N272
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.
46 reports on file, 2000-12-17 – 2006-08-14.
Part: SEAL — BLOWN (HYDRAULIC SYS)
RCH764/14 KGTB/KGTB DURING CLIMB (HYD 3 ELEV OFF) LEVEL 1 ILLUMINATED. HYD 3 WENT TO 3.8GAL. CONFERED WITH MX AND ACCOMPLISHED AIR RETURN TO KGTB. AFTER GEAR DOWN HYD 3 QUANTITY WENT TO 2.1 AND THE (HYD 3 QTY LOW) LEVEL 1 ALERT ILLUMINATED. FOUND HYD SYSTEM SHUTOFF VALVE SEALS BLOWN. REMOVED AND REPLACED VALVE IAW MM 29-12-95. OPS AND LEAK CHECK GOOD AFTER SYSTEM SERVICED AS REQUIRED. AIRCRAFT OK FOR SERVICE.
Part: ENGINE — FLAMED OUT (NR 2)
NR 2 ENG FLAMED OUT APPROX 30 MINS INTO FLIGHT. PRECEDED BY A LEVEL 2 SELECT FADEC ALTN ALERT NR 2 EPR OBSERVED WITH AN AMBER X EGT DECREASING. FUEL OFF INDICATION IN THE FUEL FLOW DISPLAY. FADEC ALT SELECTED AND ENG RESTARTED. ALT TIME OF OCCURRENCE 360 DEG AIRSPEED 83M. FADEC RESET.
Part: CHARGER — FAILED (MASTER BATTERY)
AIR TURNBACK DUE TO BATTERY DISCHARGING LEVEL 1 ALERT, INTERMITTENT BATTERY VOLTAGE 29V WHEN ALERT OFF. REPLACED BATTERY CHARGER AND BOTH AIRCRAFT BATTERIES, PERFORMED TEST ALL CHECK NORMAL PER MD11 AMM.
Part: ADC — MALFUNCTIONED (NR 2)
ON DEPARTURE LOST FLT DIRECTOR PITCH BAR, GOT AMBER AUTO PILOT BOX, AND IAS AND ALT COMPARATOR ON BOTH SIDES. LOST AUTO THROTTLES. ACCOMPLISHED -AIRSPEED LOST, SUSPEND- CHECKLIST. DETERMINED CADC 2 WAS SUSPECT. DIVERTED TO ATLANTA. REMOVED AND REPLACED NR 2 AIR DATA COMPUTER IAW AMM 34-16-01. PUMPED UP AIR DATA SYS DUE TO RVSM COMPONENT. R/R NR 2 AIR DATA COMPUTER IAW AMM 34-16-01. PERFORMED PITOT STATIC CHECK IAW MM 34-11-00 ALL SYSTEM CHECKS NORMAL. PUMPED UP AIR DATA SYS DUE TO RVSM COMPONENT.
Part: PITOT TUBE — OBSTRUCTED (PITOT/STATIC SYS)
ON DEPARTURE, FLIGHT DIRECTOR INOP BOTH SIDES AMBER A/P AND ATS BOXES IAS COMPARATOR BOTH SIDES. FA USING AIRSPEED LOST, SUSPECT ERROR. CHECKLIST DETERMINED. DETERMINED CADC NR 1 WAS AT FAULT. DIVERT TO ATL. FOUND FOD NR 1 PITOT TUBE. ALSO TUBE L/E ERODED. PURGED LINES FROM CADC NR 1 & 2 TO PITOT TUBES PER MM 34-11-0. LINES CLEAN, REPLACED NR 1 PITOT TUBE AND NR 1 CADC PRECAUTION PER 34-16-01. A/C RETURNED TO ATL.
Part: TIRE — FLAT (LANDING GEAR)
UPON TOUCHDOWN SPOILERS DEPLOYED AUTOMATICALLY, ONCE DEPLOYED ABS FAIL ALERT DISPLAYED AND AIRCRAFT WAS SLOWING NORMALLY. WHEN BRAKES WERE APPLIED CAPTAIN AND F/O FELT NO PRESSURE AND AIRCRAFT WAS HOLDING ON THE TAXIWAY JUST AT THE END OF RUNWAY. AIRCRAFT OVERRAN BY APPROX 80FEET, LEFT NOSE TIRE INDICATED FLAT, BRAKE TEMPS WERE NOT VERY HIGH AND RUNWAY WAS WET BUT WITH NO STANDING WATER. ACCOMPLISHED WOA TASK CARD 0250 INSPECTION, NO DAMAGE FOUND. REMOVED AND REPLACED LEFT AND RIGHT NOSE TIRES AND NR 2 MLG TIRE. AS PRECAUTIONARY REMOVED AND REPLACED ASCU AND ABSCU. PERFORMED NOSE GEAR SWING PER MM 32-21-01.
Earlier reports · 2000–2004 · 40 reports
2004
Part: CONTROLLER — MALFUNCTIONED (TE FLAPS)
FRA/KWI REJECTED TAKEOFF AT 40 KTS DUE TO FLAPS TAKEOFF WARNING. RECYCLED FLAPS, OPERATIONS CHECK ALL NORMAL. RESUMED NORMAL PROCEDURES.
Part: FAN — OBSTRUCTED (E/E BAY) · airframe 11,716 hrs · 9,265 cycles
CREW REPORTED THEY FAINTLY DETECTED A BURNING RUBBER AND ELECTRICAL ODOR DURING LANDING. AT THE GATE WITH THE PASSENGERS OFF THE AIRCRAFT THE ODOR BECAME VERY STRONG AND WAS LOCATED NEAR THE FORWARD COAT CLOSET. MAINTENANCE FOUND INSULATION IN THE LT AVIONICS FAN. REMOVED INSULATION FROM FAN IAW EMB 145 AMM 21-21-04. NO ODOR NOTED AT THIS TIME.
2003
Part: CONTROL UNIT — MALFUNCTIONED (MLG) · airframe 7,852 hrs · 6,558 cycles
LANDING GEAR WOULD NOT RETRACT, LG A/G FAIL EICAS MESSAGE. REMOVED AND REPLACED LGEU.
Part: PROXIMITY SENSOR — CRACKED (MLG) · airframe 7,788 hrs · 6,514 cycles
AFTER TAKEOFF GEAR WOULD NOT RETRACT. EICAS MESSAGE LANDING GEAR AIR/GRND FAIL. RAN QRH CHECKLIST, CONTACT DISPATCH AND MTX AND RETURNED TO MCO FOR LANDING. NO EMERGENCY WAS DECLARED, BUT EMERGENCY EQUIPMENT WAS DISPATCHED. FOUND LF AFT (WOW) PROXIMITY SENSOR FACE CRACKED. REMOVED AND REPLACED PROXIMITY SENSOR, PERFORMED GEAR SWING OPS CHECK GOOD.
2002
Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 5,243 hrs · 4,619 cycles
NR 2 THRUST REVERSER DISAGREE MESSAGE ON TAKEOFF ROLL. MEL'D NR 2 THRUST REVERSER.
Part: SKIN — CRACKED (L/E SLAT) · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED LT WING NR 1 SLAT LOWER SKIN CRACKED AT LAST ROW OF RIVETS, OUTBOARD OF MAIN TRACK. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER SRM 57-43-01.
Part: SILL — CORRODED (FUSELAGE) · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON R1 DOOR MOP SEAL AND THRESHOLD SUPPORT. REMOVED CORROSION PER SRM 53-10-01 AND INSTALLED NEW MOP SEAL PER SRM 51-30-02.
Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON STRAP AT BS 857, RBL 18. REPLACED STRAP PER SRM 51-30-5 AND 51-30-2.
Part: SILL — CRACKED (FUSELAGE) · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED R1 DOOR LOWER SILL WEB CRACKED AT FWD DRAIN HOLE. REMOVED DAMAGED WEB, FABRICATED AND INSTALLED REPAIR DOUBLER AND FILLER PER SRM 51-40-02 AND SOPM 20-41-02.
Part: STRUCTURE — CORRODED (RUDDER) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON RUDDER BULLNOSE BY NR 3 HINGE. REPLACED CORRODED AREA OF RUDDER BULLNOSE PER SRM 51-40-02 AND BOEING DRAWING 65-53740.
Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON FLOOR ANGLE INBD OF R1 GUTTER AT BS 336, RBL 54. FABRICATED AND INSTALLED REPLACEMENT SUPPORT ANGLES PER BOEING DRAWING 65C15677 AND SRM 51-30-2.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON TWO SEAT TRACKS BETWEEN BS 947 AND BS 967, RBL 11.50. FABRICATED AND INSTALLED REPLACEMENT SEAT TRACK PER SRM 51-30-02.
Part: SEAT TRACK — CORRODED (BS 947-967) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON TOP OF SEAT TRACK BETWEEN BS 947 AND BS 967, RBL 36.5. FABRICATED AND INSTALLED REPLACEMENT SEAT TRACK PER SRM 51-30-2.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON TOP OF FLOORBEAM AT STA. 947.5, RBL 38 TO RBL 43.75. REPAIRED FLOOR BEAM PER SRM 53-10-9.
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON TOP OF FLOORBEAM AT STA 987.5, RBL 36 TO RBL 40. REPLACED FLOORBEAM PER SRM 53-10-9, FIG 3.
Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON CARGO FLOOR TRACK, STA 797 TO 809, RBL 14. REPLACED CARGO FLOOR TRACK PER SRM 51-30-02.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED FLOOR SUPPORT CORRODED BETWEEN STA 967 TO 987.5, RBL 20. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER EA 53-737-173 AND SRM 51-30-2.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED SURFACE CORROSION ON FLOOR SUPPORT BETWEEN BS 947 AND BS 967, FROM RBL 11.50 TO RBL 36.50. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER SRM 51-30-02 AND EA 53-737-173.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED SURFACE CORROSION ON FLOOR SUPPORT BETWEEN STA 987.5 AND 1006, BL 0. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER EA 53-737-173 AND SRM 51-30-02 AND SRM 53-10-2.
Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED SURFACE CORROSION ON FLOOR SUPPORT BETWEEN STA 967 AND 987.5, LBL 18. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER EA 53-737-173 AND SRM 51-30-02 AND SRM 53-10-02.
Part: FLOORBEAM — CORRODED (STA. 947.5) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON TOP OF FLOOR BEAM AT STA. 947.5, RBL 38. REPAIRED FLOOR BEAM PER SRM 53-10-9.
Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON R1 DOOR MOP SILL AND THRESHOLD SUPPORT. REMOVED CORROSION ON MOP SILL AND FOUND TO BE OUT OF LIMITS PER SRM 53-10-01. REPLACED MOP SILL PER SRM 51-30-02.
Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON AFT CARGO DOOR OPENING LOWER WEB SILL. REPLACED CARGO WEB SILL PER SRM 51-30-2.
Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED R1 DOOR LOWER SILL WEB CRACKED AT FWD DRAIN HOLE. REMOVED DAMAGED WEB, FABRICATED REPAIR DOUBLER AND FILLER PER SRM 51-40-02, AND INSTALLED REPAIR PARTS PER SRM 51-40-02.
Part: GUSSET — GOUGED (NR 1 COWLING) · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED MULTIPLE GOUGES IN NR 1 ENGINE OTBD COWLING LOWER CHORD AND GUSSET AT SECOND LATCH FITTING FROM FWD SIDE OF COWL. REMOVED DAMAGED AREA AND FABRICATED REPAIR DOUBLER PER SRM 51-40-3 AND 54-10-2. DOUBLER CHANGED THICKNESS OF FORMED SECTION AND NECESSITATED FABRICATION OF TEE FITTING U-BOLT ATTACHMENT PER EA 71-737-022. INSTALLED PER SRM 51-40-3.
Part: SKIN — DENTED (CARGO DOOR) · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED DENT IN AFT CARGO DOOR AT TOP OF DOOR. CUT OUT DAMAGE PER SRM 52-00-3. REMOVED STIFFENER PER SRM 51-30-02. FABRICATED DOUBLER PER SRM 52-00-03. INSTALLED REPAIR DOUBLER AND STIFFENER PER SRM 52-00-3 AND SRM 51-30-2.
Part: CARGO TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON CARGO TRACK TIE DOWN SOCKET AT STA 947, LBL 17. REMOVED SECTION OF CARGO TRACK IN AFT BAY AT LBL 17 FROM STA 917 TO STA 947. SPLICED IN NEW SECTION OF CARGO TRACK PER SRM 51-30-02, 53-40-5 AND SOPM 20-41-02.
Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 26,171 hrs · 14,877 cycles
DURING C-2 CHECK, INSPECTION REPORTED CORROSION ON INTERCOSTAL AT STA 500A TO 500B, RBL 25. FABRICATED AND INSTALLED REPLACEMENT INTERCOSTAL PER BOEING DRAWING 69-41473, SRM 51-30-2 AND SOPM 20-41-02.
Part: SKIN — DELAMINATED (ELEVATOR) · airframe 26,109 hrs · 14,836 cycles
ON WALKAROUND, FLIGHT CREW REPORTED LT ELEVATOR DELAMINATED ON TRAILING EDGE. REPAIRED PER SRM 51-40-9, PARAGRAPH 4 AND EA 55-737-063.
Part: LIGHT — INOPERATIVE (CABIN) · airframe 25,497 hrs · 14,426 cycles
MAINTENANCE REPORTED EMERGENCY PATH LIGHTING AT ROW 1 INOPERATIVE AND EXPOSED WIRES NEAR ROW 16. REPLACED AISLE PATH LIGHT SOCKET AND LENS AT ROW 1 AND REPAIRING WIRING AT ROW 16. SYSTEM CHECKED OKAY.
2001
Part: AMPLIFIER — INOPERATIVE (CABIN) · airframe 24,602 hrs · 13,834 cycles
AIR TURN BACK. FLIGHT CREW REPORTED 30 TO 40 CHIMES FROM BACK OF AIRCRAFT. COULD NOT TALK TO CREW, INTERPHONE INOPERATIVE. REPLACED PA AMPLIFIER AND SYSTEM CHECKED OKAY. ALSO FOUND PILOT CALL SWITCH ON FWD ATTENDANT'S PANEL BAD, CAUSING PILOT CALL CHIME WITHOUT BEING PRESSED. REPLACED FWD ATTENDANT'S PILOT CALL SWITCH AND SYSTEM CHECKED OKAY.
Part: ENGINE — OUT OF RIG (RIGHT) · airframe 24,315 hrs · 13,657 cycles
ABORTED TAKEOFF. FLIGHT CREW REPORTED NR 2 ENGINE WOULD ONLY PRODUCE 2.0 EPR OF THE REQUIRED 2.05. PUSHED RT THROTTLE ALMOST TO FWD STOP WITH NO FURTHER THRUST. ABORTED TAKEOFF AT 90 KNOTS. PERFORMED ENGINE RUN AND FOUND ALL PARAMETERS FOR NR 2 ENGINE LOWER. TRIMMED NR 2 ENGINE PER MM 72-02-200, PAGE 201. ALL PARAMETERS CHECKED NORMAL. PERFORMED HIGH ENERGY STOP INSPECTION PER MM 05-51-111 WITH NO DEFECTS NOTED.
Part: BATTERY PACK — DISCHARGED · airframe 23,767 hrs · 13,312 cycles
PRIOR TO DEPARTURE, MAINTENANCE REPORTED BOTH EMERGENCY OVERWING EXIT LIGHTS INOPERATIVE. MAINTENANCE IS IN THE PROCESS OF TROUBLESHOOTING THE SYSTEM. AN ADDENDUM WILL BE ISSUED WHEN REPAIR IS ACCOMPLISHED. ADDENDUM: REPLACED FORWARD AND CENTER BATTERY PACKS PER MM 33-51-32.
Part: FITTING — LOOSE (NR 2 ENGINE) · airframe 23,462 hrs · 13,105 cycles
REJECTED TAKEOFF. FLIGHT CREW REPORTED NR 2 ENGINE EGT EXCEEDED RED RADIAL. AN ADDENDUM WILL BE ISSUED WHEN CAUSE OF FAILURE AND CORRECTIVE ACTION IS KNOWN. ADDENDUM: PERFORMED EPR SYSTEM TEST AND FOUND NR 2 ENGINE PT7 FITTING LOOSE. TIGHTENED PT7 FITTING, PERFORMED SECOND EPR SYSTEM TEST AND CHECKED OKAY. PERFORMED TRIM PROCEDURE PER MM 71-09-200 AND OPERATIONAL CHECK. ALL PARAMETERS CHECKED OKAY.
Part: POWER SUPPLY — DISCHARGED (CABIN) · airframe 23,109 hrs · 12,865 cycles
PRIOR TO DEPARTURE, FLIGHT CREW REPORTED EMERGENCY AISLE PATH LIGHTING IN FWD CABIN INOPERATIVE. REPLACED FWD EMERGENCY AISLE PATH LIGHTING POWER SUPPLY.
Part: ANGLE — CRACKED (RUDDER) · airframe 22,974 hrs · 12,778 cycles
DURING C-1 CHECK, INSPECTION REPORTED CRACK IN ANGLE, VERTICAL STABILIZER AT APPROXIMATELY RUDDER STA 86.59. MAINTENANCE FABRICATED AND INSTALLED REPAIR ANGLES PER SRM 51-40-4.
Part: SKIN — DENTED (FUSELAGE) · airframe 22,974 hrs · 12,778 cycles
DURING C1 CHECK, INSPECTION REPORTED 2 DENTS ON RIGHT FUSELAGE SKIN AT STA 1016, STR 20R. MAINTENANCE REMOVED DAMAGED AREA, FABRICATED FILLER, REPAIRED DOUBLER, AND INSTALLED.
Part: DOOR — CORRODED (E&E BAY) · corrosion level 2 · airframe 22,974 hrs · 12,778 cycles
DURING C-1 CHECK, INSPECTION REPORTED RT UPPER FWD CORNER OF E&E DOOR CORRODED. MAINTENANCE REMOVED CORROSION AND PERFORMED A WEB REPAIR PER SRM 51-40-02.
2000
Part: ENGINE — STALLED (COMPRESSOR) · airframe 22,293 hrs · 12,339 cycles
REJECTED TAKEOFF. FLIGHT CREW REPORTED HEARING TWO "BANGS" WHICH WAS THOUGHT TO BE A COMPRESSOR STALL AND ABORTED TAKEOFF AT 50 KNOTS WITHOUT INCIDENT. CREW COULD NOT DETERMINE WHICH ENGINE WAS AFFECTED AS THERE WERE NO ENGINE INDICATION FLUCTUATIONS. MAINTENANCE PERFORMED AN ENGINE RUN ON BOTH ENGINES AND A BLEED SURGE VALVE SCHEDULE AND COULD FIND NO DISCREPANCIES.
Part: STRUT — COLLAPSED (LT WHEEL WELL) · airframe 22,250 hrs · 12,308 cycles
AIR TURNBACK. FLIGHT CREW REPORTED LT. MAIN LANDING GEAR UNSAFE LIGHT WOULD NOT EXTINGUISH WITH GEAR HANDLE IN "UP" POSITION. RED UNSAFE AND GREEN GEAR LIGHT ILLUMINATED WITH GEAR HANDLE IN "OFF" POSITION. AIRCRAFT RETURNED TO DEN AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND STRUT COLLAPSED CAUSING GEAR TO CATCH IN WHEEL CUT OUT AREA WHEN RETRACTED. REPLACED LT. MAIN LANDING GEAR, PERFORMED GEAR SWING AND CHECKED OKAY.