N911MZ
Registered owner: MARIA & JAMIL AVIATION LLC, MT (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
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
30 reports on file, 1996-04-02 – 2016-11-01.
Part: ELEC CONNECTOR — CONTAMINATED (ENGINE DECK) · airframe 13,734 hrs · 52,975 cycles
CREW MEMBER REPORTED FUEL ODOR DURING GROUND OPERATIONS. THE PILOT SHUTDOWN THE ENGINES AND CALLED THE MECHANIC OUT TO INSPECT THE AIRCRAFT. REMOVED THE CENTER CEILING PANELS INSIDE THE CABIN, AND FOUND SOME FUEL RESIDUE AROUND SOME ELECTRICAL CONNNECTORS AND DRAINS THAT COME THROUGH FROM THE ENGINE DECK. CLEANED AND DRIED, WASHED ALL OF THE CEILING PANELS, REMOVED THE NR 2 ENGINE COWLING, CLEANED AND DRIED THE ENGINE DECK, WIPED DOWN THE COMPLETE AREA. RESEALED THE ENGINE DECK ELECTRICAL CONNECTORS AND DRAIN THAT FEED THROUGH TO CEILING AREA OF CABIN. ONCE THE SEALANT HAD SET AND DRIED, HAD THE PILOT PERFORM A GROUND RUN WITH NO ADDITIONAL FUMES, ODORS, OR DEFECTS NOTED. THE AIRCRAFT WAS RETURNED TO SERVICE AT THAT TIME.
Part: B-NUT — LEAKING (ENGINE FUEL PUMP) · airframe 13,733 hrs · 52,973 cycles
THE PILOT AND MEDICAL CREW SMELLED A STRONG FUEL ODOR WITHIN THE CABIN OF THE AIRCRAFT. THE MECHANIC WAS CALLED OUT TO INSPECT THE AIRCRAFT AND FOUND A FUEL LINE FROM THE PUMP ON THE ENGINE SIDE UNDER TORQUED. TORQUED THE B-NUT, AND ACCOMPLISHED A GROUND RUN WITH THE PILOT. NO ADDITIONAL DEFECTS NOTED.
Part: CHIP DETECTOR — CONTAMINATED (NR 2 ENGINE) · airframe 13,488 hrs
NUMBER 2 ENG CHIP LIGHT IN CRUISE, WOULD NOT EXTINGUISH WITH 3 ZAPS. SHUTDOWN NR 2 ENG IAW ACFT EMER PROCEDURE CHECKLIST. UPON ARRIVAL, INSPECTED THE CHIP DETECTOR FOR DEBRIS. COLLECTED & PRESERVED THE DEBRIS COLLECTED & TOOK A SOAP SAMPLE FOR ANALYSIS WITH ADVICE FROM LEAD, RMM, & TECH SUPPORT.. DETERMINED DEBRIS ACCUMULATION TO BE CLASSIFIED AS MINOR. HE THEN PERFORMED A DRAIN & FLUSH FILTER CHANGE OF MOTOR. THE PILOT CONDUCTED A 15 MINUTE PENALTY GND RUN & THEN THE MECHANIC RE-INSPECTED THE CHIP DETECTOR FOR DEBRIS POST GND RUN WITH NO DEBRIS FOUND. ANNOTATED PROCEDURES & FINDINGS IN ACFT LOGBOOK & RELEASED ACFT FOR NO MORE THAN 50 FLIGHT HOURS PENDING RESULTS OF SOAP SAMPLE.
Earlier reports · 1996–2015 · 27 reports
2015
Part: FIRE WARNING — FALSE ACTIVATION (COCKPIT) · airframe 13,018 hrs · 50,529 cycles
THE NR 2 FIRE WARNING LIGHT WAS GLOWING VERY DIMLY. DID NOT NOTICE THE FIRE LIGHT WAS ON UNTIL THE OTHER COCKPIT LIGHTS WERE DIMMED FOR SHUTDOWN. THERE WAS NO EVIDENCE OF A FIRE IN THE NR 2 ENG COMPARTMENT. THE FIRE WARNING SYS STILL TESTED PROPERLY & CAME ON FULL BRIGHT WHEN TESTED.
Part: MOUNT FITTING — WORN (ENGINE) · airframe 13,006 hrs · 50,500 cycles
NUMBER 2 INBD FWD ENG MOUNT FITTING BUSHING WORN & ELONGATED, REQUIRING REPAIR SCHEME. REPAIR COMPLETED WITH FORM 337 DATED 07 07 2015.
Part: FIRE WARNING — FALSE ACTIVATION (COCKPIT) · airframe 12,861 hrs · 49,990 cycles
NUMBER 2 ENG FIRE LIGHT ILLUMINATED IN FLIGHT WITH NO FIRE. ACFT LANDED WITHOUT INCIDENT. NR 2 ENG FIRE DETECTOR SYS INSPECTED & TESTED, NO FAULTS FOUND, COULD NOT DUPLICATE FAULT.
2011
Part: SKIN — MISREPAIRED (TAILBOOM) · airframe 11,337 hrs
PERFORMING INSP ON TAILBOOM AND DISCOVERED RIVETS IN TAILBOOM THAT WERE NOT CORRECTLY INSTALLED AT PREVIOUS REPAIR ON TOP SKIN BECAUSE OF DIMPLES IN SKIN DID NOT LINE UP WITH HOLES IN STRINGER CORRECTLY. PREVENTING SKIN TO RECESS CORRECTLY, THUS WITH GAP IN SKINS MATING AND BOWING OF SKIN PUTTING STRESS ON AREAS OF REPAIR PREVIOUSLY PERFORMED.
2009
Part: FRAME — CRACKED (TAILCONE) · airframe 10,714 hrs · 42,258 cycles
DURING SCHEDULED MAINTENANCE, A 1 INCH LONG CRACK WAS DISCOVERED IN THE FUSELAGE TAILCONE LT A FRAME PT NR 117-22106-01.
2001
Part: CLOCK — DEFECTIVE (INSTRUMENT PNL)
CLOCK 8 DAY - CLOCK WORKS FOR 30 TO 90 MINUTES AND THEN STOPS. REMOVED AND REPLACED.
1999
Part: O-RING — LEAKING (T1 SENSOR)
TROUBLESHOT SYSTEM PER ENGINE MM. FOUND AIR LEAK ON TEMP COMPENSATOR. REMOVED 5 O-RINGS, PN M8324811-904. INSTALLED 5 NEW O-RINGS, P/N SAME. PERFORMED 7 GROUND RUNS ON NR 1 ENGINE. PERFORMED MAXIMUM CONTINUOUS OE 1 ON NR 1 ENGINE. TOPPED NR 1 PER ACFT TECH REP. ALL TEST RUNS AND FLIGHTS PERFORMED WITH NO DEFECTS NOTED.
1998
Part: SENSOR — FAILED (NG PICKUP)
INDICATION FAILURE. TROUBLESHOOT TO NG PICKUP. INSTALLED NEW PICKUP, OPS CHECK GOOD.
1997
Part: ARTIFICIAL HORIZ — NOISY (CSAS PITCH)
ARTIFICIAL HORIZ CAUSES CSAS PITCH ACTUATOR TO FLUCTUATE. SIGNAL OUT OF PINS, X AND Y ARE TOO NOISY SIMULATING PITCH UP OR DOWN. REMOVED AND REPLACED.
Part: COMPUTER — FAILED (CSAS)
CSAS COMPUTER CAUSES FLUCTUATIONS IN PITCH ACTUATOR. NOISY SIGNAL COMING OUT OF PINS 18 AND 19. REMOVED AND REPLACED.
Part: CONTROL — OVERHEAT (LIGHTS)
INSPECTED RHEOSTAT, WIRING, AND INTENSITY CONTROL UNIT. FOUND CONTROL UNIT TO HAVE STRONG ELECTRICAL ODOR. REPLACED WITH NEW UNIT. OPS CHECK GOOD.
Part: INDICATOR — DEFECTIVE (HORIZON)
BAD INPUTS TO YAW CSAS. NOTE: RED IMPACT INDICATOR. REMOVED AND REPLACED.
Part: MANIFOLD — LEAKS (ENGINE FUEL)
SUBMITTER STATES EXCESSIVE FUEL MANIFOLD LEAKS OVER THE LAST 18 MONTHS. ALLIED SIGNAL IS IN THE PROCESS OF RELEASING AN ASB LIMITING THE LIFE OF THE FUEL MANIFOLD TUBES. OTHER OPERATORS SUBMITTER CONTACTED ARE HAVING THE SAME PROBLEMS. OMNIFLIGHT HAS GONE TO A POST-FLIGHT CHECK AND A SHIFT-CHANGE CHECK OF THIS MANIFOLD.
Part: MANIFOLD — LEAKS (ENGINE FUEL)
SUBMITTER STATES EXCESSIVE FUEL MANIFOLD LEAKS OVER THE LAST 18 MONTHS. ALLIED SIGNAL IS IN THE PROCESS OF RELEASING AN ASB LIMITING THE LIFE OF THE FUEL MANIFOLD TUBES. OTHER OPERATORS SUBMITTER CONTACTED ARE HAVING THE SAME PROBLEMS. OMNIFLIGHT HAS GONE TO A POST-FLIGHT CHECK AND A SHIFT-CHANGE CHECK OF THIS MANIFOLD.
Part: COMPUTER — MALFUNCTION (CSAS)
PITCH AND ROLL CSAS CAUTION LIGHT ILLUMINATED INTERMITTENTLY.
Part: GYRO HORIZON — INOPERABLE (CSAS PITCH ROLL)
GYRO HORIZ PITCH AND ROLL CSAS INOPERABLE.
Part: COMPUTER — FAILED (YAW CSAS)
YAW COMPUTER HAD EHA FAILED IN FULL RETRACT POSITION.
Part: GYRO HORIZON — FAILED (COCKPIT)
HORIZON STARTED SPINNING AND TUMBLING IN-FLIGHT.
1996
Part: INDICATOR — DEFECTIVE (MAST MOMENT)
INDICATOR TESTS PASSED THE CALIBRATION LINE.
Part: MANIFOLD — LEAKS (ENGINE FUEL)
SUBMITTER STATES EXCESSIVE FUEL MANIFOLD LEAKS OVER THE LAST 18 MONTHS. ALLIED SIGNAL IS IN THE PROCESS OF RELEASING AN ASB LIMITING THE LIFE OF THE FUEL MANIFOLD TUBES. OTHER OPERATORS SUBMITTER CONTACTED ARE HAVING THE SAME PROBLEMS. OMNIFLIGHT HAS GONE TO A POST-FLIGHT CHECK AND A SHIFT-CHANGE CHECK OF THIS MANIFOLD.
Part: TRANSCEIVER — INOPERATIVE (COCKPIT)
INOP WHEN INSTALLED IN A/C - WILL NOT TRANSMIT.
Part: TRIPLE TACH — INTERMITTENT (ENG N2)
INTERMITTENT N2 - NR 2 DROP OF 2 PERCENT AT 100 PERCENT.
Part: TRANSCEIVER — DEFECTIVE (COCKPIT VHF)
TRANSCEIVER WILL NOT TRANSMIT CLEAR, BUT RECEIVES OK. PART WAS JUST IN FOR REPAIR 5-14-96.
Part: INDICATOR — DEFECTIVE (COCKPIT RADAR)
TRANSMITTER FAULT. RADAR SENSOR. COLOR RADAR INDICATOR.
Part: SENSOR — DEFECTIVE (COCKPIT RADAR)
TRANSMITTER FAULT. RADAR SENSOR. COLOR RADAR INDICATOR.
Part: TRANSCEIVER — FAILED (COCKPIT)
VHF-FM HI BAND RADIO WILL NOT TRANSMIT OR RECEIVE. REMOVED AND REPLACED.
Part: GYRO — DEFECTIVE (COCKPIT ATTITUDE)
ON INSTALLATION, GYRO UNIT WAS SLOW TO SPIN-UP AND GRADE-OFF. REMOVED AND REPLACED.