Requirement Description / Qualifying Performance Requested Information IMR Certifiable The capability to achieve a FAA IMC Certification in accordance with 14 CFR Part 27 and 91. FAA Certification: ID Class (I, II, III, IV) If requirements not met identify current level of performance and shortfalls. Platform Dry (Empty) Weight Weight of the aircraft (lbs.) without fuel, internal or external payload, aircrew, capable of meeting requirements. Maximum fuel weight capacity required to meet requirements. Minimum Cruise Speed 120 Knot with internal crew of 4 souls (est. 250 lbs. / soul). Minimum and maximum Density Altitude (ft.) Minimum Endurance 2.5 hour at minimum cruise speed with available fuel reserves with internal crew of 4 souls (est. 250 lbs. / soul) for a total internal load of 1,000 lbs with full fuel tanks Minimum and maximum Density Altitude (ft.) Minimum Internal Crew / Payload Capable of carrying 4 souls (est. 250 lbs. / soul) for a total internal load of 1,000 lbs with full fuel tank. N/A Fuel Type Compatible with JP5, JP8 and commercial equivalents. N/A Refueling Capable of hot (i.e. engines / rotors turning), pressure (receiving fuel up to 55 p.s.i.), and gravity refueling. Identify aircraft refueling type attachment point and p.s.i. that fuel system can accommodate Capability to hoist load from ground to cabin. Provide maximum lift weight. Provide the cost of provision and modification. Provide any cycle limitations External Payload Capability to carry an external load. Provide maximum lift weight. Provide the cost of provision and modification. Rotor Brake Capability to slow/stop the rotation of the rotor drive system independently of the engine. N/A Blade Fold (for aircraft with 3 or more blades) capability to fold blades without maintenance actions(manual preferred). Duration (minutes), Required manpower (number of personnel). Any tooling that is required. Auto-rotations Capable of sustaining power recovery and full touchdown (zero ground speed to zero feet) auto-rotations to approved airfields and surfaces. Define structural limitations associated with auto-rotations. Identify maintenance actions required post auto-rotations.
Crashworthy data recorder Compliant with FAA Helicopter Regulations. Part 91.609. Identify if separate or integrated with ruggedized recorder. Engine and Aircraft Usage and Maintenance Data (HUMS) Compliant with existing FAA requirements Provide information on what options/systems are available. Removable or Sliding cabin doors on both sides With cabin exposed, capable of ~80 KIAS for forward flight. N/A Aircrew doors jettison capability Ability to jettison doors while on the ground during emergency situations. N/A Ergonomic adjustments Adjustable Seat and/or Pedals to accommodate pilots. Identify adjustment ranges of seat and pedals. Aircrew Cockpit Area Cockpit, seat, and seatbelt are compatible with (current) DoN Aviation Life Support System (ALSS) flight gear and NVD equipment. Provide a 3-view drawing of cockpit from eye point view (with dimensions or scaling). aircrew restraint system one aircrew member to move about the cabin safely while cabin is exposed with open or removed doors. aircrew restraint attachment points designed to withstand a limit load of 3,600 lbs. with an ultimate load of 5,400 lbs. The ultimate load of 5,400 lbs. is considered to be acting as follows: For sidewall mounted attachments (those mounted on vertical cabin frames, bulkheads or any structure along the cabin sidewalls) the ultimate load shall act through a 180° hemispherical cone of action oriented about the vertical axis. For cabin overhead mounted attachments the ultimate load acts through a 180° cone of action oriented about the aircraft lateral axis. N/A NVD HUD Interface Compatible with DOD, NVD HUD (monocle) Interface should be compliant with applicable FAA requirements If capability for interface exists. Please describe what can be displayed. Describe your platforms ability to meet the following parameters: