N424CA
Registered owner: E2R LLC, 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
- F15 WEB SAGGING UNDERFLOOR - REMOVED FRAME15 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.084 THICK, 38.5 INCHES LONG. STRAIGHTENED OUT THE WEB ON FRAME 15. FABRICATED A DOUBLER FROM 2024 T3, 0.032" THICK MEASURING 38.5" LONG X 3 1/4" TALL WITH A 1/4" FLANGE ALONG THE BOTTOM EDGE. ETCHED AND ALODINED THE FABRICATED PARTS AND PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED THE "T" ANGLE AND THE DOUBLER ON THE AFT SIDE OF THE WEB USING MS20470AD-4 AND MS20470AD-5 RIVETS. ALL WORK PERFORMED IAW THE CASA 212 SRM, SECTION IV FIG. 4.16 AND APPENDIX II FIG. B22 AS WELL AS AC43.13-1B, PARA. 4-57. SEE FAA FORM 337 DATED DEC. 8, 2025.
L F11 REAR UNDER FLOOR FITTING CORRODED BEYOND LIMITS, F11 & F6 UNDERFLOOR FITTING HAVE CORROSION AT NUT PLATES. F6 & F11 JUNCTION BAR FITTINGS FOUND CORRODED. JUNCTION BAR FITTINGS. REMOVED ALL JUNCTION BAR FITTINGS FROM F6 & F11. REMOVED CORROSION UNDER & AROUND FITTING TO WEB INTERFACE. FITTED NEW FITTINGS TO WEBS & DRILLED TO EXISTING HOLE PATERNS. ALL NEW PARTS ACID ETCHED, ALODINED, & PRIMED WITH 511K011 EPOXY PRIMER. INSTALLED NEW FITTINGS ON ALL MATING SURFACES, INSTALLED WITH THE FOLLOWING HARDWARE: FITTINGS R & R 212-22406-06-1 RT FWD, FR 6 & LT AFT FR 11, 212-22406-06-2 LT FWD FR 6, & RT AFT FR 11, 212-22406-07-1 LT AFT, FR 6 & RT FWD FR 11, 212-22406-07-2 RT AFT FR 6 & LT FWD FR 11.
F11 CAP CORRODED BETWEEN SEAT RAILS. FL 1 UNDERFLOOR T ANGLE CENTER CAP - REMOVED FRAME 11 CAP SPLICE SECTION. FABRICATED NEW CAP SPLICE SECTION FROM 2024T351 0.125" X 1 5/8" X 1" ALUMINUM TO SAME SIZE, DESIGN, AND HOLE PATERN AS PREVIOUSLY INSTALLED. PARTS WERE ACID ETCHED, ALODINED, AND PRIMED WITH SUPER KOROPON 5111<011 EPOXY PRIMER. INSTALLED SPLICE SECTION USING MS20470E / MS20426E RIVETS AND I-ILI 8 HI-LOCKS.
F12 BUCKLED UNDER FLOOR. F12 UNDERFLOOR T ANGLE CENTER CAP - REMOVED DAMAGED T ANGLE. FABRICATED NEW T ANGLE FROM 2024T3 .085" X 1 5/8" X 1" TO SAME SIZE, DESIGN, AND HOLE PATTERN AS PREVIOUSLY INSTALLED. FABRICATED REPAIR DOUBLER 4 1/2"X 39 1/2" ALL NEW PARTS ACID ETCHED, ALODINED, AND PRIMED WITH 511K011 EPOXY PRIMER. INSTALLED T ANGLE AND DOUBLER USING MS20470AD RIVETS. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION, CASA 212-200 SRM SECTION 4 FIG 4.12, 4.17, APPENDIX II FIG. B19, B22 ILL, AND AC43.13-1 B 4-57B(P4-16), 4-57E(P4-19), SECTION 4-60B (P4-40).
RT INBD. FLAP, THE OUTBD. PYLON AIRFRAME SIDE, BOTH OF THE HINGE PLATES HAVE PITTING CORROSION THAT IS BEYOND LIMITS. DRILLED BOTH HINGE PLATES AND THE INBD. AND OUTBD. PYLON SIDE SKINS OFF. FITTED AND INSTALLED NEW SIDE SKINS P/N 212-13202-05-1 (INBD.) AND P/N 212-13202-05-2 (OUTBD.) USING MS20470AD4 RIVETS AND MS20470E5 RIVETS IAW AC43.13-1B, SECTION 4, PARA. 4-57. INSTALLED 2 NEW HINGE PLATES P/N212-13202-24-1 (INBD.) AND P/N RA-212-13202-24-2 USING MS20470E-5 RIVETS, 2 JO-BOLTS P/N NAS1669-08 AND 3 CHERRYMAX RIVETS P/N CR3523-5, IAW THE CASA C212 STRUCTURAL REPAIR MANUAL SECTION II FIG. 2.24 AND AC43.13-1B CHAPTER 4, PARA 4-57. FORM 337 SUBMITTED, DATED JAN. 12, 2026
F16 TOP CAP CORRODED AT NUT PLATES. REMOVED FRAME 16 TOP CAP AND FABRICATED A NEW CAP FROM 2024 T351 ALUMINUM "T" ANGLE, 0.100 THICK. ETCHED AND ALODINED THE "T" ANGLE AND PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED THE "T" ANGLE USING MS20470AD-4 AND MS2470AD-5 RIVETS IAW AC43.13-1B, PARA. 4-57.
LOWER WING SKIN SECTION @ WING STATION 2800 UNDER FLAP PYLON WAS FOUND TO HAVE SEVERE PITTING CORROSION. FABRICATED NEW SKIN AS PER ORIGINAL, AND REPLACED PER AC43.13-1B, PAR 4-53, 4-55, 4-57 AND CASA 212 SRM SECT. II, FIG 2.26
INSPECTION FOUND A BENT AND CRACKED STRINGER BETWEEN FR18 AND FR19 ON R/H SIDE. POSSIBLE CAUSE SEEMS TO BE LOADING DAMAGE CAUSED BY CARELESS LOADING AND UNLOADING.
FOUND INTERGRANULAR CORROSION WHERE NUT PLATES WERE ATTACHED ON THE BOTTOM OF THE CAP STRIP OF FLOOR FRAME #11. SPLICED IN A NEW SECTION OF FRAME CAP PER CASA SRM.
FOUND HOLE IN BELLY SKIN BETWEEN FRAME 2/F AND 3F. CLEANED HOLE TO 1/2 INCH ROUND AND INSTALLED A FLUSH PLUG PATCH PER CASA 212 SRM.
IN COMPLYING WITH AD98-12-28, FOUND ONE FALSE SPAR PROFILE TO BE CRACKED. REPLACED PROFILE WITH A NEW FABRICATED PROFILE.
FOUND A CRACK IN AN INTERCOSTAL AT FRAME 19 RH BOTTOM, FORWARD OF RAMP ACTUATOR. REPAIRED PER SRM.
UPPER LH CARGO DOOR HINGE BRACKET AT FRAME 27 IS CRACKED. REPLACED HINGE BRACKET WITH NEW.
#1 ENGINE FORWARD COWL SUPPORT BRACKET IS CRACKED IN THE 12:00 POSITION. FABRICATED A NEW BRACKET PER AC43.13-1B, SECTION 4
COPILOT'S OUTBOARD FWD AILERON CABLE IS FRAYED WITH BROKEN STRANDS. REPLACED CABLE WITH NEW.
PILOTS OUTBOARD FORWARD AILERON CABLE FRAYED WITH BROKEN STRANDS. REPLACED CABLE WITH NEW.
PILOTS FWD ELEVATOR UP CABLE IS FRAYED WITH BROKEN STRANDS. REPLACED CABLE ASSEMBLY WITH NEW.
LH ELEVATOR SHAFT QUADRANT SUPPORT ASSEMBLY HAD CORROSION IN BOTH LOWER ATTACHMENT FEET. REPLACED SUPPORT ASSEMBLY WITH A NEW UNIT.
LH OUTBOARD WING LEADING EDGE HAS A CRACKED NOSE RIB A WING STATION 8160 AND CRACKS IN THE SKIN. REPAIRED PER SRM.
COPILOT'S FWD INBOARD AILERON CABLE FRAYED WITH BROKEN STRANDS. REPLACED CABLE WITH NEW.
PILOT'S SIDE FORWARD INBOARD AILERON CABLE FRAYED. REPLACED CABLE ASSEMBLY WITH NEW.
FOUND RUDDER CABLE FRAYED WITH BROKEN STRANDS. REPLACED CABLE ASSEMBLY WITH NEW.
FOUND RH FWD RUDDER CABLE FRAYED WITH BROKEN STRANDS. REPLACED CABLE WITH NEW.
ELEVATOR TRIM STOPS FOUND DAMAGED. ONE STOP BENT AND ANOTHER BROKEN IN HALF.
CORROSION / EROSION ON CENTER WING LOWER AFT SKIN PANEL IN THE AREA OF THE EXHAUST TRAILS OF THE LEFT AND RIGHT ENGINES FROM APPROX CWS 2230MM TO 3070MM LEFT AND RIGHT. REPAIRED REF CASA TECHNICAL INSTRUCTION LETTER 17 REV 1.
FLIGHT CREW DESCRIBED THAT THE OXYGEN SYSTEM EMPTIED TO QUICKLY. UPON FURTHER INSPECTION, DETERMINED THAT THE PRESSURE REGULATOR WAS LEAKING UNDER THE CAP / KNOB USED TO TURN THE REGULATOR ON AND OFF. THIS AREA WAS UNABLE TO GAIN ACCESS USING LEAK DETECTION FLUID.
THE PURPOSE OF THE TWO EXTINGUISHING VALVES IS TO LEAD BY MEANS OF ITS COORDINATE ACTION, THE DISCHARGE OF EXTINGUISHING AGENT TOWARDS THE DESIRED ENGINE. NR 1 ENG VALVE DISK WAS FROZEN ON SHAFT. NR 2 ENG VALVE DISK WAS PREVENTED FROM SEATING DUE MILD CORROSION. RECOMMEND: FREQ BE CHANGED FROM EVERY 6 YEARS TO 1 YEAR FOR FUNCTIONAL TEST OF SYSTEM.
CORROSION FOUND ON C-212 51D AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.
CORROSION FOUND ON C-212 5ID AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.
CORROSION FOUND ON C-212 51D AT BEARING AREA. BEARING MATERIAL IS DISSIMILAR. SUBMITTER STATED THAT POSSIBLY A BEARING WAS INSTALLED DRY AT INSTALLATION BY MFG. OPERATORS SHOULD PERFORM CLOSE INSPECTION AT 1,600 FLIGHTS.