Honda HondaJet HA-420 Pilots Operating Manual

Honda HondaJet HA-420 Pilots Operating Manual

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Honda Aircraft Company
PILOT'S OPERATING MANUAL
HondaJet
Model HA-420
Original Issue: December 10, 2015
Revision B2: March 3, 2017
This Pilot's Operating Manual is supplemental to the current FAA
Approved Airplane 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 governing authority.
These commodities, technology, or software were exported from the United States
in accordance with the Export Administration Regulations.
Diversion contrary to U.S. law is prohibited.
P/N: HJ1-29000-005-001
Copyright © Honda Aircraft Company 2016
FOR TRAINING PURPOSES ONLY

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  • Page 1 Flight Manual shall be the governing authority. These commodities, technology, or software were exported from the United States in accordance with the Export Administration Regulations. Diversion contrary to U.S. law is prohibited. P/N: HJ1-29000-005-001 Copyright © Honda Aircraft Company 2016 FOR TRAINING PURPOSES ONLY...
  • Page 2 Honda Aircraft Company Copyright © Honda Aircraft Co., LLC 2016 All Rights Reserved. Published by Honda Aircraft Company 6430 Ballinger Road Greensboro, NC 27410 USA www.hondajet.com Copyright © Honda Aircraft Company 2016 FOR TRAINING PURPOSES ONLY...
  • Page 3 Honda Aircraft Company LIST OF EFFECTIVE PAGES This list contains all current pages with effective revision date. Use this list to maintain the most current version of the manual: Insert the latest revised pages. Then destroy superseded or deleted pages.
  • Page 4 Honda Aircraft Company 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 Honda Aircraft Company RECORD OF REVISIONS DESCRIPTION OF REVISION REV. DATE REVISION Original 12/10/2015 Original Issue Not Used Added FIKI Information and 10/30/2016 General Update Removed requirement and 12/23/2016 added approval for use of fuel icing inhibitors. Updated frontmatter to align...
  • Page 6 Honda Aircraft Company This page intentionally left blank HJ1-29000-005-001 March 3, 2017 FOR TRAINING PURPOSES ONLY...
  • Page 7 Honda Aircraft Company 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. TEMP. DESCRIPTION OF REV. REVISION TEMPORARY REVISION DATE HJ1-29000-005-001 March 3, 2017...
  • Page 8 Honda Aircraft Company This page intentionally left blank HJ1-29000-005-001 March 3, 2017 FOR TRAINING PURPOSES ONLY...
  • Page 9 Honda Aircraft Company 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 REV. REVISION EFFECTIVITY INCORPORATED TITLE HJ1-29000-005-001 March 3, 2017 FOR TRAINING PURPOSES ONLY...
  • Page 10 Honda Aircraft Company This page intentionally left blank HJ1-29000-005-001 March 3, 2017 FOR TRAINING PURPOSES ONLY...
  • Page 11 Honda Aircraft Company DOCUMENTATION GROUP The following is a list that defines the group of current documents that provides pilots with the information required for the safe and efficient operation of the airplane. MANUAL REV. RELEASE MANUAL PART NO. DATE...
  • Page 12 Honda Aircraft Company This page intentionally left blank HJ1-29000-005-001 March 3, 2017 FOR TRAINING PURPOSES ONLY...
  • Page 13 Honda Aircraft Company supports authorized facilities worldwide for ease of maintenance and service on our aircraft. For information on how to obtain revisions for this manual or other Honda Aircraft Company service publications, visit the Honda Aircraft Company website: www.HondaJet.com.
  • Page 14 Honda Aircraft Company HA-420 INTRODUCTION SECTION CONTENTS Section 1 – Systems Descriptions A basic description of the airplane systems. Section 2 – Flight Planning Performance and fuel consumption data derived from flight testing. This data may be used for flight planning.
  • Page 15 HA-420 INTRODUCTION REVISION INSTRUCTIONS Honda Aircraft Company Technical Publications will update and distribute revisions to this manual as required. The List of Effective Pages shows the revision status of each page by notating the date of the revision. The Record of Revisions shows each revision and its date of release.
  • Page 16 Honda Aircraft Company HA-420 INTRODUCTION USE OF L(R) AND L-R L(R) or L-R may precede a CAS message text. L(R) applies if the message annunciates as either L or R, depending on the affected side. L-R applies to a condition affecting both sides simultaneously.
  • Page 17: Table Of Contents

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION SECTION 1 SYSTEMS DESCRIPTION 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 ....................
  • Page 18 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION ENGINE, FIRE PROTECTION AND FUEL ......75 ENGINE ....................... 75 FIRE PROTECTION ................... 87 FUEL ......................91 FLIGHT CONTROLS.............. 107 PRIMARY FLIGHT CONTROLS ............. 108 SECONDARY FLIGHT CONTROLS ............110 HYDRAULICS AND LANDING GEAR ....... 117 HYDRAULIC SYSTEM ................
  • Page 19 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION LIGHTING ................1801 EXTERIOR LIGHTING ................181 INTERIOR LIGHTING ................186 AVIONICS AND AFCS ............191 AVIONICS ....................191 AUTOMATIC FLIGHT CONTROL ............222 HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 20 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 21: Introduction

    Thrust is provided by two GE Honda HF-120 turbofan engines producing 1997 lbs. of thrust. Fuel is provided by each respective wet wing and additional fuel can be stored in the under fuselage carry through and an aft fuselage tank.
  • Page 22 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The landing gear is a fully retractable tricycle-type trailing link design with rudder pedal controlled steer-by-wire nosewheel steering and an antiskid braking system. The cabin environment is maintained using conditioned bleed air. Two independent temperature zones are provided inside the pressure vessel.
  • Page 23 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-1. Three Views of Aircraft HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 24 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-2. Turning Radius HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 25 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-3. Engine Inlet / Exhaust Danger Areas HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 26: Fuselage

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-4. Weather Radar Danger Areas FUSELAGE The fuselage structure is made from a cured carbon/epoxy material, with metal fittings for concentrated load transfer. The cabin section between the forward and aft pressure bulkheads is pressurized and contains a passenger door on the left side, an emergency exit door on the right side and includes two sky-view windows in the lavatory.
  • Page 27: Wing

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION WING The wing is a conventional aluminum design that contains a front spar, mid spar, rear spar, ribs, upper skin, lower skin and stringers. Most of the wing structural parts are machined from a solid piece of aluminum.
  • Page 28: Nacelle And Pylon

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION NACELLE AND PYLON Engine nacelles are streamlined aerodynamic panels used to house and protect engine components, direct airflow and decrease aerodynamic drag. The engine nacelles contain the forward and aft firewalls that comprise the fire zone.
  • Page 29 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-6. Aft Right Side Doors Figure 1-7. Left Side Doors HJ1-29000-005-001 October 30, 2016 1-13 FOR TRAINING PURPOSES ONLY...
  • Page 30 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 cockpit. HJ1-29000-005-001 October 30, 2016 1-14 FOR TRAINING PURPOSES ONLY...
  • Page 31 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-8. Main Entry Door – Airstair HJ1-29000-005-001 October 30, 2016 1-15 FOR TRAINING PURPOSES ONLY...
  • Page 32 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The MED has a latch/lock system with latch and locking handles that actuate the door mechanisms. The lock system has a key-lock security feature which can be used to secure the aircraft from unauthorized entry.
  • Page 33 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A pressure relief valve provides pressure equalization prior to opening and enhances the resistance to unlocking when cabin pressure is increased. Emergency Exit Door The Emergency Exit Door (EED) is located on the right side of the fuselage.
  • Page 34 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-9. Emergency Exit Door HJ1-29000-005-001 October 30, 2016 1-18 FOR TRAINING PURPOSES ONLY...
  • Page 35 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Aft Baggage Door The aft baggage door is mounted on the aft left side of the unpressurized fuselage. 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.
  • Page 36 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-10. Aft Baggage Door HJ1-29000-005-001 October 30, 2016 1-20 FOR TRAINING PURPOSES ONLY...
  • Page 37 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Forward Baggage Door The forward baggage door in the HA-420 is located at the left-hand side, in the un-pressurized nose section. The baggage door is an outward opening door hinged with two goose neck hinges. The door is latched by means of four (4) latch/lock units.
  • Page 38 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Forward Baggage Door Figure 1-11. HJ1-29000-005-001 October 30, 2016 1-22 FOR TRAINING PURPOSES ONLY...
  • Page 39 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION External Power Access Door The 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 contains a dual- pole switch to provide cockpit feedback of status.
  • Page 40 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 held closed by a button latch.
  • Page 41 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Electrical Service Doors Electrical service doors 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 latches.
  • Page 42 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Nacelle Access Doors Access doors are located on 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 each engine nacelle.
  • Page 43 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Nacelle Access Door Figure 1-15. HJ1-29000-005-001 October 30, 2016 1-27 FOR TRAINING PURPOSES ONLY...
  • Page 44 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications Status of 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.
  • Page 45 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Example STATUS Synoptic Page Figure 1-16. HJ1-29000-005-001 October 30, 2016 1-29 FOR TRAINING PURPOSES ONLY...
  • Page 46 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description The aft baggage door is not closed and latched with an engine running AFT BAG DOOR UNSAFE and the parking brake not set, on ground or in flight. The main cabin door is not closed...
  • Page 47: Windows

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION WINDOWS Flight Compartment Cockpit Windshield The cockpit is equipped with two windshields made from a laminated, fail-safe, curved and stretched acrylic as well as two side windows. All windows are de-fogged by means of warm air. Windshields also have internal heating elements for de-fogging and de-icing.
  • Page 48 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-32 FOR TRAINING PURPOSES ONLY...
  • Page 49: Flight Deck, Cabin And Cockpit

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION FLIGHT DECK, CABIN AND COCKPIT GENERAL The flight deck of the HondaJet Model HA-420 has been designed with advanced avionics and touch screen display control technologies to improve situational awareness and reduce pilot work load.
  • Page 50 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-17. Flight Deck Diagram HJ1-29000-005-001 October 30, 2016 1-34 FOR TRAINING PURPOSES ONLY...
  • Page 51: Displays

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 Pane. Figure 1-18. Primary Flight Display...
  • Page 52 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 area and two Display Panes.
  • Page 53 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Control Display Unit Two centrally mounted Control Display Units (CDUs) provide control of the avionics systems. Inputs are done using a combination of touch- screen and control knobs. The touch-screen can be used while wearing gloves.
  • Page 54 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Standby Instrument 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 navigation data from the avionics system can also be displayed.
  • Page 55: Control Panels And Controls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CONTROL PANELS AND CONTROLS Controls Cockpit switches and controls are grouped by system, and arranged to provide a workload-reducing cockpit “flow” during normal and emergency operations. Push button switches and rotary knobs are used for the majority of the controls.
  • Page 56 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Gaspers Two air gaspers, one on each outboard section of the instrument panel, provide air to each pilot. The gaspers pivot in place and can be angled as desired. Airflow can be adjusted by rotating the front edge of the gasper.
  • Page 57 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The CONTROL MODE switch is an alternate-action push-button switch. The normal state is white NORM and the non-normal state is amber HOLD. The CABIN DUMP switch is an alternate-action push-button switch with a red flip guard. The normal state is white NORM and the alternate state is amber DUMP.
  • Page 58 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Electrical Panel The Electrical Panel is located on the left side of the pilot knee bolster and is labeled ELECTRICAL. Figure 1-23. Electrical Panel The BATTERY switch is an alternate-action push-button switch. The normal state is white ON and the non-normal state is amber OFF.
  • Page 59 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION ELT Panel The Emergency Locator Transmitter (ELT) Panel is located on the pilot’s knee bolster. Figure 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 clockwise selects the ON position.
  • Page 60 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Landing Gear Panel The Landing Gear Panel is located on the pilot’s knee bolster. Figure 1-25. Landing Gear Panel The NOSE WHEEL STEERING switch is an alternate-action push- button switch. The normal state is white NORM and the non-normal state is amber OFF.
  • Page 61 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Engine Start Panel The ENGINE START control is centrally located on the center pedestal, just aft of the CDUs. Figure 1-26. Engine Start Panel The L and R ENGINE START switches are momentary push-button switches with green rings around the switch cap that illuminate.
  • Page 62 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION An illuminated BRAKE label is placed on the adjacent ENGINE START panel. Thrust Lever Quadrant The Thrust Lever quadrant is located in the center pedestal. Figure 1-27. Thrust Lever Quadrant The optional SPEED BRAKE switch is a toggle type of electro- mechanical latching switch.
  • Page 63 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The Thrust Lever controls are lever type controls that can be moved forward / aft. Four positions are labeled CUTOFF, IDLE, MCT and TO. A soft detent is incorporated at the MCT position. A ramp to a physical stop is incorporated at the TO position.
  • Page 64 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 position and rotating it clockwise selects the ON position.
  • Page 65 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The WING FLOW control is a three-position knob. The normal state is forward and is labeled NORM. Rotating the knob counter-clockwise selects the FROM L position and rotating it clockwise selects the FROM R position.
  • Page 66 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The CROSSFEED control is a three-position knob. The normal state is forward and is labeled NORM. Rotating the knob counter-clockwise selects the L ENG position and rotating it clockwise selects the R ENG position.
  • Page 67 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The YAW POWER control is an alternate-action push-button switch. The normal state is white NORM and the non-normal state is amber OFF. The YAW control is a three-position knob. The normal state is up and is labeled NORM.
  • Page 68 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Pneumatic Panel The Pneumatic panel is located on the right side of the center pedestal and labeled PNEUMATIC. Figure 1-32. Pneumatic Panel The CABIN INFLOW - L and CABIN INFLOW - R controls are alternate-action push-button switches.
  • Page 69 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Annunciator Panel An Annunciator Panel is located on the glareshield above each of the PFD displays in the primary field of view. Figure 1-33. Annunciator Panel The DISPLAY REVERSION switch is an alternate-action push-button switch.
  • Page 70 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Fire Panel The Fire Panel is located in the upper center of the glare-shield panel. Figure 1-34. Fire Panel The L ENGINE FIRE and R ENGINE FIRE switches are momentary- action push-button switches with a red flip guard. The normal state is dark and the non-normal state is red L (or R) ENGINE FIRE PUSH.
  • Page 71 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The AFCS Mode Control panel contains 14 momentary-action push- button type switches. These switches are labeled but are not illuminated. The CRS1 and CRS2 controls are rotary controls with multiple detents (“clicks”). Each knob also has a momentary push type action.
  • Page 72: Ceiling

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The PITCH switch is an alternate-action push-button switch. The normal state is dark and the non-normal state 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.
  • Page 73 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-37. Overhead Console HJ1-29000-005-001 October 30, 2016 1-57 FOR TRAINING PURPOSES ONLY...
  • Page 74: Side Walls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Two grab handles are located in the aft outboard section of the overhead console. A cockpit dome light is centrally mounted on the aft section of the overhead console. Two map lights are mounted just forward of the grab handles. The lighting pattern is designed to illuminate the lap area of the on-side crew member.
  • Page 75 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-38. Side Ledge (Pilot) HJ1-29000-005-001 October 30, 2016 1-59 FOR TRAINING PURPOSES ONLY...
  • Page 76 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Clipboard A flat area with a spring-loaded clip is placed on the forward section of the side ledge. Cup Holder A cup holder is mounted just aft of the clipboard. Oxygen Mask Container An oxygen mask container is mounted just aft of the cup holder on the side ledge.
  • Page 77 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-40. Circuit Breaker Panel (Co-Pilot) Storage The cockpit sidewalls house general storage provisions. Additional map and chart storage can be found in the optional forward left cabinet, directly behind the pilot’s seat, within reach of the pilot.
  • Page 78: Flight Controls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Flashlight A flashlight is installed behind the copilot on the right side of the plane. The flashlight has LED bulbs and will recharge when it is installed to the holder with the shed bus powered.
  • Page 79 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-41. Pilot Yoke The PITCH/ROLL control is a black momentary 4-way articulating switch (up, down, left, right to control) located on the aft side of the outboard yoke grip. The AFCS/TRIM MASTER control is a momentary red push-button switch located on the aft side of the outboard yoke grip.
  • Page 80 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The AP DISC/ACK control is a momentary black push-button switch located on the aft side of the inboard yoke grip. The SYSTEM CONTROL control is a momentary black push-button switch located on the aft side of the inboard yoke grip.
  • Page 81: Crew Seats

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The rudder pedals have two independently adjustable positions (forward and aft). The pedals are adjusted by pushing a white lever mounted on each pedal arm inboard and then moving the pedal to the desired location.
  • Page 82 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-43. Crew Seats HJ1-29000-005-001 October 30, 2016 1-66 FOR TRAINING PURPOSES ONLY...
  • Page 83 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Each crew seat is fully adjustable. Fore/aft position can be adjusted by moving a lever mounted on the inboard side by the floor aft and moving the seat to the desired location. When the lever is released, the seat will latch in place.
  • Page 84: Passenger Cabin

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION PASSENGER CABIN The standard cabin interior configuration 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 installed in the aft section of the cabin.
  • Page 85 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-44. General Floor Plan HJ1-29000-005-001 October 30, 2016 1-69 FOR TRAINING PURPOSES ONLY...
  • Page 86 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Cabin Seats When equipped with the optional Executive Seat Upgrade, the four main cabin seats can be adjusted fore/aft and inboard/outboard by lifting a lever mounted on the forward inboard side of the seat cushion and moving the seat to the desired location.
  • Page 87 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION is switched on when the Main Entry Door is opened. The timer can be reset for 10 minutes by activating a switch located on the entry area sidewall. The light will be off when the door is closed unless commanded on by the lighting control panel in the forward RH cabinet.
  • Page 88 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Safety Equipment Ordinance Signs and Placards Appropriate placards are located throughout the cabin. Illuminated Fasten Seat Belts, No Smoking and Return 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 forward side of each seat.
  • Page 89 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Oxygen Masks Drop down oxygen masks are available 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.
  • Page 90: Baggage Compartments

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION BAGGAGE COMPARTMENTS Forward Baggage The 9 cubic feet, forward baggage compartment is located just aft of the nose radome and has a single door mounted on the left side of the fuselage. The baggage space is unpressurized and unheated. Tie-down straps are provided.
  • Page 91: Engine, Fire Protection And Fuel

    Over-The-Wing Engine Mount (OTWEM) configuration. The GE Honda Aero Engines HF120 engine is a twin spool counter- rotating medium bypass ratio turbofan engine. The HondaJet HA-420 engine produces 1997 lbs. of thrust at sea level, flat rated to 77 ºF (25 ºC).
  • Page 92 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-47. GE Honda Aero Engines HF120 Engine General Arrangement Engine Control System The engine control system is a dual-channel Full Authority Digital Engine Control (FADEC) based system. The system controls the engine response to thrust command inputs from the thrust levers and other cockpit controls and provides information to the aircraft for cockpit indication, dispatch status and maintenance reporting.
  • Page 93 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION control system may limit fuel flow rate to prevent the engine from exceeding starting ITT temperature limits. Engine Start On the ground with the thrust levers in CUTOFF, engine start is initiated by pushing the engine start switch and then moving the thrust lever to IDLE.
  • Page 94 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION During ground starting, the FADEC has the authority to abort a start if ITT operating limitations are exceeded. CAUTION For all operating conditions other than ground starting, the FADEC will not limit thrust, fuel flow or any other control output to prevent ITT exceedance.
  • Page 95 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION When the TLA falls within the angle ranges associated with one of these ratings, the engine control system will control the engine to achieve the target engine speed based on ambient conditions. Separate power setting schedules have been incorporated into the software for the different bleed levels.
  • Page 96 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Synchronization The N synchronization function is used to set the N command of the right (slave) engine to be the same as the left (master) engine. The FADEC will automatically engage synchronization when all the required parameters are met.
  • Page 97 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Engine Oil System The engine oil system is completely self-contained and separate from any other aircraft fluid system. The oil system provides lubrication for the engine bearing elements and also assists in providing engine cooling.
  • Page 98 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Engine Fuel System An engine mounted, shaft-driven FPMU provides pressurized, metered fuel to the engine as well as pressurized fuel to the aircraft fuel system to be used for motive flow. Fuel passes through the FOHX before going to the engine.
  • Page 99 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications Engine parameters are displayed full-time on the EIS in green color. Analog indications are provided for N and ITT. Digital indications are available for N , ITT, N , Oil Pressure, Oil Temperature and Fuel Flow.
  • Page 100 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A white STARTER icon is displayed outboard of the secondary engine parameters when the starter is active. A white IGN icon is displayed outboard of the ITT gauge when ignition is commanded on. CAS Messages...
  • Page 101 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description The FADEC has detected a failure L(R) ENG OVERSPD PROT FAIL of the overspeed protection system The FADEC has detected starting abnormality or has automatically L(R) ENG START FAIL aborted a ground engine start, or...
  • Page 102 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-86 FOR TRAINING PURPOSES ONLY...
  • Page 103: Fire Protection

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION FIRE PROTECTION Fire Isolation Fire isolation is accomplished by firewalls incorporated as barriers between the nacelle fire zone and the pylon as well as firewalls at the forward and aft ends of the nacelle fire zone.
  • Page 104 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications The following alerts are activated when a fire is detected: • Red “FIRE” indication in the lower center of the ITT gauge • The L (or R) ENGINE FIRE PUSH switch illuminates •...
  • Page 105 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description A fire has been detected in the L(R) ENGINE FIRE indicated engine The associated fire detection L(R) FIRE DETECTOR FAIL system has failed Affected fire bottle has been L(R) FIRE BOTTLE DISCH...
  • Page 106 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-90 FOR TRAINING PURPOSES ONLY...
  • Page 107: Fuel

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 in the fuselage.
  • Page 108 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The fuel capacities are as listed below. Table 1-1. Fuel Tank Capacity Tank Capacities Tank Gal (US) lbs (Jet A) Wing L/H 93.5 Wing R/H 93.5 (C/T and Fuselage) 243.7 1635 Total 430.7 2890 A fuel temperature sensor is located in each collector tank.
  • Page 109 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Drain Valve Arrangement The fuel tanks have 7 drains. Two drain valves are located near the inboard end of each wing tank and three valves are located on the center lower surface of the carry-through tank.
  • Page 110 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A fuel isolation valve isolates the carry-through tank from the fuselage tank. 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.
  • Page 111 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-51. HA-420 Fuel Distribution System HJ1-29000-005-001 October 30, 2016 1-95 FOR TRAINING PURPOSES ONLY...
  • Page 112 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Electric Boost Pumps The fuel distribution system includes a backup Electric Boost Pump (EBP) in each collector tank. The pump is normally controlled automatically by aircraft avionics, but can be manually commanded ON or OFF using the L (R) Fuel Pump switch. The pump is automatically...
  • Page 113 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Fuel is consumed from the fuselage tank until the level of fuel in the fuselage tank reaches the water line of the level control float valve. At that time fuel from the C/T tank is consumed until the fuel level in the C/T tank drops below the level control float valve installed at the low point in the C/T tank.
  • Page 114 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION fuel tanks decreases, the valves open and allow air to enter the fuel tanks to replace consumed fuel. The inboard wing tank and the C/T tank vent float valves incorporate an integral pressure relief valve which opens to relieve positive pressure build-up in the wing tank such as caused by thermal expansion of fuel.
  • Page 115 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-52. Fuel Venting System Aircraft Refueling System A single refueling port distributes fuel to all four fuel tanks. The refuel system relies on gravity driven flow to feed fuel to each of the fuel tanks.
  • Page 116 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-53. Refueling System (Side View) An optional refueling panel and refuel master switch are located adjacent to the filler 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 to indicate if the displayed fuel quantity units are pounds or kilograms.
  • Page 117 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The primary refueling tube extends from the filler port on the aft fuselage to the bladder tank. Connecting the bladder tank and the carry-through tank is a tube containing the fuel isolation valve which is open during refueling operations.
  • Page 118 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-55. Fuel Quantity Probe Locations In addition, the fuel quantity probe located in each collector tank functions as a compensator probe to measure the fuel dielectric constant. Indications Fuel system information is displayed full time on the ASI in green color.
  • Page 119 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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, and fuel used in addition to fuel quantities and temperatures.
  • Page 120 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-57. Fuel Synoptic Page Display HJ1-29000-005-001 October 30, 2016 1-104 FOR TRAINING PURPOSES ONLY...
  • Page 121 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description Fuel Crossfeed has been selected for more than 5 minutes with FUEL CROSSFEED both engines running, or for 15 minutes with only one engine running Fuel crossfeed has been selected...
  • Page 122 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description Approximately 220 lbs or less of fuel remains in one of the wings based on either the optical low L(R) FUEL QTY LOW level sensor, or the fuel quantity indicator The left and/or right wing fuel FUEL TEMP HIGH temperature is above 60 °C...
  • Page 123: Flight Controls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION FLIGHT CONTROLS The primary flight control system on the HA-420 airplane is a reversible 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, elevators and rudder.
  • Page 124: Primary Flight Controls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION PRIMARY FLIGHT CONTROLS Pitch Axis The dual elevator control system is a manually-driven closed-loop cable and pushrod system. Two control columns allow control of the elevator system. The bottom of each column assembly, located below the floor, is connected by a horizontal tube.
  • Page 125 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-59. Gust Locks HJ1-29000-005-001 October 30, 2016 1-109 FOR TRAINING PURPOSES ONLY...
  • Page 126: Secondary Flight Controls

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION SECONDARY FLIGHT CONTROLS Pitch Trim System Each elevator is equipped with one trim tab driven by a single electrical trim actuator installed in the horizontal stabilizer. An actuator position sensor provides position feedback to the avionics system. The primary pitch trim is actuated by trim switches installed on each yoke.
  • Page 127 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Flaps Each wing is equipped with a 30%-chord, double-slotted fowler flap. The flaps can be commanded to one of three positions: UP, TO/APPR, and LDG. The Flap Actuation System (FAS) includes the aft pedestal mounted flap lever, an electronic Flap Actuation Controller (FAC), and identical left and right electrical flap actuators.
  • Page 128 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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.
  • Page 129 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications Trim, speed brake and flap information is displayed at the bottom of the ASI. Figure 1-61. ASI Secondary Flight Control Display Pitch trim position is displayed in both analog and digital form. One pointer is displayed for each tab.
  • Page 130 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION position. The pointer is displayed in amber if the flaps are failed. The flap display is decluttered above 20,300 feet. Speed brake position is indicated by a white EXTENDED or RETRACTED icon. The icon is decluttered 10 seconds after retraction.
  • Page 131 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description A fault has been detected by the roll ROLL TRIM FAULT trim system ROLL TRIM OFF Roll trim is selected OFF Speedbrake has failed SPEEDBRAKE FAIL STBY PITCH TRIM ON Standby pitch trim has been selected...
  • Page 132 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-116 FOR TRAINING PURPOSES ONLY...
  • Page 133: Hydraulics And Landing Gear

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION HYDRAULICS AND LANDING GEAR HYDRAULIC SYSTEM The hydraulic power system contains one electrical-motor-driven hydraulic pump (DCMP), a hydraulic reservoir-and-filter module, three accumulators, check valves, pressure transducers and pressure and temperature switches. The Main accumulator supplies the landing gear...
  • Page 134 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The reservoir holds approximately 1.27 gallons of hydraulic fluid at maximum full level (all three accumulators depressurized and landing gear extended). An electronic volume indicator is installed to allow monitoring of volume in the cockpit.
  • Page 135 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-62. Hydraulic Power System Schematic HJ1-29000-005-001 October 30, 2016 1-119 FOR TRAINING PURPOSES ONLY...
  • Page 136 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 change to amber or red when outside the normal operating range.
  • Page 137 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-63. Hydraulic Power System Synoptic HJ1-29000-005-001 October 30, 2016 1-121 FOR TRAINING PURPOSES ONLY...
  • Page 138 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description Main system hydraulic pressure is HYD PRESSURE LOW below allowable limits The Hydraulic Pump has failed HYD PUMP FAIL The hydraulic reservoir fluid level is HYD FLUID LEVEL LOW below allowable limits...
  • Page 139: Landing Gear

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION LANDING GEAR The tri-cycle landing gear system is hydraulically actuated and each landing gear is equipped with a single wheel. The nose landing gear uses an air/oil shock strut and has a steer-by-wire system that is electrically controlled and hydraulically actuated.
  • Page 140 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The MLG doors contain separate inboard and outboard doors. The outboard doors are mechanically operated and are attached to the strut. The inboard doors are hydraulically operated and have an uplock mechanism to lock the inboard door in the closed position. Door uplock...
  • Page 141 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Alternate Gear Extension Pulling the Alternate Gear Release handle mechanically actuates a dump valve and releases the uplocks. The landing gear starts to extend by gravity and is assisted by aerodynamic loads. The inboard doors remain open after emergency extension.
  • Page 142 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION If the landing gear is not down and locked when the aircraft is positioned/configured to land an aural “LANDING GEAR” alert will play and gear position will be displayed in red color with a solid red box around the gear indications.
  • Page 143: Wheels And Brakes

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION WHEELS AND BRAKES Main Landing Gear Wheel and Tire Assembly A single 17.5 x 5.75 R9, tubeless, radial tire with a speed rating of 190 mph (165 kts) is mounted on each MLG. If the brakes become overheated, three fusible plugs on the wheel will melt to decrease the tire pressure.
  • Page 144 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION automatic antiskid function resumes its standby mode after any wheel skid stops or brake pedal pressure is decreased below the wheel skid threshold level. Power brakes will still be available if the antiskid system fails.
  • Page 145: Nosewheel Steering

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications A white PARKING BRAKE icon is displayed below the landing gear indicator and on the STATUS synoptic page when the parking brake is set and pressure is sufficient. The color changes to amber if the brake is set but the pressure is insufficient or the brake is set in flight.
  • Page 146 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Description Message Normal wheel brakes have NORMAL BRAKES FAIL failed The antiskid braking system has ANTI-SKID FAIL failed The nosewheel steering system NOSEWHEEL STEER FAIL has failed, or is selected OFF during taxi operations...
  • Page 147: Pneumatics And Environmental

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION PNEUMATICS AND ENVIRONMENTAL Bleed air is supplied by each engine high-pressure compressor section and is used for the environmental system, wing and engine inlet anti-ice, cockpit window defog, and cabin pressurization. BLEED AIR SUPPLY SYSTEM...
  • Page 148 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The NPRSOV functions as a redundant regulator to the HPRSOV and will remain in the full open position under normal operation conditions. In the event of a failed open HPRSOV, the NPRSOV will regulate the conditioned bleed air pressure to approximately 70 psig.
  • Page 149: Environmental Control System

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications HPRSOV status as well as manifold temperature and pressure can be observed on the ENVIRONMENTAL synoptic page. ENVIRONMENTAL CONTROL SYSTEM A FCSOV regulates the conditioned bleed air from the Bleed Air Supply flow to either approximately 3 pounds per minute (ppm) or approximately 5 ppm depending on whether low or high flow condition is required.
  • Page 150 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-66. Temperature Modulating Valves HJ1-29000-005-001 October 30, 2016 1-134 FOR TRAINING PURPOSES ONLY...
  • Page 151 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The HXP is comprised of three Heat Exchangers (HX). Ambient (cooling) air entering the HX Pack first passes through a VCS condenser. The condenser exhaust air then passes through the LH and RH HX which are in parallel.
  • Page 152 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION When maximum bleed air heating or cooling is required in the cabin or cockpit, the TMV either 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 AFT Pressure Bulkhead (APB).
  • Page 153 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A Compressor Drive Module (CDM) delivers high temperature, high pressure gas to the condenser via refrigerant hoses. In the condenser, the refrigerant changes phase to a high temperature, high pressure liquid as ambient (cooling) air passing through the condenser. The liquid...
  • Page 154 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-69. CDU Thermostat Page If the Environmental system is selected to the Manual mode, the crew can directly 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...
  • Page 155 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Bleed air is available from either or both engines during ground operations. The Air Conditioner can operate on the ground with at least one generator operating or with external power. When operating on a single generator Ground Cooling Mode has to be selected through the CDU.
  • Page 156 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-70. Cabin Air Distribution System HJ1-29000-005-001 October 30, 2016 1-140 FOR TRAINING PURPOSES ONLY...
  • Page 157 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Cockpit Climate Zone The RH BAS conditioned bleed air is ducted to pilot and co-pilot foot warmers, aft through the center console and to the windshield and side window defog outlets. Circulated cockpit air, via the evaporator fan, mixes with the conditioned bleed air that is ducted to the windshield and side window defog outlets.
  • Page 158 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-71. Environmental Synoptic Page HJ1-29000-005-001 October 30, 2016 1-142 FOR TRAINING PURPOSES ONLY...
  • Page 159 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description There has been a failure of the L(R) CABIN BLEED FAIL cabin bleed system The cabin bleed temperature is above normal operating limits L(R) CABIN BLEED TEMP HIGH when operating in Manual Mode...
  • Page 160: Pressurization

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description Ground cooling mode has been ECS GND COOLING MODE selected PRESSURIZATION The cabin pressurization control system (CPCS) is comprised of the following: a Primary Outflow Valve (POFV), Secondary Outflow Valve (SOFV), a Cabin Pressurization Data Unit (CPDU), and pneumatic tube assemblies.
  • Page 161 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Mechanical positive and negative differential pressure limiters in each outflow valve will limit differential pressure within a safe range. Cabin Pressurization Data Unit The Cabin Pressurization Data Unit (CPDU) provides a redundant, and independent, set of cabin pressure data to the avionics system.
  • Page 162 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-72. CPCS Cabin Altitude Schedule The pressurization schedule ensures the cabin is depressurized upon landing. If the cabin was to be pressurized before landing, the CPCS will automatically depressurize it after touchdown. High Field Operation...
  • Page 163 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION c. The aircraft is in flight at an aircraft altitude less than 24,500feet, the cabin pressure altitude is above 8,000 feet, and the aircraft has taken off from an elevation of greater than 8,000 feet.
  • Page 164 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 icon. HJ1-29000-005-001 October 30, 2016 1-148 FOR TRAINING PURPOSES ONLY...
  • Page 165 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description Cabin differential pressure has CABIN ΔP HIGH exceeded 9.2 psid Cabin altitude has exceeded 10,000 ft (15,000 ft in High Field CABIN ALT HIGH Mode) The Cabin Pressurization system CABIN ALT CTRL FAIL...
  • Page 166: Bleed Air Leak Detection

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION BLEED AIR LEAK DETECTION A Bleed Air Leak Detection (BALD) system runs the length of the bleed air system. The BALD system runs through the hot side inlet of the Temperature Modulating Valve, including the heat exchanger inlets and the wing anti-ice system.
  • Page 167 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-74. Bleed Air Leak Detection Lines HJ1-29000-005-001 October 30, 2016 1-151 FOR TRAINING PURPOSES ONLY...
  • Page 168 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Each area uses two sensor loops except for the Left FCSOV zone and the Right FCSOV zone that use a single loop. Over Temperature Switches located in the engine inlet are used to monitor for leaks in the inlet assembly.
  • Page 169: Oxygen

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION OXYGEN The Crew and Passenger Oxygen System (CPOS) consists of an oxygen source, servicing connections and gauges, crew oxygen distribution and control and cabin oxygen distribution and control. Oxygen is stored in a single 50 cubic foot, 1850 psig oxygen bottle.
  • Page 170 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION a pneumatic harness to be filled with oxygen, which expands the harness and facilitates donning of the crew oxygen mask with one-hand operation. Releasing the levers deflates the harness to provide a tight fit of the mask.
  • Page 171 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Normal Mode At cabin altitudes between 8,000 and 30,000 feet, the regulator delivers oxygen diluted with ambient air when the user inhales. At cabin altitudes between 30,000 and 35,000 feet, the regulator delivers 100% oxygen.
  • Page 172 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Audio Opening the stowage box doors selects the on-side mask microphone on. Selecting the OXY MASK AUDIO switch to EMER forces the overhead cockpit speakers on at a preset volume and both pilots’ microphone inputs to the oxygen mask microphones.
  • Page 173 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description Cabin oxygen is off and cabin CABIN OXYGEN OFF altitude is greater than 15,500 ft Oxygen quantity is less than 465 OXYGEN LOW liters The oxygen pressure transducer is OXYGEN QTY FAIL...
  • Page 174 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-158 FOR TRAINING PURPOSES ONLY...
  • Page 175: Ice And Rain Protection

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION ICE AND RAIN PROTECTION The ice and rain protection system contains five subsystems: wing ice protection system, engine inlet ice protection system, horizontal tail ice protection system, heated air data probes and windshield vision protection system.
  • Page 176 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Wing Ice Protection System Conditioned air from the Bleed Air Supply system is routed to L and R Wing Anti-Ice Air Valves (WAIV) and to the Wing Anti-Ice Cross Flow Valve (WAIXV). From the WAIVs, the air is distributed through a pair of piccolo tubes and then vented through holes in the inboard lower wing area and a vent on the outboard lower wing.
  • Page 177 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Automatic wing anti-ice activation is inhibited in the following cases: • On the ground • During the first 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 commanded closed and the WAIXV...
  • Page 178 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Engine Inlet Ice Protection System The Engine Inlet Ice Protection System (EIIPS) uses high-pressure bleed air that is regulated by a pressure-regulating Cowl Anti-Ice Valve (CAIV). Selecting the L or R ENGINE ANTI-ICE switch to ON opens the associated CAIV, allowing bleed air to flow into the inlet lip.
  • Page 179 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION When activated, the EMEDS begins to fire in a 2-minute cycle with 20 seconds of “active firing” and a 100-second period of “dwell” between firings. If operating in the NORM mode, once the ice detected signal is...
  • Page 180 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Ice Inspection Lights The aircraft is equipped with a single ice inspection light on the left side of the fuselage. An optional right side ice inspection light is also available. The light will automatically illuminate at night when ice is detected or can manually be commanded on or off.
  • Page 181 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Horizontal Tail Ice Protection System HTIPS status is displayed on the ICE PROTECTION synoptic page. The leading edge is displayed in green when the system is operating and amber when failed. The leading edge is white when commanded off.
  • Page 182 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-78. Ice Protection Synoptic Page HJ1-29000-005-001 October 30, 2016 1-166 FOR TRAINING PURPOSES ONLY...
  • Page 183 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description The engine anti-ice system has L(R) ENG ANTI-ICE FAIL failed Both ice detectors have failed ICE DETECT FAIL Ice detected and one or more ICE PROT NOT ACTIVE protection systems are not active...
  • Page 184 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description Wing Anti-Ice has been selected WING ANTI-ICE UNAVAIL ON but is unavailable during single bleed operations There is a failure of the L(R) WSHD ZONE FAIL windshield zone heat There is an overheat of the...
  • Page 185 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description WING ANTI-ICE switch selected WING ANTI-ICE ON WING FLOW switch selected WING FLOW FROM L(R) FROM L(R) Affected zone unable to select L(R) WSHD ZONE FAULT high heat mode Applicable windshield zone not...
  • Page 186 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page intentionally left blank HJ1-29000-005-001 October 30, 2016 1-170 FOR TRAINING PURPOSES ONLY...
  • Page 187: Electrical

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION ELECTRICAL The electrical power system uses a split-bus architecture to power the airplane. The primary source of electrical power is a 28 VDC engine- driven starter-generator on each engine. Each starter-generator is air cooled and rated at 325 Amps. A dedicated Generator Control Unit (GCU) for each starter-generator supplies field excitation, voltage regulation, and protection.
  • Page 188 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-79. Electrical Schematic HJ1-29000-005-001 October 30, 2016 1-172 FOR TRAINING PURPOSES ONLY...
  • Page 189: Power Generation And Storage

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Two power distribution units (PDU) perform primary power distribution for the airplane systems. These units contain contactors, solid state relays, and electronic and processor controls. The PDUs also contain circuit breakers that route power to non-essential systems. Essential system circuit breakers are installed on the pilot’s and co-pilot’s circuit...
  • Page 190: Load Distribution

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The BATTERY switch, when selected ON, connects the batteries to BATT BUS 1 and BATT BUS 2. Both batteries are used in parallel to provide power when both generators are not online. External Power The external power can supply 28 VDC to the airplane during ground operations.
  • Page 191 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION If a generator is lost the bus tie automatically closes, allowing the remaining generator to power both sides of the electrical system. Cabin A and B and the Shed buses are automatically shed in this case as is the Air Conditioner.
  • Page 192 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-80. Electrical System ASI A white EXT PWR ON or EXT PWR AVAIL icon is displayed when external power is powering the aircraft or is available to do so. A white STARTER icon is displayed on the EIS when the starter- generator is operating in starter mode as is a green halo around the START button.
  • Page 193 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-81. Electrical System Synoptic Page HJ1-29000-005-001 October 30, 2016 1-177 FOR TRAINING PURPOSES ONLY...
  • Page 194 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description Both generators are off-line in the ELEC EMER POWER air, or on the ground with both engines running Battery bus 1 is isolated from the BATTERY BUS 1 FAIL aircraft electrical system...
  • Page 195 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description The generator has failed L(R) GENERATOR FAIL Generator load is above allowable L(R) GENERATOR OVERLOAD limits Main Bus 1 has failed or is MAIN BUS 1 FAIL isolated from the airplane electrical system...
  • Page 196 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION This page left intentionally blank HJ1-29000-005-001 October 30, 2016 1-180 FOR TRAINING PURPOSES ONLY...
  • Page 197: Exterior Lighting

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION LIGHTING EXTERIOR LIGHTING The following external lights are installed: • Landing lights • Taxi lights • Strobe / Anti-collision lights • Beacon • Navigation lights • Ice inspection lights • Recognition lights • Logo lights Figure 1-82.
  • Page 198 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION All exterior lights use light-emitting diode (LED) technology. The external lights can be operated in Normal mode or in Manual mode. In Normal mode, lights are commanded on/off automatically at certain flight phases/time of day by two Aircraft Component Control Units (ACCUs).
  • Page 199 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Table 1-2. NORMAL (Automatic) Lighting Conditions Light “ON” Condition Take-off run and landing roll or in-flight with gear Landing down. Recognition - In flight and airplane below transition altitude* during dawn to dusk. Pulsed...
  • Page 200 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Landing Lights The landing lights are two-function lights which are installed behind a lens in the forward belly fairing under the fuselage. Recognition Lights The Recognition lights are located in the outboard leading edge of each wing.
  • Page 201 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Indications Commanded state of each light is displayed on the STATUS synoptic page. Indications are magenta if in the Normal mode and cyan if in the Manual mode. Figure 1-84. STATUS Page Exterior Lights Section...
  • Page 202: Interior Lighting

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION INTERIOR LIGHTING The following interior lights are installed: • Pilot and co-pilot map light • Cockpit overhead light • Cockpit footwell lights • Instrument panel lights • Entry / overhead lights • Sconce lights •...
  • Page 203 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-85. CDU Lighting Configuration Page HJ1-29000-005-001 October 30, 2016 1-187 FOR TRAINING PURPOSES ONLY...
  • Page 204 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A Cockpit Overhead light is positioned in the ceiling and provides general illumination for the cockpit. The light can be switched on or off and brightness can be adjusted through the CDU Interior Lights page.
  • Page 205 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Cabin Lighting System The Cabin Lighting Switch Panel provides centralized control for most cabin lights. Reading lights and Table lights are controlled by switches located with the lights. Four lighting schemes can be selected by dedicated switches on the Cabin Lighting Switch Panel: Entry, Cabin, Accent, and Night.
  • Page 206 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION A cabin entry light is positioned in the ceiling centered above the Main Entry Door area of the aircraft. The Cabin Entry Overhead Light will be on for 10 minutes 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.
  • Page 207: Avionics And Afcs

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION AVIONICS AND AFCS AVIONICS ® ® The avionics system is built around a three-display Garmin G3000 system. The system includes three, 14-inch landscape GDU 1400 screens configured as two Primary Flight Displays and one Multi- Function Display.
  • Page 208 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Dual VHF Com radios, dual VHF Navigation radios (VOR, ILS, and Marker Beacon), and dual WAAS GPS receivers are included. Each PFD consists of a Primary Flight Display and a Display Pane. The MFD has two individual Display Panes or one full screen Display Pane,...
  • Page 209 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The CDUs are used for systems navigation, data entry, and data retrieval tasks. The CDU incorporates a color display, hard controls, and an infrared touchscreen as the primary means for system control and data entry.
  • Page 210 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Initialization When the system powers up, the MFD will present a splash screen with status of all databases that will have to be acknowledged before the display can be used. After the acknowledgement, the MFD will display the STATUS synoptic page and a Map in the Display Pane.
  • Page 211 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-89. EIS / ASI Data Layout HJ1-29000-005-001 October 30, 2016 1-195 FOR TRAINING PURPOSES ONLY...
  • Page 212 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Reversionary Mode A reversionary display mode is activated automatically if a display failure is detected. The Reversionary display mode presents a PFD next to a condensed version of the EIS/ASI over the top of a condensed Display Pane.
  • Page 213 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-91. PFD Reversionary Mode Crew Alerting System The crew alerting system presents visual, aural and tactile alerts triggered by signals or groups of signals sent by the monitored systems. Alerts are indicated by use of PFD flags or CAS messages presented in a dedicated window on the lower right of each PFD.
  • Page 214 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Acknowledgement Certain warning level alerts are accompanied by an aural alert. In some cases these can be silenced, or the repeat rate be reduced, by pressing the master caution/warning switch. Aural alerts can also be annunciated for certain conditions that are associated with an exceedance or PFD flags rather than a CAS message.
  • Page 215 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Primary Air Data and Temperature In addition to the basic air data parameters, two Multi-function Air Data Probes also provide angle of attack (AoA) data for the Stall Warning/Protection System (SWPS). On-side air data and attitude/heading data are normally displayed on each PFD.
  • Page 216 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION When both PFDs are displaying data from the same source, or if cross- side data is used, an annunciation is provided on the PFDs. A flag is also posted if there a miscompare between the two AHRS systems.
  • Page 217 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Barometric correction can be set using a bezel mounted rotary knob. Pushing the knob selects standard baro. Barometric units (inches of Mercury or hectoPascals) can be selected via a HP/IN bezel button. The V limits are indicated by a red thermometer-type overspeed strip on the airspeed tape.
  • Page 218 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The available pages are: STATUS – displays pre-flight data including fluid/fuel quantity as well as door status and commanded state of exterior lights. ENVIRONMENTAL – displays status of the bleed air and environmental systems including valve states, pressure / temperature readings and air conditioner/ground cooling fan running status.
  • Page 219 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 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 CONTROL button a second time returns the CDU to the previously displayed page.
  • Page 220 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The available system control pages are: Power Control – allows display and reset of tripped Solid State Relays (SSR). Manual or automatic operation mode for the optional cabin power outlets can also be selected.
  • Page 221 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION 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 conditions. Figure 1-94. Systems Controls Page...
  • Page 222 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-95. Individual Systems Control Pages HJ1-29000-005-001 October 30, 2016 1-206 FOR TRAINING PURPOSES ONLY...
  • Page 223 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION System Tests Pages A System Tests page is available on the Aircraft Systems page or through the Initialization page. This page allows activation of several pilot initiated tests. A Preflight Test button commands the system to run all the tests in a sequential manner.
  • Page 224 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Figure 1-96. System Tests Page HJ1-29000-005-001 October 30, 2016 1-208 FOR TRAINING PURPOSES ONLY...
  • Page 225 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Communication Systems VHF Communication Dual digital-tuning VHF Com radios are provided. Tuning, selection of active radio and volume/squelch control is made using the CDU touch- screen or control knobs. If availability of both CDUs should be lost, both radios are automatically tuned to 121.500 MHz.
  • Page 226 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Controller Pilot 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 CDU message icon is posted whenever a message is received.
  • Page 227 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION SatCom (Iridium) Telephone (Optional) The optional SatCom telephone provides for air-ground, world-wide communications through the Iridium satellite constellation. The pilot speaks and listens through the headset, and initiates and terminates calls through the CDU. The Iridium system is also used to provide weather data for the optional Garmin Connext weather data link.
  • Page 228 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION operations. Area navigation is GPS-based. Flight plans can be created, edited and stored using the CDUs. The navigation database contains departure, arrival and approach procedures that can be loaded into the flight plan. The system also allows the pilot to view trip planning information, fuel...
  • Page 229 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Radio Altimeter Data from the optional single Radio Altimeter is displayed on the PFD, when the height is between 0 and 2,500 ft. Minimums alert may be selected based on radio altimeter height in which case the selected height is displayed on the PFD as is rising terrain symbology on the altitude tape.
  • Page 230 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Traffic Collision Avoidance System I (TCAS I) The TCAS I system provides collision avoidance information from other suitably-equipped aircraft within the reception range. Traffic information can be displayed on a dedicated Display Pane or as an overlay on the Map page.
  • Page 231 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The red light provides an indication of the working mode for the ELT. After the self-test: a series of short flashes indicates that the self-test failed, and one long flash indicates that the self-test passed. In operating mode: periodic flashes occur during emergency frequency (121.5 MHz)
  • Page 232 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION SiriusXM® Weather Data Link An optional SiriusXM® Weather Data Link provides weather and Temporary Flight Restrictions (TFR) information as well as digital audio entertainment in the United States. Weather/TFR information can be displayed on a dedicated page or as an overlay on the Map page. Control is through the CDUs.
  • Page 233 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The optional TAWS A system provides additional alerting based on onboard sensors. Display and control is the same as the baseline TAWS B system. Windshear An automatic reactive windshear detection system provides aural alerts and PFD flags when a windshear is detected.
  • Page 234 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION moves a selection box up/down on the display. Pushing the scroll wheel with the checklist displayed selects/de-selects the highlighted checklist item. Pushing the scroll wheel for more than 2 seconds removes the checklist and restores the previously displayed page on the PFD Display Pane.
  • Page 235 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION CAS Messages Message Description AHRS 1(2) FAIL The associated AHRS unit has failed The associated air data computer is AIR DATA 1(2) FAIL not providing proper data The intercom and associated speaker, handmic, and oxygen mask mic have...
  • Page 236 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description The affected air data probe is operating in a degraded mode AIR DATA 1(2) FAULT Some minor degradation in air data may be experienced under certain flight conditions The avionics software/hardware configuration is not correct for the...
  • Page 237 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description FDR FAIL The Flight Data Recorder has failed Affected glide slope has failed GLIDE-SLOPE 1(2) FAIL Associated handmic or PTT switch is L(R) MIC STUCK ON stuck on The avionics system is in...
  • Page 238: Automatic Flight Control

    Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION AUTOMATIC FLIGHT CONTROL A digital Automatic Flight Control System (AFCS) is integrated within the System avionics architecture. The AFCS includes the following: • Flight director • Two-axis digital flight control autopilot • Manual Electric Trim (MET) for all three axes •...
  • Page 239 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Flight Director The flight director function displays pitch and roll targets, based on the selected mode and sensor data, on the Primary Flight Display. The AFCS Mode Controller panel is used to select flight director modes. Active modes are displayed in green with the lateral mode to the left and the vertical mode to the right.
  • Page 240 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Altitude The altitude mode is selected using the ALT button and will cause the FD to hold the altitude at the time of activation. The ALT mode is also automatically armed when another vertical mode is active.
  • Page 241 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Approach The approach mode is armed using the APR button. When capture criteria is met, the mode will activate and track the active navigation source. Takeoff and Go-around The Takeoff or Go-around modes are activated by pushing either TO/GA switch.
  • Page 242 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION The CWS button can be used to disengage the pitch and roll servos from the flight control surfaces and allows the crew to fly the airplane manually without disengaging the autopilot. When the CWS button is released appropriate flight director references are synchronized to the current aircraft state.
  • Page 243 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION NOTE During a single engine descent, the RB and YD will alternate depending on the thrust setting on the operating engine. The pilot has to disengage the YD prior to landing, if the YD was engaged before the RB engagement, to prevent it from auto-engaging during the flare following the thrust reduction.
  • Page 244 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION • A white CSC annunciation in the Engine Indication System (EIS) display. To maintain the CSC target speed, the FADEC will modulate engine thrust in either direction up to 5% N or 5 degrees of equivalent thrust lever angle change, whichever is more constraining.
  • Page 245 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Stall Warning and Protection The Stall Warning and Protection System (SWPS) include a stick shaker and a stick pusher, as well as visual indications and aural alerts. The stall warning and protection system is primarily driven from the air data probe angle of attack (AoA) data.
  • Page 246 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION When no longer in icing conditions and the aircraft is confirmed free of ice, the angles and speeds can be reset to the baseline settings by pushing the Stall Warn Ice Advance Reset button on the Systems Controls CDU page.
  • Page 247 Honda Aircraft Company HA-420 SYSTEMS DESCRIPTION Message Description AFCS ROLL SERVO OFF Roll Servo is selected off Yaw Servo is selected off AFCS YAW SERVO OFF AUTOPILOT FAIL The autopilot function has failed An automatic pitch trim fault has been detected by the autopilot. If...
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  • Page 249 Honda Aircraft Company HA-420 FLIGHT PLANNING 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 PERFORMANCE ..........31 ALTITUDE CAPABILITY............37 HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
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  • Page 251 Honda Aircraft Company HA-420 FLIGHT PLANNING FLIGHT PLANNING INTRODUCTION Performance data for cruise, climb, descent and holding are presented in the charts and tables on the following pages. Performance data for takeoff and landing are presented in the Airplane Flight Manual. Fuel consumption information is derived from flight test data and average engine performance.
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  • Page 287 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES SECTION 3 OPERATING PROCEDURES AND TECHNIQUES TABLE 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 ...............
  • Page 288 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES TAKEOFF ................... 21 ROLLING TAKEOFF ................. 22 PERFORMANCE TAKEOFF ..............22 AFTER TAKEOFF ..................23 ENROUTE OPERATIONS ............25 CLIMB ......................25 CRUISE ......................25 DESCENT ....................25 TERMINAL AREA OPERATIONS ......... 25 APPROACH ....................
  • Page 289 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES 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 LANDING ..............51 EMERGENCY DESCENT ................
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  • Page 291: General

    GENERAL The purpose of this section is to provide crew with common techniques to reference for operation of the HondaJet HA-420. Use of these procedures enhances crew performance and effectiveness. The techniques in this manual are not mandatory, nor are they intended to supersede airmanship and good judgment or guidance of a regulatory nature.
  • Page 292: Cockpit/Crew Resource Management

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES refers to the crew member who has the primary responsibility for control and navigation of the aircraft and accomplishes or calls for checklists, as required. The pilot monitoring (PM) assists the PF by monitoring the...
  • Page 293 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES and corresponds to the appropriate label on the center console next to the speedbrake control lever. SPEEDBRAKE (if installed)………RET Some checklist items refer to multiple user interfaces (panels and switches) or specific areas on the displays and these appear in checklists with initial capitalization convention as seen here.
  • Page 294: Crew Alerting

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES CREW ALERTING The alerting system of the HA-420 airplane follows certain conventions in accordance with the AFM. These alerts consist of visual, aural, and tactile means of notifying the pilot of advisory, abnormal, and emergency operating conditions.
  • Page 295 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Cyan advisory CAS messages only require routine pilot reaction. There are two types of advisory messages. One type posts when a control is placed in a non-normal position; the other posts due to a fault or loss of redundancy that requires simple or no crew action.
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  • Page 297: Preflight Inspection

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES PREFLIGHT INSPECTION PRELIMINARY EXTERIOR INSPECTION Accomplish the Preliminary Exterior Inspection in accordance with the AFM. See Section 4 for the number and location of covers, tie-downs, and the rudder gust lock. COCKPIT/CABIN INSPECTION Accomplish the Cockpit/Cabin Inspection in accordance with the AFM.
  • Page 298: Exterior Inspection

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES NOTE On battery power, CDU 2 is unpowered. The copilot can still transmit and tune radios through CDU 1. EXTERIOR INSPECTION Accomplish the exterior inspection in accordance with the AFM. GROUND OPERATIONS...
  • Page 299 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Trim Panel Check the trim panel in accordance with the AFM. Refer to AFM Section 5, Takeoff Pitch Trim Settings, and set the pitch trim for takeoff. NOTE The pitch trim green band varies based on flap setting. If planning to conduct the takeoff with flaps UP, the pitch trim will be in the green band at this time.
  • Page 300 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Avionics Initialization Accomplish the avionics initialization in accordance with the AFM. When all data has been entered correctly, select Accept to confirm. NOTE If powering up on battery, the SERVO POWER and...
  • Page 301: Starting Engines

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES STARTING ENGINES Accomplish the Starting Engines checklist in accordance with the AFM. Passenger Briefing The passenger briefing should include consideration of the following items as well as other regulatory guidance and industry recommended practices.
  • Page 302 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES CAS Messages The pilot should understand each CAS message displayed before engine start and correct those CAS messages not present in normal operations. NOTE The following CAS messages appear during normal operations...
  • Page 303: Before Taxi

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES BEFORE TAXI Wing Anti-Ice If ground icing conditions exist or if icing is expected during takeoff, select wing anti-ice ON to allow the system to warm up. NOTE Monitor ITT during operation of wing anti-ice.
  • Page 304: Taxi

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Runway Designate takeoff runway and enter required distance using the Flight Plan and the Takeoff Data menu. WARNING Failure to verify performance data may adversely affect SurfaceWatch™ function and prevent annunciation of warnings and cautions.
  • Page 305: Before Takeoff

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES BEFORE TAKEOFF Accomplish the Before Takeoff checklist in accordance with the AFM. Verify that flaps are in the desired position for takeoff (UP or TO/APPR) and the posted speeds and entered required runway distance are appropriate for the selected flap position.
  • Page 306 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES NOTE Crew must confirm that appropriate V-speeds are still posted. V-speeds may become deselected and revert back to default values after performing engine starts on battery power. NOTE The takeoff field length provided in the performance section of the flight manual is based on a dry runway.
  • Page 307: Takeoff

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Radar The Weather Radar may be operated on the ground. Ensure that the caution zone is kept clear of ground personnel. NOTE When using Weather Radar map overlay, the Tilt/Bearing icon can be displayed when Tilt/Bearing control is not active.
  • Page 308: Rolling Takeoff

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES ROLLING TAKEOFF When cleared for takeoff, advance thrust levers enough to begin taxi onto the runway. Steadily advance the thrust levers after aligning aircraft with the runway. After observing normal engine response and alignment with runway centerline, continue to advance thrust levers to TO.
  • Page 309: After Takeoff

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES AFTER TAKEOFF Retract the gear after achieving a positive rate of climb. When clear of obstacles and at no less than 130 KIAS, retract the flaps. Confirm the gear and flaps are retracted on the ASI, and then reduce the thrust levers to MCT.
  • Page 310 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-1. Normal Takeoff Profile HJ1-29000-005-001 October 30, 2016 3-24 FOR TRAINING PURPOSES ONLY...
  • Page 311: Enroute Operations

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES ENROUTE OPERATIONS CLIMB Accomplish the Climb checklist in accordance with the AFM. CRUISE Accomplish the Cruise checklist in accordance with the AFM. Perform routine systems monitoring throughout the duration of cruise operations.
  • Page 312 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Avionics When loading an instrument approach procedure, the pilot should thoroughly review each field on the CDU Procedures page to ensure accuracy. Additionally, the pilot should preview the instrument approach procedure chart and use it to input the approach minimums. After loading, view the flight plan to verify that it loaded correctly.
  • Page 313 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES WARNING Failure to verify performance data may adversely affect SurfaceWatch™ function and prevent annunciation of warnings and cautions. NOTE The landing distance provided in the performance section of the flight manual is based on a dry runway. If landing on a wet runway, it is recommended to increase the predicted landing distance by 30%.
  • Page 314: Instrument Approach

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES INSTRUMENT APPROACH If timing is required or desired, select the Timer on the CDU prior to commencing the approach. NOTE In VNV mode, the FMS may not command a descent to the FAF altitude when it appears in the flight plan as an “at or...
  • Page 315 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Vectors to Final Accomplish the Approach checklist no later than the base leg prior to beginning the instrument approach. Use the CDU to activate “vectors to final” after selecting HDG for flight guidance. Slow to 160 KIAS no later than intercepting the final approach course.
  • Page 316 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Wait until landing is assured, but no later than 50 ft AGL, to disconnect the yaw damper. Just prior to landing, confirm proper landing configuration. Approach with Vertical Guidance Establish the final configuration prior to the final approach fix or glideslope/glidepath intercept.
  • Page 317 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-2. Circling Approach HJ1-29000-005-001 October 30, 2016 3-31 FOR TRAINING PURPOSES ONLY...
  • Page 318 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Set the map zoom at useful range (2-5 nm) 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 (SV) runway symbol to verify the aircraft is on a 3°...
  • Page 319 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Instrument Approach Profiles Suggested profiles for precision and non-precision approaches followed by a missed approach are shown in the figures that follow. Figure 3-3. Non-Precision Approach HJ1-29000-005-001 October 30, 2016 3-33 FOR TRAINING PURPOSES ONLY...
  • Page 320 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-4. Precision Approach HJ1-29000-005-001 October 30, 2016 3-34 FOR TRAINING PURPOSES ONLY...
  • Page 321: Vfr Pattern

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES VFR PATTERN Accomplish the Approach checklist before 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...
  • Page 322: Landing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Extend landing gear no later than abeam the point of intended landing. Extend flaps to landing during the final turn, and maintain minimum 130 knots until established on final. Complete the Before Landing checklist.
  • Page 323: Balked Landing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES BALKED LANDING Initiate the balked landing by pressing the TOGA button, advance the thrust levers to TO, and pitch to maintain V . Follow the flight director initially, then adjust the pitch attitude as required to maintain...
  • Page 324: Missed Approach

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES MISSED APPROACH For a go around or missed approach, simultaneously press the TOGA button, advance the thrust levers to TO, and adjust initial pitch attitude to follow the flight director. Retract the flaps to TO/APPR and maintain .
  • Page 325: After Landing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES AFTER LANDING Accomplish the After Landing checklist in accordance with the AFM. Although the After Landing checklist should be accomplished as soon as possible after exiting the runway, none of the items on the checklist must be accomplished immediately.
  • Page 326: Shutdown

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES SHUTDOWN Upon arrival at the parking spot, set the parking brake and signal to the ground crew to install wheel chocks. Verify parking brake indication on the ASI. EXTERNAL POWER External power is not a requirement, but air conditioning and many...
  • Page 327: Emergency And Abnormal Procedures

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES EMERGENCY AND ABNORMAL PROCEDURES The purpose of this section is to provide crew with common techniques to reference for emergency/abnormal operations. The techniques in this manual are not mandatory, nor are they intended to supersede airmanship and good judgment or guidance of a regulatory nature.
  • Page 328 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES If an engine fails or another situation occurs that requires the flight crew to abort the takeoff prior to reaching V , reduce the thrust levers to idle, apply the brakes and extend the speedbrake. See the figure that follows.
  • Page 329 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES If an engine failure occurs after V but before V , at V , remove the hand from thrust levers and place it on the yoke. At V , rotate the aircraft with a steady, smooth motion to achieve the FD target takeoff pitch attitude in 3-4 seconds.
  • Page 330 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-7. Engine Failure at or Above V HJ1-29000-005-001 October 30, 2016 3-44 FOR TRAINING PURPOSES ONLY...
  • Page 331: Single-Engine Approach And Landing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES SINGLE-ENGINE APPROACH AND LANDING Use the AFM Single-Engine Approach and Landing checklist instead of the normal Descent, Approach, and Before Landing checklists. Fly the final approach at V + 5 with flaps TO/APPR. When landing is assured, select flaps to LDG and slow to V .
  • Page 332 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-8. Visual Approach Single Engine HJ1-29000-005-001 October 30, 2016 3-46 FOR TRAINING PURPOSES ONLY...
  • Page 333: Single Engine Instrument Approach Profiles

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES 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 that follow. Figure 3-9. Non-Precision Approach – Missed Approach, Single Engine...
  • Page 334 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-10. Precision Approach – Missed Approach, Single Engine HJ1-29000-005-001 October 30, 2016 3-48 FOR TRAINING PURPOSES ONLY...
  • Page 335: Approaches In Icing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES APPROACHES IN ICING Slow to 180 KIAS no later than intercepting the final approach course or reaching the initial approach fix. Arm approach mode (or NAV) when ATC approach clearance is received. Maintain 180 KIAS as long as possible.
  • Page 336 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-11. Approach in Icing Conditions HJ1-29000-005-001 October 30, 2016 3-50 FOR TRAINING PURPOSES ONLY...
  • Page 337: Reduced Flap Landing

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES REDUCED FLAP LANDING A reduced flap landing is any landing with other than LDG flaps. Use the AFM Reduced Flap Landing checklist instead of the normal Descent, Approach, and Before Landing checklists. Land on the longest suitable runway.
  • Page 338 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Approach Briefing In addition to normal approach briefing items, address non-standard landing speeds and distance. Figure 3-12. Visual Approach, No Flaps HJ1-29000-005-001 October 30, 2016 3-52 FOR TRAINING PURPOSES ONLY...
  • Page 339: Emergency Descent

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES 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 the figure that follows. Figure 3-13. Emergency Descent...
  • Page 340: Additional Maneuvers

    In addition to the normal and emergency operational skills and procedures, certain training maneuvers will be required during training for a type rating in the Honda HA-420. STEEP TURNS To initiate a steep turn, roll into a 45° bank in the desired direction while increasing the N approximately 3%.
  • Page 341 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-14. Steep Turns HJ1-29000-005-001 October 30, 2016 3-55 FOR TRAINING PURPOSES ONLY...
  • Page 342: Stalls

    Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES STALLS Stalls are to be completed at an altitude that will 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.
  • Page 343 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-16. Approach to Stall Clean Configuration - Simulator HJ1-29000-005-001 October 30, 2016 3-57 FOR TRAINING PURPOSES ONLY...
  • Page 344 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-17. Approach to Stall Takeoff Configuration – Aircraft HJ1-29000-005-001 October 30, 2016 3-58 FOR TRAINING PURPOSES ONLY...
  • Page 345 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-18. Approach to Stall Takeoff Configuration – Simulator HJ1-29000-005-001 October 30, 2016 3-59 FOR TRAINING PURPOSES ONLY...
  • Page 346 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-19. Approach to Stall Landing Configuration – Aircraft HJ1-29000-005-001 October 30, 2016 3-60 FOR TRAINING PURPOSES ONLY...
  • Page 347 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES Figure 3-20. Approach to Stall Landing Configuration - Simulator HJ1-29000-005-001 October 30, 2016 3-61 FOR TRAINING PURPOSES ONLY...
  • Page 348 Honda Aircraft Company HA-420 OPERATING PROCEDURES AND TECHNIQUES This page intentionally left blank HJ1-29000-005-001 October 30, 2016 3-62 FOR TRAINING PURPOSES ONLY...
  • Page 349 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE SECTION 4 SERVICING, HANDLING, AND MAINTENANCE TABLE OF CONTENTS GENERAL ..................3 TOWING ..................3 TOWING PROCEDURE ................3 MOORING ..................7 COVERS ......................8 GUST LOCK ....................9 EMERGENCY EXIT DOOR LOCK ............10 FUEL SERVICING ..............
  • Page 350 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 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 PREFLIGHT DE-ICING INSPECTION CHECKLIST ....... 42...
  • Page 351: General

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE SERVICE, HANDLING, AND MAINTENANCE GENERAL This section provides information to supplement the HA-420 Aircraft Maintenance Manual. In the event any information herein conflicts with information in the HA-420 Aircraft Maintenance Manual, the HA-420 Aircraft Maintenance Manual takes precedence.
  • Page 352 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 2. Install the ball-lock pin (2) in the upper torque link (1) for storage. The pin should be installed through the storage holes in the steering collar. NOTE Adapter cups are available that allow a universal tow bar to fit the HA-420 nose wheel axle.
  • Page 353 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 10. Remove the tow-bar 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 lower torque link.
  • Page 354 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-1. Nose Landing Gear Components HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 355: Mooring

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE MOORING 1. Install 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.
  • Page 356: Covers

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE COVERS Remove/install engine, probe, and static covers shown in Figure 4-3 pre/post flight. Figure 4-3. Storage Cover and Plugs HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 357: Gust Lock

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE GUST LOCK Remove/install external and internal gust locks in accordance with Figure 4-4. Figure 4-4. Gust Locks HJ1-29000-005-001 October 30, 2016 FOR TRAINING PURPOSES ONLY...
  • Page 358: Emergency Exit Door Lock

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE EMERGENCY EXIT DOOR LOCK Remove/install emergency exit door lock in accordance with Figure 4-5. Figure 4-5. Emergency Exit Door Latch Assembly HJ1-29000-005-001 October 30, 2016 4-10 FOR TRAINING PURPOSES ONLY...
  • Page 359: Fuel Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE FUEL SERVICING The HA-420 model airplane does not use a pressure fueling system but a gravity feed system through a single port adapter, installed on the upper right side of the aft fuselage. There is an optional digital external fuel gauge installed on the fuselage skin adjacent to the fuel cap (Figure 4-6).
  • Page 360 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-6. Fuel Filler Port and External Fuel Gauge HJ1-29000-005-001 December 23, 2016 4-12 FOR TRAINING PURPOSES ONLY...
  • Page 361: Fueling: Optional External Fuel Gauge Installed

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE When the refuel master switch is pushed, the external fuel gauge illuminates all three fuel tank full indicators for approximately 3 seconds to verify indicator lights are operational. During refueling, the fuel first fills the carry-through tank, the wing tanks, and then the fuselage tank.
  • Page 362 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 5. Press and hold the refuel master switch (5). a. Verify the three fuel-tank full indicator lights will illuminate for 3 seconds as an operational check. NOTE It takes approximately 5 seconds after pressing the refuel master switch before the correct fuel quantity is displayed.
  • Page 363: Fueling: Optional External Fuel Gauge Not Installed

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 7. Remove the fuel nozzle. 8. Install the fuel cap on the filler port. 9. Remove the fuel grounding cable plug from pylon receptacle. FUELING: OPTIONAL EXTERNAL FUEL GAUGE NOT INSTALLED 1. Connect the fuel grounding cable plug to the receptacle in the pylon.
  • Page 364 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 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 aircraft battery. HJ1-29000-005-001 October 30, 2016...
  • Page 365: Oil Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE OIL SERVICING Each engine has an oil tank that is integral to the intermediate compressor case. The engines use an electronic oil level sensor as the primary method of determining 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.
  • Page 366 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-7. Oil Level Sight Glass and Electronic Oil Level Sensor HJ1-29000-005-001 October 30, 2016 4-18 FOR TRAINING PURPOSES ONLY...
  • Page 367: Servicing The Engine Oil System

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE The output from the electronic oil level sensor shows the oil level on the STATUS synoptic. The oil level indication is either LOW (amber) or NORM (green), and is only available when the engines are not in operation.
  • Page 368: Oil Level Check

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE OIL LEVEL 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 until the oil level is at the FULL line (observing the time constraints as mentioned above).
  • Page 369: Oxygen Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE OXYGEN SERVICING CAUTION Use Aviators Breathing Oxygen only. NOTE Only qualified maintenance personnel should perform oxygen system servicing. NOTE Oxygen duration tables required for mission planning are located in NORMAL PROCEDURES of the Airplane Flight Manual.
  • Page 370 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-8. Oxygen Servicing Components HJ1-29000-005-001 October 30, 2016 4-22 FOR TRAINING PURPOSES ONLY...
  • Page 371: Tires

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE TIRES Inspecting Tire Pressure Calculate tire pressure with weight on wheels. The correct nose wheel tire pressure is 125 psi +5, -0 psi. The correct main wheel tire pressure is 212 psi ±5 psi.
  • Page 372 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-9. Aircraft Tire Servicing HJ1-29000-005-001 October 30, 2016 4-24 FOR TRAINING PURPOSES ONLY...
  • Page 373: Waste Water Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE WASTE WATER SERVICING The toilet is serviced internally in the lavatory area or externally through an optional external service panel installed in the aft right fuselage. Service panel caps for the drain and flush tubes are in the service panel.
  • Page 374 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 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. Internally Serviceable Toilet...
  • Page 375: External Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE EXTERNAL SERVICING CAUTION Wear personal protective equipment during servicing of the water system. 1. Prepare the lavatory service cart for service. Refer to the manufacturer’s instructions. NOTE Only qualified personnel should operate the lavatory service support equipment.
  • Page 376 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 7. Push and hold the MACERATOR PUMP switch (5) for a maximum of 15 seconds until the toilet waste tank is empty. 8. Wait 30 seconds for the waste fluid hose (2) to drain.
  • Page 377 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-11. Waste Service Panel HJ1-29000-005-001 October 30, 2016 4-29 FOR TRAINING PURPOSES ONLY...
  • Page 378 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-12. Externally Serviced Waste Water HJ1-29000-005-001 October 30, 2016 4-30 FOR TRAINING PURPOSES ONLY...
  • Page 379: Non-Potable/Grey Water Servicing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE NON-POTABLE/GREY WATER SERVICING The optional non-potable and grey water tanks are installed in the bottom of the vanity. A pump is used to pump water to the faucet. The non- potable water tank has a volume of 0.58 gallons. The grey water tank has a volume of 1.0 gallons to prevent a water overflow.
  • Page 380 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE 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.
  • Page 381: Screen Cleaning

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE SCREEN CLEANING The Garmin screens can be cleaned using a microfiber or soft cotton cloth lightly dampened with clean water. CAUTION Do not use chemical cleaning agents, as these may damage the coating on the glass surface.
  • Page 382: Ground De-Icing

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE GROUND DE-ICING This section contains procedures for de-icing HA-420 airplanes on the ground before flight. For additional information, refer to OPERATING IN ICING CONDITIONS (Section 4 - Normal Procedures) and ICING LIMITATIONS (Section 2 – Limitations) of the Airplane Flight Manual.
  • Page 383: De-Icing Methods

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Refer to TAKEOFF – ANTI-ICE FLUID PERFORMANCE ADDITIVES (Section 5 – Performance) of the Airplane Flight Manual for increased takeoff speeds and distances if Type II or IV fluids are used. DE-ICING METHODS The preferred method of de-icing is to place the airplane in a heated hangar.
  • Page 384 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE airplane surfaces. Fluid manufacturers provide recommended dilution mixtures based on outside air temperatures (OAT) and precipitation conditions. The flight crew should consult with the de-icing crew to verify that the fluid mixture is suitable for the atmospheric conditions.
  • Page 385 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Aircraft Ground holdover tables are approved by the SAE G-12 Committee and issued each year prior to the northern winter season. These are then reviewed by AEA (Association of European Airlines), FAA and TC (Transport Canada), who are the main practical sources of...
  • Page 386 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Figure 4-14. De-ice/Anti-ice Avoidance Areas HJ1-29000-005-001 October 30, 2016 4-38 FOR TRAINING PURPOSES ONLY...
  • Page 387 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE The areas listed below require special attention during the ground de- icing process. CAUTION If snow or ice has accumulated on the horizontal tail, the tail must be de-iced first Horizontal Tail Remove all accumulations from the upper surface of the stabilizer and elevator.
  • Page 388 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Fuselage Remove snow top-to-bottom. Avoid spraying heated fluids directly on cabin and cockpit windows. Ensure that the radome area is clean. Remove any fluid runoff from cockpit windows and radome prior to departure.
  • Page 389 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE Engines Snow/ice removal from the engine inlet should be accomplished using mechanical means. Check the engine for freedom of movement. If the engine fan does not rotate freely, hot air or some other means is recommended to de-ice the engine.
  • Page 390: Preflight De-Icing Inspection Checklist

    Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE PREFLIGHT DE-ICING INSPECTION CHECKLIST In addition to the normal preflight inspection, a de-icing inspection must be performed immediately following or during the ground de-icing/anti- icing process. All items below must be confirmed free of snow, ice and/or frost accumulation: •...
  • Page 391 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE A final inspection shall be performed prior to takeoff to ensure effectiveness of the de-icing procedure. The inspection should be conducted within 5 minutes of takeoff and may be conducted from inside the airplane.
  • Page 392 Honda Aircraft Company HA-420 SERVICE, HANDLING, AND MAINTENANCE This page intentionally left blank HJ1-29000-005-001 October 30, 2016 4-44 FOR TRAINING PURPOSES ONLY...
  • Page 393 Honda Aircraft Company HA-420 GLOSSARY SECTION 5 HONDA AIRCRAFT AVIATION GLOSSARY The purpose of this section is to provide crew with the common terms and acronyms used in this Pilot’s Operating Manual. TERM DEFINITION Advisory Circular Aircraft Component Control Unit...
  • Page 394 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Altitude Altitude Select ALT SEL AMLCD Active Matrix Liquid Crystal Display Airport Moving Map Display AMMD There are two anti-ice systems on the HA-420 Anti-Ice Systems aircraft that affect aircraft performance: 1. Engine anti-ice 2.
  • Page 395 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Bleed Air Leak Detection BALD Bleed Air System Battery Bus Back Course Built-In Test Bleed Off Valve Bearing Cowl Anti-Ice Valve CAIV Crew Alerting System CBIT Continuous Built-In-Test Circuit Breaker Panels Course Deviation Indicator...
  • Page 396 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Crew and Passenger Oxygen System CPOS Copilot Course Cruise Speed Control Compact Smart Probes Carry-through tank CVFDR Cockpit Voice Flight Data Recorder Cockpit Voice Recorder Control Wheel Steering Decision Altitude DACU Digital Antiskid Control Unit...
  • Page 397 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Electrical Control Panel Electrical Control Unit Emergency Exit Door Exhaust Gas Temperature Engine Inlet Ice Protection System EIIPS Entry into Service Engine Indication System Emergency Locator Transmitter Electro-Mechanical Expulsive De-Icing System EMEDS Endurance...
  • Page 398 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Full Authority Digital Engine Control FADEC Final Approach Fix Flap Actuation System Fan Air Valve Fan Air Valve Controller FAVC FAVTS Fan Air Valve Temperature Sensor FCSOV Flow Control Shutoff Valve Flight Director...
  • Page 399 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Ground Cooling Fan Generator Control Unit Ground Idle Global Positioning System Glide Path Glide Slope Garmin Touch Screen Controllers Graphical User Interface Holdover Time Heading HDG SEL Heading Select High Speed Cruise at MCT...
  • Page 400 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Horizontal Tail Ice Protection System HTIPS Heat Exchanger Integrated Avionics Computer Indicated airspeed. The airspeed indicator reading as installed in the airplane. The information in this manual is presented in terms of knots indicated airspeed (KIAS) unless otherwise stated and assumes zero instrument error.
  • Page 401 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Light-Emitting Diode Landing Field Elevation LGCL Landing Gear Control Lever Landing Gear Control Unit LGCU Landing Gear Control Valve LGCV Left Hand Localizer Loss of Integrity Flight condition that provides 99% of the...
  • Page 402 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Minimum Descent Altitude Mask Deployment System Main Entry Door Manual Electric Trim Minimum Equipment List Multi-Function Display Magnetic Heading Sensor Indicated Mach number. The Mach number reading as installed in the airplane. Zero instrument error is assumed.
  • Page 403 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Notice To Airman NOTAM Nacelle Pressure Regulating Shutoff Valve NPRSOV NWSS Nosewheel Steering System Engine Low-Pressure Fan Rotation Speed in Percent Engine High-Pressure Fan Rotation Speed in Percent Outside Air Temperature. (OAT = SAT)
  • Page 404 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Pilot Not Flying Primary Outflow Valve POFV Pilot Operating Manual Position Altitude measured from standard sea level pressure Pressure Altitude (29.92 in hg) by a pressure altimeter. It is the indicated pressure altitude corrected for position and instrument error.
  • Page 405 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Area Navigation RNAV Rotary Variable Differential Transformer RVDT SACV Service Air Check Valves Service Air Pressure Regulating Valve SAPRV Static air temperature. The ambient free air static temperature obtained from either: 1) ground meteorological sources, or...
  • Page 406 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Speed Select SPD SEL Solid-State Relays STAR Standard Terminal Arrival Route Standby STBY Synthetic Vision Synthetic Vision Technology SWPS Stall Warning/Protection System True Air Speed Total Air Temperatures TAWS Terrain Awareness Warning System...
  • Page 407 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Top Of Descent Takeoff Go Around TOGA Track Takeoff Decision Speed Takeoff Safety Speed Approach Climb Speed Volts Direct Current Vibration Detection System Visual Flight Rules Very High Frequency Maximum Operating Airspeed (270 Kcas). The Speed That May Not Be Deliberately Exceeded In Any Flight Condition.
  • Page 408 Honda Aircraft Company HA-420 GLOSSARY TERM DEFINITION Landing Reference Speed Vertical Speed Mode Vertical Situation Display Vertical Speed Required Wing Anti-Ice Air Valve WAIV WAIXV Wing Anti-Ice Cross Flow Valve Windshield Heat Controllers Wing Ice Protection System WIPS Weight-On-Wheels WTBF...

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