N831LF
Registered owner: INHS LEASING CO LLC, OR (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| LIFE FLIGHT NETWORK LLC (8LFA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
ON TAKEOFF ROLL WITH TAKEOFF THRUST LEFT ENGINE EGT TEMP RAPIDLY INCREASING TO 600 DEGREES WITH 1.45 EPR MASTER CAUTION ILLUMINATED. MTX REMOVED AND REPLACED THE LT ENGINE PRBC VALVE, OP CHECKED NORMAL IAW MM REF 71-00-00.
CAPTAIN REPORTED, DURING FLIGHT, THE F/O RMI CHANGED HEADING, BEING NECESSARY TO ADJUST CONTINUOUSLY. DURING REVISION, DETECTED A DIFFERENCE OF 20 GRADES BETWEEN COURSES. THE LT FLUX VALVE NR 1 WAS REPLACED IAW MM, SYNCHRONY TEST WAS PERFORMED IAW MM, BEING SATISFACTORY. DURING TOWING, THE LT EHSI INFORMATION GOT LOST, RMI FLAG TURNED ON. AC WAS SENT TO HANGAR, COMPASS SYS NR 1 WAS VERIFIED, DETECTING THAT FLUX TOOK TOO MUCH TIME TO COMPENSATE, REPLACED IAW MM 34-21-06, OPERATING CORRECTLY. COMPASS RACK NR 1 WAS REPLACED IAW MM 34-21-09, 360 GRADES OF AC MOVEMENT TEST WAS PERFORMED IAW MM 34-21-00, BEING CORRECT. DURING OVERNIGHT CHECK, THE COMPASS ROSE SWING TESTS WERE PERFORMED IAW MM 34-21-06, ALL CORRECT.
DURING TRANSIT CHECK THE MAIN LANDING GEAR WHEELS WERE DETECTED CONTAMINATED WITH RUNWAY RE-COVER MATERIAL. THE WHEELS WERE CHECKED; THE WHEEL POSITION 2 WAS REPLACED AND A GENERAL REVISION WAS PERFORMED AT ENGINES AND FLIGHT CONTROL SURFACES IAW MM 32-40-01, MM 05-55-00, MM 05-50-00 RESPECTIVELY, NONE DAMAGE WERE FOUND, ALL CORRECT.
AIRCRAFT RETURNED TO PLATFORM, LT ENGINE OIL PRESSURE WAS 38 PSI NEAR YELLOW RANGE. THE PARAMETERS IN FLIGHT CABIN WAS CHECKED AND OIL PRESSURE ADJUST WAS PERFORMED IAW MM 79-20-03. AFTER, TO ACCELERATE THE ENGINE, THE ENGINE PRESSURE WAS INCREASED TO 90 PSI. AIRCRAFT WAS SENT TO THE HANGAR, THE LT ENGINE OIL PRESSURE WAS ADJUSTED AND THE LOW PRESSURE SWITCH WAS REPLACED IAW 79-20-03, THE ENGINE RUNNING WAS PERFORMED IAW MM 71-00-00, TESTED CORRECT.
AIRCRAFT REJECTED TAKEOFF (WHEEL NOT TURNING) LIGHT TURNED ON. ANTISKID CONTROL BOX WAS REPLACED IAW MM 32-43-00, TESTED CORRECT.
DURING TRANSIT SERVICE, PERFORMED ANTISKID TEST, THE CIRCUIT BREAKER R-41 WAS ACTIVATED AND WOULD NOT RESEAT IT. ANTISKID VALVES CONNECTORS WERE DISCONNECTED AND TRANSDUCERS WERE CHECKED OF 4 MAIN WHEELS AND FAIL CONTINUE. ANTISKID CONTROL BOX WAS REPLACED IAW MM 32-43-00 AND FAIL CONTINUE. THE (WHEEL NOT TURNING) SOCKET WAS CHECKED IAW WDM 32-41-00, AND WAS DETECTED DAMAGED. SOCKET WAS REPAIRED AND TESTED IAW MM 32-43-00, ALL CORRECT.
DURING TRANSIT SERVICE, IN GROUND TEST THE HORIZONTAL STABILIZER MOTOR DID NOT MOVE. THE ACTUATOR AND PRIMARY MOTOR WERE REPLACED IAW MM 27-40-01, BUT FAILURE CONTINUED. AIRCRAFT WAS SENT TO THE HANGAR AND ANOTHER ACTUATOR AND PRIMARY MOTOR WAS INSTALLED, THE CONDITION OF P10-63 WAS CHECKED, THE OPERATION OF RELAYS R20-15, R20-17 AND R20-18 WERE VERIFIED, CONTINUITY AND ISOLATION TO GROUND WERE VERIFIED IAW MM 27-40-01 AND WDM 27-041-01 RESPECTIVELY, TESTED CORRECT.
CAPTAIN REPORTED PRIMARY STAB TRIM STICKS OCCASIONALLY. COMPENSATION MECHANISM OF HORIZONTAL STABILIZER CHECKED IAW MM 27-40-0, BEING CORRECT. DURING TESTS, PRIMARY MOTOR OF STABILIZER FAILED. REPLACED IAW MM 27-40-01. TESTED CORRECT.
AIRCRAFT RETURNED TO PLATFORM, LT ENGINE DID NOT ACCELERATE, N2 DECREASED BELOW 50 PERCENT AND LT GENERATOR WAS FOUND OUT OF LINE. ACCELERATION CHAMBER WAS DRAINED AND LUBRICATED, LT ENGINE WAS TESTED IAW MM 73-20-03, ALL CORRECT.
AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF LEFT GENERATOR FREQUENCY WITH OSCILLATION. MEL 24-1 PROCEDURE WAS APPLIED. AGAIN AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF LEFT ENGINE WAS NOT ACCELERATED. ACCELERATION CHAMBER WERE DRAINED AND LUBRICATED IAW MM 73-20-03, TESTED CORRECT. DURING OVERNIGHT SERVICE LEVEL OIL AND CHIP DETECTOR WERE VERIFIED, LEFT ENGINE SLOW ACCELERATION PROCEDURE WAS PERFORMED IAW 71-00-00 AND LEFT GENERATOR WAS TESTED IAW MM 24-10-00, ALL CORRECT. DEFERRED REPORT WAS CLOSED.
DURING TRANSIT CHECK INTERCOMMUNICATION SYSTEM WAS DETECTED OUT SERVICE. MAINTENANCE TEST WAS PERFORMED IAW MM 23-40-00, ALL CORRECT. AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF INTERCOMMUNICATION SYSTEM FAIL. MAINTENANCE PROCEDURE TEST WAS PERFORMED IAW MM 23-40-00, TESTED CORRECT.
AIRCRAFT RETURNED TO PLATFORM, LOW ACCELERATION (1.4 OF EPR) AND HIGH TEMPERATURE (600°C). DURING CHECK, THE RT ENGINE ACCELERATION CHAMBER WAS SERVICED, TESTS WERE PERFORMED TO BOTH ENGINES IAW MM 71-00-00, BEING CORRECT. DUE TO ART WAS INOPERATIVE, IT WAS DEFERRED IAW MEL 73-8. DURING OVERNIGHT SERVICE, RT ENGINE WAS CHECKED BY LEAKS ON PT2 AND PT7 LINES, BEING CORRECT. EPR TRANSMITTER AND RT ENGINE BULLET O-RING WERE CHECKED, ALL CORRECT. TRIM TO BOTH ENGINES WAS PERFORMED IAW MM 76-11-00, TESTED CORRECT.
DURING TRANSIT CHECK, DETECTED DAMAGE IN RIGHT ENGINE NOSE COWLING BY FOREIGN OBJECT DAMAGE WITH LIP DENT DEPTH OF 0.150 PER 1 DIAMETER AT 03:00 POSITION. AIRCRAFT WAS SENT TO THE HANGAR AND NOSE COWLING WAS REPLACED IAW MM 71-10-01 PAGE 201, ALL CORRECT.
AIRCRAFT RETURNED TO PLATFORM AS A CONSEQUENCE OF DURING PUSH BACK, CAPTAIN REPORTED LOST OF HYDRAULIC PRESSURE AND QUANTITY. DURING CHECK WAS DETECTED A LEAK FROM THE LEFT HYDRAULIC RELIEF VALVE, IT WAS REPLACED IAW MM 29-10-12, TESTED CORRECT.
CAPTAIN REPORTED THAT DURING FINAL APPROACH HORIZONTAL STABILIZER FAILED, CIRCUIT BREAKERS D-9 AND D-11 WERE ACTIVATED AND FAIL CONTINUE WITH 2 DEGREES NOSE DOWN AND 3 DEGREES NOSE UP. SCREW GEAR, RELAYS AND WIRING AFTER ACCESSORIES COMPARTMENT WERE CHECKED AND NO DAMAGES WERE FOUND. DURING REVISION THE PRIMARY WAS DETECTED WITH DAMAGE. IT AND THE TRIM GEAR BOX WERE REPLACED IAW MM 27-40-01, TEST CORRECT. HORIZONTAL STABILIZER WAS OPERATED WITH AN ALTERNATE MOTOR, ALL CORRECT.
AIRCRAFT RETURNED TO PLATFORM, (SIF) LIGHT TURNED ON. SYSTEM WAS CHECKED AND RELAY R2-58 WAS DETECTED ON FLIGHT POSITION AFFECTING LT STALL COMPUTER. RELAY WAS REPLACED IAW MM 32-62-00 AND TESTED IAW MM 34-19-00, ALL CORRECT.
DURING LANDING, TIRE NR 3 WAS LOST AND WATER DEFLECTOR WAS DAMAGED. MAIN TIRES WERE REPLACED IAW MM 32-43-10, ANTI-SKID TEST WAS PERFORMED IAW MM 32-43-00 AND DURING OVERNIGHT SERVICE AT MEX, WATER DEFLECTOR WAS REPLACED IAW MM 32-10-01, ALL CORRECT.
AIRCRAFT RETURNED OF FLIGHT AS A CONSEQUENCE OF LT GENERATOR LIGHT TURNED ON AND CSD WAS OUT OF SERVICE. ENGINE WAS SHUTDOWN TO ENGAGED CSD. THE CONTROL BOX WAS RESET AND ENGINE WAS STARTED WITH SWITCH ON "RESET" POSITION WITHOUT VOLTAGE AND FREQUENCY INDICATION. LT GENERATOR CONTROL BOXES WERE INTERCHANGED WITH APU CONTROL BOXES WITH NEGATIVE RESULTS. CONTROL BOXES WERE RETURNED TO THE ORIGINAL POSITIONS AND APU WAS STARTED OPERATING WITH LT BUS. AIRCRAFT WAS REFUELED AND LT GENERATOR WAS DEFERRED IAW MEL 24-1-1. DURING OVERNIGHT SERVICE CSD, GENERATOR AND OIL HEAT EXCHANGER WERE REPLACED IAW MM 24-10-03, 24-20-00 AND 24-10-01, RESPECTIVELY, TESTS CORRECT.
AIRCRAFT PERFORMED AN UNSCHEDULED LANDING AT HMO AS A CONSEQUENCE OF ENGINE NR 1 WITH OIL TEMPERATURE OSCILLATIONS BETWEEN 110 AND 137 DEGREES F AND OIL PRESSURE OF 47 PSI. DURING CRUISE THE OIL TEMPERATURE WAS 120 DEGREES F, DURING DESCENT THE OIL TEMPERATURE WAS 160 DEGREES F, APPROXIMATELY TO SHUTDOWN TEMPERATURE, AND OIL PRESSURE WAS BETWEEN 45 AND 50 PSI. THE TEMPERATURE SENSOR WAS REPLACED AND FAIL CONTINUE. CABLES WERE CHECKED AND SENSOR AND INDICATOR CABLES WERE GROUNDED. CABLES WERE ISOLATED AND ENGINE RUNNING WAS PERFORMED. DURING OVERNIGHT SERVICE LEFT TEMPERATURE SENSOR WAS REPLACED IAW MM 79-32-01 AND ENGINE RUNNING WAS PERFORMED IAW MM 71-00-00. CABLES WERE REPAIRED.
CAPTAIN REPORTED HIGH TEMPERATURE ON CSD DURING CLIMB, SO IT WAS DEACTIVATED. DURING TRANSIT CHECK AT MEX, THE CHIP DETECTOR WAS CKECKED AND CSD WAS DRAINED AND SERVICED IAW MM 12-12-02, TEST CORRECT. DURING OVERNIGHT SERVICE, THE RIGHT CSD AND HEAT EXCHANGER WERE REPLACED IAW MM 24-20-01 AND 24-10-03 RESPECTIVELY, TEST CORRECT.
DURING TRANSIT CHECK THE FUEL PANEL WAS DETECTED WITH DAMAGE OF 2.5 INCHES AND LEADING EDGE WITH CRACK OF 1.5 INCH IN STATION XRS 220. THE FUEL PANEL WAS REPAIRED IAW SRM 52-01 AND RIGHT WING LEADING EDGE WAS REPAIRED IAW SRM 57-06.
DURING CLIMB AND CRUISE AT SEVERAL TIMES RUDDER TRAVEL UNRESTRICTED LIGHT TURNED ON, FLASHING MODE ALL THE FLIGHT. CHECKED BY LEAK AND ADJUSTED RUDDER THROW LIMITER IAW MM 27-20-00. PROXIMITY SWITCH WAS REPLACED IAW MM 32-60-04, TEST CORRECT.
DURING TRANSIT CHECK WAS DETECTED EXCESSIVE FELT DOWN TO 33 DEGREES AND WHEN FLAPS ARE SELECTED, THERE ARE 5 DEGREE DIFFERENCE. AC WAS SENT TO HANGAR. DURING CHECK WAS DETECTED INTERNAL FLUID LEAKAGE IN EXTERIOR FLAP ACTUATOR. ACTUATOR AND PTU WERE REPLACED IAW MM. FLAPS BUS CABLE WAS ADJUSTED DUE TO BEING OUT OF TOLERANCE IAW MM AND FLAPS INDICATION WAS CHECKED IAW MM, ALL TESTS CORRECT.
FLT 610 - CUN-ATL - AIRCRAFT RETURNED AFTER APPROXIMATELY 30 MINUTES, DU TO THAT THE LEFT CONSTANT SPPED DRIVE REACHED THE HIGH TEMPERATURE RANGE AND THE RT GENERATOR WAS PREVIOUSLY DEFERRED BY MEL CAT B. CAPTAIN DISENGAGED THE CSD AND PERFORMED THE ABNORMAL PROCEDURE. AT PLATFORM, THE SYSTEM WAS TESTED. THE RT GENERATOR AND GCU AND THE LT CSD, GENERATOR AND HEAT EXCHANGER WERE REPLACED AND SYSTEM WAS TESTED IAW MM 24-10-01, 24-10-03, 24-20-01 AND 24-20-07, ALL CORRECT. (M)
MEX-GDL - DURING TRANSIT, DETECTED HYDRAULIC LEAK FROM LT MLG IN ANTI-SKID SYSTEM DUAL VALVE. VALVE WAS REPLACED IAW MM 32-43-03 AND HYDRAULIC SYSTEM WAS REFILLED, TESTS CORRECT. (M)
FLT 225 - GDL-MEX - THE RIGHT ENGINE THRUST REVERSER WAS REMOVED DUE TO INDICATION OF RIGHT ENGINE UNLOCK CAME ON AFTER TAKEOFF. AFTER THE THRUST REVERSER ASSEMBLY WAS RECEIVED AT THE SHOP, A DETAILED INSPECTION WAS PERFORMED. DOWN RIGHT OVER CENTER LINK ASSEMBLY WAS FOUND BROKEN (P/N 5938053-1) FOR THE OBSERVED EVIDENCES OF THE BLOCKAGE OF THE CARRIER, P/N 5933054-1, PROBABLY LED TO THE FOLDING OF ROD GUIDES AND BREAKING OF THE OVER CENTER LINK, RESULTING AT THE SAME TIME MISALIGNMENT OF BOTH DOORS AT THE CLOSING POSITION AND DAMAGED ON THE NOZZLE OUTSIDE SKIN. THE REVERSER SENT OUT OF SERVICE TO AN EXTERNAL SHOP IN EXCHANGE, INCLUDED IN A PROGRAM OF EXCHANGE OF PARTS. (M)
FLT 227 - CJS-MEX - DURING TRANSIT CHECK, DETECTED DAMAGES TO 28 BLADES OF THE NR 1 ENGINE. C1 DISK WAS REPLACED IAW MM 72-20-33 AND TESTS WERE PERFORMED IAW MM 71-00-00. (M)