N924FR
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| FRONTIER AIRLINES, INC. (F3LA) | Operator | 2009-11-14 – 2009-11-14 | Operator named in NTSB report |
| Frontier Airlines | Operator | 2009-11-14 – 2009-11-14 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
LIGHT INOPERATIVE AT LT EMER ESCAPE HATCH HANDLE. R & R EMER LIGHT 70WL1. OPERATIONS CHECKED GOOD IAW AMM 33-51-11-400-001-A. REF LOG PAGE 895364 ITEM 2.
AIRCRAFT OUT OF SERVICE DUE TO C7 S2 CHECK. AFT MAIN CABIN LT SHEAR PLATE HAS CRACK AT FR 69 - FR 70 STRINGER Y 1292. R & R SHEAR PLATE, AIRBUS A319 SRM 53-41-11 PAGE 6 EO A0-53EO-31434.
AIRCRAFT OUT OF SERVICE DUE TO C7 S2 CHECK. MAIN CABIN FLOOR BEAM RT AT Y 1292, FR 65 - FR 66 HAS CORROSION, BEAM CORROSION IS OUT OF LIMITS. R & R BEAM, AIRBUS A319 SRM 51-42-11 PAR 6.
AIRCRAFT OUT OF SERVICE DUE TO C7 S2 CHECK. FWD CABIN FLOOR BEAM AT FR 20 RT, Y 1292 HAS LIGHT CORROSION. REMOVED CORROSION ON FLOOR BEAM AT FR 20 RT, Y 1292 IN FWD MAIN CABIN. ORIGINAL THICKNESS .079 INCHES, REMAINING THICKNESS .068 INCHES FOUND TO BE WITHIN LIMITS IAW SRM 53-11-14, FIG 105, SH 1 & SRM 51-74-00, PAR 6 B.
AIRCRAFT OUT OF SERVICE DUE TO C7 S2 CHECK. FWD CABIN FLOOR BEAM AT FR 20 LT, Y 1292 HAS LIGHT CORROSION. REMOVED CORROSION ON FLOOR BEAM AT FR 20 LT, Y 1292 IN FWD MAIN CABIN. ORIGINAL THICKNESS .079 INCHES, REMAINING THICKNESS .071 INCHES, FOUND TO BE WITHIN LIMITS IAW SRM 53-11-14, FIG 105, SH 1 & 51-74-00, PAR 6 B.
AIRCRAFT OUT OF SERVICE DUE TO C7 S2 CHECK. AFT CARGO COMPARTMENT DOOR SILL SUB FLOOR COVER PLATE CORRODED IN SPOTS FROM FR 58 TO FR 59. REMOVED SURFACE CORROSION FROM DOOR SILL COVER PLATE, ORIGINAL MATERIAL THICKNESS .080 INCHES, MEASURED MATERIAL LOSS IS .005 INCHES. BLEND OUT WITHIN LIMITS IAW SRM 51-73-00, PAR 5, APPLIED SURFACE PROTECTION.
REF LOG PAGE 503298, ITEM 1. ON DESCENT, HAD A LOUD POP FROM THE CAPTAIN'S SLIDING WINDOW, WINDOW THAN BEGAN TO OVERHEAT. SOON THERE AFTER GOT LIGHT FUMES IN THE COCKPIT. PERFORMED INSP OF THE CAPTAIN'S SLIDING WINDOW REF AMM 56-12-11-200-001, NO DEFECTS NOTED. PERFORMED OPS CHECK OF THE WINDSHIELD ANTI-ICE/DEFOGGING REFERENCE AMM 30-42-00-710-001, OPS CHECK GOOD. REF LOG PAGE 535662 ITEM 1. REPLACED ASSEMBLED LT COCKPIT SLIDING WINDOW CORD, REF ESPM 20-48-21, OPS TEST GOOD.
THE FLIGHT CREW MADE AN AIR RETURN DUE TO MULTIPLE BIRD STRIKES DURING CLIMB OUT CAUSING THE NR 2 ENG COMPRESSOR TO STALL. MX REMOVED AND REPLACED THE NR 2 ENG ASSY AND INLET COWL ASSY, REFERENCE MP71042-01 AND MP71042-02. MX PERFORMED AN OPS CHECK, LEAK CHECK AND RETAINED CAT IIIB STATUS.
FLIGHT CREW MADE AN AIR RETURN DUE TO MULTIPLE BIRD STRIKES DURING CLIMB OUT CAUSING THE NR 2 ENGINE COMPRESSOR TO STALL. MX REMOVED AND REPLACED THE NR 2 ENG ASSY AND INLET COWL ASSY, REFERENCE MP71042-01 AND MP71042-02. MX PERFORMED AN OPS CHECK, LEAK CHECK AND RETAINED CAT IIIB STATUS.
DURING C4 C-CHECK, INSP NOTED THE AFT EMERGENCY POWER SUPPLY UNIT FAILED. MX REMOVED AND REPLACED THE EMERGENCY POWER SUPPLY UNIT AND PERFORMED OPS TEST IAW AMM 33-51-38-000-001 AND 33-51-38-400-001.
DURING C4 C-CHECK, INSP NOTED THE AFT CARGO COMPARTMENT STRUCTURAL PROFILE AT FRAME 56 HAS CORROSION AT THE NUT PLATES. MX PERFORMED MAJOR REPAIR BY REMOVING CORRODED PROFILE, FABRICATING REPLACEMENT PROFILE AND INSTALLING REPLACEMENT PROFILE IAW SRM 51-42-11, 51-72-11, 51-75-12 AND DWG D53974972.
DURING C4 C-CHECK, INSP NOTED THAT THE LT SUPPORT BRACKET AT FRAME 59 HAS CORROSION IN THE FASTENER HOLES. MX REMOVED AND REPLACED THE SUPPORT BRACKET IAW SRM 51-42-11.
DURING DEN C4 C-CHECK, INSP NOTED AT FR 59, THE AFT CENTER SUPPORT BRACKET HAS CORROSION IN FASTENER HOLES. MX PERFORMED MAJOR REPAIR BY REMOVING CORRODED SUPPORT BRACKET, FABRICATING SUPPORT BRACKET AND INSTALLING IAW SRM 51-42-11, 51-44-11, 51-75-12 AND DWG D53476483.
DURING C4 C-CHECK, INSP NOTED THAT THE CENTER LONGITUDINAL SUPPORT FROM FR 58 TO FR 59 HAS CORROSION AT THE NUT PLATE HOLE. MX REMOVED AND REPLACED THE SUPPORT IAW SRM 51-42-11.
DURING C4 C-CHECK, INSP NOTED THAT THE CENTER SUPPORT FITTING UNDER FRAME 58 HAS CORROSION AT NUT PLATE HOLES. MX REMOVED AND REPLACED THE CENTER SUPPORT FITTING IAW SRM 51-42-11.
DURING C4 C-CHECK, INSP NOTED THAT THE AFT CARGO CENTER SUPPORT FITTING ON FRAME 56 HAS CORROSION AT NUT PLATE HOLE. MX REMOVED AND REPLACED FITTING IAW SRM 51-42-00 AND 51-42-11.
DURING C4 C-CHECK, INSP NOTED THAT THE STRUCTURAL PROFILE AT FR 59 HAS SURFACE CORROSION AT NUT PLATE HOLES. MX REMOVED AND REPLACED THE PROFILE AT FR 59 IAW SRM 51-42-11.
DURING C4 C-CHECK, INSP NOTED THAT THE NR 2 ENGINE OTBD FAN COWL HAS DAMAGE ON THE INSIDE OF COWL, 2 FEET FROM THE TOP AND 1 FOOT FROM THE T/E. MX PERFORMED MAJOR REPAIR TO FAN COWL IAW SRM 54-02-00 AND 54-20-00.
DURING C4 C-CHECK, INSP NOTED THAT THE AFT LT EMERGENCY POWER SUPPLY UNIT BATTERY FAILS CAPACITY CHECK. MX REMOVED AND REPLACED THE EMERGENCY POWER SUPPLY UNIT AND PERFORMED OPS CHECK IAW AMM 33-51-38 PB 401.
PILOT REPORTED NR 1 ENGINE FAILURE INFLIGHT, RELIGHT UNSUCCESSFUL. MAINTENANCE INSPECTED NR 1 ENGINE AND FOUND THE GASKET AT THE FUEL FLOW TRANSMITTER DAMAGED. MAINTENANCE REMOVED AND REPLACED THE GASKET, PERFORMED LEAK CHECK AND POWER ASSURANCE CHECK IAW A319 AMM 73-31-10-400-002, 71-00-00-710-006 AND 71-00-00-710-008.
ON TAXI OUT, SPEED LESS THAN 10KTS, AIRCRAFT SWERVED TO THE LEFT (UNCOMMANDED) AND DID NOT RESPOND TO STEERING IMPUTS. STOPPED AIRCRAFT USING BRAKES, RECEIVED ELECTRONIC CENTRALIZED AIRCRAFT MONITORING MESSAGE: WHEEL N/W STEERING FAULT. MAINTENANCE REMOVED AND REPLACED SERVO-CONTROL MODULE AND PERFORMED FUNCTIONAL TEST OF NOSE WHEEL STEERING IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 32-51-51-400-001, 32-51-00-720-003 AND 32-51-00-720-004.
FLIGHT NR 3183. NR 1 ELECTRONIC CENTRALIZED ACFT MONITOR INDICATED LANDING GEAR CONTROL INTERFACE UNIT FAULT. ACFT VIBRATION WAS FELT AFTER LANDING AND ACFT STOPPED ON RUNWAY. MX FOUND NOSE GEAR TIRES TURNED 90 DEGREES AND SEVERAL BROKEN NLG PARTS ON THE RUNWAY. MX STRAIGHTENED OUT THE TIRES AND TOWED ACFT TO REMOTE SITE FOR INSPECTION AND REPAIR. THE NLG LEG ASSEMBLY WILL BE SENT TO THE MFG FOR EVALUATION. THE LABORATORY CONCLUDED THAT THE SHAFT FAILED BY OVERLOAD WHICH OCCURRED FROM APPLIED TORQUE IN A COUNTERCLOCKWISE DIRECTION.
DURING DESCENT & APPROACH, CREW REPORTED AN ECAM INDICATION OF LOW HYD PRESSURE & LOW HYD FLUID LEVEL FOR GREEN HYDC SYS. AN EMERGENCY DECLARED & CREW MANUALLY EXTENDED MLG. ACFT MADE AN UNEVENTFUL LANDING. MX FOUND A HYD TUBE ASSY LEAKING ON NR 1 ENGINE. TUBE ASSY R & R IAW AMM 20-25-11-911-001. MX INSPECTED NR 1 ENGINE CASE DRAIN FILTER & FOUND NO INDICATIONS OF METAL. MX R & R CASE DRAIN FILTER IAW AMM 29-11-43 PB 401. MX SERVICED GREEN HYD SYS IAW AMM 12-12-29-611-001 & RETURNED ACFT TO NORMAL CONFIGURATION IAW AMM 32-33-00 PB 501, SUB-TASK 32-33-00-860-064. MX LEAK CHECKED NR 1 ENGINE IAW AMM 71-00-00-710-006. NO LEAKS FOUND. ACFT RETURNED TO SERVICE.
DURING C CHECK INSPECTION, CABIN FLOOR PANEL 241F, LOCATED IN THE COCKPIT, HAD THE SECOND SCREW HOLE, ON THE RIGHT FORWARD SIDE, PULLED THROUGH. MAINTENANCE REPAIRED THE DAMAGE IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-53R-12384. FOLLOWING COMPLETION OF THE REPAIR AND THE INSTALLATION OF THE FLOOR PANEL, IT WAS INSPECTED AND FOUND TO BE ACCEPTABLE.
DURING C CHECK INSPECTION, THE R2 EMERGENCY DOOR DAMPENER CYLINDER FAILED ITS TEST DUE TO LOW PRESSURE. MAINTENANCE CHARGED THE CYLINDER IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 52-10-00-614-001. UPON COMPLETION OF THE CHARGING, THE CYLINDER PRESSURE WAS VERIFIED TO BE WITHIN ACCEPTABLE LIMITS.
DURING C CHECK INSPECTION, THE R1 EMERGENCY DOOR DAMPENER CYLINDER FAILED ITS TEST DUE TO LOW PRESSURE. MAINTENANCE CHARGED THE CYLINDER IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 52-10-00-614-001. UPON COMPLETION OF THE CHARGING, THE CYLINDER PRESSURE WAS VERIFIED TO BE WITHIN ACCEPTABLE LIMITS.
DURING C CHECK INSPECTION, THE FORWARD FLIGHT ATTENDANT EMERGENCY FLASHLIGHT BATTERY WAS FOUND DEAD. MAINTENANCE REMOVED AND REPLACED THE FLASHLIGHT BATTERY IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 25-65-00. UPON COMPLETION OF THE BATTERY REPLACEMENT, THE FLASHLIGHT WAS INSPECTED AND FOUND OPERATIONAL.
DURING C-CHECK INSPECTION, CORROSION WAS FOUND ON THE FLOORBEAM, AROUND THE NUT CLIP LOCATIONS (6 EACH) AT THE ATTACH POINTS OF THE FLOOR PANEL, JUST INSIDE THE L2 DOOOR. THE FLOORBEAM WAS FOUND CORRODED (OUT OF LIMITS) IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-41-14. MAINTENANCE ACTIONS WERE TAKEN TO REMOVE AND REPLACE THE FLOORBEAM IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. FOLLOWING COMPLETION OF THE INSTALLATION, IT WAS INSPECTED AND FOUND TO BE ACCEPTABLE. REFERENCE NR 25796.
DURING C CHECK INSPECTION, CORROSION WAS FOUND ON THE SHEAR PLATE ON THE RIGHT SIDE, OUTBOARD FLOOR SUPPORT BETWEEN FRAMES 68 AND 70 AT STRINGER 23. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. FOLLOWING COMPLETION OF THE INSTALLATION, THE NEW SHEAR PLATE WAS INSPECTED AND FOUND TO BE ACCEPTABLE.
DURING C-CHECK INSPECTION, THE R1 DOOR SAFETY TAPE INERTIAL REEL WAS FOUND TO HAVE CORROSION ON IT. MAINTENANCE REMOVED AND REPLACED THE R1 DOOR SAFETY TAPE INERTIA REEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-40-00. FOLLOWING COMPLETION OF THE INSTALLATION, IT WAS INSPECTED AND FOUND TO BE ACCEPTABLE. REFERENCE NON-ROUTINE 25802.
FLIGHT CREW REPORTED THAT UPON APPROACH, AT APPROXIMATELY 10 FT ABOVE THE RUNWAY, AIRCRAFT ABRUPTLY NOSED OVER DURING FLARE WITH FULL AFT STICK HELD (HAND-FLOWN APPROACH). NO ECAM WARNINGS OR OTHER INDICATIONS. THE FLIGHT DATA RECORDER HAS BEEN DOWNLOADED AND THE INFORMATION IS BEING REVIEWED. A SUPPLEMENTAL SDR WILL BE PREPARED AND SUBMITTED UPON RESOLUTION OF THE DISCREPANCY. ON 10/25/06, MAINTENANCE REPLACED THE CAPTAIN'S SIDE STICK CONTROL ASSY AS PRECAUTIONARY AND PERFORMED OPS TEST IAW MM 27-92-41-400-001. OPS TEST NORMAL. PERFORMED OPERATIONAL CHECK FLIGHT. CHECK FLIGHT SATISFACTORY, NO FAULTS NOTED. AIRCRAFT RETURNED TO SERVICE.
DURING C-2 CHECK, INSPECTION REPORTED FWD LT EPSU (EMERGENCY POWER SUPPLY UNIT) FAILED TEST. REPLACED LT FWD EPSU AND PERFORMED OPERATIONAL CHECK. TESTED GOOD.
DURING C-2 CHECK, INSPECTION REPORTED MASK BOX OVER L1 DOOR (40WR) DID NOT DROP. REPACKED O2 MASKS OVER L1 DOOR AND OPS CHECKED IAW AMM 35-23-00-720-454. CHECKED GOOD.
DURING C-2 CHECK, INSPECTION REPORTED A RIVET HEAD SHEARED OFF AT LT SIDE FWD A/C BAY, FWD LOWER CORNER WEB AT ZONE 191, I/B SIDE OF WEB, LOCATED O/B OF EMERGENCY RAM AIR CONNECTOR. REPLACED SHEARED RIVET PER A319 SRM 51-42-11.
DURING C-2 CHECK, PRE-RECORDED ANNOUNCEMENT DID NOT COME ON DURING OXYGEN MASK DROP TEST. FOUND PRE-RECORDED ANNOUNCEMENT OUTPUT WIRES CAPPED & STOWED, LIVE TV WIRES IN THEIR PLACE. WIRE 2332-5811 CAPPED & STOWED AT CONNECTOR 166VCA, SHIELDED PAIR WIRE 2332-7879 CAPPED & STOWED AT CONNECTOR 165VCA. LIVE TV WIRE 2339-9868 INSTALLED AT 166VCA PIN 29 & 2339-9867 WAS INSTALLED AT 165VCA PINS 15 & 16. RE-TERMINATED WIRES 2332-7879 ON 165VCA PINS 15, 16, 17, 2332-5811 ON 166VCA PIN 29 AND LIVE TV WIRES 2339-9867 ON 165VCA PINS 7, 1, 2 AND 2339-9868 ON 166VCA PIN 21. PERFORMED OPS CHECK, TEST GOOD.
DURING C-2 CHECK, INSPECTION REPORTED THE PASSENGER OXYGEN MASK DOOR AT ROW 7 ABC DID NOT OPEN DURING TEST. REPLACED PASSENGER OXYGEN CONTAINER ASSY PER AMM 35-21-41, PB 401, AND 35-21-41-481-050.
BLOCK TURNBACK. FLIGHT CREW REPORTED LOW PRESSURE BOTH ENGINES DURING START WITH FUMES INTO CABIN. REPLACED BMC NR1. LOW BLEED PRESSURE OPS CHECKED GOOD IAW AMM 36-11-34, PAGE 401. FOUND DE-ICE FLUID IN APU AIR INTAKE WHICH WAS CAUSING FUMES. CLEANED APU AIR INTAKE. NO FUMES NOTED IAW AMM 49-16-00-100-003.