N520MC
Registered owner: BEDROCK LLC, AL (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| MAYO AVIATION LLC (CIEA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
HEAVY CORROSION FOUND DURING PHASE INSPECTION ON WING MAIN SPAR LOWER CAP AREA WHERE IT PASSES THROUGH THE LT FUSELAGE PRESSURE VESSEL. CAUSE OF CORROSION WAS DUE TO MOISTURE BEING TRAPPED UNDERNEATH DETERIORATING SEALANT THAT SEALS THE PRESSURE VESSEL. A MAJOR REPAIR RESULTED BY REMOVING ALL CORROSION, BLENDING THE SPAR CAP AND RETREATING WITH PRIMER AND PAINT AS NECESSARY. THE ACFT MFG ASSISTED IN THE REPAIR PROCESS, AND DEVELOPED AND APPROVED THE REPAIR PROCEDURES.
FLIGHT DISCREPANCY: RT MLG LIGHT DOES NOT ILLUMINATE WHEN GEAR IS DOWN. LIGHT NOT BURNED OUT. MANUALLY EXTENDED GEAR. EMERGENCY WAS DECLARED TO TOWER. PILOT LANDED AIRPLANE SAFELY WITH NO DAMAGE OR INJURIES. A DEFECTIVE DOWNLOCK SWITCH WAS FOUND AFTER TROUBLESHOOTING.
DURING RECEIVING INSP OF O/H PRESSURE CONTROLLER AND BEFORE INSTALLATION, FOUND THE "CAB ALT" KNOB BINDING INTERMITTENTLY AND MAKING A RATCHETING NOISE WHEN ADJUSTED. PART WAS NOT INSTALLED ON ACFT. NOTIFIED THE VENDOR THAT THE PART WAS PURCHASED FROM. PLACED AN ORDER FOR A DIFFERENT CONTROLLER.
DURING CRUISE FLT, CREW HEARD A NOISE & NOTICED THAT THE LT WING LOCKER HAD COME OPEN AND DOOR WAS TRAILING A FEW INCHES OPEN IN FLIGHT. ACFT APPROXIMATELY 25 MILES FORM A SUITABLE AIRPORT & CREW LANDED WITHOUT FURTHER INCIDENT. BAGGAGE FROM WING LOCKERS REMOVED & PLACED IN BAGGAGE COMPARTMENT INSIDE ACFT. CREW INSPECTED WING LOCKING MECHANISM & DETERMINED IT WAS LOCKING. LOCKER CLOSED & UNIT LOCKED WITH KEY LOCK. ACFT CONTINUED FLT TO ITS DESTINATION. UPON RETURN OF ACFT TO ITS HOME BASE, MX INSPECTED WING LOCKER & FOUND RT RECEIVER LOCK BRACKET SLIGHTLY BENT. RECEIVER LATCH STRAIGHTENED & INSPECTED FOR ANY CRACKS & NONE NOTED. ACFT CARRYING A SOFT SIDED TYPE OF DUFFLE BAG & IT MAY HAVE BEEN SUBJECTING
SHORTLY AFTER TAKEOFF THE PASSENGER NOTIFIED THE FLIGHT CREW THAT THEY HAD OBSERVED SMOKE FROM THE AREA OF THE NO SMOKING FASTEN SEAT BELT SIGN. THE FLIGHT CREW THAN OBSERVED THAT THE NO SMOKING FASTEN SEAT BELT SIGN CIRCUIT BREAKER HAD IN FACT POPPED. THE FLIGHT CREW RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT. MAINTENANCE DID A QUICK INSPECTION OF THE AIRCRAFT AND VERIFIED THAT THERE WAS NO POWER TO THE NO SMOKING AND FASTEN SEAT BELT SIGN, TY-RAPPED THE CIRCUIT BREAKER AND MELâED THE SIGN. THE MAINTENANCE DEPARTMENT LATER INSPECTED THE SYSTEM AND FOUND ONE OF THE POWER WIRES TO THE NO SMOKING AND FASTEN SEAT BELT SIGN TO BE PINCHED IN THE FRAMEWORK OF THE EMERGENCY EXIT. THE WIRING WAS REPAIRED
DURING INSPECTION OF THE AIRCRAFT TO EVALUATE A PRESSURIZATION LEAK, THE PANEL BEHIND THE REAR SPAR WAS FOUND TO BE CRACKED IN THE LOWER RADIUS AREA. THERE WAS A CRACK APPROXIMATELY 4 INCHES LONG NEAR THE CENTER LINE OF THE AIRCRAFT. THE AIRCRAFT SKIN WAS NOT FOUND TO BE CRACKED AT THIS TIME. THIS PANEL COVERS THE REAR PART OF THE REAR WING SPAR AS IT PASSES THROUGH THE FUSELAGE. IT IS NOT BELIEVED THAT THE SPAR ITSELF IS CRACKED AT THIS TIME.
LANDING GEAR WOULD NOT EXTEND USING NORMAL PROCEDURES. LANDING GEAR WAS EXTENDED MANUALLY AND LANDING WAS PERFORMED NORMALLY. AC HAD BEEN IN AND OUT OF COLD AND SNOW ON ITS PREVIOUS FLIGHTS. AC WAS JACKED IN HANGAR AND GEAR WORKED NORMAL. GEAR WAS CYCLED SEVERAL TIMES. SWITCH WHICH DISABLES ELECTRIC MOTOR DURING AN EMERGENCY GEAR EXTENSION WAS FOUND CRACKED AND COMING APART. SUSPECT IT MIGHT HAVE CREATED AN INTERMITTENT CONNECTION. SWITCH WAS REPLACED AS A PRECAUTION. OTHER ITEMS INSPECTED WAS GEAR RIGGING, LANDING GEAR CONTROL RELAYS, AND GENERAL WIRING. NO OTHER ABNORMAL CONDITIONS WERE FOUND. GEAR WAS CYCLED A MINIMUM OF 20 TIMES IN THE HANGAR AND WORKED NORMAL EVERY TIME.
DURING AN INSPECTION OF THE AIRCRAFT, THE HINGE FOR THE ENTRY DOOR WAS LOOSE. THE HINGE WAS REMOVED AND INSPECTION REVEALED FRAME, P/N 50-430043-328, TO BE CRACKED AT 4 OF THE AFT RIVET HOLES. ALSO NOTED 3 RIVETS ATTACHING THE FRAME, P/N 50-430043-324, TO THE 2 CENTER FRAMES, WERE MISSING CAUSING FLANGES AT BOTTOM OF CENTER FRAMES TO BE CRACKED. REPAIRED BY INSTALLING INTERNAL AND EXTERNAL DOUBLERS.
AFTER TAKEOFF, CLIMBING THROUGH 15,000 FEET, THE LEFT FIRE WARNING LIGHT CAME ON. THE PILOT RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND NO EVIDENCE OF FIRE WAS FOUND. THE FIRE WARNING WAS CHECKED FOR PROPER OPERATION AND CHECKED GOOD. MAINTENANCE WAS UNABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS IN A HEAVY RAINSTORM PRIOR TO THE FLIGHT, AND SUSPECT THIS CONTRIBUTED TO THE FALSE INDICATION.
DURING AN INSPECTION OF THE AIRCRAFT, THE LEFT LEADING EDGE WING ROOT FAIRING WAS REMOVED TO PERFORM MAINTENANCE. A 2.50 INCH CRACK WAS FOUND FROM ONE OF THE RIVETS WHICH HOLD THE NUTPLATE IN PLACE FOR THE WING ROOT FAIRING IN THE PRESSURE VESSEL AREA. CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED.
DURING AN EVENT 1 INSPECTION, CRACKS IN THE WING SKIN IN THE AREA OF THE LEFT AND RIGHT LOWER WING BOLT FITTING WERE FOUND. THESE CRACKS TEND TO GO THROUGH THE HOLES WHERE SCREWS ARE USED TO SECURE THE SKIN TO THE WING SPAR CAP, AND EXTEND TO THE HOLE IN THE SKIN FOR THE FUEL DRAIN. SUBMITTER STATED SEVERAL OF THE E-90 FLEET HAVE HAD DOUBLERS INSTALLED TO REPAIR THIS PROBLEM IN THE PAST.
DURING AN EVENT 1 INSPECTION, A .50 INCH CRACK WAS FOUND IN THE SKIN AFT OF THE RIGHT FUEL FILLER CAP. THE CRACK APPEARS TO BE DUE TO IMPROPER USE OF THE FUEL NOZZLE DURING FUELING. INSTALLATION OF AN INTERNAL DOUBLER WAS REQUIRED.
DURING AN EVENT 1 INSPECTION, 3 RIBS ON THE LEFT INBOARD WING AT STA 56.00, STA 65.50, AND STA 75.50 AND ONE ON THE RIGHT AT STA 65.50 WERE FOUND CRACKED ON THE FORWARD RIVET WHERE THE STRINGER IS ATTACHED. THE CRACK WENT FROM THE RIVET HOLE FORWARD TO THE EDGE OF THE RIB. SUBMITTER STATED CAUSE IS UNKNOWN, BUT SUSPECT IT IS DUE TO FLEXING OF THE WING. REPAIRED BY INSTALLING A DOUBLER.
AFTER A HANGAR RASH INCIDENT, THE RIGHT ELEVATOR WAS BEING REPAIRED FOR DAMAGE TO THE FIBERGLASS TIP. AFTER REMOVAL OF THE TIP, THREE HOLES IN THE OUTBOARD TRAILING EDGE AREA OF THE SKIN WERE FOUND FILLED WITH BODY FILLER. THE FILLER WAS REMOVED AND AN ALUMINUM DOUBLER WAS INSTALLED AFTER BEING APPROVED ON FORM 8110-3.
DURING ROUTINE MAINTENANCE, A MECHANIC FOUND TWO SMALL CRACKS PROTRUDING FROM RIVET ON LEFT HAND WING LEADING EDGE SKIN OUTBOARD OF ENGINE NACELLE. INSPECTION OF INNER LEADING EDGE REVEALED CRACKED RIB. AFTER REMOVAL OF LEADING EDGE SKIN, FOUND SMALL ENGINE NACELLE TO WING ADJUSTABLE RIB CRACKED. ALSO, FOUND LEFT HAND OUTBOARD NACELLE SKIN AROUND THE REMOVED LEADING EDGE CRACKED. CRACK WAS ALSO NOTED ON OUTBOARD NACELLE ACCESS COVER DOUBLER RING.