N707RA
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
RIGHT FUSELAGE STRUT FITTINGS FAILED SID 53-20-07-250. LIFT STRUT FITTINGS. REMOVED FLOOR PANELS 2611127-18, 2611127-22 AND PULLY BRACKET 2612112-2 REMOVED FOR ACCESS. CAP ASSEMBLY 2611011-66 RIVETS REMOVED TO OUTBOARD SEAT RAIL FOR ACCESS. REMOVED LIFT STRUT FITTINGS 261113-6 AND 2611113-5. FITTED LIFT STRUT FITTINGS IN PLACE, ALL -3 HOLES REAMED IN PLACE TO 0.,188", ALL -4 BOLT HOLES REAMED IN PLACE TO 0.248". INSTALLED NEW LIFT STRUT FITTINGS 2611113-6 AND 2611113-5, USING NEW BOLTS,, RIVETS, AND SUBSTITUTED ONE RIVET PIN. APPLIED PS870 B1/2 TO EXTERIOR OPENING EDGES. LIFT STRUT TO FUSELAGE FITMENT FOUND SATISFACTORY. REINSTALLED: FLOOR PANELS 2611127-18, 2611127-22, PULLY BRACKET 2612112-2, AND CAP ASSEMBLY 2611011-66. MATERIALS USED; RIVET SIZE, SPACING, AND REPAIR CRITERIA WERE OBTAINED FROM ORIGINAL INSTALLATION AS WELL AS: MM D2078-13 REVISION-42: SRM 51-40-00, TURBOPROP STANDARD PRACTICES MANUAL (REV 4) 20-10-65, AC43.13-1 B: 4-60B.1 (P4-40), AND 4-57E (P4-19).
"WHEN BLEED AIR IS TURNED ON, SMOKE ENTERS COCKPIT." "INSPECTED, NO SMOKE WAS OBSERVED COMING FROM THE ENGINE COMPARTMENT." CAUSE SUSPECTED TO BE DIRT/DUST IN BLEED AIR HEAT/VENT DISTRIBUTION.
L/H AIRFRAME LOWER STRUT FITTING FOUND TO BE CORRODED/PITTED. REPLACED BOTH LH LOWER STRUT FITTINGS WITH NEW 2611113-5 AND 2611113-6. SEE 337 DATED 10/29/2024 FOR FURTHER DETAIL.
RIGHT FLAP MIDDLE FLAP TRACK HAS SEVERE CORROSION INBOARD SIDE. REMOVED AND REPLACED RIGHT FLAP MIDDLE FLAP TRACK IN REFERENCE TO C208 SRM 51-40-00.
DURING THE SCHEDULED 100HR INSPECTION, A 0.75" CRACK WAS DISCOVERED, EMANATING FROM THE OUTBD STATIC WICK BASE ON THE L/H ELEVATOR. THE STATIC WICK WAS REMOVED AND THE CRACK WAS STOP DRILLED USING A #40 DRILL BIT. A REINFORCING DOUBLER OF 2024T3, 0.025" THICK, MEASURING 2.7"X2.7" WAS INSTALLED ON THE BACK SIDE OF THE AREA, USING CR3213-4 RIVETS. THE STATIC WICK BASE WAS REINSTALLED. ELEVATOR BALANCE WAS CHECKED AND ADJUSTED TO A BALANCE WEIGHT OF +2.43 BY ADDING WASHERS TO THE BALANCE WEIGHT ATTACH BOLTS. THIS WAS WITHIN BALANCE WEIGHT LIMITS. CRITERIA FOR THIS REPAIR WAS GATHERED FROM THE CESSNA 208 STRUCTURAL REPAIR MANUAL 53-20-00, FIG 801, AND 51-75-00.
DURING AN INSPECTION, THE TWO VERTICAL BRACKETS ON EITHER SIDE OF THE FLAP ACTUATOR, BETWEEN FS 201.5 AND 215.813 WERE FOUND TO HAVE CRACKS IN THE RADIUS OF THE BOTTOM FLANGE.
LT ENGINE COWL INERTIAL SEPARATOR INLET SUPPORT BRACKET FOUND CRACKED UPON ROUTINE ENGINE INSPECTION.
UPON LANDING, NOTICED THAT THE RT SIDE IB GEAR DOOR WAS NOT IN THE STOWED POSITION. CAUSE OF FAILURE, THE ROD END THAT CONTROLS MOVEMENT OF THE IB GEAR DOOR HAD EXCESSIVE WEAR CAUSING THE BOLT TO SHEAR AND ALLOWING GEAR DOOR TO SWING FREELY.