Bering Air, Inc.

Operated by BERING AIR INC (per NTSB report)

Operated by Bering Air, Inc. (per NTSB report)

The pilot's failure to extend the landing gear before landing, which resulted in a gear-up landing. Contributing to the accident was the pilot's fatigue and complacency.

Operated by BERING AIR, INC. (per NTSB report)

The pilot's failure to maintain adequate altitude above water, and his loss of situational awareness, which resulted in an inadvertent descent and collision with water.

Operated by BERING AIR INC (per NTSB report)

The loss of directional control during landing due to a flat nose wheel tire, resulting in a runway excursion and collision with trees.

Operated by Bering Air Inc. (per NTSB report)

The pilot’s failure to maintain directional control during the landing roll in a gusting crosswind.

Operated by BERING AIR INC (per NTSB report)

The pilot's failure to maintain adequate altitude and clearance in hilly terrain. A factor contributing to the accident was the performance of a low altitude flight maneuver.

the in-flight collision with a bird.

A failure of the pilot to follow the aircraft checklist, and an inadvertent wheels up landing.

Operated by BERING AIR (per NTSB report)

THE PILOT'S FAILURE TO ADEQUATELY COMPENSATE FOR THE DOWNDRAFT. FACTORS ASSOCIATED WITH THE ACCIDENT WERE: THE SHORT, UPHILL RUNWAY, AND DOWNDRAFTS.

Operated by BERING AIR, INC. — Commuter air carrier (135) Operator Does Business As: BERING AIR (per NTSB report)

INTENTIONAL PERSONAL INJURY. FACTORS IN THE ACCIDENT WERE: THE PERSON'S PSYCHOLOGICAL CONDITION, AND THE LACK OF SUFFICIENT PROCEDURES/AIRPORT STAFF BY THE OPERATOR(S).

Operated by BERING AIR, INC. (per NTSB report)

FUEL STARVATION DUE TO IMPROPER REFUELING PROCEDURES BY THE FBO PERSONNEL, INADEQUATE PREFLIGHT BY THE PILOT, AND RESULTANT ICE IN THE FUEL, WHICH BLOCKED FUEL FLOW TO THE ENGINES. A FACTOR WAS THE LACK OF SUITABLE TERRAIN FOR A FORCED LANDING.

Operated by BERING AIR, INC. (per NTSB report)

THE PILOT'S FAILURE TO REMOVE ALL THE FROST FROM THE AIRPLANE AND EXCEEDING THE GROSS WEIGHT LIMIT OF THE AIRPLANE.

Operated by BERING AIR, INC. (per NTSB report)

THE PILOT'S FAILURE TO MAINTAIN DIRECTIONAL CONTROL OF THE AIRPLANE DURING THE LANDING ROLL.

WAS THE SHEARED FITTING ON THE NOSE GEAR ACTUATOR SHUTTLE VALVE WHICH CAUSED THE NOSE GEAR TO NOT EXTEND FOR LANDING.

Operated by BERING AIR, INC. (per NTSB report)

Operated by BERING AIR (per NTSB report)

Operated by BERING AIR INC. (per NTSB report)

Operated by BERING AIR INC (per NTSB report)

Operated by BERING AIR,INC (per NTSB report)

Sanction: $2,000 · case closed 2005-03-18

Sanction: $2,250 · case closed 2002-11-27

Part: STRUT — DAMAGED (ZONE 600) · airframe 1,428 hrs · 2,261 cycles

DURING PREFLIGHT, IT WAS DISCOVERED THAT THE RH UPPER WING STRUT MISSING PART OF METAL FAIRING. APPEARS THAT DURING MANUFACTURE THE SEAMS WERE OFFSET CAUSING A STRESS IN THE SKIN ALLOWING IT TO CRACK.

Part: ACTUATOR — CRACKED (ZONE 700) · airframe 6,405 hrs · 11,918 cycles

ACFT IN FOR A PHASE 1 INSPECTION. GEAR SWINGS REQUIRED FOR PHASE AND MAINT PERFORMED. 10 SWINGS REQUIRED TO BLEED SYS AFTER OPENING LINES. 6 SWINGS WERE PERFORMED WITH MANUAL GEAR PUMP UNTIL THE RESERVOIR WAS SERVICED PROPERLY. TECHNICIANS BEGAN PERFORMING 10 SWINGS TO BLEED THE SYS. ONE MIN REST BTWN GEAR CYCLES & 5 MIN REST AFTER 5 SWINGS OBSERVED PER MANUAL. DURING GEAR SWING 8/10, GEAR COMING UP WHEN LT MLG ACTUATOR BLEW & DUMPED ALL FLUID. POWER SHUTOFF BEFORE FLUID COMPLETELY DRAINED. FURTHER INSP REVEALED LT MLG ACTUATOR CRACKED AT FWD NECKED DOWN END OF ACTUATOR WHERE PISTON ROD MOVES IN & OUT OF CYLINDER. ACTUATOR REPLACED & RIGGED IAW MANUAL. IF THIS HAPPENED IN FLIGHT THIS AIRCRAFT MAY HAVE HAD TO LAND WITHOUT THE NOSE GEAR BEING FULLY LOCKED DOWN.

Part: SCREW — MISMANUFACTURED (ZONE 300) · airframe 11,190 hrs · 10,828 cycles

DURING AN INSPECTION ON A CESSNA CARAVAN 208B5228 THE AILERON AND ELEVATOR TRIM ACTUATOR LUBRICATION WAS DUE. THE ACTUATORS WERE DISASSEMBLED AND INSPECTED. FOUR EXTERNAL THREAD SCREWS IPC 27-30-02 FIGURE 4 ITEM 3 WERE MEASURED TO BE UNDER ALLOWABLE DIMENSION. RECEIVED 4 SCREWS FROM TEXTRN. ALL FOUR SCREWS WERE FOUND TO BE UNACCEPTABLE DUE TO THE CREWS NOT THREADING SMOOTHLY INTO THE INTERNAL THREAD SLEEVES. ALL FOUR SCREWS WERE TESTED WITH OLD AND NEW INTERNAL THREAD SLEEVES AND FOUND UNACCEPTABLE. SOME OF THE SCREWS WOULD NOT EVEN THREAD INTO THE INTERNAL THREAD SLEEVE. MCFARLANE SELLS A PMA REPLACEMENT FOR THESE PARTS. FOUR OF THE THE MCFARLANE SCREWS WERE ORDERED AND RECEIVED. ALL FOUR OF THESE SCREWS ACTUALLY HAD THE SAME PROBLEM. IF WE PUT ANY OF THESE PARTS IN SERVICE THE ELEVATOR TRIM WOULD HAVE BEEN EXTREMELY STIFF OR POSSIBLE JAMMED IN FLIGHT.

Part: TRANSDUCER — FALSE INDICATION (STALL WARNING) · airframe 1,855 hrs · 3,791 cycles

STALL WARNING HORN GOES OFF INTERMITTENTLY AS HIGH AS 140 KTS

Part: CYLINDER — LEAKING (ZONE 300) · airframe 936 hrs · 1,431 cycles

PILOT FELT STRONG LEFT RUDDER PRESSURE ON TWO CONSECUTIVE TAKE OFFS

Part: SEAL — BROKEN (ZONE 700) · airframe 461 hrs · 764 cycles

RH MAIN LANDING SCRAPPER SEAL BROKEN AND HANGING FROM BOTTOM OF STRUT.

Part: TRANSDUCER — FAILED (RT ENGINE) · airframe 295 hrs · 478 cycles

ON TAKE OFF RIGHT ENGINE LOSS TORQUE INDICATION.

Part: AHRS — FAULTED (ZONE 200) · airframe 5,072 hrs · 10,505 cycles

AHRS #1 & 2 FAILED, HEADING RED "X", LOSE OF SYNTHETIC VISION; GRS #1 S/N: 45T003846, GRS #3 S/N: 45T003702, GMU #1 1CM0333444. GMU #2 S/N: 1CM033471, REMOVED, INSPECTED, REINSTALLED. AHRS SYSTEM POST-MX CHECK PERFORMED. AHRS ADJUSTMENT/TEST, PITCH/ROLL OFFSET CALIBRATION, MAGNETOMETER CALIBRATION, HEADING OFFSET CALIBRATION PERFORMED. OPS CHECKED GOOD.

Part: PRESSURE SWITCH — FAILED (ENGINE FUEL) · airframe 961 hrs · 1,877 cycles

LOW FUEL PRESSURE ANNUNCIATOR WITH ENGINE RUNNING AND ELECTRIC BOOST PUMP ON.

Part: INDICATOR — FAULTED · airframe 4,910 hrs · 10,151 cycles

HEADING INDICATOR RED "X" THEN CAME BACK IN A FEW MINUTES, ALL WHILE ON THE GROUND. SYNTHETIC VERSION ALSO LOST BECAUSE OF RED "X". TROUBLESHOOT AND COULD NOT DUPLICATE.

Part: INDICATOR — FAULTED (ZONE 200) · airframe 3,811 hrs · 7,887 cycles

RED X ON AIRSPEED, VSI, TEMP INTERMITTENTLY; SWAPPED TO RH SIDE AND PROBLEM FOLLOWED, UNIT REPLACED

Part: FIRE WARNING — FALSE ACTIVATION (ENGINE) · airframe 10,342 hrs · 21,570 cycles

ENGINE FIRE ANNUNCIATION AND AURAL ALERT IN CRUISE & ETM EXCEED (PROP & NG EXCEED). WAS FALSE INDICATIONS. INSPECTED SYSTEMS AND NO FINDINGS NOTED.

Part: INDICATION SYS — FAULTED (ENGINE) · airframe 10,376 hrs · 22,032 cycles

ENGINE INSTRUMENTS STOPPED DISPLAYING WHILE IN CRUISE. PILOT DIVERTED TO NEAREST AIRPORT. MECHANIC DISPATCHED TO INSPECT WITH NO FINDINGS.

Part: HUB — LEAKING (PROPELLER) · airframe 10,171 hrs · 21,530 cycles

PROP INSTALLED AND RED OIL NOTED LEAKING FROM PROP BLADE ROOTS AFTER GROUND RUNS. FOLLOWED MANUFACTURES TROUBLESHOOTING AND LEAK CONTINUED. CLEANED/DRIED AND LET SIT OVERNIGHT. FOUND OIL LEAKING FROM BLADE #4 NEXT MORNING WITH PROP STATIC. "0" ENTER FOR PROP CYCLES BECAUSE CYCLES ON PROP ARE NOT TRACKED.

Part: STRUT — LOW PRESSURE (ZONE 700) · airframe 73 hrs · 102 cycles

RH MLG STRUT LOW AND NEEDS SERVICED.

Part: SHIM — MISSING (ZONE 800) · airframe 73 hrs · 102 cycles

CARGO DOOR CONTACTING FORWARD SIDE OF DOOR FRAME WHEN LOADED. FOUND SHIMS MISSING FROM MANUFACTURE

Part: HUB — LEAKING (PROPELLER) · airframe 10,171 hrs · 21,529 cycles

RED OIL LEAKING FROM PROP HUB. DISCOVERED DURING POST FLIGHT INSPECTION. 0 ENTER FOR PROP CYCLES BECAUSE THEY ARE NOT TRACK ON PROPELLERS.

Part: PROPELLER — LEAKING (HUB) · airframe 9,661 hrs · 20,204 cycles

RED OIL FOUND ON HUB. PREFORMED INSPECTIONS PER MPC26 AND PROPELLER STILL LEAKED RED OIL. PROPELLER REMOVED AND REPLACED. CYCLES ARE NOT TRACKED BUT "0" ENTERED TO ALLOW FORM TO SUBMIT.

Part: WARNING MESSAGE — ACTIVATED · airframe 10,182 hrs · 21,238 cycles

WHILE IS CRUISE FLIGHT NG WENT HIGH AND BLINKED RED FOLLOWED BY CAS EXCEEDANCE MESSAGE. INSPECTED AND NO FAULTS FOUND. BELIEVED TO BE GLITCH IN GARMIN CAUSING FALSE INDICATIONS BASED ON THE GARMIN RECORDS FROM THE DATA LOGGER CARD. NO OTHER VISUAL OR AUDITABLE INDICATIONS OF NG OVERSPEED BESIDES GAGE FLICKER AND CAS MESSAGE.

Part: EXHAUST DUCT — CRACKED (LEFT) · airframe 715 hrs · 1,055 cycles

LEFT EXHAUST ON LEFT SIDE OF THE ENGINE CRACKED AROUND WELDED TUBE FOR THE HEATED INLET LIP.

Part: EXHAUST PIPE — CRACKED (LEFT) · airframe 120 hrs · 162 cycles

LEFT OUTBOARD EXHAUST CRACKED WHERE HEATED LIP TUBE IS WELD TO BOTTOM.

Part: DISPLAY — FAILED (ZONE 200) · airframe 10,157 hrs · 21,503 cycles

PFD #1 FAILURE IN FLIGHT. NG "X" OUT. NO ABNORMAL ENGINE INDICATIONS.

Part: SHIMMY DAMPENER — LEAKING (ZONE 700) · airframe 29 hrs · 24 cycles

SHIMMY DAMPENER HAS EXCESSIVE SHIMMY AND LEAKING OIL.

Part: STRUT — LEAKING (ZONE 700) · airframe 873 hrs · 1,320 cycles

NO CHROME SHOWING ON RIGHT LANDING GEAR STRUT

Part: SHIMMY DAMPENER — LOW (ZONE 700) · airframe 79 hrs · 96 cycles

NOSE SHIMMY ON LANDING AND TAKE OFF. FOUND SHIMMY DAMPENER LOW ON FLUID AND GEAR ON TOP OF THE NOSE LANDING GEAR LOOSE.

Part: CONTROL LEVER — STIFF (FLAP SYSTEM) · airframe 63 hrs · 74 cycles

FLAP CONTROL LEVER STIFF

Part: PRESSURE SWITCH — FAILED (AGB) · airframe 833 hrs · 1,248 cycles

PROP DE-ICE CAS MESSAGE ON RUN-UP. FOUND LH & RH LOW OIL PRESSURE SWITCHES WERE FAILED.

Part: PRESSURE SWITCH — LOOSE (LT ENGINE) · airframe 715 hrs · 1,055 cycles

FOUND LH ENGINE OIL LOW PRESSURE SWITCH LOOSE IN BOSS.

Part: DOOR — OUT OF RIG (ZONE 800) · airframe 700 hrs · 1,029 cycles

AFT CABIN DOOR CAS MESSAGE CONTINUOUSLY ON. AFT DOOR PROXIMITY SWITCH NEEDED RE-RIGGED.

Part: RELAY — FAILED (ZONE 200) · airframe 31,345 hrs · 47,264 cycles

BATT TIE OPEN ANNUNCIATOR ILLUMINATED DURING FLIGHT.

Part: HEATER — FAILED (PITOT) · airframe 9,906 hrs · 21,075 cycles

RIGHT PITOT MAST HEATING ELEMENT FAILED

Part: CAP — CRACKED (TAIL BOOM) · airframe 9,176 hrs · 19,187 cycles

CAP ON TOP OF THE VERTICAL THAT BEACON MOUNTS TO CRACKED IN MULTIPLE PLACES ALLOWING THE BEACON TO BECOME LOOSE ON TOP OF THE VERTICAL STABILIZER.

Part: ROD END — BROKEN (ZONE 400) · airframe 590 hrs · 818 cycles

RH INERTIAL SEPARATOR INOPERATIVE. AFTER LANDING MAINTENANCE FOUND ROD END BROKEN THAT CONNECTS THE ELECTRIC ACTUATOR TO THE FIRE WALL.

Part: ANCHOR FITTING — MISSING (COCKPIT) · airframe 577 hrs · 799 cycles

PILOTS CROTCH SEATBELT STRAP ANCHOR MISSING ATTACHMENT BOLT.

Part: SCREW — LOOSE (YOKE) · airframe 566 hrs · 785 cycles

PILOTS CONTROL YOKE ATTACHMENT SCREWS LOOSE

Part: SCREW — LOOSE (YOKE) · airframe 418 hrs · 580 cycles

CO-PILOTS YOKE SHAFT ATTACHMENT SCREWS LOOSE.

Part: BATTERY — NO TEST (ZONE 100) · airframe 565 hrs · 784 cycles

STANDBY INDICATOR BATTERY FAILED PREFLIGHT TEST AND WOULD NOT CHARGE.

Part: CYLINDER — LEAKING (ZONE 200) · airframe 172 hrs · 214 cycles

RUDDER BIAS SYSTEM ALLOWING RUDDER TO FAVOR ONE SIDE INSTEAD OF BALANCING AS DESIGNED. MORE PILOT RUDDER INPUT REQUIRE TO COUNTER ACT.

Part: CYLINDER — LEAKING (RUDDER BIAS) · airframe 172 hrs · 214 cycles

RUDDER PEDAL HARDER TO PUSH WITH RUDDER BIAS ON. FOUND THE RUDDER BIAS AIR CYLINDER LEAKING AIR FROM ONE SIDE CAUSING THE RUDDER TO BIAS THE NON LEAKING SIDE.

Part: LONGERON — CRACKED (ZONE 400) · airframe 385 hrs · 501 cycles

BOTH LH AND RH LOWER ENGINE COWLINGS HAVE STRUCTURE CRACKED UNDER THE ATTACHMENT OF THE ICE VANE DOOR LINKAGE CASTINGS. CRACKING WAS NOTICED COMING OUT FROM UNDER THE CASTINGS AND WHEN THE INSPECTION PANELS WERE OPENED TO LOOK AT THE STRUCTURE UNDER THE CASTINGS THERE WAS ADDITION CRACKING LOCATED. LONGERON P/N: 7852121-28, SUPPORT P/N: 7852122-22

Part: LONGERON — CRACKED (NACELLE) · airframe 385 hrs · 501 cycles

BOTH LH AND RH LOWER ENGINE COWLINGS HAVE STRUCTURE CRACKED UNDER THE ATTACHMENT OF THE ICE VANE DOOR LINKAGE CASTINGS. CRACKING WAS NOTICED COMING OUT FROM UNDER THE CASTINGS AND WHEN THE INSPECTION PANELS WERE OPENED TO LOOK AT THE STRUCTURE UNDER THE CASTINGS THERE WAS ADDITION CRACKING LOCATED. LONGERON P/N: 7852121-28, SUPPORT P/N: 7852122-22

Part: DUCT — CHAFED (ZONE 400) · airframe 385 hrs · 501 cycles

LH AND RH AFT ICE VANE DOOR FOUND TO BE CHAFING ON EXIT DUCT CAUSING A GROOVE TO BE WORN INTO THE SKIN WHEN ICE VANE SYSTEM IN THE NORMAL CONFIGURATION.

Part: SUPPORT — CRACKED (LT NACELLE) · airframe 75 hrs · 74 cycles

LH LOWER ENGINE COWLINGS HAVE STRUCTURE CRACKED UNDER THE ICE VANE DOOR LINKAGE CASTING ATTACHMENTS. P/N: 7852122-28 & 7852122-27 CRACKED

Part: DUCT — CHAFED (NACELLE) · airframe 17 hrs · 11 cycles

LH & RH AFT ICE VANE DOOR FOUND CHAFING ON EXIT DUCT CAUSING A GROOVE TO BE WORN INTO THE SKIN WHEN THE ICE VANES WERE IN THE NORMAL CONFIGURATION.

Part: MOTOR — FAILED (BLOWER) · airframe 1,010 hrs · 4,644 cycles

BLOWER MOTOR MAKING LOUD NOISES DURING OPERATION. WHEN FAN SPUN BY HAND THERE WAS INDICATION OF DRAG OR ROUGHNESS IN MOTOR. MOTOR HAS ONLY BEEN INSTALLED FOR 205.1HRS.

Part: ADAPTER — CRACKED (RT ELEVATOR) · airframe 32,339 hrs · 43,123 cycles

DURING ROUTINE INSPECTION WHILE PERFORMING INSPECTION "I" CHECK PROCEDURE (5-00-I0) TABLE 1 ITEM 30. IT WAS DISCOVERED THAT THE ELEVATOR HORN TO ELEVATOR ATTACH BRACKET P/N:101-610017-1 WAS CRACKED 85% AROUND THE CIRCUMFERENCE OF THE BRACKET WITH THE CRACK TRAVELING FROM ONE RIVET TO THE NEXT. NO LOOSING OF THE RIVETS WAS OBSERVED. THE OPERATOR DID NOT REPORT ANY OVERSTRESS OF THE ELEVATOR OR ELEVATOR CONTROL SYSTEM AND NO FURTHER DAMAGE WAS FOUND THAT WOULD SUGGEST AN OVERSTRESS CONDITION. FAILURE OF THIS BRACKET WOULD CAUSE LOSS OF ELEVATOR CONTROL ON ONE SIDE AND CAUSE A SERIOUS RISK TO THE SAFETY OF FLIGHT. THE CRACKED BRACKET WAS REPLACED WITH NEW AND THE AIRCRAFT WAS PLACED BACK INTO SERVICE.

Part: PRESSURE SWITCH — FAILED (FUEL SYSTEM) · airframe 2,059 hrs · 4,225 cycles

LOW FUEL PRESSURE CASS MESSAGE. SENSOR ON ENGINE FAILED

Part: PRESSURE SWITCH — FAILED (FUEL OIL COOLER) · airframe 7,518 hrs · 18,044 cycles

LOW FUEL PRESSURE MESSAGE. SENSOR ON ENGINE FAILED.

Part: PRESSURE SWITCH — FAILED (FUEL/OIL COOLER) · airframe 898 hrs · 1,857 cycles

LOW FUEL PRESSSSSURE CASS MESSAGE. SENOR ON ENGINE FAILED

Part: PRESSURE SWITCH — FAILED (FUEL/OIL COOLER) · airframe 6,443 hrs · 12,885 cycles

LOW FUEL PRESSURE CAS MESSAGE. SENOR ON ENGINE FUEL/OIL HEAT EXCHANGER FAILED.