N12136
Registered owner: UNITED AIRLINES INC, IL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
Maintenance disclosures
LH OVERWING EXTERIOR EMERGENCY LIGHT INOPERATIVE. REMOVED AND REPLACED LH OVERWING EXTERIOR LIGHT BULB. OPS CHECK SAT. NO OTHER DEFECTS FOUND.
LANDING GEAR EMERGENCY DOOR DIFFICULT TO OPEN. CLEANED AND LUBED LANDING GEAR EMERGENCY DOOR. OPS CHECK SAT.
MCD GETTING STUCK WHEN OPENING FROM INSIDE. PERFORMED OPS CHECK OF MAIN DOOR TO FUSELAGE SKIN ADJUSTMENT. FOLDING FLAP EDGE AND MAIN DOOR EXTERNAL HANDLE WONT CLOSE ALL THE WAY. PERFORMED RODS ADJUSTMENT. REMOVED AND REPLACED REAR LOCK BOX CABLE. REMOVED AND REPLACED MCD INTERNAL HANDLE ROD #2. PERFORMED MAIN DOOR TO FUSELAGE SKIN STEP. PERFORMED MAIN DOOR CABLED ADJUSTMENT. COMPLETED ADJUSTMENT OF MAIN DOOR. CABLE ADJUSTMENT SKIN STEP ADJUSTMENT, ROD ADJUSTMENT, FOLDING FLAP ADJUSTMENT, INTERNAL HANDLE ADJUSTMENT, TOPS CHECK/PRESSURIZATION SAT. DOOR OPEN AND CLOSE SAT.
SIDE HINGED MAIN CABIN DOOR EXCESSIVE HARD TO CLOSE AND OPEN. REMOVED AND REPLACED UPPER AND LOWER AFT ROLLER. OPS CHECK SAT.
EMERGENCY LIGHTS OPS CHECK FAILED. INSTALLED ELECTRICAL CONNECTORS ON HEADLINER PANELS. EMERGENCY LIGHTS OPS CHECK SAT.
FOUND CORROSION ON RH OMEGA BEAM FR20 DOUBLER PIECE. REMOVED AND REPLACED DOUBLER PIECE AT RH OMEGA BEAM FR20.
CORROSION AROUND WATER SERVICE TUBING ON FUSELAGE DOUBLER PLATE. BLENDED CORROSION ON WATER SERVICE DOUBLER PLATE. DIMENSIONS FOR THE BLEND OUT IS 1.5"X.75"X.25" ORIGINAL THICKNESS IS .063" REMAINING IS .038" AND IS DETERMINED TO BE OUT OF LIMITS. REMOVED DOUBLER AT WATER SERVICE AREA. FABRICATED NEW DOUBLER. APPLIED PROTECTIVE COATINGS TO NEW DOUBLER. INSTALLED NEW DOUBLER AT WATER SERVICE AREA ON FUSELAGE.
LIGHT CORROSION ON BOTH CONNECTING ENDS OF PORTABLE WATER OVERFLOW LINE LOWER SECTION. REMOVED PORTABLE WATER OVERFLOW LINE LOWER SECTION. REPLACED PORTABLE WATER OVERFLOW LINE LOWER SECTION.
MODERATE CORROSION FOUND ON BOLT KEEPER AT SPRING TAB LINKAGE (RH ELEVATOR). REMOVED CORROSION ON BOLT KEEPER AT SPRING TAB LINKAGE ON RH ELEVATOR. PRIMED AND PAINTED BOLT KEEPER AT SPRING TAB LINKAGE ON RH ELEVATOR
MODERATE CORROSION FOUND ON BOLT KEEPER AT SERVO TAB LINKAGE (LH ELEVATOR). REMOVED CORROSION ON BOLT KEEPER AT SERVO TAB LINKAGE. APPLIED TOP COAT FINISH ON BOLT KEEPER AT SERVO TAB LINKAGE.
SERVICE DOOR FWD FLOOR SILL HAS CORROSION AT FRAME 20. REMOVED CORROSION AREA. PERFORMED EDDY CURRENT INSPECTION OF CORROSION REMOVAL AREA. NO DISCREPANCIES. PARTICULARLY FAB DOUBLER. APPLIED EPOXY TO DAMAGE AREA. FINISHED FAB DOUBLER. INSTALLED FOUBLER. APPLIED TOP COAT FINISH.
SERVICE DOOR AFT FLOOR SILL HAS CORROSION AT FRAME 22. REMOVED AND PARTIALLY LOCATED AND DRILLED NEW SERVICE DOOR SILL AT FR22. LOCATED AND DRILLED NEW SERVICE DOOR SILL AND PARTIALLY INSTALLED. FINISHED INSTALLING SERVICE DOOR SILL. REAPPLIED CIC TO NEW SERVICE DOOR SILL.
FRAME 60 BUTTLINE 0 FLOORBEAM HAS CORROSION AROUND NUTPLATES. REMOVED CENTER BEAM FOR FLIGHT CONTROL CABLES AT FR61. REMOVED BOTTOM CARBON FIBER PIECE ON FR61. REMOVED AND REPLACED GUSSET BETWEEN FR60 AND 61. INSTALLED BOTTOM CARBON FIBER PIECE ON FR61. INSTALLED CENTER BEAM FOR FLIGHT CONTROL CABLES AT FR61
SUSPECTED CORROSION FOUND ON THE OUTBOARD SIDE OF THE LH AILERON UPPER SHROUD ATTACHMENT. REMOVED MILD CORROSION ON THE OUTBOARD SIDE OF THE LH AILERON UPPER SHROUD OF THE LH AILERON UPPER SHROUD ATTACHMENT. PREP, PRIMED REWORK AREA ON THE OUTBOARD SIDE OF THE LH AILERON UPPER SHROUD ATTACHMENT.
SEAT TRACKS AT FRAME 31 AMD 33 RH FLOOR, AND FRAMES 53 AND 55 RH WALL SUSPECTED CORROSION. REMOVED AND REPLACED SEAT TRACK AT FR33 RH FLOOR FOR CORROSION OUT OF LIMITS. REMOVED AND REPLACED SEAT TRACK AT FR31 FOR CORROSION OUT OF LIMITS. BLENDED OUT SEAT TRACK AT FR53 AND 55 RH WALL AND FOUND NO CORROSION AT THIS TIME.
MAIN CABIN DOOR EMERGENCY LIGHT AND FA OVERHEAD LIGHT INOPERATIVE. REMOVED AND REPLACED BULB. OPS CHECK FAIL. FOUND QUICK DICONNECT SP 7425 BROKEN. REPAIRED QUICK DISCONNECT. OPS CHECK FAIL. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY #1. OVERHEAD LIGHT OPS CHECK SAT, MCD LIGHT OPS CHECK FAIL. REMOVED AND REPLACED HOUSING. OPS CHECK FAIL. REMOVED AND REPLACED EMERGENCY LIGHT BATTERY 1 CRADLE. OPS CHECK SAT. ALL LIGHTS WORK.
LT SIDE EMERGENCY EXIT SIGN DOES NOT LIGHT UP. PERFORMED EMERGENCY LIGHTS FUNCTIONAL CHECK AND FOUND ALL LIGHTS AND SIGNS ARE OPERATIONAL
LOUD WHISTLE AND AIR FLOW COMING NEAR CA DV WINDOW IN CRUISE. PRESSURIZATION DIFFICULT TO CONTROL IN AUTO/MAN MODE. PRESSURIZED A/C. OPS CHECK PASSED. INSPECTED CA DV WINDOW AND FOUND MULTIPLE DISCREPANCIES ON FWD SEAL. REMOVED AND PREPPED SURFACE FOR SEAL AND SEALANT INSTALL. INSTALLED DV WINDOW SEAL. PERFORMED PRESSURIZATION LEAK CHECK, MANUAL MODE OPS CHECK, AND AUTO MODE OPS CHECK. CA DV WINDOW LEAK CHECK SAT. MANUAL AND AUTO MODE OPS CHECK SAT. INSTALLED CA DV WINDOW.
MCD EMERGENCY LIGHT OUT. REMOVED AND REPLACED MCD EMERGENCY LIGHT BULB. OPS CHECK FAILED. SSUPECT LIGHT ASSY TO BE FAULTY. REMOVED AND REPLACED MCD LIGHT ASSEMBLY. OPS CHECK SAT.
MCD EMERGENCY LIGHT INOPERATIVE. REMOVED AND REPLACED MCD EMERGENCY LIGHT LAMP. OPS CHECK SAT
EXIT SIGN ABOVE F/A JUMP SEAT NOT SECURE. RESECURED EXIT SIGN ABOVE FA JUMPSEAT
EXIT SIGN ABOVE FA JUMPSEAT NOT SECURE. RESECURED EXIT SIGN ABOVE FA JUMPSEAT
LIGHT STRIP ON FLOOR INOP ON ROW 1-3. R&R EMERGENCY LIGHT STRIP BETWEEN ROW 1 - 3
SUPPLEMENTAL INFORMATION: REMOVED DAMAGE PORTION OF WIRES AND DAMAGED ELECTRICAL CONNECTOR PLUG TO #1 WINDSHIELD TEMP CONTROLLER. PINNED NEW ELECTRICAL CONNECTOR PLUG TO #1 WINDSHIELD TEMP CONTROLLER. PINNED ELECTRICAL CONNECTOR PINS FOR #1 WINDSHIELD TEMP CONTROLLER ELECTRICAL CONNECTOR PLUG. REPLACED ELECTRICAL POWER WIRE FROM #1 WINDSHIELD TEMP CONTROLLER TO WINDSHIELD. REMOVED AND REPLACED #1 WINDSHIELD TEMP CONTROLLER. REPLACED DAMAGED COCKPIT AIR CONDITION TUBING. OPS CHECK SAT.
SMOKE ODOR AT FLT 190 AND REMAIN THE REMAINDER OF THE FLIGHT. REMOVED AND REPLACED BOTH THE CAPTAINS AND FLT ATTENDANTS FLASH LIGHT ASSEMBLIES.
EMERGENCY EXIT SIGN ABOVE FA JUMP SEAT IS BROKEN. RESECURED EMERGENCY EXIT SIGN ABOVE FA JUMP SEAT. NO FURTHER DEFECTS NOTED
SMOKE COMING FROM RT DIST PANEL IN COCKPIT. PERFORMED OPERATIONAL CHECK ON COOLING PACKS. NO SMOKE OF FAULTS DETECTED. OPS CHECK GOOD.
NLG UPLOCK LH INTERCOATINAL CRACKED FWD INSIDE. REMOVED AND REPLACED NLG UPLOCK LH INTERCOSTAL.
CORROSION ON CARGO DOOR CUTOUT LOWER SILL DOUBLER AT FR67 AND Y =-19". REMOVED AND REPLACED CARGO DOOR SILL DOUBLER AT AFT CARGO DOOR.
CORROSION ON 2 EA ANGLES AT PAX DOOR SILL BETWEEN FR 16 - FR 17. REMOVED AND REPLACED 2 EA ANGLES AT PAX DOOR SILL BETWEEN FR 16 - FR 17
AFT WET AREA LH SIDE CROSS MEMBER FLOOR SUPPORT IS CORRODED AT F58+8" AND Y-8". REMOVED AND REPLACED LH FLOOR CROSS MEMBER SUPPORT AT F 58=8 AND Y-8.
CORROSION ON PANEL 231 FF SUPPORT PROFILE AT L EDGE BETWEEN FR 18-19. REMOVED AND REPLACED PROFILE FOR PANEL 231FF AT LH EDGE BETWEEN FRAME 18 AND 19
CORROSION IN THE CARGO ON CENTER AT SECTION UPPER DOUBLER AT FR 65, 67, AND 68. REMOVED AND REPLACED CENTER HAT SECTION UPPER DOUBLER AT FR 65, 67, AND 68 IN CARGO.
AFT WET AREA, RH SIDE FLOOR BEAM IS CORRODED AT F59+19" AND Y+3.5". INSTALLED NEW UPPER BEAM CAP IN AFT WET AREA, RH SIDE FLOOR AT FR 59+19" AND Y+3.5".
FWD CABIN EMERGENCY LIGHTS INOPERATIVE. R & R EMERGENCY BATTERY POWER SUPPLY NR 1. OPERATIONS CHECK SATISFACTORY.
REPAIR DOUBLER ON LT WING LEADING EDGE 3 NOSE BETWEEN RIB 6-7. PATCH REPAIR ON LT WING LEADING EDGE 3 BETWEEN RIB 6-7 PERFORMED.
MULTIPLE DENTS ON LT CENTER FUSELAGE SKIN 1 BETWEEN FR 19-21 AND BETWEEN STR 11L-14L. PATCH REPAIR ON LT FUSELAGE SKIN 1 BETWEEN FR 19-20 AND STR 13L-14L PERFORMED.
DENT WITH A CREASE FOUND ON RT SIDE OF THE TRAILING RUDDER 1.10" ABOVE RIB ZV 2357.0 AND 3.90" AFT OF FRONT SPAR. PATCH REPAIR ON RT SKIN OF TRAILING RUDDER 1.00 ABOVE RIB ZV 2357.0 AND 3.900 PO AFT OF FRONT SPAR.
DENT ON LT WING LEADING EDGE 3 NOSE BETWEEN RIB 3-4. DENT ON LT WING LEADING EDGE NR 3 BETWEEN RIB 3-4 REPAIRED.
CRACK ON RT REAR FUSE 2, AROUND RIVET, ON FR 79 AND BETWEEN STR 5R-6R. ON RT REAR FUSE 2, ON FR 79 AND BETWEEN STR 5R-6R, PAINT STRIPPED FOR INVESTIGATION. RIVET AND SKIN DAMAGE REMOVED ON RT REAR FUSE 2 ON FR 79 BETWEEN STR 5-6R. FASTENER DIAMTETER 0.161 SKIN REWORK DIAMETER 0.438. CRACK ON RT REAR FUSE 2 SKIN AT FR 79 BETWEEN STR 5-6R REPAINTED. AT FRAME 79 AND BETWEEN STR 5R AND 5-6R METAL REPROTECTED.
CRACK ON RT REAR FUSE 2, AROUND RIVET, ON FR 79 AND BETWEEN STR 3R-4R. ON RT REAR FUSE 2, ON FR 79 AND BETWEEN STR 3-4R PAINT STRIPPED FOR INVESTIGATION. RIVET AND SKIN DAMAGE ON RT FUSE 2 ON FR 79 BETWEEN STR 3-4R REMOVED. FASTENER DIAMETER 0.161. SKIN REWORK DIAMETER 0.438. CRACK ON RT REAR FUSE 2 AT FR 79 BETWEEN STR 3-4 REPAIRED. AT FRAME 79 AND BETWEEN STR 3R-4R, METAL REPROTECTED.
REAR FUSELAGE 2 LT SKIN, CRACKS FOUND AROUND RIVER ON FR 79 AND BETWEEN STR 3L-4L. FOR INVESTIGATION, PAINT REMOVED ON DAMAGED SKIN AREA, AT FR 79 AND BETWEEN STR 3L-4L. FASTENER AND SKIN DAMAGE ON REAR FUSE 2 FR 79 BETWEEN STR 3-4L REMOVED. FASTENER DIAMETER 0.161. SKIN REWORK DIAMETER 0.438. CRACKED REAR FUSELAGE 2 LT SKIN AT FR 79 BETWEEN STR 3-4L REPAIRED. AT FRAME 79 AND BETWEEN STR 3L-4L REPROTECTED.
CRACK ON RT REAR FUSE 2, AROUND RIVET, ON FR 78 AND BETWEEN STR 5R-6R. ON RT REAR FUSE 2, ON FR 78 AND BETWEEN STR 5R-6R, PAINT STRIPPED FOR INVESTIGATION. RIVET AND SKIN DAMGE ON RT REAR FUSE 2 ON FR 78 BETWEEN STR 5-6R REMOVED. FASTENER DIAMETER 0.161. SKIN REWORK DIAMETER 0.438. CRACK ON RT REAR FUSE 2 SKIN ON FR 78 AND BETWEEN STR 5R-6R REPAIRED. AT FRAME 78 AND BETWEEN STR 5R-6R METAL REPROTECTED.
REAR FUSELAGE 2 LT SKIN, CRACKS FOUND ON FR 78 AND BETWEEN STR 5L-6L. FOR INVESTIGATION PAINT REMOVED ON DAMAGED SKIN AREA, AT FR 78 AND BETWEEN STR 5L-6L. FASTENER AND SKIN DAMAGE ON REAR FUSE 2 FR 78 BETWEEN STR 5-6L REMOVED. FASTENER DIAMETER .161. SKIN REWORK 0.438. CRACK REAR FUSE 2 LT SKIN AT FR 78 BETWEEN STR 5-6L REPAIRED. AT FRAME 78 AND BETWEEN STR 5-6L METAL REPROTECTED.
REAR FUSELAGE 2 LT SKIN, CRACKS FOUND AROUND RIVET ON FR 77 AND BETWEEN STR 8L-9L. FOR INVESTIGATION, PAINT REMOVED ON DAMAGED SKIN AREA, AT FR 77 AND BETWEEN STR 8L-9L. FASTENER AND SKIN DAMAGE ON FR 77 BETWEEN STR 8-9L REMOVED. FASTENER DIAMETER .161. SKIN REWORK .438. CRACKED REAR FUSE 2 LT SKIN ON FR 77 BETWEEN STR 8-9L REPAIRED. AT FRAME 77 AND BETWEEN STR 8L-9L METAL REPROTECTED.
REAR FUSELAGE 2 SKIN, CRACKS FOUND AROUND RIVET ON FR 77 AND BETWEEN STR 3L-4L. FOR INVESTIGATION, PAINT REMOVED ON DAMAGED SKIN AREA, AT FR 77 AND BETWEEN STR 3L-4L. FASTENER AND SKIN DAMAGE ON FR 77 BETWEEN STR 3-4L REMOVED. FASTENER DIAMETER .161 SKIN REWORK DIAMETER .438. CRACKED REAR FUSE 2 LT SKIN AT FR 77 BETWEEN STR 3-4L REPAIRED. AT FRAME 77 AND BETWEEN STR 3L-4L METAL REPROTECTED.
CRACK ON RT REAR FUSE 2, AROUND RIVET, ON FR 79 AND BETWEEN STR 6R-7R. ON RT REAR FUSE 2, ON FR 79 AND BETWEEN STR 6R-7R, PAINT STRIPPED FOR INVESTIGATION. RIVET AND SKIN DAMAGE ON RT FUSE 2 ON FR 79 BETWEEN STR 6-7R REMOVED. FASTENER DIAMETER 0.161, SKIN REWORK DIAMETER 0.438. CRACK ON RT REAR FUSE 2 SKIN ON FR 79 BETWEEN STR 6-7R REPAIRED. AT FRAME 79 AND BETWEEN STR 6R-7R METAL REPROTECTED.
REAR FUSELAGE 2 LT SKIN, CRACKS FOUND AROUND RIVET ON FR 79 AND BETWEEN STR 6L-7L. FOR INVESTIGATION, PAINT REMOVED ON DAMAGE SKIN AREA AT FR 79 AND BETWEEN STR 6L-7L. FASTENER AND SKIN DAMAGE LT FUSELAGE 2 FR 79 BETWEEN STR 6-7L REMOVED. FASTENER DIAMETER 0161. REWORK DIAMETER 0.438. REAR FUSELAGE 2 LT CRACKED SKIN AT FR 79 BETWEEN FR 6-7L REPAIRED. AT FRAME 79 AND BETWEEN STR 6L-7L, METAL REPROTECTED.
REAR FUSELAGE 2 LT SKIN, CRACKS FOUND AROUND RIVET ON FR 79 AND BETWEEN STR 5L-6L. FOR INVESTIGATION, PAINT REMOVED ON DAMAGED SKIN AREA, AFTER 79 AND BETWEEN STR 5L-6L. FASTENER AND SKIN DAMAGE AT REAR FUSE 2 FR 79 BETWEEN STR 5-6L REMOVED. FASTENER DIAMETER 0.161 SKIN REWORK DIAMETER 0.438. REAR FUSE 2 LT CRACKED SKIN AT FR 79 BETWEEN STR 5-6L REPAINTED. AT FRAME 79 BETWEEN STR 5L-6L METAL REPROTECTED.
IN CABIN, THE SIDEWALLS ARE NOT PROPERLY INSTALLED AROUND THE OVERWINGS EMERGENCY EXIT DOORS. CABIN, LT SIDEWALL REINSTALLED PROPERLY AROUND OVERWINGS EMERGENCY EXIT DOORS. CABIN, RT SIDEWALL REINSTALLED PROPERLY AROUND OVERWINGS EMERGENCY CABIN RT SIDEWALL BRACKET UPPER FWD GLUED.
REPAIR DOUBLER ON RT WING LEADING EDGE 2 BETWEEN RIB 4-5. SPLICE 613AR, 612AR, AND RT LEADING EDGE NR 2 REMOVED FOR ACCESS. PICOLO TIBE REMOVED FROM RT LEADING EDGE NR 2. LEADING EDGE NR 2 ON RT WING HAS BEEN DECLARED UNREPAIRABE DUE TO A DENT. PICOLO TUBE INSTALLED RT LEADING EDGE NR 2. INSTALLED A SERVICEABLE LEADING EDGE NR 2. INSTALLED SPLICE 613AR AND 612AR.
LATCH BROKEN ON EMERGENCY LANDING GEAR FREE FALL DOOR ON COCKPIT FLOOR, UNABLE TO OPEN. LATCH REPLACED ON EMERGENCY LANDING GEAR FREE FALL DOOR ON COCKPIT FLOOR.
COCKPIT EMERGENCY EXIT, COPILOT SIDE, STRIP SEAL DISBONDED ON SURROUND FRAME AND HARD TO OPEN. COCKPIT EMERGENCY EXIT COPILOT SIDE, STRIP SEAL SURROUND FRAME REPAIRED. COCKPIT EMERGENCY CO-PILOT ADJUSTMENT CUT OUT.
*MAJOR REPAIR* L/H LOWER WING SKIN HAS GOUGE BETWEEN I/B AND O/B FLAPS(DMI#70062907...... REPAIRED L/H LOWER WING SKIN IAW EO-EMB145-57-023-0
STOP SIGN DOUBLERS AT FRM 20 AND FRM 22 HAVE CORROSION ... REMOVED AND REPLACED STOP SIGN DOUBLERS AT FRM 20 AND FRM 22 IAW SRM 51-40-02
Z ANGLE CARGO DOOR LOWER FRM HAS CORROSION. REMOVED AND REPLACED Z ANGLE CARGO DOOR LOWER FRM.
CABIN FLOOR SUPPORT L/H FRM 20 CORRODED THROUGH STRUCTURE. REMOVED AND REPLACED CABIN FLOOR SUPPORT AT FR 20...
L/H FWD WING TO FUSELAGE FAIRING ANGLE SUPPORT IS CRACKED. REMOVED AND REPLACED L/H FWD WING TO FUSELAGE FAIRING ANGLE SUPPORT...
L/H FLOOR SILL FRM 68 TO FRM 71 IS GOUGED.... REMOVED AND REPLACED L/H FLOOR SILL PER SRM 51-40-02
FWD CARGO RAMP WEB HAS CORROSION. REMOVED AND REPLACED FWD CARGO RAMP WEB ANGLE...
CARGO RAMP FWD ANGLE HAS SURFACE CORROSION ON LOWER MOUNTING HOLE. REMOVED AND REPLACED CARGO RAMP FWD ANGLE...
SHEAR CLIP AT FR 68 AT STR 6L TO 9L IS CRACKED. REMOVED AND REPLACED SHEAR CLIP.....
SHEAR CLIP AT FR 67 AT STR 6L 7L IS CRACKED. REMOVED AND REPLACED SHEAR CLIP AT STR 6 AT FR 67 IAW SRM 51-40-02
WEATHER RADAR FAIL. R&R WEATHER RADAR. OPS CHECK GOOD.
BAGGAGE DOOR INDICATION READ OPEN IN FLIGHT. CREW COULD NOT MAINTAIN CABIN PRESSURE. CHECKED INDICATION SWITCH IN CARGO DOOR. FOUND NO DISCREPANCIES. SUSPECT VENT PANEL ON CARGO DOOR NOT CLOSED PROPERLY. C/W PRESSURIZATION CHECK. OPS CHECK GOOD AND DOOR SHOWED CLOSED THROUGH OUT TEST.
BLEED 1 AND 2 OVERTEMP. R&R REFERANCE LINE BELOW CARGO FLOOR FOR HIGH TEMP THERMOSTATS. OPS CHECK GOOD.
A/B TO LESS THAN 80 KTS FOR MAIN CABIN DOOR OPEN INDICATION ON EICAS. DEFERRER DOOR WARNING. READJUSTED PAX DOOR MICRO SWITCHES. OPS CHECK GOOD.
ON POST FLIGHT. FOUND MAIN CABIN DOOR DIFFICULT TO OPEN. ADJUSTED MAIN DOOR AND OPS CHECK GOOD AT THIS TIME.
AFT FA FLASHLIGHT WILL NOT ILLUMINATE YET IS SHOWING CHARGING. R&R FA FLASHLIGHT, OPS CHECK GOOD.
OILY SMELL WITH APPARENT HAZE IN CABIN. R&R 0 CARBON SEAL ON NR 1 ENGINE. PERFORMED OPS CHECK. OPS CHECK GOOD. PERFORMED LEAK CHECK. NO LEAKS NOTED. PERFORMED VIBRATION TESTS. NO FAULTS NOTED.
OIL PRESSURE DROPPED ON NR 1 ENGINE. OIL QUANTITY SHOWED 3 QTS AT CRUISE. PERFORMED PRECAUTIONARY ENGINE SHUTDOWN CHECKLIST AND LANDED WITHOUT INCIDENT. REMOVED NR 1 GENERATOR, REPLACED O-RING AND INSPECTED FOR OIL LEAK. REPLACED NR 1 GENERATOR. PERFORMED OPS CHECK OF GENERATOR. OPS CHECK GOOD. PERFORMED NR 1 ENGINE HIGH POWER RUN. OIL PRESSURE AND QUANTITY REMAINED STABLE AND WITHIN LIMITS. NO FAULTS FOUND.
CABIN DOOR DIFFICULT TO OPEN & CLOSE. PERFORMED ADJUSTMENT AND TEST OF MAIN PAX DOOR. OPS CHECK GOOD AT THIS TIME.
MAIN CABIN DOOR DIFFICULT FOR FA TO OPEN. CLEANED AND LUBED MAIN CABIN DOOR PERFORMED OPS CHECKED.
BLEED 1 OVERTEMP IN ICING ON EICAS. PERFORMED QRH THEN GOT BLEED 2 OVERTEMP EXITED ICING. REMOVED AND REPLACED FAN AIR VALVE AND OUTLET TEMP SENSOR FOR BLEED SYSTEM 1. BOTH SYSTEMS OPS CHECK GOOD. TEMP SENSOR P/N: 0132ADT, S/N: E0380
BLEED 1 LEAK IN FLIGHT. INSPECTED LT AND RT BLEED BOTH ENG'S AT PACK CARGO & AT AVIONICS NO LEAK NOTED. RAN BOTH ENGINES COULD NOT DUPLICATE.
LOSS OF CABIN PRESSURIZATON IN FLT, STABILIZED CABIN PRESSURE AT 3.5. COMPLIED WITH GROUND PRESSURIZATION IN AUTO AND MANUAL MODES IAW AMM 21-31-00. OPS CHECKED GOOD AT THIS TIME.
DURING MX INSPECTION, BOTH EXTERIOR OVERWING EMERGENCY EXIT LIGHTS WERE DISCOVERED INOPERATIVE. MX R & R THE NR 4 EMERGENCY LIGHT SYSTEM BATTERY CHARGER WITH OPS CHECK GOOD. ACFT WAS APPROVED FOR RETURN TO SERVICE.
AIRCRAFT FWD EMERGENCY EXIT SIGN LIGHT INOPERATIVE. MAINTENANCE CLEANED CONTACTS FOR FWD EMERGENCY EXIT SIGN LIGHT IAW SWPM 20-21-00, OPS CHECK GOOD. THE ACFT WAS APPROVED FOR RETURN TO SERVICE.
DURING MAINTENANCE INSPECTION THE MAIN DOOR EMERGENCY EXIT LIGHT WAS FOUND INOPERATIVE. MX R & R THE MAIN DOOR EMERGENCY LIGHT ASSY WITH OPS CHECKED GOOD. ACFT WAS APPROVED FOR RETURN TO SERVICE.
THE CREW REPORTED AN NR 2 ENGINE LOW OIL PRESSURE, ACFT DIVERTED AND LANDED WITHOUT INCIDENT. MAINTENANCE R & R NR 4 GENERATOR GARLOCK SEAL, OPS AND LEAK TESTED WITH NO DEFECTS, ACFT APPROVED FOR RETURN TO SERVICE. ON REPOSITION FLIGHT, CREW REPORTED THAT THE NR 2 ENGINE LOST OIL AT 1QT PER 5 MINUTES, WHEN LEVEL REACHED 5QTS CREW RAN QRH AND SHUTDOWN ENGINE. ACFT DIVERTED AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND FOUND NR 4 GENERATOR TO BE DAMAGING THE GARLOCK SEAL. MAINTENANCE R & R THE NR 4 GENERATOR AND AFFECTED GARLOCK SEAL, OPS AND LEAK CHECKED WITH NO DEFECTS NOTED, AND ACFT APPROVED FOR RETURN TO SERVICE.
C-CHECK, THE CARGO DOOR FWD LWR SIDE WAS FOUND WITH 3 NUTPLATES SURROUNED BY CORROSION. MX CUT OUT THE DAMAGE AND INSTALL A FILLER WITH A INTERNAL DOUBLER IAW EC 52-30-10304.
C-CHECK, CORROSION WAS FOUND ON THE RT FLOOR SUPPORT AT NUTPLATES BETWEEN FRAME 18 AND 19. MX BLENDED CORROSION BEYOND LIMITS. REMOVED THE DAMAGE PART AND LOCATED AND PLACED A NEW PART, REF SRM 51-40-02.
C-CHECK,THE BAGGAGE DOOR LOWER SILL WAS FOUND CORRODED AROUND THE SCREW HOLES FOR THE DOOR EDGE TRIM. MX REMOVED ALL CORROSION AND INSTALL NEW PARTS IAW SRM 51-40-02.
C-CHECK, CORROSION WAS FOUND AROUND THREE NUTPLATES ON THE CENTER OMEGA BEAM AT FRAME 15 TO 16. MX REMOVED THE CORROSION AND REPLACED A NEW DIGITIAL AND REPAIR DOUBLERS REF SRM 51-40-02. ALL WORK ACCOMPLISHED AND WILL BE RELEASED AT THE END OF THE CHECK.
C-CHECK, CORROSION FOUND AT THE BOTTOM OF LT CARBON FIBER FRAME SUPPORT AT FRAME 61. MX REMOVED DOUBLER ALODINED AND INSTALL A NEW DOUBLER IAW SRM 51-40-02. ALL WORK ACCOMPLISHED AND WILL BE RELEASED AT THE END OF THE CHECK.
C-CHECK,CORROSION WAS FOUND ALONG THE RT OTBD FLOOR SUPPORT AT FRAME 41 THRU 47. MX R & R THE PART IAW SRM 53-23-00.
C-CHECK, CORROSION WAS FOUND ON THE LT OTBD FLOOR SUPPORT FROM FRAME 23 THRU 35. REMOVED CORROSION AND FOUND BEYOND LIMITS. REPLACED FLOOR SUPPORT IAW SRM 53-23-00.
C-CHECK, FRAME 10 WAS FOUND CRACKED NEAR THE DV WINDOW DRAIN. MX R & R FRAME IAW 53-11-00.
C-CHECK, CORROSION WAS FOUND ALONG THE LT OTBD FLOOR SUPPORT BETWEEN FRAME 36 TO 41. MX R & R IAW SRM 53-23-00.
C-CHECK , CORROSION WAS FOUND ON THE RT OMEGA BEAM IN 3 AREAS BETWEEN FRAME 59 AND 61. MX REMOVED THE CORROSION AND WAS OUT OF LIMITS. REMOVED THE DAMAGED PART AND DRILLED NEW PART AND INSTALL REF SRM 51-40-02. ALL WORK ACCOMPLISHED AND WILL BE RELEASED AT THE END OF THE CHECK.
C-CHECK, CORROSION WAS FOUND IN 2 AREAS OF THE LT FLOOR SUPPORT BETWEEN FRAMES 59 THRU 61. MX R & R A NEW PART IAW SRM 51-40-02 AND 51-20-03.
C-CHECK, THE LT FLOOR SUPPORT WAS FOUND CORRODED FROM FRAME 41 THRU 52. MX R & R IAW SRM 51-40-02.
CORROSION WAS FOUND ON THE LT OMEGA BEAM IN 2 AREAS BETWEEN FRAMES 59 THRU 61. MX R & R IAW SRM 51-40-02.
C-CHECK, THE LEFT ENGINE HAD SURFACE CORROSION AT THE 12 O'CLOCK POSITION. MX REMOVED THE SURFACE CORROSION ON REAR FLANGE IAW SRM 51-10-03. RESTORED SURFACE PROTECTION REF CPM 51-21-04. ALLOWABLE DAMAGE IAW EC 7230-01075. ALL WORK ACCOMPLISHED AND WILL BE RELEASED AT THE END OF THE CHECK.
C-CHECK, THE RT ENGINE HAD MINIOR CORROSION AT THE 12 O'CLOCK POSITION. MX REMOVED THE LIGHT CORROSION IAW SRM 51-10-03. RESTORED SURFACE PROTECTION IAW CPM 51-21-04. ALLOWABLE DAMAGE IAW EC7230-01075. ALL WORK ACCOMPLISHED AND WILL BE RELEASED AT THE END OF THE CHECK.
RIGHT OMEGA BEAM CORRODED BEYOND LIMITS AFTER BLEND OUT. R & R GUSSET.
OMEGA BEAM IS CORRODED BEYOND LIMITS AFTER BLEND-OUT IN 2 AREAS. REMOVED AND REPLACED GUSSET.
RIGHT FLOOR SUPPORT AT FRAME 23 THRU FRAME 25 CORRODED BEYOND LIMITS. AFTER BLEND-OUT, REMOVED AND REPLACED FLOOR SUPPORT.
GUSSET OF FRAME 22 RT FLOORBEAM, Y=479 CORRODED BEYOND LIMITS AFTER BLEND-OUT. R & R STRAP.
LEFT FLOOR SUPPORT BETWEEN FRM 41-47 IS CORROED BEYOND LIMITS AFTER BLEND OUT. REMOVED AND REPLACED SUPPORT.
CREW REPORTED STRONG ELECTRICAL ODOR COMING FROM F/O'S DISTRIBUTION BOX AND RETURNED TO GATE. CONTRACT MX FOUND CONTACTOR K0002, NR 2 WINDSHIELD HEAT TO BE BURNED AND SOURCE OF ODOR. DEACTIVATED SYS AND DEFERRED IAW MEL 30-42-02. ACFT WAS APPROVED FOR RETURN TO SERVICE WITH MEL. MX R & R NR 2 WINDSHIELD CONTACTOR K0002 WITH OPS CHECKS SUCCESSFUL. CLEARED MEL AND ACFT WAS APPROVED FOR RETURN TO SERVICE.
DURING PREFLIGHT, LIGHT WAS OUT ON GALLEY DOOR EMERGENCY EXIT SIGN. MX PERFORMED OPS CHECK ON GALLEY DOOR EMERGENCY EXIT SIGN, OPS CHECK GOOD IAW AMM 33-50-00. NO FURTHER MX REQUIRED. THE ACFT WAS APPROVED FOR RETURN TO SERVICE.
THE CREW REPORTED THAT THEY WERE UNABLE TO CONTROL THRUST SETTING IN FLIGHT. ON TAKEOFF ROLL THE THRUST SETTING WENT TO "E/T/O RESERVE". THE POWER THRUST RATINGS KEEP CHANGING RANDOMLY. THE ACFT RETURNED TO DEPARTURE AND LANDED WITHOUT INCIDENT, WHERE MX REPLACED THE THRUST SETTING MODULE SWITCH BOX, PERFORMED OPS CHECKS AND CLEARED THE DISCREPANCY.
DURING SCHEDULED MX INSP THE AFT EMERGENCY EXIT AT ROW 12 WAS FOUND INOPERATIVE. RIC MX R & R NR3 EMERGENCY LIGHT BATTERY IAW AMM 33-50-04 WITH OPS CHECK SUCCESSFUL. ACFT WAS APPROVED FOR RETURN TO SERVICE.
DURING SCHEDULED MX INSPECTION, BOTH RIGHT AND LEFT ROW 12 EMERGENCY EXIT AISLE LIGHTS FAILED TO ILLUMINATE. RIC MX FOUND NR 4 EMERGENCY LIGHT BATTERY CHARGER TO BE FAULTY. REMOVED AND REPLACED NR 4 EMERGENCY LIGHT BATTERY CHARGER IAW EMB145 AMM 33-50-04 WITH OPERATIONAL CHECK SUCCESSFUL. ACFT WAS APPROVED FOR RETURN TO SERVICE.
TYS - A/C WAS EN ROUTE TO RDU FROM IAD WHEN THE BLEED 1 OVERTEMP IN ICING CONDITIONS, QRH FOLLOWED BLEED 2 OVERTEMP PEGGED TO THE TOP. A/C WAS FERRIED TO TYS WHERE MAINTENANCE REMOVED AND REPLACED THE NR 1 HIGH TEMP THERMOSTAT IAW 36-11-06. REMOVED AND REPLACED THE NR 2 PRECOOLER IAW EMB 145XR AMM 36-11-04. REMOVED AND REPLACED THE NR 2 FAN AIR VALVE IAW EMB 145XR 36-11-03, OPS CHECK GOOD ON ALL REPLACEMENT PARTS AND WAS RELEASED. PARTS INVOLVED (PRECOOLER-PN-145-30609-401/SN 3267) (THERMOSTAT- 816624-9/SN-200212148).
IAD FLT 6026 - THE CREW REPORTED THE THRUST RATING QUADRANT IS ERRATICALLY SELECTING HIGH TAKEOFF THRUST SETTINGS. MAINTENANCE INSPECTED AND REPLACED THE LANDING GEAR ELECTRONIC UNIT. OPERATIONAL CHECKS WERE GOOD.
IAH - FLIGHT 2198, THE CREW REPORTED PRESSURIZATION LOST IN CRUISE. THE AIRCRAFT RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE MANUAL PRESSURIZATION CONTROLLER, AND PNEUMATIC OUTFLOW VALVE, OPERATIONALLY TESTED WITH NO DEFECTS, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.
IAH - FLIGHT 2198, THE CREW REPORTED PRESSURIZATION LOST IN CRUISE. THE AIRCRAFT RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE MANUAL PRESSURIZATION CONTROLLER, AND PNEUMATIC OUTFLOW VALVE, OPERATIONALLY TESTED WITH NO DEFECTS, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.
CLE FLT 3033 THE CREW REPORTED A LANDING GEAR AIR/GROUND FAIL MESSAGE IN FLIGHT. MAINTENANCE INSPECTED AND RE-ADJUSTED THE LEFT SHOCK ABSORBER WOW PROXIMITY SWITCH. OPERATIONAL CHECKS WERE GOOD.
FLIGHT 3000 - EWR - FLIGHT CREW REPORTED AFT FLIGHT ATTENDANCE HAND SET SHOWS EMERGENCY. EWR MX REMOVED AND REPLACED CONNECTOR (J8100 & P8100) AND PERFORMED OPERATIONAL CHECK SUCCESSFULLY. ACFT WAS APPROVED TO RETURN TO SERVICE.
IAH - FLIGHT 2121, THE CREW REPORTED THAT THE EXIT ROW EMERGENCY LIGHTS ILLUMINATED IN FLIGHT AND THEN TURNED OFF AFTER ABOUT 15 MINUTES. THE AIRCRAFT LANDED AT IAH WITHOUT INCIDENT. MAINTENANCE RE-SECURED A LOOSE PIN IN CONNECTOR P8031, OPERATIONALLY TESTED WITH NO DEFECTS, AND THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.
THE 12A EMERGENCY LIGHT IN OVERHEAD IS INOP. REMOVED AND REPLACED BULB IAW EMB 145XR AMM33-50-08, OPS CHECK GOOD.
FLIGHT 2900 - EWR - FLIGHT CREW REPORTED CABIN EMERGENCY LIGHTS ON IN ARMED POSITION DURING PUSHBACK. EWR MX REMOVED AND REPLACED INVERTER NR 4 & 5 AND POWER SUPPLY NR 5 AND PERFORMED OPERATIONAL CHECK SUCCESSFULLY. ACFT WAS APPROVED TO RETURN TO SERVICE. C2XA09RI209 REPORTS INVERTER INFORMATION AND C2XA09RI210 REPORTS POWER SUPPLY INFORMATION.
FLIGHT 2900 - EWR - FLIGHT CREW REPORTED CABIN EMERGENCY LIGHTS ON IN ARMED POSITION DURING PUSHBACK. EWR MX REMOVED AND REPLACED INVERTER NR 4 & 5 AND POWER SUPPLY NR 5 AND PERFORMED OPERATIONAL CHECK SUCCESSFULLY. ACFT WAS APPROVED TO RETURN TO SERVICE. C2XA09RI209 REPORTS INVERTER INFORMATION AND C2XA09RI210 REPORTS POWER SUPPLY INFORMATION.
FLIGHT 2353 - EWR - FLIGHT CREW REPORTED EMERGENCY EXIT LIGHTS INSIDE THE CABIN, ON OVER THE WING, CAME ON DURING FLIGHT. CREW RECYCLED EMERGENCY LIGHT AND IT WOULD GO OFF, BUT CAME BACK. EWR MX PERFORMED OPERATIONAL CHECK AND COULD NOT DUPLICATE THE PROBLEM. ACFT WAS APPROVED TO RETURN TO SERVICE.
IAH FLT 2124 - THE CREW REPORTED AN IAS COMPARATOR AND SPS ADVANCED MESSAGE ON THE EICAS IN FLIGHT. THE AIRCRAFT DIVERTED INTO CLE AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND REPLACED THE NR 1 AIR DATA COMPUTER. OPERATIONAL CHECKS WERE GOOD.
IAH - FLIGHT 2246, DURING CLIMB THE CREW REPORTED THAT THE PRIMARY PITCH TRIM SWITCH WAS INOPERATIVE. THE AIRCRAFT RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE REMOVED AND REPLACED THE F/O'S YOKE PITCH TRIM SWITCH, OPERATIONALLY TESTED WITH NO DEFECTS. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.
TYS FOR IAH - THE NR 2 PACK VALVE CLOSED MESSAGE WING A/1 FAIL. CREW DIVERTED TO MOB, WAS RELEASED IAW MEL 21-51-00/2 CAT (C) CONTROL/NUMBER 171254. LATER MAINTENANCE REMOVED AND REPLACED THE DUAL HEAT EXCHANGER AND OPS CHECK GOOD AND WAS REL.
FLT 4920 (FERRY FLIGHT) CABIN DOOR FAIL TO CLOSE. MX ADJUSTED STABILIZER ARMS AND ROLLERS ON CABIN DOOR OPS CHECK GOOD, FORCE APPLIED CHECK 40 LBS IAW AMM 52-18-00. THE AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.
SHV - DURING C-CHECK THE CARGO DOOR CUTOUT LOWER BEAM WAS FOUND TO BE CORRODED BETWEEN FRAMES 65 THROUGH 68. MAINTENANCE REMOVED AND REPLACED THE AFFECTED BEAM IAW EMB 145XR SRM 51-40-02. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE.
SHV - DURING C-CHECK CENTER OMEGA BEAM HAS CORROSION ON FR 20. MX REMOVED AND REPLACED CENTER OMEGA BEAM AT FR 16-24 IAW EMB 145 SRM 51-40-02. THE AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.
SHV - DURING C-CHECK CENTER OMEGA BEAM AT PREVIOUS REPAIR HAS CORROSION FR 24-25. MX REMOVED AND REPLACED PREVIOUS REPAIR AT CENTER OMEGA BEAM BETWEEN FR 24-25 IAW EMB 145 XR SRM 53-00-10 FIG 203 DET A. THE AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.
SHV - DURING C-CHECK LT OMEGA BEAM AT PREVIOUS REPAIR BETWEEN FR 24-25 IS CORRODED. MX REMOVED AND REPLACED LT PREVIOUS REPAIR BETWEEN FR 24-25 IAW EMB 145 XR SRM 53-00-10 ITEM 3. THE AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.
SHV - DURING C-CHECK LT OMEGA BEAM HAS CORROSION AT FR 21-23. MX REPAIRED LT OMEGA BEAM AT FR 21-23 IAW EC 5320-01406. THE AIRCRAFT WAS APPROVED TO RETURN FOR SERVICE.
FLIGHT 2513 - EWR - CREW REPORTED VIBRATION AND EXCESSIVE NOISE IN FLIGHT AFTER GEAR RETRACTION. EWR MX FOUND NOSE GEAR DOORS NOT TO CLOSE. MX REMOVED AND REPLACED GEAR DOOR SOLENOID VALVE. MX ALSO REMOVED AND REPLACED LANDING GEAR CONTROL LEVER. MX PERFORMED OPERATIONAL CHECK OF LANDING GEAR SUCCESSFULLY. ACFT WAS APPROVED TO RETURN TO FLIGHT.
IAH FLIGHT NR 3098, THE CREW REPORTED A SPOILER OPEN INDICIATION IN FLIGHT. THE AIRCRAFT DIVERTED INTO CLE AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED AND REPLACED THE LEFT OUTBOARD PROXIMITY SENSOR. OPERATIONAL CHECKS WERE GOOD.