# Service difficulty reports: N771EA A list on [N771EA](https://openairdocs.org/aircraft/N771EA.md). Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first. - [SDR HYIA20210208001](https://openairdocs.org/sdr/HYIA20210208001.md): Fitting · cracked · Feb 8, 2021 · N771EA · Cessna 402C · Nacelle/Pylon, Attach Fittings > 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 TEXT - [SDR HYIA20181003007](https://openairdocs.org/sdr/HYIA20181003007.md): Beam · cracked · Oct 3, 2018 · N771EA · Cessna 402C · Nacelle/Pylon, Main Frame > 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 W - [SDR HYIA20181003005](https://openairdocs.org/sdr/HYIA20181003005.md): Angle · corroded · Oct 3, 2018 · N771EA · Cessna 402C · Vertical Stabilizer Miscellaneous Structure > 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 O - [SDR HYIA20181003004](https://openairdocs.org/sdr/HYIA20181003004.md): Door Frame · corroded · Oct 3, 2018 · N771EA · Cessna 402C · Fuselage Main, Structure > 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 REMO - [SDR HYIA20181003003](https://openairdocs.org/sdr/HYIA20181003003.md): Fitting · corroded · Oct 3, 2018 · N771EA · Cessna 402C · Wing Miscellaneous Structure > 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. - [SDR HYIA20181003002](https://openairdocs.org/sdr/HYIA20181003002.md): Rib · cracked · Oct 3, 2018 · N771EA · Cessna 402C · Wing, Rib/Bulkhead > 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 I - [SDR HYIA20181003001](https://openairdocs.org/sdr/HYIA20181003001.md): Spar Cap · corroded · Oct 3, 2018 · N771EA · Cessna 402C · Wing Spar > 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- - [SDR HYIA08242017001](https://openairdocs.org/sdr/HYIA08242017001.md): Spar Cap · corroded · Aug 15, 2017 · N771EA · Cessna 402C · Wing Spar > 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 W - [SDR HYIA20170705002](https://openairdocs.org/sdr/HYIA20170705002.md): Fitting · cracked · Jul 5, 2017 · N771EA · Cessna 402C · Nacelle/Pylon, Attach Fittings > WHILE PREPPING THE LOWER NACELLE SKIN FOR SID 57-10-16 NDT INSPECTION, A CRACK WAS IDENTIFIED IN THE RT INBOARD NACELLE FITTING. - [SDR HYIA20160815001](https://openairdocs.org/sdr/HYIA20160815001.md): Shaft · worn · Aug 12, 2016 · N771EA · Cessna 402C · Elevator Tab Control System > 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 AMOU - [SDR HYIA20160520001](https://openairdocs.org/sdr/HYIA20160520001.md): Clamp · loose · May 13, 2016 · N771EA · Cessna 402C · Rudder Control System > 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 C - [SDR HYIA03272015006](https://openairdocs.org/sdr/HYIA03272015006.md): Beam · cracked · Mar 27, 2015 · N771EA · Cessna 402C · Nacelle/Pylon Miscellaneous Structure > 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 - [SDR HYIA03272015005](https://openairdocs.org/sdr/HYIA03272015005.md): Beam · cracked · Mar 27, 2015 · N771EA · Cessna 402C · Nacelle/Pylon Miscellaneous Structure > 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 - [SDR HYIA20136011103](https://openairdocs.org/sdr/HYIA20136011103.md): Fuel Line · chafed · May 27, 2013 · N771EA · Cessna 402C · Engine Fuel Distribution > 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. - [SDR HYIA20140415053](https://openairdocs.org/sdr/HYIA20140415053.md): Drag Brace · cracked · Apr 18, 2011 · N771EA · Cessna 402C · Landing Gear Retraction/Extension System > 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 - [SDR HYIA771EA 619](https://openairdocs.org/sdr/HYIA771EA%20619.md): Master Switch · unserviceable · Jun 19, 2009 · N771EA · Cessna 402C · Electrical Power System > CREW REPORTED AVIONIC MASTER SWITCH INOPERATIVE. MX REMOVED AND REPLACED SWITCH, AND RETURNED ACFT TO SERVICE - [SDR HYI2003F00018](https://openairdocs.org/sdr/HYI2003F00018.md): Governor · unserviceable · Oct 31, 2003 · N771EA · Cessna 402C · Propeller Governor > 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) - [SDR 20000808SH014](https://openairdocs.org/sdr/20000808SH014.md): Pin · destroyed · Jul 12, 2000 · N771EA · Cessna 402C · Brake > 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 BEI ## The whole list in SQL Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS: ```sql SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE n_number = 'N771EA' AND registry_match = 'registration' ORDER BY difficulty_date DESC ``` This list as a web page: https://openairdocs.org/aircraft/N771EA/reports --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.