N925HA

Part: ANGLE — CRACKED (NR 2 NACELLE) · airframe 35,114 hrs · 39,740 cycles

NR 2 NACELLE HORSE COLLAR WAS FOUND CRACKED IN RADIUS OF FWD UPPER CLOSING ANGLE JUST ABOVE ENGINE HOIST ATTACH BRACKET. REPAIRED PER EO8-54-01-799.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 34,113 hrs · 38,658 cycles

EMERGENCY LIGHTS OUT NR 3 & 4, FRONT RED LIGHTS. REMOVED AND REPLACED EMERGENCY LIGHTS BATTERY BASE.

Part: LIGHT — INOPERATIVE (CABIN)

NUMBER 1 EMERGENCY FLOOR PATH LIGHT INOP. REPLACED LAMEP MODULE.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 32,379 hrs · 36,775 cycles

DURING AN UNRELATED INSPECTION FOUND THE KEEL STRUCTURE ANGLE AND WEB UNDER L/H CENTER SEAT RAIL AT STA 405.737 CRACKED FROM PREVIOUS IMPACT DAMAGE. PERFORMED MAJOR REPAIR TO STRUCTURE IAW PIEDMONT EO8-53-00-710.

Part: ENGINE — OUT OF RIG (NR 1) · airframe 32,136 hrs · 36,513 cycles

NR 1 ENGINE POWER LEVER WOULD NOT ADVANCE PAST 82 PERCENT TORQUE. AIRCRAFT RETURNED TO THE FIELD. RIGGED AND TRIMMED NR 1 ENGINE.

Part: SHROUD — CRACKED (NR 1 ENG EXHAUST)

NR 1 ENGINE EXHAUST SHROUD HAS 1 INCH CRACK STA 223.4 AT 4 O'CLOCK POSITION, REAR I/B MOUNT BOLT OF FORWARD RADIATION SHIELD IS PULLED THROUGH, REAR O/B ANGLE BRACKET 1.5 INCH CRACK STA XN276.50, OUTLET SHROUD RING 5 CRACKS AT RIVETS STA XN221.25 FROM 4 TO 6 O'CLOCK POSITIONS, DIAPHRAGM BRACKET STA XN236.50 2 INCH CRACK AT THE 8 O'CLOCK POSITION AND 1 INCH CRACK AT 6 O'CLOCK POSITION, .5 INCH CRACK STA XN240 AND 1 INCH CRACK STA XN275.50 ON O/B SIDE SKIN BRACKET, 3 INCH HOLE CHAFED IN CENTER RADIATION SHIELD STA 237.00, 6TH AND 7TH FRAME TO EXHAUST PLATE L ANGLES CRACKED, 3RD FRAME STA XN227.35 CRACKED, LOOSE RIVETS ON 3RD FRAME L ANGLE STA XN227.25, FRAME STA 236.50 CRACKED AT 4, 6 AND 8 O'CLOCK POSITIONS. RE

Part: EEL POWER SUPPLY — INOP (CABIN)

FLT NR 3040 - FLL TO TPA - DURING PREFLIGHT WALKAROUND, FOUND THE FIRST 2 RED FLOOR EMERGENCY LIGHTS INOP. REMOVED AND REPLACED THE POWER SUPPLY AT 3352-PS2. (M)

Part: CONNECTOR — FAILED (NLG)

FLT NR 3066 - MCO-TLH - AFTER GEAR EXTENSION, THE NOSE GEAR SHOWED UNSAFE. PERFORMED ALTERNATE GEAR EXTENSION AND LANDED IN TLH WITHOUT INCIDENT. REMOVED AND REPLACED THE CANNON PLUG FOR THE DRAG STAY SENSOR. (M)

Part: AUTOFEATHER SW — FAILED (COCKPIT)

TPA/MIA - FLT 3005 - THE AUTOFEATHER ARM LIGHT FLICKERED AND WENT OUT DURING TAKEOFF. THE AIRCRAFT CONTINUED ON TO MIA AND LANDED WITHOUT INCIDENT. REMOVED AND REPLACED THE PROPELLER AUTOFEATHER SWITCH AND THE NR 1 BRAIDED ENGINE HARNESS FROM FIREWALL TO EEC DISCONNECT PLUG. REFERENCE CONTROL NR 95ZZZX6133.

Part: ENGINE HARNESS — FAILED (NR 1 ENGINE)

TPA/MIA - FLT 3005 - THE AUTOFEATHER ARM LIGHT FLICKERED AND WENT OUT DURING TAKEOFF. THE AIRCRAFT CONTINUED ON TO MIA AND LANDED WITHOUT INCIDENT. REMOVED AND REPLACED THE PROPELLER AUTOFEATHER SWITCH AND THE NR 1 BRAIDED ENGINE HARNESS FROM FIREWALL TO EEC DISCONNECT PLUG. REFERENCE CONTROL NR 95ZZZX6134.

Part: TQ CONTROL UNIT — FAILED (NR 2 ENGINE)

TPA/JAX - FLT 3166 - AFTER TAKEOFF DURING CLIMB, THE AUTOFEATHER ARM LIGHT ILLUMINATED INTERMITTENTLY. THE AIRCRAFT CONTINUED ON TO JAX AND LANDED WITHOUT INCIDENT. REMOVED AND REPLACED THE NR 2 TORQUE SENSOR CONTROL UNIT.

Part: SWITCH — FAILED (AUTOFEATHER SYST)

FLT NR 3031 - TPA-JAX - THE AUTOFEATHER ARM LIGHT FLICKERED ON AND OFF SEVERAL TIMES DURING TAKEOFF. THE AIRCRAFT CONTINUED ON TO JAX AND LANDED WITHOUT INCIDENT. GROUND RUN UP WAS COMPLIED WITH IN JAX AND THE AUTOFEATHER OPERATED NORMALLY. COULD NOT DUPLICATE THE PROBLEM. AT RON, THE AUTOFEATHER SELECT SWITCH WAS REMOVED AND REPLACED. (M)

Part: AUTOFEATHER SW — DIRTY (NR 1/2)

MCO/TLH - FLT 3092 - ON TAKEOFF ROLL, AUTOFEATHER WOULD NOT ARM WHEN POWER LEVERS ADVANCED TO TAKEOFF SETTINGS. THE CREW ABORTED THE TAKEOFF AND RETURNED TO THE GATE WITHOUT INCIDENT. CLEANED NR 1 AND NR 2 AUTOFEATHER MICROSWITCHES.