N802MH
Registered owner: WORLD TRADE ENTERPRISES LLC, TX (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| SUNSHINE HELICOPTERS, INC. (SSHA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
AMBER GOVERNOR LIGHT ILLUMINATED IN FLIGHT. NO FAULT CODE WAS GENERATED THAT POINTED TO THE SWITCH AS THE PROBLEM AS WOULD NORMALLY OCCUR WITH THIS TYPE OF FAILURE. NO FURTHER PROBLEMS DEVELOPED FOLLOWING THE INSTALLATION OF A NEW SWITCH. (K)
DURING CRUISE FLIGHT AC CWP RED AND YELLOW GOV GOVERNOR LIGHT SEGMENTS ILLUMINATED AND ROTOR RPM BEGAN TO DECAY WITH A LOW ROTOR WARNING AS PILOT ENTERED AUTOROTATION. A NORMAL AUTOROTATION WAS COMPLETED WITH NO DAMAGE SUSTAINED BY THE AIRCRAFT. THE VEMD INDICATED A FAULT WAS DETECTED WITH THE PUMP AND ADJUSTED VALVE METERING UNIT (HMU). AS THIS IDENTICAL EVENT WAS PREVIOUSLY CAUSED BY A RUPTURE OF THE DIAPHRAGM OF THE HMU CONSTANT DP VALVE ON 2 PREVIOUS OCCASIONS I FEEL THIS TO BE THE LIKELY CAUSE. A SERVICEABLE HMU WAS INSTALLED AND AC INSPECTED, LEAK AND OPERATIONALLY CHECKED AND RETURNED TO SERVICE. (K)
DURING ROUTINE MAINTENANCE INSPECTION OF THE TAIL ROTOR DRIVESHAFT, CENTER SECTION, AFT COUPLING RIVETED ATTACHMENT ONE OF THE SPECIAL RIVET SUPPORT BLOCKS WAS FOUND TO BE NOT SQUARE TO SHAFT CENTERLINE. FURTHER DETAILED EXAMINATION SHOWED ENTIRE COUPLING MOVEMENT RADIALLY RELATIVE TO SHAFT EXCEEDS .1250 INCH. SUSPECT DRIVESHAFT FAILURE IMMANENT.
ENGINE OIL AIR VENT TUBE POSITIONED ALONG THE RT SIDE OF THE ENGINE WITH THE AFT END CURVED UPWARD INTO THE ENGINE EXHAUST AS TO AID THE VENTURI SECTION OF THE OIL AIR VENTING HAS A WELDED CLAMP SUPPORTED BY A STRAP HANGING FROM THE ENGINE TAILPIPE TO PREVENT TUBE ROTATION OUT OF THE GAS/EXHAUST PATH. THIS CLAMP IS ROUTINELY CRACKING DUE TO FATIGUE. NO TUBE ROTATION HAS OCCURRED 3RD FAILURE THIS AC.
1 OF 4 LATCHES ON THE ENGINE FAIRING, THE LATCH HOOK SHEARED AT THE BASE OR CONTACT POINT IN THE HOOK AND EXAMINATION SHOWED NO APPARENT WEAR JUST A SHEAR BREAK LINE WITH SOME CRYSTALIZATION APPARENT MUCH LIKE A FATIGUE FAILURE. THE HOOK IS OF TITANIUM MATERIAL. AN OLDER STAINLESS STEEL VARIENT OF THE LATCH WAS MUCH MORE DURABLE AND WOULD WEAR SLOWLY AND NEVER SHEARED EXCEPT DUE TO WEAR.
WINDSCREEN DEVELOPED 3 INCH CRACK IN LT UPPER CORNER NOTICED UPON LANDING DURING POST FLIGHT CHECK. MFG METHOD OF BONDING OF WINDSCREEN TO AIRFRAME CAUSES EXPANSION AND CONTRACTION TO DEVELOP STRESS IN THE LEXAN MATERIAL LENDING TO CRACKING DEFECTS.