RFI 3 Attachment 1 _ UJTS Attributes.pdf

Aircrew anthropometric accommodation representative of fleet aircraft Two Seat aircraft with adjustable seat and/or pedals to accommodate pilots (both cockpits) and NFOs (Aft cockpit only) Zero-Zero Ejection Seat Unobstructed safe escape when fully outfitted with relevant equipment (Manual safe escape) NVIS compatible Cockpit Lighting (ANVS 9 compatibility)

Limit switch, button, and handles except for emergency functions. Shape and coloring/markings to allow for ease of recognition or identification Safety devices used to secure all safe critical components. All removable devices shall be tagged with streamers and must have securable storage somewhere in the aircraft Bird Strike Resistant Wind-screen(s) and canopy Environmental Control System to provide heating and cooling to both FWD and AFT cockpit Environmental Control system to pressurize the cockpit throughout the entire flight envelope

Operationally flown from either cockpit, including all actions necessary to safely recover the aircraft without relying on front seat occupant assistance Independent, mechanically or electronically linked controls for pitch, roll, and yaw Mechanically linked throttles for dual piloted flights Capable of executing NFO training in an aft cockpit that has been missionized or isolated (unable to influence aircraft flight [flight controls] or engines [throttles], Hands on Stick and Throttles [HOTAS] inputs continue to function) and includes dual hand-controllers

Measure of Effectiveness (MoE)

Human Engineering

Cockpit

UJTS Attributes

Front cockpit Heads Up Display (HUD), certified as Primary Flight Display, certified to fly instrument approaches without the use of a Heads Down Display Helmet Mounted Display (HMD) capable of being used simultaneously or individually in the FWD and AFT cockpit

AOA indexer symbology in HUD/HMD (E-Bracket and Digital Read out) AOA indexer on left side of glare shield in front and aft cockpit (similar to current USN CV aircraft) Workload efficient design of controls and displays to permit accomplishment of mission tasks on mission timeline

No line-of-sight obstruction from the front-cockpit pilot design eye point to the visual landing system and to the landing area including centerline during the on-turning portion of a constant AOA landing approach Configurable for single pilot operations Oxygen system capable of supporting 2 aircrew in all flight regimes w/ primary and emergency back-up Oxygen system monitoring capability for oxygen concentration and adequate flow Aircrew physiology monitoring system Aircrew ingress/egress capability to/from the cockpit for both normal and emergency ground operations Maintain fixed AoA approach targeting 3.25 degree glideslope while maintaining field of view during unflared landing Capable of 6-10 unflared landings per training event Capable of unflared landings for the service life of the aircraft

Field Emergency Arrestment Shall be able to maintain control and come to a stop within a minimum of a 6000 ft long by 100 ft wide runway during emergency scenarios All Weather capable Engine Anti-ice Day/Night/VFR/IFR certified

Fixed Angle of Attack Approach

Environment

Cockpit Configuration

Airframe

No structural damage or detrimental deformation at or below 115% of limit loads No structural rupture or collapse at or below 150% of limit load Tire loading allows for landing on a field arresting cable for all critical gross weights, CGs, and velocities

Tire loading allows for all mission and ground handling conditions (taxi, turns, takeoff, and landing) for all critical gross weights, CGs, and velocities

Tire design parameters for all critical gross weights, CGs, and velocities such that loads do not exceed aircraft structural or operational limits Show that tire plowing of the cable will not occur

Cable Assessment Verify the landing gear arrangement and servicing criteria prevents ground contact (e.g. servicing equipment, runway lights, arresting cables) at all external stores loading configurations, engine runs, and for flat gear, or flat tire, or flat gear and flat tire situations.

Aircraft start Capability of the Aircraft to start the engine(s) and essential systems with battery power and on board APU only, and with any combination of on board systems, ground power, and external air.

Cybersecurity Capable of complying with all Cybersecurity requirements per USN instruction (A/C and all SE)

Speed (Mach Number) >= .9 IMN / 450-500 KIAS

Sustained AOA >= 20 deg

Sustained "Buffet Free" Load Factor (G's) >= 3.1

Sustained Load Factor (G's) >= 6 Maximum Symmetric Load Factor (G's) >= 7.33 Operating Ceiling (feet Mean Sea Level) >= 41,000 Turn Rate >= 12 deg/sec Max Energy Addition >= 250 ft/sec

Wing and/or wingtip pylons for stores carriage per load out table (4) Optional / removable Wing station pylons

Suitability

Strength Survey

Tire Load and Deflection

Cable Rollover

External Stores

T/O Performance Able to takeoff from runways as short as 5,000 ft at defined weight (Pylons, 1x luggage pod, full fuel weight)

Critical Field Length (ft) 6,000 (5) Programmable Engine Controls (Full Authority Digital Engine Control, FADEC)

Ground and in-flight idle settings

Throttle with haptic identification of Off, IDLE, MIL and MAX (if equipped) Features to prevent inadvertent placement of throttle to Off Redundant, programmable Fly-by-wire Flight Controls Precision Landing Mode (PLM) capable

Fuel / Range / Endurance (Mission Profiles) Total fuel capacity with defined reserves to meet all planned CNATRA training sorties (6) Pilot selectable NWS Anti-skid braking system Parking Brake

Controlled Approach The aircraft shall be capable of maintaining 250 knots while in a 15 degree, flight idle descent for all gross weights and load outs.

Radar Altimeter (up to 5,000 ft) with Low Altitude Warning capabilities at programmable intervals with appropriate visual and auditory cues for airborne and landing environments

TACAN II

A/A TACAN capability

VOR/DME

Terrain Awareness and Warning System (TAWS)

INS/GPS

GPS Wide Area Augmentation System (WAAS) Auto-pilot: BARO (alt) hold, Course/HDG hold, Flight Path Hold Auto throttle: A/S hold (in-flight), On-speed hold (landing configuration), PLM compatible Traffic Collision Avoidance System (TCAS) II or equivalent Reduced Vertical Separation Minima (RVSM) capable with external fuel tank(s) and/or luggage pod

Air Vehicle Performance

Engine Controls

Flight Controls

Nose Wheel Steering (NWS)/Brakes

RVSM capable with multiple stores load outs according to the load out table (4)

RNAV1

Area Navigation-2 (RNAV-2) RNAV Terminal RNAV (GPS) Approaches RNAV (GPS) LPV approaches

RNP RNAV: RNP 1.0, 2.0, 0.3 and all ARINC 424 leg types for RNAV dep/arr Localizer Instrument Landing System (ILS) Category 1

Horizontal Situation indicator capable of showing Network information, Waypoint sequences, GPS/NAVAID with offset, planimetric course line, distance to course line and course deviation indicator

Fully integrated Flight management System (All flight pubs available on displays, digital maps, etc. with overlays and coverage in the continental US) Integrated weather information, external info on Electronic Knee Board

(EKB)

Integrated weather information, external info to displays Integrated digital cockpit control of associated navigation, communication, and identification functions External AOA Indexer Lights on the Nose landing Gear 406 MHz Emergency Location Transmitter (ELT) with GPS geolocation data that automatically activates during a crash Transponder with Mode 3/A, Mode C, and Mode S Automatic Dependent Surveillance-Broadcast (ADS-B) Out with selectable top level on/off capability ADS-B In Single, primary touch-screen display in both front and aft cockpit Integrated Digital Cockpit Display, HUD, and HMD

Single, digital standby flight instrument in the FWD and AFT cockpit

Instruments and Navigation

Identification

Integrated Augmented Reality HMD Integrated HMD connector compatible with HMD and AR HMD (single connector)

HD HUD camera to support HD recording and repeater display functions Declutter options for the HUD and HMD

High definition (HD) HUD repeater display function for FWD and AFT Cockpit Digital Flight Display Recorder High Resolution moving maps (multiple map types varying with screen scale) - (Data upload speed / mission card capable) Night Vision Device compatible (ANVS-9 spectra) Unclassified flight recording device with rapid off-board data transfer (5 min jet to debrief) Classified flight recording device with rapid off-board data transfer (5 min jet to debrief) Clear display of control and performance instruments

Same display functionality and information for front and aft cockpits with capability to know what pages are in use in the opposite cockpit Selection of instructor only pages by designated cockpit Designated instructor able to insert simulated system failure indications or errors to test procedures or recognize issues while on deck or in flight (nothing to impact SOF) Open architecture touchscreen display capable of user customizable displays Ability to configure and program HOTAS buttons Crash survivable memory and flight data recorder system

Delivery of aircraft carried A/G stores via manual, CCIP, or AUTO method (7) A/A and A/G Embedded Synthetic Training loaded via mission card

Augmented reality training system, loaded via mission card or other device, to support ground and inflight training requirements through AR HMD

Controls, Displays, Recorders

Avionics

Unclassified Embedded Synthetic Training capable of receiving preplanned mission load via mission card Synthetic training capable of Link Inject to Live training via a Live Virtual Constructive (LVC) system for both Pilot and NFOs Simulated Radar with A/A and A/G modes Radar Attack page capable of A/A and A/G views. Display real, simulated, or NET derived contacts. Movable Cursor with BRAA / Bullseye to contact information. Reverse GCI capable in A/A mode. Similar to current front line tactical A/C Simulated Electro Optical/Infra-red (EO/IR) EO/IR page capable of displaying simulated images Simulated Radar Warning Receiver (RWR) Simulated Electronic Support Measures (ESM) Simulated Electronic Warfare (EW) EW page in support of RWR/ESM/EW Simulated Electronic Attack (EA) employment Simulated Air-to-air (A/A) weapon employment (w/ necessary symbology on required pages and HUD/HMD) Simulated Gun with real-time gun sight, lead-angle optical sight, and Gun funnel mode Simulated Air-to-ground (A/G) weapon employment (w/ necessary symbology on required pages and HUD/HMD) Simulated manual, CCIP, or AUTO A/G employment options Ability to integrate actual or simulated sensor inputs and onboard cueing into simulated A/A or A/G weapons employment and validation. Data recorded to mission card for debrief.

Real time, in-flight simulated bomb scoring capability that records data to the mission card for debrief.

Automatic Ground Collision Avoidance System (Auto G-CAS) Unclassified mission planning and download/upload capability Capable of planning mission waypoints with offsets, navigation waypoints, and sequences Capable of planning mission scenarios, including virtual air or ground threats and targets, for use in flight

Mission Systems

Mission Planning System

Capable of mission planning pre-set radio frequencies, IFF information, and Network information Mission planning compatible with JMPS/NGMPS Capable of emergency jettison for stores and racks, with listed exclusions (not currently defined)

Capable of selecting appropriate store for employment (real or simulated) Capable of stores programming externally via avionics bay or in the cockpit while on the ground with weight on wheels

Capable of simulated stores programming on the ground or in flight (change stores/reload) via aircrew inputs using cockpit displays

Capable of supporting both real and simulated stores simultaneously Capable of simulating unclassified, generic A/G munitions Capable of simulating unclassified, generic A/A weapons Capable of simulating fleet representative A/G weapons Capable of simulating fleet representative A/A weapons

FCS page with visual depiction of flight control surfaces and/or aircraft with deflections and overall health (color and visual markings) Capability to show FCS system degradation of other FCS related systems and equipment Option to visualize and display stick and rudder pedal deflections on the FCS page

Direct Glide path Control Mode (PLM) with HOTAS and input settings/PVI Fuel display with discrete read out of total, internal, and/or external fuel (if equipped).

Fuel totalizer with bingo bug setting on persistent display Manual switch or Display controlled BINGO Bug with visual and audible alert.

Stores Management System (SMS)

Flight Control System (FCS)

Fuel System

Intra-System Electromagnetic Compatibility (E^3) Airframe shall be electromagnetically compatible within itself such that system and mission system performance requirements as detailed in the spec are met.

Fire detection Fire detection system that provides engine bay fire indication warnings, accessory bay fire indication warning, and bleed air lead indications 2 VHF/UHF dual-band radios that allow for monitoring of UHF/VHF Guard frequency simultaneously

Inter-Communication System (ICS) w/ voice-operated switch (VOX) Unclassified/CUI Training Network capable of hosting a virtual training system (A/A and A/G capable) Embedded, programmable flight cockpit digital simulation and training capability that can receive inputs via data link Incorporate diagnostics prognostics and design for the maintainer attributes to minimize maintenance, repairs, and cost per flight hour (Condition Based Maintenance) Capability to assess material condition on mission critical and life-limited components so that maintenance is based on actual and predicted material condition (CBM) Mean Time to Repair (MTTR) <= 5 hrs Direct Maintenance Man-hour per Flight hour (DMMH/FS) <= 8 hrs Aircraft Mean Turn-Around Time (AMTAT) <= 30 min (80% of the time) 60 min (20% of the time) Take-off to take-off time Cycle: 2.5 hours A/C MC rate >= 80%

Built in Test (BIT) Built in test capability to detect system malfunctions and isolate failures to the aircraft and mission systems. The false alarm per fight hour rate for critical sortie aborting false alarms shall be <= 1 per 1000 flight hours and for all false alarms shall be <= 1 per 100 flight hours

Routine Inspection Aircraft and mission systems shall have a routine inspection interval of not less than 10 hours, excluding daily and preflight inspections

Interoperability

Communications

Data-Link Interoperability

Supportability

Maintenance Concept

Minimum Fatigue Life (flight hours) 10,000

Landings 35,000

Size, Weight, Power and Cooling (SWaP-C) Incorporate SWaP-C for growth capability (RDR, RWR, EW add on capability plus buffer at a minimum)

(1) At level flight, 30,000 ft., maximum thrust and take-off weight less 40% useable fuel

(2) At level flight, 15,000 ft., maximum thrust and take-off weight less 40% useable fuel

(3) At level flight, 15,000 ft., maximum thrust and take-off weight less 40% useable fuel. MIL-STD-1797B defined acceptable regions of the flight envelope based on encountering intolerable buffet. AGARD AR-82 defines buffet levels.

(4) See Loadout Table Tab

(5) At Sea level, USN hot day 103 deg F (per MIL-STD-3013A), maximum thrust and takeoff weight to include 2 aircrew and full internal fuel. Critical field length is defined as the distance required to accelerate the aircraft to take-off speed, lose the engine and then stop the aircraft on the runway;

assuming 2.5 seconds for pilot recognition of engine failure and initiation of braking. Assume "take-off speed" is under V1.

(6) 10 CNATRA mission profiles in Appendix B

(7) Capable of employing a full load out of 12xMk76 or USN follow-on training munition

(8) 1,400 unflared landings per year, assuming 400 flight hours per year, and 10,000 hours of airframe fatigue life

Sustainment