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Honda HondaJet HA-420, Pilots Operating Manual

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Honda HondaJet HA-420 Pilots Operating Manual Download Page 128

Honda Aircraft Company 

HA-420  

 

 

 

 

 

          SYSTEMS 

POM 

 

 

 

 

 

 

 DESCRIPTION 

 

HJ1-29000-005-001

 

October 30, 2016 

 

1-112 

Speed Brake 

A hydraulically actuated, dual-panel speed brake is installed in the 
tailcone.  

 

Figure 1-60. Speed Brake  

The single position speed brake system is designed to “blow back” as 
speed increases to provide constant drag independent of speed. Speed 
brake deployment is commanded by moving the SPEED BRAKE switch 
aft to the EXT position where it will latch in place. To retract speed 
brakes, move the lever back to the RET position.  Speed brakes are also 
automatically retracted if either thrust lever is advanced beyond a 
position close to the MCT detent. A switch in the actuator determines 
when the speed brake is fully retracted. 

 

 

FOR TRAINING PURPOSES ONLY

Summary of Contents for HondaJet HA-420

Page 1: ...e Flight Manual HJ1 29000 003 001 If any inconsistencies exist between this Pilot s Operating Manual and the FAA Approved Airplane Flight Manual the FAA Approved Airplane Flight Manual shall be the go...

Page 2: ...y Copyright Honda Aircraft Company 2016 Copyright Honda Aircraft Co LLC 2016 All Rights Reserved Published by Honda Aircraft Company 6430 Ballinger Road Greensboro NC 27410 USA www hondajet com FOR TR...

Page 3: ...indicates pages that have been added revised or deleted MODEL HA 420 PILOT S OPERATING MANUAL Title Page March 3 2017 Copyright Page March 3 2017 List of Effective Pages March 3 2017 Record of Revisi...

Page 4: ...9000 005 001 March 3 2017 4 SECTION 4 SERVICE HANDLING AND MAINTENANCE Pages 1 10 October 30 2016 Pages 11 12 December 23 2016 Pages 13 44 October 30 2016 SECTION 5 GLOSSARY Pages 1 16 October 30 2016...

Page 5: ...ON OF REVISION Original 12 10 2015 Original Issue A Not Used B 10 30 2016 Added FIKI Information and General Update B1 12 23 2016 Removed requirement and added approval for use of fuel icing inhibitor...

Page 6: ...Honda Aircraft Company HJ1 29000 005 001 March 3 2017 6 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 7: ...7 7 RECORD OF TEMPORARY REVISIONS Temporary changes to this manual must be entered in this table and revised pages added to the document for all flight operations TEMP REVISION TEMP REV DATE DESCRIPTI...

Page 8: ...Honda Aircraft Company HJ1 29000 005 001 March 3 2017 8 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 9: ...2017 9 LIST OF SERVICE BULLETINS The following is a list of active Service Bulletins applicable to the operation of this airplane and incorporated into this manual SB NO SB REV NO REVISION INCORPORATE...

Page 10: ...Honda Aircraft Company HJ1 29000 005 001 March 3 2017 10 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 11: ...he information required for the safe and efficient operation of the airplane MANUAL PART NO REV NO MANUAL RELEASE DATE HJ1 29000 003 001 B2 Airplane Flight Manual 3 3 2017 HJ1 29000 035 001 B2 Electro...

Page 12: ...Honda Aircraft Company HJ1 29000 005 001 March 3 2017 12 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 13: ...s POM has been prepared to provide pilots with the information required for the safe and efficient operation of the airplane Honda Aircraft Company supports authorized facilities worldwide for ease of...

Page 14: ...testing This data may be used for flight planning Section 3 Operating Procedures and Techniques Recommended procedures and techniques to operate the airplane and its systems Section 4 Service Handlin...

Page 15: ...n status of each page by notating the date of the revision The Record of Revisions shows each revision and its date of release MANUAL CONVENTIONS TABLE OF CONTENTS A table of contents precedes each se...

Page 16: ...ng the associated CAS text Other systems that are redundant but not associated with the left or right side use 1 or 2 An example is AHRS 1 which is a redundant system that can couple to the left or ri...

Page 17: ...TABLE OF CONTENTS INTRODUCTION 5 FUSELAGE 10 EMPENNAGE 10 WING 11 NACELLE AND PYLON 12 DOORS 12 WINDOWS 31 FLIGHT DECK CABIN AND COCKPIT 33 GENERAL 33 DISPLAYS 35 CONTROL PANELS AND CONTROLS 39 CEILIN...

Page 18: ...DARY FLIGHT CONTROLS 110 HYDRAULICS AND LANDING GEAR 117 HYDRAULIC SYSTEM 117 LANDING GEAR 123 WHEELS AND BRAKES 127 NOSEWHEEL STEERING 129 PNEUMATICS AND ENVIRONMENTAL 131 BLEED AIR SUPPLY SYSTEM 131...

Page 19: ...ny HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 3 LIGHTING 1801 EXTERIOR LIGHTING 181 INTERIOR LIGHTING 186 AVIONICS AND AFCS 191 AVIONICS 191 AUTOMATIC FLIGHT CONTROL 222 FOR TR...

Page 20: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 4 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 21: ...ht controls are fully reversible ailerons rudder and elevators that are manually controlled through cables bell cranks and push pull tubes Electrically actuated trim tabs are installed for all three a...

Page 22: ...independent temperature zones are provided inside the pressure vessel Two aft pressure bulkhead outflow valves control pressurization to a scheduled cabin altitude for the flight deck cabin and aft l...

Page 23: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 7 Figure 1 1 Three Views of Aircraft FOR TRAINING PURPOSES ONLY...

Page 24: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 8 Figure 1 2 Turning Radius FOR TRAINING PURPOSES ONLY...

Page 25: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 9 Figure 1 3 Engine Inlet Exhaust Danger Areas FOR TRAINING PURPOSES ONLY...

Page 26: ...ide an emergency exit door on the right side and includes two sky view windows in the lavatory A fuel bladder tank is installed on the aft pressure bulkhead structure behind the pressurized cabin EMPE...

Page 27: ...at make an integral center fuel tank The bottom of the outboard wing includes 14 vortex generators to energize the airflow across the lower surface of the aileron A bump device is mounted to the upper...

Page 28: ...re zone The engine pylon contains a front engine mount rear engine mount firewall spars stringers ribs and skins Titanium and steel materials are used on the engine mount and firewalls where a firepro...

Page 29: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 13 Figure 1 6 Aft Right Side Doors Figure 1 7 Left Side Doors FOR TRAINING PURPOSES ONLY...

Page 30: ...SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 14 Main Entry Door A single piece main entry door MED with integral stairs is mounted on the left side of the fuselage just aft of the cockp...

Page 31: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 15 Figure 1 8 Main Entry Door Airstair FOR TRAINING PURPOSES ONLY...

Page 32: ...is indicated by bright orange surfaces on the inside of the latch opening and the latch handle When the door latch system is disengaged gravity assists opening the door A spring and cable system loca...

Page 33: ...nd an interior cover Switches are mounted in the latching mechanism to provide cockpit feedback of status On the outside there is an integral pressure valve that can be depressed to unlatch the door T...

Page 34: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 18 Figure 1 9 Emergency Exit Door FOR TRAINING PURPOSES ONLY...

Page 35: ...lage The door is equipped with four latches and a handle The door is hinged on the forward edge so that when the handle is pulled it moves first out and then translates forward and latches in place A...

Page 36: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 20 Figure 1 10 Aft Baggage Door FOR TRAINING PURPOSES ONLY...

Page 37: ...The latch lock units have an independent locking feature to lock the latching features The latches mounted on the forward side of the door are equipped with a switch guarding the locking feature of t...

Page 38: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 22 Figure 1 11 Forward Baggage Door FOR TRAINING PURPOSES ONLY...

Page 39: ...he external power access door is located on the right side in the forward section of the wing to body fairing The door is hinged on the forward edge and is held closed by a one push latch The door con...

Page 40: ...4 Lavatory Service Door The optional lavatory service door is located on the right side of the fuselage in the aft section of the wing to body fairing The door is hinged along the forward edge and is...

Page 41: ...are located in the left and right wing to body fairing forward of the wing Each electrical service door is hinged at the forward side with two goose neck hinges and is held closed with two button latc...

Page 42: ...the outboard side of each engine nacelle Each nacelle access door is hinged on the forward edge and is held closed by a dual button latch An additional access door is located on the inboard side of e...

Page 43: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 27 Figure 1 15 Nacelle Access Door FOR TRAINING PURPOSES ONLY...

Page 44: ...all monitored doors can be viewed on the STATUS synoptic page Doors that are expected to be open during normal operations are shown in cyan Doors that are not expected to be open are shown in amber An...

Page 45: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 29 Figure 1 16 Example STATUS Synoptic Page FOR TRAINING PURPOSES ONLY...

Page 46: ...FE The emergency exit door is not closed and latched on ground or in flight EXT PWR DOOR UNSAFE The external power door is not closed with an engine running and the parking brake not set FWD BAG DOOR...

Page 47: ...cabin windows three on each side of the fuselage The cabin windows are laminated stretched acrylic Electrically dimmable cabin window shades are installed at the five cabin mounted window locations T...

Page 48: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 32 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 49: ...n designed with advanced avionics and touch screen display control technologies to improve situational awareness and reduce pilot work load The cockpit electronic displays consist of three 14 inch wid...

Page 50: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 34 Figure 1 17 Flight Deck Diagram FOR TRAINING PURPOSES ONLY...

Page 51: ...005 001 October 30 2016 1 35 DISPLAYS Primary Flight Display A Primary Flight Display PFD is mounted in front of each crew station The PFD displays primary flight and navigation data and a Display Pan...

Page 52: ...36 Multi Function Display A single Multi Function Display MFD is mounted between the PFDs The MFD is divided into a full time Engine Information System EIS and Aircraft System Information ASI display...

Page 53: ...tems Inputs are done using a combination of touch screen and control knobs The touch screen can be used while wearing gloves A bezel is located around the front face of the CDU units and includes a sm...

Page 54: ...A standby instrument is mounted on the glare shield panel in front of the pilot The instrument displays airspeed altitude Mach attitude and heading data full time using dedicated sensors VHF navigatio...

Page 55: ...utton switches display white illuminated text to indicate a normal switch state while a non normal state is illuminated amber text Switches that due to their location could interfere with crew duties...

Page 56: ...angled as desired Airflow can be adjusted by rotating the front edge of the gasper Push To Talk A push to talk control is mounted on each outboard side of the glare shield This is a black momentary pu...

Page 57: ...alternate action push button switch The normal state is white NORM and the alternate state is amber EMER The SUPPLY knob control is a locking pull cable The supply on position is pushed forward The o...

Page 58: ...is white ON and the non normal state is amber OFF The L and R GENERATOR switches are alternate action push button switches The normal state is white NORM and the non normal state is amber OFF The BUS...

Page 59: ...gure 1 24 ELT Panel The ELT control is a three position knob The normal state is up and is labeled NORM Rotating the knob counter clockwise selects the momentary TEST RESET position and rotating it cl...

Page 60: ...ion lever switch that has to be pulled out before being moved between the UP and DN positions A solenoid mounted behind the panel prevents motion under certain conditions Alternate Gear Release The AL...

Page 61: ...rk and the non normal state is white PUSH TO DISC Parking Emergency Brake The Emergency Parking Brake control is located on the right side of the center pedestal below the CDUs The EMERGENCY BRAKE con...

Page 62: ...ed in the center pedestal Figure 1 27 Thrust Lever Quadrant The optional SPEED BRAKE switch is a toggle type of electro mechanical latching switch The normal RET state is in the forward position and t...

Page 63: ...required to move the thrust levers between the IDLE and CUTOFF positions The TO GA switches mounted on the outboard side of each thrust lever are momentary push button switches The switches are not il...

Page 64: ...0 2016 1 48 Figure 1 28 Ice Protection Panel The WING ANTI ICE control is a three position knob The normal state is forward and is labeled NORM Rotating the knob counter clockwise selects the OFF posi...

Page 65: ...tate is white OFF and the alternate normal state is white ON The TAIL DE ICE control is a three position knob The normal state is forward and is labeled NORM Rotating the knob counter clockwise select...

Page 66: ...and rotating it clockwise selects the R ENG position Trim Panel The trim panel is located on the center pedestal and labeled as TRIM Figure 1 30 Trim Panel The PITCH MODE control is an alternate actio...

Page 67: ...wise selects the momentary NOSE R position The STANDBY PITCH control is a dual pole split toggle switch The normal state is centered and is not labeled Moving the switch forward selects the momentary...

Page 68: ...eled PNEUMATIC Figure 1 32 Pneumatic Panel The CABIN INFLOW L and CABIN INFLOW R controls are alternate action push button switches The normal state is white NORM and the non normal state is amber OFF...

Page 69: ...entary action push button switch The normal state is dark and the non normal state is amber MUTE The two CHIME switches are synchronized and pushing either will toggle the mode of both switches The ma...

Page 70: ...normal state is dark and the non normal state is red L or R ENGINE FIRE PUSH The fire extinguisher switch located just inboard of the associated ENGINE FIRE switch is a momentary action push button sw...

Page 71: ...with multiple detents clicks The knob also has a momentary push type action The ALT SEL control is a rotary control with multiple detents clicks The SPD SEL control is a rotary control with multiple d...

Page 72: ...is amber OFF The ROLL switch is an alternate action push button switch The normal state is dark and the non normal state is amber OFF The YAW switch is an alternate action push button switch The norm...

Page 73: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 57 Figure 1 37 Overhead Console FOR TRAINING PURPOSES ONLY...

Page 74: ...ted on the forward outer part of the overhead panel The gaspers pivot in place and can be angled as desired Airflow can be adjusted by rotating the front edge of the gasper Sun Visor Two sun visors ar...

Page 75: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 59 Figure 1 38 Side Ledge Pilot FOR TRAINING PURPOSES ONLY...

Page 76: ...ner An oxygen mask container is mounted just aft of the cup holder on the side ledge In addition to the quick don oxygen mask the stowage container holds a pair of smoke goggles Circuit Breaker Panel...

Page 77: ...on Panel Headset audio connections are located on the forward side of each forward cabinet just aft of the side ledge Fire Extinguisher A fire extinguisher is installed behind the pilot on the left si...

Page 78: ...arge when it is installed to the holder with the shed bus powered FLIGHT CONTROLS Yoke The control yokes are located on control columns at each pilot station The column is hinged at the bottom and rot...

Page 79: ...grip The AFCS TRIM MASTER control is a momentary red push button switch located on the aft side of the outboard yoke grip The CHECKLIST control is an up down scroll wheel switch with detents and a mom...

Page 80: ...h located on the aft side of the inboard yoke grip The IDENT control is a momentary black push button switch located on the forward side of the inboard yoke grip Rudder Pedals The rudder pedal arms ar...

Page 81: ...ted by pushing a white lever mounted on each pedal arm inboard and then moving the pedal to the desired location CREW SEATS The pilot can reach the design eye point by adjusting the seat so that the p...

Page 82: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 66 Figure 1 43 Crew Seats FOR TRAINING PURPOSES ONLY...

Page 83: ...unted on the aft inboard side of the seat cushion When raised the seat back can be adjusted to the desired angle Just above the recline lever on the seat back are two buttons The top button adjusts th...

Page 84: ...onfiguration includes four belted passenger seats in a club arrangement A luggage valet with retention straps or an optional side facing seat is located opposite the main entry door A lavatory is inst...

Page 85: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 69 Figure 1 44 General Floor Plan FOR TRAINING PURPOSES ONLY...

Page 86: ...angle When the lever is released the seat back will latch in place A three point seat belt is provided for each seat The optional side facing seat is non adjustable A lap belt is provided for this loc...

Page 87: ...e lower section A slim partition with limited storage is installed directly forward of the main entry door and behind the LH crew seat A RH luggage valet is located between the RH Forward Cabinet and...

Page 88: ...turn to Your Seat signs are placed at appropriate locations Life Vests and Raft When equipped with the executive seat upgrade and optional life vests the life vests are located in a drawer under the f...

Page 89: ...le for each passenger location The masks are the type that covers the nose and mouth and is held in place with an elastic strap Four masks are available for the four cabin compartment passengers Addit...

Page 90: ...e of the fuselage The baggage space is unpressurized and unheated Tie down straps are provided Aft Baggage The 57 cubic feet aft baggage compartment is located just aft of the rear pressure bulkhead a...

Page 91: ...ressure LP turbine on the LP shaft The single stage centrifugal compressor is driven by a single stage high pressure HP turbine on the HP shaft The engine does not incorporate any variable geometry bu...

Page 92: ...the aircraft for cockpit indication dispatch status and maintenance reporting Power is provided to the FADEC by a dedicated dual wound Permanent Magnet Alternator PMA which is integral to the Fuel Pu...

Page 93: ...h initiates fuel flow and ignition in response to engine core speed After a light off occurs the system controls the FPMU fuel metering valve to accelerate the engine to the power setting calculated f...

Page 94: ...flight ambient conditions Engine thrust is modulated by moving the thrust lever to select either a desired engine thrust rating or an intermediate thrust level The thrust management settings incorpor...

Page 95: ...four idle modes are available Ground idle Anti ice ground idle Flight idle Ground APU mode The FADEC will select between the idle modes based on the weight on wheels and whether engine and or wing ice...

Page 96: ...ed of the engine Limit protections are provided within the FADEC software for fan speed core speed fuel flow and HP compressor discharge pressure The system also includes an independent rotor overspee...

Page 97: ...oil pressure sensor is located on the engine accessory gearbox to measure the supply oil pressure The engine low pressure and high pressure warning level is a variable value continuously calculated by...

Page 98: ...er for the engine A Pressurizing and Shutoff Valve serves as the fuel shutoff valve for the engine under all normal operating conditions The shutoff valve also shuts off the fuel flow during certain f...

Page 99: ...alue changes color to amber or red as appropriate Figure 1 48 GE Engine Indication and Status EIS Display On the ground or when a rated thrust is commanded a cyan thrust mode icon is displayed above t...

Page 100: ...anded N2 deceleration of the associated engine has been detected L R ENG FLAMEOUT An uncommanded N2 deceleration of both engines has been detected L R ENG OIL PRESS LOW Engine oil pressure is below th...

Page 101: ...start or the pilot has detected a reason to abort the start attempt L R ENG CHIP DETECTED Engine oil chip detected L R ENG FAULT Minor engine fault detected L R ENG FUEL BYPASS An impending bypass of...

Page 102: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 86 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 103: ...itors the Fire Detector Sensor integrity Engine Fire Suppression System The fire suppression system for each nacelle consists of a single pressurized halon filled fire extinguisher bottle located in t...

Page 104: ...to close 2 Removes the generator field 3 Arms the associated fire extinguisher FIRE EXT push button switch illuminated Depressing the ENGINE FIRE switch a second time commands the fuel shutoff valve t...

Page 105: ...tected in the indicated engine L R FIRE DETECTOR FAIL The associated fire detection system has failed L R FIRE BOTTLE DISCH Affected fire bottle has been discharged L R FIRE BOTTLE LOW The associated...

Page 106: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 90 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 107: ...016 1 91 FUEL Fuel Storage System The storage system is comprised of four fuel tanks an integral tank in each wing an integral carry through tank in the wing center section and a bladder fuselage tank...

Page 108: ...ump are located The collector tanks supply fuel to the onside engine during normal operation The collector tanks contain approximately 14 7 gallons of fuel each and are isolated from the wing tanks by...

Page 109: ...wing to pump fuel into that wing s collector tank The scavenge pumps are distributed throughout the wing tank such that at least one scavenge pump is submerged under all aircraft attitudes Two transf...

Page 110: ...nk The valve is commanded OPEN on ground for refueling operations and is CLOSED at all other times to isolate the fuselage tank pressure head from the C T tank The valve is controlled automatically by...

Page 111: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 95 Figure 1 51 HA 420 Fuel Distribution System FOR TRAINING PURPOSES ONLY...

Page 112: ...e electric boost pump in the supplying wing tank is commanded on Since much of the fuel fed to the engines is returned to the wing as motive flow the operation of the fuel crossfeed system can also be...

Page 113: ...r pressure to the expansion space The expansion space is located within the fuselage bladder tank Vent lines connect the expansion space to all other tanks A vent drain valve is located in the carry t...

Page 114: ...el vent system includes a single float level switch installed in the L surge tank to detect a dual failure of the L and R outboard wing vent valves Flame Arrestor The vent system incorporates flame ar...

Page 115: ...ks The refuel system relies on gravity driven flow to feed fuel to each of the fuel tanks The aircraft refueling system consists of the refuel tubes filler port fuel isolation valve and an optional ex...

Page 116: ...r port The external fuel gauge has a numeric fuel quantity display which shows the total fuel quantity in the fuel tanks three LED lights to indicate when each of the tanks is full and two LED lights...

Page 117: ...el line Fuel Gauging System The fuel system incorporates a fuel gauging system to measure and display the quantity of fuel in the tanks for cockpit and external fuel gauge indication purposes The syst...

Page 118: ...reen color Total quantity as well quantity of each tank is displayed together with left and right tank fuel temperature Wing tank quantity is displayed in amber when below 220 lbs and red when zero Fu...

Page 119: ...6 1 103 Figure 1 56 Fuel ASI Display The Fuel System Synoptic Page provides additional detailed fuel system information to the crew such as pump operation valve positions engine inlet fuel pressure an...

Page 120: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 104 Figure 1 57 Fuel Synoptic Page Display FOR TRAINING PURPOSES ONLY...

Page 121: ...been detected FUEL LEVEL CTRL FAULT A fault has been detected in the fuel level control system L R FUEL PRESSURE LOW Fuel pressure is below minimum allowable limits for both engines L R FUEL PRESSURE...

Page 122: ...SFEED OPEN Fuel Crossfeed valve is open when commanded closed FUEL ISO VALVE CLOSED Isolation valve has failed in the closed position FUEL ISO VALVE OPEN Fuel isolation SOV has failed in the open posi...

Page 123: ...system using cables bellcranks sectors and pushrods which provide mechanical link from the cockpit to the applicable flight control The primary flight control system is comprised of the ailerons elev...

Page 124: ...rons manually driven by a closed loop cable system The ailerons are controlled via two yokes installed on respective control columns The control yokes move simultaneously Yaw Axis The single rudder is...

Page 125: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 109 Figure 1 59 Gust Locks FOR TRAINING PURPOSES ONLY...

Page 126: ...standby pitch trim mode that bypasses the normal trim drive circuit and provides single speed direct drive of the actuator Roll Trim System Each aileron is equipped with one trim tab driven by a sing...

Page 127: ...ation Controller FAC and identical left and right electrical flap actuators Flap panels are synchronized electronically by the FAC In the event of an asymmetric flap malfunction the FAS locks the flap...

Page 128: ...speed increases to provide constant drag independent of speed Speed brake deployment is commanded by moving the SPEED BRAKE switch aft to the EXT position where it will latch in place To retract speed...

Page 129: ...and the pointers and value changes color from white to green when the trim is set within this band In air the pointers and value are displayed in white If a trim actuator has failed the associated tr...

Page 130: ...has been powered for three days without performing the Built In Test PITCH TRIM FAIL The primary pitch trim has failed or a stuck switch has been detected SPEEDBRAKE EXTENDED Speedbrake is not fully c...

Page 131: ...the roll trim system ROLL TRIM OFF Roll trim is selected OFF SPEEDBRAKE FAIL Speedbrake has failed STBY PITCH TRIM ON Standby pitch trim has been selected YAW TRIM FAIL Yaw trim has failed or a stuck...

Page 132: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 116 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 133: ...and the Emergency accumulator supplies the emergency parking brake and the nosewheel steering Each accumulator is isolated by a check valve Control of the hydraulic system is fully automatic and no c...

Page 134: ...r is installed to allow monitoring of volume in the cockpit There are two types of thermal protection the DC motor over temperature switch and hydraulic fluid high temperature switch Both protection f...

Page 135: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 119 Figure 1 62 Hydraulic Power System Schematic FOR TRAINING PURPOSES ONLY...

Page 136: ...20 Indications Systems and accumulator pressures reservoir volume and pump running status can be monitored on the HYDRAULIC synoptic page Values and flow lines are normally depicted in green color but...

Page 137: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 121 Figure 1 63 Hydraulic Power System Synoptic FOR TRAINING PURPOSES ONLY...

Page 138: ...LOW Main system hydraulic pressure is below allowable limits HYD PUMP FAIL The Hydraulic Pump has failed HYD FLUID LEVEL LOW The hydraulic reservoir fluid level is below allowable limits HYD FLUID OVE...

Page 139: ...ear WOW switch prevents landing gear switch movement from the DN position to the UP position Main Landing Gear Each main landing gear MLG strut attaches to the wing and retracts inboard into the wing...

Page 140: ...position The NLG drag brace actuator has a downlock mechanism to lock the nose landing gear in the down position and a NLG uplock roller engages a latch on the uplock retract actuator hook after the...

Page 141: ...n be partially stowed Indications Landing gear status is displayed on the ASI Figure 1 64 ASI Landing Gear Display The landing gear status indicators will show one of three landing gear states based o...

Page 142: ...tem include the landing gear position landing gear switch position flap position aircraft altitude height airspeed and thrust lever angle Under certain conditions the aural alert can be silenced by ac...

Page 143: ...three stationary steel discs Two brake wear indicator pins are installed on the pressure plate and protrude through the cylinder housing When the wear indicators are flush with the cylinder housing wi...

Page 144: ...er main landing gear wheel slows to 30 or less when compared to the other wheel speed a full brake release occurs which removes the locked wheel condition Wheel spin down braking applies minimum wheel...

Page 145: ...YDRAULICS synoptic page NOSEWHEEL STEERING The nosewheel steering NWS system contains one steering control unit SCU one steering control valve and actuator assembly SCVA installed on the nose landing...

Page 146: ...ng system has failed or is selected OFF during taxi operations PARK BRAKE FAIL Brake pressure is less than 1450 psi with the PARK BRAKE set PARK BRAKE ON The parking brake is pressurized during flight...

Page 147: ...Cooler PC A solenoid function on the HPRSOV will close the valve if commanded The PC is an air to air heat exchanger that functions as the first stage of bleed air conditioning cooling The conditioni...

Page 148: ...conditions In the event of a failed open HPRSOV the NPRSOV will regulate the conditioned bleed air pressure to approximately 70 psig From the NPRSOV the conditioned bleed air is ported to the environ...

Page 149: ...on is required A solenoid function on the FCSOV will close the valve if commanded The FCSOVs can be closed by selecting the associated L CABIN INFLOW or R CABIN INFLOW switch to OFF From the FCSOVs co...

Page 150: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 134 Figure 1 66 Temperature Modulating Valves FOR TRAINING PURPOSES ONLY...

Page 151: ...re in parallel There are two sources for ambient cooling air the Ground Cooling Fan GCF on the ground and two ram air inlets located at the base of the vertical stabilizer in flight The GCF draws air...

Page 152: ...her bypasses all bleed air flow from the HX or directs all bleed air flow through the HX The bleed air exiting the TMV is ducted into the aircraft pressure vessel through check valves mounted on the A...

Page 153: ...g heat and moisture from the aircraft cabin air This cool dry air exits the evaporator and is then forced through the aircraft system distribution ducts via the evaporator fans If the Air Conditioner...

Page 154: ...rectly adjust each TMV Each push of the Cold or Hot button drives the valve in the appropriate direction for a short time If the duct temperature is driven beyond approximately 93 C the valve will aut...

Page 155: ...will be shed On battery power when on ground the Air Conditioner and GCF are not powered and the Cabin and Cockpit evaporator fans are speed limited During single engine operations on the ground bleed...

Page 156: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 140 Figure 1 70 Cabin Air Distribution System FOR TRAINING PURPOSES ONLY...

Page 157: ...oling outlets Cabin Climate Zone The LH BAS conditioned bleed air is ducted to three floor vents along the LH distribution duct and two floor vents along the RH distribution duct which are open at all...

Page 158: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 142 Figure 1 71 Environmental Synoptic Page FOR TRAINING PURPOSES ONLY...

Page 159: ...e when commanded L R ENG BLEED FAIL There has been a failure of the bleed system or the aircraft was powered up with a high bleed manifold temperature L R CABIN BLEED FAULT A fault in the affected cab...

Page 160: ...pressure limiter and negative differential pressure relief function The POFV ECU provides pressurization data to the aircraft avionics system including cabin pressure altitude cabin pressure altitude...

Page 161: ...ers are advanced for takeoff the CPCS enters a pre pressurization mode in which the CPCS maintains the cabin rate until a small differential pressure is achieved If the takeoff is aborted the CPCS dep...

Page 162: ...g the CPCS will automatically depressurize it after touchdown High Field Operation The CPCS incorporates a High Field mode that activates when the following is true a The aircraft is on the ground and...

Page 163: ...ltitude Hold Mode If the pressurization control signal from the aircraft avionics system fails the CPCS will automatically enter a Cabin Altitude Hold Mode Hold Mode Hold Mode maintains the current ca...

Page 164: ...SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 148 Figure 1 73 Cabin Pressurization ASI Indications If Dump or Hold mode is active the LFE indication is replaced by a white DUMP or HOLD i...

Page 165: ...RL FAULT A fault has been detected which affects the cabin dump function CABIN ALT HIGH FIELD The Cabin Pressurization system has been operating in the High Field Mode for more than 30 minutes NO LDG...

Page 166: ...ve tube filled with an extruded eutectic salt around a core As the temperature surrounding a sensing element reaches its alarm point the BALD Controller activates a discrete alarm output The following...

Page 167: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 151 Figure 1 74 Bleed Air Leak Detection Lines FOR TRAINING PURPOSES ONLY...

Page 168: ...he inlet assembly Indications In addition to CAS alerts bleed leaks are indicated by associated flow lines on the ENVIRONMENTAL and ICE PROTECTION synoptic pages changing from green to red color CAS M...

Page 169: ...ply is provided with a pressure relief valve that provides a back up to the oxygen pressure regulator Pushing pulling the SUPPLY knob opens closes a mechanical valve at the high pressure source All lo...

Page 170: ...e crew oxygen mask with one hand operation Releasing the levers deflates the harness to provide a tight fit of the mask Crew oxygen masks operate on three modes Normal 100 Oxygen and Emergency There i...

Page 171: ...Emergency Mode The regulator delivers 100 oxygen through positive pressure regardless of cabin altitude Crew Mask Storage The mask stowage provides the ability to test the flow of oxygen and test the...

Page 172: ...itch is in the NORM position A noise suppressor is mounted on each oxygen hose When the ON OFF switch is selected ON it filters out some of the breathing noise when the mask is in use Passenger Oxygen...

Page 173: ...f and cabin altitude is greater than 15 500 ft OXYGEN LOW Oxygen quantity is less than 465 liters OXYGEN QTY FAIL The oxygen pressure transducer is indicating out of range OXYGEN UNAVAILABLE Oxygen qu...

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Page 175: ...e protection system engine inlet ice protection system horizontal tail ice protection system heated air data probes and windshield vision protection system The airplane also incorporates an ice detect...

Page 176: ...bleed source is available The system is automatically tested on the ground following the second engine start The system can be manually commanded on by selecting the WING ANTI ICE switch ON position a...

Page 177: ...30 seconds after liftoff At or above FL340 In the Keep Out zone Figure 1 77 Wing Anti Ice Keep Out Zone If the WING FLOW switch is selected to FROM L or FROM R the WAIV on the opposite to side is comm...

Page 178: ...ine inlet lip The system is automatically tested on the ground following the second engine start Horizontal Tail Ice Protection System The Horizontal Tail Ice Protection System HTIPS is an Electro Mec...

Page 179: ...ophobic material to assist in rain removal When the windshield L or R ZONE switch is in the NORM position the associated zones will be heated in low power mode whenever an engine is running on the gro...

Page 180: ...board and outboard temperature sensor readings but will change to the lowest reading if an under temperature reading is detected or the highest if an over temperature reading is sensed A green leading...

Page 181: ...s to amber The windshield is white when the heater is commanded off Air Data Probes Heat System Each of the probes are displayed in green on the ICE PROTECTION synoptic page when heating is commanded...

Page 182: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 166 Figure 1 78 Ice Protection Synoptic Page FOR TRAINING PURPOSES ONLY...

Page 183: ...iled or is not powered STBY PROBE HEAT FAIL The standby air data probe heater has failed or is not powered L R WING A I TEMP LOW The wing anti ice system is operating at a lower than expected temperat...

Page 184: ...und but wing temperature is less than 10 C L R ENG ANTI ICE FAULT A fault has been detected in the affected engine anti ice system ICE DETECTED Ice has been detected ICE DETECT FAULT One ice detector...

Page 185: ...G ANTI ICE ON WING ANTI ICE switch selected ON WING FLOW FROM L R WING FLOW switch selected FROM L R L R WSHD ZONE FAULT Affected zone unable to select high heat mode L R WSHD ZONE OFF Applicable wind...

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Page 187: ...ted at 325 Amps A dedicated Generator Control Unit GCU for each starter generator supplies field excitation voltage regulation and protection The GCUs also supply the control function for the generato...

Page 188: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 172 Figure 1 79 Electrical Schematic FOR TRAINING PURPOSES ONLY...

Page 189: ...starting sequence is initiated During start the bus system isolates the number 2 battery The loads that are normally powered by the number 2 battery are powered by the number 1 battery through the bu...

Page 190: ...ide overcurrent protection and control sequencing of loads during engine start and perform load shed of high power loads in the event that one or both generators go off line Tripped SSRs can be reset...

Page 191: ...shed when operating in the Ground Cooling mode Cabin Power The CABIN POWER switch controls power to CABIN BUS A and CABIN BUS B Cabin lighting entertainment systems and optional 110 VAC cabin outlets...

Page 192: ...perating in starter mode as is a green halo around the START button The PUSH TO DISC switch illuminates during this condition too Status of each individual bus is displayed on the ELECTRICAL synoptic...

Page 193: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 177 Figure 1 81 Electrical System Synoptic Page FOR TRAINING PURPOSES ONLY...

Page 194: ...tery bus 1B has failed or is isolated from the aircraft electrical system BATTERY BUS 1C FAIL Battery bus 1C has failed or is isolated from the aircraft electrical system BATTERY BUS 2 FAIL Battery bu...

Page 195: ...stem BATTERY OFF Battery selected off BATTERY 1 2 FAIL The associated battery has failed BATTERY 1 2 FAULT A fault has been detected in the battery or charging system or the battery temperature is too...

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Page 197: ...0 2016 1 181 LIGHTING EXTERIOR LIGHTING The following external lights are installed Landing lights Taxi lights Strobe Anti collision lights Beacon Navigation lights Ice inspection lights Recognition l...

Page 198: ...l mode In Normal mode lights are commanded on off automatically at certain flight phases time of day by two Aircraft Component Control Units ACCUs The normal mode is the default mode and becomes activ...

Page 199: ...dawn to dusk Recognition Steady In flight and airplane below transition altitude during dusk to dawn Taxi Parking brake not set on ground at low speed Strobe Take off run or in flight Navigation Dusk...

Page 200: ...g light also illuminates when taxi lights are on Strobe Navigation Lights Strobe and Navigation light assemblies are located on the outboard leading edge of each wing A Tail Strobe and Navigation ligh...

Page 201: ...ications are magenta if in the Normal mode and cyan if in the Manual mode Figure 1 84 STATUS Page Exterior Lights Section CAS Messages Message Description EXT LIGHTS MAN OFF Some external lights have...

Page 202: ...gy Cockpit Lighting System Instrument panel lights and display brightness controls are part of the integrated cockpit interior lighting system Panel backlighting and display brightness are automatical...

Page 203: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 187 Figure 1 85 CDU Lighting Configuration Page FOR TRAINING PURPOSES ONLY...

Page 204: ...ight can be switched on or off and brightness can be adjusted through the CDU Interior Lights page This page also allows for toggling the Pilot and Co Pilot Footwell lights on or off Figure 1 86 CDU I...

Page 205: ...effect illuminates around the selected icon while a user input is detected Entry switches the Entry Overhead light on off Cabin controls the cabin Wash lights Additional presses of the Cabin switch w...

Page 206: ...inutes when the Main Entry Door is opened The timer can be reset for 10 minutes by activating the switch located on the entry area sidewall The light will be off when the door is closed unless command...

Page 207: ...as two Primary Flight Displays and one Multi Function Display A detailed description of the avionics system can be found in the Garmin G3000 Integrated Avionics System Pilot s Guide for the HondaJet...

Page 208: ...em Indications ASI display area and a Status Bar which presents eight pilot selectable navigation information parameters The PFDs display data for the capabilities that follow Critical Flight paramete...

Page 209: ...rol Display Pane Control FMS Function Control Transponder Control Weather Radar Control System Control Navigation Control Avionics Settings Planning Tools TAWS Control TCAS Control Weather Data Link C...

Page 210: ...ludes the following items System Tests Weight and Fuel Flight Plan V speeds Pilot Profile Aircraft System Data Essential information related to the Engines Fuel Cabin Pressure Electrical Power Landing...

Page 211: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 195 Figure 1 89 EIS ASI Data Layout FOR TRAINING PURPOSES ONLY...

Page 212: ...of a condensed Display Pane PFD1 State MFD State PFD2 State PFD1 Offline Reversionary Normal MFD Offline Reversionary Normal PFD2 Offline Normal Normal Figure 1 90 Automatic Display Reversion Logic Re...

Page 213: ...w on the lower right of each PFD CAS Messages CAS messages are divided into warning messages red caution messages amber advisory messages cyan and system status white messages based on urgency Warning...

Page 214: ...Under the following conditions a TAKEOFF CONFIG warning will alert when thrust levers are advanced for takeoff while on the ground If the aircraft flaps speedbrake parking brake or trims are not conf...

Page 215: ...tting is adjusted using the BARO SET knob and is displayed below the altimeter tape Barometric pressure units are selectable through the CDU in inches of mercury in Hg or hectoPascals hPa Airspeed Mac...

Page 216: ...ompare between the two AHRS systems A heading bug can be set using the HDG knob on the Mode Control panel Standby Instrument The standby instrument is an integrated solid state system displaying altit...

Page 217: ...stems the Standby system can provide attitude heading or air data information for display on the PFDs System Synoptic Pages Six system synoptic pages can be selected for display on any Display Pane us...

Page 218: ...itioner ground cooling fan running status Oxygen quantity is also displayed ELECTRICAL displays status of electrical buses contactors batteries generators as well as voltage current readings FUEL disp...

Page 219: ...1 93 Systems Synoptic Pages System Control Pages A Systems Control page is available on the Aircraft Systems page or by pressing the SYSTEM CONTROL button mounted on each yoke Pressing the SYSTEM CONT...

Page 220: ...tomatic mode or manual control of the exterior lights Interior Lights allows for switching of cockpit lights and ordinance signs Lighting Config allows for dimming of overall display panel brightness...

Page 221: ...001 October 30 2016 1 205 Stall Warn Ice Advance Reset resets the approach reference speed green donut and the stall protection system angles to baseline values The button is greyed out in icing cond...

Page 222: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 206 Figure 1 95 Individual Systems Control Pages FOR TRAINING PURPOSES ONLY...

Page 223: ...sts that require a pilot evaluated condition Fire Detection Illumination Stall Protection and Switch Illumination indicate Done when the test sequence has run to completion and all associated automate...

Page 224: ...Honda Aircraft Company HA 420 SYSTEMS POM DESCRIPTION HJ1 29000 005 001 October 30 2016 1 208 Figure 1 96 System Tests Page FOR TRAINING PURPOSES ONLY...

Page 225: ...hield In addition to the headset and oxygen mask microphones an always active hand held microphone is mounted on each control column The hand held microphone input is separate from the headset oxygen...

Page 226: ...Data Link Communication Controller Pilot Data Link Communication CPDLC using a third digital VHF radio is available as an option Logon and communication is through the CPDLC CDU page A PFD and CPDLC C...

Page 227: ...VHF NAV or the optional ADF and overlaid on the CDI When selected the associated data is displayed below the CDI VOR ILS Marker Beacon Dual VOR ILS Marker Beacon receivers are installed Tuning and con...

Page 228: ...data Flight plan data is overlaid on the navigation map Automatic Direction Finder The optional Automatic Direction Finder ADF provides the capability to determine direction to non directional beacon...

Page 229: ...for ATC and TCAS I surveillance requirements as well as Extended Squitter for ADS B Out functionality Mode selection code and flight ID entry is performed through the CDU IDENT function can be activat...

Page 230: ...to and avoid instruction are provided visually on the PFD as well as aurally Emergency Locator Transmitter The Emergency Locator Transmitter is an Automatic Fixed COSPAS SARSAT ELT two frequency trans...

Page 231: ...a recording provided A bulk erase feature is available through the CDU when the parking brake is set An internal Recorder Independent Power Supply RIPS provides ten minutes of backup power when all pr...

Page 232: ...enable SiriusXM capability ConnextTM Weather Data Link The optional ConnextTM weather data link uses the Iridium based Data Link system to provide weather and Temporary Flight Restrictions TFR inform...

Page 233: ...Flight Bag Functions FliteCharts Garmin FliteCharts provides high resolution equivalents to paper charts It has full color capability and shows current aircraft position on charts that are to scale T...

Page 234: ...aceWatch feature provides crew alerts during takeoff and landing to notify the flight crew of critical situations such as runway incursions and overruns An information window in the PFD contains runwa...

Page 235: ...has failed AVIONICS COMPUTER 2 FAIL Avionics computer 2 has failed CPDLC FAIL The CPDLC has failed DATA ACQUISITION 1 FAIL Data Acquisition Unit 1 has failed DATA ACQUISITION 2 FAIL Data Acquisition U...

Page 236: ...ntenance One or more displays may be dimmer than usual COM 1 2 TEMP HIGH Affected radio reporting a high internal temperature effective range may be reduced CONFIG BRAKE Parking brake pressure is grea...

Page 237: ...d including ConnextTM Weather or there has been a failure to receive data correctly during an update STBY AIR DATA FAIL Standby instrument air data computer is not providing proper data STBY AHRS FAIL...

Page 238: ...or pitch axis Stall Warning Protection Yaw Damper Turn Coordinator Rudder Bias Cruise Speed Control CSC A dedicated Flight Mode Annunciator FMA area on the top of each PFD shows both active and armed...

Page 239: ...ector in the default pitch and roll modes if no modes were previously selected If the autopilot is engaged the flight director button function is inhibited If the autopilot is not engaged removing the...

Page 240: ...track offset waypoints the VNAV Direct To button on the VNAV Altitude page could be misleading The button has the same label as the next waypoint in the flight plan that is not an along track offset w...

Page 241: ...The autopilot system follows attitude command inputs from the flight director The autopilot system controls the pitch servo which moves the elevator and the roll servo which moves both ailerons The au...

Page 242: ...ce Dutch Roll oscillations and to provide turn coordination The yaw damper will automatically engage after takeoff or can be manually selected on off using the AFCS mode control panel The yaw damper a...

Page 243: ...ithout disengaging the mode The function is engaged by pressing the CSC button on the AFCS Mode Control Panel when Altitude Hold ALT is the active vertical Flight Director mode airspeed rate is stable...

Page 244: ...d to disengage the CSC function Press the CSC button on the AFCS Mode Control Panel Move either thrust lever by more than 1 degree Press the AFCS Trim Master button on either control yoke Select a ver...

Page 245: ...ot occurred within expected time In addition to the stall warning and protection the airspeed indicator incorporates a complementary function in the Low Speed Awareness LSA cue The LSA appears as a co...

Page 246: ...essage Description TAKEOFF CONFIG One or more configuration items are not properly set for takeoff AFCS MISTRIM Autopilot is holding constant force FLT DIR MODE CHANGE The flight director function has...

Page 247: ...t be able to be reengaged CRUISE SPD CTRL FAIL Cruise speed control has failed RUDDER BIAS FAULT Rudder Bias system has detected a fault but can still activate Message may post when aircraft on batter...

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Page 249: ...001 October 30 2016 2 1 SECTION 2 FLIGHT PLANNING TABLE OF CONTENTS INTRODUCTION 3 CLIMB PERFORMANCE 5 LONG RANGE CRUISE PERFORMANCE 11 HIGH SPEED CRUISE PERFORMANCE 19 DESCENT PERFORMANCE 25 HOLDING...

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Page 251: ...engine performance NOTE When necessary interpolation may be used between table values to determine performance for the current ambient conditions and aircraft weight If interpolation is not used the...

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Page 287: ...ABLE OF CONTENTS GENERAL 5 RESPONSIBILITIES 5 COCKPIT CREW RESOURCE MANAGEMENT 6 CHECKLIST 6 CREW ALERTING 8 PREFLIGHT INSPECTION 11 PRELIMINARY EXTERIOR INSPECTION 11 COCKPIT CABIN INSPECTION 11 EXTE...

Page 288: ...FF 22 AFTER TAKEOFF 23 ENROUTE OPERATIONS 25 CLIMB 25 CRUISE 25 DESCENT 25 TERMINAL AREA OPERATIONS 25 APPROACH 25 INSTRUMENT APPROACH 28 VFR PATTERN 35 LANDING 36 NORMAL LANDING 36 CROSSWIND LANDING...

Page 289: ...3 3 EMERGENCY AND ABNORMAL PROCEDURES 41 ENGINE FAILURE DURING TAKEOFF 41 SINGLE ENGINE APPROACH AND LANDING 45 SINGLE ENGINE INSTRUMENT APPROACH PROFILES 47 APPROACHES IN ICING 49 REDUCED FLAP LANDI...

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Page 291: ...functions customization and settings If there is a conflict the AFM shall take precedence This manual contains techniques for using standard and optional equipment The reader may omit steps referring...

Page 292: ...tion and design features that will enhance single pilot operations Where possible it also provides suggestions for effective crew resource management when additional crew members are available CHECKLI...

Page 293: ...he checklist item with no ellipses The response appears in parentheses as seen here Avionics Flight Data Set Entered The AFM normal checklist procedures will specify Normal when a switchlight is dark...

Page 294: ...evels of alerts warning caution and advisory as well as status information messages Certain CAS messages will also have aural alerts associated with them Aural alerts include tones and spoken alert me...

Page 295: ...nce the AFM for required actions AFM advisory procedures for cyan CAS messages note whether or not that failure is included in the manufacturer provided master minimum equipment list MMEL All failures...

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Page 297: ...ur on synoptic pages Pilot initiated tests can be started after the IBIT has finished and the pilot initiated tests are no longer grayed out The MFD shows a splash screen with software version and dat...

Page 298: ...the oxygen mask and panel in accordance with the AFM Each pilot should confirm on side speaker operation by listening for oxygen flow while simultaneously depressing the oxygen box TEST RESET and the...

Page 299: ...st Standby Instrument Verify the standby instrument has powered on completed its alignment and displays valid data Use the baro knob to set the current altimeter setting Exterior Lights When left in t...

Page 300: ...anels and the throttle quadrant will not be powered and therefore those switchlights cannot be checked during the Switchlights test If desired re run this test following engine start NOTE The optional...

Page 301: ...f electronic devices Securing carry on items Flight duration Rudder Pedals After adjustment confirm both pedals are in the selected detent and that full deflection can be achieved Seats Safety Belts A...

Page 302: ...ed NOTE The Status Synoptic L R OIL QUANTITY indication may toggle between NORMAL and LOW following engine start on battery power until synoptic declutters following engine start Single Engine Cooling...

Page 303: ...ance with the AFM NOTE An amber HDG miscompare flag may post on the PFDs while parked or taxiing in the vicinity of a GPU or other metal structures This flag should clear when the aircraft is clear of...

Page 304: ...to verify removal of wheel chocks before releasing the parking brakes TAXI Accomplish the Taxi checklist in accordance with the AFM Check the brake operation as soon as the airplane begins to move Cl...

Page 305: ...should review each CAS message Navigation Select the appropriate navigation source for departure If necessary set the course deviation indicator CDI to the course desired for takeoff and departure Ve...

Page 306: ...s based on a dry runway If departing from a wet runway it is recommended to increase the predicted takeoff field length by 30 Takeoff Briefing The takeoff briefing should include consideration of the...

Page 307: ...d selecting the WXR control page by pushing the joystick may result in the inability to select active tile Selecting the Home or Back button should restore normal functionality Ice Protection If takeo...

Page 308: ...O is displayed in large font in the EIS Verify that airspeed is increasing at expected rate and readings are matched Prior to 80 knots confirm responsiveness of aircraft to crosswind control inputs if...

Page 309: ...en reduce the thrust levers to MCT The pilot should consider all factors when deciding when to retract flaps including industry best practices noise abatement obstacle clearance etc Select FD vertical...

Page 310: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 24 Figure 3 1 Normal Takeoff Profile FOR TRAINING PURPOSES ONLY...

Page 311: ...operations DESCENT Accomplish the Descent checklist in accordance with the AFM Confirm Transition Altitude alert is set correctly for the arrival TERMINAL AREA OPERATIONS APPROACH Accomplish the Appr...

Page 312: ...ypoints Landing Data Reference the AFM for landing distance and speeds Load V speeds and select landing runway and required distance If ice has accumulated on the aircraft plan to use flaps set to TO...

Page 313: ...During normal operations there will be no CAS alerts present Nominal system operations such as use of engine anti ice may result in status CAS messages The pilot should review each CAS message Approac...

Page 314: ...proach mode will not capture a back course Back course mode BC is armed by pressing the NAV key When making a back course approach set the Selected Course to the localizer front course Initial Approac...

Page 315: ...o both RNAV and VHF NAV approaches VOR or LOC Final Approach Accomplish the Before Landing checklist prior to starting final descent The pilot should establish stable approach criteria If exceeding th...

Page 316: ...ing the GP mode to fly the vertical path with a non precision approach the aircraft will not level off at the selected altitude Non precision Approach without vertical guidance Establish the final con...

Page 317: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 31 Figure 3 2 Circling Approach FOR TRAINING PURPOSES ONLY...

Page 318: ...while approaching the airfield Use the navigation map and the runway extension line together with predicted flight path to evaluate rollout onto final Use the flight path marker and Synthetic Vision S...

Page 319: ...IQUES HJ1 29000 005 001 October 30 2016 3 33 Instrument Approach Profiles Suggested profiles for precision and non precision approaches followed by a missed approach are shown in the figures that foll...

Page 320: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 34 Figure 3 4 Precision Approach FOR TRAINING PURPOSES ONLY...

Page 321: ...entering the VFR pattern Slow to 160 KIAS no later than intercepting downwind For closed patterns maintain 160 knots during the turn to downwind NOTE The closed pattern refers to those VFR pattern ope...

Page 322: ...eet charted performance Excess airspeed tailwind and runway downslope will increase the runway required to land NOTE Establish directional control using rudder and then apply brakes symmetrically duri...

Page 323: ...cles accelerate to 130 KIAS minimum and retract flaps UP It may not be possible to safely retract flaps to UP in case of a balked landing if icing conditions were encountered with the flaps extended C...

Page 324: ...It may not be possible to safely retract flaps to UP in case of a missed approach if icing conditions were encountered with the flaps extended Climb performance capability and increased fuel burn duri...

Page 325: ...g was encountered with the flaps extended or after landing on a snow or slush covered runway do not retract flaps to UP until they can be verified to be free from ice and snow accumulation CAUTION Ret...

Page 326: ...vailable connect external power prior to shutting down both engines EXT PWR AVAIL will display on the ASI when suitable electrical power is connected to the airplane and available for use THRUST LEVER...

Page 327: ...but still applies whenever it appears in an abnormal or emergency checklist ENGINE FAILURE DURING TAKEOFF When cleared for takeoff advance thrust levers enough to begin taxi onto the runway If conduc...

Page 328: ...er 30 2016 3 42 If an engine fails or another situation occurs that requires the flight crew to abort the takeoff prior to reaching V1 reduce the thrust levers to idle apply the brakes and extend the...

Page 329: ...eving a positive rate of climb Adjust pitch to maintain V2 during the initial climb Use yaw and roll trim to reduce control forces and engage the autopilot as desired Further yaw trim adjustments may...

Page 330: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 44 Figure 3 7 Engine Failure at or Above V1 FOR TRAINING PURPOSES ONLY...

Page 331: ...ction on the operating engine should minimize yaw transients during the flare and landing NOTE If the YD was engaged before the rudder bias engagement the pilot has to disengage the YD prior to landin...

Page 332: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 46 Figure 3 8 Visual Approach Single Engine FOR TRAINING PURPOSES ONLY...

Page 333: ...016 3 47 SINGLE ENGINE INSTRUMENT APPROACH PROFILES Suggested profiles for single engine precision and single engine non precision approaches followed by a missed approach are shown in the figures tha...

Page 334: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 48 Figure 3 10 Precision Approach Missed Approach Single Engine FOR TRAINING PURPOSES ONLY...

Page 335: ...PR just prior to starting final descent Accomplish the Before Landing checklist Wait until landing is assured to disconnect the yaw damper but no later than 50 ft AGL Just prior to landing confirm pro...

Page 336: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 50 Figure 3 11 Approach in Icing Conditions FOR TRAINING PURPOSES ONLY...

Page 337: ...rrected landing speed during level flight prior to the FAF With lower than normal drag precise flight path control will be required to avoid the possibility of being high and fast on final without the...

Page 338: ...CEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 52 Approach Briefing In addition to normal approach briefing items address non standard landing speeds and distance Figure 3 12 Visual Ap...

Page 339: ...05 001 October 30 2016 3 53 TAWS Warning Flap Override if TAWS A equipped should be selected to avoid a nuisance alert EMERGENCY DESCENT An emergency descent may be conducted utilizing the profile in...

Page 340: ...desired direction while increasing the N1 approximately 3 Subsequently increase back pressure to maintain altitude or use pitch trim to relieve the control forces At 200 KIAS the pitch attitude in th...

Page 341: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 55 Figure 3 14 Steep Turns FOR TRAINING PURPOSES ONLY...

Page 342: ...allow recovery to be safely completed at least 3 000 ft AGL Configure the airplane as required Smoothly adjust pitch power and bank angle to induce a stall At the first indication of a stall promptly...

Page 343: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 57 Figure 3 16 Approach to Stall Clean Configuration Simulator FOR TRAINING PURPOSES ONLY...

Page 344: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 58 Figure 3 17 Approach to Stall Takeoff Configuration Aircraft FOR TRAINING PURPOSES ONLY...

Page 345: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 59 Figure 3 18 Approach to Stall Takeoff Configuration Simulator FOR TRAINING PURPOSES ONLY...

Page 346: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 60 Figure 3 19 Approach to Stall Landing Configuration Aircraft FOR TRAINING PURPOSES ONLY...

Page 347: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 61 Figure 3 20 Approach to Stall Landing Configuration Simulator FOR TRAINING PURPOSES ONLY...

Page 348: ...Honda Aircraft Company HA 420 OPERATING PROCEDURES POM AND TECHNIQUES HJ1 29000 005 001 October 30 2016 3 62 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 349: ...NG PROCEDURE 3 MOORING 7 COVERS 8 GUST LOCK 9 EMERGENCY EXIT DOOR LOCK 10 FUEL SERVICING 11 FUELING OPTIONAL EXTERNAL FUEL GAUGE INSTALLED 13 FUELING OPTIONAL EXTERNAL FUEL GAUGE NOT INSTALLED15 OIL S...

Page 350: ...HJ1 29000 005 001 October 30 2016 4 2 NON POTABLE GREY WATER SERVICING 31 SCREEN CLEANING 33 WINDSHIELD CLEANING 33 GROUND DE ICING 34 GENERAL 34 DE ICING ANTI ICING FLUIDS 34 DE ICING METHODS 35 PRE...

Page 351: ...3 TOWING The HA 420 can be towed forward or pushed backward on hard surfaces if a tow bar is used The tow bar attaches to the axle of the nose wheel The towing vehicle must have a minimum drawbar pull...

Page 352: ...ers 7 have fully engaged each side of the nosewheel axle 4 If necessary extend the tow bar extension 6 so that it is longer than the nose of the airplane 5 Connect the tow bar to the towing vehicle 6...

Page 353: ...from the nose landing gear 11 Connect the nose landing gear torque links a Remove the ball lock pin from the upper torque link b Install the ball lock pin 2 to attach the upper torque link 1 to the lo...

Page 354: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 6 Figure 4 1 Nose Landing Gear Components FOR TRAINING PURPOSES ONLY...

Page 355: ...tall a mooring pin 4 in the receptacle 3 in each pylon Figure 4 2 2 Install a mooring pin 2 in the receptacle 1 in the bottom of the aft fuselage 3 Attach the mooring straps from the ground mooring po...

Page 356: ...0 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 8 COVERS Remove install engine probe and static covers shown in Figure 4 3 pre post flight Figure 4 3 Storage Cover and Plugs...

Page 357: ...y HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 9 GUST LOCK Remove install external and internal gust locks in accordance with Figure 4 4 Figure 4 4 Gust Locks FOR TR...

Page 358: ...HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 10 EMERGENCY EXIT DOOR LOCK Remove install emergency exit door lock in accordance with Figure 4 5 Figure 4 5 Emergency Exit Door Latch...

Page 359: ...tity units are in LBS or KGS There is a refuel master switch which is installed adjacent to the external fuel gauge that energizes the external fuel gauge and the fuel quantity signal conditioner NOTE...

Page 360: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 December 23 2016 4 12 Figure 4 6 Fuel Filler Port and External Fuel Gauge FOR TRAINING PURPOSES ONLY...

Page 361: ...turn the electric boost pumps ON during aircraft refueling Doing so may cause fuel to leak into vent system and prevent the airplane from refueling to maximum capacity If the electric boost pumps are...

Page 362: ...minimize risk of fuel fill overflow and spillage maintain a slow steady refuel rate as follows When Fuel Level is With Total Gallons Fueling Rate 1500 lbs Less than 225 gal 50 GPM Approx 4 gal every 5...

Page 363: ...the fuel cap 3 Remove the fuel cap 1 from the filler port Make sure that you do not let the fuel cap hit the side of the fuselage Figure 4 6 a Turn on the aircraft battery b Select FUEL synoptic 4 Add...

Page 364: ...NG POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 16 5 Remove the fuel nozzle 6 Install the fuel cap on the filler port 7 Remove the fuel grounding cable plug from pylon receptacle 8 Turn off...

Page 365: ...mining oil level Figure 4 7 The electronic oil level sensor is installed on the engine intermediate case on the optical sight glass mounting pad located on the inboard side of the engine The oil level...

Page 366: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 18 Figure 4 7 Oil Level Sight Glass and Electronic Oil Level Sensor FOR TRAINING PURPOSES ONLY...

Page 367: ...patch with an amber LOW oil level on the STATUS page as long as the sight glass on the outboard side of the engine shows oil above the add line WARNING Do not get engine oil on your skin or in your ey...

Page 368: ...EL CHECK Examine the oil level at the oil sight gauge if the oil level is at the FULL line no oil servicing is necessary Optional If the oil level is between the FULL and ADD lines you can add oil unt...

Page 369: ...d pressure TCP use the following formula Tambient in C TCP 294 26 Tambient 273 15 x Pcylinder Oxygen quantity turns amber on the STATUS page when oxygen quantity is below 465 liters The oxygen quantit...

Page 370: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 22 Figure 4 8 Oxygen Servicing Components FOR TRAINING PURPOSES ONLY...

Page 371: ...wheel tire pressure is 212 psi 5 psi 1 Remove the cap 2 from the tire air valve 1 Figure 4 9 2 Connect the tire pressure gauge to the tire air valve 3 If the NLG tire pressure is less than 125 psi or...

Page 372: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 24 Figure 4 9 Aircraft Tire Servicing FOR TRAINING PURPOSES ONLY...

Page 373: ...ened new flushing fluid is pumped from the service cart to the toilet by the fill switch on the airplane service panel Reference the AMM for required fluids INTERNAL SERVICING CAUTION Wear personal pr...

Page 374: ...INTENANCE HJ1 29000 005 001 October 30 2016 4 26 10 Remove the waste tank cap 2 and store it in the toilet cabinet 11 Close the bowl assembly 1 12 Install the toilet shroud panel assembly Figure 4 10...

Page 375: ...e waste service port 1 on the waste service panel Figure 4 11 4 Connect the lavatory servicing adapters to the lavatory service cart 5 Connect the flushing fluid hose 3 to the fill service port 4 on t...

Page 376: ...2 Reference the AMM for required fluids 11 Wait 30 seconds for the flushing fluid hose 3 to drain 12 Examine the waste tank 3 Figure 4 12 and the flushing fluid tank 1 Make sure the waste tank 3 fluid...

Page 377: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 29 Figure 4 11 Waste Service Panel FOR TRAINING PURPOSES ONLY...

Page 378: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 30 Figure 4 12 Externally Serviced Waste Water FOR TRAINING PURPOSES ONLY...

Page 379: ...1 Open the vanity cabinet door Figure 4 13 2 Rotate latch 5 90 degrees to remove tanks 3 Remove the dual tank assembly 2 and 4 from the airplane Separate the non potable water tank 2 from grey water t...

Page 380: ...30 2016 4 32 12 Install the non potable water tank 2 and the grey water tank 4 in the vanity cabinet 13 Rotate latches to lock tanks in place 14 Make sure fittings have mated correctly 15 Close the v...

Page 381: ...cloth lightly dampened with clean water CAUTION Do not use chemical cleaning agents as these may damage the coating on the glass surface WINDSHIELD CLEANING The windshields should be cleaned using a...

Page 382: ...d prior to takeoff Airplane de icing anti icing may be accomplished in either a one step or two step process During periods of precipitation once the airplane has been de iced anti icing is likely to...

Page 383: ...precipitation the process should begin as soon as possible after the airplane is clear of the hangar Holdover time after anti icing should be minimized Other methods of de icing anti icing include mec...

Page 384: ...The two step process is generally accomplished using Type II or IV fluid CAUTION Care must be taken not to allow the aircraft surfaces to re freeze between the de icing and anti icing processes Holdo...

Page 385: ...ues their own version of the hold over time and associated support publications independently of each other and SAE The L and R CABIN INFLOW switches must be selected to OFF prior to conducting a de i...

Page 386: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 38 Figure 4 14 De ice Anti ice Avoidance Areas FOR TRAINING PURPOSES ONLY...

Page 387: ...ice accumulation Ensure that elevator attach hinge points and elevator horn are completely de iced NOTE Minimize spray into the elevator control surface cavities Vertical Stabilizer Rudder The leading...

Page 388: ...dshield CAUTION Do not apply Type II or IV fluid to the radome NOTE Ensure the area between the speedbrake and fuselage is completely de iced Minimize spray into speedbrake cavities NOTE Minimize spra...

Page 389: ...d spraying de icing fluids directly into the engine There is no need to apply fluid to the engine inlet because nacelle heat may be turned on while on the ground The engines should be at idle during t...

Page 390: ...Wing including leading edges upper and lower surfaces aileron control surfaces and winglet Flaps Vertical and horizontal stabilizers including leading edges horns upper and lower surfaces rudder eleva...

Page 391: ...is adhering perform a tactile check Indications of loss of effectiveness of de icing anti icing fluid or contamination on airplane surfaces include Progressive surface freezing or snow accumulation Ra...

Page 392: ...Honda Aircraft Company HA 420 SERVICE HANDLING POM AND MAINTENANCE HJ1 29000 005 001 October 30 2016 4 44 This page intentionally left blank FOR TRAINING PURPOSES ONLY...

Page 393: ...erating Manual TERM DEFINITION AC Advisory Circular ACCU Aircraft Component Control Unit ADF Automatic Direction Finder ADS Air Data System ADS B Automatic Dependent Surveillance Broadcast AEO All Eng...

Page 394: ...Anti Ice Systems There are two anti ice systems on the HA 420 aircraft that affect aircraft performance 1 Engine anti ice 2 Wing anti ice AOA Angle of Attack AP Autopilot APB AFT Pressure Bulkhead AP...

Page 395: ...Back Course BIT Built In Test BOV Bleed Off Valve BRG Bearing CAIV Cowl Anti Ice Valve CAS Crew Alerting System CBIT Continuous Built In Test CBP Circuit Breaker Panels CDI Course Deviation Indicator...

Page 396: ...art Probes C T Carry through tank CVFDR Cockpit Voice Flight Data Recorder CVR Cockpit Voice Recorder CWS Control Wheel Steering DA Decision Altitude DACU Digital Antiskid Control Unit DCMP DC Electri...

Page 397: ...ngine Inlet Ice Protection System EIS Entry into Service EIS Engine Indication System ELT Emergency Locator Transmitter EMEDS Electro Mechanical Expulsive De Icing System END Endurance EPS Electrical...

Page 398: ...Fan Air Valve FAVC Fan Air Valve Controller FAVTS Fan Air Valve Temperature Sensor FCSOV Flow Control Shutoff Valve FD Flight Director F I Flight Idle FLC Flight Level Change FMA Flight Mode Annunciat...

Page 399: ...Idle GPS Global Positioning System GP Glide Path GS Glide Slope GTC Garmin Touch Screen Controllers GUI Graphical User Interface HOT Holdover Time HDG Heading HDG SEL Heading Select High Speed Cruise...

Page 400: ...mation in this manual is presented in terms of knots indicated airspeed KIAS unless otherwise stated and assumes zero instrument error IBIT Initiated Built In Test IF Intermediate Fix IAF Initial Appr...

Page 401: ...GCV Landing Gear Control Valve LH Left Hand LOC Localizer LOI Loss of Integrity Long Range Cruise Flight condition that provides 99 of the Maximum Specific Range LP Low Pressure LRU Line Replaceable U...

Page 402: ...ion Display MHS Magnetic Heading Sensor MI Indicated Mach number The Mach number reading as installed in the airplane Zero instrument error is assumed MMEL Master Minimum Equipment List MMO Maximum op...

Page 403: ...ine Low Pressure Fan Rotation Speed in Percent N2 Engine High Pressure Fan Rotation Speed in Percent OAT Outside Air Temperature OAT SAT OEI One Engine Inoperative OSP Over Speed Protection System PC...

Page 404: ...e altimeter It is the indicated pressure altitude corrected for position and instrument error In this manual altimeter instrument errors are assumed to be zero Position errors may be obtained from the...

Page 405: ...mbient free air static temperature obtained from either 1 ground meteorological sources or 2 from the total air temperature obtained from onboard temperature measurement adjusted for compressibility e...

Page 406: ...V Synthetic Vision SVT Synthetic Vision Technology SWPS Stall Warning Protection System TAS True Air Speed TAT Total Air Temperatures TAWS Terrain Awareness Warning System TBD To Be Determined TCAS Tr...

Page 407: ...ach Climb Speed VDC Volts Direct Current VDS Vibration Detection System VFR Visual Flight Rules VHF Very High Frequency VMO Maximum Operating Airspeed 270 Kcas The Speed That May Not Be Deliberately E...

Page 408: ...ode VSD Vertical Situation Display VSR Vertical Speed Required WAIV Wing Anti Ice Air Valve WAIXV Wing Anti Ice Cross Flow Valve WHC Windshield Heat Controllers WIPS Wing Ice Protection System WOW Wei...

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