N10242

Part: FITTING — LEAKING (OIL FILTER)

THE NR 2 ENGINE OIL QUANTITY AND PRESSURE BEGAN TO DROP WHILE EN ROUTE. THE NR 2 ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND OIL LEAKING FROM BANJO FITTING AT ENGINE OIL FILTER HOUSING. A NEW FITTING AND PACKING WERE INSTALLED. THE ENGINE WAS SERVICED WITH OIL AND LEAK CHECKS WERE GOOD.

Part: BULKHEAD — CRACKED (NLG W/W)

INSPECTION FOUND AN 8 INCH CRACK IN FORWARD PRESSURE BULKHEAD OF NOSE WHEEL WELL ON LT SIDE APPROXIMATELY THREE INCHES OUTBOARD OF DOOR STOP. DOUBLERS WERE FABRICATED AND INSTALLED IAW BOEING DRAWING NR 65C17111.

Part: HYDRAULIC LINE — CHAFED (A- HYD SYST)

I/B CREW REPORTED LOSS OF A-SYSTEM HYD. FLUID CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT.

Part: BATTERY — INOPERATIVE (CABIN)

INSPECTION FOUND THE LEFT AFT ENTRY DOOR EMERGENCY EXIT LIGHT LANYARD PULLED OUT FROM ITS SEAT AND THE LIGHT WAS NOT ON. THE BATTERY WAS REMOVED AND REPLACED AND OPERATION CHECKED GOOD.

Part: FUEL CONTROL — INOPERATIVE (APU)

THE NR 1 GENERATOR FAILED WHILE EN ROUTE. THE APU WAS STARTED AND THE FIRE WARNING BELL SOUNDED WITH THE RED APU FIRE HANDLE ILLUMINATED. THE APU START SWITCH WAS PLACED TO OFF AND THE FIRE WARNING SYSTEM TESTED GOOD. THE AIRCRAFT WAS DIVERTED TO CMH WHERE IT LANDED WITHOUT INCIDENT. TROUBLESHOOTING BY MAINTENANCE FOUND THE APU TORCHING ON START. THE APU FUEL CONTROL AND COMBUSTOR WERE REPLACED. THE APU TAILPIPE FIRELOOP HARNESS AND EGT WIRE HARNESS WERE FOUND BURNT. BOTH HARNESSES WERE REPLACED. THE EGT THERMOCOUPLE WAS REPLACED AS A PRECAUTIONARY MEASURE, OPERATION OF THE APU CHECKED GOOD. IN ADDITION, THE NR 1 GENERATOR WAS REPLACED.

Part: FIRE DET — SHORTED (APU)

THE APU FIRE WARNING LIGHT AND BELL ACTIVATED ON SHORT FINAL INTO IND WITH APU START. THE APU SWITCH WAS MOVED TO OFF, BUT THE WARNING CONTINUED. THE APU FIRE BOTTLE WAS DISCHARGED, BUT THE FIRE LIGHT STAYED ON AND THE BELL WAS INTERMITTENT. THE AIRCRAFT LANDED AT IND WITHOUT INCIDENT. MAINTENANCE FOUND NO EVIDENCE OF FIRE. THE APU MUFFLER ELEMENT WAS FOUND SHORTED. THE APU MUFFLER FIRE DETECTION ELEMENT WAS REMOVED AND REPLACED, AN OPERATIONAL CHECK WAS GOOD. IN ADDITION, THE APU FIRE BOTTLE WAS REMOVED AND REPLACED.

Part: LIGHT — INOPERATIVE (R2 DOOR SLIDE)

GSO - 42 DOOR SLIDE LIGHT BATTERY CHECKS BAD - ZERO VOLTS. REPLACED R2 DOOR SLIDE BATTERY PACK. OPS CHECK GOOD IAW B737MM 33-52-63. (X)

Part: LIGHT — INOPERATIVE (L1 DOOR)

GSO - L1 DOOR SLIDE LIGHT BATTERY CHECKS BAD - ZERO VOLTS. REMOVED AND REPLACED L1 DOOR EVAC SLIDE LIGHT BATTERY PACK ASSY, OPS CHECK GOOD IAW B737 MM 33-51-63. (X)

Part: BATTERY PACK — DISCHARGED (R1 DOOR SLIDE)

GSO - R1 DOOR SLIDE LIGHT BATTERY CHECK BAD - LOW VOLTAGE. REPLACED R1 DOOR SLIDE LIGHT BATTERY PACK, OPS CHECK GOOD IAW B737 MX MAN 33-51-63. (X)

Part: FLOOR BEAM — CORRODED (BS 986)

GSO - FLOOR BEAM AT STA 986 AT RBL 65 AND LAV SUPPORT CHANNEL CORRODED. REMOVED FLOOR BEAM CAP. FABRICATED NEW CAP AND INSTALLED PER B737 SRM 51-10-2, SRM 51-30-2, AND BOEING DWG 65-61381. REMOVED PARTITION SUPPORT AND REPLACED WITH NEW PART PER B737 SRM 51-10-2 AND SRM 51-30-2. (X)

Part: SKIN — CRACKED (R1 DOOR CUTOUT)

GSO - R1 DOOR CUTOUT, LOWER AFT CORNER CRACKED. CRACK APPROXIMATELY 1.5 INCH LONG. CUT OUT 1.5 INCH CRACK, FABRICATED REPAIR PARTS IAW B737 SRM 53-30-3 FIG 26. ALODINED AND PRIMED PER SRM 51-10-2. SEALED AND INSTALLED REPAIR IAW SRM 53-30-3 FIG 26. SCUFF PLATE MODIFIED IAW B737 SRM 53-30-3 FIG 26. (M)

Part: SKIN — CORRODED (NLG WW)

GSO - RIGHT OUTBOARD AFT CORNER OF NOSE WHEEL WELL UPPER PRESS. PANEL HAS SEVERE BULGING AROUND FASTENERS. REMOVED CORROSION, INSTALLED DOUBLER PER CAL EA 5310-02452 OP 1. ALODINED AND PRIMED BARE METAL. (M)

Part: FLOOR WEB — CRACKED (BS 259.5)

GSO - COCKPIT FLOOR HAS BULGING IN 2 PLACES AND CRACKED FLOOR WEB AT STA 259.5. CRACK LENGTH = .1250 INCH. CUT OUT AND REPLACED FLOOR SECTION AT BS 259.5. CORD SECTION CUT AND SPLICED, FLOOR SUPPORT REPAIRED, FLOOR BEAM WEB CUT AND SPLICED IAW B737, SRM 53-10-9, 51-40-2, 51-40-4, 51-10-2, AND 51-10-6. (X)

Part: BULKHEAD SKIN — CORRODED (BS 540)

GSO - CORROSION FOUND AT BS 540 BETWEEN 27L AND 26L. REMOVED DAMAGE FROM WEB. FABRICATED FILLER, DOUBLER AND SHIMS. ALODINED AND PRIMED FILLER DOUBLER AND SHIMS. INSTALLED FILLER, DOUBLER AND SHIMS IAW SRM 51-10-02 AND EC/RA 5710-01723. (X)

Part: SKIN — DISBONDED (BS 980)

GSO - DISBOND FOUND AT 6TH WINDOW FORWARD OF STATION 980 LEFT 8 INCH AREA. ADDED FIELD FASTENERS AT DISBOND AND OVERSIZE EXISTING FASTENERS AND INSTALLED PER SA004-5310-01827, SA007-5310-01827 AND JA5310-0182702001. (M)

Part: FRAME — CORRODED (BS 520)

GSO - FRAME STA 520 CORRODED BETWEEN STR 28L AND STR 28R ON UPPER LEG. CUT OUT DAMAGED AREA 12 INCHES LONG BY 3 INCHES DEEP. FABRICATED L-ANGLE REPAIR AND FILLER PER B737, SRM 51-40-3 AND SRM 51-40-4. INSTALLED REPAIR IAW B737, SRM 51-40-3 AND SRM 51-40-4. (X)

Part: STIFFENER — CRACKED (BS 540)

GSO - FOUND BS 540 STIFFENER RBL 26 CRACKED. APPROXIMATELY 1 INCH IN LENGTH. REMOVED CRACKED SUPPORT BEAM. FABRICATED NEW SUPPORT BEAM AND TAPERED SHIMS. INSTALLED SUPPORT BEAM AND SHIMS IAW B737 SRM 51-30-2. ALODINED AND PRIMED SUPPORT AND SHIMS IAW SRM 51-10-2. (M)

Part: SKIN — DISBONDED (BS 727)

GSO - DISBOND FOUND BETWEEN WINDOWS AT STATION 727 LEFT, 6 INCHES DISBOND AREA. DRILLED LOCATION FOR FIELD RIVETS AND OVERSIZED FASTENERS AND INSTALLED PER SA 004-5310-01827, SA 007-5310-01827, AND CAL CARD JA5310-0182702001. (M)

Part: BULKHEAD SKIN — CORRODED (BS 540)

GSO - CORROSION FOUND AT BS 540 BETWEEN 27R AND 26R. REMOVED CORRODED AREA AROUND PNEUMATIC DUCT. FABRICATED FILLER AND DOUBLER. ALODINED AND PRIMED AS REQUIRED. INSTALLED FILLER AND DOUBLER IAW B737 SRM 51-10-2, SRM 51-30-2, AND EC/RA 5710-01723. (X)

Part: FLOOR BEAM — CRACKED (BS 727)

GSO - AFT PIT FLOOR BEAM CRACKED, STA 727B, STR 27R AND STR 27L. CRACK APPROXIMATELY .5 INCH IN EXTRUSION. FABRICATED REPAIR PARTS IAW B737 SRM 53-10-5. TREATED AND PRIMED IAW B737 SRM 51-10-2. INSTALLED PARTS. (X)

Part: SKIN — CORRODED (BS 253.5)

GSO - RIGHT FORWARD FUSELAGE OUTER SKIN BULGED AND RIVETS PULLING THROUGH JUST FORWARD OF BS 253.5 AT STRINGER 526R. REMOVED DAMAGED SECTION OF SKIN, REMOVED RIGHT CHORD ANGLE. FABRICATED REPAIR DOUBLERS AND FILLERS. INSTALLED NEW RIGHT CHORD ANGLE AND SKIN FILLER AND DOUBLER PER B737 SRM 53-20-2 AND 52-30-2. (M)

Part: CONTROL PANEL — INOPERATIVE (COCKPIT)

BDL - FLT 1064 - THE CABIN PRESSURE BEGAN TO FLUCTUATE AT FL 270 WHILE EN ROUTE FROM CLE TO BDL, AND SHORTLY AFTER, BEGAN TO CLIMB RAPIDLY. PRESSURE CONTROL WAS SWITCHED TO STANDBY, BUT CABIN PRESSURE COULD NOT BE MAINTAINED. A DESCENT WAS STARTED, THE OXYGEN MASKS DEPLOYED, AND UNEVENTFUL LANDING MADE AT BDL. MX REMOVED AND REPLACED CABIN PRESSURE CONTROL PANEL. PRESS CONTROLLER WAS ALSO REPLACED AS PRECAUTIONARY MEASURE. ALL DOOR SEALS AND THE OUTFLOW VALVE WERE INSPECTED AND FND IN GOOD CONDITION. THE ACFT WAS PRESSURIZED TO 5 PSI, AND ALL SYSTEMS CHECKED GOOD. THE OXYGEN SYSTEM WAS SERVICED AND LEAK CHECK WAS GOOD. (X)

Part: MOUNT BOLT — BACKED OUT (LT MLG DOOR)

FLT NR 1727 - GSO - THE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF FROM GSO. THE AIRCRAFT WAS RETURNED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND GEAR DOOR FORWARD TOP MOUNT BOLT ON LEFT GEAR BACKED OUT OF HOLE. THE BOLT, NUT, AND WASHER WERE INSTALLED. THE LANDING GEAR WAS SWUNG AND OPERATION CHECKED GOOD. (M)

Part: ACTUATOR — LEAKING (NR 1 GRD SPOILER)

EWR - FLT 0244 - THE A-HYDRAULIC SYSTEM WAS LOST AFTER LANDING AT EWR. THE PUMPS WERE FEATHERED WITHIN ONE MINUTE OF LOW PRESSURE LIGHT ILLUMINATION. MAINTENANCE FOUND THE NR 1 GROUND SPOILER ACTUATOR LEAKING. THE ACTUATOR WAS REMOVED AND REPLACED IAW MM 27-62-101, PAGE 401. LEAK AND OPERATIONAL CHECKS WERE GOOD. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. (X)

Part: EEL — INOPERATIVE (FWD BULLNOSE)

GSO - THE FORWARD BULLNOSE PORTABLE EXIT LIGHT WAS FOUND INOPERATIVE. THE PORTABLE EXIT LIGHT WAS REMOVED AND REPLACED IAW MM 33-51-31. (X)

Part: EEL EXIT SIGN — INOPERATIVE (R1 DOOR)

GSO - INSPECTION FOUND THE R-1 DOOR EMERGENCY EXIT LIGHT DIM. THE EMERGENCY EXIT LIGHT WAS REMOVED AND REPLACED IAW MM 33-51-101. (M)

Part: EEL BATTERY — DISCHARGED (R2 DOOR)

GSO - INSPECTION FOUND THE R-2 DOOR SLIDE LIGHT VOLTAGE READING ZERO. THE R-2 DOOR ESCAPE SLIDE LIGHT ASSY AND BATTERY WERE REMOVED AND REPLACED IAW MM 33-51-63. (X)

Part: EEL — INOPERATIVE (E/E HATCH)

GSO - THE LT E AND E HATCH PORTABLE EXIT LIGHT WAS FOUND DIM. THE E AND E HATCH PORTABLE EXIT LIGHT WAS REMOVED AND REPLACED IAW MM 33-51-01. (X)

Part: EEL — INOPERATIVE (AFT BULLNOSE)

GSO - THE AFT BULLNOSE PORTABLE EXIT LIGHT WAS FOUND INOPERATIVE. THE LIGHT ASSEMBLY WAS REMOVED AND REPLACED IAW MM 33-51-31. (X)

Part: EEL — INOPERATIVE (R-2 DOOR)

GSO - THE R-2 DOOR PORTABLE EXIT LIGHT WAS FOUND INOPERATIVE. THE PORTABLE EXIT LIGHT BATTERIES WERE RECHARGED IAW MM 33-51-101. (X)

Part: FRAME — CORRODED (BS 227)

GSO - INSPECTION FOUND CORROSION ON CHORD AT STA 227.8, BL ZERO. THE CORRODED SECTION OF CHORD WAS CUT OUT AND A NEW SECTION WAS SPLICED IN PER SRM 51-40-4. (X)

Part: TRANSDUCER — INOPERATIVE (E/E COMPT)

FLT NR 1405 - ATL - THE AIRCRAFT HAD A SLIGHT YAW AFTER TAKEOFF FROM EWR. THE RANGE OF THE YAW GREW AS SPEED INCREASED. THE YAWING STOPPED AFTER THE YAW DAMP SWITCH WAS POSITIONED TO OFF. MAINTENANCE FOUND THE RUDDER PCU 'B' POSITION TRANSDUCER OPEN. THE TRANSDUCER WAS REMOVED AND REPLACED IAW MM 22-11-51, PAGE 501. OPERATIONAL CHECKS WERE GOOD WITH NO OTHER DEFECTS FOUND. (M)

Part: HYD LINE — CHAFED (NR 2 ENGINE)

FLT NR 1758 - GSO - THE AIRCRAFT LOST 'A' SYSTEM HYDRAULIC FLUID WHILE AT CRUISE. THE 'ABNORMAL' CHECKLIST WAS ACCOMPLISHED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 2 ENGINE HYDRAULIC PRESSURE LINE CHAFED THROUGH. THE HYDRAULIC LINE WAS REMOVED AND REPLACED. THE HYDRAULIC LINE WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED. THE ENGINES WERE RUN, AND LEAK CHECKS WERE GOOD. (W)