 PN:3054890-01, RR BETA ARM BRACKET BY REMOVING THE 2 NUTS & INSTALLED THE NEW ONE IN REVERSE ORDER PN:3111379-02 NSN REF TC 3.6.0. ITEMS 12-15.
MAJOR REPAIR, DURING A SCHEDULED INSPECTION, FOUND THE LT SIDEWALL SEAT TRACK SUPPORT, STRINGER 10L, CRACKED IN THE FLANGE BEND RADIUS, AT FS 327.63, 1" IN LENGTH. SUPPLEMENTAL INFORMATION WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
MAJOR REPAIR DURING A SCHEDULED INSPECTION, FOUND A CRACK IN THE NUTPLATE PANEL FOR THE ACCESS DOOR 632IB, WS 148.2, RT WING LOWER SIDE, 1.4" IN LENGTH. WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
MAJOR REPAIR, DURING A SCHEDULED INSPECTION, FOUND THE INBD ATTACH BOLT WORN INTO BRACKET ON THE RT INBD FLAP ACTUATOR. SUPPLEMENTAL INFORMATION WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
MAJOR REPAIR, DURING A SCHEDULED INSPECTION, FOUND FUSELAGE FRAME FLANGE CRACKED, FROM THE BEND RADIUS TO THE EDGE OF THE FLANGE, FS 150.60 BETWEEN STRINGER 2R & 3R, .75" IN LENGTH. SUPPLEMENTAL INFORMATION WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
MAJOR REPAIR, DURING A SCHEDULED INSPECTION, FOUND THE OTBD ATTACH BOLT WORN INTO THE BRACKET OF THE RT INBD FLAP ACTUATOR. SUPPLEMENTAL INFORMATION WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
DURING A SCHEDULED INSPECTION, FOUND A DENT IN THE FUSELAGE SKIN, BETWEEN FS 378.25 & 381.25, BELOW STRINGER 12L. DENT APPROX SIZE 2.7 X 2. MAJOR REPAIR.
DURING A SCHEDULED INSPECTION, FOUND THE BELLY SKIN AT FS 225.25, BETWEEN STRINGER 16 & 15R, CRACKED APPROX .2" IN LENGTH, EVIDENCE OF CORROSION FROM STRINGER 15R GOING INBD 4 FASTENERS. MAJOR REPAIR.
MAJOR REPAIR, DURING A SCHEDULED INSPECTION, FOUND AT FS 281.00, BETWEEN STRINGERS 14L & 13L, A 3" LONG, .5" WIDE WARE IMPRESSION FROM THE HYD LINE & A SMALL PIN HOLE IN THE CTR. SUPPLEMENTAL INFORMATION WILL BE SUBMITTED UPON COMPLETION OF THE REPAIR & RETENTION OF THE PAPERWORK.
SIG EVENT, PILOT NOTED THAT THE CABIN DOOR SNUBBER DETACHED IN FLIGHT. LOCATED THE UPPER BOLT FOR THE AIRSTAIR DOOR SNUBBER ON THE FLOORBOARD. INSPECTED THREADS ON THE BOLT & RECEPTACLE, NO DEFECTS NOTED. REINSTALLED UPPER BOLT IAW AIM 12 15 0, NO FURTHER DEFECTS NOTED AT THIS TIME.
THE LT BRAKE PEDAL IS MUSHY & IT MUST BE FULLY DEPRESSED TO ACTIVATE THE BRAKES. FOUND EVIDENCE TO SUSPECT THAT THE CAPTAIN'S LT BRAKE MASTER CYLINDER, SN 4112, WAS BYPASSING INTERNALLY. THE CAPTAIN`S BRAKE MASTER CYLINDER WAS R & R IAW BMM 32-40-06. DURING TROUBLESHOOTING, FOUND THAT THE FIRST OFFICER`S RT BRAKE MASTER CYLINDER, SN 3923, WAS LEAKING. THE FIRST OFFICER`S RT MASTER CYLINDER WAS R & R IAW BMM 32-40-06.
THE CAPTAIN`S LEFT BRAKE PEDAL WENT TO THE FLOOR. FOUND THE BRAKE LINE LOOSE AT CLUSTER FITTING BETWEEN 1 & 2 BRAKE. TIGHTENED BRAKE LINE & BLED BRAKES IAW TC 1900-3240.02 STEPS 6 - 9. OPS CHECKED GOOD.
PILOT REPORTED THAT AFTER REACHING CRUISE FLT LEVEL 240, NR 2 ENGINE FAILED WITH A BANG. LOST ALL POWER, PROP AUTO FEATHERED, RAN CHECK LIST, EMERGENCY DECLARED & DIVERTED. REMOVED AND REPLACED THE ENGINE R & R RT ENG ASSEMBLY IAW TC 1900-7100.00 REV 8. OPS CHECKED GOOD.
DURING A SCHEDULED INSPECTION FOUND THE RT FUSELAGE BELLY SKIN CRACKED AT JUNCTION WITH WING SPAR AT FS 288, FWD SIDE OF WING SPAR, .9" IN LENGTH. REPAIRED IAW EO 13-1900-53-055.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK IN THE COCKPIT RT SIDEWALL LONGERON AT FS 107, .5" IN LENGTH. REPAIRED IAW EO 13-1900-53-054.
DURING A SCHEDULED ROUTINE INSPECTION FOUND A CRACK IN THE COCKPIT RT SIDEWALL FRAME AT FS 107 AT UPPER FASTENER, .5" IN LENGTH. REPAIRED IAW EO 13-1900-53-053.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND THREE CRACKS IN THE FUSELAGE FRAME AT BS 183.5, BETWEEN S2-3R AND SECOND CRACK FOUND FIVE INCHES OTBD, AND THIRD CRACK ON OTHER SIDE OF FASTENER, 1.125 INCHES IN LENGTH. REPAIRED IAW EO 13-1900-53-050.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A HOLE IN THE STRINGER ON THE VERTICAL STAB, LT SIDE AT CSS-68 AND 29.75 PERCENT CHORD, HOLE APPROX .5" IN DIAMETER. REPAIRED IAW EO 13-1900-55-019.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK IN THE RT INBD WING INBD RIB AT BL-29 AFT SIDE BY SPAR, .75 INCHE IN LENGTH. REPAIRED IAW EO 13-1900-57-014.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND TWO CRACKS IN THE A/S DOOR ANGLE AT FS 150.60 AT BOTH UPPER SNUBBER MOUNT NUTPLATES, TWO INCHES IN LENGTH. REPAIRED IAW EO 13-1900-53-051.
PILOT REPORTED THAT DURING AN OPS CHECK, FLIGHT TO TEST THE GEAR, THE GEAR FAILED TO EXTEND, 2 AMP CIRCUIT BREAKER TRIPS AT HANDLE, PUMPED GEAR DOWN MANUALLY. OPS CHECK FLIGHT UNSATISFACTORY.
PILOT REPORTED ON GEAR EXTENSION, INTRANSIT LIGHT ILLUMINATED MOMENTARILY, THEN GEAR HANDLE CIRCUIT BREAKER TRIPPED, LOST ALL GEAR INDICATIONS, FOLLOWED CHECKLIST, EXTENDED GEAR MANUALLY, THREE GREEN OBSERVED, LANDED WITHOUT FURTHER INCIDENT, EMERGENCY DECLARED. MX R & R THE LANDING GEAR SERVICE VALVE, SWUNG THE GEAR, OPS CHECKED GOOD.
PILOT REPORTED THAT THE LANDING GEAR CIRCUIT BREAKER TRIPPED IN FLT, PERFORMED MANUAL EXTENTION. COULD NOT DUPLICATE.
DURING CRUISE, LOWERED LANDING GEAR HANDLE, HEARD NOTHING, INTRANSIT LIGHT WAS ON THEN WENT OUT AFTER 60 SECONDS, NOTICED LANDING GEAR HANDLE CIRCUIT BREAKER TRIPPED, RAN CHECKLIST, NO CHANGE, PUMPED GEAR DOWN, & DIVERTED. MX REPLACED THE LANDING GEAR HANDLE, MOTOR, RELAY, AND PCB 316, OPS CHECKED GOOD.
DURING CLIMBOUT EXPERIENCED SMOKE IN THE CABIN, DECLARED AN EMERGENCY AND RETURNED TO DEPARTURE, FLAPS DID NOT EXTEND, SMOKE DISSAPATED AFTER FIVE MINUTES. R & R FLAP GEAR BOX MOTOR ASSY IAW MM 27-50-03, PN 100-524073-1. SN OFF 6245 ON 979. R & R RT INBD FLAP CABLE IAW MM 27-50-03, SN OFF 27-096, SN ON 27-267. RIGGED FLAPS IAW MM 27-50-05 OPS. CHECKED GOOD.
PILOT REPORTED THAT THE CAPT'S SIDE EMERGENCY LIGHT IS INOPERATIVE. MX REPLACED LIGHT BULBS, OPS CHECKED GOOD.
PILOT REPORTED THAT THE INSTRUMENT EMERGENCY LIGHT IS INOPERATIVE. MX REPLACED THE BULB, OPS CHECKED GOOD.
DURING A SCHEDULED ROUTINE INSPECTION FOUND TWO CRACKS ON THE LT FWD SPAR CAP ANGLE ON THE VERTICAL STAB COMING DOWN TO THE FIRST FASTENER, .375" IN LENGTH, AND A SECOND CRACK NEXT TO THE SECOND FASTENER FROM THE TOP, .5" IN LENGTH. REPAIRED IAW FR-CO-02532, REV 1, STEP 1. MAJOR REPAIR.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND CRACK ON THE RT FWD SPAR CAP ANGLE ON THE VERTICAL STAB COMING DOWN TO THE FIRST FASTENER, .375" IN LENGTH. REPAIRED IAW FR-CO-02532 REV 1, STEP 1. MAJOR REPAIR.
PILOT REPORTED THAT THE F/O EMERGENCY LIGHT BULB IS INOPERATIVE. MX REPLACED BULB, OPS CHECKED GOOD.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND TWO CRACKS IN THE FWD PRESSURE BULKHEAD ALONG THE OTBD ROW OF FASTENERS NEXT TO THE RT NOSE GEAR WEB AT FS 84.00, .375" IN LENGTH. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 12-1900-53-030. MATERIALS UTILIZED ARE INCLUDED IN THE EO. MAJOR REPAIR
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK IN THE FRAME AT FS 164 AND STRINGER 9AR AT CUTOUT, .35" IN LENGTH. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 12-1900-53-026. MAJOR REPAIR.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK ON THE FWD PRESSURE BULKHEAD ALONG ROW OR FASTENERS NEXT TO THE LT NOSE GEAR WEB, FS 84.00, 7.25" IN LENGTH. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 12-1900-53-029. MATERIALS UTILIZED ARE INCLUDED IN THE EO. MAJOR REPAIR
DURING A SCHEDULED ROUTINE INSPECTION, FOUND TWO CRACKS IN THE FUSELAGE FRAME AT FS 509 AND AFT GAS STRUT MOUNT AREA FROM CENTER OF THE UPPER INBD GAS STRUT NUTPLACE SCREW HOLES. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS I.A.W. EO 12-1900-53-027. MATERIALS UTILIZED ARE INCLUDED IN THE EO. MAJOR REPAIR
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK IN THE FRAME AT FS 150 AND STRINGER 9AL, AT NUTPLATE FOR A/S DOOR STRUT LWR MOUNT, .75" IN LENGTH. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 12-1900-53-028. MAJOR REPAIR.
DURING A SCHEDULED ROUTINE INSPECTION, FOUND A CRACK ON THE HORIZONTAL FWD SPAR WEB JUST INBD OF RT HSS 00.0, APPROX .5" IN LENGTH. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTION IAW EO 12-1900-55-004. MAJOR REPAIR.
WITH THE AUTOFEATHER SWITCH OFF, AUTOFEATHER OFF ANNUNCIATOR AND MAST CAUTION ANNUNCIATOR DO NOT ILLUMINATE. MX REPLACED THE LT UPLOCK SWITCH IAW EO 11-1900-32-002, OPS CHECKED GOOD.
PILOT REPORTED THAT THE LT PROP WON'T MANUALLY FEATHER. MX INSPECTED THE LINKAGE AND RAN ENG, NO DEFECTS NOTED.
EMERGENCY LIGHT UNDER GLARESHIELD ON CAPT SIDE INOPERATIVE FOUND DURING PREFLIGHT INSPECTION BY CREW. MX DETERMINED BULB WAS BURNED OUT AND REPLACED THE BULB.
PILOT REPORTED THAT THE EMERGENCY HANDLE AT 6C IS PUSHED IN. MX RESEATED THE EMERGENCY DOOR IAW BMM 52-20-01, OK FOR SERVICE.
PILOT REPORTED THAT THERE IS A POSSIBLE FUEL LEAK ON THE RT ENGINE NACELLE INSIDE THE WHEEL WELL. MX REPLACED THE FUEL DRAIN LINES, LEAK CHECKED GOOD.
PILOT REPORTED THAT THE EMERGENCY EXIT DOOR AT 6C HANDLE SEEMS TO BE DEPRESSED. MX REINSTALLED THE DOOR IAW BMM 52-26-00, SYS OK FOR SERVICE.
PILOT REPORTED THAT THE RT SIDE EMERGENCY DOOR HANDLE LOOKS NOT SECURED. MX RESECURED THE EMERGENCY EXIT DOOR REF 52-20-00.
DURING A SCHEDULED ROUTINE INSP MX FOUND A DENT IN THE RT WING L/E AT WS 167.24 MEASURING 7" WIDE, 3" HIGH, .5" DEEP. REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 11-1900-57-008. MATERIALS UTILIZED ARE INCLUDED IN THE EO. MAJOR REPAIR.
PILOT REPORTED THAT WHEN GEAR WAS SELECT UP, GEAR FAILED TO RETRACT, LANDING GEAR CB TRIPPED, RETURNED TO DEPARTURE. MX RESECURED A LOOSE PCB AND REPAIRED A CHAFED WIRE, OPS CHECK GOOD.
MAJOR REPAIR - DURING A SCHEDULED ROUNTINE INSP MX FOUND A .5" CRACK IN THE LT HEAVY ANGLE IN THE BEND RADIUS AT FS 303.25. MX REPAIRED THE AFFECTED AREA AND PERFORMED ALL REQUIRED RII INSPECTIONS IAW EO 10-1900-53-061. MATERIALS UTILIZED ARE INCLUDED IN THE EO.
MAJOR REPAIR - DURING A SCHEDULED ROUNTINE INSP MX FOUND THE AIRSTAIR DOOR DEBONDED AT THE HINDGE ATTACH AREA AND OUTER SKIN DEBONDED 3.5" TO 4" INWARD FROM EDGE OF DOOR. MX REPLACED THE AIRSTAIR DOOR IAW MM 52-10-03, OPS CHECK GOOD, COMPLIED WITH ALL RII REQUIREMENTS.
SUSPECTED AUTOFEATHER - PILOTS REPORTED THAT THE NR 2 ENGINE AUTOFEATHER WAS CYCLING DURING FINAL APPROACH. MX R & R THE HIGH AND LOW PRESSURE SWITCHES IAW BMM 61-21-01. MX ADDITIONALLY R & R THE AUTOFEATHER PRINTED CIRCUIT BOARD IAW BMM 20-03-00. OPS CHECK OF THE SYS WAS GOOD.
UPON CLIMBING OUT, THE PILOTS REPORTED THAT THE CAPTAINS ALTIMETER FAILED, HOWEVER, IT WAS NORMAL AFTER FIVE MINUTES. MX REMOVED AND REPLACED THE CAPTAINS ENCODING ALTIMTER IAW GMM 9.7.0, FAR 43 APPENDIX (E)AND(C)(A). MX PERFORMED PITOT STATIC CHECKS IAW BMM 24 AND TASKCARD 1900-3412-04. THE OPS AND LEAK CHECK WERE GOOD.
AT 1000FT WITH TORQUE AT 1000'S PROP AT 1550 THE LT ENGINE JUMPED SEVERAL TIMES FROM 50 TO 2000 POUNDS OF TORQUE. MAINTENANCE PERFORMED ENGINE RUNS AND FOUND NO TORQUE SURGE PER BEECH MM 76-10-00. UPON FURTHER INVESTIGATION MAINTENANCE DISCOVERED THE COWLING SAFETY WIRING WAS BROKEN AND THE COWL HAD RUBBED/ HIT THE PROP GOVERNOR. WHICH CAUSED AN ERRONEOUS READING. COWL WAS INSTALLED AND ENGINE PARAMETERS WERE NORMAL UPON ENGINE RUNS.
SMOKE SMELL - FLIGHT NR 7195 - UPON DEPARTURE FROM MKE IN FLIGHT - PILOTS REPORTED SPARKS NEAR THE BOTTOM OF THE RT CORNER OF THE FIRST OFFICERS WINDSHIELD INSIDE OF COCKPIT AND SMELLED A SLIGHT BURNING SCENT. MX REMOVED PAPER CLIP FROM FIRST OFFICERS WINDSHIELD TERMINAL LUGS. INSPECTED TERMINAL LUG AND SURROUNDING WINDSHIELD AREA. NO DEFECTS NOTED. FIRST OFFICERS WINDSHIELD OPS CHECKED GOOD IAW BMM 56-10-00-201.
STRINGER 9L DISBONDED AT FS 243.25 TO FS 258.25. MAINT REPAIRED DISBONDED STRINGER 9L AT FS 243.25 TO FS 258.25 IAW SRM 53-90. REPAIR APPROX 10.5 INCH. 2024 T3. RII INSP C/W IAW TASKCARD 8.2.1.
FUSELAGE SKIN CRACK IN/AT PREVIOUS REPAIR CRACK APPROX 1 INCH LENGTH AT FS 248.0 ABOVE STR 9L. MAINT REPAIRED FUSELAGE SKIN AT FS 248.0 IAW SRM 51-70. REPAIR DIMENSIONS APPROXIMATELY 14 FT BY 12.5 FT, 2024 T3 .040. RII INSP C/W IAW TASKCARD 8.2.1.
02/18/08, FRAME CRACKED AT STR 9R CUTOUT. CRACK APPROX .500 IN LENGTH AT FS 177.35. MAINT REPAIRED FRAME CRACK AT STR RELIEF HOLE AT FS 177.35 AND STR 9R IAW SRM 51-70. REPAIR APPROX 5 INCH X 2.5 INCH 2024 T-3 .071. RII INSP C/W IAW TASKCARD 8.2.1.
RT WING TO FUSELAGE HEAVY ANGLE CRACKED APPROX 2.125 INCH AT FWD BEND RADIUS AT FS 288.0. MAINT REPAIRED THE LT TO FUSELAGE HEAVY ANGLE IAW SRM 53-90. REPAIR APPROX 13.5 INCH. RII INSP COMPLIED WITH IAW TASKCARD 8.2.1.
LT WING TO FUSELAGE HEAVY ANGLE CRACKED APPROX 1.750 AT FWD BEND RADIUS AT FS 288.0. MAINT REPAIRED THE LT TO FUSELAGE HEAVY ANGLE IAW. SRM 53-90. REPAIR APPROX 13.5 INCH. RII INSP COMPLIED IAW TASKCARD 8.2.1.
EES SYSTEM - PILOTS REPORTED DIFFICULTY WITH THE AIRSTAIR DOOR NOT LOCKING PROPERLY. MAINTENANCE DISCOVERED THE DOOR CABLE WAS BROKEN ON THE INSIDE. MAINTENANCE REMOVED AND REPLACED THE AIRSTAIR DOOR CABLE IAW MM 52-10. OPERATIONAL CHECK GOOD. RII INSPECTION COMPLIED IAW TASKCARD 8.2.1.
DURING ROUTINE INSPECTION, EMERGENCY EXIT 4C WINDOW PAN FOUND CRACKED AT RADIUS. REPLACED WINDOW PAN IAW EO. AIRCRAFT RETURNED TO SERVICE.
DURING ROUTINE INSPECTION, BULKHEAD AT FRAME STATION 492.75 FOUND TO BE CRACKED WHERE IT ATTACHES TO TOP OF CARGO DOOR FRAME. REPAIRED IAW EO. AIRCRAFT RETURNED TO SERVICE.
DURING ROUTINE INSPECTION, CORROSION DISCOVERED AROUND AIRSTAIR DOOR HANDLE APPROX 2 INCH IN DIA AREA REPAIRED IAW EO. AIRCRAFT RETURNED TO SERVICE.
DURING ROUTINE INSPECTION, FOUND WEB CRACK ON FRAME FS 466.0 STRINGER 10R. REPAIRED CRACK IAW WITH EO. AIRCRAFT RETURNED TO SERVICE.
RT NACELLE POWER CABLE OPENING AT WHEEL WELL IS DAMAGED, REPAIRED.
RT ITT INDICATOR NOT WORKING, REMOVED AND REPLACED INDICATOR.
RADAR WILL NOT PAINT, R & R WX RADAR OPS CHECK GOOD.
RIGHT FUEL LOW PRESS LIGHT ILLUM. REMOVED AND REPLACED LP FUEL PUMP, OPS CHECK GOOD.
RT FUEL INDICATOR READS ZERO. REMOVED AND REPLACED RT FUEL FLOW TRANSMITTER CONNECTOR, OPS CHECK GOOD.
RT PITOT HEAT ANNUNCIATOR ILLUMINATED IN FLIGHT, OPS CHECK GOOD
LANDING GEAR LIGHT RIGHT SIDE WILL NOT ILLUMINATE, REPLACED BULB
DUAL ENVIRO FAIL ON TAKEOFF ROLL, PERFORMED GROUND RUNS AND P-TEST AND OPS CHECK GOOD.
CABIN DOOR SEAL LEAKING, REPLACED SEAL OPS CHECKED SATISFACTORY
DUAL ENVIRONMENTAL FAILURE ON CLIMBOUT. REPLACED PRSOV VALVE.
#2 ENCODER REPORTED HIGH BY ATC, REPLACED ENCODING ALTIMETER OPS CHECKED SYSTEM SATISFACTORY
ALTIMETER SPLIT. COULD NOT DUPLICATE, OPS CHECKED SATISFACTORY.
ELT WOULD NOT SILENCE. REPLACE ELT, OPS CHECKED SYSTEM SATISFACTORY.
LANDING GEAR INTRANSIT LIGHT FAILED TO EXTINGUISH, CYCLED GEAR AGAIN LIGHT REMAINED ON FOR APPROX 1 MINUTE. INSPECTED GEAR INDICATION SYSTEM AND PERFORMED TEST FLIGHT. COULD NOT DUPLICATE PROBLEM.
RIGHT ENVIROMENTAL FAIL ON T/O ROLL. INSPECTED, COULD NOT DUPLICATE.
PILOT WRITE-UP WAS ''HDG WON''T MOVE WITH AIRCRAFT MOVEMENT''. THIS GYRO IS LOCKED UP. (X)
CAPTAIN'S ALTIMETER READS 80 FEET - 100 FEET HIGH AT ALL ALTITUDES AND ENCODER TRANSITION POINTS ARE OUT OF TOLERANCE. REMOVED AND REPLACED ALTIMETER. BENCH TEST VERIFIED ALTIMETER TO BE INDICATING 80 FEET HIGH AT 1,500 FEET AND 110 FEET HIGH AT 10,000 FEET. COMP P/N KEA-346/066-03062-00. (X)
KOLLSMAN KNOB FOUND BINDING WHEN REMOVED FROM STOCK. RETURNED.