N319DL

Part: INDICATOR — FAILED (COCKPIT) · airframe 52,857 hrs · 40,048 cycles

DURING PUSHBACK A ELECTRICAL SPARKING ARCING LIKE SOUND A VERY SLIGHT SMELL OF ELECTRICAL FUMES WHICH STOPPED VERY QUICKLY F/O`S VSI WENT INOP. REPLACED VSI.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 52,365 hrs · 39,668 cycles

FLT 7000 FT CLIMB EPR 250 - CLIMBING CLEAN HEARD LOUD BOOM WITH A/C SHUDDER ONCE. ALL ENG IND NORM AND STEADY. PNEU NORM. NO VISIBLE DAMAGE FROM CABIN F/A'S. ATB CVG UNEVENTFUL. DECLARED EMERGENCY WITH CVG DEPT CONTROL. BORO BOTH ENGINES, OK. FOUND LEFT ENGINE ANTI-ICE VLV LIGHT FLICKERING AT POWER. REPLACED ANTI-ICE VLV, OPS CHECKS OK.

Part: BALLAST — INOPERATIVE (CABIN LIGHTS) · airframe 52,189 hrs · 39,533 cycles

CREW REPORTED ACRID SMELL THROUGHTOUT CABIN. INSP E/E COMP, CARGO BAYS, CABIN BALLAST. FOUND BALLAST OF SEAT 2CD BAD. REPLACED BALLAST. A/C OK FOR SERVICE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 51,702 hrs · 39,186 cycles

THE FUSELAGE SKIN WAS FOUND WITH A 4 INCH CRACK RUNNING ALONG THE BONDED DOUBLER EDGE JUST BELOW STRINGER 23R BETWEEN FS 927 & 947. AN EXISTING SKIN DOUBLER WAS IN AN ADJACENT FRAME BAY. THE EXISTING REPAIR WAS REMOVED, THE CRACK WAS CUT OUT OF THE SKIN, AND BOTH AREAS REPAIRED WITH AN ALUMINUM REPAIR DOUBLER PER ER/A 094642-14, REV A.

Part: ACCESSORY UNIT — FAILED (LT MLG) · airframe 50,108 hrs · 37,951 cycles

ON T/O WHEN GEAR HANDLE RAISED LEFT MAIN GEAR RED UNSAFE LIGHT REMAINED ON. NO OTHER ABNORMAL INDICATIONS. REPLACED LANDING GEAR ACCESSORY UNIT.

Part: SKIN — DENTED (FUSELAGE) · airframe 50,073 hrs · 37,923 cycles

THE UPPER SKIN OF THE S19R WAS FOUND DENTED. DENTED WAS REMOVED AND REPAIR INSTALLED IAW 386089-14.

Part: CLEVIS — CORRODED (FUSELAGE) · airframe 50,073 hrs · 37,923 cycles

CORROSION DAMAGE WAS NOTED ON THE NR 5, NR 6 AND NR 11 BODY CLEVIS LUGS. CORROSION WAS REMOVED AND FITTINGS REWORKED IAW 386170-14.

Part: SUPPORT FITTING — CORRODED · airframe 50,073 hrs · 37,923 cycles

CORROSION WAS NOTED ON BOTH THE LT AND RT BS 685 MLG SUPPORT FITTINGS IN THE LUG BORES AND FACES. CORROSION WAS REMOVED AND FITTINGS REWORKED IAW ERA 386114-14.

Part: BULKHEAD — CORRODED · airframe 50,073 hrs · 37,923 cycles

CORROSION WAS NOTED AT BS 1016 PRESSURE BLKHD, AT BL 0 AND AFFECTED THE WEB/GORE AND CHANNEL STIFFENERS. REPAIRED PER ERA 386069-14AD.

Part: FRAME — CRACKED (FUSELAGE) · airframe 50,073 hrs · 37,923 cycles

DURING INSPECTION OF THE BS 663 FRAME CRACKS WERE NOTED IN THE FRAME AT S3L, S2L AND S1. DURING INSTALLATION OF THE SRM FRAME REPAIR IT WAS NECESSARY TO CUT THE FUSELAGE SKIN TO ACCOMMODATE FRAME REPAIR FASTENERS. FRAME WAS REPAIRED PER SRM, SKIN REPAIRED PER ERA 386063-14.

Part: FLAP TRACK — CORRODED (TE FLAPS) · airframe 50,073 hrs · 37,923 cycles

THE REAR ENGINE MOUNT ATTACH HOLES, LOCATED AT THE NR 2 AND NR 3 T/E FLAPS, OUTBOARD TRACKS WERE NOTED WITH CORROSION IN THE BORES. CORROSION WAS REMOVED AND TRACKS WERE REWORKED PER ERA 386130-14.

Part: ATTACH FITTING — CORRODED (HORIZONTAL STAB) · airframe 50,073 hrs · 37,923 cycles

THE STABILZER ATTACHMENT LUGS WERE FOUND WITH DAMAGE EXCEEDING THE LIMITS OF SB 737-55-1033. DAMAGE WAS REMOVED BY BLENDING AND OVERSIZING BORES PER ER/A 386108-14AD.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 50,073 hrs · 37,923 cycles

DURING INSPECTION THE BS 520 FLOORBEAM WAS NOTED WITH CRACKS IN THE RADIUS, ALONG THE UPPER CHORD TO WEB RADIUS AT LBL 24.75, LBL 45.5 AND RBL 24.75. UPPER CAP WAS REMOVED AND A NEW SECTION SPLICED IN PER ERA 386080-14.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 50,073 hrs · 37,923 cycles

NUMEROUS ATTACHMENT FITTING LUGS ON THE HORIZ STAB TO FUSELAGE JOINT REQUIRED MACHINING BEYOND PUBLISHED LIMITS IN ORDER TO REMOVE CORROSION. CORROSION WAS REMOVED AND LUGS REWORKED IAW ERA 386108-14AD.

Part: ACTUATOR — INTERMITTENT (NR 1 ENGINE) · airframe 46,718 hrs · 36,512 cycles

AFTER STARTING NR 1ENG (NORMAL START) DURING TAXI OUT NR 1 ENG FLAMED OUT. ON RESTART ATTEMPT AT GATE, NO FUEL FLOW INDICATION AFTER START LEVER RAISED TO IDLE. REPLACED BAD FUEL SOV ACTUATOR AND GATE ASSY PER MM. RAN NR 1 ENG, ALL PARAMETERS GOOD.

Part: ANTENNA — INOPERATIVE (WX RADAR) · airframe 45,452 hrs · 35,968 cycles

WEATHER RADAR INOP, CON/IND FAULT. REPLACED R/T AND ANT PER MM, PUSHED OUT INTO RAMP AND PAINTED ACTUAL WEATHER, OPS NORMAL IN ALL MODES.

Part: CONTROLLER — MALFUNCTIONED (E/E BAY) · airframe 44,865 hrs · 35,706 cycles

ON DESCENT INTO TPA PASSING THROUGH 15000 FT, RECEIVED A WHEEL WELL FIRE INDICATION. AFTER PERFORMING APPROPRIATE PROCEDURE WHEEL WELL FIRE LIGHT BECAME INTERMITTENT. T/S PER MM. UNABLE TO DUPLICATE DISCREPANCY. REPLACED COMP OVHT CONTROLLER MODUEL AS PRECAUTIONARY.

Part: VALVE — MALFUNCTIONED (E/E BAY) · airframe 44,708 hrs · 35,634 cycles

AIRCRAFT FAILED TO PRESSURIZE AFTER T/O FROM PBI. OUTFLOW VLVS INDICATED FULL CLOSED. F/A REPORTED THERE WAS LOUD WIND NOISE AROUND L1 DOOR. DOOR INDICATED CLOSED AND LOCKED. DIVERTED TO MCO. PRESSURIZED AC TO 7 PSID. CHECKED ALL DOOR SEALS- CABIN, CARGO AND EQUIP DOORS. ALL CHECK OK. FOUND EQUIP COOLING EXH VLV STICKING OPEN (SLOW TO CLOSE). REPLACED EQUIP COOL EXH VLV. REPRESSURIZED AC TO 6.5 PSID. ALSO PERF PRESS CK PER MM, ALL CKS GOOD.

Part: WIRE — FAILED (BS 1088)

STAB TRIM CONTROL WHEEL SWITCHES INOP. POPS ACTUATOR C/B. AUTOPILOT TRIM IS OK. FOUND WIRES SHORTED TO GROUND AT BULKKHEAD 1088. REPAIRED WIRE WITH SPLICES. WIRE NRS W326-313, W326-312, W326-311 PER BOEING STANDARD WIRING PRACTICES MANUAL.

Part: O-RING — FAILED (NR 3 SPOILER ACT)

LOSS OF HYD SYS A QTY IN FLT. REPL NO3 FLT SPOILER ACTUATOR. O-RING RUPTURED ON ACTUATOR. ALL LEAK AND OPN TEST NML.

Part: FITTING — CRACKED (RT MLG)

DURING INSPECTION PER SB 737-57-1216 TWO CRACKS WERE FOUND IN THE MLG BEAM AFT SUPPORT FITTING ON THE RS OF THE RT WING. THE INBD CRACK LOCATION IS TYP PER SB. THE OUTBOARD FASTENER LOCATION WAS OS TO 0.438 DIAM AND THE CRACK WAS REMOVED. REPAIRED PER ERA 331269-14.

Part: BULKHEAD WEB — CRACKED (BS 178)

SEVERAL CRACKS FOUND IN THE FS 178 BULKHEAD. REPAIRED PER ERA 331261-14.

Part: SPAR CHORD — CORRODED (HORIZ STAB)

CORROSION FOUND ON THE UPPER SURFACE OF THE AFT FLANGE OF THE HORIZ STAB REAR SPAR UPPER CHORD. REPAIRED PER ERA 331272-14.

Part: SKIN — CRACKED (BS 379)

SKIN AT THE COOLING DUCT CUTOUT AT BS 379, APPROXIMATELY BL0 WAS FOUND CRACKED AT THE AFT EDGE OF THE CUTOUT. CRACK IS APPROXIMATELY 1.5 IN LENGTH AND IS TYPICAL OF CRACKS DESCRIBED BY SB 737-53-1117. REPAIRED PER ERA 331270-14 (SB 737-53-1117).

Part: APU — ODOR (AFT FUSELAGE)

SMOKE ALARM WENT OFF IN FWD LAV CREW COULD SMELL ACRID SMELL. FOUND APU PUTTING OIL INTO PNEUMATIC DUCTS. FWD APU TO MCO REPLD DETECTOR BATTERY, REPLD LT AND RT COALESCER BAGS RAN BOTH ENGS AT 1.80 EPR FOR APPROX 15 MINS TO BURN OIL SMELL OUT.

Part: SKIN — CRACKED (GALLEY DOORWAY)

FUSELAGE SKIN AND BEAR STRAP AFT GALLEY DOOR SURROUND. REPAIR FOR CRACK AT LWR HINGE CUT OUT. A .25 INCH CRACK WAS FOUND IN THE SKIN AND A 1.0 INCH CRACK IN THE BEAR STRAP OF THE AFT GALLEY DOOR SURROUND LOWER HINGE CUT OUT. A TIME-LIMITED REPAIR DOUBLER WAS INSTALLED PER ER/A 362990-14.

Part: POWER SUPPLY — INOPERATIVE (CABIN)

FWD CABIN EMERGENCY LIGHTS STUCK ON AFTER TEST. REPLACED POWER SUPPLY.

Part: P6 PANEL — TRIPPED (E/E COMPT)

BOTH GENRATORS WERE LOST AT FL310. ACCOMPLISHED LOSS OF BOTH GENERATORS CHECKLIST PER AOM. DIVERTED TO JFK, STIMATED LANDING WT 103,500 AND LANDING NORMAL. REPLACED G7 BUS PROTECTION PANEL AND R3 RELAY. RUN UP AND FUNCTIONAL CHECK GOOD.

Part: CHARGER — INOPERATIVE (CABIN)

FOUND ON L/O CHECK, EMERGENCY FLOOR TRACK LIGHTING HAS A SECTION INOP. REPLACED CHARGER ASSY, OPS CHECK NORMAL.

Part: SKIN — DAMAGED (RUDDER)

RUDDER HAS TEMPORARY REPAIR ON UPPER RT SIDE SKIN. REPAIRED DAMAGE AS PER SRM 55-40-5 WITH REF TO 51-40-15.

Part: SKIN — DAMAGED (FS 935)

FUSELAGE SKIN AT FS 935 BETWEEN STR 21 AND 22, SUSTAINED PUNCTURE DAMAGE FROM GROUND EQUIPMENT. REPAIRED PER DL ERA 302319-14 AND SRM 53-10-3 FIG 1 FOR DAMAGE TO FS 935 FRAME.

Part: ANTI-ICE DUCT — CRACKED (NR 2 ENGINE)

AFTER TAKEOFF, NR 2 OIL TEMP CLIMBED THROUGH YELLOW ZONE, ENGINE WAS SHUTDOWN WHEN TEMP WENT TO RED. RETURNED TO ATL. FOUND ENGINE ANTI-ICE DUCT CRACKED AND BLOWING HOT AIR ON FUEL HEAT VALVE. THE DUCT AND FUEL HEAT VALVE WERE REPLACED, OPERATION NORMAL.

Part: GCU — FAILED (E/E COMP)

DURING CRUISE, LOST NR 1 GENERATOR, GCU BREAKER TRIPPED. STARTED APU, UNABLE TO TRANSFER POWER, DIVERTED BOS. REPLACED NR 1 GCU AND NR 1 GEN BREAKER. OP CHECK NORMAL.

Part: RELAY — FAILED (LT FLT DECK)

ON CLIMBOUT, LOST ALL FLT INSTRUMENTS ON LEFT SIDE, RETURNED TO CVG. FOUND NORMAL TRANSFER C/B TRIPPED. REPLACED R3 TRANSFER RELAY, OPERATION NORMAL.

Part: FLOOR BEAM — CRACKED (FS 657)

DURING ROUTINE INSPECTION, THE BL 0.07 FLOORBEAM OF THE WING CENTER SECTION WAS FOUND CRACKED AT STA 657. THE UPPER CAP WAS COMPLETELY CRACKED, BUT NO CRACKS WERE FOUND IN THE WEB. PER B737 S/B 737-57-1210, THE CAP WILL BE REPAIRED.