Supp._3_-_Attach._B_1510-4636_As-Built.docx

December 27, 2022 Attachment 2 1510-46368[r1] *As-Built* Department of the California Highway Patrol

Airplane Specifications Specification Number: 1510-4636[r1] *As Built* [October 4, 2019] *December 27, 2022*

Scope:

This specification identifies the minimum performance, equipment, installation, and completion requirements for a, high-wing, turbine-powered, single-engine land, 10 place or greater, tricycle landing gear airplane for the Department of the California Highway Patrol (CHP). The airplane shall be a 2019 model year or later, with not more than 25 flight hours since date of manufacture for airframe or engine. The airplane shall be certified under Code of Federal Regulations (CFR) Title 14, Part 23 as amended by 23-1 through 23-28 (through amendment 28) at the time of bid submission. The airplane 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. Unless otherwise indicated, references to the airplane include the airframe, avionics, and specialized equipment described herein.

AIRCRAFT CERTIFICATION REQUIREMENTS:

1.1. The airplane must have a Type Certificate (TC) issued by the Federal Aviation Administration (FAA) at the time of aircraft bid.

1.2. The airplane shall be certified by the FAA as a Normal or Utility Category Airplane.

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

1.4. The airplane must be certified for day and night visual flight rules and be certified for Flight Into Known Icing (FIKI).

1.5. The airplane must be FAA certified and equipped for single pilot flight in instrument meteorological conditions (IMC).

1.6. All installed equipment and accessories must have FAA approval and have no negative impact on the standard airworthiness certificate.

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

1.8. The airplane shall be FAA type certificated from the factory, issued an STC, or by FAA field approval to accommodate up to a 15.5-inch diameter, externally mounted, multi-sensor imaging system weighing up to 95 pounds and an interior mounted operator workstation.

1.9. 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, at latest amendment.

GENERAL REQUIREMENTS:

1.10. The airplane shall be equipped with dual flight controls and shall be certified for operation from both the front left and front right seat.

1.11. The contractor shall furnish and install on the flight deck, cabin, and instrument panel all required flight information, placards, and warning labels. All labels must be legible, professional quality and permanent. Label style, color, size, and mounting locations shall be approved by the CHP at the Pre-Work Conference.

1.12. The airplane shall have an interior design capable of seating a minimum of ten (10) occupants prior to integrating any specialized mission equipment.

1.13. The airplane shall have a built-in oxygen system to include a 115 cubic foot composite oxygen bottle and ports for the both the cockpit and cabin. A minimum of two (2) crew masks with built-in microphones and eight (8) passenger masks shall also be provided.

1.14. The airplane shall be capable of seating a minimum of six (6) occupants, including the flight crew, when the imaging system and full mission equipment are installed. The seats that are removed for equipment installation shall be provided to the CHP and shall be shipped separately as loose equipment.

1.15. The airplane shall be equipped with an environmental control system which includes an air conditioning and heating system capable of delivering hot and cold air to both the cabin and cockpit.

1.16. The airplane shall come equipped with a single point refueling system.

1.17. A flight time hour meter air switch shall be installed which measures time from takeoff to landing.

1.18. All systems installed must be compatible with each of the other systems installed.

1.19. Any equipment, capabilities, or provisions provided on a basic equipped aircraft of the make and model offered by the contractor shall be incorporated on the aircraft offered for purchase without regard to whether or not the equipment, provision, or capability is specified herein.

1.20. The floor covering shall be made of a durable, non-textile, slip-resistant, and fire-retardant material. The floor covering shall be constructed of a material that allows easy clean-up and limits/retains fluids in a limited space. The floor covering shall meet FAA flammability requirements as specified in FAR 23.853.

1.21. The vendor shall utilize a professional aircraft paint scheme designer to design the paint scheme for the aircraft such as:

Scheme Designers, Inc., 21 Broadway, Suite 204 Cresskill, NJ 07626 www.schemedesigners.com.

The vendor shall be responsible for the payment of the design directly to the aircraft paint scheme designer if a sub-contractor is used. The paint scheme designer sub-contractor shall be discussed at the pre-work conference and the CHP project coordinator shall give final approval of the selected company. The airplane shall be custom painted with top grade, EPA approved paint. The exact colors, paint scheme, and lettering dimensions will be coordinated with the vendor by the CHP project coordinator. The paint scheme shall be similar to the existing CHP aircraft and pictures are available upon request during the bidding process.

1.22. The cabin interior shall be of a deluxe (or comparable) construction and of a color compatible with the exterior paint scheme. Seat material and color scheme to be discussed and agreed upon at the Pre-Work Conference.

1.23. All seats shall be of a crashworthy design. Crashworthiness refers to those seat design characteristics that protect the occupant from injury or death during a crash event.

1.24. Rear interior configuration shall consist of the following:

1.24.1. One (1) flight officer workstation console assembly and equipment rack shall be installed to accommodate mission specific equipment, three (3) monitors, a hand controller, satellite phone, downlink control head, mapping keyboard, communication audio panels, and mission specific radios.

1.24.2. The flight officer workstation console shall be of design and material that will allow for simple removal and re-installation via canon plugs by a maximum of two (2) crewmembers. The removal and re-installation shall be able to be accomplished in no more than 1 hour.

1.24.3. Upon removal of the flight officer workstation the interior of the aircraft shall be able to be reconfigured to accommodate the original number of passenger seats.

1.24.4. The aircraft must have the capacity to accommodate a minimum of three (3) additional passenger seats, in addition to the pilot and co-pilot seats, when the flight officer workstation console and equipment rack are installed.

1.24.5. The aircraft center of gravity shall be in the acceptable range as certified by the manufacturer when configured with the mission equipment, TKS ice system, and camera with the following configuration: 1,000 pounds of fuel, one (1) pilot weighing 165 pounds occupying the primary pilot position, and four (4) passengers occupying the rear of the cabin with an average weight of 200 pounds per occupant.

ELECTRICAL REQUIRMENTS:

1.25. The airplane shall have an electrical system capable of supporting all avionics and mission equipment described herein.

1.26. An amperage management matrix shall be provided at delivery of the aircraft 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.

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

1.28. A secondary avionics power switch and circuit breaker shall be provided to permit power control for mission specific equipment (i.e., flight officer workstation and camera system).

1.29. An avionics cooling fan system shall be installed as necessary to reduce the heat build-up of mission 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.

1.30. 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, at latest amendment. All wiring shall be properly shielded and grounded. All shielding shall be of high quality and reviewed and approved at the Pre-Work Conference.

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

1.32. 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.

1.33. All wiring for the mission equipment installed by the finishing center 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.

1.34. Service loops shall be provided for mission equipment (service loop size and locations shall be discussed and agreed upon at the Pre-Work Conference).

1.35. 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.

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

1.37. 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.

1.38. Radios, control heads, wiring harnesses, brackets antennas, etc., shall not be installed in such a manner as to interfere or hinder the flight officer workstation or passenger accommodations.

1.39. 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 an antenna or antennas shall 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.

1.40. 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. At the Pre-Work Conference, the contractor shall submit a drawing for approval of all antennas selected and their mounting locations. Any changes must be approved 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, at latest amendment.

1.41. All electronics installed shall be checked for radiated electromagnetic interference as described in FAA Advisory Circular 43.13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations, at latest amendment.

OPERATIONAL REQUIREMENTS:

1.42. The airplane shall meet the minimum performance specifications listed in this section. These performance specifications are necessary for the variety of missions conducted in CHP airplanes. The performance parameters were determined based on mission needs and objective data. The performance specifications required in this section shall be the minimum performance requirements prior to installation of mission equipment.

1.43. Aircraft performance and weight and balance figures used to meet the specifications described herein must be supported by FAA approved manufacturer performance and weight and balance charts for the make and model of aircraft specified in the bid.

1.44. The airplane must have a turbine engine with a minimum horsepower rating of 675 horsepower.

1.45. The airplane shall have a useful load of a minimum of 3,300 pounds.

1.46. The airplane must have a certified maximum operating altitude of 25,000 feet or greater.

1.47. The airplane must have a stall speed of 67 KIAS or less and a true airspeed of 172 knots or greater at a pressure altitude of 12,000 feet and at 0° Celsius.

1.48. The airplane must have a sea level takeoff distance over a 50-foot obstacle of not more than 2602 feet at maximum gross weight with ISA and zero wind.

1.49. The airplane must have a wingspan of less than 53 feet.

1.50. The airplane must have a cabin width of 54 inches or greater and a cabin height of 54 inches or greater.

1.51. The contractor shall provide, at the time of aircraft delivery, a detailed weight and balance worksheet indicating the weight, station arm, and moment of all equipment installed.

AVIONICS EQUIPMENT REQUIREMENTS:

The following avionics shall be provided by the vendor and installed in/on the airplane:

1.52. Flight and Engine Instruments:

1.52.1. One (1) Electronic Angle of Attack Indicator with display integrated into the avionics.

1.52.2. One (1) Garmin G1000nxi or G3000nxi glass panel system with the following options installed: Synthetic Vision Technology, Jeppesen Chart View, and Video Input. The avionics system shall come with a Chart View Unlock Key and include a one (1) year Jeppesen Chart Pilot Pak Bundle for the Western United States.

1.52.3. One (1) radar altimeter which provides an absolute altitude indication from 2,000 to 0 feet AGL. The radar altimeter shall provide for a selection of warning altitude, and annunciation via both a decision height light and an aural warning.

1.52.4. One (1) GTS 800 Traffic Avoidance System (TAS). The system shall be capable of displaying the position of nearby aircraft on the glass panel and provide an aural warning when there is a potential conflict.

1.52.5. One (1) Garmin GTX 345 transponder with ADS-B out and in capability. Transponder shall come equipped with the ability to turn off mode S and only provide mode C reporting to ATC (mode A/C enablement). This is a feature available to law enforcement agencies when necessary to conduct covert operations.

1.52.6. One (1) Garmin Flight Stream 510 shall be installed in the aircraft allowing advanced connectivity and avionics integration.

1.52.7. Garmin Search and Rescue Enhanced Enable Card

1.52.8. One (1) Autopilot. The autopilot shall be 3-axis and fully integrated with the aircraft GPS and other navigation systems to allow autopilot coupled precision and non-precision instrument approaches as well as enroute navigation using GPS steering. The autopilot shall also be integrated with the AHRS digital altitude/heading reference system. The autopilot shall include a control wheel steering and missed approach feature with a yoke mounted switch.

1.52.9. One (1) Digital Outside Air Temperature Gauge

1.52.10. One (1) Digital Clock with Timer

1.52.11. A built in Engine Data Management System that is capable of recording engine data parameters and displaying at minimum the following:

· Fuel remaining

· Fuel flow

· Fuel required to destination

1.52.12. A built-in digital Voltmeter/Ammeter capable of monitoring both aircraft and mission equipment electrical loads.

1.53. Navigational/Communications Systems:

1.53.1. The aviation communications radio antenna installation shall allow for simultaneous transmission of the COM 1 and the COM 2 radios from any audio panel station without interference.

1.53.2. One (1) 406 MHz Emergency Locator Transmitter (ELT) with Global Positioning Satellite (GPS) interface, remote flexible antenna, and activation/reset switch. There shall be an instrument-panel switch to allow for testing of the ELT.

SPECIALIZED MISSION EQUIPMENT REQUIREMENTS:

The following specialized equipment shall be provided by the contractor and installed in/on the airplane. All support equipment will be provided with the airplane at the time of delivery.

1.54. One (1) Churchill ARS-700 mapping system shall be installed to include one (1) backlit, mechanical keyboard.

1.54.1. The Churchill ARS-700 system shall be equipped with direct input from the LoJack system (described in Section 12.6.) to the Churchill moving map. The Churchill ARS-700 shall be fully integrated with the features of the LoJack system.

1.54.2. The Churchill ARS-700 system shall be capable of recording audio from any of the CHP or law enforcement radios without recording any intercom audio. In addition to recording the current station, a selector switch shall be installed at the FO workstation to allow the FO to select which radio audio to be recorded.

1.54.3. The mapping system shall include the following additional features:

· Augmented reality map overlay

· Map database updates for the life of the unit

· Two (2) USB ports shall be installed at the operator workstation for the purpose of supporting the ARS-700 video recording capability

· Ten (10) SanDisk Ultra 256 GB USB 3.0 flash drives

1.54.4. The mapping system shall include at a minimum the following map system database:

· Aeronautical Sectional and Terminal Area Charts for the Continental United States (CONUS)

· Vector Data for all of CONUS to include road data, rooftop parcel data for at least 90% of CONUS, Ski Lifts, Ski Runs, Railroads, Water Bodies, Schools, Parks, and Dams

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

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

· 24k Topographical Maps

· Maps for all California forest, state, and national parks

1.55. Camera Imaging System

1.55.1. One (1) L3 MX-15 HDIR, Multi-Spectral, Gyro-Stabilized Turret Unit shall be installed on the underside of the fuselage. The turret unit shall include the following payloads, features, and support equipment:

· One (1) 1280 X 1024 Native HD format Infrared (IR) Thermal Imager

· One (1) HD Color/Low Light Zoom Camera

· One (1) 3-Step Color Dual Channel EO Narrow (EON)/Low Light Camera

· One (1) laser illuminator

· One (1) laser range finder

· One (1) laser arming panel

· Image Fusion feature

· One (1) L3 Hand Controller Unit

· One (1) Turret Mounted, Tightly Coupled, Inertial Measuring Unit

· (IMU) with Geo Point

· One (1) Standard Cable Kit

· One (1) HD video Common Cable Kit

· Software Interface for operation with Churchill Navigation ARS Map System

· One (1) GPS dual channel L1/L2 antenna for IMU/Geo Point package

· One (1) Purge Kit

1.55.2. All turret unit outputs shall be fully integrated with the Churchill ARS- 700 Mapping System describes in Section 7.1. and the monitors described in Section 7.3.

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

1.55.4. If the turret is installed on a retractable belly mount, there shall be a failsafe system installed to automatically retract the turret when below 500 feet above the ground and certain other operational parameters as discussed and agreed upon at the Pre-Work Conference.

1.55.5. If the turret is not installed on a retractable belly mount, it shall be mounted utilizing a system that would allow a maximum of two (2) crewmembers the ability to remove the camera in no more than 15 minutes. Connections between the camera and the underside of the aircraft shall be easily removed and there shall be no connections left dangling on the underside of the aircraft upon removal of the turret. In the event TKS icing is installed on the aircraft, the aircraft shall still be certified for FIKI when the camera turret is removed.

1.55.6. If the turret is located in a pod and the camera cannot be fully deployed and removed while on the ground, the airplane shall be delivered with one (1) set of aircraft main wheel jacks to be delivered to the location in California designated by the project coordinator.

1.55.7. If the turret is installed in a belly pod using a retractable system, the airplane shall be delivered with one (1) Pod Jack to remove the camera pod. The Pod Jack shall be delivered to the location in California designated by the project coordinator.

1.55.8. If the turret is installed in a belly pod using a retractable system, the camera shall have a heat exchanger for the L3 MX-15 camera imaging system.

1.55.9. If the turret is not installed in a belly pod, the airplane shall be delivered with one (1) camera storage box for the MX-15 (not the storage box delivered with the camera). This storage box will be used to store the MX-15 camera in the airplane in the event the camera must be removed in the field and secured in the airplane. The design material and specifications of this box will be agreed upon at the pre-work conference by the project coordinator.

1.55.10. The total camera turret weight shall not exceed 95 pounds.

1.55.11. The hand controller shall be mounted where it is easily accessible from the flight officer workstation.

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

1.56. Monitors: Four (4) Multi-Function display monitor units shall be installed. Three (3) monitors shall be mounted in a location viewable from the flight officer workstation and one (1) mounted on the flight deck viewable from the pilot seat.

1.56.1. Flight Officer Workstation Primary Monitor

One (1) Airborne Displays AB 22W 21.5 HD-SDI high definition, wide screen monitor with touch screen shall be installed at the flight officer workstation. The video graphics array (VGA) and VGI feed from the Churchill ARS-700 shall be sent to the monitor. A dedicated HDSDI video feed from all sensors to include the Native IR, HD Color, and HD Low Light/HD Color Zoom (including EON and EOW) from the MX-15 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.

1.56.2. Flight Officer Work Station Second and Third Monitors Two (2) Airborne Displays AB-156W, 15.6 inch, HD-SDI, high definition, wide screen monitor with touch screen shall be installed at the flight officer workstation. The video graphics array (VGA) and VGI feed from the Churchill ARS-700 shall be sent to each monitor. A dedicated HDSDI video feed from all sensors to include the Native IR, HD Color, and HD Low Light/HD Color Zoom (including EON and EOW) from the MX-15 HD sensor will also be wired to each monitor for redundancy. The monitors shall include HDSDI and DVI input capability and be wired with HDSDI input from the ARS-700 and DVI input from the MX-15 HD sensor. The touch screen shall work when touched with nomex gloves. The precise location of the flight officer workstation second and third monitors is to be determined during the Pre-Work Conference and is dependent on the aircraft platform and space available.

1.56.3. Flight Crew Monitor

One (1) Airborne Displays AB9-W HD-SDI high definition (HD), wide screen monitor with touch screen display shall be installed at a location viewable from the pilot station. The video graphics array (VGA) and VGI feed from the Churchill ARS-700 shall be sent to the monitor. A dedicated HDSDI video feed from all sensors to include the Native IR, HD Color, and HD Low Light/HD Color Zoom (including EON and EOW) from the MX-15 HD sensor will also be wired to the monitor for redundancy. The monitor shall include HDSDI and DVI input capability and be wired with HDSDI input from the ARS-700 and DVI input from the MX-15 HD sensor. A button or switch on the pilot’s dedicated switch panel shall allow the pilot to toggle video feeds from the MX-15 HD sensor and Churchill ARS-700 mapping system or approved alternate monitor as discussed and agreed upon at the Pre-Work Conference. The precise location of the flight crew monitor is to be determined during the Pre-Work Conference and is dependent on the aircraft platform and space available. A suitable alternate monitor may be substituted if space does not allow for the specified monitor. Any alternate monitor must have full functionality as specified and shall be approved by the project coordinator. The touch screen shall work when touched with nomex gloves.

1.56.4. Primary Avionics MFD Video Display

The primary avionics MFD installed on the aircraft shall be equipped with an auxiliary analog input and appropriate video converter to display video from the MX-15 sensor and map data from the Churchill ARS-700 Mapping System. The MFD shall also have a bearing pointer tied in to the Churchill ARS-700 to display the direction the sensor is pointing.

1.56.5. *Display Port to 3-G Scaling Convertor*

· *The Convertor shall have an IP 68 or better weather resistance rating. *

· *The Convertor shall have at least 3 channels. *

1.56.6. *3-G SDI Video Switch*

· *The Video Switch shall have the capacity for 8 Inputs of High Definition (HD), Standard Definition (SD), and/or 3-G SDI video. *

· *The Video Switch shall have the capacity for 8 outputs of High Definition (HD), Standard Definition (SD), and/or 3-G SDI video. *

· *The Video Switch shall be low latency. *

· *The Video Switch shall be stand alone and suitable for rugged environments. *

1.56.7. *Programmable User Interface Rotary Switch* *Through a direct interface the Rotary Switch shall allow the Technical Flight Officer to select between various presets programmed into the 3-G SDI Video Switch. *

1.57. Electronic Flight Bags (EFBs)

1.57.1. Each EFB shall have an eleven-inch viewing screen, 256 GB memory, WIFI+Cellular, OEM digital pen with wireless charging and magnetic storage, a power adapter compatible with the aircraft power source, an Otterbox Defender protective case, Armorglass tempered glass anti-reflective coating, and shall be current generation or newer at time of aircraft bid.

1.57.2. The EFBs shall be mounted utilizing a removable Ram mount on the aircraft at a location viewable by the pilot and co-pilot stations (to be discussed and agreed upon at the Pre-Work Conference).

1.57.3. Two (2) X-Grip Ram mounts to mount the EFB’s to the aircraft.

1.57.4. Wiring shall be installed to provide a dedicated plug-in aircraft power source for the two (2) EFBs.

1.58. *LTE/Wi-Fi Router*

1.58.1. *The Router shall be able to provide Gigabit Wi-Fi, Gigabit Ethernet, and cellular uplink and downlink over the latest commercially available cellular standard*

1.58.2. *The Router shall contain multi-SIM functionality with automatic fallback or fallover.*

1.59. *Wi-Fi/LTE Aviation External Antenna*

1.59.1. *The Antenna shall be able to transmit LTE or latest commercially available signal type.*

1.59.2. *The Antenna shall be hermetically sealed and able to operate under the following conditions:

· Temperature: -67°F to +185°F (-55°C to +85°C)

· Altitude: 70,000 miles

· Vibration: 10 Gs

LAW ENFORCEMENT RADIO REQUIREMENTS:

1.60. One (1) Technisonic model TFM-30CHP transceiver with Very High Frequency (VHF) analog Low Band (T1 – 30 to 50MHz) to be mounted at the flight officer workstation. The TFM-30CHP shall be set up to allow car-to-car and car-to-dispatch communication. The TFM-30 shall be NVIS compatible.

1.61. One (1) Technisonic model TDFM [9300] *9000* transceiver to be mounted at the flight officer workstation. The TDFM shall be NVIS compatible. The TDFM [9300] *9000* transceiver shall include five (5) Type A, P25 Radio Frequency (RF) modules, installation kit, and necessary cabling. The TDFM [9300] *9000* transceiver shall have the capability of transmitting on each of the installed radio bands simultaneously. The base TDFM [9300] *9000* transceiver shall include one (1) each of the following modules:

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

1.61.2. 700/800 (764-870 MHz), VHF (136-174 MHz), UHF (380 – 520 MHz) ALL BAND operations module

1.61.3. 700/800 (764-870 MHz), VHF (136-174 MHz), UHF (380 –520 MHz) ALL BAND operations module

1.61.4. 700/800 (764-870 MHz), VHF (136-174 MHz), UHF (380 –520 MHz) ALL BAND operations module

1.61.5. 700/800 (764-870 MHz), VHF (136-174 MHz), UHF (380 –520 MHz) ALL BAND operations module

1.61.6. Each of the above listed Technisonic TDFM [9300] *9000* modules shall have the following options included:

· Legacy System Key Software

· Advanced System Key

· Enable All Band Operation

· TDMA Operation

· FCC Mandated Narrow Band Operation

· CAI for P25

· Smartzone Trunking

· Astro P25 Trunking

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

· Multikey

· Front panel programming capability for each module

1.62. Antennas required for the Technisonic TFM 30 and TDFM [9300] *9000* radio modules:

1.62.1. Four (4) Comant SAR Tri-Band Antennas each with the following frequency ranges:

· Frequency range: 136 - 174 MHz

· Frequency range: 403 - 520 MHz

· Frequency range: 764 – 870 MHz

1.62.2. Two (2) Foxtronics Tunable Antennas each with a frequency range of: 28 – 50 MHz

1.63. The law enforcement radio antenna installation shall allow for simultaneous transmission of any combination of installed law enforcement or aviation radio modules from any audio panel station without interference.

1.64. One (1) Technisonic RC-9000 Remote Radio Head for the Technisonic TDFM 9300 to be mounted in a location reachable from the pilot positions. The remote radio head shall have full functionality and control all installed modules on the installed TDFM [9300] *9000* radio.

SATELLITE PHONE/TRACKING REQUIREMENTS

1.65. One (1) Flightcell DZMx DZUS with Satellite and 4G Cell, SBD and Wi-Fi/blue tooth capable, to be mounted on the flight officer workstation. The Flightcell DZMx shall be capable of tracking via satellite and cellular 4G and shall include the following options:

1.65.1. One (1) Dual flat antenna L1 GPS/Iridium BNC/TNC White TSO Cert.

1.65.2. One (1) Blade Cell Antenna 700 – 2700 MHz

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

1.65.4. One (1) Flight Cell DZMx Bluetooth APP

1.65.5. One (1) Flight Cell DZMx Wi-Fi App

1.66. One (1) Flightcell DZP 05000 Remote Head to be mounted in a location reachable from the pilot positions.

COMMUNICATIONS EQUIPMENT REQUIREMENTS:

1.67. Two (2) Becker DVCS ACU6100 Digital Audio Panels and installation kits. One (1) mounted in the cockpit and one (1) at the flight officer workstation. The co-pilot position will be slaved to the cockpit audio panel and the cabin passenger positions will be slaved to the flight officer audio panel.

1.68. Two (2) Becker EP101 Audio Expansion Panels

1.69. One (1) Becker REU6100-3-(110) Remote Electronics Unit

1.70. One (1) Becker JB104-(000) Junction/Switch Box

1.71. All communication and navigation audio at the flight officer workstation shall be integrated with the Becker DVCS Digital Audio Panel System (to be discussed and agreed upon at the Pre-Work Conference). Two (2) rear passenger seats shall be slaved to the flight officer workstation Becker DVCS ACU6100 audio panel.

1.72. The pilot and co-pilot stations shall retain the ability to use the OEM aircraft audio panel for transmitting and receiving on the aviation frequencies. The ACU 6100 installed in the cockpit shall be usable by either the pilot or co-pilot when either of those positions are not utilizing the OEM audio panel. If the OEM audio panel is equipped with a third communication channel, the ACU 6100 shall be installed in a manner that allows for the ACU 6100 to be routed through the third channel. If the OEM avionics does not have a third audio channel, a switch type relay shall be installed in the cockpit which allows the pilot and/or co-pilot to utilize the ACU 6100. At all times, the pilot and co-pilot shall be able to monitor all channels of the ACU 6100.

1.73. The audio panels shall be installed so that the pilot station, co-pilot station, and flight officer workstation shall 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.

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

1.74.1. Pilot and/or co-pilot stations shall be able to transmit and receive on all installed law enforcement and aviation radios while the flight officer station is transmitting on any installed law enforcement or aviation radio.

1.75. The pilot station, co-pilot station, and flight officer workstation 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.

1.76. Intercom System (ICS):

1.76.1. An ICS shall be installed with Lemo “Bose style headset” compatible jacks located at each seat station in the maximum seating configuration.

1.76.2. The system shall provide ICS between front crew positions and the flight officer workstation with the aircraft battery switch on regardless of radio/mission master switch position.

1.76.3. The pilot station shall have the ability to switch between and isolate the pilot, co-pilot, flight officer workstation, and rear passenger ICS functions. A selector switch shall be installed to allow the pilot to isolate the crew from the non-crew passenger’s ICS. There shall be three (3) ICS isolate selections: “Pilot only”, “Crew only”, and “All”. The Pilot only selection will isolate the pilot from all other positions. The Crew only selection will isolate the pilot, co-pilot, and flight officer positions from the other cabin passenger positions.

1.77. 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.

1.78. All communications must be through the headsets/helmets.

1.79. Transmit switches for the radios and ICS shall be installed on both control yokes. The control yoke transmit switch shall have a toggle to allow for car to car and car to station transmissions on the CHP low band radio.

1.80. Transmit switches for the radios and ICS shall be installed on the flight officer workstation to include both a hand toggle switch mounted on the workstation and a foot activated switch that can be reached while seated at the flight officer workstation.

MISCELLANEOUS AIRCRAFT EQUIPMENT

1.81. Lighting: In addition to standard lighting provided on a basic equipped aircraft, the contractor shall meet the following additional lighting requirements:

1.81.1. Two (2) flight officer workstation map lights. The map lights shall be adjustable intensity, LED, green and white lights with the ability to display each color of light independently. The lights shall have a minimum 12-inch long “gooseneck” design. The location of the flight officer workstation lights shall be determined during the Pre-Work Conference.

1.81.2. LED Landing Light and Taxi Light

1.81.3. LED Navigation Lights

1.81.4. LED Anti-Collision Lights

1.81.5. Pulselight system

Note: If an LED light is available from the manufacturer, then it shall be supplied with the aircraft. If no LED is available from the manufacturer, then a High-intensity discharge (HID) light is acceptable.

1.82. Three (3) Cup Holders shall be mounted as follows: one (1) cup holder accessible from the flight officer workstation, one (1) cup holder accessible from the pilot station, and one (1) cup holder accessible from the co-pilot station.

1.83. Pitot Cover

1.84. Window covers to fit on the interior side of each window

1.85. Removable tinted window inserts for all windows aft of the pilot and co-pilot windows with a minimum visible light transmission (VLT) of 20% shall be provided for all aircraft side windows aft of the pilot seat. The tinted inserts shall provide enough glare reduction to read the flight officer workstation monitors in direct sunlight. The precise VLT percentage necessary to reduce glare on the flight officer workstation monitors to an acceptable level shall be determined at the pre-work conference.

1.86. Two (2) Rosen adjustable, tinted sun visors. One (1) mounted above the pilot station and one (1) mounted above the co-pilot station.

1.87. Gust lock for flight controls

1.88. Cargo nets for each cargo section

1.89. Two (2) Fire Extinguishers mounted as follows: one (1) reachable from the pilot and co-pilot stations and one (1) reachable from the flight officer workstation. The fire extinguishers shall be FAA approved for use in aircraft.

1.90. One (1) aviation certified USB power outlet with 2 ports capable of a minimum 2.4-amp power output shall be installed and located at or near the flight officer workstation.

1.91. One (1) aviation certified USB power outlet with 2 ports capable of a minimum 2.4-amp power output shall be installed and located at or near the pilot station.

1.92. One (1) Document holder to consist of a carbon fiber or metal type storage holder of sufficient size suitable to accommodate aviation charts, street maps, a Pilot Operating Handbook, and other documents. The map/chart holder shall be installed at a location accessible from the cockpit.

1.93. All aircraft shall be equipped with an OEM internal keyed lock on all access doors and if equipped with a pod the pod must be able to be locked with an integrated keyed lock. All keyed access shall be easily opened without special tools once unlocked.

1.94. Ten (10) exterior access lock keys

1.95. Aircraft registration “N” number shall start with the number “1” and end with the letters “HP”. For example: N148HP. The precise N number shall be coordinated with the project manager.

1.96. All loose equipment listed in this specification which is not attached to the aircraft shall be shipped by the primary contractor to the address in California specified by the project coordinator. This includes all manuals and documentation, extra aircraft seats, aircraft wheel jacks, pod jack, aircraft power supply/charger, downlink system, and the Lektro powertug. The costs for this shipping shall be included in the bid.

MANDATORY OPTIONS

1.97. One (1) Lektro AP8360 power tug with headlight and12/24/30 VDC GPU package to be delivered to the location in California designated by the project coordinator.

1.98. One (1) ground power unit (GPU) capable of providing power for running all of the electrical equipment on the ground as well as providing power to start the aircraft.

1.99. Turned out exhaust stack(s) to direct the exhaust away for the fuselage and camera equipment.

1.100. 300 AMP starter/generator.

1.101. TKS Ice Protection System.

1.102. One (1) LoJack stolen vehicle finding system.

1.102.1. LoJack PTC-3 FP Kit, part number 4105-0015-00

1.102.2. Required LoJack antennas, part number 200-0088-00

1.102.3. Antenna cabling and associated connectors shall be provided by the integration center.

1.102.4. The LoJack system shall be integrated into the Churchill ARS-700 as described in Section 7.1

1.103. One (1) Rho Theta RT-600LE direction finding system to include:

1.103.1. One (1) RT-8620 Direction Finding Unit.

1.103.2. One (1) RT-8621 Antenna Unit.

1.103.3. One (1) RT-8622 Display and Control Unit.

1.103.4. One (1) RT-8503 Connector Kit.

1.103.5. One (1) RT-28146 Interconnect Cable

Integration of the Rho Theta RT-600LE direction finding system shall be done at the direction of a Rho Theta representative who shall participate in the Pre-Work Conference. Onsite flight testing shall be conducted with participation of a RhoTheta specialist to ensure proper function with no radio interference.

1.104. One (1) Panasonic CF-20 Tough Book.

1.104.1. Public Sector Specific-Premium, Win 10 Pro, 8GB, 256GB SSD, Intel, a/b/g/n/ac, 4G LTE multi-Carrier, 8MP Webcam

1.104.2. Panasonic AC (100W) adapter

1.104.3. Panasonic 4th and 5th year public safety service bundle add-on. Must be purchased in conjunction with PS bundle base unit. Includes premier, protection plus, customer portal, and disk image management.

1.104.4. Panasonic CF-20 Tough Book Docking Station

1.104.5. Extra battery for CF-20

1.104.6. Enhanced rotating hand strap

1.104.7. The CF-20 Toughbook shall be integrated with the rest of the video and mapping system so that the Toughbook display can be displayed on either of the flight officer monitors. The CF-20 shall be securely mounted during flight within reach of the flight officer and shall be recharged from aircraft power while mounted. The CF-20 shall be detachable from mounting and power connection during flight so that it can be used elsewhere in the aircraft.

1.105. Six (6) Comm Innovations CIX200 series PTT switch/cable assemblies. The switch/cable assemblies shall include the following features:

1.105.1. PTT

1.105.2. Slide switch which shall allow for CHP radio car-to car communications in one direction and CHP car-to dispatch communications in the other direction.

1.105.3. Volume control

1.105.4. Cell phone port

1.105.5. U174/U Jack

1.105.6. Coiled cable 3 feet in length

1.106. Two (2) Nexus U94A/U PTT assemblies with 2 feet of coiled cable and U174/U jack and plug

1.107. Bose A2 active noise cancelling (ANR) headset with blue tooth. The headset shall include aircraft power connector kit. The headsets shall have the ability to be powered by aircraft power or a battery pack. The headset shall be equipped with U-174/U plugs.

1.108. U174/U to Dual Aviation Plug Adapter

1.109. One (1) Fujinon Techno-Stabi 14x40 Binocular and hard case

1.110. One (1) Churchill Navigation System ARS-GCS Ground Control Station

1.111. Two (2) Technisonic KVL 9000 Key Loader Cables and Two (2) PC 9000 Cables for the Technisonic TDFM 9300

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

1.113. One (1) Package of Orion Skyblazer II signal flares [four (4) flares per package]

1.114. One (1) 2-person deluxe 72-hour survival kit. The survival kit shall come fully contained in backpacks and contain at minimum the following equipment:

1.114.1. Eight (8) emergency water pouches

1.114.2. 40 servings of just add water meals

1.114.3. One (1) handcrank FM radio/LED flashlight with USB port allowing small electronics to be recharged via USB.

1.114.4. One (1) canteen cup and stove with 4 clean-burning, non-combustible fuel pouches and rechargeable, windproof electric ARC lighter

1.114.5. Two (2) Mylar thermal emergency blankets

1.114.6. 81-piece first aid kit

1.114.7. Emergency whistle

1.114.8. Compass

1.114.9. Survival knife with a paracord-550 wrapped sheath.

1.114.10. Two (2) rain ponchos and 2-pair of nitrile-coated work gloves.

1.114.11. One (1) 1-liter H2O level-2 advanced filtration water bottle that has been lab tested to remove 99.99% of giardia lamblia and Cryptosporidium.

1.115. One (1) L3 ESI 500 Electronic Standby Instrument System (ESIS) certified to take the place of the factory back up instruments. The unit shall come installed standard with altitude, attitude, slip/skid, vertical speed and aircraft track and have options available for the display of navigation information and synthetic vision, including terrain and obstacles. Options shall also include a coupled MAG-500 magnetometer.

1.116. One (1) Downlink System installed in the aircraft to allow downlink of live video from the aircraft to a ground-based receiver. The downlink system shall meet the following minimum equipment and performance requirements:

1.116.1. Aircraft Video Downlink Transmit System Requirements: The proposed aircraft video downlink RF transmitter shall be a [IMT Vislink HDX-1100 high-power airborne digital HD/SD video transmitter] *TROLL FTCA, DO-160 Certified Airbourne Multi-Protocol Transmitter-Receiver and Data Link Controller*. This aircraft transmit system will operate in the 6.425-6.525 GHz band and shall meet the following minimum requirements

· FCC Certified for Part 101, compliant with RTCA DO-160F.

· Capable of transmitting a high-definition (HD) video signal using MPEG-4/H.264 in Baseline Profile (BP), Main Profile (MP), and High Profile (HiP) standards.

· Video inputs including HD-SDI and SD-SDI.

· Conforms to the DVB-T 2K transmission standard in 8 MHz of occupied bandwidth.

· RF power output must be a minimum of +37dBm with a minimum MER of 23dB.

· Capable of encrypting the signal using standards based Bcrypt1and AES 128/256 schemes.

· Operates over a wide input voltage range of +18 – +32 VDC.

· Utilizes a touch sensitive front panel color LCD screen for local monitoring and control.

· Capable of storing at least nine (9) user defined preset configurations.

· Mounted in a single/standard ARINC aircraft tray.

1.116.2. Aircraft Video Downlink Antenna: The proposed aircraft video downlink transmit antenna array shall be an [IMT Vislink V-Link8] *TROLL SkyLine Mini S-LBand*, solid state, high-gain, fully integrated, directional antenna solution, that contains no internal moving parts and will operate in the 6.425-6.525 GHz band and shall meet the following minimum requirements:

· Array must be mounted to the aircraft utilizing a Meeker Aviation dove-tail mount.

· Provide both directional and full-time downlink coverage to support long-range and tactical downlink operations.

· Provide a minimum of [11] *14* dBi gain, vertical polarity on the directional array and a minimum of 5 dBi gain, right hand circular polarity, on the downlink array.

· Antenna beam width is to be 45° azimuth and 35° elevation, with automatic directional switching at the aircraft maneuvers.

· Capable of transmitting a high-definition (HD) video signal using MPEG-4/H.264 generated from the HDX-1100 aircraft transmit system.

· RF input to array shall be via a type-N female connector.

· DC voltage and control input to array shall be via a 19-pin circular type connector.

· GPS/INS input to array shall be via a type-sma female connector.

· Array shall operate over a wide input voltage range of +7 – +28 VDC

· *The Antenna shall have an Internal Inertial Navigation System (INS) that is GPS based*

1.116.3. Hand-Held Portable Video Downlink Receive System Requirements: The proposed aircraft video downlink hand-held portable receiver shall be an IMT Vislink MobilCMDR HD/SD integrated unit.

· This portable receive system will operate in the 6.425-6.525 GHz band shall meet the following minimum requirements:

· Capable of receiving a high-definition (HD) video signal using MPEG-4/H.264 standards.

· Outputs to include SDI and IP.

· Conforms to the DVB-T 2K transmission standard in 8 MHz of occupied bandwidth.

· Capable of decrypting the signal using standards based Bcrypt1and AES 128/256 schemes.

· Operates utilizing clip-on battery packs.

· Two (2) battery packs and one (1) charger are to be provided.

· Two (2) magnetic mount antenna bases with 12-foot coaxial cables are to be provided.

· One (1) 25-foot BNC male coaxial cable and one (1) SDI to HDMI converter are to be provided so that the hand-held unit can be connected to an external monitor that accepts an HDMI input.

· One (1) Pelican type transport case shall be provided.

NON-MANDATORY OPTIONS

1.117. Redbird CRV 208B--Full Motion, Fully Enclosed AATD configured with G1000 avionics (upgraded to NXI when available) with the following equipment: Custom CRV Throttle, Redbird Premium Dual Control Loading Yoke, Premium Redbird Dual Rudder Pedals, Redbird Horizon Pro - 260* Visuals Monitor Expansion, Navigator Tablet-Instructors Station, iOS Connection Tool Enabling EFB Capability, RealNAV-Worldwide Navigational Data Updates (4 per year) Provides SIDS, STARS (Required for WAAS). Shall include crating and material costs, shipping, and installation (provided by Redbird Services)

1.118. Redbird CRV 208B--Non-Motion, Fully Enclosed AATD configured with G1000 avionics (upgraded to NXI when available) with the following equipment: Custom CRV Throttle, Redbird Premium Dual Control Loading Yoke, Premium Redbird Dual Rudder Pedals, Redbird Horizon Pro - 260* Visuals Monitor Expansion, Navigator Tablet-Instructors Station, iOS Connection Tool Enabling EFB Capability, RealNAV-Worldwide Navigational Data Updates (4 per year) Provides SIDS, STARS (Required for WAAS). Shall include crating and material costs, shipping, and installation (provided by Redbird Services) image1.gif