Attachment 1 - HATT Initial Requirements.pdf

Attachment 1: Helicopter Autorotational/ High Risk Testing Trainer (HATT), Initial Requirements

Parameter Threshold (Required) Objective (Desired)

General Cockpit Two-place / Dual controls

Environmental control with Heating/Ventilation/Air Conditioning

(HVAC) and /or removable doors in place of air condition

Rotor System Conventional Helicopter, Main rotor / tail rotor, tandem, or counter rotating.

Flight Control System Fully safe and effective unaugment controls or hydraulic boost controls with appropriate Stability Augmentation System/ Stability and Control

Augmentation System (SAS /SCAS) augmentation.

Trim system with FTR (Force Trim Release) switch and/or incremental trim.

Control system which provides for:

1. AFCS degradable to unaugment control in all flight regimes.

2. Auto Pilot with flight condition capture and hold modes.

External Stores / Cargo ballast

No

1. Ability to mount weapons or external fuel tanks.

2. Cargo passenger compartment suitable for ballast within the allowable Center of Gravity (CG) limits

Engine - Rotor Governing System / Engine Control

Easily manipulated throttles for throttle idle and power recovery autorotations.

Engine-rotor response to permit safe, effective, repeated power recovery to wave off throughout descent and flare while remaining within the established limits.

-Full Authority Digital Engine Control FADEC) control easily manipulated, safe, and effective for in flight recovery from idle to powered flight

Direct control of variable Nr for performance measurement testing.

-Capable of in-flight engine shutdown and restart

Ground servicing/turnaround

-No unique or aircraft-specific ground power or ground support equipment required

Hot-pit refueling with pilot hot-switch capability

Maintenance / Supply

Interim maintenance support from the OEM while we transition to either contracted or organic support (24 Month Period)

Parts and materials available for at least two of the first phase events and an option for parts available for the first major phase event.

Minimum of 95% material availability for the most commonly used components and order fulfillment within 1 week of placing the order

Performance Start / Shutdown/ Rotor

Engagement

- -45 knots any azimuth

-Rotor Brake Mission Length 2 Hours 2.5 Hours

Max. Airspeed, knots - 150 forward 45 lateral / aft

Hover / Vertical Climb Capability

Out of Ground Effect (OGE) hover on MIL STD hot day, Sea Level mid mission GW

OGE hover and 500 fpm (feet per minute) vertical climb, MIL STD hot day, Sea Level Maximum T/O GW nz +.5g to +2.0g 0 to 3.0g Aircraft Attitude and rate

Limits 30 deg pitch 60 deg roll

30 deg/ sec yaw rate

45 deg pitch 60 sustained transient 90 deg roll

60 deg/ sec yaw rate Autorotation Capable of safe and effective repeatable autorotation at idle to a prepared soft or hard surface at 15 knots ground speed or less without restriction on number of repetitions per flight hour or annually /

TBO (gear cycles or otherwise). Without restriction to gross weight.

Rotor inertia normalized by gross weight and disk loading to provide good autorotative characteristics to include a reasonable decay from throttle reduction. Effectiveness and behavior similar to OH-58, UH-1B, AH-1S.

Safety Seats / Crash Attenuation Five-point restraint harnesses for all occupants, or demonstrated equivalent survivability

-Jettison-able Cockpit Doors, meeting egress time requirements.

- Jettison-able / removable cabin egress port.

Self-sealing fuel cells

Threshold + Crash attenuating landing gear

Crash Attenuating Seats

Traffic Collision Avoidance Systems (TCAS)

TCAS w/ADS-B out (Automatic Dependent Surveillance-Broadcast)

TCAS with w/ ADS-B in/out.

Map display of ADS-B in traffic, weather, etc.- Altitude Warning Radar Altimeter with Low Height warning setting and visual and audible signal Enhanced Ground Proximity Warning System (EGWPS) DH / Altitude Alert settings integrated w/ PFD Flight Data Recorder Downloadable w/TSPI, Flight Control

Position, and Systems State data

Systems Navigation Suite Visual Flight Rules (VFR) with GPS, moving map and display of ground / inertial speed and track angle

Instrument Flight Rules (IFR) certified w/RNAV (to include LPV – Localizer Performance with Vertical Guidance)

Recording System Digital cockpit audio Digital cockpit audio & visual w/advanced debriefing capability

Instrumentation Data System Access to bus data or discrete signals (wherever they exist) for all cockpit indications, control positions, actuator positions, aircraft state information

(attitudes, rates, accelerations, etc.) Time Space and Position Information (TSPI), and navigation information.

Ability and information (ICDs etc.)

necessary to instrument flight test parameters where they are not available.

Integrated Flight Test Data System to capture, display and record threshold data.

Low Airspeed Data System displayed and recordable.

Operational “LAADS, HADS” type or flight test instrumentation.

Weapons / Sensor Systems - - Integrated Weapon aiming system through fixed HUD /

Reticle or Helmet Mounted Sight and Display (HMSD) System