N6NR
Registered owner: SDI AVIATION LLC, WI (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
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.
5 reports on file, 2001-10-22 – 2006-10-02.
Part: TURBINE WHEEL — FRACTURED (NR 2 ENGINE)
IN FLIGHT, CREW FELT SLIGHT TO MODERATE VIBRATION FROM NR 2 ENGINE. AFTER LANDING FURTHER INSPECTION FOUND APPROX ONE INCH OF ONE OF THE 3 LPT DISK BLADES MISSING. REASON FOR FAILURE AT THIS TIME UNDER INVESTIGATION BY MFG, SB 72-3689. (K)
Part: BRACKET — WORN (WING TO FUSELAGE)
WHILE FLYING THROUGH TURBULENCE SITTING IN THE VIP CHAIR (CABIN RT FWD FACING) A SLIGHT VIBRATION CAN BE FELT COMING THROUGH THE FLOOR AND WILL DIMINISH AFTER LEAVING TURBULENCE. AFTER TALKING WITH MFG TECH SUPPORT, THIS PROBLEM IS COME TO BE KNOWN AS (WING CLUNK). IT IS CAUSED BY THE PLAY IN THE BRACKET VERTICAL LINK SPHERICAL BEARING AND ATTACH BOLT, IE ONE OR ALL. THERE IS NO SB, IL, COMMUNIQUÃ OUT ON THIS PROBLEM BUT MFG IS AWARE AND HAS A REPAIR KIT OUT THAT ONLY CAN BE DONE AT MFG SERVICE CENTER. (GL13200508700) (K)
Part: LINE — CRACKED (HYD SYSTEM) · airframe 9,564 hrs · 6,143 cycles
PILOTS STARTED TAXI OUT TO TAKEOFF. IN PROCESS CONDUCTED THE LANDING SPOILER EXTENSION OPERATIONAL TEST WHICH SURGES AND SLAMS THE HYDRAULIC SYSTEM FAIRLY HARD. WITHIN A FEW SECONDS RECEIVED MASTER WARNING CAUTION LIGHT AND NOTICED LOW HYDRAULIC PRESSURE. RETURNED TO HANGAR. INSPECTION REVEALED .75 INCH LONG STRESS CRACK IN UPPER FORWARD RADIUS OF ALUMINUM HYDRAULIC LINE THAT WAS UNDETECTABLE TO THE EYE UNTIL UNLESS HYD PUMP WAS ON. PROBABLE CAUSE IS MOST LIKELY WORK HARDENING AND STRESS DUE TO SURGES AND HYDRAULIC SYSTEM SLAM EXPERIENCED WITH SUDDEN SPOILER BOARD EXTENSION ON LANDINGS.
Part: LINE — CRACKED (HYD SYSTEM) · airframe 9,311 hrs · 5,986 cycles
MAINTENANCE PERSONNEL NOTICED FLUID LEAKAGE FROM BELLY PANEL AFT OF LANDING GEAR FOLLOWING PILOT'S COMPLETION OF "SPOILER AUTO EXTEND" PREFLIGHT CHECK BY FLIGHT CREW. VISUAL INSPECTION DETERMINED SPOILER AUTO EXTEND LINE ASSEMBLY TO BE LEAKING PAST B-NUT AND SLEEVE WHERE IT CONNECTS TO SPOILER CONTROL DUMP VALVE. DEFECT WAS CRACK AT LIP OF DOUBLE FLARE. MOST PROBABLE CAUSE IS SUDDEN SHOCK FROM AUTO EXTEND ACTIONS AT LANDING AND DURING PREFLIGHT CHECKS.
Part: WINDSHIELD — ARCED (COCKPIT) · airframe 9,205 hrs · 5,939 cycles
PILOTS NOTICED INTERNAL ARCING IN WINDSHIELD AT UPPER EDGE ALONG HEAT ELEMENT BUS STRIP. ARCING CONTINUED FROM ONE SIDE AND PROGRESSED TO OPPOSITE SIDE AND BURNED BUS STRIP PARTIALLY THROUGH. WINDSHIELD CONTINUED TO HEAT UNTIL BUS STRIP BURNED COMPLETELY THROUGH WIDTH AT ONE LOCATION. WINDSHIELD WAS REPLACED PRIOR TO NEXT FLIGHT. REASON FOR ARCING IS MOST LIKELY DELAMINATION IN UPPER EDGE OF WINDSHIELD IN BUS STRIP AREA. RECOMMEND PRE-FLIGHT VISUAL INSPECTION OF THIS AREA FOR DELAMINATION AND EVIDENCE OF INTERNAL ARCING STARTING TO HAPPEN IN ANY AREA. IF REPLACEMENT IS REQUIRED, REPLACE WITH PPG BRAND WINDSHIELD.