SPECIFICATIONS

is integrated with a cabin configurable for a wide variety of missions and payloads. It features a spacious interior with room for up to five passengers to enjoy wide-open, club seating. Passenger comfort is enhanced with a quiet and smooth ride in virtually all weather conditions. The Rolls Royce 250-C47E/4 turbine FADEC engine delivers exceptional hot and high performance along with a cruise speed of 133 kts (246 kph). Bell’s products are backed by our renowned in-service support. The Bell 407GXi proves you don’t have to sacrifice comfort for performance. The superior performance of the Bell 407GXi Garmin G1000H NXi suite provides critical flight information for crews at a glance, allowing for greater situational awareness and safety. TAKING THE BELL 407 PRODUCT LINE EVEN FURTHER No matter what today’s mission might be, the Bell 407GXi provides the performance, reliability and capability you need to safely accomplish it. Federal Aviaton Administration (FAA) NextGen Capability Now: The Bell 407GXi exceeds the requirements of the FAA’s NextGen air traffic management system, that all aircraft in controlled airspace must be equipped with ADS-B “Out” technology”. The Bell 407GXi is certified for ADS-B “Out” and ADS-B “In”. The GTX 335R ES transponder provides the ADS-B “Out” capability required by NextGen. For more complete situational awareness that exceeds the FAA’s NextGen requirements, an optional Garmin GTX 345R ES transponder is available for the Bell 407GXi. The GTX 345R transponder gathers information about the Bell 407GXi position, track and speed from the G1000H® NXi WAAS GPS and combines it with the ADS-B “In” data for a more precise picture of what’s happening in the sky. This allows for better pilot situational awareness and leads to safer air traffic separation capabilities. The GTX 345R also receives subscription-free Flight Information Service- Broadcast (FIS-B) weather broadcasts from ADS-B ground stations. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 2 Specification Summary (U.S. Units) WEIGHTS (LB) Empty Weight (Base Aircraft) [1] 2700 Max Gross Weight with External Load 6,000 Max Internal Gross Weight (Normal / Optional [2]) 5,000 / 5,250 Maximum External Load (Cargo Hook Limit) 3,100 Useful Load (Base Aircraft, Normal / Optional [2]) 2,300 / 2,550 PERFORMANCE SUMMARY [3] (International Standard Day except as noted) Takeoff Gross Weight (lb) 4,000 4,500 5,000 5,250 [2] IGE Hovering Ceiling ISA ft 19,900 16,790 13,550 5,420 ISA + 20 °C ft 17,160 13,410 9,960 3,140 ISA + 30 °C ft 15,380 11,580 7,880 2,070 OGE Hovering Ceiling ISA ft 18,720 15,260 11,940 5,420 ISA + 20 °C ft 15,540 11,730 8,270 3,140 ISA + 30 °C ft 13,720 9,760 5,850 2,070 Service Ceiling (MCP) ISA ft 20,000+ 20,000+ 18,940 17,490 ISA + 20 °C ft 20,000+ 19,230 16,050 14,510 ISA + 30 °C ft 20,000+ 17,720 14,320 12,650 Maximum Cruise Speed (True Airspeed) SL, ISA ktas 136 135 133 132 SL, ISA + 20 °C ktas 138 136 134 133 4,000 ft, ISA ktas 141 140 136 134 4,000 ft, ISA + 20 °C ktas 141 138 134 131 Cruise at Long Range Cruise Speed (LRC) Range (Standard Fuel, No Reserve) SL, ISA nmi 350 344 337 332 LRC Speed (Average True Airspeed) ktas 118 118 120 120 Range (Standard Fuel, No Reserve) 4000 ft, ISA nmi 393 383 373 365 LRC Speed (Average True Airspeed) ktas 118 119 120 120 Endurance at Loiter (60 kias) (Standard Fuel, No Reserve ) SL, ISA hr 4.2 4.1 4.0 3.9 4,000 ft, ISA hr 4.7 4.5 4.3 4.2 ENGINE RATING TRANSMISSION RATING (Engine Output) Rolls-Royce 250-C47E/4 with Full Authority Digital Electronic Control Takeoff Power (5 minutes) 674 SHP Takeoff Power Uninstalled Thermodynamic Capability 862 SHP Maximum Continuous 630 SHP Mechanical Limit 674 SHP Maximum Continuous Uninstalled Thermodynamic Capability 761 SHP FUEL CAPACITY (Usable) Mechanical Limit 630 SHP Standard 127.8 US Gallons Auxiliary (Optional) 19.0 US Gallons Notes: [1] The Empty Weight (base aircraft) includes 7-place upholstered interior with individual seat belts, carpeting, and soundproofing material. Ballast is not included since it is a function of installed optional equipment. 13 pounds of oil is included. [2] Operation at Internal Gross Weight above 5,000 pounds requires the Optional Increased Internal Gross Weight Kit. [3] Refer to demonstrated takeoff and landing and maximum operating altitude notes on the performance charts. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 3 BELL 407GXi Specification Summary (Metric Units) WEIGHTS (KG) Empty Weight (Base Aircraft) [1] 1,224 Max Gross Weight with External Load 2,722 Max Internal Gross Weight (Normal / Optional [2]) 2,268 / 2,381 Maximum External Load (Cargo Hook Limit) 1,406 Useful Load (Base Aircraft, Normal / Optional [2]) 1,043 / 1,156 PERFORMANCE SUMMARY [3] (International Standard Day except as noted) Takeoff Gross Weight (kg) 1,814 2,041 2,268 2,381 [2] IGE Hovering Ceiling ISA m 6,066 5,118 4,130 1,652 ISA + 20 °C m 5,230 4,087 3,036 957 ISA + 30 °C m 4,688 3,530 2,402 631 OGE Hovering Ceiling ISA m 5,706 4,651 3,639 1,652 ISA + 20 °C m 4,737 3,575 2,521 957 ISA + 30 °C m 4,182 2,975 1,783 631 Service Ceiling (MCP) ISA m 6,096+ 6,096+ 5,773 5,331 ISA + 20 °C m 6,096+ 5,861 4,892 4,423 ISA + 30 °C m 6,096+ 5,401 4,365 3,856 Maximum Cruise Speed (True Airspeed) SL, ISA km/h 252 249 246 244 SL, ISA + 20 °C km/h 255 253 248 246 1,200 m, ISA km/h 262 259 252 248 1,200 m, ISA + 20 °C km/h 261 256 248 243 Cruise at Long Range Cruise Speed (LRC) Range (Standard Fuel, No Reserve) SL, ISA km 649 637 624 616 LRC Speed (Average True Airspeed) km/h 218 219 222 222 Range (Standard Fuel, No Reserve) 1,200 m, ISA km 728 710 690 676 LRC Speed (Average True Airspeed) km/h 218 221 222 222 Endurance at Loiter (111 km/h) (Standard Fuel, No Reserve ) SL, ISA hr 4.2 4.1 4.0 3.9 1,200 m, ISA hr 4.7 4.5 4.3 4.2 ENGINE RATING TRANSMISSION RATING (Engine Output) Rolls-Royce 250-C47E/4 with Full Authority Digital Electronic Control Takeoff Power (5 minutes) 503 kW Takeoff Power Uninstalled Thermodynamic Capability 643 kW Maximum Continuous 470 kW Mechanical Limit 503 kW Maximum Continuous Uninstalled Thermodynamic Capability 567 kW FUEL CAPACITY (Usable) Mechanical Limit 470 kW Standard 484 Liters Auxiliary (Optional) 72 Liters Notes: [1] The Empty Weight (base aircraft) includes 7-place upholstered interior with individual seat belts, carpeting, and soundproofing material. Ballast is not included since it is a function of installed optional equipment. 5.9 kilograms of oil is included. [2] Operation at Internal Gross Weight above 2,268 kilograms requires the Optional Increased Internal Gross Weight Kit. [3] Refer to demonstrated takeoff and landing and maximum operating altitude notes on the performance charts. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 4 Helicopter Dimensions LOW SKID GEAR HIGH SKID GEAR WITH AA FLITESTEP® SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 5 BELL 407GXi Helicopter Dimensions OPTIONAL BLADE FOLDING KIT DIMENSIONS MINIMUM HANGAR SIZE US Units Metric Units Rotor not Folded 25.1 ft x 36.7 ft 7.7 m x 11.2 m Rotor Folded (High Skid Gear) 8.7 ft x 41.6 ft 2.6 m x 12.7 m Note: Allowance should be made for skid gear, ground wheels, empty fuel condition and door lip when considering hangar door width and height OPTIONAL EMERGENCY FLOAT GEAR WITH AA FLOATSTEP™ BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 6 LANDING GEAR LOADING AT MAXIMUM GROSS WEIGHT (5,000 LB/2,268 KG) - based on one “G” static conditions at most structural cg limit HELIPAD LOADING (5,000 lb) - US UNITS GEAR TYPE LOADING POUNDS CONTACT AREA SQ.IN. CONTACT PRESSURE PSI FORWARD AFT FORWARD AFT FORWARD AFT Standard Skid 1338 3662 16.5 x 2 16.5 x 2 41 111 High Skid 1307 3693 16.5 x 2 16.5 x 2 40 112 Emer Float Skid 1307 3693 16.5 x 2 16.5 x 2 40 112 HELIPAD LOADING (2,268 KG) - METRIC UNITS GEAR TYPE LOADING (KG) CONTACT AREA (CM²) CONTACT PRESSURE KG/CM² FORWARD AFT FORWARD AFT FORWARD AFT Standard Skid 606.9 1661.1 106.5 x 2 106.5 x 2 2.9 7.8 High Skid 592.9 1675.1 106.5 x 2 106.5 x 2 2.8 7.9 Emer Float Skid 592.9 1675.1 106.5 x 2 106.5 x 2 2.8 7.9 HELIPAD LOADING (2,381 KG) - METRIC UNITS GEAR TYPE LOADING (KG) CONTACT AREA (CM²) CONTACT PRESSURE KG/CM² FORWARD AFT FORWARD AFT FORWARD AFT Standard Skid 637.3 1744.1 106.5 x 2 106.5 x 2 3.0 8.2 High Skid 622.3 1759.0 106.5 x 2 106.5 x 2 2.9 8.3 Emer Float Skid 622.3 1759.0 106.5 x 2 106.5 x 2 2.9 8.3 LANDING GEAR LOADING AT MAXIMUM GROSS WEIGHT (5,250/2,381 KG) - based on one “G” static conditions at most structural cg limit HELIPAD LOADING (5,250 LB) - US UNITS GEAR TYPE LOADING POUNDS CONTACT AREA SQ.IN. CONTACT PRESSURE PSI FORWARD AFT FORWARD AFT FORWARD AFT Standard Skid 1405 3845 16.5 x 2 16.5 x 2 43 117 High Skid 1372 3878 16.5 x 2 16.5 x 2 42 118 Emer Float Skid 1372 3878 16.5 x 2 16.5 x 2 42 118 SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 7 BELL 407GXi Approximate Cargo Space Aft cabin 85 ft 3 2.4 m3 Left front 20 ft3 0.6 m3 Baggage compartment 16 ft 3 0.45 m3 Floor Loading Cabin 75 lb/ft2 366 kg/m2 Baggage 86 lb/ft2 420kg/m2 Max baggage weight 250 lb 113 kg CABIN DIMENSIONS BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 8 Garmin G1000H® NXi RAISING THE PROVEN PERFORMANCE AND RELIABILITY OF THE BELL 407 TO A HIGHER LEVEL The Garmin G1000H® NXi Integrated Avionics System in the Bell 407GXi has been designed to improve situational awareness and reduce pilot workload through easy to read displays of critical flight information, tuning of communication and navigation frequencies, and simple flight planning management. The Bell 407GXi’s standard configuration G1000H® NXi includes the Synthetic Vision System (SVS) and initial installation of the HTAWS and Navigation database [1]. The system has two SD card slots to facilitate data Input/Output tasks such as flight plan and database uploading or critical flight data downloads. The system takes advantage of the latest in display, computer processing, and digital data bus technology to provide a high degree of redundancy, reliability, and flexibility. The main components of the Garmin G1000H® NXi Integrated Avionics system includes: y Two 10.4” (26.4 cm) GDU 1050H high definition LCD displays (interchangeable PFD/MFD) y Two GIA 64H Integrated Avionic Units, including: – GPS / WAAS Receiver – VHF COM Transceiver – VHF NAV and Glideslope Receivers – Aural Alert Generation y GEA 71HB Engine and Airframe Unit (signal processing of engine parameters and major system sensors) y GSU 75 Air Data and Attitude Heading Reference System and GMU 44 Magnetometer y GMA 350Hc Audio System [2] y GTX 335R Extended Squitter (ES) Mode S Transponder Notes: [1] Database subscription updates are the responsibility of the helicopter owner/operator. [2] Integrated Marker Beacon Receiver capability is available with customizing of a Marker Beacon Antenna, and 3D Audio capability is available with customizing of stereo headsets. The Bell 407GXi Garmin G1000H NXi suite. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 9 BELL 407GXi INTEGRATED GARMIN G1000H ® NXi Suite Feature Two-Display System Twin 10.4” (26.4 cm) flat panel high definition LCDs, interchangeable for Primary Flight Display (PFD) or Multi Function display (MFD) Flight Instruments Integrated on PFD with stand-by airspeed, altimeter, compass Engine Instruments Integrated on PFD / MFD with Power Situation Indicator (PSI), Engine Indication System (EIS), fuel flow, automated power assurance check EICAS & Audio Alerts Engine Indicating and Crew Alerting System (EICAS) integrated on PFD / MFD. Audio alerts integrated into intercom system COM/NAV Dual COM / NAV / GPS, WAAS, Mode S Transponder with Extended Squitter (ES), ADS-B out, FMS, auto-tuning Situational Awareness Integrated on PFD / MFD, Traffic Information System (TIS), HTAWS, Synthetic Vision System, Moving Map, Fuel and NAV range, Tail Rotor Camera display on MFD, optional TAS, optional transponder with ADS-B “In” is available Intercom ICS with recorder / playback, cell phone and MP3 jack, Automatic Speech Recognition, Bluetooth capability Garmin G1000H® NXi Garmin G1000H® NXi DISPLAYS The Garmin G1000H® NXi presents critical flight information to the pilot at a glance for greater situational awareness, simplicity and safety. The pilot can easily and quickly select the information formats to display on the interchangeable Primary Flight Display (PFD) and Multi Function Display (MFD). The Power Situation Indicator (PSI), located in the lower left-hand corner of the PFD provides a “one stop shop” for power indications and limits. The displays accept both NTSC and PAL format composite video signals from external sources, including the Bell 407GXi’s standard configuration Tail Rotor Camera and optional imaging devices such as multi-sensor camera thermal imaging systems for operations. Primary Flight Display (PFD) Typical User Selected Formats The PFD displays all major flight parameters in an intuitive, easy to scan layout: Attitude, Airspeed, HSI, Altitude and VSI. Primary and inset screens can be user-selected to display a variety of additional functions, including “Pathways in the Sky”, Flight Path Vector, Synthetic Vision, HTAWS, and Traffic Information System (TIS) [1] . Notes: [1] The GTS 800 TAS (Traffic Advisory System) is available as an optional kit. PFD Main Screen Display PFD Map Overlay in HSI PFD Flight Planning Display PFD ‘Pathways in the Sky’ Display SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 11 BELL 407GXi MFD Range Ring Display. MFD Flight Planning Display. MFD Tail Rotor Camera / Map Display. MFD Power Assurance with HOGE performance in real time mode. Notes: [1] Subscription to XM Satellite Weather and/or Radio is the responsibility of the helicopter owner/operator. [2] Iridium ® is a registered trademark of Iridium Satellite LLC. [3] Subscription to Iridium® Voice/Data service is the responsibility of the helicopter owner/operator. Garmin G1000H® NXi Multi Function Display (MFD) Typical User Selected Formats User-selectable MFD display options in the standard configuration G1000H® NXi Suite include System Status, checklists, flight planning, maintenance pages, engine pages, Power Assurance Screen, NAV map, Traffic Information System (TIS), engine and transmission information, fuel status, and calculated range. Optional features include satellite weather through an XM satellite datalink [1] (North America) or Iridium® [2] Voice/Data transceiver [3] (worldwide), and the Garmin GTS 800 Traffic Advisory System. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 12 Garmin G1000H® NXi Power Situation Indicator (PSI) The PSI is a single indicator section of the PFD that provides the pilot quick information about power settings. The color-coded parameter display automatically highlights normal performance (green), near limits (yellow) or exceedence (red) (red). COMMUNICATIONS AND NAVIGATION Each of the standard configuration dual Garmin GIA 64H Integrated Avionics Units includes a GPS/ WAAS receiver, VHF COM Transceiver and VHF NAV and Glideslope receivers. It also maintains a prioritized queue of aural alerts for Aural Alert Generation. AUDIO SYSTEM [1] The GMA 350Hc Audio Control Panel incorporate Bluetooth technology for wireless access to music, phone and more. This adds to an impressive list of features including industry-first Telligence Voice Command technology, 3D audio processing and enhanced auto squelch capability and more. These features decrease heads-down time and increase overall situational awareness in the cockpit. The GMA 350Hc provides cockpit ICS, pilot and copilot volume control and dual stereo entertainment inputs. The COM interface supports up to three (3) transceivers and the NAV interface supports up to five (5) radios. The system can accommodate up to seven (7) mono/stereo headsets (two (2) for pilot/copilot and five (5) for passengers), and provides ICS audio isolation modes for the pilot, copilot and passenger headset positions. The GMA 350Hc features two (2) entertainment inputs (MUSIC 1 and MUSIC 2), with identical streaming content from the optional GDL 69H XM Radio Datalink [2]. A 3.5 mm front panel mini-jack on the GMA 350Hc can be used as an entertainment input or as a telephone input when the optional GSR 56H Iridium® Voice/Data Transceiver [3] is installed. EXTENDED SQUITTER (ES) MODE S TRANSPONDER The GTX 335R Extended Squitter (ES) Mode S Transponder functions are controlled by the PFD display, and support European Mode S mandates for Extended Squitter, Elementary Surveillance and Enhanced Surveillance. In addition, the GTX 335R ES provides Automatic Dependent Surveillance-Broadcast (ADS-B) “Out”capability. With ADS-B “Out” capability, position velocity and heading information are automatically transmitted to other aircraft and ground stations to improve situational awareness and flight safety. Notes: [1] Integrated Marker Beacon Receiver capability is available for the GMA 350H by installing a marker beacon antenna. [2] Subscription to XM Satellite Weather and/or Radio is the responsibility of the helicopter owner/operator. [3] Subscription to Iridium® Voice/Data service is the responsibility of the helicopter owner/operator. Power Situation Indicator. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 13 BELL 407GXi GARMIN SOFTWARE FEATURES The Weight and Balance Multi-Function Display (MFD) page provides information about the helicopter weight and center of gravity. It uses pilot data entry for the crew, passengers, baggage loads, helicopter empty weight and the fuel load. It can synchronize with fuel quantity indication instead of relying on manual entry. Longitudinal and lateral aircraft CG are automatically calculated and displayed graphically with a digital readout. The Longitudinal CG slider indicator includes a cyan bar to show CG migration due to fuel burn. The Hover Performance page presents the pilot with real-time or pre-flight planning power required to perform OGE or IGE hover operations when OAT and altitude are in the certified envelope. The page consists of a Hover Power Indicator (HPI) and the Hover Performance Display section. The HPI indicator displays power required to hover OGE or IGE at the current aircraft weight, OAT, pressure altitude, and wind condition. The PSI displays predicted power required to hover OGE or IGE at the pilot’s entered destination aircraft weight, OAT, pressure altitude, and wind condition. This improves hot/high operations by letting pilots know ahead of time if they can take-off at a hot/high landing site. In real time operation, the avionics system function displays the HPI indicator based on the largest hover power margin condition between the installed engine hover performances, all these being in terms of Q-HOV, MGT-HOV or NG-HOV. This indication aids pilots with respect to the appropriate engine setting. The automated tool, represented by the power performance check, helps further reduce pilot workload. In hover predictive mode, the parameters in the Hover Performance Display section can be manually adjusted and are displayed in cyan. The HPI is also displayed in cyan. The avionics system displays the MAX INTERNAL HOV WT and MAX EXTERNAL HOV WT, information which is suppressed in real time. This hover performance prediction function allows the internal/external hover weight predictions based on the Pilot adjustable parameters or additional inputs; e.g. anti-ice aircraft kits configuration, pressure altitude, OAT, wind speed, engine margin (i.e. this is a pilot input, which represents the average of the last ten power assurances checks), generator load, and hook weight. Weight and Balance CG Display Page. Weight and Balance Data Entry Page. Pre-flight planning hover performance check (HOV-Predictive Mode). Garmin G1000H® NXi BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 14 The impending exceedance alert tone provides an aural alert to the pilot before encountering an engine exceedance. The aural alert tone is generated when any of the engine parameters are operating in a time-limited range. This capability especially benefits Bell 407GXi missions where it is common practice for the pilot to operate the aircraft at high power settings while also looking outside the aircraft. Profile and Path views are selectable and displayed on the Navigation Map MFD page. When the Profile View is enabled, it is displayed in a window below the Navigation Map. Altitude is shown along a vertical scale, with an aircraft icon positioned at the current altitude. Distance is represented horizontally along the bottom of the Profile View, and increases from left (present position) to right. The Profile View is based on the current aircraft track (or heading if track is unavailable) and shows the highest known terrain or obstacles within a predetermined width from the present aircraft position to the end of the profile range. The Profile Path displays the horizontal and lateral boundaries of the Profile View. The path is shown as a white rectangle on the Navigation Map Page and is only available when Profile View is enabled. White range markers both edges of the Profile Path rectangle match the range markers along the distance scale inside the Profile View display window whenever the profile range is at least 4 nm. for Bell 407 aircraft. It features greater capabilities at a lower cost and is the only kit that is fully- integrated with the Garmin G1000H® NXi avionics suite to display autopilot modes, hold references, audio alerts and CAS messages. These kits provide enhanced lateral, longitudinal, and yaw stability in low- speed flight and a cyclic force trim release switch, a beep reference switch, pitch/roll hands-on stability augmentation, and pilot-initiated automatic recovery. OPTIONAL EQUIPMENT ENHANCEMENTS The following optional kits are available to further enhance the capabilities of the Bell 407GXi helicopter’s Integrated Avionics System. GDL 69AH XM Weather Radio Datalink A remote-mounted XM satellite radio receiver capable of receiving digital datalink weather and digital audio entertainment from an XM satellite. XM Weather and Radio operate in the S-band frequency range to provide continuous uplink capabilities at any altitude throughout North America. An individual 3rd party XM / WX subscription is required to receive XM / WX data signals. Subscriptions are available for either weather or digital audio entertainment services separately or for both services. Real-time hover performance check. Profile Path. Garmin G1000H® NXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 15 BELL 407GXi Garmin G1000H® NXi GDL 59H Datalink Management Unit Provides a flight parameter recorder function and a high speed data link between the aircraft systems and ground computers using 802.11 g (“Wi-Fi”) while the aircraft is on the ground, and a required interface to the optional GSR 56H Iridium® Voice/Data Transceiver. GSR 56H IRIDIUM® Voice/Data Transceiver Provides low speed data transmission via the Iridium® satellite network supporting both Iridium® RUDICS (Internet) or Iridium® Short Burst data formats, fully integrated satellite phone functionality which can be dialed through the MFD, SMS Text Messaging, and Worldwide Weather capability. Subscription to Iridium® Voice / Data service is the responsibility of the helicopter owner / operator. GTS 800 TAS (Traffic Advisory System) Provides expanded traffic alerts through both active and passive surveillance capabilities, and the ability to process 1090 MHz ADS-B extended squitter from other aircraft. When installed, the optional GTS 800 TAS System replaces the standard configuration TIS (Traffic Information System), using active interrogation of Mode S and Mode C transponders to provide Traffic Advisories to the pilot independent of the air traffic control system. GRA 55 Radar Altimeter (Including 5G Filter) Provides a smooth and consistent readout of your altitude Above Ground Level (AGL) utilizing the same tech- nology as the GRA 5500. The GRA 55 is designed to work in a multitude of environments, allowing you to go from rough terrain to tree canopies, to sand, to choppy water and know exactly how much altitude you have to maneuver. Includes a remote external filter to meet FAA/TCCA airworthiness directives, ensuring safety and compliance by mitigating 5G interference. GTX 345R Transponder The Garmin GTX 345R Transponder (ADS-B In & Out) Capability replaces the basic ship GTX 335R. BELL 407GXi Autopilot Kit The Bell 407GXi autopilot Stability and Control Augmentation System (SCAS) significantly reduces pilot workload by providing precise control during all modes of flight, regardless of wind conditions or the aircraft’s center of gravity. It also features a recovery mode which allows the aircraft to safely exit inadvertent IMC or unusual attitudes if a pilot loses visual reference due to limited visibility conditions. Upon initiating the autopilot “Go Around” mode using the collective or mode panel switch, the Bell 407GXi autopilot system will level the pitch and roll attitude of the aircraft. The pilot can then apply power using the collective for a wings- level climb at best climb rate airspeed (70 KIAS) to safely navigate through the appropriate emergency or initiate a go-around procedure. The Bell 407GXi Garmin G1000H NXi suite. AFCS mode select panel Go-around switch - Force trim release - AP disconnect - Beep trim BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 16 The 2-axis and 3-axis autopilot kits are a Bell 407GXi alternative to other third-party autopilots currently on the market. The modes and annunciations of the Bell 407GXi autopilot include: y Autopilot (AP) Modes – Attitude hold – Heading hold y Coupled AP Pitch Axis Modes – Altitude hold – Altitude preselect – Airspeed hold – Glideslope capture and track (with Radar Altimeter installed) Flight Stream 510 Wireless cockpit connectivity unlocks more capabilities from within the G1000 NXi suite. Available as an option, Flight Stream 510 enables Database Concierge, the wireless transfer of aviation databases from the Garmin Pilot™ app on a mobile device to the G1000 NXi system. Flight Stream 510 also supports two-way flight plan transfer, the sharing of traffic, weather, GPS information, back-up attitude information and more, between the G1000 NXi suite and compatible mobile devices running Garmin Pilot or ForeFlight mobile. • 1090 MHz ADS-B “Out” enables aircraft to operate at any altitude, in airspace around the globe • Combines Mode S Extended Squitter (ES) transponder and optional WAAS/GPS position source in a single unit • Provides access to dual-link ADS-B “In” traffic and subscription-free weather on compatible displays • Wirelessly stream weather, traffic, GPS position and backup attitude via Connext link to Garmin Pilot and ForeFlight Mobile apps as well as the aera 795/796 Garmin portables • Compatible with a variety of Garmin cockpit displays including G1000 and GTM 750/650 series which offer transponder code entry and control Search and Rescue (SAR) charts The Garmin G1000H® NXi software includes Search and Rescue (SAR) charts. The Search and Rescue feature has four basic search patterns (Parallel Track, Sector, Expanding Square and Circular) to provide air crews with step by step tracking procedures for search and rescue missions. Normal SAR patterns are accessible via one unlock card. Enhanced SAR charts, featuring circular SAR patterns, are accessible via a second unlock card. All patterns have adjustable parameters. The most effective pattern may be chosen based on available information about the search object, the weather and the terrain. Typical flight planning parameters, such as time, speed, distance and fuel remaining, are given throughout the search mission on the flight plan pages. y Coupled AP Roll Axis Modes – Heading select – FMS flight plan following – VOR capture and track (with Radar Altimeter installed) – Localizer capture and track y PFD Annunciations – Pitch/Roll mode indications – Beep/Hold references – Out-of-Detent indications – AFCS-related CAS messages Wireless Cockpit Connectivity with Flight Stream 510 Garmin G1000H® NXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 17 BELL 407GXi Enhancements included in standard Bell 407GXi PRECISE FLIGHT PULSELIGHT® The Precise Flight Pulselite® system is included as standard equipment on all new Bell 407GXi. When enabled, the Pulselite® system alternately pulses the landing and taxi lights to enhance the visibility of the aircraft to traffic and birds. It can also be linked to automatically respond to a Traffic Collision Avoidance System (TCAS) input. According to the manufacturer, the Pulselite® system has a direct impact on reducing the number of bird strikes. The system is also available as an aftermarket installation. HOT AND HIGH OPERATIONS Bell customers require more from their aircraft and the Bell 407GXi delivers. The upgraded Rolls-Royce M250-C47E/4 engine in the Bell 407GXi provides more power at hot & high conditions. This provides for significantly more external payload at attitude or a higher hover ceiling for the same gross weight. For example, at 6,000 ft, ISA +20°C the Bell 407GXi provides 325 lb more payload for external load operations. With the approval of BTI-407-FMS-12, Hot and High Operations, fleeted Bell 407s equipped with R250 engines with sufficient power margins, may also take advantage of the performance increase. No additional equipment is required for installation. As shown in the charts below, the capability gained with the Hot and High performance allows for significantly more payload at altitude. Additionally, operators flying at a given gross weight can now hover higher than before. 1814 1914 2014 2114 2214 2314 2414 2514 2614 2714 0 500 1000 1500 2000 2500 3000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 4000 4500 5000 5500 6000 Max GW (kg) Pressure Altitude (m) Pressure Altitude (ft) Max GW (lb) Min Spec High/Hot MGW Limits External Load Only External Load Only 1814 1914 2014 2114 2214 2314 2414 2514 2614 2714 0 500 1000 1500 2000 2500 3000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 4000 4500 5000 5500 6000 Max GW (kg) Pressure Altitude (m) Pressure Altitude (ft) Max GW (lb) Min Spec High/Hot MGW Limits Hover In Ground Effect (HIGE) Hover Out of Ground Effect (HOGE) BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 18 Additional Enhancement Options SINGLE PILOT INSTRUMENT FLIGHT RULES (IFR) STC KIT An excellent solution to navigate the skies and safely complete critical missions despite low cloud ceilings. With this single-engine IFR certified aircraft, owners/operators can now maximize their uptime and accept more flights knowing that they will be completed safely. For pilots on search and rescue or medical first responder teams, don’t let low visibility keep you from answering your calls. The Bell 407GXi Single Pilot IFR Kit received it’s STC certification from the FAA in August, 2019 and is applicable to all FAA registered 407GXi’s. When any pilot flies under IFR, he is required to be under the direction of ATC (Air Traffic Control). They direct you regarding the aircraft direction course, speed, altitude, etc. IFR is imperative in weather with visibility lesser than 2 miles. The Bell 407GXi is the most cost efficient IFR Platform in the market. FORESIGHT MX HEALTH AND USAGE MONITORING SYSTEM (HUMS) (AERONAUTICAL ACCESSORIES) The Foresight MX 407 Health and Usage Monitoring System (HUMS) utilizes next generation technology to provide enhanced visibility into your Bell 407GXI helicopter. This saves time, cost and offers improve safety and reliability at a low cost and is lightweight at only 8.8 lbs. The system provides flight data, mechanical diagnostics, monitors exceedances and offers maintenance predictability by monitoring engine performance and vibration of critical components so you get early warning of potential maintenance problems. In addition. the system also streamlines the Rotor Track and Balance (RTB) maintenance process. Through a required subscription, operators receive text message and email notifications regarding the status of their 407, and a single model or entire fleet can be monitored in one clean dashboard that is simple to use and provides a color-coded diagnosis of the 407’s condition. POLYCARBONATE WINDSHIELD A polycarbonate windshield offers enhanced bird strike resistance compared to the standard acrylic windshield and is available as a customizing option on all new Bell 407GXi aircraft as well as a replacement for fielded aircraft. AIRFRAME FUEL FILTER A fuel filter option is now available for the 407GXi 250-C47E/4 engine that removes the need for anti-icing fuel additives when conducting cold weather operations. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 19 BELL 407GXi Seating and Interiors CREW SEATING Two individual, ergonomically designed seats, with adjustable lumbar support, each equipped with seat belt, double strap shoulder harness and inertia reel, are located in the cockpit. The color and upholstery material for the seats and interior trim of the cockpit match that which is selected for the cabin. STANDARD SEATING AND INTERIOR TRIM The standard cabin seating consists of five, ergonomically designed seats with individual seat belts and single strap shoulder harness, arranged with three equal width, forward facing seats across the rear of the cabin and two individual, rearward facing seats aft of the cockpit. Seats are available in fabric or vinyl with black, gray, tan or blue color options and are paired with black seat belts. The standard interior trim consists of full plastic closeouts on all airframe areas, leather covered arm rests, and molded plastic outboard headliners. The floor is covered in color coordinated low loop blend carpet or optional Aermat vinyl. The standard seating and interior trim are included in the basic aircraft weight. CORPORATE SEATING AND INTERIOR TRIM The corporate cabin seating consists of five ‘overstuffed style’ seats with individual seat belts and single strap shoulder harnesses, arranged with two extra wide forward facing outboard seats and a middle seat for occasional use across the rear of the cabin (with a fold down arm rest between the outboard seats) and two individual rearward facing seats aft of the cockpit. The corporate seats are available in a variety of Volo leather color options with color coordinated seat belts. The corporate interior trim consists of full plastic closeouts on all airframe areas, along with color coordinated Volo leather headliner inserts and armrests. The flooring is 100% wool cut pile carpet. Selection of the corporate interior trim also specifies installation of soundproofing, which provides a reduced interior noise level. The corporate seating and interior trim (and corporate soundproofing) increase the basic aircraft empty weight 21 lb (9 kg). DESIGNER SERIES SEATING AND INTERIOR TRIM The Designer Series interior is Bell’s bespoke VIP offering, featuring black trim throughout the aircraft, complemented by black Kydex panels, including the headliner. Interior door jambs and seams are painted in matching black for a seamless, coordinated finish. This premium interior is available in five bespoke color schemes: Arctic Grey/Charcoal, Charcoal/Jet Black, Crimson/Jet Black, Sand/Jet Black, and Snow/Jet Black. The seats are upholstered in upgraded Forte leather with custom stitching, a Bell logo, and color coordinated restraints. The Designer Series package includes enhanced cockpit storage, leather wrapped center map storage, automatic door openers for crew, cabin, and baggage compartments, color coordinated crew assist handles, USB A/C connections, ICS jacks, and a corporate soundproofing kit. Optional chrome plated vents and cup holders round out this VIP interior. Standard Seating and Interior Trim. Approved by:_______________________________________ Date:_________________ Serial # Registration Customer PA # Tmp Pmt Date: Time: Model 407GXi TBD Color Coordinated Wool carpet Brushed Metal Light Gray Leather Volo 6011 Smoke Grey Leather Volo 946 Bell 407 Corporate Interior - Two extra wide seats across aft row with seatbelts for occasional center passenger - Pull down center armrest - Armrests covered with color coordinated leather - “over stuffed” seat styling - leather seat upholstry - plush wool carpet - color coordinated seat belts - NO 407 logo in door insert - Brushed metal plate in armwrests and door Corporate Seating and Interior Trim. Designer Series Seating and Interior Trim BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 20 Mission Profiles CORPORATE This high performance single-engine helicopter provides comfortable seating for seven occupants with an available Quiet CruiseTM kit for decreased cabin noise. The Bell 407GXi’s spacious 85 ft3 (2.4 m3) cabin accommodates five passengers. It’s all composite, four-blade rotor provides superior hover performance, speed and a smooth quiet ride. The dual digital FADEC (Full Authority Digital Engine Control) fuel management system of the Rolls-Royce 250-C47E/4 turbine engine enhances safety and reduced operating costs. The Bell 407GXi is supported by Bell’s globally acclaimed Customer Support and Services. MEDICAL Helicopter emergency medical services is demanding. The Bell 407GXi is the ideal helicopter for HEMS operations. It strikes the perfect balance between performance, reliability and mission flexibility. A smooth ride is essential to the mission and the Bell 407GXi delivers due to the all-composite, four-bladed rotor system that also provides excellent hover performance and speed. The Bell 407GXi is ideal for extreme environments: high altitudes, arctic conditions or even the hottest locals. Quick and easy patient loading and unloading is provided by a standard bi-fold door with a 61-inch (155 cm) opening. Safety features include a rupture resistant fuel system, engine exceedence monitoring and a collective-mounted throttle that keeps power at the pilot’s fingertips. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 21 BELL 407GXi Mission Profiles GENERAL/UTILITY A high performance helicopter known for its reliability, the Bell 407GXi offers single-engine operators proven technology combined with Bell’s globally acclaimed customer support. The helicopter’s spacious 85 ft3 (2.4 m3) cabin accommodating five passengers in club seating and high useful load makes the Bell 407GXi a workhorse for utility operators. Superb overall performance is delivered by an 862 SHP FADEC- controlled Rolls-Royce 250-C47E/4 turbine engine. The all composite, four-blade rotor provides superior hover performance, speed and a smooth, quiet ride. Safety features include a rupture resistant fuel system, engine exceedence monitoring and a collective-mounted throttle that keeps power at the pilot’s fingertips. The Bell 407GXi delivers value to utility operators every day. PUBLIC SAFETY You protect, we serve. The Bell 407GXi is a high-tech, single-engine helicopter with an airframe that has a track record of performance and reliability, not to mention tangible cost benefits for your organization. Its all-composite, four-blade rotor provides superior hover performance, speed and a smooth quiet ride. Safety features include a rupture resistant fuel system, engine exceedence monitoring and a collective-mounted throttle that keeps power at the pilot’s fingertips. The Bell 407GXi’s spacious 85 ft3 (2.4 m3) cabin is configurable for many different missions and has an abundant capacity for law enforcement equipment (multi- sensor camera, searchlight, etc) with nearly 4-hours of loitering capabilities for surveillance missions. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 22 External Paint Schemes For more color options, please visit BellFlight.com or speak with a Sales Representative. Notes: 1. Color renderings (original) must be provided for any deviation to the standard schemes (all models). 2. Custom paint schemes to customer specification are available, and a price quote will be provided on request. Please provide as much detail as possible when describing special instructions and custom paint schemes. 3. The danger arrow is always applied on the tail boom between the horizontal stabilizer and the tail rotor, not withstanding any other illustrations. 4. Unless clearly specified (location, dimension, color), registration markings will be applied per FAA regulations (all models). 6. Placement of Bell model logos is effected by individual paint schemes, and will be applied at the discretion of Bell unless otherwise specified by the customer. SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 23 BELL 407GXi AIRFRAME Cabin; bonded aluminum honeycomb, and semimonocoque structure with composite side panels and aft fuselage skins Doors (five), one hinged double door and copilot door on left side, pilot and passengers on right side, all doors are composite material Landing gear, tubular skid type with replaceable skid shoes Locks for cabin doors and luggage compartment Luggage compartment with composite door Provisions for mooring, jacking and single point lifting Tail boom, monocoque structure with vertical fin and fixed stabilizer Tail skid (tail rotor guard) Windows (except windshield), gray tinted plexiglass Three color exterior paint schemes INTEGRATED AVIONICS SYSTEM with GARMIN G1000H® NXi SUITE Two 10.4” high definition display units, providing Primary Flight Display (PFD) and Multi-Function Display (MFD) functionalities Two Integrated Avionics Units, each consisting of a 16-watt VHF communication transceiver with 8.33 kHz spacing, VHF navigation, WAAS GPS navigation, and glideslope receiver One audio control panel with clearance recording and Automatic Speech Recognition (ASR) capability One digital Air Data Computer (ADC) with Outside Air Temperature (OAT) probe One Air Data and Attitude Heading Reference System (ADAHRS) and magnetometer One mode S transponder with extended squitter, including Traffic Information Service (TIS), with ADS-B “Out” capability One engine and airframe interface unit One engine signal conditioner Tail rotor video camera system with capability to view approximately 25 feet in complete darkness Synthetic Vision System (SVS), and Helicopter Terrain Awareness and Warning System (HTAWS) features INTEGRATED AVIONICS SYSTEM with GARMIN G1000H® NXi SUITE (continued) Integrated Engine Indication and Crew Alerting System (EICAS), including Power Situation Indicator (PSI) that provides an integrated display presentation of all critical engine parameters into a single indicator to present the power “margin” remaining Fuel flow indication with range ring display capability Flight Data Recording of 60 standard aircraft and engine parameters and 40 customer selectable parameters ELECTRICAL 28 volt DC system Battery, 17 amp-hour nickel cadmium External power and grounding receptacle Starter-generator (180 ampere) Solid state voltage regulator 28 volt outlet in cockpit Heated pitot tube and Static ports LED lighting: Anticollision strobe Cockpit / map Instrument Landing Position INTERIOR 7-place interior with soundproofing, carpeting, and data case. Color options available for upholstery and carpet 7-place shoulder harnesses, dual straps in cockpit, single strap in cabin Fire extinguisher, cabin First aid kit Parcel shelf (behind aft seat) Ram air ventilation system Storage area behind pilot and copilot seats Two David Clark headsets Basic Bell 407GXi Configuration BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 24 LOOSE EQUIPMENT (not included in empty weight) Covers, engine inlet and exhaust stack Cover pitot tube Flight bag Ground handling wheels with lift tube Operating manuals: Rotorcraft flight manual Aircraft log book Engine log book Aircraft maintenance manuals are available on ePubs located here: mybell.com Tie-down assemblies, main rotor and tail rotor POWERPLANT Rolls-Royce Model 250-C47E/4 turboshaft engine with dual digital FADEC. Fuel pump, engine driven Fuel pumps (4 canister type) with 2 boost pumps submerged in main tank, and 2 transfer pumps in the forward fuel tanks Crashworthy Fuel System Oil system with sight glass Compressor wash provisions Engine mounted 3-micron oil filter ROTORS AND CONTROLS Main rotor, soft in plane flex beam hub with four fiberglass blades Tail rotor; two fiberglass blades, semirigid Hydraulic boost system for Main and Tail Rotor (separate pump and reservoir) Mechanical flight control linkages throughout Airspeed Activated Pedal Stop (AAPS) with built in test function, electrical override release switch, and manual override release TRANSMISSION DRIVE SYSTEM Soft mounted pylon isolation system Freewheeling unit (between engine and main transmission) Kaflex input drive shaft Gearbox, tail rotor, 90° reduction Main transmission Oil cooler Oil filter with replaceable type cartridge Oil pump, constant pressure Basic Bell 407GXi Configuration BASIC BELL 407GXI CONFIGURATION EMPTY WEIGHT lb kg Additional kits for basic configuration 2,700 1,225 ADDITIONAL KITS Jettisonable doors (crew only) Auxiliary fuel tank provisions Dual controls Wire Strike Protection System High skid gear (including AA Flitestep®) Rotor brake 28 Amp-hour Sealed Lead Acid (SLA) battery (replaces 17 amp battery) High visibility main rotor blades Sliding windows Rubber Mounted Chin Bubbles Pulse Light STANDARD CONFIGURATION EMPTY WEIGHT lb kg Additional kits for standard configuration 2,802 1,271 Standard Configuration SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 25 BELL 407GXi OPTIONAL ACCESSORIES Kit Description Weight Notes lb kg AIRFRAME 5,250 lb Max. Gross Weight 0 0 Aerodynamic Hub Cover and Mounts (without Hub Frahm) 7.5 3.4 Air Conditioner with Dual Forward Evaporators (Air Comm) 105.6 47.9 1, STC Auxiliary Fuel Tank Equipment (19 USG / 72 L) 30.4 13.8 Baggage Floor Protector (AA) 4.5 2 STC Bleed Air Heater with Windshield and Chin Bubble Defrost (Air Comm) 26.0 11.8 2, STC Cargo Mirror Kit (AA) 2.0 0.9 STC Cockpit/Cabin Floor Protector Kit (AA) 8.5 3.9 STC Door Openers - Automatic - Baggage Door (AA) 0.9 0.4 STC Door Openers - Automatic - Cabin Doors (AA) 1.2 0.5 STC Door Openers - Automatic - Crew Doors (AA) 2.8 1.3 STC Sliding Passenger Door Kit - LH (AA) 10.5 4.8 3, STC Sliding Passenger Door Kit - RH (AA) 10.5 4.8 3, STC Emergency Floats Landing Gear Only (including Floatstep™) 84.5 38.3 4, 5, 6 Emergency Floats Reservoir 68.7 31.2 7 Flotation Equipment with Landing Gear (including Floatstep™) 173.2 78.6 4, 5, 6, 7 Foreign Certification - Russia (C.I.S) or China or Japan or Arabic or Mexico or Brazil or Argentina 0.1 0 Hub Frahm (includes Hub Cover) 52.2 23.7 Locking Fuel Cap (AA) 0.1 0 STC Low Skid Gear -32.1 -14.5 Rappelling Fixture Kit LH & RH (AA) 7.0 3.2 STC Rescue Hoist - 300 lb Capacity (Breeze Eastern/AA) 58.4 26.5 8, STC Skid Gear Fairings - Low Skid Only 11.7 5.3 WINDOWS Polycarbonate Windshields (AA) 20.4 9.3 STC AVIONICS Aft Cabin ICS - 5 Place (includes David Clark Headsets) 8.4 3.8 Cargo Hook release on Co-pilot AFCS Controls 0 0 15 Co-pilot AFCS Controls - 2 Axis 0.7 0.3 16 Co-pilot AFCS Controls - 3 Axis 0.7 0.3 16 ICS – 7 Place - Bose LEMO jacks (No Headsets included) 3.0 1.4 ICS – Cabin Call -w- LED Light 0.2 0.1 Artex C406-NHM ELT with PGM Adaptor 6.2 2.8 Autopilot - 2-Axis AFCS 27.6 12.5 Bell 407GXi Optional Accessories Refer to notes for kit compatibility. Additional kits and STC items may be available for factory installation. Please consult sales or contract personnel regarding special needs prior to selection of final configuration. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 26 OPTIONAL ACCESSORIES Kit Description Weight Notes lb kg AVIONICS (CONTINUED) Autopilot - Addition of 3rd Axis 9.0 4.1 14 Garmin GDL 69AH XM Weather with Audio 4.4 2 Garmin GTS 800 TAS 20.7 9.4 9 Garmin Flight Stream 510 0 0 Garmin Transponder GTX 345R 0 0 Marker Beacon (Garmin GMA 350H Audio Panel) 0.6 0.3 13 Mid-Continent Standby Attitude Module (SAM) (AA) 1.8 0.8 STC Search Patterns (displayed on G1000H NXI) 0 0 Radar Altimeter - GRA 55 with 5G Filter 9.9 4.5 9 EQUIPMENT Cargo Hook Equipment 8.9 4 17 Cargo Hook Provisions 5.3 2.4 Cargo Restraint Internal Provisions 1.9 0.9 Cockpit Storage Kit 1.4 0.6 Litter Equipment (One) -13.3 -6.0 10 Litter Provisions 5.7 2.6 Litter Ski Provisions 1.5 0.7 10 Main Rotor Blade Expandable Bolts (2) 1.5 0.7 4 Main Rotor Blade Folding Kit with 2 Expandable Bolts (Paravion) 0.5 0.2 11, STC Non-Halon Cockpit Fire Extinguisher 3.5 1.6 Snow Baffles 5.2 2.4 INTERIOR Armrests - Corporate 0.3 0.1 4, 12 Headliner - Standard with AC Ducting 4.7 2.1 4 Interior Trim - Corporate 7.3 3.3 4, 12 Designer Series Interior Trim (Black): Interior Black Panels (including Headliner), Paint Exposed Interior Airframe 37038 Camo Black & Black Instrument Panel 7.3 3.3 12 Passenger and Crew Seats - Corporate 0.9 0.4 4 Soundproofing - Corporate 8.2 3.7 4, 12 Spacemaker and Cover (AA) 6 2.7 STC 4-point Restraint system (Crew & Passengers) 8.7 3.9 POWERPLANT Airframe Fuel Filter 6.2 2.8 Engine Fire Detector 2.0 0.9 Increased Starter Generator 1.0 0.5 Inducer Vent Filter (AA) 2.8 1.3 STC Inlet Barrier Filter with Access Door (AA) 12.2 5.5 STC Particle Separator with Engine Bleed Air Network 16.9 7.7 2, 4 Quiet Cruise 0.2 0.1 Bell 407GXi Optional Accessories SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 27 BELL 407GXi OPTIONAL ACCESSORIES Kit Description Weight Notes lb kg OTHER No Ground Handling Wheels 0 0 4 Paint - No Exterior Paint -16.7 -7.6 Paint - White Paint Only 0 0 GPMS Foresight MX HUMS 8.8 4 STC Single Pilot IFR (FAA STC – Other counties validation pending) 56.3 25.5 13, STC Lightweight FDR Hensoldt LCR-100 (Bell Prague) TBD TBD STC EXPLANATORY NOTES All equipment kits require Provision Kits prior to installation. Notes: For commonality, notes shown below are identical in Product Specification and Price List. 1. Requires Headliner - Standard with AC Ducting. 2. Particle separator and Bleed Air Heaters both include Bleed Air Network. If both kits are installed subtract 3.8 lb (1.7 kg). 3. Sliding Passenger door(s) require sliding door armrest(s) which subtracts 1.9 lb (0.9 kg) per door. 4. Price and/or Weight includes credit for basic ship hardware removed. 5. Kit includes Floatstep™ (STC # 407-303-003) (29 lb [13 kg]). 6. The High Skid Gear (including AA Flitestep®) included in the Standard Configuration Empty Weight, is not required when a Float Landing Gear is installed, therefore remove 32.1 lb (14.6 kg) from Standard Configuration Empty Weight. 7. A Complete Emergency Flotation System requires Flotation Equipment with Landing Gear (including Floatstep™) and Emergency Float Reservoir. 8. Weight assumes the L/H Flitestep® is removed (14.5 lb [6.6 kg]) 9. Avionic Shelf Kit must be installed prior to or concurrently with the installation of this kit. 10. Requires installation of Litter provisions. Delta weight of this Litter Equipment shown includes removing the Copilot’s Seat, L/H Aft-facing, L/H Forward-facing, and Center Forward-facing Passenger Seats. 11. Weight is for provisions only. 12. Corporate or Designer Series interiors require corporate soundproofing and corporate armrests. 13. Single Pilot IFR Kit (STC) requires the Autopilot - 3-Axis AFCS kit and 28 Amp-hour Sealed Lead Acid (SLA) Battery installed. If operating under PART 135 requires a Marker Beacon installed. 14. Autopilot - 3-Axis AFCS requires the Mid-Continent MD-302 Standby Attitude Module (AA), Radar Altimeter - GRA 55, Autopilot - 2-Axis AFCS. 15. Either Co-pilot AFCS Controls kit (2 or 3 axis) and the Cargo Hook provisions must be installed prior to or concurrently with Cargo Hook release on Co-pilot AFCS Controls kit. 16. 2 or 3 Axis Autopilot must be installed prior to or concurrently with either Co-pilot AFCS Controls kits (2 or 3 axis). 17. Requires provision kit installed prior to or concurrently with equipment. STC KITS Select Supplemental Type Certificated Optional Equipment Kits are available for installation at the Bell Textron Inc. factory. Please contact your Bell sales representative for availability and pricing information. Bell 407GXi Optional Accessories BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 28 Helicopter Performance Charts IGE and OGE hover, and service ceiling performance chart data based on the following: y Rolls-Royce 250-C47E/4 engine y Basic inlet installed y FMS-12 engine data SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 29 BELL 407GXi Note: Takeoff and Landing is approved up to 20,000 feet (6,096 meters) density altitude. Demonstrations were made up to 25,000 feet (7620 meters) density altitude. 28 30 32 34 36 38 40 42 44 46 48 50 52 54 56 58 60 GROSS WEIGHT - 100 LB 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 PRESSURE ALTITUDE - 1000 FT M407 IGE HOVER CEILING TAKEOFF POWER, BASIC INLET INSTALLED HEATER & ANTI-ICE OFF, NO WIND 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 GROSS WEIGHT - 100 KG 0 5 10 15 20 25 30 35 40 45 50 55 60 PRESSURE ALTITUDE - 100 METERS Image filename: M407-VIP_HIGE_CEILING_CHART.GRF Date: 13 May 2014 SKID HEIGHT 4 FT (1.2 M) 0°C 10°C 20°C 40°C ISA ISA+10°C ISA+20°C ISA+30°C MAX INT GW 5000 LBS MAX EXT GW 6000 LBS MAXIMUM OAT 50°C 30°C -10°C -20°C -40°C & -30°C Helicopter Performance Charts IGE HOVER CEILING Conditions: y Rolls-Royce 250-C47E/4 engine at takeoff power y Basic inlet installed BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 30 Note: Takeoff and Landing is approved up to 20,000 feet (6,096 meters) density altitude. Demonstrations were made up to 25,000 feet (7620 meters) density altitude. Helicopter Performance Charts OGE HOVER CEILING Conditions: y Rolls-Royce 250-C47E/4 engine at takeoff power y Basic inlet installed 28 30 32 34 36 38 40 42 44 46 48 50 52 54 56 58 60 GROSS WEIGHT - 100 LB 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 PRESSURE ALTITUDE - 1000 FT M407 OGE HOVER CEILING TAKEOFF POWER, BASIC INLET INSTALLED HEATER & ANTI-ICE OFF, NO WIND 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 GROSS WEIGHT - 100 KG 0 5 10 15 20 25 30 35 40 45 50 55 60 PRESSURE ALTITUDE - 100 METERS Image filename: M407-VIP_HOGE_CEILING_CHART.GRF Date: 13 May 2014 0°C 10°C 20°C 40°C ISA ISA+10°C ISA+20°C ISA+30°C MAX INT GW 5000 LBS MAX EXT GW 6000 LBS MAXIMUM OAT 50°C 30°C -10°C -30°C -40°C -20°C SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 31 BELL 407GXi Note: Takeoff and Landing is approved up to 20,000 feet (6,096 meters) density altitude. Demonstrations were made up to 25,000 feet (7620 meters) density altitude. Helicopter Performance Charts SERVICE CEILING Conditions: y Rolls-Royce 250-C47E/4 engine at maximum continuous power y Basic inlet installed 28 30 32 34 36 38 40 42 44 46 48 50 52 54 56 58 60 GROSS WEIGHT - 100 LB 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 PRESSURE ALTITUDE - 1000 FT M407 SERVICE CEILING MAX CONTINUOUS POWER, BASIC INLET INSTALLED HEATER & ANTI-ICE OFF, NO WIND 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 GROSS WEIGHT - 100 KG 0 5 10 15 20 25 30 35 40 45 50 55 60 PRESSURE ALTITUDE - 100 METERS Image filename: M407-VIP_MCP_SVC_CEILING_CHART.GRF Date: 14 May 2014 -30°C -10°C 0°C 10°C 20°C ISA+20°C ISA+30°C ISA+10°C MAX EXT GW 6000 LBS MAX INT GW 5000 LBS MAXIMUM OAT 30°C -20°C -40°C ISA BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 32 Helicopter Performance Charts TAKE-OFF AND LANDING LIMITATION Conditions: y Optional 5,250 lb / 2,381 kg Internal Gross Weight Kit y Rolls-Royce 250-C47E/4 engine at Maximum Continuous Power y Basic inlet installed 36 38 40 42 44 46 48 50 52 54 56 GROSS WEIGHT - LBS x 100 0 2 4 6 8 10 12 14 16 18 PRESSURE ALTITUDE - FEET x 1000 0 4 8 12 16 20 24 28 32 36 40 44 48 52 PRESSURE ALTITUDE - METERS x 100 17 18 19 20 21 22 23 24 25 GROSS WEIGHT - KG x 100 Image filename: M407 5250 WAT CHART (TOP).WMF Date: 02 November 2000 M407 WAT LIMITS FOR GW = 5250 LBS TAKEOFF POWER, BASIC INLET INSTALLED HEATER & ANTI-ICE OFF, NO WIND MAX INT GW = 5250 LBS MAXIMUM OAT OAT - DEG C 11,000 FT H D ISA ISA+30C ISA+10C -40 -30 -20 0 -10 10 20 30 ISA+20C 40 SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 33 BELL 407GXi Fuel Flow vs. Airspeed Charts Fuel Flow vs. Airspeed chart data based on the following conditions: y ISA & ISA+20°C y Rolls-Royce 250-C47E/4 engine y Basic inlet installed y Low skid gear without fairings with FMS-12 engine data Notes: For particle separator installed: Increase fuel flow 2 lb/hr (1 kg/hr) For cross tube fairings: Increase airspeed 3 knots (5 km/hr) Recommended cruise speed is the Long Range Cruise (LRC) Speed. BELL 407GXi SPECIFICATIONS © 2026 Bell Textron Inc. Specifications subject to change without notice. FEBRUARY 2026 34 Fuel Flow vs. Airspeed PRESSURE ALTITUDE = SEA LEVEL, OAT = 15°C (ISA) FUEL FLOW VS AIRSPEED PRESSURE ALTITUDE = SEA LEVEL OAT = 15°C CLEAN CONFIGURATION ENGINE RPM 100% GENERATOR 180 AMPS ZERO WIND HEATER OFF ANTI-ICE OFF BASIC INLET 50 60 70 80 90 100 110 120 130 140 150 TRUE AIRSPEED - KNOTS 50 60 70 80 90 100 110 120 130 140 INDICATED AIRSPEED - KNOTS 160 180 200 220 240 260 280 300 320 340 360 380 400 FUEL FLOW - LB/HR 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 TORQUE - % 100 120 140 160 180 200 220 240 260 TRUE AIRSPEED - KM/HR 80 90 100 110 120 130 140 150 160 170 180 FUEL FLOW - KG/HR VNE LRC MCP TORQUE LIMIT MAX ENDURANCE GW x 100 LB 52.5 50 46 42 38 30 34