N211SL

ATA 7321

Part: FUEL CONTROL — MALFUNCTIONED (NR 2 ENGINE) · airframe 16,437 hrs · 62,549 cycles

AT APPROX 1030 AM WHILE STARTING AN APPROACH INTO THE HOSPITAL. HAD A PRONOUNCED YAW FOLLOWED BY THE NR 2 ENGINE LOW LIGHT COMING ON, OBSERVED THE ENGINE RPM CLIMB TO 110 PERCENT AND DROP OFF, ENGINE RPM FELL BELOW 20 PERCENT AS WELL. AUDIBLE WARNING WAS GOING OFF, LOST NR 2 ENGINE. ADVISED AIR COM AND DIVERTED TO AIRPORT AND EXECUTED A SINGLE ENGINE RUN ON LANDING.

ATA 7200

Part: ENGINE — FAILED (NR 2) · airframe 16,437 hrs · 62,549 cycles

AT START OF APPROACH, HAD A PROUNOUNCED YAW FOLLOWED BY NR 2 ENGINE LOW LIGHT COMING ON, OBSERVED ENGINE RPM CLIMB TO 110 PERCENT AND DROP OFF, ENGINE RPM FELL BELOW 20 PERCENT AS WELL. AUDIBLE WARNING ACTIVATED, LOST NR 2 ENGINE. DIVERTED TO AIRPORT AND EXECUTED A SINGLE ENGINE RUN ON LANDING.

ATA 2120

Part: UNKNOWN — ODOR (COCKPIT) · airframe 16,106 hrs · 61,613 cycles

ROLL CSAS LIGHT ILLUMINATED AND AN ACRID ODOR FOLLOWED. ROLL CSAS CIRCUIT WAS DISENGAGED AND THE ODOR WAS NO LONGER PRESENT. RETURNED TO BASE. TROUBLESHOOTING FOUND NO DISCREPANCIES WITH ACFT, GROUND TURNED ACFT AND THEN A MX TEST FLIGHT WAS ACCOMPLISHED WITH THE ROLL SYSTEM WORKING AS DIRECTED WITH NO ODOR. NO DISCREPANCIES FOUND.

ATA 2435

Part: STARTER GEN — DEFECTIVE (NR 2 ENGINE) · airframe 15,629 hrs

NR2 STARTER/GENERATOR CAUSING IRREGULAR AMPERAGE SPIKES ON AMMETER DURING NORMAL FLIGHT. MOMENTARILY KICKED OFF NR1 GENERATOR. FOUND FAULTY STARTER/GENERATOR UPON EXAMINATION. STARTER BRUSHES WERE WORN BEYOND SERVICEABLE LIMITS AND IRREGULAR BRUSH WEAR NOTED ON 2 OF THE BRUSHES. ONE OF THE BRUSHES DOWN TO NO LIFE LT, ANOTHER DOWN TO APPROX. 10 PERCENT AND THE OTHER (2) HAD APPROX. 40 PERCENT LIFE LEFT. UNIT HAD ONLY 50+19 HRS TSO. THE STARTER WAS REPLACED AND THE SHIP RETURNED TO SERVICE WITH NO FURTHER DEFECTS NOTED AT THIS TIME.

ATA 6230

Part: SLIDING SLEEVE — DEBONDED (SWASHPLATE) · airframe 15,577 hrs · 59,518 cycles

UPON AIRWORTHINESS INSPECTION IN THE MORNING, THE MECHANIC FOUND THAT THE MAIN ROTOR SWASHPLATE SLIDING SLEEVE TEFLON BUSHING HAD TEFLON LINER DEBONDED FROM BUSHING AND WAS WORKING ITS WAY OUT OF THE LOWER PORTION OF THE SLIDING SLEEVE ASSEMBLY AND THUS AFFECTING THE SLIDING SLEEVE FLIGHT CONTROL.

ATA 5330

Part: SKIN — DENTED (BS 4750) · airframe 15,481 hrs · 59,138 cycles

DAMAGE FOUND NEAR THE RT REAR JACK POINT STA 5000MM AND DAMAGE LT OF CTR LINE APPROX 370MM AT STA 4750 MM.

ATA 2435

Part: STARTER GEN — OUT OF ADJUST

EXTREMELY FAINT ELECTRICAL BURNING ODOR DETECTED. ASKED TRANSPORT TEAM IF THEY DETECTED ODOR AND THEY INDICATED THAT THEY DID NOT. PILOT NOTICED NR 2 GENERATOR AMP GAUGE INDICATING APPROXIMATELY 50 AMPS WHILE NR 1 GENERATOR AMP GAUGE INDICATED APPROXIMATELY 10 AMPS. NO OTHER INDICATIONS NOTED SWITCHED OFF NR 2 GENERATOR AND LOAD INCREASED ON NR 1 GENERATOR TO APPROXIMATELY 40 AMPS. SWITCHED NR 2 GENERATOR BACK ON AND ORIGINAL LOAD IMBALANCE RETURNED. AS THE ODOR WAS NO LONGER DETECTABLE, & THERE WERE NO INDICATIONS OF A MALFUNCTION, OTHER THAN AMPERAGE LOAD IMBALANCE, FLT CONTINUED TO ORIGINAL DESTINATION. UPON RETURN TO BASE, INCIDENT REPORTED TO MX & AN ENTRY MADE BY PILOT IN ACFT MX LOG. MECHANIC DIAGNOSED PROBLEM & ADJUSTED ELECTRICAL LOAD BALANCE IAW ACFT MM. A SUBSEQUENT INSPECTION OF NR 2 STARTER/GENERATOR BRUSHES FOUND NOTHING ABNORMAL AND THE SOURCE OF THE EXTREMELY FAINT BURNING ELECTRICAL ODOR WAS NEVER LOCATED.

ATA 6520

Part: FITTING — CRACKED (TAIL ROTOR G/B) · airframe 12,904 hrs · 43,347 cycles

WHILE PERFORMING A LIFENET AAIP INSPECTION, THE MECHANIC FOUND A .7500 INCH (APPROX) CRACK EXTENDING FROM THE UPPER LEFT HAND T/R GEARBOX MOUNT HOLE INBOARD THROUGH AN ADJACENT RIVET HOLE TERMINATING AT A CORNER FILLET, ON THE MOUNT FITTING FOR THE TAIL ROTOR GEARBOX. THE AIRCRAFT WAS REMOVED FROM SERVICE AND TRUCKED BACK TO SAINT LOUIS, MO. FROM JOPLIN, MO. FOR TAILBOOM REPLACEMENT. THE AFFECTED TAILBOOM WILL BE SENT TO EUROCOPTER CANADA FOR MOUNT FITTING REPLACEMENT. THE CRACK WAS FOUND VISUALLY AND VERIFIED WITH DYE PENETRANT. THIS AREA OF THE TAILBOOM HAS BEEN KNOWN TO CRACK, IT IS IMPERATIVE THAT THOROUGH INSPECTIONS ARE PREFORMED AT SCHEDULED INSPECTION INTERVALS.

ATA 5302

Part: STRUCTURE — CRACKED (TAILBOOM)

WHILE PERFORMING A DAILY INSP, MECHANIC FOUND A .5000 INCH CRACK EXTENDING PAST THE LEADING EDGE FAIRING FOR THE HORIZONTAL STABILIZER, THE CRACK WAS IN THE TAILBOOM OF THE AIRCRAFT, AFTER REMOVING THE FAIRING FOR FURTHER INSPECTION, IT WAS DETERMNED THAT CRACK WAS 1.5 INCHES LONG EXTENDING UPWARDS FROM THE LEADING EDGE OF THE HOLE PROVIDE FOR THE HORIZONTAL STABILIZER, IN THE LEFT HAD SIDE OF THE TAILBOOM. TAILBOOM WAS REMOVED FROM AC AND SENT FOR REPAIR, A SERVICEABLE TAILBOOM WAS INSTALLED AND THE AC WAS RETURNED TO SERVICE ON 8/2/03. THIS AREA OF TAILBOOM IS PRONE TO CRACKS, PILOTS AND MECHANICS SHOULD PAY CLOSE ATTENTION TO THIS AREA ON PREFLIGHT AND DAILY INSPECTIONS.

ATA 2824

Part: PUMP — FAILED (FUEL TRANSFER)

AFTER TAKEOFF, AFT FUEL TRANSFER PUMP LIGHT ILLUMINATED. CIRCUIT BREAKER WAS PULLED AND RESET. SWITCH WAS CYCLED. PROBABLE CAUSE, BEARINGS SEIZED.

ATA 7323

Part: GOVERNOR — FAILED (NR 2 ENGINE)

PILOT REPORTED ENROUTE TORQUE SPLITS BETWEEN ENGINE. AC MADE SCHEDULED LANDING AT HOSPITAL. PILOT ATTEMPTED TO START NR 2 ENGINE, ENG WOULD NOT ACCELERATE BEYOND 42% NG SPEED. UPON INSP OF ENGINE AND COMPONENTS, TECH DISCOVERED NP GOVERNOR SHAFT SEIZED, REPLACED GOVERNOR WITH SERVICEABLE UNIT. AC CHECK RUN AND FLIGHT COMPLETED AND RETURNED TO SERVICE. GOVERNOR DISASSEMBLED, BRG BETWEEN FLYWEIGHTS AND INTERNAL GOV LEVER FAILED, WHICH BENT THE SHAFT PROHIBITING ANY ROTATION WITHIN THE GOVENOR, SUSPECTED WHEN SHAFT BENT IT ALSO WEDGED GOV LEVER WHICH MODULATES PR BLEED PORT OPEN IN THE MIDRANGE.

ATA 5302

Part: FRAME — CRACKED (TAIL BOOM)

DURING ROUTINE TAIL BOOM INSPECTION, FOUND FRAME 10L CRACKED ALL THE WAY THROUGH. REPORTED DISCREPANCY TO AMERICAN EUROCOPTER. AMERICAN EUROCOPTER SENT TECH REP TO REMOVE FRAME 10L AND INSTALL NEW FRAME.