N732KA
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
IN CRUISE FLIGHT THE LEFT ENGINE SURGED REPEATEDLY. THE ENGINE STOPPED SURGING WHEN AT FLIGHT IDLE. AIRCRAFT LANDED WITH THE LEFT ENGINE AT IDLE POWER.
CORROSION FOUND ON THE UPPER SURFACE OF THE UPPER CHORD OF THE FLOORBOARD FLOOR SUPPORT @STATION 360, RBL 5 TO RBL 66.
CORROSION FOUND ON THE L1 DOOR LOWER SILL WEB (MOP SILL) AND C CHANNEL.
CORROSION FOUND ON THE AFT LAVATORY INBOARD SUPPORT FITTING. STATION 947, LBL 25, WL208.
CORROSION FOUND ON THE UPPER SURFACE OF THE UPPER CHORD OF THE FLOORBOARD FLOOR SUPPORT @STATION 986.5, LBL 25 TO RBL 24.
CORROSION FOUND ON THE L2 DOOR LOWER SILL INNER CHORD (MOP SILL) AND WEB.
CORROSION FOUND ON THE UPPER SURFACE OF THE UPPER CHORD OF THE FLOORBOARD FLOOR SUPPORT @ STATION 312, RBL 8, WL208.
CORROSION FOUND ON THE UPPER SURFACE OF THE UPPER CHORD OF THE FLOORBOARD FLOOR SUPPORT @ STATION 344, LBL 66 TO RBL 10.
CORROSION FOUND ON THE FORWARD CARGO SIDE PLATE (Z CHANNEL) AT RBL 21.8 BETWEEN BS 482 AND BS 482A.
CORROSION FOUND ON THE UPPER SURFACE OF THE LEFT AND RIGHT WINGS ALONG STRINGER HI-LOK ROWS. LEFT WING LOCATION STRINGERS S-11 AND S-12 FROM APPROX WBL 183.4 TO WSTA 479. RIGHT WING LOCATION STRINGERS S-10, S-11 AND S-12 FROM APPROX WBL 70.85 TO WSTA 505.00. BOEING ENGINEERING CONTACTED FOR REPAIRS.
ENGINE BLEED AIR 5TH STAGE CHECK VALVES ON BOTH ENGINES INSPECTED FOR EMERGENCY AD 2020-16-51. BOTH CHECK VALVES SHOW SIGNS OF CORRODED FLAPPER PLATES, BUSHINGS AND WILL BE REPLACED.
CORROSION FOUND ON THE BOTTOM FRAME ON THE RIGHT OVERWING ESCAPE HATCH. MATERIAL THICKNESS REMAINING AFTER CORROSION REMOVAL FROM THE DOOR NOT WITHIN THE LIMITS OF SRM 52-20-02. REPLACED THE RIGHT OVERWING ESCAPE HATCH.
CORROSION FOUND ON THE BOTTOM FRAME ON THE LEFT OVERWING ESCAPE HATCH. MATERIAL THICKNESS REMAINING AFTER CORROSION REMOVAL FROM THE DOOR NOT WITHIN THE LIMITS OF SRM 52-20-02. REPLACED THE LEFT OVERWING ESCAPE HATCH.
LEFT CENTER FUEL TANK BOOST PUMP LOW PRESSURE LIGHT CAME ON. RESET SWITCH AND WORKED INTERMITTENTLY. REPLACED LEFT CENTER FUEL TANK BOOST PUMP AND OPERATIONAL CHECK NORMAL.
APU GENERATOR WOULD NOT COME ONLINE WHEN SELECTED ON AFTER APU START. REPLACED APU GENERATOR AND OPERATIONAL CHECKED NORMAL.
INTERMITTENT LEFT DUCT OVERHEAT LIGHT ON WITH NORMAL DUCT TEMPERATURE INDICATION. DETERMINED TO BE AN INDICATION PROBLEM. REPLACED THE 190 DEGREE AND 250 DEGREE SWITCHES IN THE AIR CONDITIONING DUCT/PLENUM. OPERATIONAL CHECK NORMAL.
APU SHUTDOWN AFTER AN HOUR OF RUN TIME ON THE GROUND. PUT A PRESSURE GAUGE IN THE FUEL LINE BETWEEN THE FUEL CONTROL AND FUEL ATOMIZER. FOUND FUEL PRESSURE AT 25 PSI WITH A REQUIREMENT FOR 50-60 PSI. REMOVED FUEL CONTROL UNIT AND FOUND DRIVE SHAFT SHEARED. REPLACED THE FUEL CONTROL UNIT AND OPERATIONAL CHECK NORMAL.
APU DRAGS DOWN DURING MAIN ENGINE START. REPLACED APU PROPORTIONAL CONTROL VALVE. ENGINE START AND APU OPERATIONAL CHECKS NORMAL.
DUCT PNEUMATIC PRESSURE DURING CRUISE WAS 40 PSI BUT VERY LOW FLOW IN CABIN. FOUND LEFT 35 DEG SENSOR FAULTY. REPLACED THE SENSOR AND OPS CHECKED OK.
UNSTABLE CABIN PRESSURIZATION. PERFORMED FUNCTIONAL CHECK OF CABIN PRESSURIZATION CONTROLLER WITH NO FAULTS FOUND. FOUND RESIDUAL PRESSURE IN THE BLEED AIR MANIFOLD WITH APU NOT RUNNING. REPLACED THE APU LOAD CONTROL VALVE.
START VALVE ON RIGHT ENGINE WAS INTERMITTENT OR SLOW TO OPEN WHEN START WAS INITIATED. REPLACED START VALVE AND OPERATIONAL CHECK NORMAL.
DURING AIR CONDITIONING PACK OPERATION ON THE GROUND, LEFT AIR CONDITIONING PACK INDICATED A PACK TRIP AND DUCT OVERHEAT AT PACK START UP. INDICATION FOR THE DUCT TEMPERATURE DID NOT SHOW A DUCT OVERHEAT. DETERMINED THIS TO BE AN INDICATION PROBLEM USING THE FIM. REPLACED THE AIR CONDITIONING ACCESSORY UNIT AND OPERATIONAL CHECK WAS NORMAL.
LEVEL 3 CORROSION FOUND ON THE UPPER SURFACES OF THE LEFT AND RIGHT WING UNDER THE EMERGENCY EXIT WING WALK PAINT. RIGHT WING UPPER SURFACE LOCATIONS STRINGERS 2,3,4,5,7,8 AND REAR SPAR AT APPROX WBL 71.24-92.5. LEFT WING UPPER SURFACE LOCATIONS STRINGERS 1,4,5,9 AND REAR SPAR AT APPROX WBL 71.24-92.5 AND 165-235. CORROSION DEPTH IS GREATER THAN THE SRM LIMITS AND REQUIRES ENGINEERING FOR REPAIRS.
THE STANDBY ALT SELECT KNOB ON THE PRESSURIZATION PANEL WAS FOUND TO BE INTERMITTENTLY SLIPPING INTERNALLY WHEN ATTEMPTING TO MAKE NUMBER CHANGES. REPLACED THE PANEL AND OPERATIONAL CHECK NORMAL.
PERFORMED AN OIL QUANTITY INSPECTION ON THE LEFT PACK AIR CYCLE MACHINE. FOUND THE OIL LEVEL BELOW LIMITS IN THE SIGHT GLASS AND SIGNS OF FLUID LEAKAGE FROM THE AIR CYCLE MACHINE. REPLACED THE LEFT PACK AIR CYCLE MACHINE.
PERFORMED ENGINE STARTER CHIP DETECTOR INSPECTION. FOUND EXCESSIVE METAL PARTICLES ATTACHED TO THE CHIP DETECTOR. REPLACED ENGINE STARTER.
RIGHT ENGINE HYDRAULIC PUMP FOUND LEAKING HYDRAULIC FLUID FROM SHAFT SEAL DRAIN. REPLACED PUMP AND OPERATIONAL CHECKED NORMAL.
AMBER "L ELEV PITOT" LIGHT ILLUMINATED. THIS LIGHT INDICATES A PROBLEM WITH THE ELEVATOR FEEL PITOT PROBE HEATER. REMOVED PROBE AND FOUND INTERNAL HEATER FAILED. REPLACED PITOT PROBE AND OPERATIONAL CHECK NORMAL.
NOSE LANDING GEAR RETRACT ACTUATOR FOUND LEAKING HYDRAULIC FLUID. REPLACED ACTUATOR AND OPERATIONAL & LEAK CHECKED OK.
LEFT DUCT OVERHEAT LIGHT ON, IAW THE FIM REPLACED THE CABIN TEMPERATURE CONTROLLER.
DURING AIR CONDITIONING OPERATIONAL CHECKS, LT MIXING VALVE WAS FOUND TO BE STICKING AND INTERMITTENT. REPLACED MIXING VALVE.
LEFT DUCT OVERHEAT LIGHT ON, IAW FIM REPLACED AIR CONDITIONING ACCESSORY UNIT.
RIGHT WING FUEL QUANTITY INDICATOR INTERMITTENTLY DISPLAYED "0" WITH CODES 1, 2, 3, 5, 7, 10. IAW TROUBLESHOOTING WITH THE FAULT ISOLATION MANUAL, REPLACED THE RIGHT FUEL QUANTITY INDICATOR AND DIGITAL CALIBRATION TRIM UNIT ATTACHED TO THE INDICATOR. PERFORMED OPERATIONAL CHECKS WITH NO DEFECTS NOTED.
DIGITAL FLIGHT DATA ACQUISITION UNIT CIRCUIT BREAKER POPPED AND WOULD NOT RESET. REPLACED DFDAU AND OPERATIONAL CHECK NORMAL.
APU WOULD HANG AT 250-300 DEGREES FOR APPROXIMATELY 30 SECONDS DURING START AND THEN ACCELERATE. APU WAS MAKING CHUGGING EXHAUST NOISES WHEN RUNNING. SB GTCP85-49-7484 INCORPORATES A NEW FUEL CONTROL, PN 3617750-1 AND ATOMIZER/LINER ASSEMBLY TO IMPROVE START TIMES. REPLACED THE FUEL CONTROL AND ATOMIZER/LINER ASSEMBLY IAW THE SB AND AMM. APU STARTS MUCH QUICKER NOW AND NO LONGER MAKES CHUGGING NOISES WHEN OPERATING.
FOUND PROPORTIONAL CONTROL VALVE BODY LOOSE. VALVE IS LOCATED ON LOWER SIDE OF THE APU. REPLACED VALVE AND OPERATIONAL CHECK NORMAL.
APU WOULD HANG AT 250-300 DEGREES FOR APPROXIMATELY 30 SECONDS DURING START AND THEN ACCELERATE. APU WAS MAKING CHUGGING EXHAUST NOISES WHEN RUNNING. SB GTCP85-49-7484 INCORPORATES A NEW FUEL CONTROL AND ATOMIZER/ LINER ASSEMBLY, PN 3604524-54 TO IMPROVE START TIMES. REPLACED FUEL CONTROL AND ATOMIZER/LINER ASSEMBLY IAW THE SB AND AMM. APU STARTS MUCH QUICKER NOW AND NO LONGER MAKES CHUGGING NOISES WHEN OPERATING.
OBSERVER SEAT HAND MIKE HAD NO AUDIO. REPLACED THE REMOTE ELECTRONICS UNIT. OPERATIONAL CHECKED NORMAL.
LEFT ENG FUEL FLOW WAS INTERMITTENTLY DISPLAYED ON THE EIS PRIMARY DISPLAY. TROUBLESHOOTING OF THE FUEL FLOW TRANSMITTER & ASSOCIATED WIRING FOUND NO DEFECTS. THE EIS PRIMARY DISPLAY WAS REPLACED & FUEL FLOW INDICATION IS NORMAL.
REPLACED CARBON SEALS FOR THE RT ENG HYD PUMP, CSD & MEC TO IMPROVE ENG OIL CONSUMPTION.
VMU FLAG APPEARED ON CAPTAIN'S ASI & BARBER POLE DID NOT MATCH FIRST OFFICERS SIDE. REPLACED DEFECTIVE AIRSPEED INDICATOR. OPERATIONAL CHECKED NORMAL.
EXCESSIVE OIL LEAK FROM NR 2 ENGINE. BAGGED ACCESSORY GEARBOX PAD SEAL DRAINS AND OPERATED ENGINE. FOUND STARTER PAD SEAL DRAIN LEAKING. REPLACED CARBON SEAL AND OPERATIONAL CHECK NORMAL.
ON APPROACH, THE FIRST OFFICERS AIRSPEED INDICATOR & ALTIMETER FAILED WITH ALL FLAGS SHOWN. DURING TROUBLESHOOTING THE AIR DATA COMPUTER WOULD NOT TEST. THE AIR DATA COMPUTER WAS REPLACED. LEAK & OPERATIONAL CHECKS WERE ACCOMPLISHED WITH NO WARNING INDICATIONS SHOWN.