Attach_2_-_1520-3093r2.pdf

STATE OF CALIFORNIA

BID SPECIFICATION 1520-3093R2

HELICOPTER, TWIN ENGINE, FIREFIGHTING

CAL FIRE PAGE 1 OF 7 2/16/16

REQ-100411 HELICOPTER, TWIN ENGINE, FIREFIGHTING

1 SCOPE

This specification identifies the minimum performance, equipment, installation, and completion requirements for the purchase of twin-engine turbine helicopters, with a minimum of nine passenger seats, 500 gallons water carrying capacity with a full fuel load and a maximum gross weight of 10,000 to 19,000 pounds for the California Department of Forestry and Fire Protection (CAL FIRE). Unless otherwise indicated, references to the helicopter include the airframe, avionics, and specialized equipment described herein. The helicopter shall be a new, current production model, Federal Aviation Administration (FAA) type certificated or standard or transport category for airframe and engines. The helicopter shall not have sustained any damage as the result of accident and/or incident prior to acceptance by CAL FIRE.

2 APPLICABLE SPECIFICATIONS / STANDARDS / CODES

Specifications, standards and codes referenced in this document in effect on the opening of the ‘Invitation For Bid’, form a part of this specification.

3 HELICOPTER REQUIREMENTS

3.1 CERTIFICATIONS

3.1.1 Helicopter must be certificated for day and night visual flight rules.

3.1.2 Helicopter must be certificated for single pilot flight under Visual Flight Rules (VFR) operations and certificated for single or dual pilot flight under Instrument Flight Rules (IFR).

3.1.3 Helicopter certification must be FAA Standard or Transport category.

3.2 GENERAL

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

3.2.2 Twin Engine

3.2.3 Gross/Max Weight (Internally Loaded):

10,000 pounds (minimum) 19,000 pounds (maximum)

3.2.4 Useful Load: 5000 pounds (minimum)

3.2.5 Cargo Hook Weight: 4,800 pounds (minimum)

3.2.6 Airspeed at Full Weight: 135 knots at cruise power setting (minimum)

3.2.7 Pilot Stations (dual controls): 2

3.2.8 Passengers: 9 (minimum)

3.2.9 Ground Clearance: 17 inches (minimum) measured from a flat, level, surface to the lowest point of the helicopter fuselage, antenna, or required equipment

3.2.10 Allowable lateral slope landing: 8 degrees (minimum)

3.2.11 Allowable landing nose up / nose down slope: 7 degrees (minimum)

3.2.12 Hovering Out of Ground Effect (HOGE): 7000 feet Density Altitude (DA) at Gross Weight (minimum)

3.3 OPERATIONAL

3.3.1 Performance must be supported by manufacturer performance charts and demonstrated 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). Bidder shall be required to submit computations and supporting material in bid response. The bidder may be required to demonstrate the operational requirements listed in this specification through a flight demonstration.

1520-3093R2

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3.3.2 The helicopter must possess an on-board electronic means of tracking engine cycles and flight hours, or other engine parameters that are required to be tracked to determine when airworthiness limitations have been reached for engine components.

3.3.3 The helicopter must possess an on-board means of tracking fuel flow, and fuel time remaining.

3.3.4 Meets USFS interagency carding requirements. The USFS requirements for helicopters may be found at http://www.fs.fed.us/fire/contracting/helicopters_cwn/helicopter_contract_cwn.pdf

Reference Section C and Section C “Exhibits”

3.3.5 A service hour (Hobbs) meter shall be installed 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.

3.3.6 The helicopter must be capable of external load operations.

3.3.7 Main rotor brake must be installed.

3.3.8 Wire strike protection kit must be installed.

3.3.9 Inlet barrier filter system or equivalent engine inlet filtration system must be installed.

3.3.10 ALL appropriate engine equipment, if required, for operation in falling or blowing snow.

3.3.11 Chip detectors installed with quick disconnect plugs wherever possible.

3.3.12 The aircraft shall have an airframe mounted fuel filter, separate from any engine fuel filters, if available.

3.3.13 External engine oil filter (if available).

3.3.14 Equipment capable of tracking personnel locator beacons.

3.3.15 Cockpit switches, wiring and the proper connectors shall be included for:

Hoist Remote Hook Belly Hook Plastic Sphere Dispenser (PSD) Helitorch

This includes a cyclic thumb switch for water release, remote hook opening and helitorch or sphere dispersal and a separate cyclic switch, not thumb activated, for opening the belly hook.

Hoist controls per OEM STC or manufacturer’s installation instructions.

3.4 INTERIOR/CABIN

3.4.1 Pilot and Co-pilot seats shall have a four-point harness system and be of a crashworthy design (energy absorbing). Crashworthiness refers to those seat design characteristics that protect the occupant from injury or death during a crash event.

3.4.2 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.

3.4.3 Adjustable seat/cargo rails shall be installed in the floor (Brownline or equivalent) with a minimum of eight (8) hard point attachments for securing cargo.

3.4.4 Door shocks or opening struts for left and right front doors.

3.4.5 Aft cabin sliding doors on the left and right side.

3.4.6 Cabin heating system required.

3.4.7 Must have the ability to accommodate a minimum of two (2) six-foot long medical litters.

3.4.8 Utility purposed floor and side panels.

3.5 EXTERIOR

3.5.1 If equipped with skid landing gear, they must have full length skid protection on the bottom.

3.5.2 Removable snow skis or tundra pads (Dart Bear Paws or similar)

3.5.3 Complete set of aircraft covers and tie-downs.

3.5.4 Provide one (1) set of hydraulically operated maintenance ground handling wheels or equivalent, if appropriate.

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3.5.5 All available security devices (locks) offered by the manufacturer shall be included.

3.6 AVIONICS

3.6.1 Traffic Collision Avoidance System (TCAS).

3.6.2 Terrain Warning Alert System (TWAS)

3.6.3 Radar Altimeter

3.6.4 One (1) Churchill ARS-500C, or equivalent mapping system, shall be installed. The mapping system shall include at a minimum the following map system equipment and databases:

Keyboard Aeronautical Sectional and Terminal Area Charts for the Western United States Roads for the Western United States 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 California trail systems California Parcel Data

3.6.5 An avionics cooling fan system shall be installed as necessary to reduce the heat build-up of avionics equipment. It shall 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.

3.7 ELECTRICAL

3.7.1 All mission equipment must be compatible with the normal systems installed in the helicopter.

No hoist, helitorch, water tank, water bucket, remote hook or other well established helicopter external load device may cause unacceptable interference with avionics/navigation radios, auto-pilot, ICS system, lighting (including NVG) or instrumentation. 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.

3.7.2 Complete wiring diagrams must be supplied for all systems, electronic and hard copy.

3.7.3 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.

3.7.4 Wire harness service loops shall be provided for all mission equipment that are panel mounted or may be removed to suit particular missions. Service loop size and locations shall be reviewed and agreed upon at the Pre-work Conference.

3.7.5 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.

3.7.6 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.

3.7.7 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.

3.7.8 Automatic Flight Following with data transmission and reception shall be installed.

3.7.9 406 MHz Emergency Locating Transmitter with a cockpit located test/on/off switch installed

3.7.10 All lighting must be Night Vision Goggle (NVG) compatible.

3.7.11 One (1) power outlet that converts 28 volts DC to 12 volts DC and has a cigarette lighter style receptacle near the co-pilot’s seat.

3.7.12 One (1) 28 volt, 50 amp outlet located near the cargo hook.

3.7.13 One (1) 28 volt, 5 amp outlet located near the cargo hook.

3.7.14 Wiring diagrams and specs for the connectors for the external load devices and the AUX FM on the pages listed on the link. https://www.nifc.gov/NIICD/documents.html

3.7.15 Minimum of three (3) USB charging/data ports in cockpit.

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3.7.16 One (1) power outlet 28 volts, 10 amp DC located in the back cabin for operating PSD machine.

3.7.17 Flush-mounted, retractable landing/search light, with azimuth and elevation control, visible with NVGs.

3.7.18 Forward facing Light Emitting Diode (LED) pulse light system with a minimum of two lamps separated by a minimum distance of 3 feet and capable of flashing in unison or alternately.

3.7.19 Dual LED strobe light system. One (1) flash unit shall be mounted to the lower fuselage assembly, one (1) mounted on the top of the cabin or the top of the vertical fin (so it can be seen from above. The color and specific location shall be determined at the Pre-Work Conference.

3.7.20 Electronic load cell for monitoring weight on cargo hook

3.8 PAINT/COLOR SCHEME

3.8.1 The helicopter shall be custom high visibility, three color, paint manufacturer specified by CAL FIRE. A picture of current configuration is available upon request.

3.8.2 High visibility paint scheme on top surface of main rotor blades and on T/R blades.

3.8.3 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.

4 EQUIPMENT REQUIREMENTS

4.1 GENERAL

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

4.1.2 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.

4.2 HOIST

4.2.1 One (1) rescue hoist capable of carrying 600 pounds shall be installed.

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

4.2.3 The hoist must have a D-LOK hook, or equivalent.

4.2.4 The hoist must be able to withstand fleet angles of 15 degrees (30 degree cone) or greater for hoisting in heavy winds or ocean rescues.

4.2.5 Wall mount for the hoist manual cable cutter.

4.2.6 Sufficient hard points for securing hoist crewmembers harnesses that are capable of sustaining loads that may be caused by a falling crewmember.

4.3 TANK PROVISION

4.3.1 Aircraft shall be delivered with provisions for water tank installation and operation (Simplex Manufacturing or equivalent). This shall include the mechanical fasteners and anchor points needed as well as any electrical or hydraulic connections (see Section 5.4 for details on the water tank).

4.4 EXTERNAL LOAD PROVISIONS

4.4.1 Aircraft shall be delivered with provisions for the attachment of:

A Simplex 5400 Helitorch and include a 50 amp (minimum) breaker.

Remote hook for use at the end of a long line requiring a separate switch on the collective or cyclic as determined by post award consult.

The largest water bucket recommended by the manufacturer.

All items listed above shall be controlled by a mid-cyclic grip switch/button, thumb activated.

4.4.2 Belly hook preferably controlled by a button at the bottom of the cyclic stick (separate from the switch/button for the helitorch/remote hook/water bucket).

4.4.3 PSD 28 volt receptacle in rear compartment on a 10 amp circuit.

4.5 RADIO

4.5.1 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

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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.

4.5.2 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 shall be responsible to correct any radio frequency interference problems with any receiver(s) at no cost to the CAL FIRE. 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.

4.5.3 Two (2) FM VHF Hi-band 151 – 159 MHz FM tactical radios mounted on the pedestal, accessible to pilot and co-pilot, preferably by looking slightly down and forward Specific radio model to be discussed at the Pre-Work Conference.

4.5.4 One (1) auxiliary tactical radio outlet installed near the co-pilot seat per US Forest Service requirements. Wiring harness for selecting the use of a “handy talkie”, portable FM radio must be installed per USFS suggested diagram and be operable by selecting an AUX position on the Co-pilot audio panel. A separate antenna shall be installed for use with this connection with a BNC type connector.

4.5.5 An emergency bypass circuit shall be incorporated to allow one COM radio, ICS and CAL FIRE radio operation in the event of master radio relay failure.

4.5.6 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.

4.6 SATELLITE PHONE

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

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

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

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

4.6.2 One (1) Flightcell 9505 Iridium Satellite phone cradle with Iridium handset, or similar, installed in a location to be reviewed and agreed upon at the Pre- Work Conference.

4.7 COMMUNICATION EQUIPMENT

4.7.1 Three (3) Becker DVCS ACU6100-2-5300 or equivalent 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.

4.7.2 The audio panels shall accommodate a minimum of eight transceivers. The design and size of the accessory switching panel is to be determined during the Pre-Work conference.

4.7.3 One (1) Becker REU6100, or equivalent Remote Electronics Unit.

4.7.4 All communication and navigation audio shall be integrated with the Becker DVCS or equivalent Digital Audio Panel System to be reviewed and agreed upon at the Pre-Work Conference. All rear passenger seats shall be slaved to the overhead aft station audio panel. One (1) exterior mounted located near the refueling port, U174/U jacks shall be slaved to the copilot audio panel.

4.7.5 One (1) Power Sonix PSAIR 22A or equivalent Public Address/Siren System.

4.7.6 All passenger seats shall have ICS intercom system installed so passengers may plug in without location or interference issues, all positions, the exact number of positions shall be determined at the Pre-work Conference.

4.7.7 One (1) U-174/U compatible jack shall be located at each of the following locations:

Pilot station.

Copilot location.

Jump seat position if applicable

4.7.8 Exterior helmet/headset jack (may be ICS only) shall be located near the refueling port.

4.7.9 Quick-connect cannon plugs for each rear passenger seat, to be determined at post award conference. Brand of drop cord to be specified at post award conference.

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

4.7.11 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.

4.7.12 The audio panels shall be integrated to allow the communications to occur simultaneously without interference.

4.7.13 All stations shall be able to transmit and receive on all installed radios.

4.7.14 The pilot station, co-pilot station 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.

4.7.15 All communications must be through the headsets/helmets.

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

4.7.17 Transmit switches for the radios and ICS shall be installed to include foot activated switches that can be reached from both the pilot and copilot workstation.

4.7.18 Each aft cabin seat installed with Comm Innovations CIX200 series, or equivalent, Push-To-Talk (PTT) switch/cable assemblies. The switch/cable assemblies shall include the following features:

PTT

Slide switch with ICS, momentary, and lock positions Volume control U174/U Jack Coiled cable 3 ft. in length

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5 MANDATORY OPTIONS

5.1 PASSENGER SEATS (TROOP)

5.1.1 Troop seats shall allow the helicopter to accommodate the largest possible number of passengers with at least one shoulder harness (3-point). Seats shall be of a durable, utility type that allows for continuous operation with the doors open and capable of being removed by the crew with no or simple hand tools.

5.2 CLOSED CIRCUIT FUEL OPTION

5.2.1 Closed circuit refueling (CCR) is desired, using the Eaton P/N 64017 nozzle. The corresponding receiver shall be installed if available. Per MIL-N-52747F(AT), Type I.

5.3 AIR CONDITIONER

5.3.1 Manufacturer’s standard cabin air conditioning system

5.4 WATER TANK

5.4.1 Simplex Manufacturing or equivalent

5.4.2 Water Capacity: 500 gallons (minimum)

5.4.3 Ground Clearance: 6 inches (minimum) measured from closed tank door to the ground meeting the FAA certification requirements and guidelines.

5.4.4 If the water tank snorkel cannot be left installed during flight, then the snorkel must be stowed in a location that still allows a minimum 9 passengers and their gear in be in the cabin.

6 NON-MANDATORY OPTIONS

6.1 PASSENGER SEATS (COMFORT)

6.1.1 Comfort seats may allow the helicopter to accommodate fewer passengers than the troop seats, but with increased comfort of the passengers and come equipped with two shoulder harnesses (4-point, meaning one lap belt and two shoulder straps). Seats shall be of a durable, utility type that allows for continuous operation with the doors open and capable of being removed by the crew with no or simple hand tools.

6.2 SEARCH LIGHT PROVISION

6.2.1 All required provisions to the helicopter shall be included to allow the installation of the optional searchlight described below. This includes electrical connections, mounting points and all required fasteners (less search light). 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).

6.3 SEARCH LIGHT

6.3.1 An 800 Watt (minimum) searchlight with a peak illuminance at one (1) kilometer of 21 lux (minimum)

6.4 RADIO (800 MHZ)

6.4.1 700/800 MHz / UHF High Band Radio Module Primary Band: 700/800 MHz (764 to 870 MHz) Secondary Band: UHF High (450-520 MHz)