N439RA
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
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.
17 reports on file, 2023-07-18 – 2026-05-06.
Part: STIFFENER — CRACKED (ZONE 500) · airframe 41,791 hrs · 68,048 cycles
FOUND A CRACK IN STIFFENER ON THE LH WING FALSE SPAR AT W.S. 4900. THE CRACKED STIFFENER WAS R&R WITH NEW, FABRICATED STIFFENER MADE FROM 2024-T3 ALUMINUM .032" THICK, THE PRE-EXISTING SPACER HAD NO DAMAGE AND WAS REUSED. THE NEW STIFFENER WAS PRIMED WITH SUPER KOROPON BAC452 DESOTO PRIMER AND INSTALLED USING CR3213 BLIND FASTENERS, AND HLI 8PB HI-LOKS OF VARYING LENGTHS. ALL WORK PERFORMED WAS ACCOMPLISHED IRW CASA TL NO. 27 AND CASA SRM SECTION II, AND WAS DETERMINED TO BE AIRWORTHY. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IAW CURRENT INSPECTION PROGRAM OR AC MANUFACTURERS INSPECTION PROGRAM. WEIGHT AND BALANCE CHANGE WAS CONSIDERED NEGLIGIBLE.
Earlier reports · 2023–2025 · 16 reports
2025
Part: SKIN — CRACKED (ZONE 300) · airframe 41,484 hrs · 67,561 cycles
RIGHT HORIZONTAL STAB TOP SKIN CRACKED JUST OTBD OF AFT ATTACH FITTING HSS 740. REMOVED TOP REAR SKIN FROM STAB ROOT TO WS 1200. ELEVATOR COVE SKIN WAS DE-RIVITED TO WS 1500 FOR ACCESS. FABRICATED NEW SKIN AND PATTER AS ORIGINAL INSTALLATION. ACID ETCHED, ALODINED, & PRIMED. INSTALLED NEW SKIN ON STABILIZER. REINSTALLED ELEVATOR COVE SKIN. AFFECTED AREAS WERE PAINTED.
Part: FRAME — BUCKLED (ZONE 100) · airframe 41,286 hrs · 67,231 cycles
LH FWD FRAME OF THE LOWER RAMP OPENING (P/N 212-23201-03-1) IS BUCKLED BETWEEN FRAME 17+18. REPLACED DAMAGED C CHANNEL 212-23201-03-1 WITH NEW. SEE 337 DATED 08/13/2025 FOR FURTHER INFORMATION. IMPACT DAMAGE FOUND IN C CHANNEL 212-23201-03-1 FWD OF F18. REMOVED C CHANNEL AND INTERCOSTALS AT F18. FABRICATED NEW INTERCOSTALS FOR F18 FROM 2024T3 ALUMINUM 0.032â THICK. ALL NEW PARTS WERE ACID ETCHED , ALODINED AND PRIMED WITH 511K011 SUPER KOROPON BEFORE INSTALLATION. INSTALLED NEW INTERCOSTALS AND C CHANNEL (P/N RA-212-23201-03-1) USING MS20470AD, MS20470E, AND MS20426AD RIVETS AS REQUIRED. C CHANNEL WAS INSTALLED WITH PS890B1/2 ON ALL MATING SURFACES. FIVE RIVETS BETWEEN F17 ANDF18 WERE SUBSTITUTED WITH HL18PB PINS. MATERIALS USED, RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM C212 SRM SECTION IV FIG. 4.28, AC43.13 1B 4.57E (P4-19), AND ORIGINAL INSTALLATION. CONTINUED AIRWORTHINESS WILL BE MAINTAINED IN ACCORDANCE WITH CURRENT INSPECTION PROGRAM OR AIRCRAFT MANUFACTURERâS INSPECTION PROGRAM. W&B CONSIDERED NEGLIGIBLE.
2024
Part: PROFILE — CRACKED (ZONE 500) · airframe 40,528 hrs · 65,997 cycles
L/H OUTBOARD WING HAS ONE CRACKED PROFILE ON THE FALSE SPAR AT WING STATION 4900. REPLACED CRACKED PROFILE WITH ONE OF LOCAL MANUFACTURE.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
THE EXTRUSION ON THE FWD. SIDE OF FRAME 6 (LEFT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 LH FWD FITTING 212-22406-06-2 WITH NEW RA-212-22406-06-2 FITTING. SEE 337 DATED 07-24-2024 FOR FURTHER DETAIL.
Part: FRAME — BUCKLED (ZONE 100) · airframe 40,528 hrs · 65,997 cycles
FRAME 16 IS BUCKLED UNDER THE FLOOR JUST LEFT OF CENTER. REMOVED BUCKLED SECTION OF FRAME 16 WEB AND SPLICED IN A NEW PIECE OF MATERIAL. WORK WAS DONE REFERENCING THE CASA 212 STRUCTURAL REPAIR MANUAL APPENDIX II FIGURE B25. DETAILS OF THE REPAIR ARE AVAILABLE ON THE FORM 337.
Part: FRAME — CRACKED (ZONE 100)
ONE PROFILE AT FRAME 10 IS CRACKED AT THE TOP END AND THE FRAME IS BUCKLED (UNDER FLOOR). REPLACED PROFILE, STRAIGHTENED FRAME, AND INSTALLED FRAME DOUBLER. FAA FORM 337 WAS COMPLETED.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
THE EXTRUSION ON THE FWD. SIDE OF FRAME 6 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 RH FWD FITTING 212-22406-06-1 WITH NEW RA-212-22406-06-1 FITTING. SEE 337 DATED 07-24-2024 FOR FURTHER DETAIL.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
THE EXTRUSION ON THE AFT SIDE OF FRAME 6 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 RH AFT FITTING 212-22406-07-1 WITH NEW RA-212-22406-07-1 FITTING. SEE 337 DATED 07-24-2024 FOR FURTHER DETAIL.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
THE EXTRUSION ON THE AFT SIDE OF FRAME 11 (RIGHT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 1 RH AFT FITTING 212-22406-06-2 WITH NEW RA-212-22406-06-2 FITTING. SEE 337 DATED 07-24-2024 FOR FURTHER DETAIL.
Part: ATTACH FITTING — CORRODED (ZONE 300) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
LH HORIZONTAL STABILIZER FORWARD ATTACH FITTING HAS CORROSION AT THE GUIDE PIN HOLE FOR THE TRIANGLE LEADING EDGE. (LOCATED INSIDE THE STABILIZER). REMOVED THE HORIZONTAL STABILIZER. DRESSED OUT THE CORROSION AND TREATED (ETCHED AND ALODYNED) PER THE CASA CORROSION CONTROL MANUAL SECTION 5, PARA 5.4, PG. 5-11 THRU 5-20, THEN PRIMED WITH SUPER KOROPON EPOXY PRIMER. REINSTALLED THE HORIZONTAL STABILIZER IAW THE CASA MM CH. 55-10-00.
Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,528 hrs · 65,997 cycles
THE EXTRUSION ON THE AFT SIDE OF FRAME 6 (LEFT SIDE UNDER FLOOR) HAS INTERGRANULAR CORROSION. REPLACED ORIGINAL FRAME 6 LH AFT FITTING 212-22406-07-2 WITH NEW RA-212-22406-07-2 FITTING. SEE 337 DATED 07-24-2024 FOR FURTHER DETAIL.
Part: FRAME — BUCKLED (ZONE 100)
FRAME 16 IS BUCKLED UNDER THE FLOOR JUST LEFT OF CENTER. REMOVED BUCKLED SECTION OF FRAME 16 WEB AND SPLICED IN A NEW PIECE OF MATERIAL. WORK WAS DONE REFERENCING THE CASA 212 STRUCTURAL REPAIR MANUAL APPENDIX II FIGURE B25. DETAILS OF THE REPAIR ARE AVAILABLE ON THE FORM 337.
Part: PROFILE — CRACKED (LT WING) · airframe 40,528 hrs · 65,997 cycles
FOUND A CRACKED PROFILE ON THE AFT FALSE SPAR OF THE LH WING AT STA 2820. PROFILES AT FURTHER OUT STATIONS HAVE INSPECTIONS REQUIRED BY AN AD NOTE 98-12-28 WHICH DIDN'T COVER THIS PROFILE. THE CRACKED PROFILE WAS REMOVED AND ANOTHER PROFILE FABRICATED TO REPLACE IT.
Part: FITTING — CRACKED (FRMS 6 & 11) · airframe 40,528 hrs · 65,997 cycles
FOUND FLOOR BEAM TO SIDEWALL EXTRUDED FITTINGS TO BE CORRODED AND CRACKED AT FRAME 6 AND 11, BOTH RH AND LH. REPLACING FITTINGS WITH NEW.
2023
Part: FRAME — CRACKED (ZONE 200) · airframe 40,221 hrs · 65,522 cycles
WHILE INSPECTING THE AIRFRAME PER AD2022-17-06, AOT C212-53-0001 AND SB212-53-0055, A CRACK OF 0.75" WAS FOUND IN THE AREA OUTLINED. THE AIRCRAFT WAS REPAIRED BY PARTIALLY APPLYING THE SB ALREADY MENTIONED, AND AN EA FROM THE MANUFACTURER.
Part: CASTING — CRACKED (ZONE 100) · airframe 40,035 hrs · 65,211 cycles
DURING ROUTINE SCHEDULED MAINTENANCE FOUND A CRACK IN THE R/H MLG UPPER FORWARD LANDING GEAR ATTACH POINT CASTING. REMOVED AND REPLACED CASTING. THIS SCHEDULED INSPECTION IS PART OF AN INSPECTION PROGRAM THAT WAS BROUGHT ON BY AD96-07-14. (PSE53-20-08)