177Cardinal · Cardinal RG

Parts most often named Bolt (5) · Support (3) · Gear (3) · Rod End (3)

MAIN LANDING GEAR MAIN SECTOR GEAR HAS GOUGE MARKS IN GEAR TEETH, MAIN LANDING GEAR PINION GEARS HAS CHIPPED AND DAMAGED TEETH. TWO BOLTS FOUND SHEARED THAT HOLD MAIN LANDING GEAR SECTOR GEAR IN PLACE.

NOSE LANDING GEAR FAILED TO LOCKDOWN. THE NAS404-5A15 BOLT THAT BOTH SECURES AND PROVIDES A PIVOT POINT FOR THE LOCK ASSY TO THE DRAG LINK HAD BACKED OUT OF THE DRAG LINK TOTALLY DISCONNECTING THE LOCK ASSY FROM THE DRAG LINK. THERE WAS EVIDENCE OF RED LOCKTITE IN THE DRAG LINK AS IS REQUIRED BY THE SRM BUT IT BACKED OUT ANY WAY. THIS BOLT IS NOT A DRILLED HEAD BOLT, BUT I RECOMMEND THAT IT BE REPLACED WITH ONE TO AVOID REOCCURRENCE. (K)

NOSE GEAR FAILED TO EXTEND ON LANDING SUBSTANTIAL DAMAGE OCCURRED. JACKED AIRCRAFT, CYCLED GEAR TO UP POSITION WITH AFT LG DOORS DISCONNECTED. ON EXTENTION, NOSE GEAR FAILED ONCE AGAIN. MECHANICAL UPLOCK FAILED TO RELEASE. SUSPECT OUT OF ADJUSTMENT.

Parts most often named Coil (2) · Magneto (2) · Impulse Spring (1) · Gasket (1)

LOST POWER ON TAKEOFF. VERIFIED PROBLEM OF LT MAGNETO INOPERATIVE. INSPECTED AND FOUND MAGNETO DISTRIBUTOR GEAR MISSING SEVERAL TEETH. GEAR WAS LOOSE ON SHAFT WHICH PROBABLY CONTRIBUTED TO BREAKAGE. SUSPECT CAUSE WAS LACK OF PROPER MAINTENANCE OVER LIFE OF MAGNETO. ANNUAL INSPECTION WAS SIGNED OFF IN AUGUST 2004.

THE AIRCRAFT MADE AN EMERGENCY LANDING IN A FIELD AFTER A LOSS OF ENGINE POWER. INSPECTION BY A MECHANIC REVEALED THE POINTS WERE BURNED AND THE CONDENSER WERE PART OF A NEWLY INSTALLED FACTORY REMANUFACTURED MAGNETO. THE POINTS AND CONDENSER WERE REPLACED, AND THE MAGNETO REINSTALLED AND RETURNED TO ENGINE. ENGINE PERFORMED SATISFACTORILY. (X)

DURING 100-HOUR ANNUAL INSPECTION, MAGNETO TYPE BENDIX D2000 [S/N removed] REMOVED FOR CONTACT BREAKER REPLACEMENT AND INTERNAL TIMING CHECK. MAGNETO REFITTING WITH LYCOMING GASKET P/N 62224 INSTEAD OF LW-12681. THE MAGNETO BECAME LOOSE AND BACKED OFF FROM THE ENGINE DRIVE. THE ENGINE STOPPED IN-FLIGHT AND THE AIRCRAFT WAS FORCED TO LAND ON A NEARBY AIRFIELD. THERE WAS NO DAMAGE OR INJURY SUSTAINED TO AIRCRAFT OR PERSONNEL.

Parts most often named Hose (5) · Line (4) · Hydraulic Line (1) · Connector (1)

LANDING GEAR WOULD NOT EXTEND DUE TO FAILURE OF NOSE GEAR DOWN PRESSURE HYD HOSE ASSY. GEAR HYD HOSE ASSY (ALL) SHOULD BE CHANGED EVERY 10 YRS OR 1000 HRS TIS BETWEEN CHANGES.

"AFTER T/O SELECTED GEAR UP AND HYDRAULIC CAUTION LIGHT ILLUMINATED. COMPLETED MEMORY ITEMS THEN COMPLETED AFTER T/O CHECK. COMPLETED EMERGENCY/NON-NORMAL CHECKLIST HYDRAULIC PROC 2. RETURNED TO TRI. DECLARED EMERGENCY AND RETURNED TO GATE. FLAPS REMAINED ZERO. REMOVED AND REPLACED LT PDU IAW SAAB AMM 24-31-20. OPS CHECK GOOD AT THIS TIME, P/N ON AND OFF A2042C, S/N ON CL-86429, [S/N removed] CG-81553. REMOVED AND REPLACED RELAY 7ML IAW SAAB AMM 20-20-00 OPS CHECK GOOD, P/N ON AND OFF MS24142D1.

(CAN) AIRCRAFT PLANNING ON LANDING WHEN UNDERCARRIAGE LIGHT FAILED TO INDICATED GEAR DOWN AND LOCKED. DECLARED AN EMERGENCY. AFTER SEVERAL ATTEMPTS AT TRYING TO PUMP GEAR DOWN BY HAND THE PILOT GOT A GEAR DOWN AND LOCKED LIGHT. AIRCRAFT LANDED WITH NO EVENT TAKING PLACE. MAINTENANCE LATER FOUND THE NOSE GEAR ACTUATOR HOSE HAD SLID PARTIALLY FROM ITS SWAGED END CONNECTOR AND WAS LEAKING BADLY. HOSE REPLACED. (TC NR 20070426007)

Parts most often named Air Filter (5) · Door (1) · Air Box (1) · Air Door (1)

FACTORY NEW PART- SCREEN ATTACH TABS ARE BENT 90, AND SPOT WELDED ON TO SCREEN FRAME. WELDS DO NOT PENETRATE BASE MATERIAL. ATTACH TABS WORK LOOSE. HAVE FOUND THIS CONDITION 3 TIMES. SOME HAVE BEEN REPAIRED WITH SHEET METAL SCREWS. TABS SHOULD BE RIVETED ON OR, BETTER WELDS.

OWNER OF AIRCRAFT SAID FUEL FLOW WAS LOW. RAN UP, OPS CHECKED FUEL FLOW AT 14 PSI AT FULL POWER. INSPECTED ACFT AND FOUND TWO BOLTS MISSING FROM THROTTLE CABLE MOUNT ON BOTTOM OF ENGINE AND ALTERNATE AIR DOOR LAYING IN THE AIRBOX ASSY. INSTALLED TWO NEW BOLTS IN THROTTLE CABLE MOUNT AND INSTALLED NEW ALTERNATE AIR DOOR AND HINGE AND SPRING IN AIR BOX ASSY. (ACFT HAS 10 HRS FROM LAST ANNUAL INSPECTION). NEEDS INSPECTION OF AIR BOX ASSY AND ALTERNATE AIR DOOR ASSY (VISUAL INSPECTION).

THE RUBBER SEAL AROUND THE EDGE OF THE VALVE RIPPED AND LOOKED LIKE IT WOULD HAVE BEEN SUCKED INTO THE ENGINE IN A COUPLE OR MORE HOURS. SUBMITTER STATED THE RUBBER SEAL LOOKED LIKE IT WAS MADE FROM THE WRONG MATERIAL . TT ON PART, 8 HOURS.

Parts most often named Cylinder (5) · Valve (1) · Head (1) · Rocker Shaft (1)

(CAN) PILOT REPORTED HEARING A BANG DURING CLIMB, FOLLOWING BY PARTIAL POWER LOSS AND VIBRATION WAS FELT. AN EMERGENCY WAS DECLARED AND AIRCRAFT RETURN FOR AN UNEVENTFUL LANDING. INITIAL INVESTIGATION REVEALED NR 3 CYLINDER HAS A VALVE HEAD SEPARATED AND IS STICKING OUT OF BOTTOM SPARK PLUG HOLE AREA. FURTHER DETAIL WILL BE SUBMITTED UPON ENGINE TEARDOWN.

THE PUSH ROD TUBE RETAINER CLIPS, SL 14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS. DETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER. SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT. (X)

THE PUSH ROD TUBE RETAINER CLIPS, PN SL14995, IN NR 2, NR 3, AND NR 4 VALVE COVERS WERE BROKEN OFF AT THE BOLT HEADS. DETECTION WAS DUE TO A DENT IN THE VALVE COVER OF NR 2 CYLINDER. SUBMITTER STATED IT APPEARED TO BE A MATERIAL DEFECT. (X)

Parts most often named Bracket (9)

THREE OF FOUR BALANCE WEIGHT SUPPORT BRACKETS WERE CRACKED ALONG THE BEND RADIUS. CRACKS WERE 1.25 INCHES, 1.50 INCHES, AND 1.75 INCHES ON EACH. THIS WAS NOTICED DURING STABILIZER BEARING REPLACEMENT WITH THE STABLIZER OFF THE AIRCRAFT. SUBMITTER RECOMMENDED FREQUENT INSPECTIONS. UNKNOWN CAUSE. (X)

DURING ANNUAL INSPECTION, CRACKS WERE NOTED ON (3 OF THE 4) STABILATOR WEIGHT ARM MOUNT BRACKETS. CAUSE, NORMAL WEAR AND VIBRATION. SUBMITTER RECOMMMENDS CLOSER INSPECTION AND DYE CHECK. ALSO INCLUDES FORWARD MOUNT P/N 1732010-1 AND DASH 2.

DURING ANNUAL INSPECTION, FOUND CRACK IN BEND RADIUS OF ONE FORWARD AND ONE AFT STABILATOR BALANCE ARM SUPPORT BRACKET ON STABILATOR. RECOMMEND REPLACEMENT OF THESE WITH LATER STEEL BRACKETS, PN 1732063-1 AND DASH 2, AND 1732064-1, AND DASH 2 PER CESSNA SEB 89-1, REV 3.

Parts most often named Blade (7) · Snap Ring (1)

(AU) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADES WERE FOUND CORRODED ON THE LEADING EDGES AND THE BUTTS. THIS PROPELLER WAS LAST INSPECTED ON 7 NOVEMBER 1990.

(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE LEADING EDGES OF THE PROPELLER BLADES WERE FOUND NICKED. THE BLADES HAD NOT BEEN REPAIRED PER THE MCCAULEY MANUAL.

(CAN) STONE DAMAGE ON THE LEADING EDGE AND THE FACE OF THE PROPELLER BLADE. THE BLADE REQUIRED FILING AND GRINDING. THE PROPELLER HUB BREATHER SEALANT WAS MISSING.

Parts most often named Bearing (3) · Actuator (1) · Pin (1) · Pivot Assy (1)

INSPECTION OF THE ACFT FOUND THE MLG ACTUATOR ROD END HAD FAILED. THE ROD END BODY APPEARS TO FIRST BROKE AT THE GREASE [S/N removed] PORT. AIRCRAFT RECORDS RESEARCH FOUND NO RECORD OF REPLACEMENT SINCE DATE OF MFG. SL SE7937R1 DATED 12/15/1980 AND BULLETIN CE-14-17 ADDRESSES REPLACING THE ROD END.

PILOT COULDN’T OBTAIN GEAR DOWN INDICATION AFTER EXTENDING GEAR. JACKED AC AND FOUND MAIN GEAR WOULDN’T COMPLETELY ENTER DOWN-AND-LOCKED POSITION. FOUND MAIN GEAR RETRACT ACTUATOR REAR MOUNTING/ PIVOT PIN HAD ONE SIDE COMPLETELY SHEARED. THIS ALLOWED/CAUSED THE TUBULAR MOUNT STRUCTURE TO FLEX FROM SIDE TO SIDE AND CRACK MOST OF THE WAY THROUGH. (K)

MAIN LANDING GEAR ACTUATOR ROD-END FAILED DURING FLIGHT. LANDING GEAR COULD NOT BE LOWERED AND LOCKED DOWN. PILOT MADE A LANDING WITH GEAR UP. THE AIRCRAFT AND THE PARTICULAR PART IN QUESTION WERE INSPECTED 5 HOURS PRIOR WITH NO VISIBLE DISCREPANCY.

Parts most often named Switch (4) · Support (1) · Downlock Switch (1) · Horn (1)

(CAN) PILOT EXPERIENCED NO GEAR DOWN AND LOCK INDICATION LIGHT AFTER GEAR HAD COMPLETED CYCLE. AFTER AN UN-EVENTFUL LANDING AND INSPECTION, FOUND NOSE GEAR DOWNLOCK SWITCH WIRE WAS BROKEN AT BASE OF SWITCH.

FOUND THAT RT MLG DOWNLOCK SWITCH TO BE STUCK IN THE CLOSED POSITION WHICH, WHEN COMBINED WITH THE LT MLG DOWNLOCK SWITCH OPERATING IMPROPERLY, LED TO A LANDING WHERE THE MAIN GEAR COLLAPSED WITH A GREEN DOWN AND LOCKED LIGHT.

ON GEAR RETRACTION, BOTH THE UP AND DOWN LIGHTS WERE ON. PLACED GEAR SELECTOR IN DOWN POSITION AND GEAR STAYED UP. WHEN EMG PUMP GIVEN STROKES, NOSE GEAR STARTED DOWN. THE PUMP THEN CAME ON AND GEARS STARTED TO EXTEND. WHEN THE NOSE GEAR LOCKED DOWN THE PUMP STOPPED, LEAVING MAINS IN TRAIL POSITION. CONTINUED TO PUMP EMG PUMP, BOTH MAINS LOCKED DOWN. ON INSPECTION, GEAR DOWN MAGNET FOR RT GEAR WAS WELDED CLOSED, AND LT WAS INTERMITTENT. REPLACED BOTH SWITCHES AND ALL SYSTEMS OK TO NORMAL.

Parts most often named Camshaft (2) · Crankcase (1) · Crackcase (1) · Shaft (1)

FAILURE OF CONNECTING ROD BOLT DUE TO LOSS OF NUT ON OTHER BOLT. ENGINE HAD FIREWALL FORWARD STC SE2741NM PISTON, CONNECTING ROD AND HARDWARE INSTALLED. ENGINE PROPELLER WAS NOT CORRECT PER STC, NR 3 CYLINDER HAD ONE CONNECTING ROD BOLT SHEARED, THE OTHER ONE WAS HAD SECONDARY DAMAGE WAS IN PLACE IN THE CAP. NO SIGNS OF FAILURE OF THIS BOLT THREADS WERE IN GOOD SHAPE NUT WAS MISSING.

(CAN) ENGINE HAD A PROPELLER STRIKE. PERFORMED A PROPELLER STRIKE INSPECTION AND FOUND WHAT APPEARS TO BE AN INCLUSION OR POSSIBLY A CRACK ON 1 OF THE CAMSHAFT LOBES.

ENGINE WAS OVERHAULED USING MFG PISTON RINGS ST203P010. AFTER 25.4 HRS, RINGS STILL NOT SEATED AND EXCESSIVE BLOW-BY WAS FOULING PLUGS. REPLACED WITH ANOTHER SET OF ST203P010 AFTER HAVING CYLINDERS REWORKED. AFTER 4.2 HRS, ENGINE WAS OPERATING SO POORLY, DUE TO BLOW-BY, THAT IT WAS CONSIDERED UNSAFE AND GROUNDED. INDEPENDENT HARDNESS TESTING BY QUALITY TESTING SVCS, INC, COMFIRMED THE RINGS WERE SOFT. COMPARATIVE TESTS WERE PERFORMED AGAINST PISTON RINGS. AFTER SWITCHING TO OTHER, THERE HAVE BEEN NO PROBLEMS.(K)