Aitheras Aviation Group, LLC

Operated by Aitheras Aviation group, LLC (per NTSB report)

The vehicle driver’s inadequate visual lookout while driving on a non-licensed vehicle roadway in restricted visibility conditions, which resulted in a collision with a taxiing airplane.

Operated by Aitheras Aviation Group (per NTSB report)

The pilot experienced spatial disorientation during the inital climb causing him to lose control of the airplane.

Sanction: $10,000 · case closed 2025-08-07

Part: TORQUE TUBE — CRACKED (RUDDER) · airframe 1,096 hrs · 681 cycles

DURING SCHEDULED INSPECTION, THE RUDDER TORQUE TUBE WAS FOUND CRACKED APPROXIMATELY 90% OF DIAMETER. CAUSE IS BELIEVED TO BE WIND DAMAGE DUE TO CONTROL LOCKS NOT ENGAGED WHEN PARKED. RUDDER WAS REMOVED AND SENT TO CESSNA FOR REPAIR.

Part: LINER — DAMAGED (NR 2 ENGINE)

ENGINE WAS INSPECTED TO CHECK OUT BASE MX (FOD INSPECTION). ABRADABLE MATERIAL WAS FOUND MISSNG FROM LOW COMPRESSOR CASE FTO 9 O`CLOCK THROUGH OUT 10:30 O`CLOCK POSITION. BELIEVE THE MATERIAL WAS LOOSENED BY THE BIRD STIKE BUT NOT EASILY DETECTED. THE MATERIAL THEN DEPARTED FROM ENGINE ON RETURN FLIGHT TO BASE. NO ADDITIONAL DAMAGE OR PROBLEMS WERE ENCOUNTERED. THE MATERIAL WAS REPLACED IAW MM.

Part: SKIN PANEL — DENTED (RT WING) · airframe 13,151 hrs

ACFT WAS INSPECTED TO CHECK OUT BASE MX (FOD INSPECTION). A 3" BY 5" DENT .125" DEEP WAS DISCOVERED 2 FT INBD OF STALL STRIP UNDER THE DEICE BOOT. DAMAGE WILL BE REPAIRED IAW EA RECOMMENDATIONS.

Part: ACTUATOR — LEAKING (RT MLG) · airframe 11,203 hrs · 9,257 cycles

RIGHT MAIN LANDING GEAR FAILED TO RETRACT. PILOT'S SELECTED DOWN AND RECEIVED A SAFE INDICATION. AIRCRAFT LANDED WITHOUT INCIDENT. AIRCRAFT WAS PLACED ON JACKS AND TROUBLESHOOTING REVEALED ACTUATOR WAS LEAKING INTERNALLY. ACTUATOR WAS REPLACED IAW C560MM CH32-31-04. RETRACTION TEST SATISFACTORY.

Part: UNKNOWN — MALFUNCTIONED (LANDING GEAR) · airframe 11,196 hrs · 9,248 cycles

UPON DEPARTURE CREW REPORTED LANDING GEAR RETRACTED FOLLOWED BY RIGHT MAIN GEAR EXTENDING TO DOWN AND LOCKED POSITION. INDICATION WAS A RED INTRANSIT AND RIGHT GEAR DOWN (GREEN) LIGHTS ILLUMINATED. CREW EXTENDED LANDING GEAR AND RECEIVED THREE GEAR DOWN (GREEN) LIGHTS. CREW RETURNED AND LANDED AT DEPARTURE AIRPORT UNEVENTFULLY. AIRCRAFT WAS PLACED ON JACKS AND RETRACTION TESTED SEVERAL TIMES BUT COULD NOT DUPLICATE PROBLEM. LANDING GEAR UPLOCK HOOK AND ROLLER WAS CLEANED AND LUBRICATED. SEVERAL ADDITIONAL GEAR RETRACTIONS WERE CONDUCTED WITH NO DEFECTS NOTED. AIRCRAFT WAS RETURNED TO SERVICE.

Part: LIGHT — INOPERATIVE (COCKPIT) · airframe 10,471 hrs · 8,701 cycles

LEFT MAIN GEAR DOWN LIGHT FAILED TO ILLUMINATE WHEN LANDING GEAR WAS EXTENDED. CREW RECYCLED GEAR WITH SAME RESULT. THEN EXTENDED THE LANDING GEAR USING THE EMERGENCY SYSTEM. THE LANDING WAS UNEVENTFUL. INVESTIGATION REVEALED THE INDICATOR LAMP HAD FAILED. LANDING SYSTEM WAS RESET AND RETRACTION TEST WAS SATISFACTORY. AIRCRAFT RETURNED TO SERVICE.

Part: UPLOCK SWITCH — STUCK (NLG)

ON TAKEOFF, LANDING GEAR WOULD NOT FULLY RETRACT AS INDICATED BY "IN TRANSIT" AND "HYD ON" LIGHT STAYED ON. ACFT ALSO EXPERIENCED BUFFETING. FLIGHT CREW RECYCLED LANDING GEAR WITH SAME RESULT THEN EXTENDED LANDING GEAR NORMALLY. ACFT RETURNED WITH A NORMAL LANDING. ACFT WAS FERRIED TO A REPAIR FACILITY WITH LANDING GEAR EXTENDED. TROUBLESHOOTING REVEALED A STICKY NOSE GEAR UPLOCK AND SWITCH. UNITS WERE CLEANED AND LUBRICATED. OPS TEST OF LANDING GEAR RETRACTION WAS SATISFACTORY. ACFT WAS RETURNED TO SERVICE.

Part: SKIN — DAMAGED (FS 171.80)

ACFT WAS PARKED, POSITIONED WITH STRONG TAILWIND COMPONENT. WHEN CREW OPENED CABIN DOOR PILOT LOST GRIP ON HANDLE AND WIND SLAMMED DOOR OPEN, BREAKING THE HINGE AND DAMAGED THE FUSELAGE SIDE AT FS 171.80. REPAIR IS BEING COMPLETED IAW REPORT S-500-ATA53-07RD.

Part: WINDOW — CRACKED (ZONE 200) · airframe 13,689 hrs · 12,403 cycles

DURING PHASE 49 INSPECTION, CRACKS AT HOLES NR 5 AND 6 WERE FOUND IN COPILOT'S OUTER SIDE WINDOW. THESE EXCEED ALLOWABLE LIMITS IAW THE MFG. WINDOW WILL BE REPLACED IAW MM.

Part: STRUCTURE — CRACKED (ZONE 200) · airframe 13,689 hrs · 12,403 cycles

DURING PHASE 49 INSP EDDY CURRENT INP INDICATED A POSSIBLE CRACK. PAINT AND FILLER WERE REMOVED AND AREA INSPECTED BY VISUAL INSP USING MAGNIFICATION WHICH CONFIRMED 3 CRACKS IN BAND AT FS 287.78. IT APPEARS BAND WAS DAMAGED DURING LAST REPAINT OF ACFT, CAUSING STRESS RISERS AND SUBSEQUENT CRACKING.

Part: ANGLE — CRACKED (SPEEDBRK DOOR)

DURING ROUTINE MX, THE RT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.

Part: ANGLE — CRACKED (SPEEDBRK DOOR)

DURING ROUTINE MX, THE LT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.

Part: FITTING — LOOSE (WHEEL HUBCAP)

ON LANDING, PILOT REPORTED BRAKING ACTION WAS NORMAL. UPON SECOND APPLICATION OF BRAKES TO ENTER A TAXIWAY, LOST ALL BRAKING ACTION. ACFT WAS STOPPED WITHOUT INCIDENT, USING EMERGENCY PNUEMATIC SYS. MX BLED BRAKES AND TROUBLESHOT SYS TO A LOOSE FITTING DRIVE CLIP IN RT HUBCAP. CLIP WAS ADJUSTED AND OPS TEST WAS STATISFACTORY. ACFT TAXI TEST WAS SATISFACTORY.

Part: MANIFOLD — LEAKING (LT ENGINE)

MECHANIC EXPERIENCED A SLOW/COLD START ON LT ENGINE. ENGINE IDLED SLOWER THAN NORMAL. ALL OTHER PARAMETERS WERE NORMAL. UPON SHUTDOWN, FLUID (FUEL) WAS PUDDLED IN BYPASS DUCT AND DRIPPING FROM AFT ENGINE CORE. INVESTIGATION REVEALED PRIMARY AND SECONDARY CROSS MANIFOLD AREA WAS LEAKING. FUEL MANIFOLD WAS REMOVED FOR FURTHER INSPECTION. (K)

Part: SUPPORT BRACKET — MISSING (THRUST REVERSER)

DURING ROUTINE INSPECTION, THE LT OB THRUST REVERSER STANG FOUND DISPLACED .2500 INCH OB FROM NORMAL POSITION. REMOVAL OF STANG REVEALED THE LOWER FWD SUPPORT WAS MISSING THE UPPER FWD SUPPORT SHEARED OFF. THE ATTACHING RIVETS HAD FAILED. FURTHER INSPECTION REVEALED THE UPPER AFT MOUNTING LUG OF OB (BIRDCAGE) WAS CRACKED DUE TO STRESSES IMPOSED DUE TO MISSING FWD SUPPORT. THRUST REVERSER WAS REMOVED AND SENT TO MFG FOR REPAIR. AS PREVENTIVE MEASURE, THE RT OB THRUST REVERSER STANG WAS REMOVED AND THE LOWER FWD SUPPORT WAS FOUND LOOSE WITH ONE SHEARED ATTACHING RIVET. THE UNIT WAS REMOVED FOR REPAIR. CAUSE MAY HAVE BEEN ACCUMULATED AGE AND VIBRATION. (K)

Part: CONTROL CABLE — BROKEN (TE FLAPS)

FLAPS WOULD NOT EXTEND DURING APPROACH. AN UNEVENTFUL (NO FLAP)LANDING WAS ACCOMPLISHED. INSPECTION REVEALED THE FLAP FOLLOWUP CABLE (AFT) HAD BROKEN WHERE IT PASSES OVER 1 PULLEY FORMING AN (S) ROUTING. THIS IS A HIGH WEAR AREA AND COMMON PROBLEM ON THIS MODEL AC. THE CABLE WAS REPLACED. (K)