# Johnson Philip B 404 - Type: Aircraft model (FAA registry) - Registry code: 056231G - Manufacturer (registry): JOHNSON PHILIP B - Model: 404 - Aircraft type: Fixed wing single engine - Category: Airplane - Engines: 1 · 2 cycle - Seats: 1 - Weight class: Up to 12,499 lb - Certification: Not type certificated - Registered aircraft: 1 - Page: https://openairdocs.org/model/johnson-philip-b-404 Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker. ## ADs that may apply (OpenAirDocs) Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. None matched. ## Registered aircraft (1) - [N8852](https://openairdocs.org/aircraft/N8852): [Johnson Philip B](https://openairdocs.org/faa-owner/JOHNSON%20PHILIP%20B), [North Grafton, MA](https://openairdocs.org/faa-place/MA/North%20Grafton), built 2008, S/N 4025 ## NTSB investigations None matched to aircraft with this model. ## FAA accident and incident reports None matched to aircraft with this model. ## Service difficulty reports (53, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR 2024FA0000433](https://openairdocs.org/sdr/2024FA0000433), May 26, 2024: ENGINE. POWER LOSS. ON DEPARTURE FROM KBFL, THE LEFT ENGINE LOST POWER SHORTLY AFTER TAKEOFF, THE ENGINE RETAINED PARTIAL POWER AND THE PROPELLER WAS NOT FEATHERED. THE PILOT IMMED - [SDR 2023FA0000115](https://openairdocs.org/sdr/2023FA0000115), Jan 27, 2023: LANDING GEAR. INOPERATIVE. PILOT REPORTED RIGHT LANDING GEAR WOLD NOT EXTEND, WHEN SELECTED. THE EMERGENCY BLOW DOWN BOTTLE WAS ACTIVATED AND ALL GEARS CAME DOWN AND LOCKED. - [SDR HTKA202001080000](https://openairdocs.org/sdr/HTKA202001080000), Nov 14, 2019: ENGINE. FAILED. ENGINE FAILED IN FLIGHT. NUMBER 1 CONNECTING ROD AND (CRANK END) PROTRUDING THROUGH TOP OF ENGINE CASE. RIGHT MAGNETO BROKEN OFF ITS MOUNT. THE ENGINE HAS BEEN - [SDR 2020FA0000006](https://openairdocs.org/sdr/2020FA0000006), Oct 28, 2019: ENGINE. MALFUNCTIONED. ENGINE DEVELOPED LOW OIL PRESSURE IN FLIGHT APPROX 20 PSI. REMOVED AND CLEANED OIL PRESSURE RELIEF PLUNGER. FOUND CARBON BITS IN OIL FROM CAVITY. ABOUT 20 HOURS - [SDR HTKA2020010800001](https://openairdocs.org/sdr/HTKA2020010800001), Aug 16, 2019: ENGINE. FAILED. ENGINE FAILED IN FLIGHT. NR 5 AND NR 6 CONNECTING ROD (CRANK END) PROTRUDING THROUGH TOP OF ENGINE CASE. HOLES IN BOTH SIDES OF CASE BELOW NR 5 AND NR 6 CYLINDE - [SDR DUFA20190619001](https://openairdocs.org/sdr/DUFA20190619001), Jun 15, 2019: CASE. CRACKED. WHILE ON A ONE MILE FINAL APPROACH, THE RIGHT HAND ENGINE DEVELOPED A SEVERE VIBRATION AND BEGAN TO LOSE POWER. THE AUXILIARY FUEL PUMP WAS SELECTED TO HIGH BUT - [SDR DUFA20170330001](https://openairdocs.org/sdr/DUFA20170330001), Mar 28, 2017: LINE. FAILED. DEPARTED, SELECTED GEAR UP AND SHORTLY AFTER BEGAN TO GET A PETROLEUM ODOR IN THE CABIN. IMMEDIATELY AFTER THAT THE LEFT HYD FLOW ANNUNCIATOR LIGHT ILLUMINATED, - [SDR DUFA20140506002](https://openairdocs.org/sdr/DUFA20140506002), May 6, 2014: HOSE. DETERIORATED. WHILE IN CRUISE FLIGHT, THE PILOT NOTICED THE LT ENG OIL PRESS DROPPING. ONCE THE OIL PRESS DROPPED BELOW THE GREEN ARC, SHUT DOWN THE LT ENG & CONTACTED CTR. D - [SDR BGJA2014042300002](https://openairdocs.org/sdr/BGJA2014042300002), Apr 3, 2014: ALTERNATOR. FAILED. THE ACFT HAD TOTAL ELECTRICAL FAILURE DURING FLIGHT, DUE TO BOTH CHARGING SYSTEMS FAILING TOGETHER. RT ALTERNATOR FAILED DURING CRUISE, SHORTLY AFTER LT ALTERNA - [SDR BGJA201404230001](https://openairdocs.org/sdr/BGJA201404230001), Apr 3, 2014: CLUTCH. FAILED. DURING FLIGHT, THE LT ENGINE ALTERNATOR STOPPED PRODUCING POWER DUE TO THE DRIVE CLUTCH SLIPPING. AFTER LANDING, REMOVED ALTERNATOR AND CHECKED THE DRIVE CLUTCH - [SDR KY7A20131204001](https://openairdocs.org/sdr/KY7A20131204001), Dec 4, 2013: GASKET. FAILED. PRIOR TO DEPARTURE FROM DEN, THE PILOT REPORTED THAT THE LT PNEUMATIC PUMP WAS INOPERATIVE. MX REPLACED THE PNEUMATIC PUMP & THE ACFT DEPARTED, CRUISING AT FL20 - [SDR KY7A20120727002](https://openairdocs.org/sdr/KY7A20120727002), Jul 26, 2012: OIL SYSTEM. LOW PRESSURE. PILOT REPORTED THAT WHEN CONFIGURING THE ACFT FOR CRUISE FLIGHT THE LT ENGINE MANIFOLD PRESSURE DECREASED. PILOT NOTED THAT THE OIL PRESSURE WAS DECLINING AND S - [SDR KY7A12052501](https://openairdocs.org/sdr/KY7A12052501), May 25, 2012: HINGE. CRACKED. NLG FAILED TO EXTEND DURING NORMAL OPERATIONS DURING TRAINING FLIGHT. FLIGHT CREW PERFORMED EMERGENCY LANDING GEAR EXTENSION PROCEDURES; NOSE GEAR EXTENDED AND - [SDR CA120227001](https://openairdocs.org/sdr/CA120227001), Feb 12, 2012: INDICATION SYS. SPLIT. (CAN) DURING SCHEDULED PRE-FLIGHT AUTO-FEATHER CHECKS, THE PILOTS REPORTED A TORQUE SPLIT OF 300 LB FT, NR 2 LAGGING. AFTER RETURNING TO THE RAMP, RETARDING & A - [SDR 2010FA0000387](https://openairdocs.org/sdr/2010FA0000387), Apr 1, 2010: BRACKET. BROKEN. (H12R) PREFLIGHT CONTROL CHECKED GOOD, THE ELEVATOR WAS HITTING THE CONTROL STOPS, ON TAKEOFF THE ACFT HAD PARTIAL ELEVATOR CONTROL, ON LANDING THE ACFT HAD PAR - [SDR KY7A14756](https://openairdocs.org/sdr/KY7A14756), Jul 6, 2009: CONTROL CABLE. WORN. ALL FOUR AILERON PRIMARY CONTROL CABLES FOUND WORN, SEVERING SEVERAL STRANDS AT WING STATION 50.021 WHERE IS PASSES IN FRONT OF THE OUTBOARD FLAP BELLCRANK. ONE - [SDR KY7A14634A](https://openairdocs.org/sdr/KY7A14634A), Jun 5, 2009: LINE. FRACTURED. HYDRAULIC PRESSURE LINE FAILURE IN RIGHT WING LEADING EDGE BETWEEN FLOW VALVE AND FILTER HOUSING OCCURRED IN 90° BEND. - [SDR KY7A14634](https://openairdocs.org/sdr/KY7A14634), Jun 5, 2009: LINE. FAILED. HYDRAULIC LINE FAILURE CAUSED TOTAL LOSS OF FLUID PREVENTING NORMAL GEAR EXTENSION. EMERGENCY BLOWDOWN FAILED DUE TO FAILURE OF PNEUMATIC LINE FAILURE AT BLOWDO - [SDR 2009FA0000483](https://openairdocs.org/sdr/2009FA0000483), May 27, 2009: LINE. CRACKED. HYDRAULIC FLUID DEPLETION HAVE OCCURRED. (TWO WERE FLAP FAILURE TO EXTEND AND ONE THE LANDING GEAR HAD TO BE EXTENDED USING THE EMERGENCY EXTENSION SYS. THESE F - [SDR GNB2009F00000](https://openairdocs.org/sdr/GNB2009F00000), May 26, 2009: SLEEVE. CRACKED. AFTER TAKEOFF, PILOT FELT ENGINE RUNNING ROUGH. ACFT RETURNED TO FIELD. MX DISCOVERED NR 2 CYLINDER UPPER DECK NOZZLE TUBE CRACKED. POSSIBLE WEAK WELD OF OUTSID - [SDR M7JA2009030200001](https://openairdocs.org/sdr/M7JA2009030200001), Sep 13, 2008: ENGINE. MALFUNCTIONED. IN CRUISE FLIGHT THE CAPTAIN NOTICE A DROP IN THE RT ENGINE OIL PRESSURE WITH INCREASE IN OIL TEMP. THERE WAS NOT VIBRATION OR VISIBLE OIL LEAKS ON THE MENTION - [SDR DUFA20070002](https://openairdocs.org/sdr/DUFA20070002), Apr 10, 2007: STUD. SHEARED. WHILE ON APPROACH TO AIRPORT, THE PILOT NOTICED MANIFOLD PRESSURE DROPPING AS WELL AS OIL PRESSURE FROM THE RIGHT ENGINE. HE ALSO BEGAN TO FEEL A VIBRATION FROM - [SDR DUFA041007001](https://openairdocs.org/sdr/DUFA041007001), Apr 10, 2007: STUD. SHEARED. WHILE ON APPROACH TO AIRPORT, THE PILOT NOTICED MANIFOLD PRESSURE DROPPING AS WELL AS OIL PRESSURE FROM THE RT ENGINE. HE ALSO BEGAN TO FEEL A VIBRATION FROM TH - [SDR 2007FA0000226](https://openairdocs.org/sdr/2007FA0000226), Feb 20, 2007: ENGINE. FAILED. THIS ENGINE FAILED TO THE TERMINOLOGY OF CATASTROPHIC AT THE NR 1 AND NR 2 CYLINDER CONNECTING ROD LOCATIONS DURING A MAINTENANCE TEST FLIGHT WITHIN TEN MINUTES - [SDR BAC001](https://openairdocs.org/sdr/BAC001), Aug 2, 2006: LINE. DISCONNECTED. PILOT REPORTED THAT WHILE IN CRUISE FLIGHT THE LEFT ENGINE FUEL FLOW SUDDENLY DROPPED OFF AND THE ENGINE BEGAN TO RUN ROUGH AND LOSE POWER. THE BOOST PUMP WAS S - [SDR BAC005](https://openairdocs.org/sdr/BAC005), Aug 2, 2006: TUBE. DISCONNECTED. PILOT REPORTED THAT WHILE IN CRUISE FLIGHT THE LT ENGINE FUEL FLOW SUDDENLY DROPPED OFF AND THE ENGINE BEGAN TO RUN ROUGH AND LOSE POWER. THE BOOST PUMP WAS SEL - [SDR BGJ2006F00000](https://openairdocs.org/sdr/BGJ2006F00000), Jan 6, 2006: CYLINDER. CRACKED. THE AIRCRAFT WAS IN CRUISE POWER CONFIGURATION. NR 5 CYLINDER BARREL ON RT ENGINE CRACKED AND SEPARATED APPROXIMATELY 3 INCHES FROM MOUNTING BASE IN THE BARREL - [SDR AU510002176](https://openairdocs.org/sdr/AU510002176), Dec 12, 2005: CONNECTOR. FAULTY. (AUS) RT MAIN LANDING GEAR DOWN MICROSWITCH WIRE CONNECTOR FAULTY. SUSPECT CONNECTOR WAS NOT AN APPROVED ITEM. (OTHER CAUSE: MAINTENANCE CONTROL ISSUE ) (CASA N - [SDR AU510001970](https://openairdocs.org/sdr/AU510001970), Dec 12, 2005: HUB. CORRODED. PROPELLER HUB CORRODED BEYOND LIMITS IN BLADE SOCKET AREA. - [SDR AU510001816](https://openairdocs.org/sdr/AU510001816), Dec 12, 2005: STUD. BROKEN. RT ENGINE NR 5 CYLINDER HOLD-DOWN STUDS (2OFF) BROKEN OFF FLUSH WITH THE CYLINDER BASE. - [SDR AU510001799](https://openairdocs.org/sdr/AU510001799), Dec 12, 2005: SWITCH. UNSERVICEABLE. (AUS) RT MAIN LANDING GEAR UPLOCK MICROSWITCH FAILED. SWITCH HAD ONLY 54.5 HOURS OPERATION SINCE REPLACEMENT. (CASA NR 510001799) - [SDR AU510001730](https://openairdocs.org/sdr/AU510001730), Dec 12, 2005: BEARING. COLLAPSED. RT ENG DRIVEN ALT FAILED. ALT DRIVE COUPLING SHEARED AND ALT FRONT BEARING COLLAPSED. RED ELASTOMER MAT`L FROM ALT DRIVE COUPLING AND MINOR METALLIC PARTICLES V - [SDR AU510001695](https://openairdocs.org/sdr/AU510001695), Dec 12, 2005: BEARING. DAMAGED. ENGINE METAL CONTAMINATION. BULK STRIP FOUND THAT THE TWO REARMOST MAIN BEARINGS WERE DAMAGED. INSPECTION OF THE CRANKSHAFT IN THE VICINITY OF THE TWO REARMOST - [SDR AU510001619](https://openairdocs.org/sdr/AU510001619), Dec 12, 2005: HEATER. FAULTY. (AUS) CABIN HEATER FAULTY. SMOKE IN CABIN. INVESTIGATION FOUND THE FORWARD VENT BLOWER INOPERATIVE DUE MOTOR BRUSH HANGUP. INSPECTION OF THE HEATER FOUND DISCOL - [SDR AU510001530](https://openairdocs.org/sdr/AU510001530), Dec 12, 2005: UPLOCK SWITCH. FAILED. LT MAIN LANDING GEAR UPLOCK MICROSWITCH FAULTY. - [SDR AU510001489](https://openairdocs.org/sdr/AU510001489), Dec 12, 2005: BEARING. FAILED. (AUS) ENGINE METAL CONTAMINATION. WORKSHOP STRIP AND INVESTIGATION FOUND NR 2 AND NR 3 MAIN BEARINGS FAILED. BEARING SHELLS BROKE UP CAUSING DAMAGE TO CRANKCASE - [SDR AU510001447](https://openairdocs.org/sdr/AU510001447), Dec 12, 2005: BOLT. BROKEN. (AUS) ENGINE INTERNAL DAMAGE. SUSPECT CAUSED BY FAILURE OF NR 5 CONNECTING ROD BOLT OR CONNECTING ROD. INVESTIGATION CONTINUING. - [SDR AU510001529](https://openairdocs.org/sdr/AU510001529), Sep 6, 2005: UPLOCK SWITCH. DAMAGED. LT MAIN LANDING GEAR MICROSWITCH DAMAGED INTERNALLY. - [SDR AU510002082](https://openairdocs.org/sdr/AU510002082), Aug 11, 2005: CIRCUIT CARD. FAILED. GPS DATA CARD FAILED. - [SDR 2005FA0000621](https://openairdocs.org/sdr/2005FA0000621), Apr 11, 2005: CONTROL CABLE. DAMAGED. DURING INSPECTION, FOUND CABLE TO BE BLENDED AT FAIRLEAD APPROX 6 INCHES FROM AFT END OF CABLE. PROBABLE CAUSE FROM NEW STYLE (STAINLESS STEEL) CABLE. NEW STYLE - [SDR AU510001856](https://openairdocs.org/sdr/AU510001856), Mar 6, 2005: SWITCH. FAILED. LT ENGINE STARTER SWITCH FAILED. SWITCH REMAINED ENGAGED. - [SDR GNB2005F00003](https://openairdocs.org/sdr/GNB2005F00003), Jan 11, 2005: LINE. CORRODED. FAILED HYDRAULIC PRESSURE CHECK. LINE LAYING ON DUCTING FOR HEATING CAUSING CORROSION TO FORM. (SW01200502894) (K) - [SDR 2004F00429](https://openairdocs.org/sdr/2004F00429), Nov 29, 2004: SENSOR. BURNED OUT. WHILE IN CRUISE FLIGHT, THE PILOT NOTICED SPARKS COMING FROM THE LEFT ENGINE FORWARD COWL AREA. AS A PRECAUTION, THE ENGINE WAS SHUTDOWN AND SECURED. THE AIRCRA - [SDR 2004FA0000839](https://openairdocs.org/sdr/2004FA0000839), Oct 14, 2004: SPAR CAP. CORRODED. DURING OUR INITIAL INSPECTION OF THIS AIRCRAFT, DISCOVERED SEVERE INTERGRANULAR CORROSION ON UPPER AND LOWER REAR SPAR CAPS. THE AREA OF CORROSION IS LOCATED IN - [SDR 2004FA0000838](https://openairdocs.org/sdr/2004FA0000838), Oct 14, 2004: SPAR CAP. CORRODED. DURING OUR INITIAL INSPECTION OF THIS AIRCRAFT, DISCOVERED SEVERE INTERGARNULAR CORROSION ON UPPER AND LOWER REAR SPAR CAPS. THE AREA OF CORROSION IS LOCATED IN - [SDR EAT2003F00000](https://openairdocs.org/sdr/EAT2003F00000), Feb 1, 2003: SPAR. DAMAGED. DURING A REPAIR FOR A EXHAUST BRACKET AND LOWER SKIN REPAIRS ON THE LEFT ENGINE NACELLE HEAT DAMAGE WAS FOUND ON THE LFET FORWARD SPAR BETWEEN WING STA CWS88-10 - [SDR J7H2002F00000](https://openairdocs.org/sdr/J7H2002F00000), Sep 1, 2002: CRANKCASE. CRACKED. THREE FACTORY NEW ENGINE CRANK CASE CRACKED JUST OVER ONE THOUSAND HOURS OF OPERATIONS, DURING NORMAL OPERATIONS. THE LAST ENGINE CRANK CASE CRACKED AT 1034 AND - [SDR GNB2002F00001](https://openairdocs.org/sdr/GNB2002F00001), May 30, 2002: CONTROL CABLE. DAMAGED. DURING FUSELAGE INSPECTION FORWARD LEFT RUDDER CABLE BLENDED WERE THE CABLE WEST THRU A RIB WHICH HAD A FANALIC BLOCK ON RIB FOR ANTI-CHAFE PROTECTION. - [SDR 2001FA0000062](https://openairdocs.org/sdr/2001FA0000062), Jun 11, 2001: CONTROL CABLE. INOPERATIVE. LEFT HAND AFT AILERON CABLE. PN 5815103-26CR ( BLENDED ) - [SDR 2001FA0000061](https://openairdocs.org/sdr/2001FA0000061), Jun 11, 2001: LINK. BENT. LINK ASSEMBLY DRAG. PN 0842122-19 All 53: https://openairdocs.org/model/johnson-philip-b-404/reports.md ## The same model under other registry codes Amateur-built copies and renamed makers get their own codes. - [Cessna 404](https://openairdocs.org/model/cessna-404): 26 registered aircraft, registry code 2075901 - [Martin 404](https://openairdocs.org/model/martin-404): 5 registered aircraft, registry code 5450702 - [David R Dantonio 404](https://openairdocs.org/model/david-r-dantonio-404): 1 registered aircraft, registry code 05632AV --- 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.