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October 12, 2018 CHP RFI 1520-4572_RFI Attachment 1

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Department of the California Highway Patrol

Helicopter Specifications Specification Number: 1520-4572_RFI

October 12, 2018

Section 1 - Scope Section 2 - General Requirements Section 3 - Operational Requirements Section 4 - Emergency Medical Services (EMS) Requirements Section 5 - Avionics Equipment Requirements Section 6 - Specialized Equipment Requirements Section 7 - Law Enforcement Radio Requirements Section 8 - Satellite Phone/Tracking Requirements Section 9 - Communications Equipment Requirements Section 10 - Electrical Requirements Section 11 - Options


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1 SCOPE: This specification identifies the minimum performance, equipment,

installation, and completion requirements for the purchase of a turbine engine helicopter for the Department of the California Highway Patrol (CHP). Unless otherwise indicated, references to the helicopter include the airframe, avionics, and specialized equipment described herein. The helicopter shall be a current production model, with not more than 25 flight hours since new for airframe or engine. The helicopter shall be certified under Code of Federal Regulations (CFR) 14, Part 23. The helicopter may not have sustained any damage as the result of accident and/or incident prior to acceptance by the CHP. This specification includes avionics and specialized equipment to be installed. This specification is based on the current configuration of AS350B3 helicopters but with updated requirements for the equipment.

2 GENERAL REQUIREMENTS:

2.1. The helicopter shall be certified by the Federal Aviation Administration (FAA) as a Normal or Utility Category Helicopter.

2.2. The helicopter must have a Type Certificate (TC) issued by the FAA at the time of the vendor’s bid response.

2.3. The helicopter must have a standard airworthiness certificate issued by the FAA at the time the helicopter is accepted by the CHP after installation of all equipment as described herein.

2.4. The helicopter must be certified for day and night visual flight rules.

2.5. The helicopter must be FAA certified and equipped for right seat piloting (single pilot operations and solo flight).

2.6. All installed equipment and accessories shall be certified by the FAA under the aircraft TC, Supplemental Type Certificate (STC), or by FAA field approval.

2.7. The helicopter must be FAA certified and equipped for flight in falling and blowing snow, unless there is a restriction on CHP requested equipment.

2.8. All installed equipment and any aircraft modifications shall be done in accordance with the guidelines published in FAA Advisory Circular 43.13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations, dated March 3, 2008.

2.9. The helicopter shall be equipped with dual flight controls.

2.9.1. If it is necessary to reconfigure the aircraft to accommodate a litter patient for medevac transport, the cyclic, collective and tail rotor


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controls in the copilot’s (left) position shall be capable of being quickly removed by a pilot or qualified crewmember without tools within three (3) minutes.

2.9.2. If it is necessary to reconfigure the aircraft to accommodate a litter patient for medevac transport, it shall be reconfigurable by a pilot or qualified crewmember within 5 minutes total.

2.9.3. In addition to the standard tail rotor control pedals in the pilot’s (right) position, one extended length right pedal shall be provided if available as an option.

2.10. The helicopter shall be FAA type certificated from the factory or issued an STC/337 to accommodate up to a 15.5 inch diameter, externally mounted, multi-sensor imaging system weighing up to 100 pounds (lbs.).

2.11. The helicopter shall have an interior design capable of seating a minimum of six (6) occupants and afford the flight crew unrestricted visibility and access into the passenger compartment. When seated in the primary pilot’s position, looking outside the helicopter, the pilot shall have a field of view, relative to the nose of the aircraft, approximately 135º to the left and right of the aircraft.

2.12. The helicopter must have a flat, unobstructed cabin floor to allow for ease of movement of hoist operator and rescue personnel during rescue/hoist operations.

2.13. ALL installed equipment shall be Night Vision Goggle (NVG) compatible from the manufacturer. If NVG equipment is unavailable from the manufacturer, lighting must be installed in accordance with (IAW) Aero Dynamix STC #SR09456RC. Instrument panel mounted equipment shall be rheostat controlled to attain balanced night lighting. If a combination of 28V and 5V lighting is used, two separate rheostats shall be used. Film overlays will not be accepted unless agreed upon at the Pre-Work Conference.

2.14. A service hour (Hobbs) meter shall be installed in the instrument panel in series with the transmission’s oil pressure sensor and a collective lever switch to indicate usage only when the engine is running and the collective lever is not fully down.

2.15. The aircraft shall have an airframe fuel filter, Michigan Dynamics or similar.

2.16. Minimum vertical clearance as measured from a flat, level, surface to the lowest point of the helicopter fuselage, antenna, or required equipment shall be at least 9 inches.

2.17. Any equipment, capabilities, or provisions provided on a basic equipped aircraft and listed as standard equipment for the make and model offered by the contractor shall be incorporated on the aircraft offered for purchase


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without regard to whether or not the equipment, provision, or capability is specified herein.

2.18. The helicopter shall be custom, 3 color, with top grade, EPA approved paint. The exact color(s), paint scheme and lettering dimensions will be reviewed and agreed upon at the Pre-Work Conference. Picture of current configuration available upon request.

2.19. The cabin interior shall be compatible with the exterior paint scheme. Seat material and color scheme to be reviewed and agreed upon at the Pre-Work Conference. 2.19.1. Seats shall be of the cushion type (not webbed). 2.19.2. Two (2) front seats shall be of a crashworthy design with a five (5)

point restraint system. Fischer+Entwicklungen Crew Seat 230/260 H110, or similar, is to be mounted in the pilot station. Fischer+Entwicklungen Crew Seat 230/260 H110, or similar, with a Fischer+Entwicklungen swivel base is to be installed on the copilot seat. If needed for medevac operations (to accommodate the litter), the left front seat must be capable of being relocated to a position adjacent to the littered patient’s torso. Final solution for relocation of the seat shall be discussed at the Pre-Work Conference.

2.19.3. Rear seating shall consist of the following three configurations:

2.19.3.1. Passenger Transport: Seating for a minimum of four passengers with cushion type (not webbed) seats capable of being removed by the crew with simple hand tools in less than 15 minutes.

2.19.3.2. Law Enforcement: Minimum of one rear seat, location and type shall be determined at the Pre-Work Conference.

2.19.3.3. Emergency Medical Services (EMS): A minimum of two rear seats for medical attendants and all medical equipment specified in Section 4.

3 OPERATIONAL REQUIREMENTS:

3.1. Performance must be supported by FAA approved manufacturer performance charts for the make/model aircraft bid. For the purpose of defining the following specifications, fuel weight shall be predicated upon the consumption rate published in the manufacturer’s direct operating cost computations, regardless of altitude. Aircraft operating weight shall be the sum of the helicopter’s basic weight, required Jet-A fuel weight, and specified equipment/personnel weight(s). Upon request from the State, the bidder may be required to submit computations and supporting materials. The bidder


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shall provide the requested information within 5 working days of the request by the State. The bidder may be required to demonstrate the operational requirements listed in this specification through a flight demonstration.

3.2. The helicopter must possess on-board electronic performance computer (Airbus VEMD or equivalent ) which shows real-time fuel flow, endurance, HOGE/HIGE capabilities, and all up weight (AUW).

3.3. The helicopter must be able to perform a downwind hover with no time limit, in winds up to 30 knots, both IGE and OGE.

3.4. The helicopter, with all avionics and special equipment installed (excluding FLIR ball and Night Sun), shall be within center of gravity limitations in the following conditions with the specified fuel and payload (fuel calculations are at 6.8 pounds per gallon):

3.4.1. Condition 1: Fuel endurance (includes 20 minute reserve) at 110 knots IAS on a standard day (ISA) at sea level shall be a minimum of 2 hours, 30 minutes (2+30), aircraft at maximum gross weight internal load. No auxiliary fuel tanks shall be installed to accommodate this requirement.

3.4.2. Condition 2: The helicopter must be capable of HOGE with no wind at 3,000 feet pressure altitude (PA), 44°C, with 2 hour, 20 minutes (2+20) fuel, and equipped as specified in this specification at maximum gross weight internal load.

3.4.3. Condition 3: The helicopter must be capable of HOGE with no wind at 10,000 feet pressure altitude (PA), 25ºC, with 1 hour, 30 minutes (1+30) fuel, with hoist installed, all aircrew removable equipment removed, and with 600 pounds of payload onboard. (Note: In this condition the aircraft baggage areas are emptied of all gear, the FLIR ball is removed, the Night Sun search light is removed, the aft seats are removed, and all medical equipment is removed).

3.4.4. Condition 4: The helicopter must be capable of HIGE with no wind at 14,000 feet PA, 3ºC, with 1 hour, 20 minutes (1+20) fuel, and equipped as in Condition 3 above.

3.5. Medical Operational Requirements:

3.5.1. The flight officer/paramedic must be able to clearly observe and have access to the patient’s head, upper torso and upper extremities while seat belted in the attendant seating position.

3.5.2. While transporting a patient, the attendants must have access to provide two-person cardiopulmonary resuscitation (CPR) to an average adult patient (6 feet, 200 lbs).


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4 EMS EQUIPMENT LIST: The following equipment is based on the CHP’s current fleet of AS350B3 helicopters; if the winning bid includes a type of helicopter other than the AS350B3, then the EMS equipment list will be adjusted during the Pre-Work conference. Alternatives to this equipment may be considered based on efficiency of design for specified operations and weight savings over current equipment.

4.1 Collapsible single patient litter with a minimum two tie down brackets (Ferno Part Model #12-2A or equivalent). Dart Aerospace Full Emergency Litter Kit, P/N D350-616-011 (this option shall be discussed at the Pre-Work Conference).

4.2 One double receptacle that converts 28 Vdc to 12 Vdc to also include a cigarette lighter style receptacle.

4.3 LifePort Inc. Medical Wall System (STC SR01193LA) to include (to be discussed at the Pre-Work conference):

4.3.1 One Wall Rack Assembly Part #100-5352.

4.3.2 One Wall Rack Installation Part #375-3550-KIT.

4.3.3 One (1) Cargo Pallet Part #ST2-267-01.

4.4 One Cardiac Monitor Mount.

4.5 Two Intravenous (IV) hooks shall be installed overhead on the left side above the litter kit.

4.6 Medical oxygen system. This system shall have removable oxygen tank(s) which can be quickly removed by aircrew for field use and/or servicing. The intent is to have two (2) aluminum oxygen cylinders mounted in the aft baggage compartment plumbed to the cabin.

5 AVIONICS EQUIPMENT REQUIREMENTS: The following avionics equipment or suitable equivalent shall be provided by the vendor and installed in/on the helicopter:

5.1 Flight and Engine Instruments:

5.1.1 One (1) Garmin G500H, with OEM NVG, Integrated Flight Display System with Synthetic Vision Technology and Jeppesen Chart View. The Garmin G500H, (Standard equipment), installed on the aircraft shall be equipped with an auxiliary analog input and appropriate video converter to display video from the hoist camera sensor and map data from the Churchill ARS-500C Mapping System.


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5.1.2 One (1) L-3 Avionics TRILOGY ESI-2000, entirely self-contained, battery backup, solid-state instrument providing attitude, altitude, slip and airspeed information.

5.1.3 One (1) 2 inch backup NR gauge.

5.1.4 One (1) Garmin GRA 5500 Radar Altimeter and appropriate antenna.

5.1.5 One (1) independent radar altimeter display (this is a Garmin product with a large readout to supplement the small readout in the Garmin G500H).

5.1.6 One digital clock with timer with backup battery.

5.2 Navigational/Communications Systems:

5.2.1 One (1) Garmin GTN 650H, with OEM NVG, integrated touch screen Nav/Com system.

5.2.2 One (1) Garmin GTN 750H, with OEM NVG, integrated touch screen Nav/Com system.

5.2.3 One (1) Garmin GTX 33 ES Mode S transponder.

5.2.4 One (1) Garmin GDL 88 ADS-B.

5.2.5 One (1) Garmin GTS 800 TAS with Dual Directional antennas.

5.2.6 Garmin GRA 5500 Radar Altimeter

5.2.7 The communications radio antenna installation shall allow for simultaneous transmission of the COM 1 and the COM 2 radios without interference.

5.2.8 One (1) Kannad 406mhz ELT with antenna and dongle.

5.2.9 One Cobham HeliSAS system with full functionality.

5.2.10 Geneva Avionics P132 switch console, if applicable.

6 SPECIALIZED EQUIPMENT REQUIREMENTS: The following specialized equipment shall be provided by the contractor and installed in/on the helicopter. All support equipment will be provided with the helicopter at the time of delivery.

6.1 One UTC Aerospace Systems Rescue Model #44301-10-5 Hoist shall be installed.

6.1.1 The hoist shall have a minimum 500 lbs lift capability, staying with operational lateral and longitudinal CG limits.


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6.1.2 The hoist mount must allow for the rescue hoist cable to be outside the skid envelope during hoisting operations.

6.1.3 The hoist shall have a “hoist camera” installed with recording capability.

6.1.4 The hoist must have a slip clutch.

6.1.5 The hoist must have unlimited duty cycles (no cool down periods).

6.1.6 The hoist must have a self-locking hook.

6.1.7 The hoist must be able to withstand fleet angles of 30 degrees (60 degree cone) or greater for hoisting in heavy winds or ocean rescues.

6.1.8 The hoist shall have a downward oriented LED light of suitable intensity for hoisting operations. Type to be reviewed and agreed upon at the Pre-Work Conference.

6.2 One (1) Churchill ARS-500C mapping system shall be installed.

6.2.1 The mapping system shall include the following additional features:

6.2.1.1 Augmented reality map overlay.

6.2.1.2 One (1) Aero Computer (AK-4-NVIS) tray mounted keyboard.

6.2.1.3 The system shall be fully integrated with the features of the Rho Theta RT-600 / SAR-DF-517 direction finding system.

6.2.1.4 Two (2) USB ports shall be installed at the operator workstation for the purpose of supporting the ARS-500C video recording capability.

6.2.1.5 Two (2) Sandisk MicroMate USB to SD/SDHC Memory Card Reader/Writers.

6.2.1.6 Four (4) Sandisk 32 GB SDHC Memory Cards.

6.2.1.7 One Churchill Ground Control System (ARS-GCS)

6.2.1.8 Built-in digital video recorders, able to play back video while recording.

6.2.1.9 Software shall include functional augmented reality showing street labels, roof top addresses and business names.

6.2.1.10 Software customization at no additional charge.


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6.2.1.11 The system shall have the capability to have software updates installed in the mapping system without the necessity to remove mapping “box” from the aircraft.

6.2.1.12 System lifetime software updates at no additional charge.

6.2.1.13 Spares shall be provided at no charge, if needed, shipped to the CHP within 24 hours. Spares can be either a replacement mapping system, or a replacement component (i.e. Hard Drive, Flash Memory, etc.)

6.2.2 The mapping system shall include at a minimum the following map system databases:

6.2.2.1 Aeronautical Sectional and Terminal Area Charts for the entire continental United States.

6.2.2.2 Roads for the entire continental United States.

6.2.2.3 One (1) Meter aerial imagery for the entire state of California and Nevada.

6.2.2.4 One (1) foot resolution imagery for all major metropolitan areas in California.

6.2.2.5 24k Topographical Maps.

6.2.2.6 California trail systems.

6.2.2.7 California Parcel Data.

6.3 Rho Theta RT-600 / SAR-DF-517 direction finding system, with installation kit, antenna and control head integrated with the Churchill navigation system specified above.

6.3.1 Integration of the Rho Theta RT-600 direction finding system shall be done at the direction of a Rho Theta representative who shall participate in the pre-work conference.

6.3.2 Onsite testing shall be conducted with a Rho Theta specialist to ensure proper function with no radio interference.

6.4 Camera Imaging System. One (1) FLIR Star Safire 380c HD Turret shall be installed. The imager shall include:

6.4.1 One (1) HD thermal Imager with Native 1280x720 FPA with 40x continuous zoom.


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6.4.2 One (1) HD CCD Color Camera with 1080p and 40x continuous zoom.

6.4.3 Both the HD IR and the HD Color Sensor will utilize a Continuous Zoom for uninterrupted viewing between the optical Wide and Narrow Field-of-View limits.

6.4.4 Both HD IR and HD Color sensors must have an optical Wide Field of View (WFOV) of at least 40° and an optical Narrow Field of View (NFOV) of 1.2° or less.

6.4.5 One (1) LP – Laser Pointer, Near-IR, 150mW

6.4.6 One (1) Universal Hand Controller Unit.

6.4.7 CALI – Cover Active Laser Illuminator, Near-IR, 2W

6.4.8 IMU – GeoPoint Package w/IMU, GPS Receiver and Nav Processor

6.4.9 Auto Tracker

6.4.10 Image Blending

6.4.11 One (1) Standard Cable Kit

6.4.12 One (1) HD video Common Cable Kit

6.4.13 Any mount and mounting hardware necessary to install the turret on the aircraft shall be provided by the contractor.

6.4.14 The total camera turret weight shall not exceed 55 pounds.

6.4.15 There shall be a place to mount the hand controller where it shall be easily accessible from all seats.

6.4.16 The system shall be capable of being turned on and off at any time during operation of the helicopter, without causing damage to any component of the system.

6.4.17 The system shall be capable of displaying time, date, GPS annotation, indication of the scene window when switching from WFOV to NFOV, gimbal position (azimuth and elevation), autotracker status, magnification status of both sensors on the multi-function display unit, and indication of system cool down status.

6.5 Monitors: One (1) Multi-Function display units shall be installed.

6.5.1 Copilot Work Station Monitor. One (1) Avalex AVM 4167T, 15.6 inch, high definition (HD), wide screen (16:9 aspect ratio) monitor with touch screen shall be installed and oriented to maximize visibility from the


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copilot seat. The video graphics array (VGA) feed from the Churchill ARS-500C shall be sent to the monitor. A dedicated composite video feed from all sensors to include IR, EOW, EON, and Low Light from the FLIR 380 HD sensor will also be wired to the monitor for redundancy. The monitor shall include HDSDI and DVI input capability. The touch screen shall work when touched with nomex gloves.

6.6 Two overhead, adjustable intensity, NVG compatible map lights shall be installed. All interior lighting shall be Night Vision Goggle (NVG) compatible. White LED lighting compatible with NVG’s is preferred.

6.7 A wide instrument panel shall be utilized to mount all specified instrumentation, avionics and equipment. The panel shall have Aero-Dynamix NVG instrument modification. Layout design to be discussed and agreed upon at the Pre-Work Conference.

6.8 Three (3) hard point provisions in the rear cabin area suitable for attaching a carabineer/tether, capable of sustaining a 250 pound side-load. Location and type to be discussed and agreed upon at the Pre-Work Conference.

6.9 Door shocks for left and right front doors to be mounted on the upper portion of the door.

6.10 Sliding doors on the left and right side.

6.11 The aft sliding doors shall have comfort windows with sliding vent openings and smoke/gray tint. (Tech-Tool model #3501CC-2032)

6.12 The forward reduced doors shall have comfort windows with sliding vent openings and smoke/gray tint. (Tech-Tool model #3501CC-2030)

6.13 Hard point hand grip on cabin upper left rear bulk head. Location and type to be discussed and agreed upon at the Pre-Work Conference.

6.14 High skids with full length skid protection on the bottom of the skids.

6.15 Full length “flight step” on left and right sides. Location and type to be discussed and agreed upon at the Pre-Work Conference.

6.16 Removable snow skis or tundra pads (Dart Bear Paws or similar) to be discussed and agreed upon at the Pre-Work Conference.

6.17 Cargo hook swing with at least 1600 pounds capacity.

6.18 Cabin air conditioner system, Integrated Flight Systems. Location and type to be discussed and agreed upon at the Pre-Work Conference.

6.19 Trakkabeam A800 searchlight


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6.19.1 Installation shall include provision for the pilot to control all functions while piloting the helicopter (cyclic mounted switch location/s to be discussed and agreed upon at the Pre-Work Conference).

6.19.2 Infrared LED ring shall be incorporated when/if available.

6.20 Flush-mounted, retractable landing/search light, with azimuth and elevation control, visible with NVGs, XeVision XV-36-SL 50 watt.

6.21 Fixed landing light, visible with NVGs, XeVision HID XV-36-SL 35 watt, or similar.

6.22 Fixed Taxi light, visible with NVGs, XeVision HID XV-36-ST 35 watt, or similar.

6.23 Belly mounted, left side, LED flood light.

6.24 Pulse light system connected to the landing light and taxi light.

6.25 Whelen Comet flash, dual LED strobe light system. One flash unit shall be mounted to the lower fuselage assembly, one mounted on the top of the vertical fin. The lower flash assembly shall have a lens half white/half red, with red mounted forward.

6.26 DevoreTM Tel-Tail lighting system, visible with NVGs.

6.27 Rotor brake.

6.28 Aft door assembly and hinge modification kit (Airbus Canada or equivalent).

6.29 Dart rear locker extender.

6.30 Heated pitot tube.

6.31 Pitot cover.

6.32 Dual control covering, if required when dual controls are removed.

6.33 Provide one (1) set of hydraulically operated maintenance ground handling wheels or equivalent.

6.34 One (1) ChopperSpotter. Model MS, ground handling system.

6.35 Window covers.

6.36 One set of aftermarket Blade Tie downs (Airbus Canada or equivalent).

6.37 External engine oil filter (Facet).


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6.38 Wire strike protection kit.

6.39 Tail rotor guard.

6.40 AFS/aerofilter inlet barrier filter system.

6.41 Any other appropriate engine equipment, if required, for operation in falling or blowing snow.

6.42 An audible engine-out alarm or an audible low rotor RPM alarm.

6.43 Chip detectors shall be installed on the main rotor gearbox, tail rotor gearbox and engine gear box. The chip detectors shall be wired to illuminate an appropriately labeled segmented caution light in the helicopter’s cockpit. Wherever possible, quick disconnect plugs shall be installed.

6.44 Fire Extinguisher

6.45 A heavy duty Lead Acid Battery shall be installed in the aft (tailboom) position (Airbus Canada battery relocation kit with a Concorde RG0390 E battery). One spare battery shall be provided at the time of delivery (Concorde RG0390 E).

6.46 One (1) Cup holder accessible from the copilot work station.

6.47 One (1) Cup holder accessible from the pilot station.

6.48 Lonseal loncoin #2, featherweight, (123 black), vinyl floor covering that allows easy clean-up and limits/retains fluids in a limited space.

6.49 One (1) power outlet that converts 28 Vdc to 12 Vdc and has a cigarette lighter style receptacle and/or USB port located at or near the copilot work station.

6.50 One (1) power outlet that converts 28 Vdc to 12 Vdc and has a cigarette lighter style receptacle and/or USB located at or near the pilot station.

6.51 A master DC power switch and circuit breaker shall be provided to permit single-point power control for all radios, fuel management, public address, and intercom systems.

6.52 An emergency bypass circuit shall be incorporated to allow NAV/COM 1, ICS and CHP radio operation in the event of master radio relay failure.

6.53 Two (2) ACR Aqualink PLB 350-B Personal Locator Beacons.

6.54 Three (3) aluminum publications boxes of size and design to be reviewed and agreed upon at the Pre-Work Conference. Two boxes are to be affixed to the


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pilot’s collective barrier, and one box is to be affixed to the cabin floor to the right side of the pilot’s seat and will accommodate the fire extinguisher mount.

6.55 Two (2) seat back publications holders with two pouches, fabricated from leather or a similar material, to be mounted on the back of the pilot’s and copilot’s seat and quickly removable during reconfiguration.

7 LAW ENFORCEMENT RADIO REQUIREMENTS:

7.1 One (1) Technisonic model TFM-30 transceiver to be mounted in the center console area. .

7.2 (1) Technisonic model TDFM 9300 transceiver to be mounted in the center console area. The TDFM 9300 transceiver shall include four (4) Type A, P25 Radio Frequency (RF) modules, installation kit, and necessary cabling. The TDFM 9300 transceiver shall have the capability of transmitting on each of the installed radio bands simultaneously. The base TDFM 9300 transceiver shall include one each of the following modules:

7.2.1 VHF analog Low Band Module (T1 – 30 to 50MHz)

7.2.2 VHF/Ultra High Frequency (UHF) Low Band Radio Module 7.2.2.1 Primary Band: VHF (136 - 174 MHZ)

7.2.2.2 Secondary Band: UHF Low (380 – 470 MHz)

7.2.3 VHF / (UHF) Low Band Radio Module

7.2.3.1 Primary Band: VHF (136 - 174 MHz)

7.2.3.2 Secondary Band: UHF Low (380 – 470 MHz)

7.2.4 700/800 MHz/ UHF High Band Radio Module

7.2.4.1 Primary Band: 700/800 MHz (764 to 870 MHz)

7.2.4.2 Secondary Band: UHF High (450-520 MHz)

7.2.5 700/800 MHz/ UHF High Band Radio Module

7.2.5.1 Primary Band: 700/800 MHz: (764-870 MHz)

7.2.5.2 Secondary Band: UHF High (450-520 MHz)

7.2.6 Each of the above listed Technisonic TDFM 9300 modules shall have the following options included:

7.2.6.1 Legacy System Key Software


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7.2.6.2 Advanced System Key

7.2.6.3 Enable Dual Band Operation

7.2.6.4 TDMA Operation

7.2.6.5 FCC Mandated Narrow Band Operation

7.2.6.6 CAI for P25

7.2.6.7 Smartzone Trunking

7.2.6.8 Astro P25 Trunking

7.2.6.9 AES Encryption with DES, DES-XL and DES-OFB

7.2.6.10 Multikey

7.2.6.11 Front Panel Programming

7.3 One (1) Technisonic KVL 9000 Key Loader with all required equipment for the Technisonic TDFM 9300 to include all necessary hardware, cables, and software for the modules installed.

7.4 One (1) PC9000 cable for code plug programming.

7.5 Antennas required for the Technisonic TFM 30 and TDFM 9300 radio modules:

7.5.1 Four (4) Comant SAR Tri-Band Antennas each with the following frequency ranges: 7.5.1.1 Frequency range: 136 - 174 MHz 7.5.1.2 Frequency range: 403 - 520 MHz 7.5.1.3 Frequency range: 764 – 870 MHz

7.5.2 Two (2) Foxtronics Tunable Antennas each with the following frequency range:

7.5.2.1 Frequency range: 28 – 50 MHz

7.6 One (1) Uniden BCD536HP Scanner to be mounted at a location reachable by the Pilot or Copilot.

8 SATELLITE PHONE/TRACKING REQUIREMENTS:


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8.1 One (1) Flightcell DZMx DZUS with Satellite and 3G Cellular capability to be mounted on the copilot workstation. The Flightcell DZMx shall include the following options:

8.1.1 One (1) Dual flat antenna L1 GPS/Iridium BNC/TNC White

8.1.2 One (1) Blade Cell Antenna 800 – 2500 MHz

8.1.3 One (1) Flight Cell USB/Ethernet Civilian Connector Box

8.1.4 External satellite phone cradle for Iridium Extreme® handset.

8.1.5 Internal cellular modem.

Note: The total line of service requirement shall be two (2), one for the cellular service and one for the satellite service.

9 COMMUNICATIONS EQUIPMENT REQUIREMENTS:

9.1 Three (3) One (1) Becker DVCS ACU6100-2-5300 Digital Audio Panels and installation kits. One mounted at the pilot position, one at the co-pilot position, and one overhead in the aft cabin area.

9.1.1 The audio panels shall accommodate a minimum of eleven (11) transceivers and four (4) receivers. This requirement may be met through the use of an accessory switching panel, the design and size of the accessory switching panel is to be determined during the Pre-Work conference.

9.2 One (1) Becker REU6100 Remote Electronics Unit.

9.3 All communication and navigation audio shall be integrated with the Becker DVCS Digital Audio Panel System to be reviewed and agreed upon at the Pre-Work Conference. Four rear passenger seats shall be slaved to the overhead aft station Becker DVCS ACU6100 audio panel. Two exterior (belly mounted) U174/U jacks shall be slaved to the copilot audio panel.

9.4 One (1) Power Sonix PSAIR 22A Public Address/Siren System. The speakers must be recessed.

9.4.1 The PA/siren system controller and speaker mounting plans shall be reviewed and agreed upon at the Pre-Work Conference.

9.5 One (1) Technisonic A790 Loud Hailer Controller Audio Panels to control the Power Sonix PSAIR 22A.

9.6 Intercom System (ICS):

9.6.1 A six (6) place ICS shall be installed.


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9.6.1.1 One U-174/U compatible jack shall be located at each of the following locations:

9.6.1.1.1 Pilot station.

9.6.1.1.2 Copilot location.

9.6.1.1.3 Left exterior hot mic, belly area (location to be discussed and agreed upon at the Pre-Work Conference).

9.6.1.1.4 Right exterior hot mic, belly area (location to be discussed and agreed upon at the Pre-Work Conference).

9.6.1.1.5 Install Active Noise Reduction (ANR) jacks at pilot and copilot headset jack locations.

9.6.1.2 Four (4) quick-connect cannon plugs compatible with Comm

Innovations CIX200 (reference 9.12 below) accessible to the four rear passenger seats. Location to be discussed and agreed upon at the Pre-Work Conference.

9.6.2 The system shall provide ICS between front crew positions with the aircraft battery switch on regardless of radio master switch position.

9.6.3 The pilot station shall have the ability to switch between pilot, crew, and rear ICS functions.

9.7 During transmission, transmit side-tone shall be present in the operator’s headset. The same side-tone shall be heard in the other operating positions unless that position has the circuit muted.

9.8 The audio panels shall be integrated so that the pilot station, co-pilot station and rear stations function as separate stations to allow for the independent transmission and reception of aural radio communications via all installed radio devices capable of transmitting or receiving aural radio communications.

9.9 The audio panels shall be integrated to allow the following communications to occur simultaneously without interference:

9.9.1 Pilot and co-pilot stations shall be able to transmit and receive on all installed law enforcement and aviation radios while the rear station is transmitting on any installed law enforcement and aviation radios.

9.10 The pilot station, co-pilot station, and rear station audio panels shall be installed in a manner allowing each respective station to be isolated from any and all combinations of electronic communications installed in the aircraft.


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9.11 All communications must be through the headsets/helmets.

9.12 Transmit switches for the radios and ICS shall be installed on both cyclics.

9.13 Transmit switches for the radios and ICS shall be installed at the copilot workstation to include both a hand toggle switch mounted on the center console and a foot activated switch that can be reached while seated at the copilot workstation which does not interfere with the Dart litter when installed for Medevac.

9.14 Four (4) Comm Innovations CIX200 series PTT switch/cable assemblies. The switch/cable assemblies shall include the following features:

9.14.1 PTT

9.14.2 Slide switch with ICS, momentary, and lock positions

9.14.3 Volume control

9.14.4 Cell phone port

9.14.5 U174/U Jack

9.14.6 Coiled cable 3 ft. in length

9.15 Four (4) David Clark H10-13H headsets. All headsets shall be equipped with retractile cords and U-174/U plugs.

10 ELECTRICAL REQUIRMENTS:

10.1 The helicopter shall have an electrical system capable of supporting all avionics and mission equipment described herein (minimum 200 Amp output).

10.2 All options and systems installed shall be compatible with each of the other options and systems installed. An amperage management matrix shall be provided to outline each electrical system and the electrical load each item draws. The amperage matrix shall demonstrate the ability of the aircraft electrical system to handle the electrical load of all equipment installed. In any event, the air-conditioner and nightsun should be able to run simultaneously.

10.3 A master avionics power switch and circuit breaker shall be provided to permit single-point power control for all radios, fuel management, public address, and intercom systems.

10.4 An emergency bypass circuit shall be incorporated to allow NAV/COM 1, ICS and CHP radio operation in the event of master radio relay failure.

10.5 An avionics cooling fan system shall be installed as necessary to reduce the


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heat build-up of avionics equipment. It will be the contractor’s responsibility, based on manufacturer’s recommendations, to determine the number of cooling fans required to adequately cool all the avionics equipment.

10.6 A disconnect circuit shall be incorporated to automatically disconnect all radios when the starter is energized with the radio master in the “On” position, thus preventing damage to the sensitive electronic circuitry.

10.7 Wiring harnesses supplied by electronic manufacturers must meet the standards set forth by the FCC and FAA Advisory Circular 43.13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations, dated March 3, 2008. All wiring shall be properly shielded and grounded. All shielding shall be of high quality which shall be reviewed and agreed upon at the Pre-Work Conference.

10.8 All wiring, wiring harnesses, and connector ports shall be marked for future identification.

10.9 All options and systems installed must be compatible with each of the other options and systems installed.

10.10 The installation/completion vendor shall include and install all wiring, necessary displays, switches, relays, interconnects, hardware, firmware, and software to make all systems and devices fully functional and interface together to the full extent of their design capabilities.

10.11 All wiring installed shall be indelibly marked along its entire length at a minimum of every 12 inches to identify its function. After installation every individual installed wire shall be checked for excessive electrical resistance (ohms) and integrity.

10.12 Service loops shall be provided for all mission equipment (service loop size and locations shall be reviewed and agreed upon at the Pre-work Conference).

10.13 All wiring and wiring harnesses, all installed equipment, all antennas, all headset positions, all control heads and indicators, and all switches/circuit breakers (fuses) shall be labeled.

10.14 All circuits shall be protected by appropriate circuit breakers or fuses.

10.15 Radios, control heads, wiring harnesses, brackets, racks, antennas, etc., cannot be installed in such a manner as to interfere or hinder the flow of cooling air anywhere around the radio stack.

10.16 Radios, control heads, wiring harnesses, brackets antennas, etc., cannot be installed in such a manner as to interfere or hinder the pilot/copilot work station or passenger accommodations.


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10.17 Throughout this document particular antennas are specified for some applications and particular antennas are not specified for other applications. The vendor shall ensure that equipment requiring antenna or antennas have those items properly installed to operate all the listed equipment and that each antenna is labeled as to its function and/or assigned piece of equipment.

10.18 Due to the numerous radios being installed, the selection of matched and properly sized antennas and their mounting locations is a critical factor. The contractor shall ensure that all antennas are matched, of proper size, and installed for optimum performance. The contractor will be responsible to correct any radio frequency interference problems with any receiver(s) at no cost to the CHP. The contractor shall supply a drawing to be reviewed and agreed upon at the Pre-Work Conference of all antennas selected and their mounting locations prior to beginning installation. All antennas installed shall meet the guidelines published in FAA Advisory Circular 43.13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations, dated March 3, 2008.

10.19 All electronics installed shall be checked for radiated electromagnetic interference as described in FAA AC 43.13-2B, Acceptable Methods, Techniques, and Practices-Aircraft Alterations, dated March 3, 2008.

11 OPTIONS:

11.1 EMS Equipment List: The following equipment is based on the CHP’s current

fleet of AS350B3 helicopters; if the winning bid includes a type of helicopter other than the AS350B3, then the EMS equipment list will be adjusted during the Pre-Work conference. Alternatives to this equipment may be considered based on efficiency of design for specified operations and weight savings over current equipment.

11.1.1 One (1) Laerdal Compact suction unit (LCSU 4) 300ml capacity.

11.1.2 Provide one Zoll X Series ® Manual Monitor/Defibrillator (Part #601-

2231511-01) with 4 trace tri-mode display monitor/defibrillator/printer, comes with Real CPR Help®, advisory algorithm, advanced communications package (Wi-Fi, Bluetooth, USB cellular modem capable) USB data transfer capable and large 6.5"( 16.5cm) diagonal screen, full 12 EKG lead view with both dynamic and static 12-lead mode display. Accessories Included:

11.1.2.1 Six foot 3-Lead ECG cable. 11.1.2.2 MFC cable. 11.1.2.3 MFC CPR connector. 11.1.2.4 A/C power adapter/battery charger. 11.1.2.5 A/C power cord. 11.1.2.6 One (1) roll printer paper.


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11.1.2.7 6.6 Ah Li-ion. 11.1.2.8 Carry case. 11.1.2.9 Declaration of Conformity. 11.1.2.10 Operator’s Manual. 11.1.2.11 Quick Reference Guide. 11.1.2.12 One (1)-year EMS warranty.

11.1.3 Advanced Zoll X Options:

11.1.3.1 Real CPR Help Expansion Pack: CPR Dashboard

quantitative depth and rate in real time, release indicator, interruption timer, perfusion performance indicator (PPI), See - Thru CPR artifact filtering.

11.1.3.2 ZOLL Noninvasive Pacing Technology. 11.1.3.3 Masimo Pulse Oximetry SP02& SpCO: Signal

Extraction Technology (SET), Rainbow SET ( for SpCO & SpMet).

11.1.3.4 NIBP Welch Allyn includes: Smartcuff 10 foot Dual Lumen hose, SureBP Reusable Adult Medium Cuff.

11.1.3.5 End Tidal Carbon Dioxide monitoring (ETCO2). 11.1.3.6 Oridion Microstream Technology. 11.1.3.7 Interpretative 12- Lead ECG: 11.1.3.8 12-Lead one step ECG cable- includes 4- Lead limb

lead cable and removable precordial 6- Lead set. 11.1.3.9 Invasive pressure waveform capability display with

digital monitoring. 11.1.3.10 Two Temperature monitoring channels with digital

displays. 11.1.3.11 SpO2/SpCO/SpMet Rainbow Resuable Patient

Cable (Part# 8000-0341): Connects to Single Use Sensors (4 ft).

11.1.3.12 SpCO/SpMet Rainbow DCI Adult Reusable (Part#8000-000371): Sensor with connector (3 ft).

11.1.3.13 SurePower 4 Bay Charging System including 4. 11.1.3.14 Battery Charging adapters (Part# 8300-0500-01). 11.1.3.15 Six hour rechargeable Smart battery (Part #8000-

0580-01). 11.1.3.16 YSI reusable adult Skin Temperature probe (Part#

8000-0670). 11.1.3.17 Collapsible single patient litter with a minimum two tie

down brackets (Ferno Part Model #12-2A or equivalent). Dart Aerospace Full Emergency Litter Kit, P/N D350-616-011 (this option shall be discussed at the Pre-Work Conference).


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11.1.3.18 One double receptacle that converts 28 Vdc to 12 Vdc to also include a cigarette lighter style receptacle.

11.1.4 LifePort Inc. Medical Wall System additional components (to be discussed at the Pre-Work conference):

11.1.4.1 One (1) Wall Rack Assembly Part #100-5352. 11.1.4.2 One (1)Wall Rack Installation Part #375-3550-KIT. 11.1.4.3 Three (3) Cargo Pallets Part #ST2-267-01. 11.1.4.4 Modular equipment pouches, to be installed on cargo

pallet. Size and number to be determined. 11.1.4.5 One Cardiac Monitor Mount for Zoll X Series. 11.1.4.6 Three (3) Standard Thin Seat Cushion 16 inch Part

#100-7115-03-1. 11.1.4.7 One (1) Short Seat Thin Cushion 14 inch Part #100-

7115-04-1. 11.1.4.8 One (1) Lifeport lightweight “rag and tube seat”, 16-

00101-07-P00 PN-07.

11.2 Avionics:

11.2.1 One (1) Polycon Wireless Intercom System. Two (2) Jupitor Avionics Wireless Intercom System.

11.2.2 Two (2) Aviator Night Vision Goggles, F4949 AN/AVS-9 Class B or similar, with helmet mount and low profile battery pack.

11.3 Miscellaneous Flight Equipment:

11.3.1 Two (2) Portable Helicopter Oxygen Delivery Systems (PHODS, Transaero p/n 102935).

11.3.2 One (1) FAA approved (per FAA AC 91-78) tablet style Electronic Flight Bag (EFB) capable of supporting the Foreflight Aviation Application. The EFB shall have a seven to eight inch viewing screen, 32 GB memory, WIFI, external GPS, a protective case, and kneeboard. The EFB shall be mounted utilizing a removable Ram mount on the aircraft at a location to be reviewed and agreed upon at the Pre-Work Conference.

11.3.3 One (1) Fujinon Techno-Stabi 14x40 Binocular and case and a secure mount for the binocular case accessible from the copilot work station.

11.4 Ground Support Equipment:

11.4.1 One (1) Chopper Spotter model MS.

11.4.2 One (1) Hoffman Engineering ANV-20/20 Infinity Focus System.

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