- Registered owner
- Ryan Air Inc
- Location
- Anchorage, AK
- Owner type
- Corporation
- Serial number
- 174
- Type
- Fixed wing multi engine
- Engine
- Turbo-prop
- Certificate issued
- July 17, 2006
- Expires
- April 30, 2028
- Mode S code
- A54C15
From the FAA registry file of October 24, 2026.
On this page
Airworthiness directives that may apply · 44
Matched by this aircraft’s airframe and engine models. Each AD’s applicability may narrow it by serial number, part number or equipment.
| 1983 | 1 |
|---|---|
| 1984 | 2 |
| 1986 | 1 |
| 1987 | 7 |
| 1988 | 1 |
| 1989 | 6 |
| 1991 | 1 |
| 1992 | 1 |
| 1996 | 3 |
| 1997 | 2 |
| 1998 | 5 |
| 1999 | 2 |
| 2004 | 1 |
| 2005 | 1 |
| 2006 | 2 |
| 2007 | 1 |
| 2008 | 1 |
| 2009 | 2 |
| 2014 | 1 |
| 2015 | 1 |
| 2017 | 2 |
| 2018 | 1 |
| 2020 | 1 |
| 2021 | 1 |
| 2022 | 1 |
Airframe · Construcciones Aeronauticas C-212-CC
AD 2022-17-06FuselageAD 2020-03-18Flight ControlsAD 2018-19-02Flight controlsInformation bulletins that may apply
Advisory, not mandatory.
No bulletins matched this aircraft’s models
NTSB investigations · 1
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
FAA incident reports · 1
FAA accident and incident reports matched to this aircraft by N-number and event date, checked against the reported make and model.
Service difficulty reports · 12
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.
SDR UATA2026072835701Hinge Fitting · corrodedRT & LT INNER FLAP, OTBD PYLON, OTBD HINGE FITTINGS FOUND CORRODED. APPROXIMATE WS 2900. REMOVED DAMAGED FITTINGS. COPIED EXISTING RIVET PATTERNS AND HOLE SIZE TO NEW FITTINGS. 5 RIVETS IN LT PYLON FITTING INSTALLATION OVERSIZED BY 1 SIZE FOR HOLE DAMAGE OR INSDR UATA202603275702Skin · crackedRIGHT WING HAS CRACK ON TRAILING EDGE UNDERSIDE ABOVE OUTBOARD FLAP ASSEMBLY AT WS5000 AS MARKED. REPAIRED CRACKED SECTION OF RH FLAP COVE SKIN. SEE 337 DATED 3/20/2026. REMOVED 75MM X 25MM SECTION FROM INBOARD CRACKED AREA AND 90MM X 25MM SECTION FROM OUTBOARSDR UATA1740327265701Skin · crackedRH WING HAS CRACK ON TRAILING EDGE UNDERSIDE ABOVE OUTBOARD FLAP ASSEMBLY AT WS4800 AS MARKED. REPAIRED CRACKED SECTION OF RT FLAP COVE SKIN. REMOVED 75MM X 25MM SECTION FROM INBOARD CRACKED AREA AND 90MM X 25MM SECTION FROM OUTBOARD CRACKED AREA. REMOVED RIVSDR UATA202603275304Channel · wornWEAR MARK ON C CHANNEL SECTION BETWEEN L/H FRAMES 17-20. R&R WITH P/N: 212-23201-03-1 IRW CASA 212 SRM SECTION IV FIGURE 4.28 PAGES 0A-02 & INSTALLED WITH FASTENERS AN470E5, AN470E6, AN426E4, AN426E5, HL18-5, HL18-6, HL70-5, & HL70-6. IRW AC-43.13-1 B SECTION SDR UATA1740327265303Doubler · crackedREPAIR DOUBLER AT LOWER END OF FRAME 19 CRACKED (LH SIDE). REPLACED DOUBLER SEE 337 DATED 3/18/2026. CRACK FOUND AT DOUBLER FOR L/H FRAME 19. R&R WITH 2 DOUBLERS (ONE FWD AND ONE AFT OF FRAME) WITH .032IN 2024 T-3 ALUMINUM IRW CASA 212 SRM SECTION IV FIG 4.28 SDR UATA1740327265301Gusset · corrodedRH SIDE FR 6 & FR 11 FLOOR SUPPORT GUSSETS NUT PLATES CORRODED. REPLACED F6/F11 JUNCTION BARS. FOUND 4 FUSELAGE JUNCTION FITTINGS CORRODED ON RH AT FRAME 6 & 11 UNDERFLOOR. FOUND RH WALL SEAT RAIL MIDDLE SECTION CORRODED. F6 &
ALL NEW PARTS ACID ETCHED, ALODSDR UATA1740327265302Seat Track · corrodedRH SIDE WALL SEAT RAIL IS CORRODED AT FRAME 5F. REPLACED RH WALL MIDDLE SEAT RAIL SECTION. RH WALL SEAT RAIL SECTION. REMOVED SEAT RAIL. FABRICATED NEW SEAT RAIL FROM 206196-1 :2024-T3511 SEAT RAIL STOCK TO SAME DIMENSIONS AS PREVIOUSLY INSTALLED. INSTALLED SESDR UATA202408024531Fairing · crackedTHE FUSELAGE TO WING FILLET FAIRING, WHERE IT WRAPS AROUND THE FUSELAGE TO ATTACH AT FRAME 5 WAS FOUND CRACKED. THIS IS THE THIRD AIRCRAFT IN OUR FLEET THIS YEAR WITH A SIMILAR CRACK. THERE IS AN AD NOTE ON THE FRAME 5 AND FUSELAGE SKIN CRACKING IN THIS AREASDR UATA202005155301Frame · buckledUPON SCHEDULED UNDERFLOOR INSPECTION, FOUND FRAME 16F RIB WEBBING AT BL 0.0 SLIGHTLY BUCKLED OR DEFORMED. A DOUBLER WAS FABRICATED, USING 2024 T3 MATERIAL OF 0.040" THICKNESS, APPROXIMATELY 39.5" LONG BY 3.75" WIDE. DOUBLER WAS INSTALLED USING UNIVERSAL MS2047SDR UATA202005165301Frame · buckledUPON SCHEDULED INSPECTION FOUND FRAME 14F SLIGHTLY BUCKLED. TECHNICIANS WERE ABLE TO STRAIGHTEN THE BUCKLE, AND FABRICATE A DOUBLER OF ONE GAUGE THICKER THAN ORIGINAL MATERIAL, 4.25" BY 10" IN SIZE. THE DOUBLER WAS INSTALLED USING AN470AD4 RIVETS. A FAA FORM 3SDR UATA2020040200001Floorbeam · corrodedFOUND FRAME 17 FLOOR BEAM CAP ANGLE CORRODED BETWEEN THE CENTER LINE AND RH BUTT LINE. APPROXIMATELY 29 INCHES WAS REMOVED AND REPLACED WITH A SPLICE REPAIR PER THE CASA 212 SRM FIGURE B14.SDR UATA2020040200000Support Angle · corrodedFOUND CORROSION ON A FLOOR BOARD SUPPORT ANGLE UNDER THE COCKPIT FLOOR. ANGLES AT FRAME 5 AND NEAR FRAME 6B WERE SEVERELY CORRODED UNDER NUT PLATES. CORRODED AREAS OF ANGLE WAS REMOVED AND SPLICE REPAIRS WERE MADE PER CASA 212 SRM, FIGURE B14.
STCs that may be installed · 66
Approved for this aircraft’s airframe or engine model. The registry doesn’t record which STCs an aircraft has; its records do.