N27465

Part: MECHANISM — LACK OF LUBE (MCD CLICK CLACK)

THE CARGO DOOR WARNING LIGHT CAME ON DURING CLIMB AT 11,000 FEET, CREW FOLLOWED CHECKLIST PROCEDURES AND RETURNED TO STATION. DESCENDING THROUGH 6,000 FT, THE CARGO DOOR LIGHT WENT OUT. CREW LANDED WITH NO FURTHER INCIDENT. INSPECTED CARGO DOOR CLICK CLACKS AND BAYONETS IN GOOD CONDITION, BUT SUSPECTED THAT THEY WERE DRY. CLICK CLACKS AND BAYONETS WERE THEN LUBRICATED. GROUND PRESSURIZATION CHECK TO 7 PSID WAS PERFORMED, NO PROBLEMS WERE NOTED. (M)

Part: SENSOR — OUT OF ADJUST (CARGO DOOR)

THE CARGO DOOR WARNING LIGHT CAME ON DURING CLIMB TO ALTITUDE, CREW FOLLOWED CHECKLIST PROCEDURES AND RETURNED TO STATION. CREW LANDED WITH NO FURTHER INCIDENT. PERFORMED RIG CHECK OF CLICK CLACKS USING STUN1-5 TASK CARD, ADJUSTED LOWER FORWARD CLICKCLACK, AND LOWER CLICKCLACK SWITCHES. PERFORMED AN EXTENSIVE OPERATOINAL CHECK FLIGHT TO VERIFY OPERATION OF CARGO DOOR, WENT TO MAXIMUM DIFFERENTIAL CABIN PRESSURE, SYSTEM OPS CHECK GOOD. (M)

Part: HANDLE — STUCK (CARGO DOOR)

FLT 1303 - HOT - JUST AFTER TAKEOFF UPON ROTATION, THE CARGO DOOR WARNING LIGHT CAME ON. CREW DID A GO AROUND AND RETURNED TO STATION. STICKY HANDLE OR CLICK, OR DOOR CLOSING PROCEDURES. CLEANED AND LUBED CLICK CLACKS. (M)

Part: LATCH — STUCK (CARGO DOOR)

JUST AFTER TAKEOFF UPON ROTATION, THE CARGO DOOR WARNING LIGHT CAME ON. CREW DID A GO AROUND AND RETURNED TO STATION. STICKY HANDLE OR CLICK CLACKS, OR DOOR CLOSING PROCEDURES. CLEANED AND LUBED CLICK CLACKS. (M)

Part: LINE — LEAKING (HYD SYSTEM)

DFW - FLT 1302 - ONE HUNDRED THIRTY MILES FROM ORGINATING STATION, AIRCRAFT LOST HYDRAULIC PRESSURE. CREW RETURNED TO STATION AT MAX GEAR EXTENSION SPEED. GEAR WAS PUMPED DOWN USING EMERGENCY CHECKLIST. HYDRAULIC LEAK CAUSED LOSS OF HYDRAULIC FLUID LEADING TO LOSS OF HYDRAULIC PRESSURE. REPAIRED LINE BY SPLICING IN NEW SECTION PER MM. BOTH HYDRAULIC PUMPS CHANGED DUE TO EXCEEDING MM RESTRICION ON LENGTH OF TIME THE PUMPS CAN RUN WITHOUT FLUID. (M)

Part: LINE — LEAKING (HYD SYSTEM)

130 MILES FROM ORIGINATING STATION, AIRCRAFT LOST HYDRAULIC PRESSURE. CREW RETURNED TO STATION AT MAX GEAR EXTENSION SPEED. GEAR WAS PUMPED DOWN USING EMERGENCY CHECKLIST. HYDRAULIC LEAK CAUSED LOSS OF HYDRAULIC FLUID LEADING TO LOSS OF HYDRAULIC PRESSURE. REPAIRED LINE BY SPLICING IN NEW SECTION PER MM. BOTH HYDRAULIC PUMPS CHANGED DUE TO EXCEEDING MM RESTRICTION ON LENGTH OF TIME THE PUMPS CAN RUN WITHOUT FLUID. (M)

Part: HYDRAULIC LINE — DAMAGED (HYD SYSTEM)

FLT 1302 - DFW - 130 MILES FROM ORIGINATING STATION, AIRCRAFT LOST HYDRAULIC PRESSURE. CREW RETURNED TO STATION AT MAX GEAR EXTENSION SPEED. GEAR WAS PUMPED DOWN USING EMERGENCY CHECKLIST. HYDRAULIC LEAK CAUSED LOSS OF HYDRAULIC FLUID LEADING TO LOSS OF HYDRAULIC PRESSURE. REPAIRED LINE BY SPLICING IN NEW SECTION PER MM. BOTH HYDRAULIC PUMPS CHANGED DUE TO EXCEEDING MM RESTRICTION ON LENGTH OF TIME THE PUMPS CAN RUN WITHOUT FLUID. (M)

Part: RUDDER PEDAL — CRACKED (COCKPIT)

MAINTENANCE FOUND PILOTS RIGHT RUDDER PEDAL CRACKED DURING COCKPIT INSPECTION. FATIGUE OR EXCESSIVE FORCE. REPLACED RUDDER PEDAL. (M)

Part: PIN — BROKEN (RT MLG)

RIGHT MLG UPPER TORQUE LINK PIN BROKE IN TWO PLACES. REPLACED BROKEN PIN, INSPECTED GEAR, ATTACH TRUNNION, KEELSON WEBS, DRAG LINK ATTACH EARS, AND PERFORMED GEAR SWING. NO DEFECTS NOTED. ONE FRACTURE PLANE EXTENDED THROUGH APPROX 25 PERCENT OF THE PIN, THIS IS THE SUSPECTED ORIGINAL FRACTURE. IT IS SUSPECTED THAT THE INITIAL FRACTURE PLANE GREW UNTIL THE REMAINING CROSS SECTION OF THE PIN WASN'T SUFFICIENT TO MAINTAIN INTEGRITY. AT THAT TIME THE REMAINING CROSS-SECTION OF THE ONE END OF THE PIN FAILED. THIS IS THE SUSPECTED ORIGINAL BREAKAGE POINT. WHEN THIS HALF OF THE PIN FAILED, THE OTHER SIDE WAS SUBJECTED TO SUCH A HIGH LOAD THAT IT COMPLETELY FAILED AT ONE TIME, DURING THE LAST LANDING. (M)

Part: PIN — BROKEN (RT MLG)

ON LANDING ROLL OUT, THE AIRCRAFT STARTED VIBRATING AND PULLING TOWARD THE RIGHT SIDE OF THE RUNWAY. THE AIRCRAFT STAYED ON THE RUNWAY AND WAS BROUGHT TO A FULL STOP. INVESTIGATION REVEALED THAT THE RIGHT MAIN GEAR WAS COCKED OFF TO THE SIDE 30 TO 45 DEGREES. TROUBLE TRACED TO UPPER RIGHT TORQUE LINK PIN BROKEN IN TWO PLACES. THE -001 PIN WAS REPLACED BY A -003 PIN AND HAS TWO ADDITIONAL HOLES DRILLED IN THE PIN. THE FAILED PIN SHOWS TWO AREAS OF POSSIBLE EXISTING CRACKS OR FLAWS. WHEN ONE SIDE OF THE PIN FAILED, THE OTHER SIDE WAS SUBJECTED TO HIGH STRESS CAUSING IT TO FAIL. (M)

Part: PIN — BROKEN (RT MLG)

GEAR WAS COCKED TO THE SIDE BETWEEN 30 AND 45 DEGREES. CREW THOUGHT THEY HAD A FLAT TIRE BEFORE THEY GOT OUT OF THE AIRCRAFT. RIGHT MLG UPPER TORQUE LINK PIN BROKE IN TWO PLACES. PIN BROKE AT THE TWO ADDITIONAL HOLES THAT AREN'T USED FOR THIS INSTALLATION. THE OLDER 001 PIN ONLY HAD THE ONE HOLE FOR THE ROLL PIN. THE 001 PIN HAS BEEN REPLACED BY THE 003 PIN. HAVE NOT RECEIVED THE PIN FROM THE OUTSTATION YET TO TRY AND DETERMINE THE FAILURE MODE/CAUSE ON THE TORQUE LINK PIN. REPLACED BROKEN PIN, INSPECTED GEAR, ATTACH TRUNNIONS, KEELSON WEBS, DRAG LINK ATTACH EARS, AND PERFORMED GEAR SWING. NO DEFECTS NOTED. (M)

Part: LINE — CHAFED (HYD SYSTEM)

MWH - FLT 6003 - THE CREW NOTICED A SMELL AND RED HAXE IN THE COCKPIT. IMMEDIATELY AFTER THAT BOTH HYD PRESSURE LIGHTS CAME ON AND HYDRAULIC PRESSURE DROPPED TO 0. THE GEAR WAS MANUALLY EXTENDED. THE CREW RETURNED TO STATION WITH NO FURTHER PROBLEMS. HYDRAULIC PRESSURE WAS LOST DUE TO HYDRAULIC LEAK. FOUND LINE CHAFED THROUGH IN THE AREA UNDER THE J BOX. LINE DIDN'T LEAK UNTIL FULL SYSTEM PRESSURE WAS APPLIED. LINE WAS REPAIRED BY SPLICING. (M)

Part: WARNING LIGHT — ILLUMINATED (COCKPIT)

FLT 1325 - BWD - DURING CLIMB-OUT, THE RIGHT WING OVERHEAT LIGHT CAME ON. THE LIGHT WENT OUT WHEN LANDING GEAR WAS EXTENDED FOLLOWING THE EMERGENCY CHECKLIST. CREW RETURNED TO STATION. NO APPARENT MECHANICAL CAUSE. THIS TEMP SENSOR IS LOCATED IN THE WHEEL WELL FORWARD OF THE MASS FLOW VALVE, APPROXIMATELY THE LEADING EDGE OF THE TIRES. IF THE BRAKES WERE HOT, AND FULL HEAT IS SELECTED, IT IS POSSIBLE THAT THE COMBINATION OF HEAT SOAKED BRAKES AND THE HOT BLEED AIR IN THE BLEED AIR LINE GOING TO THE MASS FLOW VALVE REACHED THE TRIP POINT FOR THE WING OVERHEAT SENSOR. MAINTENANCE WAS DISPATCHED, INSPECTED WINGS FOR SIGNS OF OVERHEAT, BLEED AIR LEAKS, AND DAMAGED WIRING. NONE WAS FOUND. NO FURTHER DISCREPA

Part: CONNECTOR — CORRODED (BATTERY SYSTEM)

BIL - FLT 2585 - RIGHT BATTERY OVERHEAT LIGHT CAME ON ABOUT 20 MINUTES AFTER DEPARTURE WHILE CLIMBING. CREW FOLLOWED EMERGENCY CHECKLIST PROCEDURES. CREW RETURNED TO STATION WITH NO FURTHER PROBLEMS. BATTERY WAS COOL TOUCH, SUSPECT WIRING PROBLEM. REPLACED CORRODED AIRFRAME SIDE CANNON PLUG. SYSTEM OPS CHECKED GOOD. (M)

Part: TURBINE — FAILED (LT ACM)

FLT 2584 - AFTER LANDING, THE CABIN STARTED TO FILL WITH SMOKE. THE CREW SHUT OFF BOTH BLEEDS. IT WAS DETERMINED THAT THE LEFT ACM COOLING TURBINE HAD FAILED. LEFT ACM COOLING TURBINE FAILED. (M)

Part: RIB — CRACKED (WS 81)

DURING TURN-BACK INSPECTION, A CRACK WAS FOUND IN THE WING RIB LOWER FLANGE AT WS 81 WITHIN THE RT BATTERY BOX. REPAIR WAS COMPLETED BY INSTALLING A REPAIR DOUBLER IAW AEROTECH DESIGNS E.O. NR 01-96125. (X)

Part: FRAME — WORN (PAX DOORWAY)

DURING TURNBACK INSPECTION, CABIN DOOR FUSELAGE FRAME WAS FOUND TO HAVE A WORN AREA WHERE THE CABIN DOOR TEFLON GUIDE CONTACTS THE DOOR FRAME ON THE FORWARD LOWER DOOR FRAME. DAMAGED AREA INSPECTED AND FOUND TO BE OUT OF LIMITS. REPAIRS COMPLETED PER ARP 53-20-9116 FAIRCHILD AIRCRAFT STRUCTURAL REPAIR MANUAL 53-90-20. (M)

Part: HEAT DUCT — MALFUNCTIONED (LT OIL COOLER)

FLT 2997 - DURING FLIGHT, LEFT OIL COOLER DUCT HEAT WOULD NOT OPERATE. PULLED AND RESET CIRCUIT BREAKER WITH NO CHANGE. FLIGHT RETURNED TO DTW. MAINTENANCE INSPECTED OIL COOLER DUCT HEAT AND CANNON PLUG. NO DEFECTS NOTED. MAINTENANCE PERFORMED FUNCTIONAL CHECK IAW SA-227 MM 30-20-10. ALL CHECKS GOOD. (M)

Part: INTERCOSTAL — CRACKED (BS 287)

DURING A BLOCK INSPECTION IN MSP, MAINTENANCE FOUND A .25 INCH CRACK IN LEFT INTERCOSTAL RELIEF RADIUS AT LOWER FS 287. COMPLETED REPAIR TO THE LEFT LOWER INTERCOSTAL IAW AERO TECH DESIGNS EA 01-96136. (X)

Part: RIB — CRACKED (TE FLAP)

DURING A BLOCK INSPECTION IN MSP, FOUND A CRACK IN RIGHT FLAP, S/N C-171, OUTBOARD FLAP NOSE RIB. (X)

Part: SKIN — CRACKED (RT TE FLAP)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE FOUND THREE CRACKS ON RT FLAP UPPER SKIN SURFACE P/N 27-36000. TWO AT WS 39.134, BOTH 1 INCH LONG AND 1 AT WS 51.167, .50 INCH LONG. INSTALLED PERMANENT REPAIR DOUBLER PER FAC SRM 57-90-60, FIGU 10, PAGES 19-21. (X)

Part: INTRANSIT LIGHT — FAILED (LT MLG)

FLT 3135 - ON APPROACH TO MSP, THE LEFT GEAR INTRANSIT LIGHT FAILED TO ILLUMINATE. ALL OTHER INDICATIONS WERE NORMAL. MAINTENANCE WAS UNABLE TO DUPLICATE THE DISCREPANCY. THE GEAR POSITION SWITCHES WERE CLEANED AND LUBED. ALL CHECKS SATISFACTORY. (M)

Part: UPLIMIT SW — OUT OF ADJUST (NLG)

DURING A MAINTENANCE TEST FLIGHT IN MSP, THE NOSE GEAR BEGAN TO CYCLE IN THE GEAR WELL AND THE RED INTRANSIT LIGHT ILLUMINATED. THE AIRCRAFT LANDED IN MSP WITHOUT FURTHER INCIDENT. MAINTENANCE ADJUSTED THE NOSE GEAR UPLIMIT POSITION SWITCHES. SYSTEM OPERATED SATISFACTORILY. (M)

Part: FRAME — CRACKED (FS 189)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER LEFT BELT FRAME FLANGE AT FS 189. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: FRAME — CRACKED (FS 197.27)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER LEFT BELT FRAME FLANGE AT FS 197.27. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: FRAME CORNER — CRACKED (PAX DOOR)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER FORWARD PASSENGER DOOR FRAME CORNER. THEY REPLACED THE CORNER IAW FAC SRM 51-40-01 AND 02. (M)

Part: FRAME — CRACKED (FS 212)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER LEFT BELT FRAME AT FS 212. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: SKIN — DENTED (FS 438.06)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A DENT IN THE FUSELAGE SKIN AT FS 438.06 AND WL 75.13. THEY FABRICATED AND INSTALLED AN EXTERNAL DOUBLER IAW 53-90-20. (M)

Part: FRAME — CRACKED (FS 212)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER RIGHT BELT FRAME AT FS 212. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: FRAME — CRACKED (FS 227)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER LEFT BELT FRAME AT FS 227. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: FRAME — CRACKED (FS 347.271)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER RIGHT BELT FRAME AT FS 347.271. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A DOUBLER IAW FAC SRM 53-90-20. (M)

Part: FRAME — CRACKED (FS 174.06)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE PERSONNEL NOTED A CRACK IN THE LOWER BELT FRAME AT FS 174.06. THEY STOP DRILLED THE CRACK AND FABRICATED AND INSTALLED A REPAIR DOUBLER IAW FAC SRM 53-90-20. (M)

Part: CORNER — PUNCTURED (FS 133.87)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE FOUND THE FORWARD LOWER PASSENGER DOOR FUSELAGE AT FS 133.87 TO BE DAMAGED. REPAIRS WERE COMPLETED BY REPLACING THE FORWARD LOWER CORNER, P/N 27-24087-901, IAW FAC SRM 51-00-00 PAGE 4, 51-40-02 AND 51-30-04. (M)

Part: SELECTOR — MALFUNCTIONED (LANDING GEAR)

FLT NR 3379 - ON APPROACH TO DTW, THE GEAR WOULD NOT EXTEND ON COMMAND. THE GEAR EXTENDED NORMALLY AFTER THE CREW RESET THE LANDING GEAR CONTROL CIRCUIT BREAKER. MAINTENANCE WAS UNABLE TO DUPLICATE THE DISCREPANCY. AS A PRECAUTION, THE GEAR SELECTOR CONTROL, P/N 709201-1, WAS REPLACED. SYSTEM OPERATED SATISFACTORILY. (M)

Part: SWITCH — OUT OF ADJUST (NLG)

FLT NR 3360 - AFTER THE LANDING GEAR WAS RETRACTED ON TAKEOFF FROM DTW, THE NOSE GEAR UNSAFE LIGHT ILLUMINATED. THE AIRCRAFT RETURNED TO DTW AND LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL ADJUSTED THE NOSE GEAR UP POSITION SWITCH. ALL SYSTEMS OPERATED SATISFACTORILY. (M)

Part: GEAR LIGHT — MALFUNCTIONED (NLG)

FLT NR 3463 - EN ROUTE TO DTW, THE CREW NOTED GEAR INTRANSIT INDICATIONS FROM THE NOSE GEAR. THE AIRCRAFT CONTINUED TO DTW AND LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL INSPECTED AND FUNCTIONALLY TESTED THE GEAR INDICATION SYSTEM BUT WERE UNABLE TO DUPLICATE THE DISCREPANCY. ALL SYSTEMS OPERATED SATISFACTORILY. (M)

Part: DOOR FRAME — CRACKED (FS 491.06)

DURING A SCHEDULED INSPECTION IN MSP, MAINTENANCE FOUND THE FUSELAGE/CARGO DOOR LEFT FRAME CRACKED AT GAS STRUT MOUNT POST HOLE AT FS 491.060. REPAIRS WERE COMPLETED BY INSTALLING A REPAIR ANGLE IAW ARP 53-20-9503. (M)

Part: ANGLE — CRACKED (LEFT NACELLE)

DURING A SCHEDULED INSPECTION IN MSP, THE LEFT INBOARD WING TO NACELLE TRANSIT ANGLE WAS CRACKED. REPAIRS WERE COMPLETED BY STOP DRILLING THE CRACK AND INSTALLING A REPAIR DOUBLER IAW ARP 54-20-9101. (M)

Part: POSITION SWITCH — FAILED (RT MLG)

FLT 3271 - MSP - DURING APPROACH, LT MAIN GEAR INTRANSIT LIGHT DID NOT ILLUMINATE WHEN GEAR WAS SELECTED DOWN. THE FLIGHT CONTINUED TO MSP WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE LT MAIN LANDING GEAR UP POSITION SWITCH. THE SYSTEM OPERATED SATISFACTORILY. (W)

Part: GCU — FAILED (LT ENGINE)

MSP/YQT - FLT 3084 - IN CRUISE FLIGHT TO YQT, THE LEFT GENERATOR FAIL LIGHT ILLUMINATED. THE CREW WAS UNABLE TO RESET THE GENERATOR. THE AIRCRAFT RETURNED TO MSP. MAINTENANCE REPLACED THE LEFT GENERATOR CONTROL UNIT. SYSTEM OPERATED SATISFACTORILY. (X)

Part: TRANSDUCER — FAILED (LT ENG OIL PRESS)

FLT 3218 - ON CLIMB-OUT FROM MSP, THE LEFT ENGINE OIL PRESSURE BEGAN TO FLUCTUATE. THE AIRCRAFT RETURNED TO MSP. MAINTENANCE REPLACED THE LEFT OIL PRESSURE TRANSDUCER. SYSTEM OPERATED SATISFACTORILY. (W)

Part: LE SKIN — CHAFED (RT TE FLAP)

DURING PHASE INSPECTION IN MSP, MAINTENANCE FOUND THE RT FLAP CHAFED AT LEADING EDGE SKIN OUTBOARD END. REPAIRED CHAF DAMAGED ITEMS (2) TO LEADING EDGE FORWARD OF FRONT SPAR AT WS 160.00. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED DOUBLER REPAIRS IAW FAIRCHILD SRM 57-90-60, REV NOV 1/94 PGS 11-14. (W)

Part: FRAME — CRACKED (FS 212.27)

MSP - DURING SCHEDULED MAINTENANCE INSPECTION, MAINTENANCE FOUND RT LOWER BELT FRAME, PN 27-22104-047 AT FS 212.27, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW FAIRCHILD SRM. (X)

Part: FRAME — CRACKED (FS 174.060)

MSP - DURING SCHEDULED MAINTENANCE FOUND RT LOWER BELT FRAME, PN 27-22093-145 AT FS 174.060, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW FAIRCHILD SRM. (X)

Part: ANGLE — CRACKED (LT WING)

MSP - DURING SCHEDULED INSPECTION, MAINTENANCE FOUND THE INBOARD, UPPER WING SKIN TO NACELLE ATTACH ANGLE, PN 27-35112-026, CRACKED AT LT NACELLE. COMPLETED REPAIR TO THE ATTACH ANGLE IAW FAIRCHILD ARP 54-20-9101, REV B AND THE SRM. (X)

Part: DOUBLER — WORN (WS 27.103)

MSP - DURING SCHEDULED INSPECTION - MAINTENANCE FOUND THE SUPPORT DOUBLER, PN 27-31141-001, FOR THE LT FLAP WALKING BEAM ROLLER BEARING AT WS 27.103 WORN. COMPLETED REPAIR BY THE PART FOR PART REPLACEMENT OF THE DOUBLER IAW THE FAIRCHILD SRM AND ARP 57-20-9424. (X)

Part: FRAME — CRACKED (FS 227.27)

MSP - DURING A SCHEDULED MAINTENANCE INSPECTION, MAINTENANCE FOUND THE LT LOWER BELT FRAME, PN 27-22093-155 AT FS 227.27, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW FAIRCHILD SRM. (X)

Part: FRAME — CRACKED (FS 159.247)

MSP - DURING A SCHEDULED INSPECTION, MAINTENANCE FOUND RT LOWER BELT FRAME, PN 27-22093-146 AT FS 159.247, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW THE FAIRCHILD SRM. (X)

Part: FRAME — CRACKED (FS 144.24)

MSP - DURING MAINTENANCE INSPECTION, MAINTENANCE FOUND RT LOWER BELT FRAME, PN 27-22093-146 AT FS 144.24, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW FAIRCHILD SRM. (X)

Part: FRAME — CRACKED (FS 197.27)

MSP - DURING A SCHEDULED INSPECTION, MAINTENANCE FOUND THE LT LOWER BELT FRAME, PN 27-22093-153 AT FS 197.27, CRACKED AT THE UPPER OUTBOARD FLANGE RELIEF RADIUS. COMPLETED REPAIR TO THE LOWER BELT FRAME IAW THE FAIRCHILD SRM. (X)

Part: DNLOCK SW — FAILED (RT MLG)

FLT 3198 - ON CLIMB-OUT FROM DSM, THE RIGHT GEAR INTRANSIT LIGHT FAILED TO ILLUMINATE UPON RETRACTION. ALL OTHER GEAR INDICATIONS WERE NORMAL. ON APPROACH TO MSP, THE RIGHT GEAR INTRANSIT LIGHT ALSO FAILED TO ILLUMINATE DURING GEAR EXTENSION. MAINTENANCE REPLACED THE RIGHT INBOARD DOWNLOCK SWITCH. SYSTEM OPERATED SATISFACTORILY. (Z)

Part: POSITION — INTERNAL FAULT (NLG WW)

FLT 3495 - AFTER TAKEOFF FROM MSP, THE RED NOSE GEAR INTRANSIT LIGHT FAILED TO ILLUMINATE UPON GEAR RETRACTION. THE BULB TESTED GOOD. THE AIRCRAFT RETURNED TO MSP. MAINTENANCE REPLACED THE NOSE LANDING GEAR POSITION SWITCH. SYSTEM OPERATED SATISFACTORILY. (Z)