N728PL
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
107 reports on file, 1995-02-05 – 2003-12-24.
Part: DOWNLOCK SWITCH — BROKEN (MLG) · airframe 85,189 hrs · 24,142 cycles
WHEN GEAR WAS EXTENED THE LT GEAR LIGHT DID NOT ILLUMINATE. AFTER CYCLING GEAR ALL THREE GEAR LIGHTS WERE NORMAL. MAINTENANCE REMOVED AND REPLACED LT MAIN LANDING GEAR DOWN LOCK INDICATION SWITCH. OPERATIONAL CHECK GOOD. AIRCRAFT WAS RETURNED TO SERVICE.
Part: BEARING — LACK OF LUBE (OUTFLOW VALVE) · airframe 84,791 hrs · 24,055 cycles
DURING CLIMB FROM FJDG CREW LOST CABIN PRESSURIZATION. CREW RETURNED TO FJDG AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED OUTFLOW VALVE. THEY LUBED MECHANICAL ARMS AND BEARINGS. OPERATIONAL CHECK GOOD BOTH IN AUTO AND MANUAL PER ALL APPLICABLE MANUALS. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: UPLOCK SENSOR — CONTAMINATED (MLG) · airframe 84,665 hrs · 24,030 cycles
ON APPROACH, WITH ALL 3 MLG'S DOWN AND LOCKED, BOTH (DOOR NOT LATCHED, GEAR NOT LATCHED) LIGHTS WERE ILLUMIN, ALSO AUDIBLE WARNING HORN. GEAR WAS RECYCLED TWICE, THIS CORRECTED PROBLEM. MAINT INSPECTED LANDING GEAR, GEAR DOOR WARNING SYS. NO DEFECTS WERE NOTED. MAINT THEN PERFORMED TEST OF LANDING GEAR DOOR POSITIONS AND WARING SYS IAW ALL APPLICABLE MANUALS. THEY CLEANED ELECTRICAL CONNECTORS AT NOSE AND MAIN GEAR UPLIMIT SWITCHES, LUBED NOSE, MAIN GEAR UPLATCH MECHANISMS. UNABLE TO DUPLICATE PROBLEM ON GROUND. REVIEW OF LOG NOTED A/C HAD BEEN WASHED AT PREVIOUS STATION. SUSPECT MOISTURE RELATED PROBLEM. ALL SWITCHES INSPECTED, ANY MOISTURE REMOVED. SYS OPS CHECK NORMAL ON GROUND. A/C WAS RETURNED TO SERVICE.
Part: VALVE — MALFUNCTIONED (OIL PRESSURE) · airframe 24,628 hrs · 24,005 cycles
DURING CLIMB NR 4 ENG QTY DROPPED & OIL PRESS ROSE TO 60 PSI, TEMP INCREASED. POWER WAS REDUCED PARAMETERS REDUCED OIL PRESS, OIL TEMP REDUCED 20 DEGREES & OIL QTY INCREASED. OIL PRESS LIGHT NEVER ILLUM & OIL PRESS NEVER DROPPED BELOW 40 PSI. MX REMOVED & INSPECTED NR 4 ENG OIL FILTER. OIL FILTER REPLACED. MX INSPECTED ENG, NO LEAKS. ENG RESERVICED & RUN AT IDLE, NO LEAKS. ENG RUN AT PART PWR FOR 5 MINS, TAKEOFF PWR FOR 5 MINS & CLIMB PWR FOR 5 MINS. QTY CHECK OK, OIL PRESS 57 PSI, INSPECTED OIL PRESS RELIEF VALVE, NO DEFECTS. REINSTALLED VALVE. MX ADJUSTED NR 4 ENG OIL PRESS RELIEF VALVE. IDLE PRESS 39 PSI T/O POWER 52 PSI, SYS LEAK CHECK GOOD. OIL QTY INDICATING SYS OP CHECK OK.
Part: OUTFLOW VALVE — CONTAMINATED (CABIN PRESSURE) · airframe 83,802 hrs · 23,849 cycles
DURING CRUISE AT FLIGHT LEVEL 28K CABIN ALTITUDE BEGAN TO CLIMB. CREW ELECTED TO DEPLOY PASSENGER O2 MASKS. FLIGHT CONTINUED TO WSAP AND MADE AN UNEVENTFUL LANDING. UPON INSPECTION MAINTENANCE CLEANED OUTFLOW VALVE, INSPECTED DUCTING AND OPERATIONALLY CHECKED THE AIRCRAFT PRESSURIZATION SYSTEM. ALL CHECKS INDICATED NORMAL OPERATION. ALL WORK WAS COMPLETED PER APPLICABLE MANUALS AND AIRCRAFT WAS RETURNED TO SERVICE.
Part: LANDING GEAR — FALSE INDICATION (MAIN) · airframe 83,315 hrs · 23,751 cycles
DURING FLIGHT FROM KWAK TO RJTY LANDING GEAR WAS PUT IN DOWN POSITION. THERE WAS NO LEFT GEAR INDICATION. THE GEAR WAS RECYCLED AND IT INDICATED GEAR DOWN. MAINTENANCE JACKED AIRCRAFT AND SWUNG GEAR A TOTAL OF FIVE TIMES. OPERATIONAL CHECK GOOD IN ACCORDANCE WITH DOUGLAS AIRCRAFT MAINTENANCE MANUAL. AIRCRAFT RETURNED TO SERVICE.
Part: O-RING — LEAKING (HYD PUMP) · airframe 83,015 hrs · 23,682 cycles
DURING CRUISE CREW NOTED HYD QTY DROPPING ABNORMALLY. CREW COMPLETED ABNORMAL CHECKLIST AND PROCEEDED TOWARDS QPG. WHILE ON FINAL APPROACH, AFTER ADVISING QPG ATC OF ABNORMAL CHECKLIST COMPLETION. QPG ATC DENIED LANDING CLEARANCE. CREW ELECTED TO PROCEED TO ALTERNATE AIRPORT AND MADE AN UNEVENTFUL LANDING. INSPECTION REVEALED NO INDICATION OF ANY HYD LEAK. SYSTEM OPERATIONALLY CHECKED NORMAL. JUST PRIOR TO DEPARTURE MAINTENANCE NOTED STATIC HYD LEAK AT NR 2 ENGINE DRIVEN HYD PUMP OUTPUT AREA. REPLACED O-RINGS AND SYSTEM LEAK CHECKED GOOD. ALL WORK COMPLETED PER APPLICABLE MANUALS AND THE AIRCRAFT WAS RETURNED TO SERVICE.
Earlier reports · 1995–2002 · 100 reports
2002
Part: O-RING — LEAKING (HYD SELECT VALVE) · airframe 82,710 hrs · 23,620 cycles
EN ROUTE FROM NKW TO BAH. FLIGHT CREW NOTED MAIN HYDRAULIC SYSTEM FLUID QUANITY DECLINING. CREW FOLLOWED COMPANY PROCEDURES AND CONTINUED WITHOUT INCIDENT TO BAH. MAINTENANCE DISCOVERED O-RING LEAKING AT MAIN HYDRAULIC SYSTEM SELECTOR VALVE. REPLACED O-RING AND SERVICED HYDRAULIC SYSTEM IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL.
Part: STRIKER — LOOSE (MLG UPLOCK) · airframe 82,639 hrs · 23,602 cycles
ENROUTE KWA TO HIK, THE GEAR DOOR NOT LATCH LIGHT ILLUMINATED. THE FLIGHT CREW CYCLED THE GEAR, PERFORMED AN GEAR UPLOCK CHECK AND THE WARNING INDICATION EXTINGUISHED. THE FLIGHT CONTINUED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR INDICATION SYSTEM LOCATING THE MAIN GEAR DOORS STRIKERS LOOSE. MAINTENANCE SECURED THE STRIKERS AND PERFORMED A SUCCESSFUL OPERATIONAL TEST IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: STRUCTURE — CORRODED (HORIZONTAL STAB) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LEFT HORIZONTAL STABILIZER LEADING EDGE STATION XFS 178 TO XFS 285. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND REPAIR DOUBLER IN ACCOURDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND ENGINEERING AUTHORIZATION 28260-5508-2002-99.
Part: SKIN — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE EXTERNAL PLATING BETWEEN FUSELAGE STATION 857 TO 902 BETWEEN LONGERONS 10L TO 21L. REPAIR ACCOMPLISHED CORROSION REMOVAL AND FOUND TO BE WITHIN LIMITATIONS. CORROSION REMOVAL AT FUSELAGE STATION 857, STRINGER 12 FOUND OUT OF LIMITATION. REPAIR ACCOMPLISHE REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION A FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND DRAWING Q38-R03.
Part: WING — CRACKED (LEADING EDGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED ON THE RIGHT WING UPPER LEADING EDGE OUTBOARD OF NUMBER FOUR PYLON. REPAIR ACCOMPLISHED REOMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND EXTERMAL DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE EXTERNAL PLATING AT FUSELAGE STATION 902, LONGERONS 14,17 AND 18 RIGHT. REPAIR ACCOMPLISHED CORROSION REMOVAL AND DETERMINED TO BE WITH LIMITATION IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND BOEINGS FAX TIN-MIA-02-00012H.
Part: DOOR — CORRODED (AFT PASSENGER) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AT FUSELAGE STATION 15OO, AFT PASSENGER DOOR FRAME AT THE LOWER AFT CORNER. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGE AREA, FABRICATION AND INSTALLATION OF A NEW INTERNAL REPAIR ANGLE AND FRAME IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: DOOR — CRACKED (FWD ENTRANCE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, A CRACK WAS DETECTED UNDER A TEMPORARY REPAIR OF THE FORWARD ENTRANCE DOOR CUT OUT FORWARD UPPER CORNER. REPAIR ACCOMPLISHED, REMOVAL OF THE TEMPORARY REPAIR AND DAMAGED AREA, FABRICATION AND INSTALLATIN OF A REPAIR FILLER, EXTERNAL DOUBLER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REAPIR MANUAL.
Part: SKIN — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LEFT HAND SIDE FUSELAGE SKIN BELOW THE AFT PASSENGER DOOR SKIN CUT OUT AT STATION 1480 TO 1510. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED SKIN, FABRICATION AND INSTALLATION OF FILLER REPAIR DOULBER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND BOEINGS FAX TIN-MIA-02-00007H
Part: SKIN — CRACKED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK, A CRACK WAS DETECTED IN THE AFT PASSENGER DOOR FORWARD LOWER SKIN CORNER AT SKIN CUTOUT. REPAIR ACCOMPLISHED, REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER, DOUBLER AND TRIPLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REAPIR MANUAL AND BOEINGS FAX TIN-MIA-02-00005F AND TIN-MIA-02-00014H.
Part: SPAR — CORRODED (LT WING) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON TOP OF THE LEFT WING INTERSPAR SKIN BETWEEN XRS 190 INBOARD TO WING WALK AREA TO INCLUDE THE MAIN SKIN EXTENSION OVER GEAR TRUNNION AREA. REPAIR ACCOMPLISHED CORROSION REMOVAL. FABRICATION AND INSTALLATION OF A REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL, BOEING'S FAX TIN-MIA-02-001, DRAWING 01-08-31-002 AND FAA DER APPROVED DRAWING Q38-R02.
Part: SPAR — CORRODED (WING) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE UPPER WING EXTERNAL PLATING BETWEEN WING STATION XFS 172 AND XFS 255. REPAIR ACCOMPLISHED, CORROSION REMOVAL OF THE DAMAGE ARE, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND FAA DER APPROVED DRAWING Q38-R02.
Part: SKIN — CORRODED (LT WING) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, LIGHT CORROSION WAS DETECTED ON THE TOP OF THE LEFT WING INTERSPAR SKIN BETWEEN STATION XW 408 XRS 590 TO STATION XRS 590. REPAIR ACCOMPLISHED CORROSION REMOVAL OF THE AFFECTED AREA IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL AND BOEINGS FAX TIN-MIA-02-0001. THE CORROSION REMOVAL WAS FOUND TO BE WITHIN LIMITATION.
Part: SKIN — CRACKED (RT WING LE) · airframe 84,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION AND A CRACK WAS DETECTED ON THE RIGHT WING LEADING EDGE AT WING STATION XES710, UPPER CHORD MOUNTS. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND EXTERNAL DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CRACKED (RT WING LE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, A CRACKED WAS DETECTED ON THE RIGHT WING OUTBOARD LEADING EDGE PANEL AT THE INBOARD AREA AT STATION XRS 634. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: STRUCTURE — CORRODED (LEADING EDGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE RT WING OUTBOARD LEADING EDGE AT STATION XFS 705. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER AND INTERNAL FILLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: STRUCTURE — CORRODED (LEADING EDGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED IN THE LEFT WING LEADING EDGE TOP SIDE AT STATION XFS 825. REMOVAL ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: STRUCTURE — CORRODED (LEADING EDGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE LT WING OUTBOARD UPPER LEADING EDGE AT STATION XFS 705. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER AND FILLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CORRODED (LT WING) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED AROUND THE SCREW HEADS ON THE TOP LEFT WING LEADING EDGE XFS 885. REPAIR ACCOMPLISHED, REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CRACKED (LT WING LE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION AND A CRACK WAS DETECTED ON THE LEFT WING OUTBOARD LOWER LEADING EDGE AT STATION XFS 566. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND EXTERNAL DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE AFT LOWER FUSELAGE FORWARD OF ACCESS PANEL NUMBER 60, STATION 1557 TO 1574, LONGERON 35 RT. REPAIR ACCOMPLISHED, REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A INTERNAL FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE FUSELAGE AT STATION 1440 AT LONGERON 22RT. REPAIR ACCOMPLISHED REMOVAL OF THE DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR DOUBLER AND INTERNAL FILLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
Part: SKIN — CORRODED (FUSELAGE) · airframe 81,868 hrs · 23,437 cycles
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS DETECTED ON THE AFT LOWER FUSELAGE STATION 1520 BETWEEN LONGERONS 30LT TO 30RT. REPAIR ACCOMPLISHED, DAMAGED AREA CUT OUT, FABRICATION AND INSTALLATION OF FILLER AND REPAIR DOUBLER IN ACCORDANCE WITH THE DOUGLAS STRUCTURAL REPAIR MANUAL.
2001
Part: FAN — DEFECTIVE (FWD BELLY) · airframe 80,916 hrs · 23,209 cycles
ENROUTE FROM KWA TO HIK, THE FLIGHT CREW SENSED AN ODOR IN THE COCKPIT AND THE AFT PASSENGER COMPARTMENT WHEN THE RIGHT RECIRCULATION FAN WAS OPERATING. THE FLIGHT CREW SECURED THE FAN AND THE ODOR SUBSIDED. THE FLIGHT CONTINUED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE FAN WHICH WAS FOUND DEFECTIVE. MAINTENANCE PLACED THE FAN ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: UPLOCK — LACK OF LUBE (RT MLG) · airframe 80,195 hrs · 23,038 cycles
EN ROUTE FROM HIK TO SUU, THE LANDING GEAR NOT LATCH LIGHT ILLUMINATED DURING THE LANDING GEAR UPLATCH CHECK. THE FLIGHT CREW CYCLED THE LANDING GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO SUU FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECT THE LANDING GEAR WHICH REVEALED THE RIGHT MAIN GEAR UPLATCH MECHANISM LACKING LUBRICATION. MAINTENANCE CLEANED AND LUBRICATION THE UPLATCH MECHANISM, PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: DOOR — MISSING (RT MLG)
AFTER AN UNEVENTFUL LANDING AND DURING POST FLIGHT INSPECTION AT WRI. MAINTENANCE FOUND THE RIGHT MAIN LANDING GEAR LOWER FLYING DOOR MISSING FROM THE GEAR. NO OTHER DAMAGE TO THE AIRCRAFT WAS NOTED.
Part: DOOR — MISSING (RT MLG) · airframe 79,428 hrs · 22,861 cycles
AFTER AN UNEVENTFUL LANDING AND DURING POST FLIGHT INSPECTION AT WRI. MAINTENANCE FOUND THE RIGHT MAIN LANDING GEAR LOWER FLYING DOOR MISSING FROM THE GEAR. NO OTHER DAMAGE TO THE AIRCRAFT WAS NOTED. THE AIRCRAFT WAS FERRIED TO A MAINTENANCE FACILITY FOR REPAIRS. THE MAINTENANCE FACILITY REPLACED THE LOWER FLYING DOOR AND PERFORMED A SUCCESSFUL OPERATIONAL CHECK IN ACCORDANCE WITH THE MAINTENANCE MANUAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
2000
Part: FAN — DEFECTIVE (A/C BAY) · airframe 78,729 hrs · 32,639 cycles
EN ROUTE FROM ASI TO ANU, THE FLIGHT CREW DETECTED SMOKE IN THE COCKPIT ACCOMPANIED BY THE LEFT RECIRCULATION FAN SHUTING DOWN, SMOKE SUBSIDED. THE FLIGHT CONTINUED TO ANU FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECT THE LEFT RECIRCULATION FAN AND FOUND IT TO BE DEFECTIVE. MAINTENANCE PLACED THE FAN ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: FAN — DEFECTIVE (A/C BAY) · airframe 78,285 hrs · 22,550 cycles
EN ROUTE FROM FJR TO NKW, THE FLIGHT CREW NOTICED SMOKE INTO THE COCKPIT WHEN THE LEFT RECIRCULATION FAN WAS OPERATING. THE FLIGHT CREW SECURED THE FAN AND THE SMOKE SUBSIDED. THE FLIGHT CONTINUED TO NKW FOR AN UNEVENFUL LANDING. MAINTENANCE INSPECTED THE FAN, WHICH WAS FOUND DEFECTIVE. MAINTENANCE PLACED THE FAN ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
1999
Part: FAN — FAILED (A/C BAY)
EN ROUTE FROM QPG TO NKW, AN ELECTRICAL ODOR WAS SENSED IN THE COCKPIT WHEN THE RIGHT RECIRCULATING FAN WAS TURNED ON. THE FLIGHT CREW SECURED THE FAN AND THE ODOR SUBSIDED AND THE FLIGHT CONTINUED TO NKW. MAINTENANCE INSPECTED THE FAN AND WAS FOUND DEFECTIVE AND WAS PLACED ON DEFERRAL. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: TURBINE — FAILED (LT ENGINE)
EN ROUTE FROM PKWA TO PHIK DURING CLIMB, A LOUD NOISE WAS HEARD FROM THE NUMBER TWO ENGINE, ACCOMPANIED BY INCREASING ENGINE GAS TEMPERATURE AND A DECLINE IN OIL PRESSURE. THE FLIGHT CREW SECURED THE ENGINE FOLLOWING COMPANY PROCEDURES AND CONTINUED TO PHIK FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE ENGINE WITH TURBINE BLADE DISCREPANCIES NOTED IN THE EXHAUST AREA. THE ENGINE WILL BE REPLACED PRIOR TO THE AIRCRAFT RETURNING TO SERVICE.
1998
Part: TIRES — WORN (NLG)
AFTER TAKEOFF, WHEN THE LANDING GEAR WAS RETRACTED, THE FLIGHT CREW HEARD AND FELT A VIBRATION THROUGH THE COCKPIT FLOOR. THE AIRCRAFT RETURNED TO RMS FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE NOSE TIRES OUT OF ROUND. MAINTENANCE PERFORMED A SUCCESSFUL NOSE GEAR SWING IN ACCORDANCE WITH THE MAINTENANCE MANUAL.
Part: RETRACT MECH — LACK OF LUBE (NLG DOOR)
AFTER TAKEOFF, WHEN THE LANDING GEAR WAS RETRACTED, THE FLIGHT CREW NOTICED A NOSE GEAR DOOR HAD FALLEN OPEN CAUSING A LOUD NOISE AND SLIGHT VIBRATION FROM THE NOSE WHEEL WELL AREA. THE CREW CYCLED THE GEAR, THE VIBRATION CONDITION WAS STILL PRESENT. THE AIRCRAFT RETURNED TO RMS FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE AIRCRAFT WHICH REVEALED THE LEFT FORWARD NOSE GEAR DOOR WAS OPEN. MAINTENANCE LUBRICATED THE FORWARD DOOR TELESCOPING ROD LINKAGE ASSEMBLY AND SECURED THE DOOR.
Part: SWITCH — DEFECTIVE (LT GEAR)
EN ROUTE FROM BWI TO WRI, WHEN THE LANDING GEAR WAS RETRACTED, THE LANDING GEAR UNSAFE LIGHT REMAINED ON. THE CREW CYCLED THE GEAR BUT THE WARNING INDICATION REMAINED THE SAME. THE FLIGHT CONTINUED TO WRI FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR AND INDICATION SYSTEMS LOCATING A DEFECTIVE LEFT MAIN GEAR UPLATCH SWITCH. MAINTENANCE REPLACED THE SWITCH IN ACCORDANCE WITH THE DOUGLAS MAINTENANCE MANUAL AND A SUCCESSFUL OPERATIONAL CHECK RETURNED THE AIRCRAFT TO SERVICE.
Part: BALLAST — FAILED (COCKPIT)
EN ROUTE FROM KWA TO HIK, SMOKE EMANATED FROM THE FIRST OFFICERS RIGHT PEDESTAL CONSOLE. THE CREW EXTINGUISHED THE MAIN INSTRUMENT GLARESHIELD WHITE LIGHTING, THE SMOKE STOPPED. THE FLIGHT CONTINUED TO HIK FOR AN UNEVENTFUL LANDING. MAINTENANCE FOUND THAT THE GLARESHIELD WHITE LIGHTING BALLAST HAD FAILED AND PRODUCED THE SMOKE. MAINTENANCE DEFERRED THE GLARESHIELD LIGHTING IN ACCORDANCE WITH COMPANY MEL PROCEDURES. THE AIRCRAFT WAS RETURNED TO SERVICE.
Part: ACTUATOR — MISRIGGED (LT MLG)
EN ROUTE, THE GEAR UPLATCH CHECK FAILED WITH THE GEAR NOT LATCH WARNING LIGHT ILLUMINATED. THE CREW CYCLED THE GEAR WITH THE INDICATION REMAINING THE SAME. THE FLIGHT CONTINUED TO SUU FOR AN UNEVENTFUL LANDING. MAINTENANCE INSPECTED THE LANDING GEAR AND INDICATION SYSTEMS WITH DISCREPANCIES NOTED. MAINTENANCE PLACED THE UPLATCH CHECK ON DEFERRAL IAW CO MEL PROCEDURES, ACFT VISITED HEAVY MAINTENANCE. HEAVY MAINTENANCE PERFORMED A GEAR SWING WHICH REVEALED THE LT UPLATCH MECHANISM AND LT MAIN GEAR RETRACT CYLINDER MISRIGGED. HEAVY MAINTENANCE CORRECTED THE DISCREPANCIES IAW THE MM AND A SUCCESSFUL GEAR SWING.
Part: FAN — FAILED (E/E COMPT)
ENROUTE, A BURNT ELECTRICAL ODOR WAS SENSED IN THE COCKPIT WITH THE RIGHT RECIRCULATION FAN OPERATING. THE FAN WAS SHUT OFF FOR THE REMAINDER OF THE FLIGHT. MAINTENANCE INSPECTED AND FOUND THE FAN DEFECTIVE. MAINTENANCE DEFERRED THE RIGHT RECIRCULATION FAN.
Part: SWITCH — DEFECTIVE (LT MLG)
ENROUTE, GEAR UPLATCH CHECK FAILED WITH THE GEAR NOT LATCHED WARNING LIGHT ILLUMINATED. THE FLIGHT CREW CYCLED THE GEAR EXTINGUSHING THE WARNING LIGHT. GROUND INSPECTION FOUND THE LEFT MAIN GEAR UPLATCH SWITCH INTERMITTENT AND ELECTRICAL CONNECTOR DAMAGED. MAINTENANCE REPLACED THE SWITCH AND REPAIRED THE CONNECTOR IAW MAINTENANCE MANUAL 32-60-0 AND ACCOMPLISHED A GEAR SWING. THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER DISCREPANCIES NOTED.
Part: SEALING TAPE — MISINSTALLED (CARGO COMPT)
DURING DESCENT INTO HIK, THE NUMBER TWO AND FIVE MAIN CARGO COMPARTMENT SMOKE DETECTOR WARING LIGHTS ILLUMINATED. THE FLIGHT CREW TURNED OFF THE CARGO COMPARTMENT LIGHTING AND THE WARNING LIGHTS EXTINGUISHED. MAINTENANCE INSPECTED THE CARGO COMPARTMENT WITH THE LIGHTING SYSTEM ILLUMINATED. MAINTENANCE FOUND CONOLITE LINER SEALING TAPE PARTIALLY COVERING TWO COMPARTMENT LIGHT FIXTURES SMOLDERING. THE TAPE WAS REMOVED AND A SUCCESSFUL OPERATIONAL CHECK OF THE SMOKE DETECTION SYSTEM WAS PERFORMED IN ACCORDANCE WITH THE MAINTENANCE MANUAL, AND THE AIRCRAFT WAS RETURNED TO SERVICE.
1997
Part: PLATING — CORRODED (BS 1120)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE EXTERNAL PLATING BETWEEN FUSELAGE STATIONS 1120 TO 1160, LONGERON 31 RIGHT. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R34 AND ENGINEERING ORDER 53-DC8-769.
Part: BULKHEAD PANEL — CRACKED (BS 133/148)
DURING ROUTINE D-CHECK INSPECTION, A CRACK WAS FOUND ON THE PRESSURE BULKHEAD PANEL BETWEEN FUSELAGE STATIONS 133 AND 148. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF FILLER, NESTED ANGLE DOUBLERS AND FINGER DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R29, C88-R29, C88-30 AND ENGINEERING ORDER 53-DC8-766.
Part: FRAME — CORRODED (BS 133)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE FRAME AT FUSELAGE STATION 133 LONGERON 21 RIGHT. REPAIR ACCOMPLISHED BY CORROSION REMOVAL, FABRICATION AND INSTALLATION OF TWO NESTED ANGLE REPAIR DOUBLERS IN ACCORDANCE WITH FAA PER APPROVED C88-R31 AND ENGINEERING ORDER 53-DC8-767.
Part: SPAR CAP — CORRODED (WS 361)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE RIGHT WING LOWER LEADING EDGE SPAR CAP TEE AT STATION XFS 361. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND A REPAIR DOUBLERS, AND TRIPLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R23 AND ENGINEERING ORDER 57-DC8-514.
Part: ACCESS PANEL — CORRODED (WS 361)
DURING ROUTINE D CHECK INSPECTION, CORROSION WAS FOUND ON THE RIGHT WING LEADING EDGE ACCESS PANEL LAND AT STATION XFS 361. REPAIR ACCOMPLISHED REMOVAL OF DAMAGE AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND TWO REPAIR DOUBLERS AND THIPLERS IN ACCORDANCE WITH DER APPROVED DRAWING C88-R23 AND ENGINEERING ORDER 57-DC8-514.
Part: PLATING — CRACKED (RT WING)
DURING ROUTINE D-CHECK, A CRACK WAS FOUND ON THE RIGHT WING UPPER LEADING EDGE EXTERNAL PLATING, TWELVE INCHES OUTBOARD OF THE NUMBER THREE PYLON. REPAIR WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R19 AND ENGINEERING ORDER 57-DC8-510.
Part: SKIN — CRACKED (RT WING)
DURING ROUTINE D CHECK INSPECTION, A CRACK WAS FOUND ON THE RIGHT WING UPPER LEADING EDGE PLATING TWELVE INCHES OUTBOARD OF NUMBER THREE PYLON. REPAIR ACCOMPLISHED STOP DRILLING CRACK, FABRICATION AND INSTALLATION AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R19 AND ENGINEERING ORDER 57-DC8-510.
Part: PLATING — CRACKED (RT WING)
DURING ROUTINE D-CHECK INSPECTION, A CRACK WAS FOUND ON THE RIGHT WING UPPER LEADING EDGE EXTERNAL PLATING TWELVE INCHES OUTBOARD OF NUMBER THREE PYLON. REPAIR ACCOMPLISHED BY STOP DRILLING CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R19 AND ENGINEERING ORDER 57-DC8-510.
Part: FRAME — CORRODED (BS 270)
DURING ROUTINE DCHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE FRAME SPLICE AT FUSELAGE STATION 270 BETWEEN LONGERONS 24 AND 25 LEFT. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER, AND NESTED REPAIR ANGLES IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R32 AND ENGINEERING ORDER 53-DC8-768.
Part: LONGERON — CORRODED (BS 866)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON LONGERON ONE AT FUSELAGE STATION 866. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF TWO REPAIR ANGLE DOUBLERS IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R24 AND ENGINEERING ORDER 53-DC8-515.
Part: RIB — CRACKED (WS 255)
DURING ROUTINE D-CHECK INSPECTION, FOUND THE RIGHT WING LEADING EDGE RIB CRACKED AT STATION XFS 255. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND TWO REPAIR ANGLE DOUBLERS IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R20 AND ENGINEERING ORDER 57-DC8-511.
Part: SPAR CAP — CRACKED (RT WING)
DURING ROUTINE D-CHECK INSPECTION, A CRACK WAS FOUND ON THE LOWER SPAR CAP STRAP AT STATION XW 475. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL REPAIR FILLER AND A REPAIR ANGLE IN ACCORDANCE WITH SERVICE REWORK DRAWING SR08570014 AND ENGINEERING ORDER 54-DC8-775
Part: PLATING — CORRODED (LT WING)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT HAND WING UPPER EXTERNAL PLATING BETWEEN STATIONS XRS 693 AND XFS 772.5 BETWEEN STRINGERS 2 AND 6. REPAIR ACCOMPLISHES CORROSION REMOVAL OF AFFECTED AREAS, FABRICATION AND INSTALLATION OF INTERNAL FILLERS AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R17 AND ENGINEERING ORDER 57-DC8-762.
Part: PLATING — CORRODED (BS 181)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE FUSELAGE EXTERNAL PLATING AT FUSELAGE STATION 181 ABOVE LONGERON 31 LEFT. REPAIR ACCOMPLISHED BY REMOVING DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS STRUCTURAL REPAIR MANUAL 53-2-0, DAC FAX FILE NUMBER 350400 AND ENGINEERING ORDER 53-DC8-773.
Part: SPAR WEB — CORRODED (RUDDER)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE RUDDER FRONT SPAR WEB DOUBLERS AT STATION ZR 163. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED DOUBLERS, FABRICATION AND INSTALLATION OF TWO NEW DOUBLERS IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R13 AND ENGINEERING ORDER 27-DC8-758.
Part: BULKHEAD DOUBLER — CORRODED (BS 188)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE PRESSURE BULKHEAD FINGER DOUBLER BETWEEN FUSELAGE STATION 188 AN 208. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER, ONE EXTERNAL REPAIR DOUBLER, AND TWO INTERNAL REPAIR DOUBLERS IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R12 AND ENGINEERING ORDER 53-DC8-757.
Part: DOUBLER — CORRODED (BS 188-208)
DURING ROUTINE D CHECK INSPECTION, CORROSION WAS FOUND ON THE NOSE PRESSURE PANEL FINGER DOUBLER BETWEEN FUSELAGE STATION 188 AND 208. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL FILLER, ONE EXTERNAL REPAIR DOUBLER AND TWO INTERNAL REPAIR DOUBLERS IN ACCORDANCE WITH DER APPROVED DRAWING C88-R12 AND ENGINEERING ORDER 53-DC8-757.
Part: PLATING — CORRODED (LT WING)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT WING EXTERNAL UPPER PLATING AT STATION XRS 22.5. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R14 AND ENGINEERING ORDER 57-DC8-759.
Part: FLOORBEAM — CORRODED (BS 1520)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE FLOORBEAM AT STATION 1520, BUTT LINE 45.O RIGHT. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF A REPAIR FILLER AND REPAIR ANGLE DOUBLERS IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R26 AND ENGINEERING ORDER 53-DC8-518.
Part: PLATING — CRACKED (WS 20)
DURING ROUTINE D-CHECK INSPECTION, A CRACK WAS FOUND ON THE RIGHT WING UPPER EXTERNAL PLATING AT STATION XRS 20 STRINGER 17. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DOUGLAS ROD SKETCH 97-07-31-009, ACTION LETTER 340049/340132 AND ENGINEERING ORDER 57-DC8-772.
Part: SKIN — CRACKED (CARGO DOOR)
DURING ROUTINE D CHECK INSPECTION, FOUND THE MAIN CARGO DOOR LOCK PIN ACTUATOR MOUNT ATTACHMENT SKIN TORN AND SEPARATED. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R07 AND ENGINEERING ORDER 52-DC8-533.
Part: ANGLE — CRACKED (BS971-980)
DURING ROUTINE D CHECK INSPECTION, FOUND T ANGLE TO CENTER KEEL WEB CRACKED BETWEEN FUSELAGE STATION 971 AND 980. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION INTERNAL FILLER AND TWO ANGLE DOUBLERS IN ACCORDANCE WITH APPROVED DER DRAWING C88-R08 AND ENGINEERING ORDER 53-DC8753.
Part: WEB — CRACKED (BS 971)
DURING ROUTINE D-CHECK INSPECTION, FOUND A TEE ANGLE CRACKED ON THE CENTER KEEL BEAM WEB BETWEEN FUSELAGE STATION 971 AND 980. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND TWO ANGLE DOUBLERS IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R08 AND ENGINEERING ORDER 53-DC8-753.
Part: SKIN — GOUGED (RT TE FLAP)
DURING ROUTINE D CHECK INSPECTION, FOUND THE RIGHT HAND OUTBOARD FLAP UPPER PLATING GOUGED AT STATION XF 226. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R05 AND ENGINEERING ORDER 27-DC8-531.
Part: SKIN — GOUGED (LT TE FLAP)
DURING ROUTINE D-CHECK INSPECTION, FOUND THE LEFT HAND OUTBOARD FLAP UPPER PLATING GOUGED AT STATION XF 415. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R04 AND ENGINEERING ORDER 27-DC8-530.
Part: PLATING — GOUGED (RT TE FLAP)
DURING ROUTINE D-CHECK INSPECTION, FOUND THE RIGHT HAND OUTBOARD FLAP UPPER PLATING GOUGED AT STATION XF 226. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R05 AND ENGINEERING ORDER 27-DC8-531.
Part: PLATING — CORRODED (WS 291)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE RIGHT WING LEADING EDGE UPPER PLATING AT STATION XFS 291. REPAIR ACCOMPLISHED BY REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF INTERNAL FILLERS AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA PER APPROVED DRAWING C88-R18 AND ENGINEERING ORDER 57-DC8-509.
Part: SKIN — CRACKED (WS 595)
DURING ROUTINE D CHECK INSPECTION, A CRACK WAS FOUND ON THE LEFT WING LOWER LEADING EDGE PLATING AT STATION XFS 595. REPAIR ACCOMPLISHED STOP DRILLING ENDS OF CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R03 AND ENGINEERING ORDER 57-DC8-529.
Part: PLATING — CRACKED (LT WING)
DURING ROUTINE D-CHECK INSPECTION, A CRACK WAS FOUND ON THE LEFT WING LOWER LEADING EDGE PLATING AT STATION XFS 595. REPAIR ACCOMPLISHED STOP DRILLING ENDS OF CRACK, FABRICATION AND INSTALLATION OF AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R03 AND ENGINEERING ORDER 57-DC8-529.
Part: PLATING — CORRODED (RUDDER)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE RUDDER EXTERNAL PLATING BETWEEN STATIONS ZR145 TO ZR150 RIGHT. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R09 AND ENGINEERING ORDER 27-DC8-754.
Part: SKIN — CORRODED (RUDDER)
DURING ROUTINE D CHECK INSPECTION, CORROSION WAS FOUND ON THE RIGHT RUDDER EXTERNAL PLATING BETWEEN STATIONS ZR145 TO ZR150. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREA, FABRICATION AND INSTALLATION OF AN INTERNAL FILLER AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH DER APPROVED DRAWING C88-R09 AND ENGINEERING ORDER 27-DC8-754.
Part: SKIN — CORRODED (LT HORZ STAB)
DURING ROUTINE D CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT HORIZONTAL STABILIZER LEADING EDGE UPPER PLATING BETWEEN STATIONS XFS114 AND XFS178. REPAIR ACCOMPLISHED REMOVAL OF DAMAGED AREAS, FABRICATION AND INSTALLATION OF INTERNAL FILLERS AND A EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH APPROVED DER DRAWING C88-R22 AND ENGINEERING ORDER 55-DC8-513.
Part: PLATING — CORRODED (LT HORZ STAB)
DURING ROUTINE D-CHECK INSPECTION, CORROSION WAS FOUND ON THE LEFT HORIZONTAL STABILIZER LEADING EDGE UPPER PLATING BETWEEN STATIONS XFS114 AND XFS178. REPAIR ACCOMPLISHED CORROSION REMOVAL, FABRICATION AND INSTALLATION OF INTERNAL FILLERS AND AN EXTERNAL REPAIR DOUBLER IN ACCORDANCE WITH FAA DER APPROVED DRAWING C88-R22 AND ENGINEERING ORDER 55-DC8-513.
Part: FLAP SUPPORT — CRACKED (LT TE FLAP)
DURING ROUTINE B-CHECK INSPECTION, THE FLAP SUPPORT FITTING AT STATION 219 LEFT WAS FOUND TO BE CRACKED. THE FLAP SUPPORT FITTING WAS REPLACED IN ACCORDANCE WITH DOUGLAS MAINTENANCE MANUAL 27-51-12.
1996
Part: FAN — FAILED (AIR COND BAY)
AFTER TAKEOFF, AN ACRID ELECTRICAL SMELL ACCOMPANIED WITH SMOKE WAS DETECTED BY THE FLIGHT CREW. THE RECIRCULATION FANS WERE TURNED OFF AND THE SMOKE AND SMELL DISIPATED. MAINTENANCE INSPECTED BOTH FANS AND FOUND THE RIGHT FAN APPEARED TO BE OVERHEATED AND AT FAULT. THE FAN WAS DEFERRED AND THE AIRCRAFT RETURNED TO SERVICE. (M)
Part: DOOR TRACK — WORN (CARGO COMPT)
DURING ROUTINE C-CHECK INSPECTION, THE AFT LOWER FORWARD CARGO DOOR FORWARD GUIDE TRACK WAS FOUND WORN BEYOND LIMITS. REPAIR OF THE DOOR TRACK WAS ACCOMPLISHED IAW REPAIR SKETCH A40-R05 WHICH IS FAA DER APPROVED. (X)
Part: ANGLE — CRACKED (VERTICAL)
DURING ROUTINE C-CHECK INSPECTION, THE VERTICAL STABILIZER FUSELAGE ATTACH ANGLE AT STATIONS 1626, 1640, AND 1667, WAS FOUND CRACKED. REPAIR OF THE CRACKED ANGLE WAS ACCOMPLISHED IAW DOUGLAS ROD SKETCH 96-04-02-005, WHICH IS FAA DER APPROVED. (X)
Part: SKIN — CORRODED (WS 195)
DURING ROUTINE C-CHECK INSPECTION, LOCALIZED CORROSION WAS FOUND TO THE LEFT LEADING EDGE, STA XFS 195, UPPER ATTACH BOLT HOLES. REPAIR TO THE LEADING EDGE WAS ACCOMPLISHED IAW FAA DER APPROVED SKETCH A40-R04. (X)
Part: COVER PLATE — CRACKED (LEFT WING)
DURING ROUTINE C-CHECK INSPECTION, FUEL PROBE ATTACH PLATES 9, 15, AND 17, OF THE LEFT WING WERE FOUND CRACKED. REPAIR OF THE ATTACH PLATES WAS ACCOMPLISHED IAW FAA DER APPROVED SKETCHES 96108-1, 96108-2, AND 96108-3.
Part: AUX SPAR WEB — CRACKED (RT WING)
DURING ROUTINE C-CHECK AND MLG ATTACH FITTING REPLACEMENT, THE LEFT AUXILIARY SPAR WEB WAS FOUND WITH LOCAL CORROSION AND CRACKS. THE WEB WAS REPLACED WITH A NEW WEB IAW DOUGLAS DRAWING 3641823-1. (X)
Part: FITTING — CRACKED (FS 895 AND 902)
DURING ROUTINE C-CHECK INSPECTION, KEEL BEAM SUPPORT FITTINGS AT FS 895 AND FS 902 WERE FOUND CRACKED. THE FITTINGS WERE REMOVED, FABRICATED, AND INSTALLED IAW AIRCRAFT SRM 53-1-0. (X)
Part: T-FITTING — CRACKED (FS 950)
DURING ROUTINE C-CHECK INSPECTION, THE KEEL BEAM SUPPORT FITTING AT FS 950 WAS FOUND CRACKED. THE FITTING WAS REMOVED, FABRICATED AND INSTALLED IAW AIRCRAFT SRM 53-1-0. (X)
Part: PLANK — CRACKED (NR 1 PYLON)
DURING ROUTINE C-CHECK INSPECTION, THE NR 1 OUTBOARD PYLON REMOVABLE PLANK WAS FOUND CRACKED. THE PLANK WAS REMOVED, REPAIRED, AND REINSTALLED IAW AIRCRAFT SRM 54-2-2 AND SRM 5-1-21. (X)
Part: AUX SPAR WEB — CORRODED (XW 97)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT AUXILIARY SPAR WEB AT APPROXIMATE WS XW 97 WAS FOUND WITH LOCAL CORROSION. THE CORROSION WAS REMOVED, TREATED, AND PROTECTED IAW AIRCRAFT SRM 51-1-8. (X)
Part: RIB — CRACKED (NR 2 PYLON)
DURING ROUTINE C-CHECK INSPECTION, THE NR 2 PYLON STUB WING UPPER CENTER RIB WAS FOUND CRACKED. REPAIR TO THE RIB WAS ACCOMPLISHED BY FABRICATING AND INSTALLING REPAIR DOUBLER AND ANGLE IAW THE AIRCRAFT SRM 57-2-0 AND SRM 51-1-20D. (X)
Part: LONGERON — CRACKED (FS 920)
DURING ROUTINE C-CHECK INSPECTION, THE RIGHT LONGERON 24 WAS FOUND CRACKED BETWEEN FASTENER HOLES AT FS 920. REPAIR OF THE LONGERON WAS ACCOMPLISHED BY STOP DRILLING THE CRACK, FABRICATING AND INSTALLING REPAIR DOUBLER IAW AIRCRAFT SRM 53-2-2 AND SRM 51-1-21. (X)
Part: RIB — CRACKED (NR 2 PYLON)
DURING ROUTINE C-CHECK INSPECTION, THE NR 2 PYLON STUB WING, INBOARD RIB, FORWARD SECTION, WAS FOUND WITH 2 CRACKS. THE RIB ASSEMBLY WAS REMOVED AND REPLACED IAW THE AIRCRAFT SRM 51-2-0. (X)
Part: LONGERON — CRACKED (FS 920)
DURING ROUTINE C-CHECK INSPECTION, LONGERON 24 LEFT WAS FOUND CRACKED BETWEEN FASTENER HOLES AT FS 920. THE CRACK WAS STOP DRILLED. REPAIR WAS ACCOMPLISHED BY FABRICATING AND INSTALLING REPAIR DOUBLER IAW THE AIRCRAFT SRM 53-2-2 AND SRM 51-1-21. (X)
Part: HINGE FLANGE — BENT (LT ELEVATOR)
DURING ROUTINE C-CHECK INSPECTION, THE LEFT ELEVATOR, NR 4 HINGE FLANGE WAS FOUND BENT. THE DAMAGED AREA WAS REMOVED IAW THE AIRCRAFT SERVICE REPAIR MANUAL. (X)
Part: LONGERON — CORRODED (FS 535)
DURING ROUTINE C-CHECK, LONGERON 35 RIGHT WAS FOUND WITH CORROSION, CORROSION REMOVAL WAS BEYOND SRM LIMITS. THE AFFECTED SECTION OF LONGERON WAS REMOVED, FABRICATED, AND INSTALLED IAW AIRCRAFT SRM 51-1-8 AND SRM 53-2-3. (X)
Part: LE SKIN — CORRODED (VERTICAL STAB)
DURING ROUTINE C-CHECK INSPECTION, LOCALIZED CORROSION WAS FOUND ON THE VERTICAL STABILIZER LEADING EDGE. DAMAGE WAS AT STA ZFS 173, RIGHT, ATTACHMENT SCREW HOLE. THE CORROSION WAS REMOVED, REPAIR DOUBLERS FABRICATED AND INSTALLED IAW WITH THE AIRCRAFT SRM 55-2-1. (X)
Part: PLATING — CORRODED (FS 1620)
DURING ROUTINE C-CHECK INSPECTION, LOCALIZED CORROSION OF THE FUSELAGE PLATING, AT FS 1620, LONGERON 5 LEFT, WAS FOUND. THE CORROSION WAS REMOVED, REPAIR DOUBLERS FABRICATED AND INSTALLED IAW THE AIRCRAFT SRM 51-1-8 AND SRM 53-2-1. (X)
Part: PLATING — CORRODED (BS 1500-1530)
DURING ROUTINE C-CHECK INSPECTION, EXTERNAL CORROSION OF THE FUSEAGE SKIN WAS FOUND. DAMAGE LOCATED BETWEEN FS 1500 AND FS 1530 AT LONGERON 1. REPAIR WAS ACCOMPLISHED BY CORROSION REMOVAL, FABRICATION AND INSTALLATION OF REPAIR DOUBLER. REPAIR WAS ACCOMPLISHED IAW FAA DER APPROVED SKETCH A40-R02. (X)
Part: BOLT — BROKEN (RT MLG)
ON TAKEOFF OUT OF PHIK, AFTER LANDING GEAR RETRACTION, BOTH THE MLG DOOR NOT LATCHED LIGHT AND THE GEAR NOT LATCHED LIGHT STAYED ON. AFTER SEVERAL GEAR CYCLES, THE GEAR UPLATCHED. THE AIRCRAFT RETURNED TO PHIK, WHERE MAINTENANCE INSPECTED THE LANDING GEAR AND FOUND THAT THE FORWARD BOLT ON THE RIGHT BOGIE TRIM CYLINDER HAD BROKEN. THE BOLT WAS REPLACED IAW THE DC-8 MM, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (M)
1995
Part: SKIN — CORRODED (WS 410-425)
DURING ROUTINE 'C' CHECK INSPECTION, UPPER LEFT WING SKIN CORROSION WAS FOUND. CORROSION REMOVAL WENT BEYOND LIMITS OF THE DOUGLAS SRM. REPAIR WAS ACCOMPLISHED AFTER REMOVAL OF ALL CORROSION IAW SKETCH SKA95002-2, AND E.O. 57-DC8-126. AFFECTED AREA WAS STR 9 AND STR 10 AT WS XRS 410 TO XRS 425. (X)
Part: SKIN — CORRODED (LT WING)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND OUTBOARD OF THE NR 1 ENGINE, UPPER PLATING OF THE WING AT XS-00. THE AREA CORROSION WAS BLENDED BEYOND SRM LIMITS AND REQUIRED REPAIR. REPAIR WAS ACCOMPLISHED IAW SKETCH SKA 95002-2, WHICH WAS FAA DER APPROVED, AND E.O. 57-DC8-128. REPAIR DOUBLER WAS INSTALLED. (X)
Part: LONGERON — CORRODED (FS 973R)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND ON LONGERON 32 RT FS 973. CORROSION BLEND OUT OF THE LONGERON WENT BEYOND SRM LIMITS. REPAIR OF THE LONGERON WAS ACCOMPLISHED BY INSTALLING REPAIR DOUBLERS IAW SKA93002-3, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-127. (X)
Part: LONGERON — CORRODED (FS 587-592)
DURING ROUTINE C-CHECK INSPECTION, FOUND CORROSION REMOVAL IN A LOCALIZED AREA IN THE RADIUS OF LONGERON 35 RT, STA 587-STA 592 WAS BLENDED BEYOND SRM LIMITS. REPAIR OF THE LONGERON WAS ACCOMPLISHED IAW SKETCH SKA95002-5, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-130. (X)
Part: SKIN — CORRODED (FS 980-1090)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS NOTED BETWEEN LONGERONS 34.5 LT TO 34.5 RT, BETWEEN FS 980 AND FS 1087. CORROSION REMOVAL ON THE INTERNAL SKIN WENT BEYOND SRM LIMITS. REPAIR OF THE ARA WAS ACCOMPLISHED IAW SKETCH SKA 95002-7, AND E.O. 53-DC8-131. REPAIR WAS ACCOMPLISHED BY ADDING AN INTERNAL DOUBLER, AND EXTERNAL SPLICE DOUBLER, REPLACING LONGERON SECTIONS AND ATTACH ANGLES. (X)
Part: FITTING — CRACKED (FS 905)
DURING ROUTINE C-CHECK INSPECTION, FOUND LEFT MLG TORQUE TUBE SUPPORT FITTING CRACKED BEYOND REPAIRABLE LIMITS. THE FITTING WAS REMOVED AND REPLACED IAW DOUGLAS SRM AND SB 53-61. (X)
Part: FRAME — CORRODED (FS 930)
DURING ROUTINE C-CHECK INSPECTION, CORROSION WAS FOUND AT FS 930 WINDOW FRAME LEFT SIDE. THE CORROSION WAS REMOVED AND AN EXTERNAL REPAIR DOUBLER WAS INSTALLED IAW SKETCH SKA95002-8, WHICH WAS FAA DER APPROVED, AND E.O. 53-DC8-132. (X)