N244CA

Part: SWITCH — MELTED · airframe 2,866 hrs · 2,926 cycles

PILOT REPORTED #2 PITOT HEAT INOP. MAINTENANCE INSPECTED AND FOUND THE RIGHT PITOT SWITCH AND CONNECTOR MELTED. BOTH THE SWITCH AND THE SWITCH CONNECTOR WERE REPLACED WITH NO FURTHER DEFECTS. PART NUMBERS REPLACED WERE 30-16-0687001 AND 16-705-103-13.

Part: FASTENER — SHEARED (FUSELAGE) · airframe 292 hrs

THE NLG ATTACH STRUCTURE WAS FOUND TO BE DAMAGED DURING AN INSPECTION FOR A NOISE HEARD DURING TOW OPERATIONS. THE DAMAGE IS LOCATED AT FWD MOST FUSELAGE BULKHEAD, LWR CENTER SECTION, IN THE AREA CORRESPONDING TO THE NLG MOUNTS. THE LT AND RT VERTICAL STIFFENERS (PART NUMBER 212-53-11-0402-1L AND -1R) LWR 4 RIVETS ARE SHEARED AND PULLING AWAY FROM BULKHEAD. THE BULKHEAD IS CRACKED IN THESE AREAS APPROXIMATELY 1.25" EACH SIDE. THE STRUCTURE AFT OF NLG BULKHEAD WAS INSPECTED WITH THE FOLLOWING DEFECTS NOTED: 1) RIVET ROW AT FWD EDGE OF BAGGAGE COMPARTMENT FLOOR (RUNNING LT TO RT) SHEARED FASTENERS AND DISTORTION. 2) THE FWD SECTIONS OF FLOORBOARD SUPPORTS AS THEY ARE RIVETED TO FORWARD-MOST FUSELAGE BULKHEAD SHEARED FASTENERS, DAMAGED, CRACKED, AND DISTORTED. THE OEM HAS BEEN NOTIFIED AND A FLEETWIDE INSPECTION HAS BEEN ISSUED FOR ALL COMPANY AIRCRAFT. THE ROOT CAUSE OF THIS ISSUE IS UNKNOWN AT THIS TIME. AN ATTACHMENT ILLUSTRATING THIS ISSUE WILL BE SUBMITTED AS A SUPPLEMENT TO THIS SDR.

Part: ACTUATOR — FAULTY (ELEVATOR TRIM) · airframe 210 hrs

DURING A FUNCTIONAL CHECK FLIGHT FOR AN UNRELATED ITEM AND WHILE PERFORMING MANEUVERS INCLUDING 30 DEGREE TURNS IN CLIMB AND DESCENT, THE ELEVATOR TRIM POSITION MOVES INDEPENDENTLY WITHOUT INPUT FROM CREW; TENDS TO MOVE 3/4 TO FULL NOSE DOWN POSITION. THE AIRCRAFT WAS CONTROLLABLE AND LANDED SAFELY. THE AIRFRAME OEM INSTRUCTED THE REPLACEMENT OF ELEVATOR TRIM ACTUATOR WITH IMPROVED VERSION REPORTED IN TECNAM SB-372-CS DATED 03/10/2020.

Part: SKIN — DENTED (BS 6462.6-6653)

DURING 1C INSPECTION, FOUND SMALL DENT IN FUSELAGE SKIN BETWEEN FS 6462.6 AND 6653.1 AND BETWEEN STRINGERS 19L AND 18L. REPAIRED DAMAGED AREA IAW EMB 120 SRM 53-00-01 PG 202-204.

Part: PLATE — DENTED (LT NACELLE)

DURING ENGINE REPLACEMENT, THE LEFT NACELLE CENTER PLATE SECTION WAS FOUND TO HAVE A DENT AND CHAFING DAMAGE ON THE AFT OUTBOARD SIDE. BOTH THE DENT AND CHAFING DAMAGE WERE REPAIRED PER AERODESIGN REPORT NR 3133-1, REV IR, 2-12-99.

Part: LENS — MISSING (ROW 5)

EMERGENCY EXIT LIGHT COVER IS MISSING AT ROW 5. REPLACED LIGHT COVER.

Part: VALVE — MALFUNCTIONED (RT ENGINE)

AIR CONDITIONING SYSTEM EMITS SMOKE. COULD NOT DUPLICATE DISCREPANCY. REPLACED THE RIGHT HAND ENGINE P2.5/3 SWITCHING VALVE FOR TROUBLESHOOTING.

Part: BULB — FAILED (ROW 5)

EMERGENCY FLOOR LIGHT AT ROW 5 INOPERABLE. REMOVED AND REPLACED BULB.

Part: ROLLER — WORN (LT TE FLAP)

FLAPS WOULD NOT RETRACT AFTER TAKEOFF. REPLACED FLAP ROLLERS AT LEFT HAND OUTBOARD FLAP.

Part: SENSOR — MALFUNCTIONED (NLG)

WHEN LANDING GEAR RETRACTED, THE NLG DOWN LIGHTS AND INTRANSIT LIGHTS REMAINED ON. REPLACED THE NLG DOWN LOCK PROXIMITY SENSOR.

Part: INTRANSIT LIGHT — ILLUMINATED (LT MLG)

LEFT HAND MLG INTRANSIT LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. ENTERED DISCREPANCY IN DEFERRED MAINTENANCE LOG PER MEL.

Part: SILL — CORRODED (CARGO COMPT)

DURING 2C INSPECTION TASK 161/162-01Z, FOUND RIGHT CARGO FORWARD FLOOR SILL CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: SILL — CORRODED (EMERGENCY EXIT)

DURING 2C INSPECTION TASK 151/152-01Z, FOUND AFT EMERGENCY EXIT SILL AND PIN RECEPTACLES CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PARTS AND INSTALLED SERV PARTS IAW EMB-120 SRM, CHAPTER 51.

Part: STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/01I, FOUND FIRST LEFT HAND BUTT STRAP CORRODED BEYOND EMB-LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132-01I, FOUND FLOOR SUPPORT-T AT FRAME 20R CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: SILL — CORRODED (CABIN DOOR)

DURING 2C INSPECTION TASK 5310-131/132 01I, FOUND FIRST LEFT FLOOR SILL CORRODED BYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132 01I, FOUND FIRST RIGHT BUTT STRAP CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM CHAPTER 51.

Part: SILL — CORRODED (CABIN)

DURING 2C INSPECTION TASK 5310-131/132 O1I, FOUND FIRST RIGHT FLOOR SILL CORRODED BYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: SUPPORT — CORRODED (CABIN)

DURING 2C INSPECTION TASK 5310-131/132 01I, FOUND FLOOR SUPPORT-T AT FRAME 16R CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: SUPPORT — CORRODED (CABIN)

DURING 2C INSPECTION TASK 5310-131/132 01I, FOUND FLOOR SUPPORT-T AT FRAME 16L CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM CHAPTER 51.

Part: SUPPORT — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132 01I, FOUND FLOOR SUPPORT-T AT FRAME 20L CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM, CHAPTER 51.

Part: STRAP — CORRODED (FUSELAGE)

DURING 2C INSPECTION TASK 5310-131/132 O1I, FOUND FIRST CENTER BUTT STRAP CORRODED BEYOND EMB LIMITS. REMOVED DAMAGED PART AND INSTALLED SERV PART IAW EMB-120 SRM CHAPTER 51.

Part: CONTROL BOX — FAILED (INST PANEL)

LEFT HAND MLG UNSAFE INDICATION DURING TAKEOFF. REPLACED THE LANDING GEAR CONTROL BOX.

Part: REGULATOR VALVE — FAILED (RT WING)

RT BLEED AIR DUCT LEAK WARNING ON. FOUND THE DRAIN CUP ON THE DE-ICE PRESSURE REGULATOR HAD FALLEN OFF. THIS ITEM IS RETAINED BY A WORN CLAMP. REINSTALLED DRAIN CUP.

Part: GEAR CONTROL — FAILED (INSTR PANEL)

LANDING GEAR CONTROL WAS CYCLED 3 TIMES BEFORE GEAR RESPONDED. REPLACED THE LANDING GEAR CONTROL.

Part: TQ SIGNAL COND — MALFUNCTION (RT ENGINE)

AUTO FEATHER AURAL WARNING SOUNDED DURING TAKEOFF ROLL. REPLACED THE RIGHT ENGINE TORQUE SIGNAL CONDITIONER.

Part: BULB — FAILED (LANDING GEAR)

RIGHT GEAR INDICATED UP ATER PLACING GEAR HANDLE DOWN. USED ELECTRICAL OVERRIDE, GEAR CONFIRMED DOWN, APPEARS TO BE AN INDICATION PROBLEM. REMOVED AND REPLACED ALL LANDING GEAR INDICATOR DOWN BULBS. PERFORMED SEVERAL GEAR SWINGS, NO DEFECTS NOTED.

Part: LOCKWASHER — WORN (LT MLG)

DURING E-5 INSPECTION, FOUND LEFT MAIN GEAR OUTBOARD TRUNNION BEARING NUT TO BE LOOSE. REMOVED NUT AND FOUND LOCKWASHER INNER TAB TO BE SHEARED OFF. ALSO, NOTICED THAT LOCK WASHER WAS OUT OF ROUND AND APPEARED TO BE STRETCHTED IN AREA OF INNER TAB. REPLACED LOCKWASHER WITH SERVICEABLE PART AND RETORQUED NUT.

Part: ROLLER — DIRTY (TE FLAPS)

FLAP DISAGREE WARNING AFTER TAKEOFF. REPLACED THE FLAP ROLLERS.

Part: PITCHLOCK SCREW — BENT (FEATHER STOP TAB)

ACTUATOR ASSEMBLY REMOVED FROM AIRCRAFT DUE TO FEATHER STOP TAB BEING FOUND DISPLACED. AIRCRAFT BROUGHT IN FOR SCHEDULED MAINTENANCE. UPON INITIAL RECEIVING INSPECTION THE FEATHER STOP TAB S/N S0561 WAS FOUND TO BE BENT APPROXIMATELY 0.125 INCH. PITCHLOCK SCREW WAS REMOVED FROM ASSEMBLY AND RETURNED TO MANUFACTURER. PART TOTAL CYCLES, 11,912.

Part: APU — MALFUNCTIONED (APU COMPT)

AUXILIARY POWER UNIT START CYCLE HUNG AT 45 DEGREES, START CYCLE WAS ABORTED, DISCHARGED AUXILIARY POWER UNIT FIRE EXTINGUISHER AFTER REPORT OF FIRE. INSPECTED AUXILIARY POWER UNIT AND COMPARTMENT, NO DEFECTS NOTED. DEFERRED AUXILIARY POWER UNIT AND AUXILIARY FIRE EXTINGUISHER.

Part: TRACKS — DIRTY (TE FLAPS)

FLAP DISAGREEMENT AFTER TAKEOFF. CLEANED AND INSPECTED FLAP TRACKS AND ROLLERS, OPERATIONAL CHECK GOOD.

Part: BUSHING — FAILED (RUDDER PEDALS)

WHEN CAPTAIN'S FEET CONTACT RUDDER PEDALS, PEDAL ADJUSTMENT WILL NOT HOLD. REPLACED BUSHING IN PEDAL ADJUSTMENT ASSEMBLY.

Part: PITCHLOCK SCREW — MALFUNCTIONED (PROP ASSY)

PROPELLER ASSEMBLY REMOVED FROM AIRCRAFT FOR BLADE AND HUB MAJOR INSPECTION. UPON INITIAL RECEIVING INSPECTION, THE FEATHER STOP TABS S/N S0455 WERE FOUND DISPLACED APPROXIMATELY 0.125 INCH. PITCHLOCK SCREW WAS REMOVED FROM ASSEMBLY AND RETURNED TO MANUFACTURER. PART TOTAL CYCLES, 15,648.

Part: EEC — OUT OF ADJUST (NR 1 ENGINE)

ON INITIAL CLIMBOUT, THE NR 1 ENGINE TORQUE FLUCTUATED FROM 92 PERCENT TO 100 PERCENT. WHEN POWER WAS REDUCED THE FLUCTUATION WAS FROM 72 PERCENT TO 90 PERCENT, OPERATION BECAME NORMAL SHORTLY. TRANSFERRED TO DEFERRED LIST CAT C, MEL 73-21-1, EXPIRES 11-29-96. BOTH EEC TURNED TO MANUAL.

Part: INDICATION — MALFUNCTIONED (LANG ING GEAR)

WHEN LANDING GEAR SELECTED TO RETRACT, BOTH THE GREEN DOWN AND RED INTRANSIT LIGHTS WERE ON. COULD NOT DUPLICATE DISCREPANCY. OPERATIONAL AND FUNCTIONAL CHECKS OF LANDING GEAR RETRACTION SYSTEM WERE NORMAL.

Part: CONTROL UNIT — MALFUNCTION (TE FLAPS)

FLAP CONTROL FAULT WARNING DURING TAKEOFF. REPLACED FLAP CONTROL BOX.

Part: TCAS — MALFUNCTION (AVIONICS)

PILOT'S RED HEADING FLAG LIGHT ON ALONG WITH FAILURE OF TCAS. REPLACED THE AHC-85. PART TOTAL CYCLES, 13,044.

Part: RADAR — MALFUNCTIONED (COCKPIT)

RADAR DISPLAY IS ERRATIC AND ERRONEOUS. PLACED WEATHER RADAR SYSTEM ON DEFERRED MAINTENANCE LIST. ACFT RETURNED TO SERVICE.

Part: DOOR LATCH — BROKEN (RT MLG)

RIGHT MLG OUTBOARD DOOR HANGING OPEN AND WILL NOT CLOSE. REPLACED BROKEN LATCH ASSY.

Part: RETRACT MECH — MALFUNCTIONED (LANDING GEAR)

LANDING GEAR WILL NOT RETRACT. ALL GREEN DOWN INDICATORS AND ALL RED INTRANSIT INDICATORS ARE ILLUMINATED. REVERSED THE NLG UPLOCK PROXIMITY SENSORS AND DEFERRED SYSTEM PER EMB SNL 032-0015.

Part: LINE — CHAFED (LT NACELLE)

HYDRAULIC FLUID DRIPPING FROM LEFT ENGINE NACELLE. REPAIRED CHAFED HYDRAULIC PRESSURE LINE UNDER ENGINE FIRE DECK.

Part: LEAK SENSOR — DEFECTIVE (LT DUCT)

LEFT DUCT LEAK WARNING ACTIVATED DURING FLIGHT. REPLACED DUCT LEAK SENSOR IN LT WING ROOT.

Part: DOOR SEAL — LOOSE (CARGO COMPT)

CABIN PRESSURIZATION FAILED DURING FLIGHT. REPLACED CARGO DOOR SEAL WHICH HAD COME LOOSE.

Part: WHEEL — DAMAGED (RT MLG)

MECHANIC REMOVED TIRE FROM A/C DUE TO TIRE WORN TO LIMITS. DURING INSPECTION IN WHEEL SHOP, FOUND DAMAGE TO SUB ASSY AND KEY INSERTS ANTICIPATE BRAKE FAILURE. SUB ASSY HAS BEEN REMOVED FROM SERVICE AND SENT TO BFG FOR FURTHER INSPECTION AND EVALUATION.

Part: CONTROLLER — DEFECTIVE (CABIN)

AFTER TAKEOFF, CABIN PRESSURE WAS RISING OUT OF CONTROL, SWITCHED TO MANUAL CONTROL WITH SAME RESULTS. AIRCRAFT RETURNED TO BHM. REPLACED THE ELECTRONIC PRESSURE CONTROLLER.

Part: HMU — DEFECTIVE (LT ENGINE)

LEFT ENGINE STARTS, BUT WILL NOT ACCELERATE BEYOND MIN FLOW. REPLACED THE ENGINE HMU.

Part: LEAD — BROKEN (RT PROP)

RT PROPELLER ANTI-ICE IS INOP. REPLACED BROKEN DE-ICE LEAD.

Part: SENSOR — DEFECTIVE (LT MLG)

LANDING GEAR CONTROL COULD NOT BE SELECTED TO UP UNTIL OVERRIDE RELEASE WAS USED. REPLACED THE LEFT MLG WEIGHT ON WHEELS PROXIMITY SENSOR.

Part: ROLLERS — WORN (LT TE FLAP)

FLAP DISAGREEMENT WARNING, WHEN FLAPS SELECTED UP AFTER TAKEOFF. REPLACED THE LEFT OUTBD FLAP ROLLERS.