N57SF

ATA 2436

UPON INITIATING START OF THE LT ENGINE, NOTHING HAPPENED. NONE OF THE LT ENGINE INSTRUMENTS HAD POWER AND THERE WERE SEVERAL OTHER SYSTEMS THAT WOULD NOT OPERATE AS WELL. INVESTIGATION REVEALED LT MAIN CURRENT LIMITER (FL1) HAD FAILED. NO OVERHEATING AT THE LIMITER WAS EVIDENT. CURRENT LIMITER WAS REPLACED. POWER UP INSPECTION WAS MADE AND A NORMAL START INITIATED WITH NO ANOMALIES DETECTED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE AFTER A FULL, ENGINES RUNNING, SYSTEMS CHECK.

ATA 2432

CREW WENT TO PERFORM A PREFLIGHT INSPECTION AND DISCOVERED THE BATTERY VOLTAGE WAS AT APPROXIMATELY 22.5 VOLTS AND THE BATTERY HOT LIGHT WAS ILLUMINATED. AFTER APPROXIMATELY 3.5 HRS THE BATTERY HAD COOLED TO A USEABLE TEMPERATURE. PRIOR TO THE NEXT FLIGHT, AS A PRECAUTION, THE BATTERY WAS REMOVED FOR INSPECTION AND A SERVICEABLE UNIT INSTALLED. THE REMOVED BATTERY WAS INSPECTED, DEEP CYCLED AND IS NOW APPROVED FOR RETURN TO SERVICE WITH NO DEFECTS NOTED. THE CAUSE OF THE OVERHEAT CONDITION IS BELIEVED TO BE THAT THE GPU PLUG WAS NOT FULLY INSERTED INTO THE AIRCRAFT ALLOWING FOR THE HIGH CURRENT DRAW OF THE AIR CONDITIONER TO BE DRAWN DIRECTLY FROM THE BATTERY. TO PREVENT A FUTURE OCCURRENCE, THE FLIGHT CREWS HAVE BEEN INSTRUCTED TO DISCONNECT THE SHIP’S BATTERY IF A GPU IS TO BE CONNECTED FOR ANYTHING OTHER THAN ENGINE START.

ATA 2910

ON ROLLOUT AFTER LANDING THE CREW HAD NO BRAKING. EMERGENCY BRAKES AND THRUST REVERSER WERE OPERATIONAL. THE AIRCRAFT SAFELY SLOWED AND TAXIED TO THE RAMP UTILIZING THRUST REVERSERS TO CONTROL AIRCRAFT SPEED, THEN CHOCKS WERE APPLIED. THE CREW DISCOVERED A SIGNIFICANT AMOUNT OF HYDRAULIC FLUID COMING FROM THE MID-FUSELAGE BELLY DRAINS. INVESTIGATION REVEALED A DAMAGED RT BRAKE LINE (ALUMINUM TUBING) AT APPROXIMATE FUSELAGE STATION NR 175.0 UNDERNEATH THE CABIN CENTER FLOOR, AND THE BRAKE RESERVOIR WAS DEPLETED. THE LINE WAS SLIGHTLY BENT/MISALIGNED ALLOWING THE LT ELEVATOR CABLE TO RUB ON IT, EVENTUALLY WEARING THROUGH THE TUBING WALL. THE TUBING WAS REPAIRED BY REPLACING THE DAMAGED SECTION OF TUBING. THE LINE WAS REPOSITIONED TO PREVENT FURTHER CHAFING AND THE RESERVOIR WAS SERVICED. AIR WAS BLED FROM THE SYSTEM AS NECESSARY AND THE BRAKE SYSTEM OPERATIONALLY AND LEAK CHECKED SATISFACTORY. FLUID WAS FLUSHED/CLEANED FROM THE BELLY OF THE FUSELAGE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. AFTER INITIALLY LEARNING OF THE FLUID LEAK, AN INSPECTION OF THE DEPARTURE RAMP AREA REVEALED EVIDENCE OF THE LEAK PRIOR DEPARTURE. HOWEVER, IT WAS MINOR COMPARED TO AMOUNT OF FLUID NOTICED AFTER LANDING, THE CREW VERIFIED THAT THE RESERVOIR INDICATED FULL DURING THE PREFLIGHT, WHICH SUGGESTS THE LINE BEGINNING TO LEAK AT TIME OF DEPARTURE. IT IS BELIEVED THAT, DUE TO THE FACT THAT THE CREW HAD BRAKING PRIOR TO TAKEOFF, TOTAL FAILURE OF THE LINE MOST LIKELY OCCURRED EITHER DURING TAXI FOR TAKEOFF, OR AFTER TAKEOFF, WITH TOTAL RESERVOIR DRAINAGE OCCURRING IN FLIGHT. THE RESERVOIR IS PRESSURIZED WITH CABIN PRESSURIZED AIR WHEN IN FLIGHT WHICH WOULD ACCELERATE THE LEAK. THIS AREA OF THE AIRCRAFT ONLY GETS INSPECTED DURING A PHASE 5 INSPECTION WHICH IS EVERY 1200 HRS OR 36 MONTHS, WHICHEVER OCCURS FIRST. SUGGEST MAINTENANCE SHOPS/PERSONNEL PERFORM MORE DETAILED INSPECTION OF AREAS AFTER INSPECTION/MAINTENANCE, PRIOR TO REINSTALLING PANELS.

ATA 3246

ON LANDING, ENCOUNTERED SEVERE CROSSWIND GUSTS CAUSING ACFT TO YAW ON TOUCHDOWN. AFTER A SUCCESSFUL LANDING, NOTED A SEVERE SWAYING OF THE NLG & VIBRATION FELT IN RUDDER PEDALS. ACFT STOPPED & DISCOVERED THE NLG TIRE BLOWN & RIMS BROKEN OFF. AT THE HANGER NOTED A SMALL DENT/SCRATCH ON EACH INBOARD HEATED LEADING EDGE. BOTH ENGINES WERE INSPECTED. RT ENGINE FOUND TO HAVE DAMAGE TO ROUGHLY HALF OF THE FAN BLADES FROM PIECES OF WHEEL RIM ENTERED. LT ENGINE NO DAMAGE. RT ENGINE DAMAGE LIMITED TO FAN BLADES, FAN SHROUD, FAN STATOR, AND ITT SENSOR. NO DAMAGE FOUND IN THE CORE. SOME SHEET METAL DAMAGE NOTED ON AFT EDGE OF INLET. FURTHER INSPECTION MADE ON REMAINDER OF ACFT & MINOR DAMAGE NOTED ON BOTH HEATED LEADING EDGES, A MINOR DENT WAS DISCOVERED UNDER THE FUSELAGE JUST AFT, AND TO LT OF NLG WW. LT LANDING LIGHT LENS CRACKED FROM IMPACT, & MINOR CHIP NOTED ON UNDERSIDE OF RT FLAP. THE WHEEL/TIRE ASSY REPLACED. DAMAGED FAN BLADES & ITT SENSOR ARE TO BE REPLACED AND THE FAN SHROUD & STATOR WILL BE REPAIRED AS NECESSARY. THE NDT INSPECTION ON THE REMOVED WHEEL WAS DUE AT THE NEXT TIRE CHANGE. A VISUAL INSPECTION AT THE PREVIOUS TIRE CHANGE SHOWED NO DEFECTS. WHEEL HAD 92 LANDINGS SINCE PREVIOUS TIRE CHANGE. IT IS BELIEVED THE CAUSE OF THE FAILURE IS DUE TO EXCESSIVE SIDE LOADING ON THE NOSE WHEEL DUE TO UNEXPECTED AND SEVERE WIND SHEAR UPON LANDING.

ATA 3244

THE INTERNAL BALANCE WEIGHT/PATCH BECAME LOOSE FROM THE NOSE TIRE CAUSING AN UNBALANCED CONDITION OF THE TIRE/WHEEL ASSEMBLY.