AIR GATO ENTERPRISES, INC.

DURING TAKEOFF ROLL. PILOT SET THRUST LEVERS TO APPROXIMATELY 80 PERCENT AND COMMANDED SET POWER. PM SET TAKEOFF POWER AS ACFT COMMENCED TAKEOFF ROLL. PM/SIC CALLED 80 KTS, PF CONFIRMED 80 KTS. SHORTLY THEREAFTER, BOTH PILOTS SENSED YAW TO LEFT. PIC/PF ATTRIBUTED YAW TO CROSSWIND COMBINED WITH RECENT DISCONNECTION OF NOSE-WHEEL STEERING. SIC/PM ATTRIBUTED YAW TO PF’S APPARENT EFFORT TO AVOID APPROACHING BIRD. WHEN INCREASED RUDDER-PEDAL INPUT DID NOT PRODUCE DESIRED CORRECTION BACK TO RW CENTERLINE, PF/PIC GLANCED AT ENGINE GAUGES NOTING L ENGINE N1 DECREASING THROUGH 91% DOWN TO 86%. PIC ABORTED TAKEOFF AT APPROXIMATELY 100KTS, CALLING ABORT, REDUCING BOTH THRUST LEVERS TO IDLE, APPLYING NORMAL BRAKING AND REVERSE THRUST. PM NOTIFIED TOWER OF ABORT REPORTING ENGINE ROLL-BACK.

AT APPROX 0910(L), COMMENCED TAKEOFF ROLL. PIC/PF SET THRUST LEVERS TO APPROX 80 PERCENT AND COMMANDED SET POWER. PM/SIC CALLED 80 KTS, PF CONFIRMED 80 KTS. SHORTLY THEREAFTER, BOTH PILOTS SENSED YAW TO LT. PIC/PF ATTRIBUTED YAW TO CROSSWIND COMBINED WITH DISCONNECTION OF NLG STEERING. SIC/PM ATTRIBUTED YAW TO EFFORT TO AVOID APPROACHING BIRD. WHEN INCREASED RUDDER-PEDAL INPUT DID NOT PRODUCE DESIRED CORRECTION BACK TO RW CENTERLINE, PF/PIC GLANCED AT ENGINE GAUGES NOTING LT ENGINE N1 DECREASING THROUGH 91% DOWN TO 86%. PIC ABORTED TAKEOFF AT APPROX 100KTS. REDUCED BOTH THRUST LEVERS TO IDLE, APPLYING NORMAL BRAKING AND REVERSE THRUST. PM NOTIFIED TOWER OF ABORT REPORTING ENGINE ROLL-BACK.

RIGHT GENERATOR LIGHT ILLUMINATED DURING FINAL APPROACH. DETECTED ODOR OF SMOKE. FOUND THE VOLT REGULATOR BURNED.

DURING CRUISE FLIGHT AT 37,000FT, DOOR SEAL ANNUNCIATOR LIGHT ILLUMINATED. CABIN WAS STARTING TO CLIMB. MADE AN UNSCHEDULED LANDING. COULD NOT DUPLICATE PROBLEM. REPLACED DOOR SEAL CHECK VLV & REGULATOR AS PRECAUTIONARY MEASURES.

DURING "D" CHECK, VISUAL INSPECTION ON THE LOWER AFT FUSELAGE JOINT TO TAIL CONE AREA REVEALED CORROSION ON AFT FUSELAGE CANTED BULKHEAD AND LOWER SKIN AREA.

LEFT WING ANTI-ICE DUCT ASSEMBLY HAS CRACKS WHICH EXCEED MM SRM LIMITS. REPAIRED DUCT ASSEMBLY.

DURING D CHECK INSPECTION, THE CANTED BULKHEAD LOCATED AT FS 8154 AT THE 6 O'CLOCK POSITION HAS CORROSION THAT EXCEEDS MM SRM LIMITS. THE CAUSE OF THE PROBLEM SEEMS TO BE THE BUILDUP OF WATER ENTRAPPED AFT OF THE BULKHEAD. THE DRAIN HOLE IS LOCATED TO FAR AFT OF THE BULKHEAD TO COMPLETELY DRAIN THE AREA WHICH LEAVES APPROX 1 INCH OF RESIDUAL LEFT IN THE AREA. PERFORMED MAJOR REPAIR TO THE BULKHEAD & ADJACENT AREA. REF 337 DATED 11/30/2014 FOR DETAILS. SUBMITTED DEFICIENCY REPORT TO ENGINEERING FOR EVALUATION.

RIGHT WING ANTI-ICE DUCT ASSEMBLY HAS CRACKS WHICH EXCEED MM SRM LIMITS. REPAIRED DUCT ASSEMBLY IAW 337 DATED 11/30/2014.

DURING D-CHECK INSPECTION, THE CANTED BULKHEAD LOCATED AT FS 8154 6 O'CLOCK POSITION HAS CORROSION THE EXCEEDS MM SRM LIMITS. CAUSE OF PROBLEM SEEMS TO BE WATER ENTRAPMENT AFT OF THE BULKHEAD AND THE DRAIN HOLE LOCATED TO FAR AFT OF THE CANTED BULKHEAD TO DRAIN THE AREA.

WHILE INSPECTING THE LT AFT FUEL TANK STRUCTURE, DUE TO LIGHTENING DAMAGE EVENT, FOUND THE FOAM INSULATION WATER SOAKED, AND CAUSING SERIOUS CORROSION IN OUTER FLANGE OF AFT PRESSURE BULKHEAD AND SURROUNDING STRUCTURE. THE HOLE IN THE LT OUTER PRESSURE BULKHEAD FLANGE, WHERE HOT AIR PIPE PENETRATES FLANGE HAD SEVERE INTERGRANULAR CORROSION OCCURRING , AND AREA WAS VERY WET.