TAS CHARTER LLC

TAILCONE AND SLIDE FAILED TO DEPLOY USING AFT PRESSURE BULKHEAD DOOR EMERGENCY RELEASE SYSTEM. ADJUSTED RETAINING CLIPS ON INTERIOR RELEASE PINS TO OBTAIN 30 LBS OF PULL OUT OF CLIPS AND 15 LBS FOR AFT DOOR OPENING. FUNCTIONAL TEST PASSED ON TAILCONE RELEASE SYS.

ELECTRICAL ODOR FROM FORWARD CABIN DURING AIRCRAFT BOARDING. PASSENGERS WERE DISEMBARKED AS A PRECAUTION. THE GASPER FAN IN THE LEFT CONDITIONED AIR DISTRIBUTION SYSTEM WAS FOUND TO BE DEFECTIVE.

AIRCRAFT DEPARTED KEGE, DURING CLIMBOUT AT APPROXIMATELY 11,000FT MSL THE NR 2 ENGINE STARTED SURGING +/- 10% N1 ROTATION, FOLLOWED BY A NR 2 ENGINE COMPUTER LIGHT. THE CREW FOLLOWED THE AIRCRAFT CHECKLIST AND RESET THE ENGINE COMPUTER. THE ENGINE STABILIZED FOR APPROXIMATELY 2-3 MINUTES, THEN THE ENGINE ROLLED BACK AND SHUTDOWN UN-COMMANDED. THE FLIGHT CREW THEN RAN THE AIRCRAFT CHECKLIST FOR AN ENGINE FAILURE AND ENGINE SHUT DOWN PROCEDURES. THE CREW PROCEEDED TO KDEN AND LANDED UNEVENTFULLY.

BOTH LT AND RT EXTERIOR EMERGENCY LIGHTS ARE INOPERATIVE. REMOVED AND REPLACED OVERWING EMERGENCY BATTERY PACK. (K)

PILOTS DEVIATED FROM THE PILOT OPERATING PROCEDURES FOR TAXIING OF THE AC PROCEEDING A MLG BRAKE AND WHEEL TIRE CHANGE THE AC RETURNED TO THE RAMP AREA WITH NO ABNORMAL INDICATIONS, OTHER THAN THE BRAKE/RUDDER PEDALS ACHIEVING EXCESSIVE TRAVEL TO THE FLIGHT DECK FLOOR. UPON EXITING THE AC, THEY NOTED THAT THE MAIN WHEEL BRAKES HAD BEGAN TO OMIT SMOKE AND WERE OBVIOUSLY OVERHEATED FROM EXCESSIVE BRAKING. ALL MLG BRAKES, WHEEL AND TIRES WERE REPLACED. INCLUDING THE BRAKE SUPPLY LINE HYD HOSES. THE MLG STRUTS WERE INSPECTED FOR ANY HEAT RELATED DAMAGE. (K)

TWO LIGHT INOPERATIVE ON TAILCONE SLIDE EMERGENCY LIGHT. REPLACED BATTERY PACK ASSEMBLY. (K)

AT 35,000 FEET RIGHT FIRE DETECTOR FAIL CAME ON INTERMITTENTLY. LIGHT WOULD COME ON FOR NO LONGER THAN 2 SECONDS, THEN GO OFF. REMOVED AND REPLACED FDCU FOR RIGHT ENGINE.

LEFT AND RIGHT EXTERIOR EMERGENCY LIGHTS ARE NOT ILLUMINATING. REMOVED AND REPLACED EMERGENCY BATTERY PACK.

AFT CARGO DOOR OUTER PAN HAS A CRACK LOCATED AT THE FORWARD SIDE BY CRANK GUIDE. FABRICATED AND INSTALLED DOUBLER.

AFT CARGO DOOR INNER PAN CRACKED AT FORWARD CRANK GUIDE. FABRICATED AND INSTALLED DOUBLER.

RIGHT THRUST REVERSER UPPER BUCKET AFT ZEE CHANNEL IS CRACKED ON INBOARD SIDE AT STATION 36. CUT OUT DAMAGE AND FABRICATED AND INSTALLED DOUBLER.

INTERNAL TAIL CONE RELEASE LIGHT SWITCH DID NOT ACTUATE AFTER TAIL CONE WAS RELEASED FOR TEST FUNCTION. REMOVED AND REPLACED INTERNAL TAIL CONE LOCKING SWITCH.

VISIBLE SMOKE AND ACRID SMELL POURED FROM THE HOUSING AROUND THE MASK. FOUND INSTRUMENT AND PEDESTAL LIGHT DIMMER BOX SHOWING SIGNS OF INTERNAL COMPONENT BURN AND ACRID SMELL. REMOVED AND REPLACED DIMMER BOX.

CRACK AT AIR COMPRESSOR BRACKET DURING ROUTINE POSTFLIGHT INSPECTION. BELT TENSION AND ALIGNMENT WAS INSPECTED AT THE LAST PHASE INSPECTION PERFORMED AT 299.7 HRS. AIRCRAFT TT 3064.5, LANDINGS 3146. UNIT LOCATION IS OB OF RT POWERPLANT NACELLE. SUGGEST ADDING PREPOST FLIGHT VISUAL INSPECTION TO FLIGHT CHECKLIST MAINTENANCE PROCEDURES. (K)

NUMBER TWO DISPLAY UNIT FAILED AND CABIN WAS FILLED WITH SMOKE. REMOVED AND REPLACED NUMBER TWO DISPLAY UNIT.

NOSE LANDING GEAR UNSAFE LIGHT STAYED ON. FOUND STRUT LOW, SERVICED STRUT.

UNIT SUSTAINED A MAIN BEARING ARMATURE DRIVE SHAFT FAILURE DURING FLIGHT. THE NR1 MAIN GENERATOR WARNING LIGHT ENUNCIATOR ILLUMINATED THE ARMATURE, DRIVE BALL DRIVESHAFT, AND BEARING FLANGE ARE NON-SERVICEABLE. THE ORIGINAL OVERHAUL PERIOD (TBO), FOR THIS UNIT IS 900 FLIGHT HOURS. THE AIR OPERATOR HAS NOW ELECTED TO REDUCE THE TBO OF THE UNIT TO 600 HRS.

SEAT 13D EMERGENCY EXIT ROW DOOR HAS A WIRE HANGING OUT OF LOWER PANEL. RESECURED WIRE.

LIGHTNING STRIKE DAMAGE TO TAILCONE BOTTOM RIGHT EDGE. NO OTHER INFORMATION AT THIS TIME WAITING FOR FIX.

RUDDER LIMIT FAULT ON ENGINE AND ALERT DISPLAY AND CONTROL COLUMN DISCONNECTED. PERFORMED FAULT ISLOATION MANUAL TASK OR RETURNED TO SERVICE WORK, LIGHTNING STRIKE OVERSPEED, CONTROL COLUMN DISCONNECTED, RUDDER LIMITER, ADJUSTED AIR DATA INERTIAL REFERENCE UNIT, ENGINE ELECTRICAL CONTROLLER, VERSATILE INTERGRATED AVIONICS, PITOT STATIC CHECK OF CAPTAIN AND F/O'S ALTERNATE SYSTEM. NTSB REQUIRED REMOVED AND REPLACED AIR DATA INERTIAL REFERENCE NR 1 & NR 2, FLIGHT CONTROL COMPUTER NR 1 & NR 2 AND GROUND PROXIMITY WARNING SYSTEM COMPUTER. RE-SUBMITTED REJECTED SDR ORIGINALY MWEA050043.

AUTO THROTTLES FAILED TO ADVANCE, SET POWER MANUALLY, THEN V SPEED INDICATIONS WERE LOST. PERFORMED RETURN TO SERVICE TEST, FOR FLIGHT CONTROL COMPUTER AND ENGINE ELECTRONIC CONTROLLER. PASSED, AIR DATA INTERTIAL REFERENCE SYSTEM CHECKS GOOD. OK FOR SERVICE.

LOW SPEED HIGH PROTECTION CAME ON TOGETHER AND STICK SHAKER. PERFORMED ADJUSTMENT TEST OF NUMBER 1 FLIGHT CONTROL COMPUTER AND NR 2 FLIGHT CONTROL COMPUTER STALL WARNING SYSTEM BOTH PASSED STALL WARNING CHECK.

ENGINE STARTED AND GENERATOR CAME ON LINE ALERTS BUS TIE LEFT AND RIGHT LOCKOUT EMERGENCY POWER ON BUS AC GROUND SPEED OFF ILLUMINATED. REMOVED AND REPLACED EMERGENCY BATTERY CHARGER.

GROUND SPOILER WOULD NOT ARM. PERFORMED RETURN TO SERVICE TEST. ALL TEST PASSED, OK FOR SERVICE.

GROUND SPOILER WOULD NOT ARM. REMOVED AND REPLACED SPEED BRAKE MODULE.