N806MH
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 |
|---|---|---|---|
| ALEXAIR INC. (X33A) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING ROUTINE INSPECTION A STAR ARM END BUSHING WAS FOUND LOOSE. STARFLEX REMOVED FOR REPAIR AND SERVICEABLE STARFLEX INSTALLED. THIS IS A VERY COMMON FAILURE RECENTLY FOR THIS PART. SUSPECT THAT AN ADHESIVE FAILURE IS THE PROBLEM THAT MAY BE HEAT RELATED. (K)
DURING ROUTINE INSP, FITTING WAS FOUND CRACKED IN EXCESS OF 2 INCHES FROM MOUNTING FLANGE EDGE THROUGH ONE SCREW BORE HOLE. THIS IS A COMMON FAILURE FOR THIS PART. SUGGEST THIS PART BE MFG FROM MORE ROBUST MATERIAL SUCH AS SS OR TITANIUM. CAREFUL MATCH DRILLING AND SHIMMING IS REQUIRED DURING REPLACEMENT. (K)
DURING ROUTINE OPERATIONS THE LANDING LIGHT WOULD INTERMITTENTLY NOT STOP WORKING WITH THE SELECTOR SWITCH IN THE OFF POSITION. CYCLING THE SWITCH SEVERAL TIME RAPIDLY WOULD USUALLY CORRECT THE PROBLEM. AN OBVIOUS STICKING RELAY. A NEW RELAY WAS INSTALLED AND NO FURTHER DEFECT WAS NOTED. THIS IS A REAR FAILURE FOR THIS PART. ONE FAILURE HAS BEEN NOTED IN EVERY 20,000 FLIGHT HOURS FOR OUR FLEET. (K)
A FAULT CODE WAS GENERATED ON SHUTDOWN INDICATING A DEFECT OF COLLECTIVE POTENTIOMETER. A NEW PART WAS INSTALLED, NO FURTHER FAULT WAS DETECTED. THIS IS RECURRING FAILURE FOR THIS PART WHICH HAS EFFECTED DISPATCH RELIABILITY FOR THIS MODEL HELICOPTER. SUGGEST AN ALTERATION OF FAULT SENSING SOFTWARE TO REDUCE FAULT SENSITIVITY TO PERHAPS A SIGNAL LOSS OF 0.5 SECOND RATHER THAN 1/20TH OF A SECOND. AN OPTIC RATHER THAN A RESISTANCE BASED SENSOR SHOULD BE CONSIDERED AS CONTACT POINT IS DAMAGED BY AC VIBRATION WHEN AC POWER SETTINGS ARE SET FOR CRUISE FLIGHT. (K)
(REF 0501083833) 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 THE BUSHING AND STAR ARM END. WITH ROTOR HUB SLEEVES REMOVED BUSHING COULD BE MOVE MANUALLY. A SERVICEABLE REPLACEMENT STARTFLEX 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 BUSHING 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)
FAILURE CODE AT SHUTDOWN INDICATED A FAULT WITH THE COLLECTIVE POTENTIOMETER. INSTALLED NEW POTENTIOMETER AND NO FURTHER PROBLEM NOTED. THIS IS A VERY COMMON FAULT FOR THIS PART THAT EFFECTS THE DISPATCH RELIABILITY FOR THIS MODEL AIRCRAFT. (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)
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)
FOLLOWING ENGINE INSTALLATION A GROUND RUN WAS ABORTED WHEN AN ENGINE CHIP LIGHT ILLUMINATED IN A DIM FLICKERING MANNER ON THE CWP. INVESTIGATION REVEALED THE DETECTOR END HAD BROKEN LOOSE BUT REMAINED ATTACHED BY ITS INTERNAL WIRING. CLOSE EXAMINATION REVEALED THAT A PLASTIC CENTRAL POST HAD FAILED. PERHAPS THE DETECTOR WAS DAMAGED DURING REMOVAL AND INSTALLATIONS. SUGGEST A MORE ROBUST MATERIAL THAN PLASTIC BE USED TO MAKE PART HANDLED AS MUCH AS THESE ARE. (K)
DURING ROUTINE 500 HOUR INSPECTION IT WAS DISCOVERED THAT THE CASTING AT THE AFT MOST POSITION OF THE TAILBOOM, WHICH IS THE ATTACHMENT POINT FOR THE FENESTRON (DUCTED FAN TAIL ROTOR) HAD SEVERAL CRACKS EXCEEDING 1.5 INCHES RADIATING FROM ONE POINT AT THE 3:00 POSITION WITH TAILBOOM VIEWED FROM THE REAR. THIS CRACKING COULD ONLY BE VIEWED EASILY WITH THE HORIZONTAL STABILIZER REMOVED. THIS WAS DETERMINED BY THE OEM TO BE A NON FIELD REPAIRABLE DEFECT AND SERVICEABLE TAILBOOM ASSEMBLY HAS BEEN ORDERED AND WE WILL REPLACE THE DEFECTIVE TAILBOOM WHEN IT ARRIVES IAW THE MANUFACTURERS INSTRUCTIONS AND TECHNICAL REPRESENTATIVEâS SUPERVISION. IT DID NOT APPEAR THAT A CATASTROPHIC FAILURE WAS IMMINENT. (K)