TRANS EXECUTIVE AIRLINES OF HAWAII

Operated by Trans Executive Airlines of Hawaii Inc — On-demand air taxi (135) Operator Does Business As: TransAir (per NTSB report)

Operated by TRANS EXECUTIVE AIRLINES OF HAWAII — On-demand air taxi (135) Operator Does Business As: (per NTSB report)

DUAL ENGINE HYDRAULIC PUMP FAILURE.

STA 360 FRAME BETWEEN S20R-S21R FOUND CRACK AT THE EDGE OF FASTENER HOLE (0.31" IN LENGTH)

BULGE AT RT HORIZONTAL STABILIZER REAR SPAR HSS 136.5.

BULGES AT LEFT HORIZONTAL STABILIZER REAR SPAR CHORD AT HSS 126.

BULGES AT LH SIDE HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM AT STAB 83 (3.0" X 1.5" IN AREA) & STA 116 (0.8" X 0.4" IN AREA)

BULGES AT RT HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM AT HSS 68, 120, 130, AND 137.5.

CORROSION AT LWR LT WING SKIN SURFACE INSPAR WS 583.

ON TAKEOFF LEFT ENGINE DEVELOPED ONLY 1400-1500LBS OF TORQUE WITH THROTTLES FULL FORWARD. REMOVED AND LUBRICATED POWER CONTROL CABLE AND PERFORMED A RIGGING CHECK AND POWER RUN UP. ALL PARAMETERS FOUND NORMAL AND WITHIN LIMITS.

ON INITIAL EXTENSION, THE NOSE GEAR LIGHT ILLUMINATED RED. RECYCLED GEAR FOR GREEN ILLUMINATION & CONFIRMED WITH TOWER & ACFT IN TRAFFIC PATTERN ON NOSE GEAR EXTENSION.

DURING CLIMBED OUT, AFTER PERFORMING CLIMBING CHECKLIST, THE HYDRAULIC CONTENTS GAUGE WAS IN THE MIDDLE OF THE RED ARC. THERE WERE NO CWP OR OTHER INDICATIONS. PILOT RAN THROUGH LOSS OF HYDRAULIC CONTENTS CHECKLIST. THE FIRST ITEM ON THE CHECKLIST WAS TO CLOSE THE INLET VALVES. BOTH HYDRAULIC LIGHTS CAME ON SO INLET VALVES WERE REOPENED. BOTH HYDRAULIC LIGHTS THEN WENT BACK OUT. PILOT THEN PUT LANDING GEAR DOWN, PULLED THE EMERGENCY BRAKE HANDLE, REQUESTED TO DIVERT BACK TO DEPARTURE AND DECLARED AN EMERGENCY. ACFT LANDED. HYDRAULIC SYSTEMS SERVICED AND TESTED. NO DEFECTS NOTED.

PILOT REPORTED FAULTY TORQUE INDICATION ON RT ENG.

ON TAKEOFF ROLL HYD RT ILLUMINATED. MAIN SYS PRESSURE DROPPED TO 2000 PSI.

F/A REPORTED SMOKE IN CABIN. FOUND HYDRAULIC LINE LEAKING.

FLEXIBLE LINE FOR THE NLG ACTUATOR LEAKING.

AFTER DEPARTURE, GEAR UP SELECTION, HYD LEFT AND HYDRAULIC RIGHT LIGHT ILLUMINATED ON CWP, HYD RIGHT CAME BACK ON-LINE. RETURNED TO DEPARTURE, SERVICED HYD SYS.

ON REPOSITIONING THE ACFT, THE LT MAIN TIRE BLEW AND RIM WAS DAMAGED.

AFTER DEPARTURE HYD LT LIGHT ILLUMINATED, WHEN GEAR WAS RETRACTED. RETURNED TO DEPARTURE BASE. ACFT HYD SYS WAS SERVICED AND ACFT DEPARTED WITHOUT FURTHER INCIDENT.

ON TAKEOFF ROLL THE LT ENGINE FLAMED OUT, PILOT ABORTED TAKEOFF NO FURTHER INCIDENT, RETURNED TO BLOCK. INVESTIGATION BY MX FOUND THE LT FUEL PUMP SHAFT SHEARED.

AFTER DEPARTURE, HYD LIGHT ILLUMINATED, WHEN GEAR WAS RETRACTED. RETURNED TO BASE. ACFT HYD SYS WAS SERVICED AND ACFT DEPARTED WITHOUT FURTHER INCIDENT.

LT ENGINE ITT SPIKED TO 1150, THEY REDUCED POWER TO FLIGHT IDLE AND ITT REMAINED AT 830 DEG CENT. SHUTDOWN ENGINE AND CONTINUED TO DESTINATION, LANDED WITHOUT INCIDENT. INVESTIGATION, SPLIT ENG AND DID A HOT SECTION INSPECTION AND FOUND NO DEFECTS. TESTED THE T-5 PROBES AND FOUND 7 EA BAD. REPLACED ALL 10 PROBES AS PRECAUTION AND REPLACED THE FUEL NOZZLES AS A PRECAUTION. OPS CHECKS OK ON ENGINE RUN.

LT ENGINE ITT SPIKED TO 1150 THEY REDUCED POWER TO FLIGHT IDLE AND ITT REMAINED AT 830 DEG CENT. SHUTDOWN ENGINE AND CONTINUED TO DESTINATION, LANDED WITHOUT INCIDENT. INVESTIGATION, SPLIT ENG AND DID A HOT SECTION INSPECTION AND FOUND NO DEFECTS. TESTED THE T-5 PROBES AND FOUND 7 EA BAD. REPLACED ALL 10 PROBES AS PRECAUTION AND REPLACED THE FUEL NOZZLES AS A PRECAUTION. OPS CHECKS OK ON ENGINE RUN.

UPON BLOCKING, PROP WAS FOUND FROZEN AND UNABLE TO TURN. INSPECTED FWD SCREEN AND OIL FILTER, FOUND METAL SHAVINGS IN POWER SECTION SCAVENGE SCREEN AND OIL FILTER. ENGINE WAS REMOVED AND SENT TO MFG FOR FURHTER INVESTIGATION.

LT ENG HAD FIRE WARNING LIGHT ILLUMINATED, NO FIRE, FERRY PERMIT WAS ISSUED IAS GMM CHAP 5.18. NO PART WERE CHANGED. AFT FIRE LOOP FOUND LOOSE, CONNECTION RESECURED. OPS CK OK.

ENG SN PCE 106099 WAS REMOVED FOR METAL CONTAMINATION. IN FLIGHT, OIL PRESSURE FLUCTUATED 70-80 PSI, OIL TEMPERATURE IN CAUTION RANGE. POST FLIGHT INSP FOUND PROP BINDING WITH NOISE COMING FROM POWER SECTION GEAR BOX. REMOVED SCAVENGE PUMP OIL SCREEN AND FOUND LARGE PIECES OF METAL. INSP OF ENG OIL FILTER FOUND MORE METAL. ENG WAS REMOVED AND SHIPPED TO BE REPAIRED. DURING DISASSEMBLY AND INVESTIGATION OF THE POWER SECTION MACHINE HEX BOLTS THAT SECURE THE 1ST STAGE CARRIER SPLINE ADAPTER. 3 OUT OF 6 WERE FOUND WIGHOUT THE BOLT HEAD. POWER SECTION WAS PREVIOUSLY REPAIRED AND ALL (6) BOLTS WERE INSTALLED NEW AT THE TIME. ALL (6) HAVE A TTSN INSTALL OF 229.4.

NR 1 ENGINE OIL PRESSURE DROPPED DOWN IN FLIGHT. CHANGED OIL COOLER AND LEAK CHECKED, OK.

DURING CLIMB PHASE OF FLIGHT, NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCUTATE BETWEEN 90-50 PSI ALL OTHER INDICATIONS WERE NORMAL. RETURNED TO DEPARTURE, MX CHECKED FOR OIL LEAKS, NONE NOTED. REPLACED OIL FILTER, LEAK AND RUN CHECK, OK.

SMOKE LIGHT CAME ON FOR AFT BAGGAGE COMPARTMENT DURING TAXI OUT, RETURNED TO BLOCK, INSPECTED AND FOUND NO FIRE OR SMOKE FALSE LIGHT INDICATION. MEL AFT SMOKE DETECTOR.

THE ACFT RT PROP CABLE BROKE. ACFT RETURNED TO HONOLULU STATION FOR INSPECTION AND REPAIR.

AFT CARGO DOOR/CRACKED SKIN NEAR OF LATCH HANDLE, ACO NR 0753101 PROVIDE INSTRUCTIONS ON REPAIRING CRACK IN AFT CARGO DOOR SKIN NEAR HANDLE, SRM 52-30-2 FIG 3.

SKIN IS CRACKED AT THE LOWER FWD CORNER OF THE L-2 DOOR CUT OUT. ACO NR 075397 REV 0 PROVIDES INSTRUCTIONS ON REPAIR OF L-2 DOOR CRACK SRM 53-30-3 FIGURE 46.

PASSENGER CABIN/CORRODED UPPER SURFACE ON FLOORBEAM BS 941.5 AND LBL-16 TO RBL-7ACO NR 075378 REV. 0 PROVIDE INSTRUCTION ON REPAIR OF FLOOR BEAM AT BS-947.5, LBL 36-RBL 12, SRM 53-10-9 FIGURE 9.

LIGHT SURFACE CORROSION AT SHEAR TIE ON BS 787, LOWER LOBE, BETWEEN STR 27L AND STR 27R, ACO NR 075370 REV 1. PROVIDE INSTRUCTIONS ON REPAIR AT BS 787, LOWER LOBE, BETWEEN STR 27L AND STR 27R SRM 53-10-4 FIGURE 7.

PASSENGER CABIN/CRACKED FRAME AT BS 767 NEAR STRINGER 14R. PROVIDE INSTRUCTIONS ON REPAIR OF CRACKED FRAME AT BS 767 STR 14R, BOEING SB 737-53A-1261 PART 3 REPAIR.

DENT ON FUSELAGE SKIN BETWEEN STR 26R TO STR 25R AT BS 420 R, ACO NR 075366, PROVIDE INSTRUCTIONS ON REPAIR OF SKIN AT BS 420 R STR-25R-26R, SRM 53-30-3.

PASSENGER CABIN/CRACK ON FRAME BS-663 AND STRINGER-2L, ACO NR 075365 PROVIDES INSTRUCTION ON REPAIR OF CRACKED FRAME AT BS-663, STRINGER 2L SRM 53-10-4.

LOWER LOBE/FUSELAGE SKIN, SHOWS SIGNS OF HAVING LOOSE ATTACH RIVETS FROM BS 807 TO BS 827 AT BBL-0. FOUND CORROSION AT THE TIME FASTENER REMOVAL. ACO NR 075369 PROVIDE REPAIRS INSTRUCTIONS ON SKIN REPAIR AT BS 807-827 BBL 0, SRM 53-10-4 FIGURE 6.

LOWER LOBE/FUSELAGE SKIN SHOWS SIGNS OF HAVING LOOSE ATTACH RIVETS FROM BSTA-777 BBL-0. FOUND CORROSION AT FASTENER REMOVAL, ACO NR 075380. PROVIDE INSTRUCTIONS ON REPAIR OF SKIN AT BS-777,FROM STR-27L TO STR-27R SRM 53-30-3 FIGURE 5.

FWD CARGO PIT OIL CAN EFFECT ON SKIN BETWEEN STR 22R AND STR-21R. ALSO BETWEEN STA 480R AND STA 500R ACO NR 075363, PROVIDE INSTRUCTIONS ON REPAIR OF SKIN AT BS 480-500, STR 21R-22R SRM BOEING 53-30-3.

UPPER LOBE/SEVERAL DENTS ON FUSELAGE SKIN FROM BS 995 TO BS1000 BETWEEN S-15L TO S-16L, NEAR DOOR L2.ACO NR 075385 REV 0. PROVIDES INSTRUCTIONS ON REPAIR OF FUSELAGE SKIN AFT OF L2 DOOR, SRM 53-30-3 FIG 46 AND FIG 48 BOEING MESSAGE 1-377247518-4 WITH FAA 8100-9.

DENT ON FUSELAGE SKIN AT BS 358/STR-17L NEAR DOOR L-1. ACO NR 075398 REV. 0, PROVIDE INSTRUCTIONS ON REPAIR OF GOUGE FWD OF BS 360 SRM 53-30-3 AND BOEING MESSAGE 1-326794229-26 AND FAA 8100-9.

OIL-CAN EFFECT ON FUSELAGE SKIN AT BS 384 BETWEEN STR-16L/17L, ACO NR 0753100 REV.0, PROVIDE INSTRUCTIONS ON REPAIR OF DAMAGE SKIN, BETWEEN BS 360L TO BS 420L SRM 53-30-3 AND BOEING MESSAGE 1-326794229-28 AND FAA 8100-9.

DEFECT WAS NOTED DURING INSPECTION OF HORIZONTAL AND VERTICAL STABILIZERS. SKIN AND RIB, TOP SIDE OF RUDDER BALANCE WEIGHT ATTACHMENT AND STRUCTURAL AREA CRACKED AND CORRODED. (WP13200509006) (K)

DEPARTED OUT OF HNL, BUT COULD NOT RETRACT RIGHT MAIN LANDING GEAR. GREEN DOWN AND LOCKED INDICATION LIGHT REMAINED ILLUMINATED. PILOT NOTIFIED THE TOWER AND RETURNED BACK TO BASE. MAINTENANCE WAS NOTIFIED AND UPON INSPECTION DISCOVERED RIGHT OUTBOARD DRIVE TUBE END BROKEN. FURTHER INSPECTION REVEALED NO OTHER DAMAGE TO PARTS OR AIRFRAME. REPLACED AND FULL RETRACTION TEST CARRIED OUT IAW CESSNA MM SECTION 4-19 THROUGH 4-26 AND AIRCRAFT RETURNED TO SERVICE. (M)

ON 11/5/02, POST FLIGHT INSPECTION WAS CARRIED OUT. FOUND 2 BLADES ON RIGHT PROP SN-AP37 TO HAVE EXCESSIVE FORWARD AND ACT PLAY. PROP MFG O/H FACILITY CONSULTED AND CONFIRMED PLAY TO BE EXCESSIVE. PROP REMOVED AND REPLACED. PREVENT RECURRENCE IS NOT TO USE MORE THAN 10 POUNDS OF FORCE WHEN INSPECTING BLADES IAW PROP MM.

PILOT REPORTED LT MAIN GEAR DOWN AND LOCKED BUT NO GEAR DOWN INDICATION. FOUND DOWN LOCK SWITCH FAULTY. REPLACED SWITCH AND COPLETED RETRACTION TEST SATISFACTORY.