N440RA
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 |
| Arctic Transportation Services, Inc. | Operator | on 2009-02-14 | Operator named in NTSB report |
Accident & incident history
Operated by ARCTIC TRANSPORTATION SERVICES INC (per NTSB report)
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
12 reports on file, 2020-04-01 – 2026-07-23.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 44,805 hrs · 64,349 cycles
RT & 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 INSTALLATION OF BLIND FASTENERS. ALL PARTS AND BARE SURFACES PRIMED PRIOR TO INSTALLATION. INSTALLED NEW FITTINGS. TOP COATED SURFACES TO MATCH COMPANY PAINT. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURER'S INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
Part: SKIN — CRACKED (ZONE 600) · airframe 44,605 hrs · 64,106 cycles
RIGHT 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 OUTBOARD CRACKED AREA. REMOVED RIVETS AS REQUIRED FROM UPPER FLAP COVE SKIN FOR ACCESS TO REPAIR AREA. FABRICATED FOR OUTER SECTION FROM 2024T3 ALUMINUM 90MM X 25MM X 0.025" FILLER PLATE AND 50MM X 160MM X 0.025" REPAIR PLATE. FABRICATED FOR INBOARD SECTION FROM 2024T3 ALUMINUM 75MM X 25MM X 0.025" FILLER PLATE AND 140MM X 50MM X 0.025 REPAIR PLATE. PLATES AND FILLERS FIT AND DRILLED TO REPAIR AREAS, ALL HOLES DIMPLED TO CLEARANCE REPAIR FROM FLAPS. ALL REPAIR PIECES ACID ETCHED, ALODINED, AND PRIMED WITH EPOXY PRIMER. INSTALLED REPAIR PLATES W/ MS20426AD RIVETS. REINSTALLED TOP COVE SKIN RIVETS PREVIOUSLY REMOVED WITH MS20426AD, AND CR3212 RIVETS AS REQUIRED FROM PREVIOUS INSTALLATION. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212-200 SRM SECTION II FIG. 2.5 POS. 61 , APPENDIX II FIG. B9, AC43.13-1B 4.57F3 (P:4-19) AND PREVIOUS INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
Part: SKIN — CRACKED (ZONE 600) · airframe 44,605 hrs · 64,106 cycles
RH 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 RIVETS AS REQUIRED FROM UPPER FLAP COVE SKIN FOR ACCESS TO REPAIR AREA. FABRICATED FOR OUTER SECTION, FILLER PLATE AND REPAIR PLATE. FABRICATED FOR INBOARD SECTION, FILLER PLATE AND REPAIR PLATE. PLATES AND FILLERS FIT AND DRILLED TO REPAIR AREAS, ALL HOLES DIMPLED TO CLEARANCE REPAIR FROM FLAPS. ALL REPAIR PIECES ACID ETCHED, ALODINED, AND PRIMED WITH EPOXY PRIMER. INSTALLED REPAIR PLATES W/ MS20426AD RIVETS. REINSTALLED TOP COVE SKIN RIVETS PREVIOUSLY REMOVED WITH MS20426AD, AND CR3212 RIVETS AS REQUIRED FROM PREVIOUS INSTALLATION.
Part: DOUBLER — CRACKED (ZONE 100) · airframe 44,605 hrs · 64,106 cycles
REPAIR 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 PAGES OA-02 AND CASA 212 SRM APPENDIX II REPAIRS B14 (PAGES 26-27), B15 (PAGES 28-29) AND B22 (PAGES 44-45). INSTALLED WITH AN470AD4 RIVETS IRW AC-43.13-1 B SECTION 4-57 PAGES 4-14 TO 4-17, USED PRE-EXISTING REPAIR'S RIVET SPACING & SIZE. DOUBLERS WERE ALODINED, PRIMED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR A/C MANUFACTURERS INSPECTION PROGRAM. W&B CHANGE WAS CONSIDERED NEGLIGIBLE.
Part: CHANNEL — WORN (ZONE 100) · airframe 44,605 hrs · 64,106 cycles
WEAR 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 4-57 PAGES 4-14 TO 4-17 & SECTION 4-57 PARAGRAPH E PAGES 4-19. USED PREVIOUS C-CHANNEL'S EXISTING HOLES FOR RIVET SPACING & SIZE. NEW C-CHANNEL WAS ALODINED, PRIMED, INSTALLED WET WITH PR1425 SEALANT AND PAINTED. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR A/C MANUFACTURERS INSPECTION PROGRAM.
Part: GUSSET — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,605 hrs · 64,106 cycles
RH 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, ALODINED, AND PRIMED W/ 511K011 EPOXY PRIMER. FITTINGS INSTALLED W/ THE FOLLOWING HARDWARE AS REQUIRED: HL18PB PINS, HL65PB PINS, & MS20470AD RIVETS. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, & REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION, CASA 212-200 SRM SECTION 4 FIG 4.17, & AC 43.13-1B SECTION 4-60B (P4-40), 4-57B (P4-16), 4-57E(P4-19). 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 SEAT RAIL USING CR3242 RIVETS, NAS1670 FASTENERS, & MS20426E RIVETS AS REQUIRED. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, & REPAIR CRITERIA WERE OBTAINED FROM PREVIOUS INSTALLATION. AS WELL AS AC43.13-1B 4.57B (P:4-16) 4.57F (P:4-19). CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT & BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,605 hrs · 64,106 cycles
RH 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 SEAT RAIL USING CR3242 RIVETS, NAS1670 FASTENERS, AND MS20426E RIVETS AS REQUIRED. MATERIALS USED; FASTENER TYPE, SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM PREVIOUS INSTALLATION. AS WELL AS AC43.13-1B 4.57B (P:4-16) 4.57F (P:4-19). CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
Part: FAIRING — CRACKED (ZONE 200) · airframe 43,233 hrs · 61,795 cycles
THE 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 AREA, BUT THE ONLY CRACK WAS IN THE FAIRING ON THESE THREE AIRCRAFT.
Part: FRAME — BUCKLED (FUSELAGE) · airframe 39,229 hrs · 55,240 cycles
UPON 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 MS20470 RIVETS. CRITERIA FOR ACCOMPLISHING THE REPAIR WAS FOUND IN THE CASA 212 SRM, AND A FORM 337 WAS FILED.
Part: FRAME — BUCKLED (FUSELAGE) · airframe 39,229 hrs · 55,240 cycles
UPON 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 337 WAS FILED.
Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 39,131 hrs · 55,056 cycles
FOUND 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.
Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 39,131 hrs · 55,056 cycles
FOUND 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.