N1331C
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
LEFT ENGINE OIL TEMPERATURE INCREASED TO REDLINE, PERFORMED PRECAUTIONARY SHUTDOWN. REMOVED AND REPLACED #1 OIL COOLER REF CASA MM 79-20-00 LEAK CHECK GOOD.
RH SEAT RAIL LONGITUDINAL WEB CRUSHED AT F17. REPAIRED IAW C212 SRM B26. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED SECTION OF WEB ~4.5 X 9". FABRICATED REPLACEMENT WEB SECTION TO SAME DIMENSIONS AS REMOVED FROM 2024T3 0.025", AND SPLICE PLATE 9.75" X 2.25" FROM 2024T3 0.025". ACID ETCHED AND ALODINED THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED REPLACEMENT WEB AND SPLICE PLATE USING MS20470AD AND MS20470E5 RIVETS AS REQUIRED PER ORIGINAL INSTALLATION AND REPAIR SPECIFICATIONS.
LH SEAT RAIL LONGITUDINAL WEB CRUSHED AT F17. REPAIRED IAW C212 SRM B26. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED SECTION OF WEB ~ 5.5" X 9.5". FABRICATED REPLACEMENT WEB SECTION TO SAME DIMENSIONS AS REMOVED FROM 2024T3 0.025", AND SPLICE PLATE 9.75" X 2.25" FROM 2024T3 0.025". ACID ETCHED AND ALODINED THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. INSTALLED REPLACEMENT WEB AND SPLICE PLATE USING MS20470AD4 AND MS2470E5 RIVETS AS REQUIRED PER ORIGINAL INSTALLATION AND REPAIR SPECIFICATIONS.
FOUND A SMALL PUNCTURE IN THE AFT SIDE OF THE RH WEB OF FRAME 11, 2 INCHES ABOVE FLOOR LEVEL. REPAIRED PER CASA ENGINEERING DOC 252EA-00020 REV A. SEE 337 DATED 02/10/2025 FOR FURTHER DETAIL. REMOVED DAMAGED MATERIAL. DAMAGED AREA INSPECTED BY HFEC, NO INDICATIONS OF CRACKING FOUND, SEE AIX REPORT NUMBER 11504 FOR FURTHER INFORMATION. PRIMED UNFINISHED PORTION OF REPAIR AREA WITH SUPER KOROPON. FABRICATED REPAIR DOUBLER FROM 2024T3 0.080" TO FIT IN REPAIR AREA. ACID ETCHED, ALODINED AND PRIMED REPAIR DOUBLER WITH SUPER KOROPON. INSTALLED REPAIR DOUBLER WITH PS890B1/2 BETWEEN SHEETS USING MS20470E5 RIVETS AND HL18PB PINS AS NECESSARY.
WHILE INSPECTING THE AIRFRAME PER AD2022-17-06, AOT C212-53-0001 AND SB212-53-0055, A CRACK OF 0.070" WAS FOUND ON THE FUSELAGE SKIN IN THE AREA OUTLINED TO BE INSPECTED BY THE AOT. THE OEM HAS BEEN CONTACTED, HE SITUATION REPORTED, AND A REPAIR SCHEME REQUESTED. THE OEM REPLIED WITH A SATISFACTORY EA AND RDAS.
A FORKLIFT LOADING THE AIRCRAFT SLIPPED ON ICE, AND HIT THE AFT UPPER CARGO DOOR AS WELL AS THE AIRCRAFT STRUCTURE DIRECTLY AFT OF THE DOOR, CAUSING GOUGING, AS WELL AS BUCKLING OF THE ASSOCIATED FRAMES. DAMAGE WAS REPAIRED IAW THE SRM, AND A FAA FORM 337 WAS FILLED OUT, SIGNED AND FORWARDED AS REQUIRED.
ON T/O ROLL OUT OF OOK AT V1 SPEED, #1 ENGINE BETA LIGHT CAME ON. PILOTS ELECTED TO TAKE OFF. TORQUE DROPPED 40%, AND PROPELLER SPEED INCREASED ON THE SAME ENGINE. #1 ENGINE FEATHERED DUE TO DRAG AND OVERSPEED OF THE PROP. ENGINE WAS DOWN TO 20%TQ, AND NP PEAKED AT 103.7% MOMENTARILY. AIRCRAFT CONTINUED TO BET, WHERE IT LANDED WITHOUT INCIDENT. UPON TROUBLESHOOTING, MAINTENANCE FOUND THE #1 PROPELLER GOVERNOR TO BE INOPERATIVE. REMOVED AND REPLACED AND OPS TESTED SATISFACTORILY.
INTERGRANULAR CORROSION FOUND ON UPPER FLOOR BEAM "T" CAP ANGLE AT FRAME 1F. THE SECTION OF EXTRUDED T-ANGLE WAS CUT, REMOVED AND REPLACED WITH A PIECE OF 2024T3511 OF SIMILAR SIZE AND LENGTH. IT WAS ETCHED, ALODINED AND PAINTED AS REQUIRED, AND INSTALLED USING MS20470E5 RIVETS AND HL21PB5 HI-LOKS. ALL WORK WAS CARRIED OUT REFERENCING THE CASA 212-200 SRM SECTION IV, FIG 4.13 & APPX II FIG B3 & B19.
NR 1 AND 2 ENGINE AFT SIDE OF FIREWALL LOWER DOUBLERS FOUND CRACKED NEAR OUTER EDGE OF BOTH LEFT AND RIGHT LOWER MOUNT FITTINGS. REPAIRED BOTH LT AND RT CRACKED DOUBLERS ON BOTH ENGINE FIREWALLS BY INSERTION OF NEW DOUBLER SECTIONS OF SIMILAR THICKNESS AND SIZE, USING MONEL RIVETS OF SIMILAR SIZE AT ALL 4 LOCATIONS, IAW CASA TECHNICAL INSTRUCTION TI212-0058 REV 00.
INTERGRANULAR CORROSION WAS FOUND ON THE RT FWD HORIZONTAL STABILIZER LOWER FWD ATTACH FITTING AROUND THE BUSHING HOLE. THE AFFECTED ATTACH FITTING WAS REMOVED AND REPLACED WITH A NEW FITTING OF THE SAME P/N, UTILIZING THE SAME TYPE ATTACHING FASTENERS. WORK CARRIED OUT, IAW CASA SB 212-53-52.
AIRFRAME SKIN CRACKED TO THE EDGE ON LT SIDE OF CENTER WING CUTOUT AT FR 5. REMOVED DAMAGE, FABRICATED A FLUSH PATCH AND DOUBLER, IAW CASA SRM APPX II FIG B9.
AIRFRAME SKIN CRACKED TO THE EDGE ON RT FWD SIDE OF CENTER WING CUTOUT AT FR 5. REMOVED DAMAGE, FABRICATED A FLUSH PATCH AND DOUBLER, IAW CASA SRM APPX II FIG B9.