N828AX

Part: VALVE — FAULTED (CABIN PRESSURE) · airframe 54,584 hrs · 9,496 cycles

CABIN ALTITUDE WARNING - EICAS MESSAGE @ 10650'. CABIN WOULD NOT PRESSURIZE.

Part: NONE — NONE · airframe 50,283 hrs · 8,561 cycles

EGT EXCEEDANCE ON RIGHT ENGINE AFTER TAKEOFF. CORRECTIVE ACTION: PERFORMED VISUAL INSPECT OF ENGINE NO DEFECTS NOTED & PERFORMED FIM 71-05-806 NO RELATED OVERTEMP MSGS ON MAT - ENGINE TO CONTINUE TO SERVICE. ACCOMPLISHED RIGHT ENG WASH TRENT 892 TRENT PER 77TC-1201. PERFORMED ON AIR SUPPLY SYSTEM DECAY TEST IAW B777 AMM 36-10. OPS CHECKS GOOD. NO LEAKS DETECTED AT THIS TIME. PERFORMED RESISTANCE CHECK ON ALL THERMOCOUPLES IAW B777 AMM 77-21

Part: FMU — FAILED · airframe 49,824 hrs · 8,464 cycles

LEFT ENGINE EGT EXCEEDANCE ON TAKEOFF PEAK EGT 923°CLEFT ENGINE EGT EXCEEDANCE ON TAKEOFF PEAK EGT 923°C. CORRECTIVE ACTION: PERFORMED BORESCOPE, ENGINE WASH AND R&R OF FMU. NO MAINTENANCE MESSAGES NOTED OR DAMAGE FOUND PER AMM 71-00.

Part: NONE — NONE · airframe 49,823 hrs · 8,463 cycles

EGT EXCEEDENCE LEFT ENGINE @ 200 FT ON TAKEOFF ~ CORRECTIVE ACTION: FOLLOWED FIM 71-05 TASK 806. ENGINE TEMPS AND EXCEEDENCE TIME WITHIN LIMITS. ALL INSPECTIONS AND TEST COMPLETED. NO DEFECTS NOTED AT THIS TIME. ENGINE IDLE RUN SHOWN NO SIGNS OF ISSUES. DURING INSPECTION FOUND TURBINE OVERHEAT DETECTOR CONNECTOR STUD SPINNING ON LEFT ENGINE. REMOVED AND REPLACED LEFT ENGINE IP TURBINE OVERHEAT THERMOCOUPLE PER AMM 77-22-11.

Part: LINE — DAMAGED (HYD SYSTEM) · airframe 43,027 hrs · 7,095 cycles

HYD QTY LOW C EICAS MESSAGE DISPLAYED IN FLIGHT. R & R A DAMAGED HYD LINE AT THE TRUNNIONS SWIVEL ASSY IAW AMM 20-10. LEAK CHECK GOOD AT THIS TIME.

Part: PROBE — INACCURATE (CENTER TANK FUEL) · airframe 42,286 hrs · 6,960 cycles

EICAS MESSAGE "FUEL DISAGREE" DISPLAYED ON CLIMB OUT. TOTALIZER FUEL READ 16 THOUSAND LBS. LESS THAN CALCULATED FUEL AND LIFT OFF FUEL SHOWED 6 THOUSAND LBS LESS THAN FLT PLN EXPECTED LIFT OFF FUEL. PERFORMED APPR CHECKLIST NON NORMAL. 2 POSSIBLIES - FUEL LEAK IN CTR TNK OR BAD CENTER FUEL GAUGE. QRH PROCEDURE INDICATES POSSIBLE CENTER TANK FUEL LEAK. CORRECTIVE ACTION: REMOVED AND REPLACED ALL CTR TANK FUEL PROBES PER AMM 28-11.

Part: WINDOW — CRACKED (R2) · airframe 41,336 hrs · 6,760 cycles

INFLIGHT, R2 DOOR HAD A CRACKED WINDOW, DIVERTED. PRESSURIZATION REMAINED NORMAL THROUGHOUT FLIGHT. REMOVED AND REPLACED WINDOW AT R2 DOOR IAW AMM 56-31. PRESSURE CHECK GOOD IAW AMM 05-51

Part: LIGHT — INOPERATIVE (CABIN) · airframe 37,839 hrs · 6,093 cycles

OVERHEAD EMERGENCY EXIT LIGHT AT SEAT 38AC INOP DUE TO EO B7733-08. COMPLETED EO B7733-09 ON LOG PAGE 155583 ENTRY 2. OPS CHECK NORMAL.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHT) · airframe 81,241 hrs · 27,099 cycles

A/C EMERGENCY BATTERY PAC WOULD NOT RECHARGE. REMOVED AND REPLACED EMERGENCY LIGHTING BATTERY AND RELAY UNIT. SYSTEM OPS CHECKED GOOD IAW MM 33-50-01.

Part: FITTING — CORRODED (LT WHEEL WELL) · airframe 81,091 hrs · 26,982 cycles

LEFT WHEEL WELL AT STA 902 AND HORIZONTAL PRESSURE PANEL ABOVE LONGERON 24 LEFT, SMALL ATTACH FITTING HAD EXFOLIATING CORROSION. REMOVED AND REPLACED SMALL ATTACH FITTING AT LEFT WHEEL WELL, STA 902 AND HORIZONTAL PRESSURE PANEL ABOVE LONGERON 24 LEFT IAW DC8 SRM 51-3-0 AND 51-1-20D.

Part: FITTING — CRACKED (FWD PRESS PANEL) · airframe 81,091 hrs · 26,982 cycles

RIGHT WHEEL WELL, FORWARD PRESSURE PANEL AT STA 857, RIGHT UPPER CORNER HAD CRACKED FITTING. REMOVED AND REPLACED CRACKED FITTING AT RIGHT WHEEL WELL AT STA 857 RIGHT SIDE IAW DC8 SRM 51-3-0.

Part: RIB — BROKEN (RT WING LE) · airframe 81,091 hrs · 26,982 cycles

RIGHT WING LEADING EDGE, OUTBOARD CLOSURE RIB, FORWARD EDGE OF THE HORIZONTAL FLANGE AT WING STA XS 526, BROKEN OFF. ACCOMPLISHED BLEND OUT REPAIR AT RIGHT WING LEADING EDGE CLOSURE RIB IAW REA D857-53072.

Part: STRAP — CRACKED (BULKHEAD) · airframe 81,091 hrs · 26,982 cycles

AFT CARGO COMPARTMENT FORWARD BULKHEAD REINFORCEMENT STRAP AT STATION 980 AND JUST ABOVE LONGERON 33 LEFT, CRACKED. STOP DRILLED CRACK AND INSTALLED REPAIR ANGLE AT REINFORCEMENT STRAP AT STA 980, JUST ABOVE LONGERON 33 LEFT IN AFT CARGO COMPARTMENT, FORWARD BULKHEAD IAW DC8 SRM 51-1-20D.

Part: LATCH — CRACKED (AFT CARGO DOOR) · airframe 81,091 hrs · 26,982 cycles

AFT CARGO COMPARTMENT, FORWARD DOOR, LOWER CUT OUT LOCKING LATCH, NR 1 FROM FORWARD END APPEARED CRACKED AT ATTACH UPPER FORWARD CORNER. REMOVED AND REPLACED FITTING LATCH NR 1 AT AFT CARGO COMPARTMENT FORWARD DOOR LOWER CUT OUT IAW DC8 SRM 51-1-20D.

Part: ANGLE — CORRODED (RT WHEEL WELL) · airframe 81,091 hrs · 26,982 cycles

RIGHT WHEEL WELL FORWARD BULKHEAD SHELF ANGLE CORRODED. LOCATED 14" INBOARD OF LONGERON 24 RIGHT. REMOVED AND REPLACED CORRODED ANGLE INBOARD OF LONGERON 24 RIGHT AT RIGHT WHEEL WELL FORWARD BULKHEAD.

Part: FINGER DOUBLER — CORRODED (AFT CARGO) · airframe 81,091 hrs · 26,982 cycles

AFT CARGO COMPARTMENT, CORROSION AT FINGER DOUBLER, LONGERON 31 LEFT, STA 1495 - 1510. CUT OUT DAMAGED FINGER DOUBLER, FABRICATED AND INSTALLED FINGER DOUBLER SECTION IAW REA D853-53073.

Part: RIB — CRACKED (RT WING L/E) · airframe 81,091 hrs · 26,982 cycles

RIGHT WING LEADING EDGE, RIB AND ANGLE CRACKED AT STA 520. STOP DRILLED CRACKS IN RIB, FABRICATED L-STRAP REPAIR, FABRICATED NEW ANGLE, REMOVED OLD ANGLE AND INSTALLED L-STRAP REPAIR AND NEW ANGLE IAW REA D857-53074-MR AND DC8 SRM 57-2-0, (3 CRACKS - RIB FWD = .65", RIB AFT = 2.40", ANGLE = 2.17").

Part: REPAIR — CRACKED (RT WING L/E) · airframe 81,091 hrs · 26,982 cycles

RIGHT WING LEADING EDGE EXTERIOR TOP SURFACE REPAIR DOUBLER WAS CRACKED JUST INBOARD AND AFT OF OUTBOARD SLOT. REMOVED AND REPLACED DAMAGED EXISTING REPAIR DOUBLER FORM UPPER SKIN TRAILING EDGE SECTION IAW DC8 SRM 57-2-1.

Part: SUPPORT BRACKET — CORRODED (RT WING ROOT) · airframe 81,091 hrs · 26,982 cycles

RIGHT WING ROOT TOP FAIRING SUPPORT BRACKET WAS WORN AND WITH CORROSION AT REAR SPAR, TOP SURFACE. REPLACED FAIRING SUPPORT BRACKET IAW DC8 SRM 51-1-2 AT RIGHT WING ROOT TOP FAIRING.

Part: SKIN — CORRODED (FUSELAGE) · airframe 79,788 hrs · 26,216 cycles

AFT CARGO LONGERON 35 RIGHT, BLEEDING CORROSION BETWEEN TOP OF LONGERON AND INTERCOSTAL, STA 1080. REPAIRED AREA IAW REA D853-49160MR.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 79,788 hrs · 26,216 cycles

AFT LOWER CARGO COMPARTMENT, STA 1380, AT LONGERON 36, THE FORWARD SIDE OF FRAME 1380 HAD CORROSION. BLENDED AND REMOVED ALL CORROSION IAW DC-8 SRM 51-1-8. FABRICATED REPAIR PARTS IAW REA D853-49155MR. ALODINED AND PRIMED IAW DC-8 SRM 51-1-8. INSTALLED IAW DC-8 SRM 51-1-20B.

Part: SERVO VALVE — MALFUNCTIONED (AUTOPILOT) · airframe 79,173 hrs · 25,766 cycles

UNCOMMANDED YAW IN FLIGHT. AUTOPILOT ON. REPLACED RUDDER POWER PACK TRANSFER VALVE IAW DC-8 MM 27-21-6.

Part: COMPUTER — DEFECTIVE (YAW DAMPER) · airframe 79,173 hrs · 25,766 cycles

RUDDER UNCOMMANDED LT INPUT AT 3,000 FT, 200 KTS, AND 23 DEGREES FLAPS. AUTOPILOT OFF, YAW DAMPER ON. COULD NOT DUPLICATE PROBLEM. REPLACED YAW DAMPER COMPUTER. OPS CHECKED GOOD IAW DC-8 MM 22-10-00.

Part: WEB — CRACKED (FUSELAGE) · airframe 79,156 hrs · 25,751 cycles

CUSP WEB CRACKED AT FS 300 RIGHT ON MOST OUTBOARD TRACK. REPAIRED AREA IAW DC-8 SSRM 51-1-21 AND DWG. K07142. REF: W/O 600166120.

Part: ENGINE — FAILED (NR 4) · airframe 79,112 hrs · 25,718 cycles

NR 4 ENGINE SHUTDOWN DUE TO LOSS OF OIL QUANTITY AND OIL PRESSURE, AT 1100Z WINDMILLING, OIL PRESSURE 3 PSI, N2 30 PERCENT. REMOVED AND REPLACED THE NR 4 ENGINE IAW DC-8 MM AND ABX WORK PACK 600166755.

Part: PIN — LOOSE (LT MLG ACTUATOR) · corrosion level 2 · airframe 79,049 hrs · 25,662 cycles

LT MAIN LANDING GEAR ACTUATING CYLINDER RETRACT PIN WAS LOOSE, DUE TO WORN RETRACT PIN BOSS BUSHING. DISASSEMBLED LT MAIN LANDING GEAR ACTUATOR CYLINDER, REMOVED RETRACT PIN BOSS BUSHING. INSPECTED BORE, MANUFACTURED BUSHING. INSTALLED AND REASSEMBLED IAW REA D832-44219 AND REA D832-45979MR, NEA 32130001-001.

Part: PRESSURE SWITCH — DAMAGED · airframe 78,928 hrs · 25,576 cycles

#1 OIL PRESSURE LIGHT ILLUMINATED. PRESSURE/TEMP. GOOD. #1 THROTTLE TO IDLE. LIGHT REMAINED ON. SECURED ENGINE. RAN ENGINE, NO DISCREPANCY, DISCONNECTED BOTH OIL MAIN WARNING SWITCHES. MEGGED WIRE FROM DIM BOX, NO DISCREPANCY. ON INSPECTION, FOUND DIFFERENTIAL OIL PRESSURE SWITCH DAMAGED EXTERNALLY. HOLE IN CASE. REPLACED SWITCH IAW DC-8 MM 79-33-01-2. OPS AND LEAK CHECKED GOOD ON ENGINE RUN.

Part: SKIN — BENT (LT SPOILER) · airframe 78,864 hrs · 25,535 cycles

NR 2 LEFT SPOILER INBOARD HINGE SKIN WAS BENT. REPAIRED DAMAGED AREA, FABRICATED REPAIR FILLER AND DOUBLER, INSTALLED IAW ABX REA D827-44011MR AND SRM CHAPTER 51.

Part: FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 10, ATTACHING HOLES HAD 5 CRACKS IN HOLES. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 3, HAD 5 HOLES CRACKED AT ATTACHING HOLES. REPAIRED AREA IAW REA D852-36710MR. REMOVED AND REPLACED FRAME SECTIONS IAW ABX REA D852-36710MR.

Part: FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 9, ATTACHING FASTENER HOLES HAD 5 CRACKS IN HOLES. REMOVED AND REPLACED FRAME SECTION IAW REA D852-36710MR.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 5, ATTACHING HOLES HAD 3 CRACKED HOLES. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: LATCH — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 8, ATTACHING HOLES HAD 5 CRACKS. REMOVED AND REPLACED FRAME SECTION IAW REA D852-36710MR.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 7, ATTACHING HOLES HAD 6 CRACKS IN HOLES. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 11, ATTACHING HOLES HAD 6 FASTENERS CRACKED. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 6, ATTACH HOLES HAD 5 CRACKS IN HOLES. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: DOOR FRAME — CRACKED (CARGO DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CARGO DOOR, LATCH NR 4, ATTACHING HOLES HAD 5 CRACKED HOLES. REMOVED AND REPLACED FRAME SECTION IAW ABX REA D852-36710MR.

Part: DOOR FRAME — GOUGED (PAX DOOR) · airframe 78,864 hrs · 25,535 cycles

MAIN CABIN L1 DOOR, INSIDE AFT CENTER FRAME AT EDGE, HAD A DEEP GOUGE WEAR AT POINT WHERE BAYONET CONTACTS LATCH. REPAIRED AREA IAW REA D852-44006MR.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,864 hrs · 25,535 cycles

AFT LOWER CARGO, STA 990, LONGERON 36, SKIN WAS CORRODED. REPAIRED AREA IAW REA D853-44014MR AND DC-8 SRM 51-1-8.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,864 hrs · 25,535 cycles

AFT LOWER CARGO, STA 1000, LONGERON 36 SKIN CORRODED. REPAIRED AREA IAW REA D853-44013MR, AND DC-8 SRM 51-1-8, 51-3-0, AND 51-1-20D.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 78,864 hrs · 25,535 cycles

L2 LOWER DOOR CORNER, REPAIRS DO NOT CONFORM TO CURRENT SRM, OR ABX JOB CARD NEA 53100104-002. REPAIRED AREA IAW REA D853-44010MR.

Part: PIN — SHEARED (MLG ACTUATOR) · airframe 78,834 hrs · 25,508 cycles

PLACED LANDING GEAR LEVER DOWN, HAD LOUD BANG WITH GREENLIGHT ON NOSE GEAR. FOUND RIGHT MAIN LANDING GEAR ACTUATOR LOWER PIVOT PIN SHEARED. REPLACED THE RETRACT PIN AND ACTUATOR. REWORKED THE RIGHT MAIN LANDING GEAR RETRACT PIN BOSS HOLE. OVERSIZED TO REMOVE CORROSION IAW NEA 32130001-003. WORK COMPLETED IAW D832-44721-MR. BOEING COMMERCIAL AIRCRAFT GROUP CONTACTED BY ENGINEERING FOR EVALUATION.

Part: ACTUATOR — BROKEN (LT MLG) · airframe 78,705 hrs · 25,429 cycles

RED GEAR UNSAFE LIGHT ILLUMINATED IN CRUISE FLIGHT. LANDING GEAR AND DOOR LATCHING SYSTEM ILLUMINATED IN LEFT MAIN GEAR POSITION. ALTERNATE METHOD USED TO EXTINGUISH THE GEAR UNSAFE INDICATION. FOUND THE LEFT MAIN LANDING GEAR ACTUATOR ATTACHING PIN BROKEN. REPLACED THE LEFT MAIN LANDING GEAR ACTUATING CYLINDER AND PIN IAW DC-8 MM 32-32-02-2. OPS CHECKED AND LEAK CHECKED GOOD.

Part: HANDLE — UNSECURE (CARGO DOOR) · airframe 78,390 hrs · 25,248 cycles

THE CARGO DOOR HAND CRANK TOOL DID NOT STOW PROPERLY TO HOLDING CLIPS PREVENTING CREW EGRESS SAFETY OF FLIGHT. INSTALLED VELCRO TO HOLD CARGO DOOR HAND CRANK.

Part: GROUND WIRE — DAMAGED (CABIN) · airframe 78,062 hrs · 25,070 cycles

EMERGENCY EXIT LIGHTS WOULD NOT DISARM. REPAIRED GROUND WIRE (L622C22N) AS REQUIRED. WIRE SHORTED TO 115 AC SIDE OF TERMINAL OF LIGHT ASSEMBLY CAUSING OVERHEATED WIRE. OPS CHECKED GOOD IAW DC-8 MM 33-50-01.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

AFT LOWER CARGO Z-FITTING CRACKED AT STATION 1180 FROM LONGERON 35 RIGHT TO LONGERON 34 RIGHT. REPLACED Z-FITTING AND REPAIRED AREA IAW DC-8 SRM 51-1-20D, 53-2-0, 51-1-8, AND 51-1-24.

Part: SKIN — CRACKED (LT WING) · airframe 78,059 hrs · 25,067 cycles

LEFT WING UPPER WING PLATING CRACKED AT XCW 69.5 AT TRAILING EDGE.

Part: DOOR FRAME — GOUGED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

STATION 170, BETWEEN LONGERON 17 LEFT AND 18 LEFT, ON MAIN CARGO DOOR FRAME WAS GOUGED. BLENDED OUT GOUGE AND INSTALLED NEW DOUBLER IAW REA D852-40805-MR, AND DC8 SRM 51-1-8, 51-1-15, AND 51-1-20D.

Part: BOLT — SHEARED (NR 2 ENGINE) · airframe 78,059 hrs · 25,067 cycles

NR 2 ENGINE AFT OUTBOARD ARM BOLT SUPPORT ASSEMBLY OUTBOARD END SHEARED OFF.

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

FRAME CRACKED COMPLETELY THROUGH AT FUSELAGE STA 1620 LONGERON 24L.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

LONGERON CRACKED AT CARGO DOOR ACTUATOR U-CHANNEL.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

LONGERON 4L CRACKED AT CARGO DOOR ACTUATOR U-CHANNEL STA 134.

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

AFT ACCESSORY COMPARTMENT FRAME CORRODED AT FS 1620, AT LONGERON 24 LEFT. REMOVED AND REPLACED FRAME, AND REPAIRED AREA IAW DC-8 SRM 51-1-20D, 51-1-21, 51-1-8, AND ABX DWG 5640240.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

LONGERON 6L WAS CRACKED AT THE U-CHANNEL, STA 230.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

AFT PIT FLOORBEAM FRAME AT STA 1000 HAD AN ELONGATED HOLE.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

AFT LOWER CARGO Z-FITTING CRACKED AT STATION 1200 - LONGERON 34 RIGHT AND LONGERON 33 RIGHT. REPLACED Z-FITTING AND REPAIRED AREA IAW DC-8 SRM 51-1-20D, 53-2-0, AND 51-1-8.

Part: CASE — CRACKED (NR 4 ENGINE) · airframe 78,059 hrs · 25,067 cycles

NR 4 ENGINE INLET GUIDE VANE CASE HAD NUMEROUS CRACKS AT WELDS. WELDED CRACKS ON INLET CASE IAW P&W OVERHAUL MANUAL 72-21-1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

Z-FITTING CRACKED AT STA 1200 LONGERON 33R-34R.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

Z-FITTING CRACKED IN AFT LOWER CARGO BAY AT FS 1680 FROM L34R TO L35R.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

AFT LOWER CARGO Z-FITTING CRACKED AT STATION 1680 BETWEEN LONGERON 34 RIGHT - LONGERON 33 RIGHT. REPLACED Z-FITTING AND REPAIRED AREA IAW DC-8 SRM 51-1-20D, 53-20, 53-2-0, AND 51-1-8.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

CORROSION ON THE UPPER SURFACE OF THE PRESSURE WEB AND ON FINGER DOUBLER. ALSO RIVET HEADS WERE SHEARED OFF BETWEEN FS 920-980. REPAIRED AREA AND REPLACED THE DOUBLER IAW DC-8 SRM 51-1-8, 53-2-0, AND REA D853-40413-MR, AND DAC DRAWING NR 5645332.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

BATH TUB FITTING CRACKED IN FORWARD CARGO PIT AT FS 300 L27 - L28.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

RIGHT TUNNEL STANCHION CORRODED AT FUSELAGE STATION 360, FORWARD CARGO BAY RIGHT SIDE. MAINTENANCE INSPECTED AND REPAIRED THE AREA IAW DC-8 SRM 51-1-8, 53-2-0.

Part: STANCHION — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

THE FWD CARGO RT TUNNEL STANCHION WAS CORRODED ON THE LOWER RIGHT SIDE AT STA 360. MAINTENANCE INSPECTED AND REPLACED THE STANCHION IAW DAC DRAWING 3706753 AND DC-8 SRM.

Part: DOUBLER — BULGED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

BULGING FINGER DOUBLER AND RIVET HEADS WERE SHEARED ON THE UPPER SURFACE OF THE PRESSURE WEB BETWEEN FUSELAGE STATION 880 AND BUTT LINE 00. REPAIRED AREA AND INSTALLED NEW FINGER DOUBLER IAW DC-8 SRM 51-1-21, 51-1-8, 53-2-0, 51-9-0, 51-1-20D, 51-1-11, AND DRAWING NR 5645332, AND REA D853-40767-MR.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

CORROSION AND SEVERAL RIVET HEADS SHEARED OFF BETWEEN FS 900-940, ON UPPER SURFACE OF PRESSURE WEB AT BUTT LINE 00. REPAIRED AREA AND REPLACED DOUBLER AND GUSSET IAW DC-8 SRM 51-1-20, 51-1-11, 51-3-0, 51-1-21, 51-1-8, 53-20, AND DAC DRAWING NR 5645332, AND REA D853-40767-MR.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

LEFT FRAME FITTING AT FS 700 BELOW LONGERON L21 WAS CRACKED.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

INTERCOSTAL CRACKED AT FS 975 AT LONGERON 28R.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

RIGHT MAIN LANDING GEAR WHEEL WELL AT FS 975, LONGERON 28 RIGHT INTERCOSTAL WAS CRACKED AT FORWARD END. FABRICATED INTERCOSTAL IAW DC-8 DWG 5646444. ALODINED IAW DC-8 SRM 51-1-8. PRIMED IAW DC-8 SRM 51-1-8. INSTALLED IAW DC-8 SRM 51-1-20D.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

INTERCOSTAL AT LONGERON 25R FS 960 IN THE RIGHT MAIN LANDING GEAR WHEEL WELL IS CRACKED.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

THE RIGHT MAIN LANDING GEAR WHEEL WELL FORWARD OUTBOARD LOWER BULKHEAD PANEL WAS CRACKED.

Part: FITTING — CRACKED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

RIGHT MAIN LANDING GEAR WHEEL WELL TRAPEZOID FITTING AT STA 860 WAS CRACKED.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

KEEL BEAM TO WEB ATTACHMENT ANGLE IN THE RIGHT MAIN LANDING GEAR WHEEL WELL WAS CORRODED. MAINTENANCE INSPECTED AND REPAIRED THE AREA IAW DC-8 SRM 51-1-8 AND 51-2-0.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 78,059 hrs · 25,067 cycles

RIGHT MAIN LANDING GEAR WHEEL WELL AT FS 880 KEEL BEAM TO WEB ATTACH ANGLE WAS CORRODED. REMOVED SURFACE CORROSION IAW DC-8 SRM 51-1-8. ALODINED AND PRIMED IAW DC-8 SRM 51-1-8. FOUND BLEND OUT TO BE WITHIN LIMITS IAW DC-8 SRM 53-2-0.

Part: FITTING — CRACKED (RT WING) · airframe 78,059 hrs · 25,067 cycles

RIGHT WING JACK POINT CRACKED AT XRS 139.

Part: DOOR — MISSING (LEFT MLG) · airframe 77,767 hrs · 24,889 cycles

DURING POSTFLIGHT INSPECTION, MAINTENANCE NOTED THE LEFT OUTBD MAIN LANDING GEAR DOOR WAS MISSING FROM THE AIRCRAFT. THE STRUT HOLDING ON THE LEFT OUTBD UPPER GEAR DOOR WAS CRACKED. THE DOOR AND ASSOCIATED BRAKETS WERE REPLACED IAW DC-8 MM 32-12-01 AND 32-12-02 FLIGHT CHECKED GOOD.

Part: PANEL — CONTAMINATED (COCKPIT HEATER) · airframe 77,546 hrs · 24,768 cycles

DRINK WAS SPILLED ON COCKPIT FLOOR. A BURNING SMELL WAS DETECTED SHORTLY THEREAFTER AND A SPARK BY THE FLIGHT ENGINEER''S PANEL. FOLLOWED EMERGENCY CHECKLIST FOR ELECTICAL FIRE/SMOKE OF VARIOUS ORIGIN. CLEANED SPILLED DRINK FROM AREA AROUND FLIGHT ENGINEER''S FLOOR HEATER PANELS. RESET FLOOR HEATER CIRCUIT BREAKER. PANELS HEATED UP. NO DEFECTS NOTED PER DC8 MM.

Part: CONNECTOR — LOOSE (NLG WW) · airframe 77,419 hrs · 24,686 cycles

NOSE GEAR GREEN LIGHT (DOWN LIGHT) WOULD NOT ILLUMINATE WITH GEAR HANDLE DOWN. MISSED APPROACH. ACCOMPLISHED ABNORMAL PROCEDURES, LANDING WAS UNEVENTFUL. REPLACED CONNECTORPI-215 IAW DC8 MM 32-61-01. OPS CHECKED GOOD.

Part: CONNECTOR — LOOSE (MLG) · airframe 77,404 hrs · 24,678 cycles

WHEN LANDING GEAR WAS EXTENDED FOR LANDING, THE LANDING GEAR GREEN LIGHT FOR THE NOSE GEAR DID NOT COME ON. MAINTENANCE FOUND CANNON PLUG HAD COME OFF NOSE GEAR DOWNLOCK SWITCH. CLEANED AND RESECURED PLUG, CHECKED GOOD.

Part: CONNECTOR — CONTAMINATED (NR 1 ENGINE)

WHEN THROTTLE WAS RETARDED FOR DESCENT, NR 1 LOW OIL PRESSURE LIGHT CAME ON. THROTTLE WAS PULLED BACK TO IDLE, LOW OIL PRESSURE LIGHT STAYED ON. OIL PRESSURE WAS 41 PSI, TEMP 75 DEGREES AND QUANTITY WAS 4.2 GALLONS. SHUT ENGINE DOWN IAW ABNORMAL PROCEDURES. OIL PRESSURE REMAINED ABOVE 10 PSI. INSPECTED NR 1 ENGINE OIL FILTER, NO CONTAMINATION FOUND. CLEANED CANNON PLUG AT OIL PRESSURE SWITCH. RAN ENGINE AT SEVERAL POWER SETTINGS. NO FURTHER DISCREPANCIES NOTED.

Part: BULB — FAILED (COCKPIT)

DURING CRUISE, NOTICED ODOR (BURNING SMELL) COMING FROM AREA OF FIRST OFFICER'S GLARESHIELD FLOURESCENT LIGHT. REPLACED LIGHT BULBS AND REMOVED GLUE FROM LIGHT ASSY AREA. OPS CHECKED GOOD.

Part: SWITCH — DEFECTIVE (NR 1 ENGINE)

DURING DESCENT INTO ONT, WITH POWER REDUCED TO IDLE, NR 1 ENG LOW OIL PRESS LIGHT ILLUMINATED. OIL PRESS IND 42 PSI. SHUT NR 1 ENGINE DOWN, OIL PRESS WAS 7 PSI DURING DESCENT AND APPROACH FOR 8 MINUTES. INSPECTED MAIN OIL FILTER, NO CONTAMINATION FOUND. CHECKED CONNECTORS AND WIRING, CLEANED CONTACTS ON OIL PRESSURE WARNING SWITCH AND OIL PRESSURE WARNING SWITCH, NO DEFECTS NOTED. NON SUBSEQUENT FLIGHT DURING TAXI OUT, NR 1 LOW OIL PRESSURE LIGHT ILLUMINATED, OIL PRESS INDICATED 42 PSI AT IDLE. VERIFIED OIL PRESSURE SWITCH DEFECTIVE. REPLACED SWITCH.

Part: INDICATOR — DEFECTIVE (NR 3 ENGINE)

NR 3 ENGINE OIL PRESSURE FLUCTUATED BETWEEN 36 AND 45 PSI. SHUT DOWN NR 3 IAW DC8 ENGINE SECURING CHECKLIST. REPLACED NR 3 ENGINE OIL PRESSURE INDICATOR IAW DC8 MM 79-32-0, OPS CHECKED NORMAL.

Part: SPOILER — DELAMINATED (LT WING)

SPOILER LOWER SURFACE HAS 40 PERCENT DELAMINATION. REPLACED ALL HONEYCOMB CORE, DOUBLERS AND SKIN.

Part: SKIN — CORRODED (BS 610-710)

FOUND CORROSION ON LWR FUSELAGE SKIN FS 610 TO FS 710. REPLACED SKIN IAW ABX REA D853-19477MR.

Part: ANGLE — CORRODED (BS 857)

CANTED WING BOX SHEAR WEB L-ANGLE CORRODED AT STA 857 FROM C/L TO RBL 15. REPAIRED IAW ABX D853-19085MR.

Part: KEEL BEAM — CORRODED (BS 798)

STA 798 KEEL BEAM HAS CORROSION UNDER CANTED PANEL 745C. REMOVED CORROSION AND INSTALLED DOUBLERS IAW ABX REA D853-19066MR.

Part: ANGLE — CORRODED (VERT STAB)

VERTICAL STABILIZER, TO FUSELAGE ATTACH ANGLE CRACKED AND GOUGED ON RT AFT SIDE AT REAR SPAR. REPAIRED IAW DC8 SRM 53-2-5, 51-1-8 AND ABX REA D853-19535MR.

Part: FRAME — CORRODED (BS 320)

FRAME AT FS 320 LT IS CRACKED AND BROKEN AT BOTTOM. REPAIRED IAW ABX D853-19887MR.

Part: FRAME — CORRODED (BS 280)

CARGO DOOR JAMB FRAME AT FS 280 AND LONGRON 32R CORRODED. REPAIRED IAW ABX REA 853-1913MR.

Part: WEB — CORRODED (BS 1766)

FS 1766 VERTICAL WEB CORRODED. REPAIRED IAW ABX D853-19061MR.

Part: LONGERON — CORRODED (BS 1680)

STA 1680 LONGERON 21 TO 25 LT CORRODED. REPAIRED IAW DC8 SRM 51-1-8, 53-2-0, 51-1-21 AND ABX REA D853-18569.

Part: LONGERON — CORRODED (BS 1380)

STA 1380, LONGERON 21L (CUSP) CORRODED ON BOTTOM SIDE. REPAIRED IAW ABX REA D853-19054MR.

Part: FRAME — CORRODED (FUSELAGE)

CORROSION FOUND ON THE FWD UPPER WEB OF -5 ANGLE AND ON THE LOWER FLANGE OF -3 FRAME AT L35R AND L35L. REPAIRED IAW ABX REA D853-20466, DAC DWG 5750885 AND SRM 51-1-20D.

Part: SPAR — CRACKED (WS 428)

FOUND CRACKS INSIDE UPPER/LOWER FLAP SUPPORT ATTACH HOLES IN WING REAR SPAR AND BULKHEAD INSTALLATION STRUCTURE AT XRS=428. REPAIRED IAW ABX REA D857-20371MR.

Part: LONGERON — CORRODED (BS 695)

CORROSION FOUND ON INNER SURFACE OF LONGERON 34R AT STA 695, BELOW NUT PLATE RESULTED IN BLENDOUT EXCEEDING SRM LIMITS. REPAIRED IAW ABX REA D853-20438MR.

Part: STINGER — DELAMINATED (TR UNIT)

DURING INSPECTION, FOUND THRUST REVERSER STINGER ASSY HAD SEVERE DELAMINATION AND WIDE SPREAD CORROSION. REPAIRED UNIT COMPLETE.

Part: STINGER — DELAMINATED (LOWER TR UNIT)

DURING INSPECTION, FOUND SEVERE DELAMINATION AND WIDESPREAD CORROSION ON LOWER THRUST REVERSER STINGER. REPAIRED UNIT COMPLETE.

Part: TR TRACK — WORN (NR 4 PYLON)

NR 4 PYLON THRUST REVERSER UPPER CENTER TRACK WORN AT AFT FLANGES. WELDED TRACK IAW ABX DWG C89R01, COUNTER BORED TRACK IAW DWG 9753006 AND INSTALLED TRACK IAW DC8 SRM 51-3-0.

Part: FRAME — ELONGATED HOLES (BS 1310)

STA 1310 FRAME HAS ELONGATED HOLES BETWEEN LONGERON 21L AND 20L. REPAIRED IAW ABX REA 0853-20461MR.

Part: LONGERON — CORRODED (BS 1380)

STA 1380 LONGERON 21L (CUSP) CORRODED ON BOTTOM SIDE. REPAIRED IAW ABX REA D853-19054 MR.

Part: SUB FLOOR — CORRODED (BS 52)

CORROSION ON SUB FLOOR STA.52, 24 INCHES FROM LT CUSP UNDER CAPTAIN'S SEAT TRACK. INSTALLED DOUBLER REPAIR IAW ABX REA D853-20446MR AND SRM 51-1-20.

Part: SKIN — CORRODED (BS 70-190)

BELLY SKIN CORRODED. REPLACED BELLY SKIN IAW DAC DWG 5779925 AND DC8 SRM 51-1-8.

Part: PANEL — CRACKED (LT WING)

FOUND SEVERAL CRACKS AT ATTACH HOLES ON LEFT WING PANEL 505F. INSTALLED REPAIR DOUBLER IAW ABX REA 0857-20439MR.

Part: WEB — CRACKED (BS 931)

RT AFT LOWER WEB AT STA 931 HAS CRACKED DOUBLER AND VERTICAL STIFFENER IS CRACKED. FABRICATED DOUBLER WEB REPAIR IAW 51-9-0 AND DAC DWG 564 3402, AND DC8 SRM 51-1-20D AND 51-1-21.

Part: SPAR CAP — DELAMINATED (WS 20- 40)

LEFT LEADING EDGE AUX TANK UPPER SPAR CAP DELAMINATED AND CORRODED XFS 20 AND XFS 40. INSTALLED NEW L/E UPPER SPAR CAP IAW DC-I SRM 51-1-21 AND 51-1-20D.

Part: PANEL — CRACKED (FS 1580)

FOUND DENT AND CRACK ON FUSELAGE PANEL AT FS 1580 AND L 21L AND 22L. REPAIRED IAW DC-8 SRM 51-1-20D, 51-1-21D AND 51-1-12.

Part: FRAME — CORRODED (BS 260)

FS 260, LONGERON NR 29 LT, NR 33 LT FWD FACE OF FRAME CORRODED. REPAIRED IAW DC-8 SRM 51-1-8, 53-2-0, 51-1-20D AND ABX REA D853-1572-MR.

Part: LONGERON — CORRODED (BS 200 240)

FS 300 - 240 LONGERON 31L, LONGERON AND SPLICE CORRODED. REPAIRED IAW ABX REA D853-19067-MR AND DC-8 SRM 51-3-2.

Part: FRAME — CORROSION (FS 340)

FOUND CORROSION AND GOUGE DAMAGE ON LOWER FRAME FLANGE OF CARGO DOOR JAMB FRAME AT FS 340, LONGERON 35R. REPAIRED IAW ABX REA D853-19132-MR.

Part: ANGLE — CRACKED (WS 69)

RT WING L/E STA XWO RIB ATTACH ANGLE TO UPPER FRONT SPAR CRACKED. REPAIRED IAW DC-8 SRM 51-3-0, 51-1-8 AND 51-1-1.

Part: LONGERON — CRACKED (BS 259)

LONGERON 35R IS CRACKED AT STA 259. INSTALLED NEW LONGERON SECTION IAW DC-8 SRM 51-3-2, 51-1-20D AND 51-1-8.

Part: FRAME — CORRODED (BS 1300)

FOUND CORROSION DAMAGE ON LOWER FRAME FLANGE ON FS 1300 FRAME AT LONGERON 2R. REPAIRED IAW ABX REA D853-18441-MR.

Part: DOUBLER — CRACKED (HORIZ STAB)

RT HORIZONTAL STABILIZER INNER BOX LOWER FINGER DOUBLER IS CRACKED AT AFT SPAR XE77. REPAIRED IAW ABX REA D855-18557.

Part: SKIN — CORRODED (LT ELEVATOR)

DURING C-CHECK, FOUND LEFT ELEVATOR TO HAVE CORRODED AND CRACKED SKIN. REPAIRED AND REPLACED SKIN IAW DC9 SRM.