N911TM
Registered owner: EXECUTIVE HELICOPTERS INC, SC (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.
9 reports on file, 1996-03-11 – 2023-05-20.
Part: UNKNOWN — UNKNOWN (UNKNOWN)
PLEASE CONSIDER REVISING THE R44 ROTORCRAFT FLIGHT MANUAL (RFM) TO PROHIBIT HOT FUEL LOADING. HOT FUELING CAN BE EXTREMELY HAZARDOUS DUE TO THE LOW FLASHPOINT OF AVGAS. THANKS IN ADVANCE FOR CONSIDERING THIS REQUEST.
Part: NONE — COLLAPSED (ZONE 700) · airframe 6,550 hrs
THE AIRCRAFT LANDED UNEVENTFULLY AND WAS SHUT DOWN BY THE PILOT. AFTER SHUTDOWN THE PILOT INSTALLED THE GROUND HANDLING WHEELS AND BEGAN TO MOVE THE AIRCRAFT INTO THE HANGAR. WHILE GROUND HANDLING THE AIRCRAFT THE AFT RIGHT HAND LANDING GEAR STRUT BROKE AND COLLAPSED. VISUAL INSPECTION OF THE STRUT REVEALED A CRACK THAT STARTED AT THE WELDED BRACE ON THE UPPER STRUT AND EXTENDED ALL THE WAY AROUND THE STRUT.
Part: EXHAUST VALVE — BROKEN (ENGINE) · airframe 6,204 hrs
DURING CRUISE FLIGHT PILOT REPORTED ENGINE BEGAN TO RUN ROUGH AND MANIFOLD PRESSURE INCREASED. HELICOPTER RETURNED TO HELIPAD AND MADE A NORMAL LANDING. EXHAUST VALVE STEM BROKE AT BELL CURVE AND WAS RELEASED INTO CYLINDER.
Part: ADJUSTER — LOOSE (FUEL CONTROL) · airframe 5,545 hrs
ENGINE N1 IDLE ADJUSTMENT SCREW HAS FREE MOVEMENT EITHER RIGHT HAND OR LEFT HAND. REPLACED WITH SERVICEABLE UNIT.
Part: CIRCUIT CARD — FAILED (NR 2 GENERATOR) · airframe 6,217 hrs
NR 2 GENERATOR DROPS OFF LINE. REPLACED WITH SERVICEABLE UNIT.
Part: BLADE — CRACKED (M/R)
DURING A SCHEDULED 100-HOUR INSPECTION WHILE CLEANING THE MAIN ROTOR BLADES, A 6 INCH CRACK WAS DISCOVERED ON THE LOWER SURFACE 4 FEET, 6 INCHES FROM THE ROOT END. STARTING 1 INCH FROM THE TRAILING EDGE TRAVELING CORDWISE, BUT DID NOT MEET THE SPAR AREA. NO IDEAS AS TO WHAT CAUSED THE CRACK. IT IS A GOOD IDEA TO REMOVE BLADES IF POSSIBLE WHEN INSPECTING THEM DUE TO THE DROOP OF THE BLADES WHEN STATIONARY, THE CRACK IS ALMOST IMPOSSIBLE TO SEE.
Part: UNION — CRACKED (FUEL DIST)
REMOVED FOR A FUEL PUMP BYPASS CHECK DUE TO DELAYED LIGHT-OFFS ON A C20F ENGINE. UNION WAS FOUND CRACKED AFTER LOOSENING B-NUT. BYPASS CHECK COMPLETED AND CHECK PASSED, STILL HAD NO RESOLVE TO DELAYED LIGHT-OFFS. INSTALLED UNION AND FUEL TUBE ASSEMBLY AND TIGHTENED B-NUT, THE INSIDE FLARE BROKE-OFF WITH B-NUT. AFTER INSPECTING THE UNION, SIGNS OF FRETTING WERE PRESENT AND THERE WAS A CRACK PRIOR TO IT FAILING. REPLACED UNION WITH NEW ONE. THE DELAYED LIGHT-OFFS PROBLEM WAS CORRECTED.
Part: LAMINATED HINGE — BEARING FAILED (T/R GR BOX YOKE)
PREMATURE FAILURE OF LAMINATED TEETERING BEARING. T/R YOKE REMOVED AND REPLACED.
Part: LAMINATED HINGE — EXCESS WEAR (T/R YOKE)
INSTALLED TEETERING BEARINGS (LAMINATED HINGE) AT ONE-HUNDRED HOUR INSPECTION, 60 HOURS AGO, THEN AT PRE-FLIGHT, NOTICED SEVERE WEAR. REMOVED FROM SERVICE. SUBMITTED TO MANUFACTURE FOR WARRANTY.