N771EA
Registered owner: HYANNIS AIR SERVICE INC, MA (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| HYANNIS AIR SERVICE INC. (HYIA) | Certificate holder | — | Matched by certificate designator |
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
DURING MAINTENANCE A CRACK WAS IDENTIFIED ON THE INBOARD LEG OF THE RIGHT HAND INBOARD NACELLE FITTING, (P/N: 5292029-22) THIS CRACK MEASURES APPROXIMATELY .157 INCHES LONG AND WAS DISCOVERED USING THE LIGHTED BORESCOPE INSPECTION PROCEDURE AS OUTLINED IN TEXTRON MEL-54-02R2 TO SATISFY AD2017-10-09. THIS CRACK IS CONSISTENT WITH OTHERS THAT HAVE BEEN IDENTIFIED USING THE SAME INSPECTION PROCEDURE. THIS FITTING WILL BE REPLACED USING NEW PARTS.
DURING MAINTENANCE A CRACK WAS FOUND ON THE AFT SIDE OF THE LEFT NACELLE CROSSOVER BEAM (P/N: 5654104-11) THIS CRACK BEGINS AT THE UPPER INBOARD FASTENER HOLE COMMON TO THE TURBOCHARGER MOUNTING BRACKET, AND MEASURES APPROXIMATELY .371 INCHES LONG. THIS BEAM WILL BE REPLACED WITH A NEW BEAM.
DURING MAINTENANCE CORROSION DAMAGE WAS FOUND ON THE RIGHT WING AFT LOWER CAP (P/N: 5122041-24). THIS CORROSION IS LOCATED AT APPROXIMATE RIGHT WING STATION 204.71 AND MEASURES APPROXIMATELY .019 DEEP. THIS IS GREATER THAN REMOVABLE LIMITS ALLOWED UNDER MEB95-11R1 SEC. 3. THIS PART WILL BE REPLACED WITH A FACTORY NEW PART.
DURING MAINTENANCE A CRACK WAS FOUND ON THE RIGHT HAND CLOSE OUT RIB LOCATED AT RIGHT WING STATION 106.79 (P/N: 5122115-56). THIS CRACK STARTS FROM A HOLE IN THE FORWARD ROW OF FASTENERS COMMON TO THE AFT TRUNNION PLATE AND TRAVELS FORWARD APPROXIMATELY .595 INCHES. THIS RIB WILL BE REPLACED WITH A FACTORY NEW PART.
DURING MAINTENANCE CORROSION WAS FOUND ON THE RIGHT HAND UPPER AFT WING FITTING (P/N: 0822550-46) THIS CORROSION MEASURED 1.612 INCHES LONG, .434 INCHES WIDE, AND .025 INCHES DEEP. THIS FITTING WILL BE REPLACED WITH A FACTORY NEW PART.
WHILE CONDUCTING OTHER MAINTENANCE, AN AREA OF CORROSION WAS NOTED ON THE FUSELAGE FRAME ASSEMBLY AT F.S. 214.00, JUST ABOVE THE 501110-12 STRIKER PLATE FOR THE LOWER PASSENGER DOOR PIN. THE 501110-12 STRIKER PLATE WAS REMOVED FOR FURTHER INSPECTION. UPON REMOVAL OF THE STRIKER PLATE, MORE CORROSION WAS DISCOVERED. THIS AREA OF CORROSION WAS MEASURED AT 2.10 HIGH BY .68 WIDE, WITH A DEPTH OF .055. THE FUSELAGE FRAME AND STRIKER PLATE WILL BE REPLACED WITH NEW PARTS.
DURING MAINTENANCE CORROSION WAS DISCOVERED ON THE LEFT SIDE AFT VERTICAL ANGLE (P/N: 5131007-5) OF THE VERTICAL STABILIZER BETWEEN APPROXIMATE W.L. 142.514 AND 145.380. THIS CORROSION IS 2.866 INCHES LONG, AND HAS EXFOLIATED THE FLANGE OF THE ANGLE FROM ITS ORIGINAL THICKNESS OF .150 TO .239. THIS ANGLE WILL BE REPLACED WITH FACTORY NEW PARTS. PLEASE SEE PICTURE AND MEASUREMENTS ATTACHED TO THIS SDR FOR FURTHER DETAILS.
WHILE REPAIRING A FUEL LEAK, CORROSION WAS DISCOVERED IN TWO PLACES INSIDE THE FUEL TANK, ON THE FORWARD RADIUS OF THE RT AFT OUTBOARD SPAR CAP. THE FIRST AREA OF CORROSION WAS DISCOVERED AT WS 208.1 AND WAS 1 INCH IN LENGTH. THE SECOND AREA WAS LOCATED AT WS 190.21 AND MEASURED 6.5 INCHES IN LENGTH. BOTH AREAS OF CORROSION WERE DEEPER THAN THE ALLOWABLE REMOVAL LIMITS. THE SPAR CAP WAS CHANGED WITH NEW.
WHILE PREPPING THE LOWER NACELLE SKIN FOR SID 57-10-16 NDT INSPECTION, A CRACK WAS IDENTIFIED IN THE RT INBOARD NACELLE FITTING.
PILOT REPORTED ELEVATOR VIOLENT SHUDDER AND PITCH DOWN WITH THE AMOUNT OF NOSE DOWN REQUIRED FOR 500 FPM DESCENT AT CRUISE POWER. MAINTENANCE PERFORMED INSPECTION OF ELEVATOR SYSTEM AND FOUND THE ELEVATOR TRIM TAB BINDING AND APPEARED TO HAVE SIGNIFICANT AMOUNTS OF PLAY BETWEEN THE THREADED ROD AND ACTUATOR BUSHING. TEAR DOWN INSPECTION REVEALED THE ACTUATOR SCREW AND SHAFT WERE WORN BEYOND LIMITS.
DURING TAXI & TAKEOFF CLIMB, LT RUDDER POPS, LOUD SOUND, & SEEMS TO BIND. DURING INSPECTION RUDDER SYS FOUND LT RUDDER TUBE GUIDE INTERCONNECT SPRING ATTACHING PART CLAMP & TUBE GUIDE LOOSE. RE-POSITIONED LT RUDDER TUBE GUIDE, ADJUSTED & SECURED TUBE GUIDE CLAMP IAW MM CHAPTER 27-20-00 & 27-20-01. OPERATIONS CHECK DURING TAXI WORKING PROPERLY.
THE LT NACELLE OTBD ENG BEAM WAS FOUND TO BE CRACKED JUST FWD OF AFT ENG MOUNT, TRANSVERSE TO LENGTH OF BEAM, ACROSS UPPER FACE OF BEAM, DURING NDT PRESCRIBED WITHIN MEL-54-01. REMOVE BEAM ASSEMBLY, PERFORM DETAILED VISUAL INSPECTION OF SURROUNDING STRUCTURE & INSTALL NEW BEAM ASSEMBLY. A SUPPLEMENT TO THIS SDR WILL BE SUBMITTED ILLUSTRATING RESULT OF X-RAY.
THE RT NACELLE OTBD ENG BEAM WAS FOUND TO BE CRACKED JUST FWD OF AFT ENG MOUNT, TRANSVERSE TO LENGTH OF BEAM, ACROSS UPPER FACE OF BEAM, DURING NDT PRESCRIBED WITHIN MEL-54-01. REMOVE BEAM ASSEMBLY, PERFORM DETAILED VISUAL INSPECTION OF SURROUNDING STRUCTURE & INSTALL NEW BEAM ASSEMBLY. A SUPPLEMENT TO THIS SDR WILL BE SUBMITTED ILLUSTRATING RESULT OF X-RAY.
DURING PREFLIGHT, THE CREW REPORTED A FUEL ODOR IN THE COCKPIT. MX DETERMINED THERE WAS A FUEL LEAK OTBD OF THE NACELLE AND FOUND A CHAFED FUEL LINE AFT OF FORWARD FLOAT VALVE. BOTH DISCREPANCIES WERE REPAIRED AND LEAK CHECK ACCOMPLISHED.
AT SCHEDULED INSPECTION, NLG DRAG BRACE, OEM PN 5142002-5, WAS FOUND TO BE CRACKED IN THE AREA OF NLG ACTUATOR ATTACH POINT. METHOD OF INSPECTION WAS DYE PENETRANT. THIS CRACK WAS FOUND TO BE WITHIN ALLOWABLE LIMIT. THIS UNIT HAS BEEN REPAIRED IAW PROCEDURE OUTLINED IN MEB941-11R1 & RETURNED TO SERVICE.
CREW REPORTED AVIONIC MASTER SWITCH INOPERATIVE. MX REMOVED AND REPLACED SWITCH, AND RETURNED ACFT TO SERVICE
CREW REPORTED, DURING CRUISE LEVEL FLIGHT, 658 ENGINE BEGAN TO SURGE +/- 400 RPM. AFTER REDUCING POWER, AIRCRAFT LANDED WITHOUT INCIDENT. MECHANIC FOUND 6 FT PROP GOVERNOR FAILED. MECHANIC CHANGED GOVERNOR AND RELEASED AIRCRAFT BACK TO SERVICE.(K)
ON LANDING, AFT BRAKE LOCKED UP, AND MAIN WHEEL SEIZED. MAINTENANCE FOUND ONE CALIPER ANCHOR PIN SHEARED. REMOVED AND REPLACED MAIN WHEEL ASSY, BRAKE CALIPER, AND BRAKE BACKPLATE ASSY, THEN RETURNED AIRCRAFT TO SERVICE. AT THIS TIME, ALL ANCHOR PINS ARE BEING CHANGED IN THE OPERATOR''S FLEET. (X)