N823MH
Registered owner: MUSTANG 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 HELICOPTERS, INC (M7KA) | Certificate holder | — | Matched by certificate designator |
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.
5 reports on file, 2007-09-19 – 2008-06-23.
Part: FREQ ADAPTER — CRACKED (M/R HUB ASSY)
DURING ROUTINE INSP A CRACK WAS FOUND IN ELASTOMER SURFACE OF BLUE CODED FREQUENCY ADAPTER THAT HAD REACHED MM LIMITATION OF 10MM. ALL (3) ADAPTERS WERE REPLACED AS A KIT IAE MFG RECOMMENDATIONS. SUGGEST MFG ALTER ELASTOMER FORMULATION TO IMPROVE SERVICE LIFE FOR THIS PART AS THIS HAS BECOME A VERY COMMON FAILURE FOR THIS PART WITH A 20,000 HR SERVICE LIFE. (K)
Part: FITTING — CRACKED (TAILBOOM)
DURING ROUTINE INSP, FITTING WAS FOUND CRACKED FROM AN OB ATTACHMENT SCREW BORE TO FLANGE EDGE. NEW FITTING WAS INSTALLED. THIS IS A COMMON FAILURE FOR THIS PART. BORE HOLES MUST BE MATCH DRILLED AND ALIGNED PERFECTLY. SUGGEST A MORE DURABLE MATERIAL BE USED IN THIS PARTS MFG SUCH AS TITANIUM OR SS AS ALUMINUM ALLOY FAILS ROUTINELY UNDER NORMAL STRESS APPLIED TO THIS PART. (K)
Part: POTENTIOMETER — FAILED (COLLECTIVE)
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)
Part: STARFLEX — CRACKED (M/R HUB ASSY)
(REF 1212074158) DURING ROUTINE INSP, THE 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 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 PART OR EXCESSIVE PLAY DEVELOPMENT OF BUSHING. SUGGEST THAT APPLICATION OF A SLIPPAGE MARK BETWEEN STAR ARM AND BUSHINGS TO SHOW BUSHING ROTATION BE ADDED AS A PRECAUTION TO DETECT DANGEROUS MOVEMENT. (K)
Part: BRACKET — CRACKED (STARTER GEN)
FOUND CRACKED DURING AIRFRAME 100/200/500 HOUR INSPECTION, BRACKET SUPPORTS, AIR INLET COOLING DUCT WHICH IS SUBJECT TO RAM AIR AND LIKELY VIBRATES CAUSING METAL OF BRACKET TO COLD WORK. THIS IS A COMMON PROBLEM WHICH OCCURS EVERY 200-300 HOURS FOR THIS COMPONENT. SUGGEST MFG IMPROVE STRENGTH AND INTEGRITY OF COMPONENT. USE SS INSTEAD OF ALUMINUM. (K)