ESBD_453398_1757704177636_03. Attachment B - Specifications.pdf

Attachment B Used Multi-Mission Fixed Wing Aircraft

Service and Equipment Specifications

1. General Description A. This RFP is to obtain one or more used Multi-Mission Aircraft for Texas A&M Forest

Service operations.

B. The Multi-Mission Aircraft will be used for All-Risk/All-Hazard incident support and may also be used for project, law enforcement, and administrative flights.

C. The aircraft shall be in excellent condition, no older than 5 years from the date of this RFP, and have less than 1500 airframe, engine and propeller hours and be delivered fully modified in standard airworthiness category.

D. All aircraft maintenance and special mission equipment integration records shall be provided to the Texas A&M Forest Service with delivery of the aircraft.

E. The aircraft shall be painted in a livery approved by Texas A&M Forest Service.

2. Aircraft Procurement and Testing A. The Seller shall be a company that sells upfitted aircraft as its primary business and is capable of delivering an aircraft as specified. Company must have been in continuous business for a period of 5-years. The Seller shall provide one (1) multi-mission fixed wing aircraft (MMA), meeting the enclosed specifications for performance and mission equipment. The Aircraft shall be delivered to Texas A&M Forest Service, ready to perform missions within 8 calendar months of the award.

B. Ground Test – The Seller shall:

1. Define and develop ground test plans for the Aircraft. The test plan shall include test procedures, events, and data points to complete engineering evaluation, initial acceptance of the Aircraft, EMI/EMC source victim tests, and system operational tests. The test plans shall address installed, modified, relocated or altered systems and must be approved by Texas A&M Forest Service.

2. Complete ground tests in accordance with the approved ground test plan and applicable Aircraft and/or vendor technical manual. The Seller shall record test data as defined in the approved test plan.

3. Provide all maintenance through successful completion of ground tests. The Seller shall provide all servicing consumables through successful completion of ground tests. The Seller shall document all maintenance and servicing actions in accordance with OEM procedures and manuals.

C. Flight Test – The Seller Shall:

1. Define/complete all flight test plans, procedures, and reports required to show compliance to applicable 14 CFR Part 23 regulations.

2. Complete all flight test events required to show compliance to applicable 14 CFR

Part 23 regulations.

3. Define all test events and data points necessary to demonstrate the operation of all mission system modifications.

4. Complete all flight test events as defined in the approved flight test plan to accomplish the testing of the mission systems.

5. Provide the primary flight crew for flight test activities.

6. Record all test event data points as defined in the approved test plan, and shall document the flight test results.

7. Provide all maintenance support through successful completion of all flight test activities. The Seller shall provide all servicing consumables, excluding fuel through successful completion of all flight test activities. The Seller shall document all maintenance and servicing actions in accordance with OEM procedures and manuals.

8. Provide daily reports to the Texas A&M Forest Service during flight testing. The Seller's standard format is acceptable.

2. Mission Application

A. The mission is to provide Aerial Supervision and Incident Awareness and Assessment (IAA) support using Medium or Low-Altitude Sensors during complex and emerging incident(s) in the wildland and urban interface. The resource provides enhanced situational awareness for the Air Tactical Group Supervisor (ATGS) and Incident Command personnel by producing real-time information. Missions may also include fire detection and incident mapping.

1. The minimum crew configuration for the mission is three (3) consisting of:

a. Pilot in Command (PIC)

b. Primary ATGS

c. Mission Sensor Operator (MSO)

d. “Optional” secondary ATGS, MSO or Instructor

2. ATGS seating positions shall be at the Second in Command (SIC) position. The secondary ATGS/Instructor/MSO position shall be on the right side of the aircraft, in a location that provides for minimal obstruction to the view outside the aircraft (downward looking), while sitting in an OEM seat with their shoulder beside the largest window(s) possible, their seatbelt fastened, with their back against the backrest and the ability to reach the unobstructed station avionics.

3. Aircraft shall be capable of being carded and FAA certified for:

a. Air Attack

b. Other: IAA

c. Fire Reconnaissance (Fire)

d. Passenger

e. Cargo Medical litter

3. Aircraft Requirements Texas A&M Forest Service requires one or more aircraft meeting or exceeding the following specifications. Aircraft shall be in excellent condition, but no older than 5-years from the date of this RFP, and have less than 1500 hours on the airframe, engine and propeller.:

A. Proposed single engine aircraft shall meet the following performance:

1. Turboprop Engine with minimum of 1000 SHP-Horsepower.

2. MTOW 10,000lb or greater

3. Aircraft shall have a power loading of not more than 10 pounds per horsepower.

4. Positive single engine rate of climb (1500 fpm or greater) when equipped for the contract and carrying a pilot weighing 240 lbs., two additional aircrew weighing 480 lbs., fuel for 4 hours plus a 30-minute reserve.

5. VFR/IFR certification for day and night operations

6. Pressurized cabin

7. Max cruise speed (FL220) of 250 KTAS or greater

B. Proposed multiengine, turboprop-powered aircraft shall meet the following performance requirements:

1. At least a 800 SHP-horsepower engine per side.

2. MTOW 12,000lb or greater

3. Aircraft shall have a power loading of not more than 10 pounds per horsepower.

4. Positive engine rate of climb (2000 fpm or greater) when equipped for the contract and carrying a pilot weighing 240 lbs., two additional aircrew weighing 480 lbs., fuel for 4 hours plus a 30-minute reserve.

5. VFR/IFR certification for day and night operations

6. Pressurized cabin

7. Max cruise speed (FL220) of 250 KTAS or greater

C. All equipment shall be installed and operable.

D. All aircraft shall be equipped with static pressure, altimeter, and automatic altitude reporting system.

E. All aircraft provided shall be operable, free of damage, and in good working order.

F. Aircraft systems and components shall be free of leaks, except within limitations specified by the manufacturer.

G. The aircraft interior shall be clean and neat. There shall be no un-repaired tears, rips, cracks, or other damage to the interior. All interior materials shall meet FAA standards.

H. The aircraft exterior finish, including the paint, shall be clean, neat, and in good condition (e.g., no severe fading or large areas of flaking or missing paint etc.). A paint livery mutually agreed upon between the seller and the Texas A&M Forest Service will be applied to the aircraft within three months of delivery, not to impact operational readiness. Any corrosion shall be within manufacturer or FAA acceptable limits.

I. All windows and windshields shall be clean and free of scratches, cracks, hazing, or distortion which limit mission visibility. Prior to acceptance, all temporary repair windows and windscreens shall be replaced. The forward and aft observer windows shall have either no tint, or grey tint of no less than 70 percent Luminous Transmittance (LT). All other colors of window tint are not acceptable.

J. Special Mission Aircraft Equipment

1. Equipment and lighting for night VFR operations in accordance with 14 CFR

135.159 and 14 CFR 135.161.

2. IFR aircraft must meet the equipment and lighting requirements of 14 CFR

135.163 and 14 CFR 135.165.

3. FAA approved high visibility, pulsating, forward facing, conspicuity lighting.

4. Fire extinguishers, as required by 14 CFR 135.155, shall be hand-held bottle(s), with a minimum of 2-B:C rating. Fire Extinguishers shall be maintained in accordance with current NFPA 10 standards and mounted with a quick release attachment accessible to the Flight crew while seated.

5. Flight Hour Meter. Each aircraft shall be equipped with a flight hour meter, installed in a location observable by the pilot and front seat observer while seated. The meter shall measure actual flight time from takeoff to landing in hours and tenths.

6. Cargo Restraint. The Aircraft shall have tie downs, net(s), or cargo straps meeting requirements of 14 CFR 135.87 to restrain cargo while in flight.

K. Seats, Seatbelts, and Shoulder Harnesses 1 Seat belts for all seats. One set of individual lap belts and shoulder harness of same type, design, and function for each passenger station/seat.

2. All Seats, Seat Belts, and Shoulder Harnesses for aircraft must either be an

OEM installation or STC.

3. Federal Aviation Regulations require that occupant restraints systems be replaced in aircraft manufactured after July 1, 1951; such systems shall conform to standards established by the FAA. These standards are contained in Technical Standard Order TSO-C22g. Restraint systems eligible for installation in an aircraft may be identified by the marking TSO-C22g or TSO- C114 on the webbing or by a military designation number, since military systems comply with the strength requirements of the TSO. Aircraft manufacturer installed restraint systems with part numbers are acceptable.

Each system shall be equipped with an approved metal-to-metal latching device.

4. Federal Aviation Regulations provide minimum inspection guidance, other than to state, that mildew and fraying may render the restraint system not airworthy, and that suspected webbing should be assessed for tensile strength.

The tensile strength requirement for a single person system is 525 pounds (most systems are rated at 1,500 pounds).

5. Unacceptable Condition Criteria:

Webbing Hardware Stitching TSO Tags Frayed (5%) Inoperable Broken Missing Torn Damaged Excessive Wear Illegible Crushed Corroded Missing Swollen Excessive Wear Creased Deteriorated

6. References:

14 CFR 91.205

14 CFR 21.607

AC 21-34

TSO-C22g

TSO-C114

7. Rear Seats. All installed rear seats (aft of the cockpit), including that of the instructor position, shall be capable of remaining occupied during all phases of flight, including take-off and landing. Equipment installed in front of rear seats shall not present a crash hazard to seated occupants.

5. Avionics for Special Mission Aircraft

A. Requirements:

1. A total of four VHF-AM Radios (COM 1, COM 2, COM 3, COM4), with one radio accessible from the rear MSO position

2. One of the VHF-AM Radios must be capable of monitoring the standby frequency

3. A total of four VHF-FM Radios with identical manufacturing (FM 1, FM 2, FM 3, FM4), with one radio accessible from the rear MSO position

4. VHF-FM Programing Ports.

5. Individual Volume Controls for all positions

6. Receive Audio Indicators

7. Two USB Charging Ports for the PIC

8. Two USB Charging Ports for the SIC/Observer

9. Two USB Charging Ports for the Aft Observer

6. Avionics Specifications

A. Radios Transmitters must not open squelch on, or interfere with, other AM or FM transceivers on the aircraft which are monitoring different frequencies. Transmit interlock functions must not be used with communication transceivers on special mission fire aircraft.

1. VHF-AM Radios

a. VHF-AM radios must be TSO approved aeronautical transceivers, permanently installed, and operate in the frequency band of 118.000 to

136.975 MHz with a minimum of 760 channels in 25 KHz increments.

Transceivers configured to operate in 8.33 KHz increments are not acceptable for aerial supervision aircraft. Transmitters must have a minimum of 5 Watts carrier output power.

2. VHF-FM Radios

a. VHF-FM radios must be approved aeronautical radios permanently installed in a location convenient to the PIC and SIC/observer. Aircraft performing fire missions must use P25 Digital radios with a GUARD capability constantly monitoring 168.625 MHz and have a tone of 110.9 on all GUARD transmissions. Scanning of GUARD is not acceptable.

Each radio must have two receivers (main & guard) and at least one transmitter. A list of currently approved FM radios can be found on the following website: https://www.nifc.gov/resources/NIICD/niicd-documents

3. Audio Systems

a. Intercom System (ICS). ICS must integrate with the aircraft audio control system and mix with selected receiver audio. An ICS volume control and a voice activated (VOX) capability must be provided for the PIC, SIC/observer, and all positions identified for the applicable mission category. Passenger volume adjustments must not affect the PIC. The PIC must have isolation capability.

4. Audio Control Systems

a. User Interface Audio controls must be labeled as COM-1, COM-2, FM-1, FM-2 etc. as appropriate with the corresponding transceiver labeled to match. The layout must be in the order of Com 1, Com 2, Com 3, FM 1, FM 2, FM 3 as applicable to the mission and arranged top to bottom, left to right, or forward to aft in ascending order. Controls for transmitter selection and independent receiver selection of all required radios must be provided. Crew positions must have radio Push-To-Talk (PTT) switches on their respective flight controls. Microphone jacks for all crewmembers https://www.nifc.gov/resources/NIICD/niicd-documents required by mission category must be wired with a key line allowing the use of a remote PTT switch. All required positions must have JJ-033 and JJ034 type microphone and headphone jacks separated by no more than 4 inches

b. General audio must be free of distortion, noise, or crosstalk. The system must be designed for use with 600 Ohm earphones and carbon equivalent, noise cancelling, boom type microphones. Sidetone must be provided for the user as well as for cross monitoring by all positions with ICS. Receiver audio must be automatically selected when the corresponding transmitter is selected. Receiver audio must be provided to each position provided with ICS.

5. Additional Requirements

a. All required crew member positions must have separate audio controllers installed in a location that provides the operator unobstructed access to the controls while seated. The PIC and SIC audio controllers must be identical.

Aft audio controllers must be of the same series as the PIC and SIC but do not require NAV audio.

b. Each audio controller must have a master radio volume control and controls for transmitter selection and independent receiver selection of all required radios. All required users must have the capability to simultaneously select and utilize a different transceiver. Sidetone must be provided for the user as well as for cross monitoring in all positions.

Receiver audio must be automatically selected when the corresponding transmitter is selected. Receiver audio must be provided to each position which requires ICS. Audio systems must not mute receiver or ICS audio during transmission.

c. Individual Volume Controls Each required audio controller must have separate controls to independently adjust headphone volume for each communications receiver. The individual volume controls must be a built-in, integral part of each audio controller. Toggle and push-on/push-off receiver selectors are acceptable. Push/pull style receiver selectors are unacceptable unless they use a lighted method to identify enabled receivers.

d. Receive Audio Indicators Indications must be provided for each required communications radio and activate when audio is received. Indications integral to the audio panel or a separate indicator panel are acceptable. When required for the SIC/observer, the indications must be in the user’s primary field of view.

When required for the instructor position, the indicators must be easily viewed by the user while seated.

B. Navigation Systems

1. Global Positioning Systems (GPS)

a. Aeronautical GPS

• Each required GPS must be TSO approved, permanently installed where both the PIC and SIC/observer can clearly view the display, use an approved external aircraft antenna, and be powered by the aircraft electrical system. The GPS must utilize the WGS-84 datum, reference coordinates in the DM (degrees/minutes/decimal minutes) format and have the ability to manually enter waypoints in flight. The GPS navigation database must be updated annually and cover the geographic areas where the aircraft will operate. The navigation database must be current for IFR aircraft.

b. Portable Aviation GPS

• Portable aviation GPS units (Garmin aera, Stratus 3 on Foreflight, or equivalent) are acceptable when an Aeronautical GPS is not specified. All components must be securely mounted via an approved installation and use the aircraft electrical system. A remote antenna (not attached to the unit) or external aviation GPS is required. The display must present information from an overhead perspective. The PIC must have a clear view of the display and unrestricted access to the controls. The GPS must meet the above datum, coordinate, and database requirements for an aeronautical GPS. Tablets must use an external aviation GPS displayed on compatible aviation software. Portable GPS units are not acceptable for aircraft performing IFR or NVG operations.

C. Surveillance Systems

1. Emergency Locator Transmitters (ELT)

Emergency locator transmitters must be certified to TSO-C126 or newer. ELTs must be automatic-fixed, installed in a conspicuous or marked location, and meet the requirements detailed in 14 CFR 91.207 (excluding section f). ELT mounts must use rigid attachments and meet the deflection requirements of RTCA/DO- 204.

2. Automated Flight Following systems (AFF) Automated flight following systems must be compatible with the government’s tracking program (aff.gov), utilize satellite communications, and use aircraft power via a dedicated circuit breaker. AFF must be functional in all phases of flight and in all geographic areas where the aircraft operates. The following additional requirements must be met.

a. A subscription service must be maintained through the equipment provider allowing position reporting via the Government AFF Program.

The reporting interval must be every two minutes while aircraft power is on.

b. AFF equipment must be registered with aff.gov providing all requested information. A username and password are required. Changes to equipment and registration information must be reported to aff.gov ensuring the program is current prior to aircraft use. Changes may take up to 5 business days to take effect. For assistance, email the AFF Help Desk at affadmin@firenet.gov.

3. Transponders

c. Transponder systems must meet the requirements of 14 CFR 91.215(a).

Part 135 aircraft must meet the “Mode S” requirements of 14 CFR 135.143(c). Transponder systems must be assessed and inspected every 24 calendar months as specified by 14 CFR 91.413.

4. Altimeter and Automatic Pressure Altitude Reporting Systems

a. Altimeter, static pressure, and automatic pressure altitude reporting systems must be installed and maintained in accordance with the IFR requirements of 14 CFR Part 91. These systems must be assessed and inspected every 24 calendar months as specified by 14 CFR 91.411.

5. Traffic Advisory Systems (TAS)

2. Traffic advisory systems must be TSO approved, use active interrogation, mailto:affadmin@firenet.gov graphically display traffic relative to the aircraft’s horizontal position, and provide alert audio to all required audio positions. Non flight crew members must have the ability to disable alert audio. The display must be within view of the PIC and SIC/observer. The system must provide coverage in all directions above and below the aircraft with a maximum range of at least 10 nautical miles. The display must allow range selection of 2 miles or less, unless the 2-mile display area has a diameter of 2.75 inches or larger. Traffic displays must permit aircraft IDs to be turned off.

6. Automatic Dependent Surveillance-Broadcast In (ADS-B In)

3. ADS-B In systems must receive both UAT and 1090ES and display TIS-

B traffic, with aircraft IDs, on an iPad via Foreflight using one of the methods below.

• A permanently installed ADS-B In receiver with the capability to wirelessly integrate with Foreflight. The wireless signal must be sufficient to provide uninterrupted connection from the SIC and Aft observer positions.

• Provisions to install a Stratus 3 receiver. Provisions must include an installed mount, remote GPS and ADS-B antennas providing coverage in all phases of flight with compatible connectors at the mount, and dedicated power wired to a compatible connector at the mount.

7. Automatic Dependent Surveillance – Broadcast Out (ADS-B Out)

4. ADS-B Out must broadcast the aircraft’s 3-dimensional position, heading and velocity and the aircraft’s registration number or actual call sign for all flights that are not law enforcement. Anonymous modes, privacy programs (i.e., FAA PIA), and ADS-B disabling may only be used when approved for law enforcement missions.

7. General Systems A. USB Charging Ports

1. USB charging ports must be TSO approved, capable of providing at least 2 amps of power to each port simultaneously with an output voltage of 5 VDC and permanently installed in a location convenient for the specified users.

B. Portable Electronic Device (PED) Tolerance

1. The aircraft must be certified as tolerant to portable electronic devices (PEDs), including transmitting PEDs, for all phases of flight in accordance with RTCA/DO-307. This must be accomplished via an STC equivalent to Liberty Partners STC11071SC with configuration LP-S001-B03. An appropriate supplement must be incorporated into the aircraft flight manual. Authorization for the use of electronic flight bags does not meet this requirement. The Government will use PEDs in accordance with the STC approval.

2. Tolerance of the following systems must be included:

a. Bluetooth

b. Cellular

c. Wi-Fi (802.11 b/g/n/ac)

d. VHF transceivers (136-174 MHz)

e. UHF transceivers (380-520 MHz, 764-870 MHz, and 902-928 MHz)

f. Wireless intercom adapters (1.92-1.93 GHz)

g. The seller must have documented procedures and training to clearly address:

• Situations when approved PEDs can and will not be used

• How and when PEDs must be secured or stowed

• PED modes of operation that can and will not be used

• How and when to inform passengers of the seller’s PED policies and procedures

• How to manage scenarios such as suspected or confirmed electromagnetic interference, PED unit or battery smoke or fire, or other scenarios

8. Avionics Installation and Maintenance Standards A. All avionics used in the build of the aircraft must comply with the manufacturer’s specifications and installation instructions, federal regulations, and the following requirements.

1. There must be no interference with required systems from any equipment installed in or on the aircraft.

2. Strict adherence to the guidelines in FAA AC 43.13-1B Chapter 11 “Aircraft Electrical Systems” and Chapter 12 “Aircraft Avionics Systems” as well as FAA AC 43.13-2B Chapter 1 “Structural Data”, Chapter 2 “Communication, Navigation and Emergency Locator Transmitter System Installations” and Chapter 3 “Antenna Installation” is required. 1202SA22R9102 A0002 NLFW MATOC Conformed Copy Amend 2 27 of 112 SECTION B TECHNICAL SPECIFICATIONS

3. All antennas must be FAA approved, have a Voltage Standing Wave Ratio (VSWR) less than 3.0 to 1 and be properly matched and polarized to their associated avionics system. Repairs to antennas and cracks exposing the antenna housing or element are not acceptable.

4. Labeling and marking of all avionics controls and equipment must be understandable, legible, and permanent. Electronic label marking is acceptable.

5. Avionics installations must not interfere with passenger safety, space, or comfort.

Avionics equipment must not be mounted under seats designed for energy attenuation. In all instances, the designated areas for collapse must be protected.

6. All avionics equipment must be included on the aircraft’s equipment list by model, nomenclature, weight, and arm.

7. Avionics systems must meet the performance specifications of FS/OAS A-24 Avionics Operational Test Standards.

8. Communications equipment must meet the performance specifications of FS/OAS A-30 Radio Interference Test Procedures. For a copy of all FS/OAS documents visit https://www.nifc.gov/resources/NIICD/niicd-documents.

9. Mission Equipment A. All mission-specific equipment used to meet this requirement must comply with the requirements listed below.

1. Sensor Specifications: Medium-Altitude HD Full Motion Video (FMV) Camera

System. Full Motion Video (FMV) gimbal, with Electrical-Optical (E/O), Short-wave infrared (SWIR), and Mid-Wave infrared (MWIR) cameras that meet the following:

a. Camera System (Gimble/Cameras) must weigh less than 120 lbs.

b. Sensor system dimensions shall be less than 16 inches in diameter.

c. One Digital, High-Definition Mid-Wave infrared (MWIR) camera

d. One Digital, High-Definition Short-Wave infrared (SWIR) camera

Indium Gallium Arsenide (In GaAs) based SWIR is preferred.

e. One High-Definition E/O Camera

f. Cameras must have zoom capability.

g. Gimbal must have 3 axis or better multi-axes stabilized.

h. Gimble must have vibration isolation.

i. System shall possess the capability to blend/fuse any band combination.

SWIR/MWIR, SWIR/EO, and MWIR/EO.

J. Systems will have a georeferencing laser rangefinder with a minimum effective response distance of 20 km.

k. Sensor must have a Target Illuminator compatible with ANVIS-9 Night

Vision Goggles (NVG).

l. Imager shall have an unobstructed continuous pan view from 10 degrees below the lowest horizontal plane of the aircraft (in-flight), and throughout downward pointing angle(s) to the earth's surface directly (perpendicular/nadir) below the aircraft at level (0) pitch, roll, and yaw.

m. FMV output must be recordable (Video) and contain geospatial KLV/COT metadata (i.e., Sensor points of interest, and four corners) to support the creation of geospatial products (imagery overlay/snapshots.)

n. All cameras must have a Nader GSD of 10 centimeters or less at 10,000

AGL.

10. Workstation/Interface Specifications and Functions

A. FMV Enhanced ATGS Fire Mission Workstation/Interface and Functions

1. ATGS/SIC Full Control

a. Sensor pointing via applicable hand control unit or touch screen interface available to control gimbal.

b. View and interaction with moving map, ability to created and attribution Fire IAA products including narration of videos. This position is NOT required to have to have direct access to mission sub-systems (Example, circuit breaker, UPC, switches, etc.)

c. The intent is to allow ATGS/SIC position to operate the system independently, if necessary, but more importantly support CRM between MSO and SIC position by splitting tasking (narration/ slewing camera)

d. ATGS/SIC position will not be filled by a qualified pilot. As such, offered mounting solution should be approved for a non-pilot operation while not obstructing pilot’s instrument visibility and may not be affixed to flight controls.

e. Onboard Wi-Fi and Network Management

f. All mission equipment shall be integrated in manner that does not impede ingress/egress during take-off and landing in the stowed position.

g. Position must have a minimum of one stowable or fix dedicated High

Definition (1080p); 13” diagonal, touch screen multi-function display or monitor which connects to the mission system’s control interfaces.

Mission display will be antiglare for day operations and capable of adjusting contrast and brightness for both day and night operations.

2. Rear MSO Workstation Workstation shall allow the MSO to be seated on in approved seating configuration for all phases of flight. Workstation/seating configuration shall account for and/or have reasonable ability to adjust for different sized operators to work comfortably in a natural seated/belted position.

a. Position must have a minimum of 2 dedicated High Definition (1080p) and a minimum of 15” diagonal, multi-function display or monitor.

Monitors which support touch screen, and the daisy chaining of additional monitor(s) are preferred. Laptop computers that meet the requirements above can be used in lieu of dedicated workstation monitors, but must be secured.

b. Mission display will be antiglare for day operations and capable of adjusting contrast and brightness for both day and night operations.

c. All mission equipment shall be integrated in manner that does not impede ingress/egress during take-off and landing in the stowed position. Mission Equipment such as unfolding secondary monitors, workstation circuit breaker/switches must have the ability to be stowed/manipulated/secured by a seated crewmember.

d. The MSO position shall have full control and access to sensor pointing, moving map, data attribution, imagery recording, and mission sub-components which require regular interaction to conduct the mission from their seated/belted position. (Example, circuit breaker, UPC, switches, etc.)

e. All software/user interface and process updates shall be applied to all instances of the system workstation.

3. Imagery/Mapping user interface:

a. The user interface shall provide a continuously visible moving map which displaces the aircraft location, sensor Point of Interest and sensor Field of View footprint (binding box and imagery/video overlay) over user selected base maps.

b. Sensor viewing and tasking payload via applicable hand control unit (HCU/mouse/keyboard) or touch screen interface available to control mapping system.

c. Interface shall allow user to toggle aircraft location, sensor Point of Interest and sensor Field of View footprint on and off.

d. Interface must have the ability to turn on and off a metadata overlay which contains a minimum of the Lat/long of aircraft location, lat/log of sensor Point of Interest, slant distance at Point of interest, sensor slant angle, aircraft heading, and sensor bearing metadata.

e. Required base maps are 1:150k and 1:24k scales, seamless, USGS topographical with transparent (hollow) background; best available imagery for Alaska and NAIP imagery for the continental United States (CONUS). 1. Base maps must be stored locally on the aircraft’s mission system. 2. Base maps shall have the ability to be toggled on and off and be displayed in the following order starting with the background(bottom):

NAIP/Imagery, User loaded GeoPDF incident Map, Sensor Imagery, and topo.

f. Interface shall support the recoding of the full mission systems active layers as present to the operator (I.E., base map, imagery/video overlay, sensor point of interest, metadata overlay) and/or the video/imagery only with and without metadata overlay.

g. User interface shall support the import, view, and modification of external vector and raster data stored in common GIS formats. Required formats:

GeoPDF, GeoTIFF, Shapefile, KML/KMZ.

h. User interface shall support the creation, modification, and export of polygons, points, and lines, in common GIS formats. Required formats:

Shapefile, KML/KMZ.

i. Interface shall have the following editing/ map tool functions. 1. Select, Copy, and Paste. 2. Reshape, and Merge polygons 3. Measure. Area (Acres), Distance (between to map point, and aircraft to location. (Feet/ miles) 4. Modify symbology 5. Search for location by latitude and longitude in DDM, DMS, UTM formats.

j. User interface shall support one-click collection and display of a lat/long in degrees decimal minutes (dd mm.mmm).

k. User interface shall support one-click calculation and display of acreage for any created or imported polygon feature.

l. Imagery is to be delivered as a single co-registered, orthorectified multiband mosaic, or several mosaics depending on fire size.

m. Imagery utilized to create any Geospatial data and products is to be saved in both raw (collected) and processed (classified/interpreted) format, and as an image mosaic in lossless compression format.

n. Files must be able to be compressed to facilitate being transmitted or uploaded while airborne without the need to land.

o. User interface shall support the submission, view, edit, modification, download of GIS data from ESRI REST survey/ feature services.

p. Mission software/hardware shall support the live and recorded distribution of FMV imagery/video, with metadata necessary to overlay stream/recoding in geospatial views such as Team Awareness KIT (TAK) and ArcMap. Formats must include SRT, RTP, and SRTP, RTS, UPD, Multicast. Resulting file shall show sensor points of interest and include 4 corner projections.

q. Interface shall support the creation, modification, of the following fire products: 1. Fire Perimeter 2. Narrated Video: 1-2 min in length, ATSG/MSO Narrated. 3. Imagery Overlay (Snapshot) 4. Real-time stream over LAN (Datalink) or Satcom.

r. The mission system suite shall support the use of a modern common bowser, such as chrome.

s. Mission System shall include Civilian Team Awareness KIT (CivTAK) or Civilian Window Team Awareness Kit (Civ WinTAK.) 1. TAK instance must be able to run and be viewed continuously without interfering with the Imagery/Mapping/Sensor user interface. 2. TAK instance shall have access to the FMV video/metadata feeds to support passive live video steaming over datalink to other ground Task users on the data link network.

11. Satcom A. Requirements

1. Provide operational coverage of the Continental US

2. Minimum data rate of 5 Mbps on up and 100 Mbps down.

3. Solution will have one or more 10/100Mbps (minimum). Ethernet connection(s) that are accessible within the cabin.

4. The connection data rate shall not degrade when using an ftp, sftp, or reverse ssh tunnel(s).

5. A fixed IP for the airborne platforms is preferred. If a fixed IP is not available, then a reverse ssh tunnel must be allowed.

12. Mission Equipment Installation and Maintenance Standards A. All sensor and mission equipment (including offered optional equipment) used to meet this contract must comply with the manufacturer’s specifications and installation instructions, federal regulations, and the following requirements.

B. There must be no interference with required systems from any equipment installed in or on the aircraft

C. Strict adherence to the guidelines in FAA AC 43.13-1B Chapter 11 “Aircraft Electrical Systems” and Chapter 12 “Aircraft Avionics Systems” as well as FAA AC 43.13-2B Chapter 1 “Structural Data”, Chapter 2 “Communication, Navigation and Emergency Locator Transmitter System Installations” and Chapter 3 “Antenna Installation” is required.

Sensors and mission equipment installation must be:

a. An OEM installation

b. STC

c. Approved for installation by an FAA Form 8110-3 with all DER supporting engineering substantiation documentation attached.

D. Labeling and marking of all sensor controls and equipment must be understandable, legible, and permanent. Electronic label marking is acceptable.

E. Sensor and mission equipment installations must not interfere with passenger safety, space, or comfort. Mission equipment must not be mounted under seats designed for energy attenuation. In all instances, the designated areas for collapse must be protected.

F. All sensor and mission equipment must be included on the aircraft’s equipment list by model, nomenclature, weight, and arm.

13. Training

A. For each new aircraft, complimentary aircraft training shall be provided for pilots and maintainers of the State’s choosing.