Image Air Charter LLC

Part: SKIN — CORRODED (ZONE 100) · airframe 6,483 hrs · 5,186 cycles

DURING 12, 24, 48 & 96 MONTH INSPECTIONS, CORROSION WAS DISCOVERED IN THE CABIN FLOOR LOWER SKIN AT SEVERAL LOCATIONS. FROM FS 157.00 TO FS 366.56. REPAIRS WERE MADE IN ACCORDANCE WITH TEXTRON AVIATION FIELD REPAIR # FR-560-5027-14050. DOUBLERS WERE INSTALLED TO REINFORCE 4 AREAS OF THE LOWER SKIN PN 6611040-28 AND STRINGER 16R PN 6611060-42.

Part: ACCESS PANEL — CORRODED (ZONE 500) · airframe 5,470 hrs · 3,148 cycles

LEFT AND RIGHT WING FUEL TANK ACCESS PANELS 510CB, 540AB, 610AB, 640AB, 640BB LIGHT CORROSION. REPAIRED UNDER BOMBARDIER REO 604-57-25-1062.

Part: SKIN — CORRODED (ZONE 100) · airframe 5,470 hrs · 3,148 cycles

LEFT AND RIGHT LOWER FUSELAGE SKIN AT FORWARD BELLY FAIRING ATTACHMENTS LIGHT CORROSION. REPAIRED UNDER BOMBARDIER REO 604-53-21-420.

Part: ACCESS PANEL — CORRODED (ZONE 500) · airframe 5,470 hrs · 3,148 cycles

LEFT AND RIGHT FUEL PANELS 540AB & 610AB CORROSION ON CLAMPING RINGS. REPAIRED UNDER BOMBARDIER REO 604-57-25-1061.

Part: ACCESS PANEL — CORRODED (ZONE 500) · airframe 5,470 hrs · 3,148 cycles

LEFT AND RIGHT WING FUEL ACCESS OPENINGS, 510AB,540AB & 610AB LIGHT CORROSION. REPAIRED UNDER BOMBARDIER REO 604-57-25-1060

Part: SPAR CAP — CORRODED (ZONE 500) · airframe 5,470 hrs · 3,148 cycles

LEFT WING FRONT SPAR CAP LIGHT CORROSION AT STATION BL 45. REPAIRED UNDER BOMBARDIER REO 604-57-22-108.

Part: ACCESS PANEL — CORRODED (ZONE 600) · airframe 5,470 hrs · 3,148 cycles

RIGHT WING LOWER PLANK ACCESS PANELS 640AB & 640BB LIGHT CORROSION. REPAIRED UNDER BOMBARDIER REO 604-57-25-1057.

Part: SKIN — CORRODED (ZONE 200) · airframe 5,470 hrs · 3,148 cycles

AFT FUSELAGE SKIN AT APU EXHAUST CUTOUT CORROSION. REPAIRED UNDER BOMBARDIER REO 604-53-42-490

Part: BULKHEAD — DAMAGED (TAILCONE) · airframe 4,452 hrs · 3,725 cycles

DURING COMPLIANCE WITH DOCUMENT 4 REV 44, DAMAGE WAS FOUND ON AFT SIDE OF AFT TAILCONE BULKHEAD AT 5:30 CLOCK POSITION. DAMAGE APPEARS TO BE CONSISTENT WITH THE TAIL OF A LONG SCREW CONTACTING THE BULKHEAD. A TOO-LONG SCREW WAS NOT REMOVED FROM THAT LOCATION AT THIS TIME. REPAIR INCLUDED FABRICATION OF A DOUBLER FROM STAINLESS STEEL AND AN ALUMINUM ANGLE AND INSTALLATION IAW AQRD ERO-967383 DATED 11/18/20 WITH APPROVAL FROM TEXTRON ENGINEERING ON FAA FORM 8110-3 DATED 11/20/20.

Part: ATTACH PLATE — CHAFED (HORIZONTAL STAB) · airframe 4,452 hrs · 3,725 cycles

SMALL AMOUNT OF CHAFING ON RH ATTACHMENT LUG OF HORIZONTAL STABILIZER. CAUSE APPEARS TO BE TIGHT CLEARANCE OF LUG TO CLOSEOUT FAIRING WHEN SAFETY WIRE WAS SANDWICHED IN THAT OPENING. CORRECTIVE ACTION INVOLVED BLENDING OF CHAFED AREA FOLLOWED BY EDDY CURRENT AND ULTRASONIC CHECKS IAW AQRD ERO-967382 DATED 11/09/2020.

Part: SKIN — DENTED (HORIZONTAL STAB) · airframe 4,452 hrs · 3,725 cycles

A DENT WAS FOUND AT THE LEADING EDGE OF THE LH HORIZONTAL STABILIZER UNDER THE DEICE BOOT AT HS WS50. REMOVED LH DEICE BOOT, HAND FORMED LEADING EDGE TO WITHIN 0.060" OF ORIGINAL CONTOUR. ACCOMPLISHED EDDY CURRENT CHECKS AND APPLIED AERODYNAMIC FILLER TO ACHIEVE ORIGINAL CONTOUR. INSTALLED NEW DEICE BOOT. WORK PERFOMED IAW TEXTRON STRUCTURES ENGINEERING MINOR REPAIR LETTER DQ27780M1 RRL DATED 11/19/2020.

Part: TRUNNION — CHAFED (LT MLG) · airframe 4,452 hrs · 3,725 cycles

DURING INSPECTION DOCUMENT 4, FOUND A CHAFE MARK ON LMLG TRUNNION AT THE TOP CASTING EDGE. APPEARED TO BE CAUSED FROM THE BONDING STRAP BE PULLED TIGHT DURING GEAR RETRACTION. REPAIRED BY BLENDING OUT DAMAGE AND INSPECTING WITH EDDY CURRENT IAW TEXTRON ENGINEERING MINOR REPAIR LETTER DQ27655M1 RRL DATED 11/9/2020.

Part: CLOSEOUT PANEL — CRACKED (RT WING) · airframe 4,452 hrs · 3,725 cycles

DURING COMPLIANCE WITH DOCUMENT 4 REV 44, A CRACK WAS FOUND IN THE CLOSEOUT PANEL ON THE AFT SIDE OF THE RH WHEEL WELL. REPAIR INVOLVED STOP DRILL OF CRACK AND FABRICATING A DOUBLER TO PLACE BEHIND THE CLOSEOUT PANEL IAW AQRD ERO-967381 DATED 11/16/20.

Part: TUBE — CHAFED (HYD SYSTEM) · airframe 2,959 hrs · 1,552 cycles

TUBE WAS CHAFED AT TWO LOCATIONS UNDER ADEL CLAMPS USED FOR ROUTING THE STAINLESS STEEL TUBE. WEAR WAS NOT TO THE POINT OF CAUSING ANY LEAKAGE IN THIS 3000 PSI PRESSURE LINE. THESE WERE BOTH LOCATIONS REQUIRED FOR INSPECTION WHEN PERFORMING SB 605-29-008. CONDITION WAS FOUND DURING COMPLIANCE WITH THIS SB.

Part: TRANSDUCER — INOPERATIVE (RT ENGINE) · airframe 11,478 hrs · 7,689 cycles

ON THE LAST LEG OF THE TRIP, ON START UP, THE RT ENGINE COMPUTER INOPERATIVE LIGHT ILLUMINATED. FOUND BAD N2 TRANSDUCER. REPLACED THE TRANSDUCER, OPS CHECKED GOOD.

Part: LINE — LEAKING (ACM) · airframe 7,219 hrs · 6,983 cycles

CABIN LOW PRESSURE LIGHT ILLUMINATED AT ALTITUDE. REPAIRED NUMEROUS LEAKS IN ACM AND BLEED SOURCE LINES REPLACED 3 BLEED SOURCE CHECK VALVES, OPS CHECKED PRESSURIZATION CONTROL SYSTEMS.

Part: COMPUTER — WARNING LIGHT (NR 2 ENGINE)

NR 2 ENGINE COMPUTER LIGHT ILLUMINATED IN FLIGHT.

Part: MONOPOLE — FAILED (ZONE 400)

NR 2 ENGINE COMPUTER LIGHT ILLUMINATED IN FLIGHT. FOUND MONOPOLE FAILED.

Part: ENGINE — FAILED (LEFT)

SOON AFTER TAKEOFF, A NOISE WAS HEARD AND THERE WAS AN IMMEDIATE SPOOLDOWN OF THE LEFT ENGINE. A RETURN WAS EXECUTED AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. THE ENGINE IS CURRENTLY BEING REMOVED FROM THE AIRCRAFT AND WILL BE SHIPPED TO MFG FOR EVALUATION AND REPAIR. MFG TECH THAT HAVE EXAMINED THE ENGINE EXTERNALLY SUSPECT THE FAILURE OF A TURBINE BLADE. (K)