DA20Eclipse · Katana

Parts most often named Rudder Pedal (11) · Control Cable (8) · Pedal (7) · Tube (6)

(CAN) DURING INSPECTION MAINTENANCE FOUND PILOT RIGHT HAND FORWARD RUDDER CABLE TO BE FRAYED AT RUDDER PEDAL "S" TUBE. NEW CABLE FABRICATED AND INSTALLED AS PER DIAMOND MAINTENANCE MANUAL.

(CAN) DURING SCHEDULED INSPECTION THE LEFT BRAKE PEDAL ON THE LEFT(PILOT) SIDE WAS FOUND CRACKED IN THE PIVOT AREA. NEW PART INSTALLED. UNFORTUNATELY CRACK PEDAL WAS DISCARDED BEFORE A PHOTO COULD BE TAKEN, AND PROPER IDENTIFICATION COULD BE MADE TO DETERMINED IF IT WAS OF THE LATEST MOD.

(CAN) WHEN MOVING THE ACFT, IT WAS FOUND THAT THE LT RUDDER PEDAL WAS SEIZED TO THE SHAFT. THERE WAS A SMALL CRACK RUNNING ON THE SHAFT AREA OF THE PEDAL. THERE WAS ALSO A LOT OF CORROSION POSSIBLY CAUSED BY SALT COMING OFF THE BOOTS OF THE PILOT. THE PEDAL WAS REMOVED & A NEW ONE INSTALLED.

Parts most often named Pump (28) · Seal (1)

(CAN) DURING A 150 HOUR INSPECTION A STAIN OF FUEL WAS NOTED ON THE BOTTOM COWL ABOUT THE SIZE OF A PLATE. INVESTIGATION FOUND THE MECHANICAL FUEL PUMP WAS LEAKING FUEL FROM THE PLATE THAT HOLDS MIXTURE CONTROL AND MIXTURE STOP. THE PUMP WAS REPLACED WITH A [S/N removed] UNIT.

(CAN) DURING INSPECTION AND TROUBLESHOOTING OF A OIL LEAK, AFTER CLEANING THE ENGINE AND GROUND RUN, OIL WAS OBSERVED UNDER THE FUEL PUMP AND WET AT THE GASKET SEAM OF THE PHENOLIC SPACER. (TC# 20190321004)

(CAN) AFTER TOUCH-AND-GO, AT 300 FEET AGL, 2 SECONDS AFTER SWITCHING ELECTRIC FUEL PUMP TO OFF, SIGNIFICANT POWER LOSS OCCURRED. ELECTRIC FUEL PUMP WAS SELECTED BACK ON, FULL THROTTLE APPLIED AND POWER WAS RESTORED. IMMEDIATE RETURN FOR UNEVENTFUL LANDING. FLIGHT WAS AN INSTRUCTOR STANDARDISATION FLIGHT WITH 2 INSTRUCTORS ON-BOARD. FIRST PART OF THE FLIGHT WAS IN MANEUVREING AREA, AFTER THAT ENGINE FAILURE WAS SIMULATED AND AFTER THAT 3 TRAFFIC PATTERNS FLOWN. INTERNAL INVESTIGATION IS PENDING. (TC# 20190429015)

Parts most often named Indicator (8) · Gauge (8) · Transmitter (4) · Sender (3)

(CAN) ACFT WAS BROUGHT IN FOR LOW OIL PRESSURE, STILL WITHIN LIMITS. MAINTENANCE FOUND THE OIL PRESSURE GAGE WAS READING 10 PSI LOWER THAN THE SHOP MASTER GAGE. THE OIL PRESSURE KIT WAS REPLACED WITH A NEW ONE AND WAS TESTED TO BE FOUND ACCURATE. ENGINE RUNS WERE CARRIED OUT WITH NO FAULTS FOUND.

(CAN) LOW OIL PRESSURE WAS REPORTED ON RUN UP. MAINTENANCE TESTED THE OIL PRESSURE GAGE AND SENDER AND FOUND IT TO BE READING MORE THAN 10 PSI LESS THAN THE MASTER GAGE. A NEW OIL PRESSURE KIT WAS INSTALLED, ENGINE RUNS WERE CARRIED OUT WITH NO FURTHER FAULT.

(CAN) PILOTS RETURNED TO THE AIRPORT WITH A HIGH OIL TEMP, LOW OIL PRESSURE INDICATION. MAINTENANCE FOUND THAT THE OIL PRESSURE GAUGE WAS READING 10 PSI LOW. THE GAUGE WAS INSTALLED LESS THAT 40 HOURS PREVIOUS.

Parts most often named Exhaust Riser (13) · Exhaust Stack (4) · Exhaust Pipe (3) · Riser (3)

WITHIN THE LAST FEW WEEKS, THIS FLIGHT SCHOOL DISCOVERED SEVERAL INSTANCES OF CRACKED CYLINDER NR 2 OR NR 3 EXHAUST RISER FLANGE AND FLANGES.

WITHIN THE LAST FEW WEEKS THIS FLIGHT SCHOOL DISCOVERED SEVERAL INSTANCES OF CRACKED EXHAUST RISERS AND FLANGES AFFECTING THE NR 2 AND NR 3 CYLINDERS. SEVERAL ADDITIONAL M&D REPORTS HAVE BEEN FILED FOR THIS TIME PERIOD.

CTI PROFESSIONAL FLIGHT TRAINING, LLC IS A TITLE 14 CFR, 141 PILOT SCHOOL THAT OPERATES A FLEET OF ABOUT 15 DIAMOND DA-20 C L 'S IN FT LAUDERDALE, FLORIDA AND A SATELLITE IN MILLINGTON, TN. WITHIN THE LAST FEW WEEKS, THE AFOREMENTIONED FLIGHT SCHOOL DISCOVERED SEVERAL INSTANCES OF CRACKED EXHAUST RISERS AND FLANGES ON THE #2 OR #3 CYLINDERS.

Parts most often named Fork (12) · Roll Pin (4) · Landing Gear (3) · Leg Assy (1)

NOSE FORK SEPARATED FROM NLG AT AN UNKNOWN TIME DURING FLIGHT. AIRCRAFT WAS IN A TRAINING ENVIRONMENT WITH REPETITIVE LANDINGS. REGULAR INSPECTION AND LUBRICATION OF THE FORK AND GEAR AT 100 HOUR INSPECTIONS. SUSPECT FAILURE OF THREADED ROD DUE TO NO PRIOR NOSE WHEEL SHIMMY REPORTED. SUSPECT ROD WAS STRETCHED THROUGH REPETITIVE INSPECTIONS AND POSSIBLE HARD LANDINGS. RECOMMEND ADDING DIMENSIONAL INSPECTION TO SIL20C1-014.

NOSE LANDING GEAR STUD (USED TO SECURE NOSE WHEEL ASSEMBLY TO LANDING GEAR) BROKE OFF. THE COTTER PINNED RETAINING NUT THAT HOLDS THE WHEEL ASSEMBLY TO THE LANDING GEAR IS ATTACHED TO THIS STUD AND DEPARTED THE AIRCRAFT, CAUSING THE ENTIRE NOSE WHEEL ASSEMBLY TO DEPART THE AIRCRAFT DURING THE AIRCRAFT'S INITIAL TAKEOFF.

NOSE LANDING GEAR FORK RETAINING STUD FAILED DURING TAXI OUT. NOSE LANDING GEAR FORK AND NOSE WHEEL SEPARATED FROM NOSE LANDING GEAR STRUT AFTER TAKE OFF.

Parts most often named Magneto (6) · Gear (4) · Stator (4) · Cotter Pin (3)

(CAN) PILOT REPORTED ENGINE DIED WHEN SELECTING LT MAGNETO. MAINTENANCE CONFIRMED ISSUE WITH THE MAGNETO AND REPLACED IT.

(CAN) STUDENT REPORTED UNABLE TO START AIRCRAFT. AFTER TROUBLESHOOTING FOUND THAT RETARD POINTS WERE FIRING 180 DEGREES OUT. MAGNETO TIMING WAS CORRECT EXTERNALLY. THE MAGNETO WAS SHIPPED FOR REPAIR AND A TEARDOWN REPORT WAS REQUESTED (TC# 20150223005)

(CAN) PILOT REPORTED RIGHT MAGNETO FAIL. SPARK PLUGS CLEANED ENGINE STARTED AND FOUND ENGINE CUT OUT WHEN RIGHT MAG CHECK. MAGNETO REPLACED [S/N removed] UNIT, AIRCRAFT RELEASED. MAGNETO BEING SENT FOR INSPECTION AND REPAIR.

Parts most often named Exhaust Valve (8) · Stud (3) · Intake Valve (3) · Valve (2)

DURING FLIGHT THE NR 4-CYLINDER EXHAUST ROCKER ARM HOLD DOWN STUDS BROKE CAUSING THE NR 4-CYLINDER EXHAUST VALVE TO NOT OPEN. THIS CAUSED EXTREME VIBRATION AND A SIGNIFICANT LOSS OF ENGINE POWER. AIRCRAFT WAS WITHIN GLIDING DISTANCE OF RUNWAY AND LANDED SAFELY. THIS IS THE SECOND OCCURRENCE OF THIS ISSUE WE HAVE HAD ON THESE AIRCRAFT IN LESS THAN A YEAR.

(CAN) AIRCRAFT WAS [S/N removed] FOR RUNNING VERY ROUGH AT IDLE, EXTENSIVE INSPECTION REVEALED THAT ALL 3 INDUCTION INTAKE TUBES OF THE ENGINE WERE CRACKED ON THEIR FLANGES. FURTHER INSPECTION SHOWED THAT THE INTAKE MANIFOLD PLENUM MOUNTING POINT WAS LOOSE CAUSING EXCESSIVE VIBRATION TO ALL 4 TUBES CAUSING THEM TO CRACK. (TC# 20190523001)

ACFT ON A TRAINING FLIGHT. A REPORT WAS MADE THAT THE ENGINE WAS RUNNING ROUGH AND IT FELT LIKE IT WAS RUNNING ON 3 CYLINDERS. DECLARED AN EMERGENCY, DIVERTED MADE AN UNEVENTFUL LANDING. AN INSPECTION PERFORMED BY MECHANICS VERIFIED A VALVE WAS STICKING INTERMITTENTLY. CYLINDER WAS REPLACEDT.

Parts most often named Fork (10) · Strut (3) · Fork Assy (2) · Axle (2)

(CAN) 20 FEET AFTER TAXIING, THE STUD FROM A 20-3220-02-00_1 NOSE LANDING GEAR FAILED. AFTER TAKEOFF, THE NOSE FORK DEPARTED THE AIRCRAFT. THE PILOT WAS UNAWARE OF THIS AND PROCEEDED WITH UPPER AIR WORK. UPON LANDING, THE PILOT WAS PRACTICING SOFT FIELD LANDINGS. THE STRUT CONTACTED THE RUNWAY AND CAME TO A COMPLETE STOP. THE AIRPLANE WAS QUICKLY REMOVED FROM THE RUNWAY WITHOUT FURTHER INCIDENT. (TC# 20190521020)

LANDED ON THE MAIN WHEELS AND KEPT THE BACK PRESSURE ON THE CONTROLS AND HELD THE NOSE WHEEL OFF THE GROUND FOR AS LONG AS POSSIBLE TO PREVENT ANY SHIMMY FROM THE NOSE WHEEL. UPON SETTING THE NOSE WHEEL DOWN THE AC CONTINUED TO PITCH DOWN AS THE NOSE GEAR BROKE IN TWO PIECES ABOUT 3 INCHES FROM THE TOP OF THE T JOINT WHERE THE NOSE GEAR ATTACHES TO THE FUSELAGE. THE AC CONTINUED TO PITCH DOWN UNTIL IT CAME TO REST ON THE NOSE.

NOSE LANDING GEAR STRUT BROKE UPON LANDING CAUSING A PROP STRIKE AND EXTENSIVE DAMAGE TO UNDERCARRIAGE OF AIRCRAFT FUSELAGE. THE STRUT AXLE WAS FOUND SEVERED FROM THE TUBULAR STRUT ITSELF WHERE THE AXLE IS ATTACHED TO THE STRUT. NOSE FORK ASSEMBLY AND TIRE SEVERED FROM THE STRUT UPON TOUCHDOWN. PILOT HELD NOSE UP AS LONG AS POSSIBLE BEFORE ALLOWING AIRCRAFT TO SETTLE ON THE NOSE.

Parts most often named Needle (5) · Throttle Body (4) · Diaphragm (4) · Fuel Control (3)

(CAN) DURING FUEL INJECTION, SYS PRESSURE CHECK GROUND RUN AND ADJUSTMENT, THE THROTTLE BODY CONTROL ARM BECAME STIFF TO THE POINT WHERE THE THROTTLE CONTOL WOULD NO LONGER OPEN OR CLOSE THE THROTTLE VALVE. CABLE WAS REMOVED AT THE VALVE AND FOUND TO BE RUNNING FREELY, THROTTLE BODY ARM FOUND SEIZED. THOTTLE BODY REPLACED AND ACFT RELEASED. UNIT [S/N removed], SENT FOR EVALUATION.

(CAN) ON FINAL APPROACH ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. ENGINE WAS SHUTDOWN WITH MIXTURE LEVER CUTOFF AND ACFT WAS LANDED SHORT OF PAVED RUNWAY, IN THE GRASS. NO INJURY TO CREW OR PASSENGERS. NO PHYSICAL DAMAGE TO ACFT. POST-FLIGHT INSPECTION REVEALED DAMAGE TO SPLINES ON THROTTLE BODY LEVER-TO-CABLE HOOK-UP. TELEDYNE CONTINENTAL REQUESTED RETURN OF THROTTLE BODY FOR INVESTIGATION.

(CAN) WHEN THE CARB WAS DISASSEMBLED THE DIAPHRAGM WAS FOUND TO HAVE SWOLLEN AND WAS BUBBLED UP WHEN INSTALLED IN THE CARBURETOR. THE AIRCRAFT OPERATES PRIMARILY ON UNLEADED MOGAS WITH OCCASIONAL USE OF 100LL AVGAS.

Parts most often named Starter (4) · Gear (4) · Clutch (2) · Shaft (2)

(CAN) WHILE STARTING THE ACFT THE STUDENT RELEASED THE IGNITION KEY. THE PROPELLER CONTINUED TO ROTATE AFTER THE KEY WAS RELEASED. THE PROP STOPPED ONCE THE MASTER SWITCH WAS SHUTOFF. MAINTENANCE REPLACED THE STARTER RELAY WITH A [S/N removed] RELAY AND TESTED THE ACFT WITH NO FURTHER FAULTS FOUND. THE TOTAL TIME OF THE RELAY IS UNKNOWN BUT AS IT IS NOT A LIFED ITEM IT IS POSSIBLE THE RELAY HAS 6314 HOURS TT, THE SAME AS THE ACFT.

(CAN) DURING ENGINE START THE STARTER FAILED. STARTER WAS REMOVED AND DRIVE SHAFT WAS FOUND FRACTURED. ALTHOUGH THE ENGINE DID NOT START THE CRANKSHAFT CLUSTER GEAR, P/N 656762 WAS DAMAGED. ENGINE REQUIRED REMOVAL AND REAR CASE/SUMP REMOVAL TO FACILITATE CRANKSHAFT GEAR REPLACEMENT.

STARTER FAILED DURING ATTEMPTED ENGINE START. UPON REMOVAL, GALLING WAS EVIDENT ON STARTER NOSE BOWL FROM STARTER PINION GEAR. DAMAGE WAS ALSO FOUND ON THE AFT SIDE OF THE ENGINE CASE, JUST FWD OF THE STARTER PINION GEAR. THE STARTER PINION GEAR HAS EIGHT TEETH, WHILE THE MAINTENANCE MANUAL DESCRIBES A NINE-TOOTH PINION GEAR.