N348CA

Part: HINGE — CRACKED (ZONE 500) · airframe 29,466 hrs · 34,565 cycles

LH AILERON CENTER HINGE STRUCTURE, A PREVIOUS REPAIR PATCH IS CRACKED. REPAIR WAS ACCOMPLISHED AS FOLLOWS: REMOVED THE PREVIOUS CRACKED REPAIR ANGLE. USING THE ORIGINAL ANGLE AS A PATTERN A NEW ANGLE WAS FABRICATED FROM 301 STAINLESS STEEL 0.040 THICK AND INSTALLED IN THE SAME FASHION AS THE PREVIOUS INSTALLATION USING MS20470E -4 & -5 RIVETS AS THE ORIGINAL INSTALLATION AND IAW THE CASA SRM SECTION II, AND APPENDIX II FIG. 14, TYPE II AND FIG 15 (CRACK IN BEND RADIUS AT END OF FLANGE). THE ANGLE WAS INSTALLED "WET" USING PPG, PS 890 B1/2 ADHESIVE SEALANT. PRIOR TO INSTALLATION THE ANGLE WAS PRIMED WITH DESOTO SUPER KOROPON EPOXY PRIMER. AFTER INSTALLATION THE EXPOSED PORTIONS OF THE ANGLE WERE TOP COATED WITH IMRON POLYURETHANE ENAMEL (RED-EFFECT) WHICH WAS THEN CLEAR COATED WITH IMRON 8460S. W&B NEGLIGIBLE. FAA FORM 337 SUBMITTED, DATED AUG. 13, 2025.

Part: CHANNEL — DAMAGED (ZONE 200) · airframe 29,362 hrs · 34,424 cycles

IMPACT DAMAGE FOUND IN C CHANNEL AFT OF F19. REMOVED DAMAGED C CHANNEL AND INTERCOSTALS AT F18 AND F19 THAT WERE MODIFIED TO ACCEPT A PREVIOUS REPAIR TO OLD C CHANNEL. FABRICATED NEW INTERCOSTALS FOR F18 AND F19. ALL NEW PARTS WERE ACID ETCHED, ALODINED AND PRIMED WITH 511K011 SUPER KOROPON BEFORE INSTALLATION. INSTALLED NEW INTERCOSTALS AND C CHANNEL AS REQUIRED. C CHANNEL WAS INSTALLED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT & BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 29,259 hrs · 32,241 cycles

CORROSION FOUND ON LOWER SURFACE OF LH WING AT W.S. 3450. REMOVED BRACE STRUT AT APPROXIMATE W.S. 3200 AND SPLICE PLATE AT APPROX. W.S. 3060 FOR ACCESS TO REPAIR AREA. REMOVED DAMAGED SKIN, REMOVED SEALANT FROM PREVIOUS INSTALLATION. FABRICATED NEW SKIN FROM 0.063" 2024T3 ALCLAD TO SAME DIMENSIONS AS ORIGINAL INSTALLATION. NEW SKIN WAS ACID ETCHED AND ALODINED, THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED NEW SKIN AND SERVICEABLE SPLICE PLATE WET USING PS890B1/2 SEALANT. USED MS20470E AND MS20426E RIVETS, HL18PB, HL19PB, AND HL62PB PINS AS REQUIRED FOR INSTALLATION. REINSTALLED BRACE STRUT USING HL18PB, HL62PB, AND HL218PB PINS AS REQUIRED. TOP COATED EXTERIOR REPAIR AREA WITH IMRON ELITE RED CORAL EFFECT, BRYCE OBSIDIAN BLACK, AND CLEAR COAT TO MATCH EXISTING PAINT PATTERN. MATERIALS USED, RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION AND C212-200 SRM SECTION 2 FIG. 2.27 AND AC43.13 1B 4.57E. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURER'S INSPECTION PROGRAM. W&B CHANGE CONSIDERED NEGLIGIBLE.

Part: STIFFENER — CRACKED (ZONE 500) · airframe 29,259 hrs · 34,241 cycles

CRACKED U CHANNEL IN AFT LH CENTER WING SECTION STATION 2380, AS FLAGGED. REPLACED CRACKED STIFFENER WITH NEW. SEE 337 DATED 03/11/2025 FOR FURTHER INFO. FAA FORM 337 STATES: FOUND CRACK IN STIFFENER ON THE LEFT CENTER WING AFT BEAM AT W.S. 2380. CRACKED STIFFENER WAS REMOVED AND REPLACED WITH NEW, FABRICATED STIFFENER MADE FROM 2024-T3 ALUMINUM, 0.032" THICK TO SAME DIMENSIONS AS PREVIOUSLY INSTALLED. REPLACEMENT STIFFENER WAS ALODINED, THEN PRIMED WITH SUPER KOROPON 511K011 AND INSTALLED USING MS20470AD RIVETS AND CR3213 BLIND FASTENERS. ALL WORK WAS PERFORMED WITH REFERENCE TO CASA 212 SRM SECTION II FIG 2.38. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM.

Part: SKIN — CRACKED (ZONE 200) · airframe 28,379 hrs · 32,825 cycles

WHILE INSPECTING THE AIRFRAME PER AD2022-17-06, AOT C212-53-0001 AND SB212-53-0055, A CRACK OF 0.5" WAS FOUND ON THE FUSELAGE SKIN IN THE AREA OUTLINED TO BE INSPECTED BY THE AOT. THE OEM HAS BEEN CONTACTED, THE SITUATION REPORTED, AND A REPAIR SCHEME WAS PROVIDED IN THE FORM OF AN EA AND RDAS.

Part: SKIN — CORRODED (ZONE 600) · airframe 28,174 hrs · 32,485 cycles

DURING MAINTENANCE, SEVERE CORROSION WAS FOUND IN THE UPPER SKIN OF THE R/H WING BETWEEN STA. 2380 AND STA. 2900, CENTERED OVER STRINGER #1. UNDER THE ENGINE NACELLE FAIRING/SCALLOP.

Part: FAIRING — LOOSE (ZONE 500) · airframe 27,802 hrs · 31,850 cycles

UPON SCHEDULED MAINTENANCE INSPECTION, FOUND FIBERGLASS FLAP HINGE FAIRING LOOSENED, AND SUBSEQUENTLY CHAFED THE FLAP ATTACH PYLON BEYOND LIMITS.

Part: ATTACH FITTING — CRACKED (ZONE 600) · airframe 26,927 hrs · 30,531 cycles

DURING SCHEDULED MAINTENANCE, FOUND A CRACK IN THE R/H WING LOWER OUTBOARD ATTACH FITTING USING X-RAY METHOD.

Part: ATTACH FITTING — DISLODGED (CARGO RAMP) · airframe 24,430 hrs · 26,378 cycles

LH UPPER ATTACH FITTING FOR THE CARGO RAMP ACTUATOR WAS DISLODGED, SHEARING FASTENERS. REPAIRED ATTACHMENT PER SRM.

Part: ATTACH BRACKET — CRACKED (RT AILERON) · airframe 21,529 hrs · 22,723 cycles

DURING 25 HOUR SERVICE CHECK FOUND RT OTBD AILERON & WING ATTACHMENT BRACKET CRACKED. TEMPORARY REPAIR ACCOMPLISHED IAW DERT 8110-3 TO ALLOW ACFT TO RELOCATE TO PERMANENT MAINTENANCE BASE WHERE FINAL REPAIR CAN TAKE PLACE. FORM 337 FILED & SENT TO FAA FOR TEMPORARY REPAIR.

Part: FAIRING — BROKEN (TE FLAP) · airframe 21,497 hrs · 22,713 cycles

DURING POST FLIGHT CHECK, PILOT DISCOVERED A PIECE OF BROKEN FAIRING ON LT INBD FLAP OB PYLON. FIBERGLASS FAIRING PN 212-13223.1 CHAFED A HOLE THROUGH LT INBD FLAP LE PLATE OVER TIME. REPAIRS ARE CURRENTLY IN PROCESS, SUPPLEMENTAL INFORMATION WILL BE SUBMITTED AFTER REPAIR IS COMPLETED.

Part: HINGE BRACKET — CRACKED (LT AILERON) · airframe 21,402 hrs · 22,644 cycles

DURING ROUTINE 25 HOUR INSPECTION, MAINTENANCE FOUND LT OTBD AILERON HINGE TO BE CRACKED. REMOVED & REPLACED HINGE BRACKET WITH SERVICEABLE BRACKET. MOC FLIGHT PERFORMED SATISFACTORY.

Part: WHEEL — CRACKED (LT MLG) · airframe 212,968 hrs · 22,540 cycles

DURING POST FLIGHT INSPECTION MAINTENANCE CREW FOUND LT MLG OTBD WHEEL HALF TO BE CRACKED IN FOUR PLACES, CRACK LENGTH NOT EXCEEDING .25 INCHES. ACFT WAS GROUNDED IMMEDIATELY & A NEW WHEEL & TIRE ASSEMBLY WERE INSTALLED.

Part: COUPLING — CRACKED (NR 2 NACELLE) · airframe 21,297 hrs · 22,540 cycles

DURING 400HR SCHEDULED INSPECTION MECHANIC FOUND NR 2 ENG FIRE SHIELD AUGMENTER FLANGE COUPLING ATTACHED TO FIREWALL CRACKED APPROXIMATELY 80% AROUND CIRCUMFERENCE. REMOVED & RE-INSTALLED ENG & PROPELLER TO FACILITATE REMOVAL & REPLACEMENT OF COUPLING WITH NEW. MOC FLIGHT SATISFACTORY AFTER MAINTENANCE COMPLETED. RE-INSPECTED AFTER MOC FLIGHT, NO DEFECTS NOTED.

Part: MOUNT — DEFORMED (RT ENGINE) · airframe 21,276 hrs · 22,521 cycles

DURING POST FLIGHT INSPECTION, FOUND ENG ISOLATOR MOUNT PAD TO BE DEFORMED AFTER 13.6 HOURS IN USE. THIS UNIT WAS REPLACED PREVIOUSLY ON 01/06/2013 DUE TO DE-BONDING FROM FUEL & OIL CONTAMINATION.

Part: SKIN — DENTED (FUSELAGE) · airframe 21,284 hrs · 22,529 cycles

FOUND DENT IN UPPER SKIN OF FUSELAGE DURING INSPECTION, BETWEEN FRAMES 17 & 18. REPAIRED WITH PATCH IAW SRM.

Part: COVER — DEPARTED (LT MLG) · airframe 21,270 hrs · 22,513 cycles

DURING POST FLIGHT INSPECTION, PILOT DISCOVERED THE LT MLG WHEEL AXLE BEARING COVER DEPARTED ACFT DURING TRANSIT ON PREVIOUS FLIGHT. THERE WAS NO INDICATION OF MALFUNCTION DURING FLIGHT. COVER WAS REPLACED WITH NEW FROM KIT.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 21,290 hrs · 22,531 cycles

CRACKS ON & IN THE VICINITY OF THE AFT UPPER DOOR WERE FOUND. ON 22-NOV-13 5 CRACKS WERE REPAIRED IAW THE SRM. THE ACFT WAS FLOWN UNTIL 27-NOV-13 WHEN THE DOM BECAME AWARE OF THE CRACKS, UPON READING THE E-MAIL & THEN PULLED THE ACFT OUT OF SERVICE. THIS E-MAIL WAS RESPONDED TO ON 2-DEC-13.

Part: STRINGER — CRACKED (CARGO DOOR) · airframe 21,290 hrs · 22,531 cycles

CRACKS ON & IN THE VICINITY OF THE AFT UPPER DOOR WERE FOUND. ON 22-NOV-13 5 CRACKS WERE REPAIRED IAW THE SRM. THE ACFT WAS FLOWN UNTIL 27-NOV-13 WHEN THE DOM BECAME AWARE OF THE CRACKS, UPON READING THE E-MAIL & THEN PULLED THE ACFT OUT OF SERVICE. THIS E-MAIL WAS RESPONDED TO ON 2-DEC-13.

Part: GEARBOX — INOPERATIVE (NR 2 ENGINE) · airframe 20,128 hrs · 21,206 cycles

DURING CRUISE AT FL 85, THE NR 2 ENGINE RAPIDLY STARTED TO LOSE POWER AND DISPLAYED INDICATIONS OF FAILURE. THE COPILOT AND I NOTICED A CHANGE IN ACFT AND ENGINE PERFORMANCE, VERIFIED BY ENGINE TORQUE, RPM, FUEL FLOW, EGT AND SUBSEQUENT LOSS OF OIL PRESSURE DISPLAYED ON THE ENGINE GAUGES.

Part: ENGINE — POWER LOSS (NR 2) · airframe 20,098 hrs · 21,173 cycles

DURING CLIMB, NR 2 ENGINE EGT DROPPED TO ZERO AND ENGINE LOST POWER.

Part: CONNECTOR — LOOSE (RT ENGINE) · airframe 19,651 hrs · 20,793 cycles

AFTER TAKEOFF, RT ENGINE LOST EGT INDICATION. ACFT RETURNED TO FIELD. LOOSE CONNECTOR PLUG FOUND. SAME REINSTALLED AND SYSTEM OPS CHECKED OK.

Part: FIRE LOOP — CHAFED (ZONE 400) · airframe 18,189 hrs · 19,575 cycles

RT ENGINE FIRE WARNING ILLUMINATED IN FLIGHT. MANUAL POWER REDUCTION AND VISUAL CHECK DONE, WARNING LIGHT EXTINGUISHED. NO FIRE PRESENT. FIRE DETECTION LOOP WAS FOUND CHAFFED. REPLACED DETECTION LOOP, OPS CHECK GOOD.

Part: DIODE — ARCED (INSTRUMENT LIGHT) · airframe 18,036 hrs · 19,947 cycles

PILOT REPORTED SMOKE SMELL IN THE COCKPIT. WHILE SEARCHING FOR THE CAUSE THEY FOUND THE INSTRUMENT LIGHTING CIRCUIT BREAKER POPPED. THE SMELL DISSIPATED, SO THEY CONTINUED. AFTER LANDING AT THE DESTINATION IT WAS DISCOVERED THAT A ZENER DIODE WAS INSTALLED INCORRECTLY. WHEN IT CAME LOOSE IT SHORTED OUT IN THE OVERHEAD CONTROL PANEL, UNTIL THE CIRCUIT BREAKER OPENED. NO FURTHER DEFECTS WERE NOTED. DIODE WAS REPLACED AND ALL ASSOCIATED EQUIPMENT WAS CHECKED WITH NO FURTHER PROBLEMS.

Part: ENGINE — FAILED (NR 2)

NR 2 ENGINE SHUT DOWN IN-FLIGHT DUE TO ZERO TORQUE AND DECREASING ENGINE RPM FUEL FLOW. ENGINE OIL OVER-SERVICE SUSPECTED DUE TO OIL TANK VENT VALVE OPEN.