N352CA
Registered owner: RYAN AIR INC, AK (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| RYAN AIR, INC. (UATA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
RH INNER FLAP, OUTBOARD PYLON, OUTBOARD SKIN CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGS (PIN: 212-13202-24-1 AND 212-13202-24-2) AND NEW SKIN (PIN: 212-13202-05-2). ALL PARTS AND BARE SURFACES PRIMED WITH SUPER KOROPON EPOXY PRIMER PRIOR TO INSTALLATION. INSTALLED NEW SKIN AND FITTINGS USING MS20470E RIVETS AND NASI 669 FASTENERS. TOP COATED SURFACES WITH IMRON ELITE BC TO MATCH COMPANY PAINT SCHEME. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION 2 FIG. 2.39 AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
RH INBOARD FLAP, OUTBOARD PYLON BOTH FLAP HINGE PLATES CORRODED. RH INNER FLAP, OUTBOARD PYLON, HINGE FITTINGS AND OUTBOARD SKIN FOUND CORRODED. APPROXIMATE WING STATION 2900. REMOVED DAMAGED FITTINGS AND SKIN. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGS (PIN: 212-13202-24-1 AND 212-13202-24-2) AND NEW SKIN (PIN: 212-13202-05-2). ALL PARTS AND BARE SURFACES PRIMED WITH SUPER KOROPON EPOXY PRIMER PRIOR TO INSTALLATION. INSTALLED NEW SKIN AND FITTINGS USING MS20470E RIVETS AND NASI 669 FASTENERS. TOP COATED SURFACES WITH IMRON ELITE BC TO MATCH COMPANY PAINT SCHEME. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION 2 FIG. 2.39 AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
FOUND CRACK IN RH WING TO FUSELAGE FAIRING AT FRAME F5. (SEE AOT-C212-53-0001 FOR DETAILS). REPAIRED CRACK DAMAGE AND REINFORCED F5 RH BY INSTALLATION OF SB KIT SB212530055K01. SEE 337 DATED 09/25/2025. FOR FURTHER DETAILS.
LOWER LH SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.
FRAME 19 RH CRACKED BEHIND ACTUATOR ATTACH POINT. REMOVED THE OLD REINFORCEMENT DOUBLER REPAIR. FABRICATED A NEW DOUBLER FROM 2024 T3 ALCLAD ALUMINUM 0.050 THICK, 6 INCHES TALLER THAN THE PREVIOUS DOUBLER (10 INCHES TOTAL). ETCHED AND ALODINE THE DOUBLER AND PRIMED WITH EPOXY PRIMER.
FRAME 19 CRACKED BEHIND LH ACTUATOR ATTACH POINT. FABRICATED AND INSTALLED NEW LOWER FRAME 19 AND ACTUATOR ATTACH POINT DOUBLER. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL
LOWER CARGO DOOR CUTOUT FRAME, LH SIDE "C" CHANNEL HAS A CRACK IN THE UPPER FLANGE JUST AFT OF FRAME 19. INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CRACK.. SEE FORM 337 FOR DETAILS OF THE REPAIR.
LOWER CARGO DOOR CUTOUT FRAME, RH SIDE "C" CHANNEL HAS 2 CHAFE MARKS IN THE UPPER RADIUS, JUST FWD. OF FRAME 19. BLENDED CHAFFED AREAS AND INSTALLED AN INTERNAL REINFORCING DOUBLER BEHIND THE CHAFFED AREAS. SEE FORM 337 FOR DETAILS OF THE REPAIR.
UNDER SIDE OF THE UPPER "T" FLANGE AT FRAME 11, THERE IS EXFOLIATION CORROSION UNDER THREE DIFFERENT NUT PLATES (CENTER AREA). REMOVED A 21 INCH SECTION OF THE CENTER "T" FLANGE BETWEEN THE TWO FLOOR SEAT TRACKS. FABRICATED A NEW LENGTH OF "T" FLANGE FROM THE SAME MATERIAL, 2024 T3511, 0.110 THICK ALUMINUM AND SPLICED IN THIS SECTION USING 4 (APPROXIMATELY 10 INCH LONG) 90 DEGREE EXTRUDED DOUBLER ANGLES TO BED INTO ENDS OF "T" SECTION FROM 2024 T3511 ALUMINUM OF 0.130 THICKNESS. ETCHED AND ALODINE ALL THE NEW PARTS, THEN PRIMED WITH SUPPER KOROPON EPOXY PRIMER. INSTALL THE NEW "T" SECTION AND ANGLES USING A MINIMUM OF 8 RIVETS ON EACH SIDE OF EACH SPLICE JOINT WITH MS20470E5 AND MS20429E5 SERIES RIVETS, MS20470E4 RIVETS ON THE UN-SPLICED SECTION AND 4 HL20PB5 HI-LOCKS. THIS WAS PERFORMED IAW THE CASA SRM APPX. II FIG. B19 REPAIR SCHEME. DETAILS ALSO ON FILE ON FORM 337 DATED 9/20/2024.
RH SIDE EXTRUSION ON FWD. SIDE OF FRAME 11, UNDER FLOOR IS CRACKED. (BOUNDARY LAYER CORROSION). REPLACED EXTRUSION WITH NEW 212-22406-06-1. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.
LOWER RH SIDE SKIN BETWEEN FRAME 17 AND 18 CORRODED. REMOVED DAMAGED SKIN, FABRICATED NEW SKIN AND INSTALLED. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL
MECHANIC INDUCED DAMAGE TO FRAME 11 WEB, UNDER THE FLOOR, 5 INCHES LEFT OF CENTER. DRESSED OUT THE DAMAGED AREA & FABRICATED A DOUBLER 2 1/4 INCH BY 3 INCHES OF 2024 T3 ALUMINUM 0.040 THICK. ETCHED & ALODINED THAN PRIMED WITH SUPPER KOROPON EPOXY PRIMER. INSTALLED USING MS20470E4 AND E5 SERIES RIVETS. REPAIR WAS PERFORMED IAW THE CASA SRM, APPEX II, FIG. B25, WEB REPAIRS. FAA FORM 337 SUBMITTED, DATED 10/8/2024.
LH SIDE EXTRUSION ON AFT SIDE OF FRAME 11, UNDER FLOOR HAS EXFOLIATION CORROSION. REPLACED EXTRUSION WITH NEW 212-22406-07-2. SEE FORM 337 DATED 9/20/2024 FOR FURTHER DETAIL.
THE FIBERGLAS FAIRING ON THE FRONT OF THE OB FLAP, IB HINGE ON THE RH WING CAME LOOSE AND CHAFED INTO THE BOTTOM WING SKIN JUST FORWARD OF THE FLAP HINGE. AIRBUS ENGINEERING WAS CONTACTED WITH THE DAMAGE SPECIFICATIONS AND THEY ISSUED REPAIR INSTRUCTIONS UNDER ENGINEERING AUTHORIZATION NUMBER (EA #): 24E3EA-00155 WITH REPAIR AND ENGINEERING SOLUTION APPROVAL FORM (RESAF) NUMBER AND ISSUE: RESAF-C212-57-240009-100. THE AIRCRAFT WAS REPAIRED PER THE INSTRUCTIONS LISTED AND APPROVED FOR RETURN TO SERVICE.
OB FLAP, IB HINGE FWD FAIRING BECAME LOOSE AND CHAFED INTO THE BOTTOM SKIN OF THE RH WING, JUST FORWARD OF THE HINGE. THE DAMAGE SPECIFICATIONS WERE SENT TO AIRBUS ENGINEERING AND THEY PRODUCED REPAIR INSTRUCTIONS ON ENGINEERING AUTHORIZATION (EA) NUMBER 24E3EA-00155, ACCOMPANIED BY REPAIR AND ENGINEERING SOLUTION APPROVAL FORM (RESAF) NUMBER AND ISSUE: RESAF-C212-57-240009-100. THE WING BOTTOM SKIN WAS REPAIRED THE AIRBUS EA INSTRUCTIONS AND THE PLANE APPROVED FOR RETURN TO SERVICE.
WHILE INSPECTING THE AIRFRAME PER AD2022-17-06, AOT C212-53-0001 AND SB212-53-0055, A CRACK OF 0.719" 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 REQUESTED.
L/H ELEVATOR LOWER AFT ATTACH FITTING ON FUSELAGE FOUND CRACKED AFTER ROUTINE NDI INSPECTION COMPLIED WITH. FITTING R&R PER SB212-53-52.
UPON SCHEDULED INSPECTION, FOUND L/H EXHAUST DUCT SHROUD/HEAT SHIELD CRACKED AT THE O/B AFT END. THE CRACK WAS APPROXIMATELY 6" LONG, AND RAN ALONG A ROW OF RIVETS IN A FORWARD DIRECTION.
FRAME 6 FLOOR BEAM HAS HEAVY MILLED GUSSETS THAT TIE THE FRAME 6 FLOOR BEAM TO THE FRAME 6 SIDE WALL, BOTH FWD AND AFT OF THE BEAM, ON THE LH AND RH SIDES OF THE BEAM. THERE ARE NUT PLATES CLOSE TO THE ENDS OF THE GUSSETS, AND CORROSION WAS FOUND IN THE GUSSETS WHERE THE NUT PLATE ATTACHED. THE RH SIDE GUSSETS WERE WITHIN OEM ACCEPTABLE LIMITS, BUT THE LH SIDE GUSSETS HAD CORROSION BEYOND THE OEM LIMITS. THE OEM ENGINEERED A REPAIR SCHEME FOR THE CORRODED LOCATIONS, WHICH WAS ACCOMPLISHED.
FOUND DEEP CORROSION IN CENTER OF FRAME 11 FLOOR BEAM, APPROXIMATELY 3 INCHES LONG AND 5/8 INCH WIDE. ROUTED OUT CORRODED AREA AND INSTALLED DOUBLER PER OEM SRM.
APPROXIMATELY 23 INCHES OF FRAME 17F FLOOR BEAM CAP WAS CORRODED ON TOP. REMOVED SECTION OF BEAM CAP AND SPLICED IN WITH SIMILAR CAP MATERIAL. SPLICE WAS MADE PER OEM SRM.
FOUND CORROSION ON THE UPPER SIDE OF FLOOR FRAME 11F IN CENTER OF BEAM. ROUTED OUT CORRODED AREA AND INSTALLED A DOUBLER, .010 THICKER THAN ORIGINAL MATERIAL
INSPECTION OF THE SLIPPAGE WITNESS STRIPE SHOWED THAT ONE BLADE OF THE PROPELLER SLIPPED ROTATIONALLY IN THE BLADE TO HUB CLAMP, CAUSING THE
FOUND RT FWD UP ELEVATOR CABLE (OUTBOARD) HAS MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.
FOUND LT FWD UP ELEVATOR CABLE (OUTBOARD) TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.
FOUND LH FORWARD RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH NEW.
FOUND RH FWD PRIMARY RUDDER CABLE TO HAVE MULTIPLE BROKEN STRANDS. REPLACED CABLE WITH A NEW CABLE.
DURING A CORROSION PREVENTION & CONTROL PROGRAM INSPECTION, HEAVY CORROSION WAS FOUND ON THE UPPER INBOARD ATTACH ANGLE OF THE LH WING INBOARD FLAP PYLON.
WHILE LANDING, NOSE GEAR HAD EXTREME VIBRATION CAUSING TORQUE ARM PINS TO POP OUT AND DAMAGING THE BUSHINGS.
STARTER GENERATOR FAILED TO OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE ADAPTER HAD STRIPPED OUT ON THE INTERNAL THREADS.
STARTER GENERATOR FAILED TO TURN OVER THE ENGINE ON COMMAND. INVESTIGATION REVEALED THE PLASTIC SPLINE HAD STRIPPED OUT ON THE INTERNAL THREADS.