N234TR

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,755 hrs · 33,922 cycles

CORROSION ON STR 28 LT FROM BS 985 TO BS 1016. REPAIRED DAMAGED SECTION PER SRM 53-10-3.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 43,755 hrs · 33,922 cycles

REMOVED FUSELAGE SKIN FROM BS 1016 TO 1033 FROM STR 26 RT TO 26 LT FOR ACCESS TO BS 1016 BULKHEAD REPAIRS. REPAIRED FUSELAGE SKIN PER SB 737-53A1075. REPAIRS TO THE BS 1016 BULKHEAD THAT REQUIRED REMOVAL OF FUSELAGE SKIN ARE REPORTED ON UNIQUE CONTROL NR 234TR0022 AND 234TR0023.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,755 hrs · 33,922 cycles

CORROSION ON STR 26 RT FROM BS 1006 TO BS 1016. REPLACED DAMAGED SECTION PER SRM 51-10-1 AND SRM 51-40-04.

Part: STIFFENER — CORRODED (BULKHEAD) · corrosion level 2 · airframe 43,755 hrs · 33,922 cycles

BS 1016 BULKHEAD FORWARD SIDE CHANNEL STIFFENER AT BL 0 HAS CORROSION. REPAIRED PER SB 737-53A1075.

Part: BULKHEAD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,755 hrs · 33,922 cycles

AFT SIDE OF BS 1016 BULKHEAD AT BL 0 CORRODED. REPAIRED PER SB737-53A1075.

Part: COMPUTER — INOPERATIVE (AUTOPILOT) · airframe 43,619 hrs · 33,823 cycles

AUTO PILOT A SIDE KICKED OFF BY ITSELF AND THEN WILL NOT REENGAGE. REPLACED A CHANNEL FCC IAW MM 22-11-331 AND OPS CHECKED IAW MM 22-11-01.

Part: COMPUTER — MALFUNCTIONED (FCC) · airframe 43,610 hrs · 33,814 cycles

BOTH A&B AUTO PILOTS DISENGAGE IN SMOOTH AIR, LEVEL FLIGHT, WITHOUT PROVOCATION. REPLACED B-SYSTEM FCC COMPUTER. OPS CHECKS NORMAL PER MM 22-11-331.

Part: COMPUTER — MALFUNCTIONED (AUTOTHROTTLE) · airframe 43,580 hrs · 33,793 cycles

NR 1 AUTO THROTTLE WILL NOT ARM. RESEATED AUTO THROTTLE COMPUTER AND PERFORMED BITE TEST. OPERATION NORMAL PER MM 22-31-01.

Part: BATTERY PACK — INOPERATIVE (EMERGNECY LIGHT) · airframe 43,524 hrs · 33,744 cycles

EMERGENCY LIGHTS OUTSIDE OF L1 AND R1 DOORS INOP. REPLACED BATTERY PACK IN FORWARD CARGO BIN. LIGHTS OPERATE NORMAL PER MM 33-51-01.

Part: COMPUTER — MALFUNCTIONED (COCKPIT) · airframe 43,449 hrs · 33,668 cycles

MCP AUTOPILOT B INOP AND F/O FLIGHT DIRECTOR INOP. PLACED ON MEL 22-15-2.

Part: CONNECTOR — DIRTY (CONTROL PANEL) · airframe 43,445 hrs · 33,666 cycles

MODE CONTROL PANEL SWITCHES AUTO PILOT ENGAGE INOP AND FLIGHT DIRECTOR INOPERATIVE. CLEANED AND RESEATED CONNECTOR. OPS CHECKS GOOD PER MM 22-15-0.

Part: CONTROL PANEL — MALFUNCTIONED (COURSE SELECTOR) · airframe 43,443 hrs · 33,663 cycles

COPILOT COURSE SELECTOR ON MCP WILL NOT ALLOW YOU TO SELECT 122 DEGREES. REPLACED MCP PER MM 22-11-341 AND OPS CHECKED.

Part: O-RING — LEAKING (FF TRANSMITTER) · airframe 43,362 hrs · 33,583 cycles

WHEN SERVICING NR 2 ENGINE OIL, SMELLED FUEL. FOUND FUEL FLOW TRANSMITTER LEAKING. REPLACED 3 O-RINGS. LEAK CHECKED OK PER MM 73-31-12.

Part: TRANSMITTER — OUT OF ADJUST (NR 1 THROTTLE) · airframe 43,295 hrs · 33,525 cycles

LEFT POWER LAGS FROM IDLE TO POWER IN FLIGHT WITH AUTOTHROTTLES ON. ADJUSTED NR 1 THROTTLE TRANSMITTERS PER MM 22-31-81. OPS CHECKS GOOD ON GROUND RUN.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 43,236 hrs · 33,472 cycles

EMERGENCY LIGHT ABOVE R1 DOOR INOP. REPLACED LIGHT ASSEMBLY. OPS CHECKS OK.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 43,231 hrs · 33,464 cycles

RT OVERWING EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED BATTERY POWER SUPPLY IAW MM 33-51-31. OPS CHECKS GOOD.

Part: PCU — MALFUNCTIONED (RUDDER) · airframe 43,184 hrs · 33,427 cycles

YAW DAMPER REPORTED WILL NOT STAY ENGAGED. SHOWS FAULT HISTORY MESSAGE 22-21003. REPLACED RUDDER POWER CONTROL UNIT PER MM 27-21-91 AND PERFORMED ADJUSTMENT AND TEST PER MM 27-21-91. YAW DAMPER CHECKS NORMAL PER MM 22-12.

Part: WIRE — MALFUNCTIONED (FLT CON COMP) · airframe 43,184 hrs · 33,427 cycles

FLIGHT CONTROL COMPUTER FAILS LRU INTERFACE TEST 25.21 SUBTEST 1 AND 2. REMOVED E1-1 SHELF AND CORRECTED WIRING. OPS NORMAL.

Part: SKIN — CRACKED (FUSELAGE) · airframe 43,184 hrs · 33,427 cycles

FUSELAGE SKIN CRACKED AFT OF COOLING AIR EXHAUST VENT. REPAIRED PER BOEING SB 737-53-1117.

Part: INDICATOR — MALFUNCTIONED (HSI) · airframe 43,184 hrs · 33,427 cycles

FIRST OFFICER'S HSI - VOR FROM, ILS VALID, VOR VALID, FLAG ERRONEOUS. REPLACED HSI. ALL FUNCTIONS OPERATE NORMAL.

Part: WIRE — BROKEN (AUTOPILOT SYS) · airframe 43,184 hrs · 33,427 cycles

B-AUTO PILOT FAILED LRU INTERFACE -MCP TEST 73.6 (HDG SYNC). REPAIRED BROKEN WIRE AT CONNECTOR D994 ON E1-2 SHELF. OPERATES NORMAL.

Part: GYRO — MALFUNCTIONED (COCKPIT) · airframe 43,218 hrs · 33,455 cycles

NR 1 VERTICAL GYRO SHOWS 3.5-4 DEGREES PITCH UP. REPLACED VERTICAL GYRO PER MM 34-21-21.

Part: GYRO — INACCURATE (COCKPIT) · airframe 43,218 hrs · 33,455 cycles

NR 1 VERTICAL GYRO SHOWS 3.5-4 DEGREES PITCH UP. REPLACED VERTICAL GYRO PER MM 34-21-21.

Part: FUEL CONTROL — MALFUNCTIONED (NR 1 ENGINE) · airframe 43,218 hrs · 33,455 cycles

NR 1 ENGINE ROLLED BACK ON SHORT FINAL APPROACH. REPLACED IGNITION EXCITER BOX PER MM 74-11-11 AND REPLACED FUEL CONTROL UNIT PER MM 73-09-255. OPS CHECKS OK.

Part: GPS — MALFUNCTIONED (COCKPIT) · airframe 43,205 hrs · 33,447 cycles

GPS WILL NOT ACQUIRE ANY SATELLITES. REMOVED AND REPLACED GNLU. GPS NOW ACQUIRES SATELLITES ON GROUND.

Part: SENSOR — MALFUNCTIONED (AUTOPILOT) · airframe 43,214 hrs · 33,451 cycles

AUTO-PILOT A&B NEUTRAL SHIFT SENSOR OUT OF TOLERANCE PER ELEVATOR RIGGING BITE TEST. REMOVED, REPLACED, AND ADJUSTED NEUTRAL SHIFT SENSOR. OPS. CHECKS GOOD PER MM 22-11-122.

Part: RECEIVER — UNRELIABLE (VOR SYSTEM) · airframe 43,205 hrs · 33,447 cycles

BOTH VOR RECEIVERS ARE ERRATIC AND UNRELIABLE. REMOVED AND REPLACED BOTH RECEIVERS. OPS CHECKS GOOD PER MM 34-31-41.

Part: TURBINE — FAILED (NR 2 ENGINE)

ON APPROACH, THE FLIGHT CREW NOTED A VIBRATION AT 30 PERCENT POWER IN THE RIGHT (NUMBER 2) ENGINE. THE FLIGHT CREW REDUCED POWER AND MADE A NORMAL LANDING. THE ENGINE WAS SHUT DOWN AND TAKEN TO THE GATE. DURING THE WALK AROUND INSPECTION, MAINTENANCE NOTED METAL FUSED TO THE ROSEBUD AND SIDES OF THE EXHAUST.

Part: ATTACH ANGLE — CRACKED (LT WING) · airframe 41,270 hrs · 32,152 cycles

DURING C-1 CHECK, INSPECTION REPORTED CRACKED ATTACH ANGLE ON LT WING LOWER TRAILING EDGE PANEL ON MLG BEAM. FABRICATED AND INSTALLED REPLACEMENT L-ANGLE PER SOPM 20-41-02 AND SRM 51-40-02.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,270 hrs · 32,152 cycles

DURING C-1 CHECK, INSPECTION REPORTED CORROSION ON WEB SUPPORT, STR 21L, STA 967. REPLACED WEB SUPPORT PER 51-30-2 SOPM 20-41-02.

Part: DOUBLER — CRACKED · airframe 41,270 hrs · 32,152 cycles

DURING C-1 CHECK, INSPECTION REPORTED DOUBLER CRACKED AT LOWER AFT CORNER OF EXT. POWER DOOR CUTOUT. REMOVED CRACK IN DOUBLER AND REPAIRED PER SRM 53-30-01.

Part: PANEL — CRACKED (VERTICAL STAB) · airframe 41,270 hrs · 32,152 cycles

DURING C-1 CHECK, INSPECTION REPORTED LT VERTICAL PANEL 9507L INNER BRACE WORN AND CRACKED. FABRICATED PANEL RETAINER AND INSTALLED PER SRM 51-40-2, 51-30-50 AND SOPM 20-41-02.

Part: SOLENOID — FAILED (LANDING GEAR) · airframe 40,731 hrs · 31,802 cycles

UPON TAKEOFF IN SLC, HAD TO PULL LANDING GEAR LEVER TRIGGER TO GET GEAR HANDLE UP. IN DEN, MADE LOW PASS BY DENVER TOWER TO CONFIRM GEAR DOWN. NO GEAR INDICATION LIGHTS. RECYCLED HANDLE, ALL INDICATIONS NORMAL AND LANDED WITHOUT INCIDENT. REPLACED LANDING GEAR LEVER LOCK SOLENOID PER MM 32-31-31 AND REPLACED LANDING LIGHTS CIRCUIT BREAKER PER WDM 24-56-01. PERFORMED LANDING GEAR SWING PER MM 32-32-0, TELEFLEX CABLE RIG CHECK PER MM 27-26-51, AND MANUAL EXTENSION TEST PER MM 32-38-0.

Part: HYDRAULIC LINE — LEAKING (NR 2 ENGINE) · airframe 40,504 hrs · 31,641 cycles

EN ROUTE FROM PHX TO DEN, FLIGHT CREW REPORTED A-SYSTEM HYDRAULIC QUANTITY DROPPED TO ZERO, WITH SUBSEQUENT SYSTEM FAILURE. AN EMERGENCY WAS DECLARED AND AIRCRAFT LANDED WITHOUT INCIDENT. REPLACED NR 1 ENGINE HYDRAULIC PRESSURE LINE FOUND TO BE LEAKING AND PERFORMED LEAK CHECK. NO LEAKS NOTED.

Part: OUTFLOW VALVE — OBSTRUCTED (CABIN PRESSURE) · airframe 38,480 hrs · 30,359 cycles

AIR TURNBACK. FLT CREW REPORTED PRESSURIZATION NORMAL THROUGH 10,000 FT ACFT WENT TO STANDBY MODE AND CABIN PRESSURE CONTINUED TO CLIMB. SET STANDBY MODE AT 5.6 PSI AND CABIN STILL CONTINUED TO CLIMB. MANUALLY CLOSED OUTFLOW VALVE AND SUBSEQUENTLY OXYGEN MASKS DEPLOYED. RETURNED TO MDW AND LANDED WITHOUT INCIDENT. MX INSPECTED ACFT AND FOUND A 12 INCH PIECE OF INSULATION PROTRUDING FROM OUTFLOW VALVE. REMOVED INSULATION, PERFORMED CABIN LEAKAGE TEST PER MM 5-51-91, PG 202 AND CHECKED OK. ACFT WAS FERRIED TO DEN FOR MAINTENANCE AND TO RESTOW OXYGEN MASKS. UPON ARRIVAL IN DEN, OXYGEN MASKS WERE RESTOWED, PASSENGER OXYGEN BOTTLE WAS REPLACED, A SERVICE CHECK WAS ACCOMPLISHED.

Part: RELIEF VALVE — FAILED (LT WING) · airframe 38,114 hrs · 30,118 cycles

AIR TURNBACK. FLIGHT CREW REPORTED FUEL LEAK FROM LT WING ON TAKEOFF AND CLIMB. FOUND LT WING SURGE TANK RELIEF VALVE FAILED OPEN AND REPLACED SAME PER MM 28-13-41.

Part: HOUSING — CORRODED (EXTERIOR LIGHT) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON RT WING INSPECTION LIGHT HOUSING MATING SURFACE BETWEEN HOUSING AND FUSELAGE SKIN. REPLACED RT WING INSPECTION LIGHT HOUSING PER SRM 51-30-02.

Part: WEB — CORRODED (CARGO DOORWAY) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT CARGO DOOR SCUFFPLATE WEB CORRODED. REPLACED STRAP PER SRM 51-30-2 AND DRAWING NR 65-47957.

Part: STRAP — CORRODED (CARGO BAY) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT FLOOR NUT PLATE STRAP AT STA 770 CORRODED. REPLACED STRAP PER SRM 51-10-2.

Part: SHEAR TIE — CORRODED (CARGO BAY) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON SHEAR TIE AT STA 500A BETWEEN STR 27L AND 26L. FABRICATED AND INSTALLED REPLACEMENT SHEAR TIE PER SRM 53-10-2, SRM 53-10-4, SRM 51-30-2 AND SOPM 20-41-02.

Part: SHEAR TIE — CORRODED (FWD CARGO COMPT.) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON STRINGER TO FRAME TIE CLIP IN FORWARD CARGO COMPARTMENT STA 540, STR 25L. FABRICATED AND INSTALLED REPLACEMENT TIE CLIP PER SRM 53-10-2, 51-30-4 AND 51-30-2.

Part: FAIRING — CRACKED (NR 2 ENGINE) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED A 1/2 INCH CRACK ON INSIDE AFT CORNER OF NR 2 ENGINE INBOARD FIXED FAIRING. MAINTENANCE REMOVED DAMAGED GUSSET AND "L" ANGLE AND FABRICATED AND INSTALLED REPLACEMENT PARTS PER SRM 54-10-2, 51-10-2 AND 51-30-2.

Part: LIGHT — CORRODED (LT WING) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED LT. WING INSPECTION LIGHT HOUSING CORRODED AROUND OUTER PERIMETER OF MATING SURFACE TO FUSELAGE SKIN AT STA. 500B INSIDE AIRCRAFT. MAINTENANCE REMOVED LIGHT HOUSING AND CLEANED, TREATED AND PRIMED AREA. INSTALLED NEW LIGHT HOUSING ASSY. AND TREATED, PRIMED AND PAINTED EXTERIOR PER SRM 51-10-6, 53-10-1 51-30-2 AND SOPM 20-41-02.

Part: ANGLE — CORRODED (AFT CARGO PIT) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION UNDER AFT CARGO COMPARTMENT SUPPORT ANGLE THRESHOLD. MAINTENANCE REPLACED AFT CARGO COMPARTMENT SUPPORT ANGLE UNDER THRESHOLD PER SRM 51-30-2 AND DRAWING NO. 69-43233.

Part: ANGLE — CORRODED (AFT CARGO PIT) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION UNDER AFT CARGO COMPARTMENT SUPPORT ANGLE THRESHOLD. MAINTENANCE REPLACED AFT CARGO COMPARTMENT SUPPORT ANGLE UNDER THRESHOLD PER SRM 51-30-2 AND DRAWING NO. 69-43233.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED FLOOR INTERCOSTAL CORRODED FROM STA. 947.6 TO 967, RBL 8". REPLACED FLOOR INTERCOSTAL PER SRM 53-10-9 AND 51-10-2.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CRACK IN WEB BETWEEN STA. 344 AND STA. 360, STR. 16L. MAINTENANCE REMOVED DAMAGED AREA AND FABRICATED AND INSTALLED FILLER AND DOUBLER PER SRM 51-40-2.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED ANGLE CRACKED UNDER WING-TO-BODY FAIRING AT STA. 540, STR. 22-R. MAINTENANCE STOP DRILLED CRACKS, FABRICATED AND REPLACEMENT ANGLE PER SRM 51-30-02.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION UNDER AFT CARGO COMPARTMENT THRESHOLD IN THE FRAME AREA (UNDER KICK PLATE). MAINTENANCE REMOVED CORROSION, TREATED AND PRIMED AREA PER SRM 53-10-1.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON STRINGER 27L AT STA. 510A, FORWARD CARGO PIT. MAINTENANCE FABRICATED REPLACEMENT STRINGER AND INSTALLED IN ACCORDANCE WITH SRM 53-10-3 AND SRM 51-30-2.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION AND CRACK ON SHEARTIE AT STA. 500, STRINGER 25R, AFT OF FORWARD CARGO DOOR, LOWER CORNER. MAINTENANCE REMOVED DAMAGED AREA AND REPAIRED IN ACCORDANCE WITH SRM 53-10-4.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 37,857 hrs · 29,952 cycles

DURING C-7 CHECK, INSPECTION REPORTED STRINGER TIE CLIPS CRACKED AT STA. 1040, STRINGERS 13L, 14L, 15L AND 16L. REPLACED STRINGER CLIPS PER SRM 51-10-2 AND 51-30-2.