N172GA
Registered owner: ALPINE AVIATION INC, UT (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| ALPINE AVIATION, INC. (TIMA) | Certificate holder | — | Matched by certificate designator |
| ALPINE AVIATION, INC. (TIMA) | Operator | 2018-04-29 – 2018-04-29 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
FOUND FUEL TANK INTERCONNECT TUBES IN LEFT AND RIGHT MAIN LANDING GEAR WELLS TO BE CHAFED WHERE THE TUBES PASS THROUGH THE OUT BOARD KEEL BEAM. THE RIGHT HAND SIDE WORN TO OVER 90% OF THE WALL THICKNESS. THE LEFT HAND SIDE WAS WORN TO APPROX 75% OF THE WALL THICKNESS.
RIGHT MAIN LANDING DRAG BRACE DISCONNECTED FROM WING ATTACH POINT. LANDING GEAR STRUT RETRACED THE AFT CONTACTING WING STRUCTURE. INVESTIGATION FOUND DRAG BRACE ATTACH BOLT BROKEN AT GREASE GALLEY.
DURING TAKEOFF ROLL BAGGAGE DOOR ANNUNCIATION ILLUMINATED. PILOT ABORTED TAKEOFF. INSPECTION REVEALED THE NOSE BAGGAGE DOOR SWITCH HAD FAILED.
DURING MX INSPECTION, THE LT SIDE SEAT RAIL WAS FOUND TO BE CORRODED.
DURING MX, THE RT SIDE SEAT RAIL WAS FOUND TO BE CORRODED.
INSPECTION REVEALED CORROSION DEVELOPING ON THE LT UPPER MAIN SPAR CAP UNDER THE VORTEX GENERATORS.
SEVERAL CRACKS DEVELOPED IN THE SKIN OTBD OF THE LT NACELLE & AFT OF THE MAIN SPAR ORIGINATING FROM VARIOUS RIVETS.
RIGHT WING DEBOND. UPPER SKIN OF BONDED PANEL IN AREA AROUND FUEL BAY ACCESS OVAL PANEL DEBONDED FROM FUEL ACCESS DISH & HONEYCOMB CORE.
LEFT WING DEBOND. UPPER SKIN OF BONDED PANEL IN AREA AROUND FUEL BAY ACCESS OVAL PANEL DEBONDED FROM FUEL ACCESS DISH & HONEYCOMB CORE.
TWO CRACKS WERE DISCOVERED IN THE VERTICAL STABILIZER RIB AT CSS 69. REPAIRED IAW SRM 51-10-21.
A CRACK WAS DISCOVERED IN THE LT HORIZONTAL STABILIZER FWD SPAR DOUBLER. THE LT HORIZONTAL STABILIZER FORWARD SPAR DOUBLER WAS REPLACED WITH A NEW PART.
A CRACK WAS DISCOVERED IN THE LT FWD SPAR CAP OF THE VERTICAL STABILIZER ABOVE CSS 61. REPAIRED IAW FR-CO-02599, REV 1.
DURING AN INSPECTION, A CRACK IN THE LT HORIZONTAL STABILIZER LOWER TEE EXTRUSION WAS DISCOVERED. REPAIRED THE CRACKED TEE EXTRUSION BY SPLICING IN A NEW SECTION IAW REPAIR FR-CO-02598. TWO REPAIR ANGLES WERE FABRICATED USING A SECTION OF A NEW TEE.
MAIN LANDING GEAR ACTUATOR ROD END CAP FOUND CRACKED DURING NDT INSPECTION TO C/W AD 2009-23-01.
WHILE CLEANING LITE CORROSION ON SURFACE OF BELLY AFT OF WINGS, NOTICED SOME APPARENT BLISTERING OF THE SKIN. INVESTIGATION REVEALED THERE WAS CORROSION BETWEEN THE SKIN AND THE FUSELAGE FRAME. AFFECTED SKIN WAS CUT OUT AND REPLACED AS A COVER PATCH IN ACCORDANCE WITH BEECH STRUCTURAL REPAIR MANUAL.
PILOT EXPERIENCED A FIRE WARNING ANNUNCIATION DURING TAKEOFF ROLL. PILOT ABORTED TAKEOFF. MAINTENANCE FOUND THAT ONE FIRELOOP HAD FAILED AND CAUSED THE FALSE FIRE INDICATION. (K)
LEADING EDGE OF STABILIZER DISBONDED ON LOWER SIDE AND A CRACK FORMED JUST OFF THE END CAP AND COMPOSITE JOINT. (CONTROL NR 74)
ANGLE LOCATED ABOVE THE ICE DOOR HINGE. THIS ANGLE HOLDS THE LOWER FIRE SEAL BULK HEAD WHEN THIS ANGLE CRACKS, IT ALLOWS THE OUTSIDE COWL RIVETS TO WORK LOOSE, AND THIS CAUSES THE COWL SIDE SKIN TO CRACK.
BOLT PN 908200115, CONNECTING NOSE GEAR DRAG BRACE TO NOSE STRUT, AND BOLT PN 908200111 CONNECTING THE TWO DRAG BRACE HALVES WAS FOUND WITH PITTING TYPE CORROSION.
AIRSTAIR DOOR CABLE BROKE, ALLOWING ONE SIDE OF THE DOOR TO REMAIN UNLOCKED.
THE ICE VANE CONTROL WIRE NUMBER 20A20 BROKE AT THE TERMINAL END UNDER THE PANEL AT INST ZONE 245 CAUSING A SHORT WHICH CAUSED SMOKE IN THE COCKPIT.
INSPECTION OF FLAP CABLES AS OUTLINED IN BEECH S/B 27-3397 PER AD 2001-18-07 REVEALED THE RIGHT OUTBOARD FLAP CABLE DEFECTIVE. THE INNER SHAFT RETAINER WAS NOT ATTACHED TO THE FERRULE AS REQUIRED. (M)
OIL LINE TO THE TORQUE MANIFOLD, B-NUT CAME LOOSE, OIL PRESSURE FLUCTUATED AND ENGINE SHUT DOWN. AIRCRAFT LANDED. ENGINE WAS INSPECTED AS PER MM, LOW OIL PRESSURE PROCEDURE. NO DAMAGE FOUND - OIL SERVICED AND ENGINE TEST RUN PER P/W CHECK.
OIL LINE TO THE TORQUE MANIFOLD B-NUT CAME LOOSE. OIL PRESSURE FLUCTUATED AND ENGINE SHUT DOWN. AIRCRAFT LANDED. ENGINE WAS INSPECTED AS PER PWA MM. LOW OIL PRESSURE PROCEDURE, NO DAMAGE FOUND. OIL SERVICED AND ENGINE TEST RUN, PER PWA CHECK.
LOWER CAP LEFT STABILIZER OUTER 6 IS CORRODED.
LEFT AILERON TRIM TAB HORN CORRODED.
P43 INSPECTION FOUND A .8 INCH CRACK IN THE OUTDBOARD FLANGE RADIUS OF THE INTERCOSTAL AT THE UPPER CARGO DOOR FRAME AT FS 494.
FOUND THE OUTBOARD 6 INCHES LOWER RIGHT REAR SPAR CAP EXTRUSION CORRODED. CORROSION WAS FOUND WHILE REPLACING A CORRODED OUTBOARD ELEVATOR HINGE BRACKET.
DURING INSPECTION, THE RIGHT OUTBOARD AND THE RIGHT MIDDLE ELEVATOR HINGE BRACKET WERE FOUND TO BE CORRODED.
FLT 9410 - MIA/EYW - AFTER ROTATION, RIGHT PROP RPM DROPPED TO APPROXIMATELY 1200 RPM. RETURNED TO MIA. DETERMINED RIGHT BETA BLOCK TO BE WORN. REPLACED RIGHT BETA BLOCK AND RIGGED. (M)
FLT 9209 - ON CLIMB-OUT FROM TAMPA, RIGHT T-HANDLE FIRE WARNING ILLUMINATED. PILOT SHUT DOWN ENGINE, DECLARED EMERGENCY AND RETURNED TO TAMPA. AIRCRAFT LANDED WITHOUT INCIDENT. INSPECTED RIGHT ENGINE. NO EVIDENCE OF FIRE. DETERMINED TO BE HOT AIR LEAKING FROM LOOSE INLET HEAT BLAST TUBE. SECURED BLAST TUBE CLAMP. (M)