AA-5Traveler · Cheetah · Tiger

Parts most often named Valve (6) · Cylinder (3) · Valve Guide (1) · Cover (1)

FRONT PILOT SIDE CYLINDER (#2?) BROKE APART IN FLIGHT. I'M NOT SURE WHICH CYLINDER [S/N removed] BROKE, BUT IT IS ONE OF: 28520-16, 28279-14, 28387-30, 28415-23.

DURING A 100 HOUR INSPECTION, DISCOVERED THAT CYLINDERS NR 1 AND 3 HAD COMPRESSIONS IN THE 20PSI RANGE. ATTEMPTS TO CORRECT THIS WERE NOT SUCCESSFUL. CYLINDERS NR 1 AND 3 WERE REPLACED.

ANNUAL INSPECTION FOUND NO COMPRESSION ON NR 1 CYLINDER. REMOVED CYLINDER, SENT FOR REPAIR. FOUND INTAKE VALVE SEAT INSTALLED WRONG (AT ANGLE) HAD BENT INTAKE VALVE. ALSO, ENGINE HAD NOT BEEN DE-SLUDGED AT OVERHAUL CAUSING PITS. FOUND AT AD INSPECTION AFTER 20 HOURS. (X)

Parts most often named Float (3) · Carburetor (2) · Throtle Body (1) · Screw (1)

ON FINAL APPROACH TO THE AIRPORT, REDUCED POWER AND LOWERED THE FLAPS. TRIED TO ADD POWER, THE THROTTLE BOUND. REMOVED THE THROTTLE CABLE AND IT'S MOVEMENT WAS FREE. THEN ACTUATED THE THROTTLE ARM ON THE CARBURETOR AND BINDING COULD BE FELT ON THE LAST .333 OF THE MOVEMENT. CALLED THE FACTORY AND THEY SAID THERE WERE OTHER OCCURRENCES OF THIS PROBLEM WITH THIS MODEL CARBURETOR. THIS IS A NEW AIRPLANE WITH A NEW CARBURETOR.

OPERATOR REPORTED ENGINE WOULD NOT RUN WELL AT LOW SPEEDS. FOUND CARBURETOR BODY TO BOWL LOOSE. LOCK TABS ARE WERE IN LOCKED POSITIONS. THIS IS THE SECOND OCCURRENCE ON THIS AIRCRAFT IN APPROXIMATELY 200 HRS OF FLYING. THE BOWL THREADS APPEARED TO BE EXCESSIVELY WORN. A [S/N removed] BOWL WAS INSTALLED. EXACT CAUSE COULD NOT BE DETERMINED. GASKET SHRINKAGE IS SUSPECTED [S/N removed] WAS NOT RECORDED.

ENGINE WOULD NOT RUN UNLESS MIXTURE WAS LEANED ALMOST TO IDLE CUT OFF. IT WAS VERY RICH AND WOULD NOT RUN ABOVE 1,500 RPM. FOUND PLASTIC FLOAT TO BE FILLED WITH AVGAS TWO OF THREE CHAMBERS. FLOAT, P/N 30-800, CARBURETOR ASSY DATE, 9-97. (X)

Parts most often named Bracket (2) · Aileron (1) · Counterweight (1) · Skin (1)

AIRCRAFT WAS BEING ANNUALED AND AD 79-22-04 PARA (A)(2) WAS BEING PERFORMED. FOUND THE UPPER SKIN DELAMINATED FROM THE LEADING EDGE AFT FROM 1 INCH TO 4 INCHES AT THE BONDED RIBS.

(AUS) AILERON CONTROL CABLES LOOSE - AILERON BEARINGS WORN - OUTBOARD TORQUE TUBES WORN - TRIM TABS LOOSE - FOUND DURING INSPECTION IAW SB 165A

DURING ANNUAL INSPECTION ON GRUMMAN TIGER AA5B, FOUND LEFT AILERON OUTBOARD BEARING SUPPORT ASSY CRACKED APPROXIMATELY .25 INCH INBOARD OF LOWER BOLT HOLE.

Parts most often named Strut (4) · Nut (1) · Fork (1)

NOSE STRUT DISBONDED AT NOSE FORK BEARING SPINDLE. SPINDLE AND STRUT ARE BONDED VIA A HOT BOND AGENT WHILE IN AUTOCLAVE. SUSPECT DISBONDING OCCURED DUE TO UNREPORTED HARD LANDINGS AND EXTREME STRESS DUE TO IMPROPER GROUND HANDLING.

NOSE WHEEL, FORK, AND FAIRING DEPARTED THE AIRCRAFT IN-FLIGHT. NOSE STRUT FAILED ON LANDING. NO PARTS RECOVERED. NOSE STRUT STUD, WHICH RETAINS NOSE FORK, FAILED ABOVE THREADED AREA. CAUSE UNKNOWN. SUBMITTER RECOMMENDED PERIODIC NDT FOR CRACKS IN STUD.

(AUS) NOSE LANDING GEAR STRUT CORRODED (RUSTED) AND SEIZED IN TORQUE TUBE FITTING - PROTECTION BOOT OLD AND DETERIORATED

Parts most often named Bracket (4) · Seat Belt (1)

SUBJECT BRACKETS ATTACH PILOT'S SEAT BACK TO SEAT PAN. THESE BRACKETS ARE ALUMINUM AND WHEN BACK SEAT PASSENGER PULLS PILOT'S SEAT AFT (TO ASSIST GETTING OUT), THESE BRACKETS FLEX AND WILL FAIL. ALL BRACKETS ON THIS AIRCRAFT HAVE CRACKED OR TOTALLY FAILED. IF THESE BRACKETS FAIL, THE PILOT'S SEAT BACK WILL FALL INTO THE BACK SEAT AND UNDER CERTAIN FLIGHT CONTDITIONS COULD RESULT IN LOSS OF CONTROL. SUBMITTER STATED FIX WAS TO INSTALL STEEL BRACKETS.

DURING LANDING APPROACH, BACK OF PILOT'S SEAT BROKE LOOSE. LANDING WAS MADE WITHOUT INCIDENT. SEAT BACK BRACKET ON RIGHT SIDE OF PILOT'S SEAT (P/N 5102328-26) HAD BROKEN CLEAN THROUGH. EXAMINATION INDICATED PART HAD PREVIOUSLY BEEN CRACKED AND FINALLY PARTED. SUBMITTER RECOMMENDED SEAT BRACKETS BE PERIODICALLY INSPECTION.

DURING GROUND RUN-UP, THE SEAT BRACKETS FAILED ALMOST SIMULTANEOUSLY ALLOWING THE PILOT'S SEAT BACK TO FALL INTO THE REAR SEAT AREA. FAILURE APPEARS TO BE BENDING FATIGUE, A FLEXURE OF THESE ALUMINUM BRACKETS IS NOTED WHEN THE TOP OF THE SEAT IS PULLED AFT (PASSENGER EXITING THE AIRCRAFT). THE LATER MODEL, AG5-B, HAS STEEL BRACKETS. THERE WAS NO EVIDENCE OF A PREVIOUS CRACK PRIOR TO FAILURE.

Parts most often named Angle (2) · Stiffener (1) · Nut (1) · Nutplate (1)

MAINT NOTICED A CLICKING NOISE AND EXCESSIVE MOVEMENT WHEN APPLYING UP AND DOWN PRESSURE TO HORIZONTAL STABILIZER TIPS. FOUND DELAMINATION, CRACKS AND WRINKLES IN HORIZONTAL STAB FWD SPAR CARRY-THROUGH ATTACH ANGLES INSIDE EMPENNAGE. WE BELIEVE THE SINGLE MOST CAUSE TO BE PILOTS AND MAINT PUSHING DOWN ON THE FWD SSPAR AREA TO RAISE THE NOSEWHEEL OFF THE GROUND. (K)

CRACKS IN TWO STIFFENERS AT HORIZONTAL STABILIZER SPAR, ONE RT SIDE OF FUSELAGE ABOVE THE SPAR. THE OTHER IN HORIZONTAL STIFFENER LOWER LEFT SIDE. FOUND WHILE INSPECTING IAW SPECIAL AIRWORTHINESS INFORMATION BULLETIN NR CE-04-34.

(CAN) AIRCRAFT DAMAGED IN LANDING ACCIDENT. WHEN HORIZONTAL STABILIZER WAS BEING REINSTALLED AFTER REPAIR, A BOLT WOULD NOT REACH PROPER TORQUE. HORIZONTAL STABILIZER WAS REMOVED AND IT WAS FOUND THAT 4 OF THE 8 FRONT SPAR ANCHOR NUTS WERE CRACKED.

Parts most often named Aileron (2) · Control Cable (1)

DURING ANNUAL INSPECTION, FOUND BOTH AILERONS TO HAVE CONTROL LOOSENESS INTERNALLY. REMOVED AILERON ASSYS AND FOUND BOTH TO HAVE LOOSE RIVETS AT TORQUE TUBE TO AILERON ATTACHMENT. SUSPECT AIRCRAFT EXPERIENCED HIGH WINDS FROM REAR WHILE PARKED. GUST LOCKS ON AILERONS PROPER, WOULD PREVENT THIS.

Parts most often named Shoulder Bolt (2) · Bolt (1)

DURING C/W AD 95-19-15, ONE OF THE FOUR INBOARD WING ATTACH BOLTS WAS FOUND TO HAVE BEEN INCORRECTLY MANUFACTURED, WITH AN AREA OF THE THREADED SHANK MISSING, AND AN AREA OF THE HEX HEAD MIS-MACHINED.

PART OF HANGAR FELL ON TAIL ASSEMBLY RENDERING PLANE UNFLYABLE. WHEN REMOVED WINGS FOR TRANSPORTATION TO REPAIR SHOP, A RIGHT WING SHOULDER ATTACH BOLT WAS SHEARED (DID NOT HAPPEN WHEN THE TAIL WAS DAMAGED). ONLY TWO HOURS SINCE ANNUAL. AD IN EFFECT, 94-CE-15-AD.

Parts most often named Support Angle (2) · Nutplate (1)

AIRCRAFT WAS INSPECTED IAW CE-04-34. BUCKLING WAS FOUND ON BOTH OF THE SUPPORT ANGLES (1 AND 2) JUST BELOW THE HORIZONTAL STAB. MOUNTING BOLTS. SMALL CRACKS FOUND AT THE TOP OF THESE SUPPORT ANGLES. MINOR BUCKLE FOUND AT LT SIDE OF LOWER STIFFENER AT ARROW NUMBER 7.

AIRCRAFT WAS INSPECTED IAW SAIB CE-04-34. BUCKLING WAS FOUND ON BOTH OF THE SUPPORT ANGLES JUST BELOW THE HORIZONTAL STAB. MOUNTING BOLTS. SMALL CRACKS FOUND AT THE TOP OF THESE SUPPORT ANGLES. MINOR BUCKLE FOUND AT LT SIDE OF LOWER STIFFENER AT ARROW NUMBER 7 IN SAIB PICTURE.

ALL EIGHT NUTPLATES FOUND CRACKED ON FORWARD HORIZONTAL SPAR ATTACH. SUSPECT CAUSE SITTING ON TAIL TO PARK AIRCRAFT. NUTPLATES WERE FOUND AFTER REMOVING STABILIZER FOR REPAIR AND CANNOT BE SEEN ON NORMAL INSPECTION. SUBMITTER WOULD RECOMMEND REMOVING STABILIZER EVERY 500 HOURS FOR VISUAL INSPECTION.

Parts most often named Line (1) · Fitting (1) · Hose (1)

ENGINE AIR BREATHER PINCH HOLE HAD B EEN ELIMINATED BY PARTIES UNKNOWN. BREATHER LINE FROZE SHUT AT 15,000 FEET. EXCESSIVE CRANKCASE PRESSURE CAUSED THE CRANKSHAFT OIL SEAL TO LEAK OIL. BREATHER LINE WAS REPOSITIONED AND A PINCH HOLE WAS DRILLED.

OIL PRESSURE FITTING AT ENGINE TO GAUGE HAD BRASS FITTING AND THEN 90 DEGREE RESTRICTIVE FITTING. APPEARS TO HAVE BEEN TOO CLOSE TO MOUNT. BRASS FITTING BROKE FLUSH AT ACCESSORY CASE AND OIL PUMPED OUT OF ENGINE. BRASS FITTING APPEARED TO BE INCORRECT PART NUMBER.