N815MH
Registered owner: AIRSTAR LEASING LLC, NV (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| MAVERICK AIRSTAR LLC (Q2KA) | Certificate holder | — | Matched by certificate designator |
| MAVERICK HELICOPTER INC (M7KA) | 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 AND SUBSEQUENT TO FAILURE REPORT GENERATION THE COLLECTIVE POTENTIOMETER WAS INDICATED TO BE DEFECTIVE. A NEW PART WAS INSTALLED AND NO FURTHER DEFECT NOTED. (K)
(REF 0213084022) DURING ROUTINE INSP, ADHESIVE BEAD FOR A STAR ARM END BUSHING WAS FOUND CRACKED. FURTHER EXAMINATION UTILIZING A SOAP WATER DETECTION METHOD REVEALED RELATIVE MOTION BETWEEN BUSHING & STAR ARM END. WITH ROTOR HUB SLEEVES REMOVED BUSHING COULD BE MOVED MANUALLY. A SERVICEABLE REPLACEMENT STARFLEX WAS INSTALLED. THIS IS A DEFECT THAT RECENTLY HAS BECOME MORE COMMON THAN IN THE PAST. SUGGEST A DIFFERENT ADHESIVE BE UTILIZED OR THE STAR ARM ENDS AND BUSHINGS BE DESIGNED TO HAVE A LARGER ADHESIVE BONDING SURFACE SUCH AS ADDING INNER BUSHING AND OUTER STAR ARM END SPLINING. THERE WAS NO EVIDENCE OF ANY IMMINENT FAILURE FOR THE PART OR EXCESSIVE PLAY DEVELOPMENT OF THE BUSHING. SUGGEST THAT THE APPLICATION OF A SLIPPAGE MARK BETWEEN THE STAR ARM AND THE BUSHINGS TO SHOW BUSHING ROTATION BE ADDED AS A PRECAUTION TO DETECT DANGEROUS MOVEMENT. (K)
DURING ROUTINE MAINT (1) OF (2) BELT TENSIONING ARMS FOUND CRACKED IN (2) PIECES. FAILURE ORIGINATED AT WELDMENT. SEVERAL HAVE FAILED IN THIS MANNER. SUGGEST POST WELD, HEAT TREATMENT TO RELIEVE WELD STRESS. (K)
PILOT REPORTS AMBER GOVERNOR LIGHT CAME ON IN FLIGHT. NO FAULT CODE WAS GENERATED INDICATING A POTENTIOMETER DEFECT HOWEVER CIRCUMSTANCES REPORTED POINTED TO THIS. A NEW POTENTIOMETER HAS BEEN INSTALLED. PROBLEM FIXED THIS PART HAS LASTED MUCH LONGER THAN TYPICAL THIS IS A RECURRING PROBLEM FOR THIS PART THAT HAS EFFECTED THE DISPATCH RELIABILITY OF THIS MODE AC. THIS PART CAN ON OCCASION ALSO CAUSE ENGINE FLUCTUATIONS IN FLIGHT WHEN THE RESISTANCE VALUE SIGNAL IS DISRUPTED FOR A LITTLE AS 1/20TH OF A SECOND, WHICH IS THE SAMPLE RATE FOR THE ENGINE CONTROL SYS. AN ADDITIONAL FACTOR FOR THESE TYPE OF FAULTS IS NO RESET FUNCTION AVAILABLE TO THE PILOT TO DIFFERENTIATE BETWEEN A MOMENTARY OR AN ACTIVE FAULT. ONCE THE AMBER WARNING LIGHT IS ILLUMINATED IT REMAINS ON UNTIL THE FLIGHT IS TERMINATED EVEN IF SIGNAL DISRUPTION WAS ONLY FOR 1/20TH OF A SECOND DURING AN IN-FLIGHT TURBULENCE EVENT. (K)
FITTING FOUND CRACKED DURING POST FLIGHT INSP AND A NEW FITTING MATCH DRILLED AND INSTALLED. THIS IS A COMMON DEFECT FOR THIS PART AND OCCURS MULTIPLE TIMES ON SOME AIRCRAFT AND NEVER ON OTHER AIRCRAFT FOR REASONS UNKNOWN. SOME SHIMMING CAN BE REQUIRED AND MATCH DRILLING THE PART MUST BE DONE CAREFULLY. IF THE INSTALLATION IS NOT DONE CAREFULLY THIS MAY BE A FACTOR IN CRACK DEVELOPMENT AS WELL. (K)
AC HAD SOME SUDDEN YAWING WHEN PASSING THROUGH A SPECIFIC COLLECTIVE POWER SETTING THAT WAS REPEATABLE AND INDICATED A SUDDEN CHANGE OF ENGINE TORQUE SUCH AS ONE MAY EXPERIENCE WITH COMPRESSOR STALLS. NO FAULT CODES WERE GENERATED AD THE ENGINE HAD NO OBSERVABLE DEFECT WHEN EXAMINED. APPARENT THAT A DEAD SPOT HAD DEVELOPED IN THE POTENTIOMETER SIGNAL CONTROLLING ENGINE ANTICIPATION. NEW POTENTIOMETER WAS INSTALLED WITH NO FURTHER DEFECT. (K)
THIS ANTI-COLLISION LIGHT AND POWER SUPPLY ASSY HAS PROVEN TO BE OF LOW QUALITY AS MOST FAIL WITHIN THEIR FIRST 1000 HOURS OF SERVICE AND ARE NOT REPAIRABLE IAW MFG. AS THIS UNIT IS VERY EXPENSIVE TO REPLACE WE RECOMMEND THAT THE WHEN LED FLASHING ANTI COLLISION LAMP ASSY BE INSTALLED IN ITS PLACE UNDER A FIELD APPROVAL. THIS LIGHT IS VERY BRIGHT WITH A LONG DURATION FLASH IS LESS THAN .333 THE PRICE AND IS REPAIRABLE BY THE MFG. (K)