Att_(2)_AHTS_PBS_v.1.83PR.pdf

PMA273-0013/Rev 1.83PR

PERFORMANCE BASED SPECIFICATION

FOR

TH-XX HELICOPTER SYSTEM

Prepared for and by:

DEPARTMENT OF THE NAVY

PROGRAM EXECUTIVE OFFICE PMA-273

NAVAL AIR SYSTEMS COMMAND

Patuxent River, MD 20670

11 JAN 2019

DISTRIBUTION STATEMENT A: Approved for public release: distribution unlimited.

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Prepared by:

AHTS Chief Engineer Date

Reviewed by:

PMA-273 Chief Engineer Date

SRB Concurrence:

APEO(E)/PEO(T) Date

APEO(L)/PEO(T) Date

APEO(T&E)/PEO(T) Date

Specification Approval:

PMA-273 Date

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Change History

The table below identifies all changes incorporated into the updated version of this document after initial approval.

Date Revision Change Description 03 Jan 19 1.8PR Basic document, including unclassified appendices A-X.

10 Jan 19 1.81PR AV-111 Updated to “should”, AV-141 deleted 11 Jan 19 1.82PR Typo in Verification Matrix AV-111 corrected

1.83PR Updated AV-080 in Verifaction Matrix to Match PBS Body Updated AV-128 to remove ambiguity Updated AV-33 to allow multiple refueling connections Updated AV-35 to align with choice of multiple connectors Added AV-145 to establish pressure refueling as desired Added MIL-PRF-52747F to Table 2.1

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Table of Contents

1 SCOPE

1.1 AHTS Overview

1.2 Application

1.3 Specification Terms

1.3.1 TH-XX System Terminology

1.3.1.1 "Shall"

1.3.1.2 “Should"

1.3.1.3 “Will”

1.3.1.4 TH-XX

2 DOCUMENTS

2.1 General

2.2 Government Documents

2.2.1 Specifications, Standards and Handbooks

2.2.2 Other Government Documents, Drawings and Publications

2.2.3 Non-Government Documents

2.3 Document Tiering

2.4 Document Order Of Precedence

3 TH-XX SYSTEM CAPABILITIES

3.1 Helicopter

3.1.1 Airworthiness Certification

3.1.2 Environmental Conditions Definitions

3.1.3 Temperature Range for Operation

3.1.4 Performance

3.1.4.1 Mission Takeoff Gross Weight (MTGW)

3.1.4.2 Mission Profiles

3.1.4.3 Cruise Airspeed

3.1.4.4 Cruise Airspeed Doors Removed

3.1.4.5 Altitude for Operation

3.1.4.6 HOGE

3.1.4.7 Endurance

3.1.4.8 Wind Limitations

3.1.5 Flying Qualities

3.1.6 Environmental Control System

3.1.7 Automatic Flight Control System (AFCS)

3.1.8 Power and Propulsion System

3.1.8.1 Main Rotor

3.1.8.2 Tail Rotor

3.1.8.3 Rotor Brake

3.1.8.4 Autorotation

3.1.8.5 Engine Particle Separator

3.1.8.6 Skid

3.1.8.7 Blade Fold

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3.1.8.8 Fuel System

3.1.8.9 Electric Power

3.1.9 Hoist and External Loading

3.1.10 Avionics Systems

3.1.10.1 Radio Configuration

3.1.10.2 Intercom Communication System (ICS)

3.1.10.3 Tactical Air Navigation (TACAN)

3.1.10.4 VHF Omni-directional Range (VOR) Navigation

3.1.10.5 Localizer

3.1.10.6 Instrument Landing System (ILS)

3.1.10.7 Global Positioning System (GPS) Receiver

3.1.10.8 Automatic Dependent Surveillance-Broadcast (ADS-B)

3.1.10.9 Mid-Air Collision Avoidance System

3.1.10.10 Crash Survivable Cockpit Voice and Flight Data Recorder

3.1.10.11 Emergency Locator Transmitter (ELT)

3.1.10.12 Helicopter Terrain Awareness and Warning System

3.1.10.13 Radar Altimeter

3.1.11 Flight Management System (FMS) Navigation

3.1.11.1 Mission Planning System

3.1.11.2 FMS

3.1.11.3 FMS Flight Path Steering

3.1.11.4 FMS Navigation Data

3.1.11.5 Aeronautical Database

3.1.11.6 Flight Plans Database

3.1.11.7 Reference Points/Waypoints Database

3.1.11.8 Digital Moving Map

3.1.11.9 Declutter

3.1.12 Human Factors

3.1.12.1 Personal Aircrew Gear

3.1.12.2 Cockpit Storage

3.1.12.3 Emergency Egress

3.1.12.4 Passenger Door

3.1.12.5 Night Vision Device (NVD) Compatibility

3.1.12.6 Seating

3.1.12.7 Seating Anthropometric Design

3.1.12.8 Seating Emergency Landing Conditions

3.1.12.9 Passenger Seating

3.1.12.10 Cockpit Controls and Displays

3.1.12.11 Exterior Lighting

3.1.13 External Appearance

3.2 Readiness

3.2.1 Support Equipment

3.2.2 Health and Usage Monitoring System (HUMS)

4 Verification

APPENDIX A: DEFINITIONS, ABBREVIATIONS AND ACRONYMS

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APPENDIX B: PROFILES

APPENDIX C: TH-XX USAGE SPECTRUM

Table of Figures Figure 3-1 Interior Temperature Limits

List of Tables Table 2-1 Government Documents - Specifications, Standards and Handbooks Table 2-2 Other Government Documents, Drawings and Publications Table 2-3 Non-Government Documents Table 3-1 Primary Fuel Table 3-2 Anthropometric Attributes (Threshold) Table 3-3 Anthropometric Attributes (Desired) Table 3-4 HUMS Data Elements

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1 SCOPE

This Performance Based Specification (PBS) establishes the overall system capabilities, functionality, and equipage for the commercial helicopter that is part of Advanced Helicopter Training System (AHTS). When necessary, to insure interface requirements to the other system elements of AHTS, detailed specifications are included. Section 3 of this document establishes the mandatory and preferred capabilities of the system. Section 4 contains the criteria used to verify Section 3 requirements. The Department of the Navy (DON) as represented by PMA-273 will be refered to as the “acquirer” throughout this document reflecting the standard acquirer and producer relationship as outlined in ISO/IEC 12207.

1.1 AHTS Overview

The mission of Chief of Naval Air Training (CNATRA) is to produce aviators and flight officers in sufficient quantity to support Naval Air Forces tasking. Since 1981, CNATRA has utilized a fleet of more than 100 TH-57B and TH-57C helicopters, six full-motion simulators, three cockpit procedure trainers, and classroom and computer-aided instruction to conduct undergraduate advanced rotary training at Naval Air Station Whiting Field. Since 2007, that training has included intermediate tiltrotor training for the United States Marine Corps . In the spring of 2018, the Navy began tiltrotor student training. Rotary and tiltrotor pilots now make up more than 50% of all Naval Aviators in the fleet with a Pilot Training Requirements (PTR) forecast of more than 600 rotary wing and tiltrotor pilots through 2040.

Aircraft training is conducted by military instructors with simulator and academic training by both military and civilian instructors. Student Naval Aviators (SNAs) are prepared for Fleet Naval Aviation through training in necessary skills, including, but not limited to, Contact, Energy Management, Basic and Radio Instruments, Navigation, Low-Level Navigation, Shipboard Operations, Search and Rescue, Formation Training, Confined Areas Landings, External Load Operations, and Night Vision Device training. The training missions require TH-XX helicopter to operate in varying environmental and climatic conditions throughout the continental United States with minimal mission degradation.

Key characteristics of AHTS include:

• A commercial helicopter that meets all requirements under Federal Aviation Regulations to operate under both Visual Flight Rules (VFR) and Instrument Flight Rules (IFR) within the United States national airspace system.

• The combination of the helicopter (TH-XX) and Ground Based Training System (GBTS) will train contact, basic and radio instruments, basic formation, and tactical events.

Tactical mission sets contained in the training curriculum include: Night Vision Devices, low level navigation, external load, search and rescue (SAR), hoist, shipboard operations and tactical formation.

• Ability to incorporate and integrate future capabilities (i.e. avionics upgrades, simulated weapons employment, etc.)

• Helicopter maintenance support, support equipment, and spares for the commercial helicopter.

1.2 Application

This specification, including its appendices and attachments, represents the technical requirements for the procurement of the TH-XX.

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1.3 Specification Terms

This PBS contains two broad categories of requirements. The first category represents the minimum acceptable capabilities, functionality, interfaces, or environmental factors. The specification items contained in this first category are represented by “shall” statements. The second category represents desired capabilities, functionality, or interfaces that may be incorporated at the discretion of the producer. These items will be represented as “should” statements in this specification.

1.3.1 TH-XX System Terminology

1.3.1.1 "Shall" Requirements throughout this document, inclusive of the appendices and annexes that are defined using "shall" statements, are considered to be mandatory, binding and require formal verification.

1.3.1.2 “Should" Statements using "should" express intent or desired functionality or performance above the minimum requirements for TH-XX.

1.3.1.3 “Will” Statements using "will" express intent, declaration of purpose on the part of the Government. In general, “will” statements express actions done on the part of the acquirer to evaluate the producers compliance with the PBS.

1.3.1.4 TH-XX

The term TH-XX refers to the TH-XX helicopter throughout this document.

2 DOCUMENTS

2.1 General

This PBS for the TH-XX System consists of this main body, Appendix A (Definitions), Appendix B (Mission Profiles), and Appendix C (Usage Spectrum).

2.2 Government Documents

2.2.1 Specifications, Standards and Handbooks

The following specifications, standards, and handbooks form a part of this specification to the extent specified herein. (Unless otherwise indicated, copies of federal and military specifications, standards, and handbooks are available from the Defense Logistics Agency (DLA) Data Services Online or ASSIST <http://www.assistca.dla.mil>.)

http://www.assistca.dla.mil/

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Table 2-1 Government Documents - Specifications, Standards and Handbooks

Document Number Government Specifications, Standards and Handbooks 14 CFR Part 27 Airworthiness Standards: Normal Category Rotorcraft 14 CFR Part 27-Appendix B Airworthiness Criteria For Helicopter Instrument Flight 14 CFR Part 29 Airworthiness Standards: Transport Category Rotorcraft 14 CFR Part 91 General Operating And Flight Rules ASTM-D1655 Aviation Turbine Fuels FAA AC-20-146A Methodology for Dynamic Seat Certifcation by Analysis for Use in Parts 23, 25, 27, and 29 Airplanes and Rotorcraft FAA AC 20-153B Acceptance of Aeronautical Data Processes and Associated Databases FAA HF-STD-001 Human Factor Design Standard FAA SAFO 10020 14 CFR, parts 91, 133, and 137 and hot fueling/loading FAA SAIB NE-14-28 Engine Fuel – NATO Grade F-24 Jet Fuel MIL-DTL-5624W Detail Specification Turbine Fuel, Aviation, Grades JP-4 And JP-5 MIL-DTL-83133J Detail Specification Turbine Fuel, Aviation, Kerosene Type, JP-8 (NATO F-

34), NATO F-35, And JP-8+100 (NATO F-37) MIL-PRF-52747F Nozzle Assembly, Closed-Circuit Refueling, Standard And Arctic Service MIL-STD-2161 Paint Schemes and Exterior Markings for U.S. Navy and Marine Corps

Aircraft RTCA DO-200B Standards for Processing Aeronautical Data RTCA DO-309 Minimum Operational Performance Stadards (MOPS) for Helicopter Terrain

Awareness and Warning System (HTAWS) Airborne Equipment TSO-C114 Torso Restraint Systems

2.2.2 Other Government Documents, Drawings and Publications

The following other Government documents, drawings, and publications form a part of this specification to the extent specified herein. Unless otherwise specified, the issues are those in effect on the date of the solicitation. Copies of specifications, standards, handbooks, drawings, publications, and Government documents required by contractors in connection with specific acquisition functions should be obtained from the PMA-273 Program Office.

Table 2-2 Other Government Documents, Drawings and Publications

Document Number Other Government Documents, Drawings and Publications NAVAIRINST 13100.16 Designating And Naming Defense Military Aerospace Vehicles OPNAVINST 13210.1B Naval Aviation Policy For Aircraft Avionics Safety Systems

2.2.3 Non-Government Documents

The following document(s) of the exact revision level listed below form a part of this document to the extent specified herein. Non-Government standards and other publications are normally available from the organizations that prepare or distribute the documents. These documents also may be available on the Internet, or accessible in or through libraries or other informational services.

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Table 2-3 Non-Government Documents

Document Number Non-Government Documents SAE-AS5877 Nozzle, Aircraft Pressure Refueling SAE-AS8043B Restraint Systems for Civil Aircraft SAE-AS35061A Connector, Receptacle External Electric Power, Aircraft, 28Volt DC

Operating Power

2.3 Document Tiering

This PBS, including its appendices, is a first-tier document and is contractually binding. All documents directly referenced in this first-tier specification are second tier documents and are applicable to the extent specified. All documents directly referenced in second-or lower-tier documents are for guidance only, unless otherwise directed by the Government.

2.4 Document Order Of Precedence

In the event of a conflict between the text of this specification and the references cited herein, the text of this specification takes precedence. Nothing in this specification, however, supersedes applicable laws and regulations.

3 TH-XX SYSTEM CAPABILITIES

3.1 Helicopter

3.1.1 Airworthiness Certification

[AV-001] The TH-XX shall have a current Federal Aviation Administration (FAA) Type Certification

(TC) that authorizes single-pilot and dual-pilot operations under day and night VFR 14 Code of Federal Regulations (CFR) Part 27 or Part 29 and 14 CFR Part 91.

[AV-002] The TH-XX shall have a current FAA TC or STC that authorizes single-pilot IFR operations in accordance with 14 CFR Part 27, 14 CFR Part 27-Appendix B, and 14 CFR Part 91.

[AV-004] The TH-XX shall implement all requirements in this PBS in a single aircraft configuration to be implemented in a single military Type/Model/Series (T/M/S) in accordance with

NAVAIRINST 13100.16.

3.1.2 Environmental Conditions Definitions

[AV-005] The following definitions shall apply throughout this specification:

Cold Day – Temperature -40ºF (-40ºC) at 10,000 feet PA Standard Day – Temperature 59ºF (15ºC) at 0 feet PA Operational Day – Temperature 95ºF (35ºC) at 3,000 feet PA High Hot Day – Temperature 95ºF (35ºC) at 6,000 feet PA

3.1.3 Temperature Range for Operation

[AV-006] The TH-XX shall be capable of continuous operations in temperatures ranging from -2ºF (-19ºC) to +102ºF (39ºC) OAT at NAS Whiting Fld, FL.

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3.1.4 Performance

3.1.4.1 Mission Takeoff Gross Weight (MTGW)

[AV-007] The TH-XX MTGW shall be calculated by adding Helicopter Basic Weight, Mission Fuel, Mission Equipment Weight, Reserve Fuel, and Mission Payload.

3.1.4.2 Mission Profiles

[AV-008] The TH-XX shall be capable of executing APPENDIX B profiles in Operational Day environmental conditions at or below MTGW with ECS-ON.

3.1.4.3 Cruise Airspeed

[AV-009] The TH-XX shall be capable of 115 KTAS cruise airspeed in accordance with the Appendix B profiles in Operational Day environmental conditions with ECS-ON.

3.1.4.4 Cruise Airspeed Doors Removed

[AV-010] The TH-XX shall be capable of 80 KTAS cruise airspeed with the doors opened or removed in

Operational Day environmental conditions.

3.1.4.5 Altitude for Operation

[AV-011] The TH-XX shall have a Service Ceiling greater than or equal to 15,000 feet MSL.

3.1.4.6 HOGE

[AV-012] The TH-XX shall be capable of Hover Out of Ground Effect (HOGE) at MTGW at 5500 feet

MSL in Standard Day environmental conditions with ECS-ON.

3.1.4.7 Endurance

[AV-013] The TH-XX shall be capable of 2 hour and 30 minutes endurance from takeoff at MTGW to landing in Operational Day environmental conditions with Mission Fuel equal to Endurance Fuel; and Reserve Fuel available over destination.

3.1.4.8 Wind Limitations

[AV-014] The TH-XX shall be capable of flight operations in steady state winds of 40 kts to include rotor engagement, taxi, take-off, and landing. It is understood that re-orienting the helicopter into the wind for rotor engagement, takeoff and landing may be necessary to remain within helicopter operating parameters and limitations.

3.1.5 Flying Qualities

[AV-017] All flying quality requirements shall apply to both pilot stations.

[AV-018] The TH-XX shall incorporate independent, mechanically linked controls.

3.1.6 Environmental Control System

[AV-134] The TH-XX shall have an Environmental Control System (ECS).

[AV-019] The TH-XX ECS should maintain the cockpit and cabin temperature ranges identified in

Figure 3-1.

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Figure 3-1 Interior Temperature Limits

3.1.7 Automatic Flight Control System (AFCS)

[AV-020] The TH-XX AFCS controls shall be accessible from either pilot position.

[AV-021] The TH-XX AFCS should provide the capability for a coupled approach to hover, coupled hover, coupled departure from hover, and a pilot-initiated coupled Go-Around mode.

[AV-022] The TH-XX AFCS should provide the capability to capture and hold attitude, altitude, airspeed, course and heading.

3.1.8 Power and Propulsion System

3.1.8.1 Main Rotor

[AV-023] The TH-XX main rotor shall rotate counter-clockwise.

3.1.8.2 Tail Rotor

[AV-024] The TH-XX shall have a tail rotor.

3.1.8.3 Rotor Brake

[AV-025] The TH-XX rotor brake shall be capable of completely stopping the rotor.

[AV-026] The TH-XX rotor brake should stop the rotor within 60 seconds of securing all engines.

3.1.8.4 Autorotation

[AV-027] The TH-XX shall be capable of conducting power recovery autorotations with engines disengaged from the rotor system.

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[AV-028] The TH-XX should be capable of conducting practice autorotations with engines disengaged from the rotor system to ground landing.

3.1.8.5 Engine Particle Separator

[AV-029] The TH-XX shall have an engine particle separator or inlet barrier filter.

3.1.8.6 Skid

[AV-135] The TH-XX shall have a skid landing gear.

3.1.8.7 Blade Fold

[AV-030] The TH-XX shall have blade fold.

[AV-031] The TH-XX should have blade fold without the removal of any blades.

3.1.8.8 Fuel System

3.1.8.8.1 Crash Resistance

[AV-136] The TH-XX shall comply with requirements under paragraphs (1), (2), (3), (5), and (6) of section 27.952(a), section 27.952(c), section 27.952(f), section 27.952(g), section 27.963(g) (but allowing for a minimum puncture force of 250 pounds if successfully drop tested in-structure), and section 27.975(b) of Title 14, Code of Federal Regulations.

3.1.8.8.2 Fuels

[AV-032] The TH-XX shall be authorized to use all Primary Fuels specified in Table 3-1.

Table 3-1 Primary Fuel

US MIL

CODE

NATO

CODE

US MILITARY

SPECIFICATION

COMMERCIAL

DESIGNATION

(SPECIFICATION)

BRITISH

DESIGNATION

(SPECIFICATION)

WT

(lbs/gal)

JP-5 F-44 MIL-DTL-5624

NONE

DEF STAN 91-86

(AVCAT/FSII) 6.8

JP-8 F-34 MIL-DTL-83133 DEF STAN 91-87

(AVTUR/FSII) 6.7

NONE F-35 MIL-DTL-83133

JET A-1

(ASTM-D1655)

DEF STAN 91-91

(AVTUR)

6.7

NONE F-24

JET A

(ASTM-D1655)

(SAIB NE-14-28)

6.7

3.1.8.8.3 Refueling Interfaces

[AV-033] The TH-XX fuel subsystem shall allow the helicopter to be refueled by a SAE-AS5877, Type

D-1, locking pressure refueling nozzle or MIL-PRF-52747F, Closed Circuit Refueling (CCR) nozzle.

[AV-034] The TH-XX shall be capable of hot refueling during ground operations with the engines operating and rotors turning in accordance with FAA SAFO 10020.

[AV-035] The TH-XX shall be capable of refueling and gravity refueling during ground operations with engines off, rotors stationary, and no external power supplied.

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[AV-145] The TH-XX should be capable of pressure refueling during ground operations with engines off, rotors stationary, and no external power supplied.

3.1.8.8.4 Defueling Interfaces

[AV-036] The TH-XX shall have the ability to gravity defuel the main tanks on the ground and/or suction defuel the main tanks through the helicopter's refueling adapter designed to 7 psi suction pressure.

3.1.8.9 Electric Power

[AV-037] The TH-XX shall accept external power.

[AV-039] The TH-XX external power monitor function shall protect in accordance with FAA 14 CFR Part

27.1357.

[AV-040] The TH-XX external power receptacle shall be in accordance with SAE-AS35061A.

3.1.9 Hoist and External Loading

[AV-043] The TH-XX shall be capable of hoist operations.

[AV-044] The TH-XX shall be capable of external load operation.

[AV-045] The TH-XX shall provide a hard point to restraint mobile aircrew located in the cabin capable of withstanding the structural component design criteria of FAA 14 CFR Part 27 for 500 lb nominal load (8.5 kN (1900 lb) ultimate load).

3.1.10 Avionics Systems

[AV-046] The TH-XX shall have approved TC, STC, or Technical Standard Order (TSO) for all installed avionics equipment.

[AV-047] The TH-XX avionics equipment controls shall be accessible from either pilot position.

[AV-048] The TH-XX cockpit shall provide an integrated crew vehicle interface through independent, digital cockpit Multi-Function Displays (MFD).

[AV-049] The TH-XX avionics equipment output shall be within the Field of View (FOV) for both pilots.

[AV-050] The control and indications of TH-XX avionics equipment should be integrated in pilot displays.

3.1.10.1 Radio Configuration

[AV-051] The TH-XX shall be equipped with two independent radios.

[AV-137] The TH-XX minimum radio configuration shall be one VHF radio and one independent UHF radio.

[AV-138] As a minimum, each independent TH-XX radio shall have a dedicated antenna.

3.1.10.1.1 Very High Frequency (VHF) Radio

[AV-052] The TH-XX shall be equipped with a VHF radio using 8.33 kHz channel spacing with VHF guard frequency capability.

3.1.10.1.2 Ultra High Frequency (UHF) Radio

[AV-053] The TH-XX shall be equipped with a UHF radio using 50 kHz or less channel spacing with UHF guard capability.

3.1.10.1.3 Dual Band Radios

[AV-054] The TH-XX should provide redundant dual band radios.

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3.1.10.2 Intercom Communication System (ICS)

[AV-139] The TH-XX ICS shall be available to pilot and passenger stations.

3.1.10.3 Tactical Air Navigation (TACAN)

[AV-055] The TH-XX shall be equipped with a TACAN.

[AV-056] The TH-XX shall be capable of executing TACAN approaches.

[AV-057] The TH-XX shall have TACAN air-to-air ranging capability.

3.1.10.4 VHF Omni-directional Range (VOR) Navigation

[AV-058] The TH-XX shall be equipped with a VOR.

[AV-059] The TH-XX shall be capable of executing VOR approaches.

[AV-060] The TH-XX shall be capable of enroute navigation utilizing VOR-DME radio navigation aids.

[AV-061] The TH-XX shall be capable of executing VOR-DME approaches.

3.1.10.5 Localizer

[AV-062] The TH-XX shall be capable of executing localizer (LOC) approaches.

3.1.10.6 Instrument Landing System (ILS)

[AV-063] The TH-XX shall be capable of executing ILS approaches in accordance with FAA standards for

Category (CAT) I Weather Minima.

3.1.10.7 Global Positioning System (GPS) Receiver

[AV-064] The TH-XX shall be equipped with a GPS WAAS reciever.

[AV-065] The TH-XX shall be capable of executing GPS approaches to Localizer Performance with

Vertical Guidance (LPV) minima.

3.1.10.8 Automatic Dependent Surveillance-Broadcast (ADS-B)

[AV-066] The TH-XX shall be equipped with Automatic Dependent Surveillance Broadcast (ADS-B) Out and In capability for traffic information.

[AV-067] The TH-XX ADS-B shall allow the user to mute traffic alerts.

3.1.10.9 Mid-Air Collision Avoidance System

[AV-068] The TH-XX shall be equipped with a midair collision avoidance capability which provides cues and warning to aircrew of conflicting air traffic.

[AV-069] The collision avoidance system shall allow the user to mute traffic alerts.

3.1.10.10 Crash Survivable Cockpit Voice and Flight Data Recorder [AV-070] The TH-XX shall be equipped with a crash survivable cockpit voice and flight data recorder system.

3.1.10.11 Emergency Locator Transmitter (ELT)

[AV-071] The TH-XX shall be equipped with a 406 MHz ELT integrated with GPS geolocation data.

3.1.10.12 Helicopter Terrain Awareness and Warning System

[AV-072] The TH-XX shall be equipped with a Helicopter Terrain Awareness and Warning System

(HTAWS) for Controlled Flight Into Terrain (CFIT) avoidance.

[AV-073] The TH-XX HTAWS shall reduce nuisance alerts in accordance with RTCA DO-309.

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3.1.10.13 Radar Altimeter

[AV-074] The TH-XX shall be equipped with a radar altimeter that is functional and displays from zero to a minimum of 2000 ft AGL.

3.1.11 Flight Management System (FMS) Navigation

3.1.11.1 Mission Planning System

[AV-075] The TH-XX System shall include a mission planning system capable of uploading flight plan waypoints and routes from an offline system to the helicopter.

3.1.11.2 FMS

[AV-076] The TH-XX shall incorporate an integrated FMS.

[AV-077] The TH-XX FMS shall retain the navigation data settings after loss or interruption of electrical power without manually saving to a removable data storage medium.

3.1.11.3 FMS Flight Path Steering

[AV-078] The TH-XX FMS shall determine steering commands necessary to maintain the defined path for all supported flight plan legs in an active flight plan.

[AV-079] The TH-XX FMS shall determine steering commands necessary to fly coupled VOR, ILS, and

GPS approaches.

[AV-080] The TH-XX should provide a system that allows for autonomous navigation and a coupled approach to a HOGE over the landing zone.

[AV-081] The TH-XX FMS shall provide steering commands to the AFCS and displayed to both pilots.

3.1.11.4 FMS Navigation Data

[AV-082] The TH-XX FMS shall have the capability to transfer, hold, process, and update data contained within the aeronautical navigation database.

[AV-084] The TH-XX FMS shall provide the capability for the pilots to build, modify and update user defined navigation data manually while on the ground and while airborne.

3.1.11.5 Aeronautical Database

[AV-085] The TH-XX FMS shall accept and use navigation data from the authorized aeronautical database that is compliant with FAA AC 20-153B and RTCA DO-200B.

[AV-086] The TH-XX shall have the ability to display DOD Flight Information Program (FLIP) instrument approach plates or supplement commercial package that includes military approach plates.

[AV-087] The TH-XX shall have the ability to display information from the FAA Digital Obstacle File

(DOF).

3.1.11.6 Flight Plans Database

[AV-088] The TH-XX FMS shall have the capability to create and store flight plans, including flight plans loaded through electronic media or wireless device.

[AV-089] The TH-XX FMS should allow individual user defined flight plans to be locked preventing manipulation while airborne.

[AV-090] Each TH-XX flight plan database shall be capable of holding, at a minimum, 500 waypoints.

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3.1.11.7 Reference Points/Waypoints Database

[AV-091] The TH-XX FMS shall have the capability to store user defined reference points, hospital waypoints, and markpoints, independent of the flight plans, in addition to those contained in the aeronautical database, and includes points loaded from the FMS.

[AV-092] The TH-XX FMS shall allow a user database to be created and uploaded.

[AV-144] The TH-XX FMS should allow the user database to be locked by maintenance preventing manipulation by general users while airborne.

3.1.11.8 Digital Moving Map

[AV-093] The TH-XX shall provide a Digital Moving Map (DMM) system to store, select, and display map data, and graphics.

[AV-094] The TH-XX DMM shall provide each pilot the capability to independently configure a separate digital map display.

[AV-095] The TH-XX DMM should provide the ability to selectively overlay on any map display, the active flight plan, obstacle database, any navigation aid, any airfield, any fix, and any reference point or waypoint contained in the aeronautical database or the user navigation database.

[AV-096] The TH-XX DMM should integrate with the FMS to provide un-slaved manual navigation selection, which updates the selected flight plan and provides an auto-track capability to any selected Navigation Reference Point (NRP).

3.1.11.9 Declutter

[AV-097] The TH-XX FMS shall provide each pilot the ability to declutter the display.

[AV-140] The TH-XX FMS should provide each pilot the ability to independently declutter a multiple display cockpit configuration.

3.1.12 Human Factors

3.1.12.1 Personal Aircrew Gear

[AV-098] All requirements of this specification shall be satisfied with Mission Aircrew equipped with the following personal aircrew equipment:

• Flight gloves

• HGU-84 Helmet

• Flight Vests-CMU-33 (vest) and LPU-37 (flotation)

• ANVS-9 Night Vision Devices

• Air Vest with survival equipmet and Helicopter Air Breathing Device (HABD)

• Aircrew Restraints

3.1.12.2 Cockpit Storage

[AV-099] The TH-XX cockpit should provide a storage compartment or area suitable for flight publications and mission-related items, accessible by the pilots during flight.

3.1.12.3 Emergency Egress

[AV-100] The TH-XX shall meet FAA 14 CFR Part 27.805 and 14 CFR Part 27.807 emergency egress requirements for Mission Aircrew and passengers equipped with personal aircrew gear.

3.1.12.4 Passenger Door

[AV-102] The TH-XX shall provide sliding passenger doors.

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3.1.12.5 Night Vision Device (NVD) Compatibility

[AV-103] The TH-XX shall accommodate both pilots wearing helmet mounted ANVS-9 NVDs.

[AV-104] The TH-XX shall provide exterior Class B NVD compatible lighting.

[AV-105] The TH-XX shall provide IR position lights and IR formation lights.

[AV-106] The TH-XX shall be capable of being piloted with Class B NVDs while all cabin lights and instrument lights are fully illuminated.

3.1.12.6 Seating

[AV-108] The TH-XX shall provide side-by-side seating for the pilots.

3.1.12.7 Seating Anthropometric Design

[AV-109] The TH-XX shall be capable of being piloted from either pilot station by naval aircrew personnel with anthropometric attributes shown in Table 3-2.

Table 3-2 Anthropometric Attributes (Threshold)

Attribute Minimum Maximum Sitting Eye Height (SEH) ≥ 27.5 N/A Thumb Tip Reach (TTR) ≥ 27.5 N/A Buttock-Knee Length ≥ 21.0 ≤ 27.9 Sitting Height ≥ 32.0 ≤ 39.5

SEH + TTR ≥ 55.5 N/A

Weight Range 103 lbs to 225 lbs NOTE: Units are in inches unless otherwise indicated. Attributes defined in FAA HF-STD-001

[AV-110] The TH-XX should be capable of being piloted from either pilot seats by naval aircrew personnel with anthropometric attributes shown in Table 3-3.

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Table 3-3 Anthropometric Attributes (Desired)

Minimum Maximum Sitting Eye Height (SEH) ≥ 27.5 N/A Thumb Tip Reach (TTR) ≥ 27.0 N/A Buttock-Knee Length ≥ 21.0 ≤ 28.9 Sitting Height ≥ 32.0 ≤ 40.9

SEH + TTR ≥ 55.5 N/A

Weight Range 103 lbs to 245 lbs NOTE: Units are in inches unless otherwise indicated. Attributes defined in FAA HF-STD-001

3.1.12.8 Seating Emergency Landing Conditions

[AV-111] The TH-XX seating systems should provide crashworthy protection in accordance with the latest revisions of 14 CFR Part 27.561.

[AV-142] The TH-XX seating systems should provide emergency landing protection in accordance with the latest revisions of 14 CFR Part 27.562.

[AV-112] The TH-XX pilot and passenger seats shall meet the requirements of TSO-C114 and Type 3

Restraints of SAE-AS8043.

3.1.12.9 Passenger Seating

[AV-118] The TH-XX shall be equipped with seating for at least two passengers in addition to two pilots.

[AV-119] The TH-XX should allow multiple passenger cabin configurations for different training profiles including hoist, external operations, and passenger transport operations.

3.1.12.10 Cockpit Controls and Displays

[AV-120] The TH-XX physical controls and touch screens shall be within human performance limitations, while wearing a glove, with respect to dimensions, resistance, displacement, separation, orientation, color and illumination.

[AV-121] The TH-XX automated systems shall provide information to keep the aircrew continuously informed of each system’s operating mode, intent, function, output, automation failures, and potentially unsafe modes being manually selected.

3.1.12.11 Exterior Lighting

[AV-122] The TH-XX exterior lighting shall comply with FAA requirements for visible intensity distribution and color contained in the Code of Federal Regulations (CFR).

[AV-123] The TH-XX shall have an overt searchlight, capable of rotating 90 degrees left and right of helicopter center line.

[AV-124] The TH-XX shall have an integrated overt/covert IR searchlight capable of rotating 90 degrees left and right of helicopter center line.

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3.1.13 External Appearance

[AV-125] The TH-XX shall have a high visibility paint scheme and marking in accordance with

MIL-STD-2161C.

[AV-143] The government will approve the final paint drawings before implementation.

3.2 Readiness

3.2.1 Support Equipment

[AV-126] The TH-XX should interface and be compatible with DOD Common Support Equipment (CSE).

3.2.2 Health and Usage Monitoring System (HUMS)

[AV-127] The TH-XX shall provide a Health and Usages Monitoring System (HUMS) for ground based display of health data and information.

[AV-128] The TH-XX HUMS data shall be recorded and retained in memory which overwrites the oldest data when full.

[AV-129] The TH-XX HUMS data storage capacity shall be equal or greater than data generated from 24 continous flying hours.

[AV-130] The TH-XX HUMS should provide diagnostics and health monitoring of drivetrain components, rotor components, engines and engine performance, absorbers, hydraulic systems, electrical systems, hydro-mechanical and electro-mechanical systems, and for structural usage monitoring/regime recognition.

[AV-131] The TH-XX HUMS should have a single access location for retrieving diagnostic and health monitoring data from the helicopter.

[AV-132] The TH-XX HUMS should provide the government the ability to independently recover the data directly from the helicopter, have the ability to de-partition, decrypt, and decompress extracted raw data, and decode the raw data to a common .CSV format.

[AV-133] The TH-XX HUMS should record the parameters list in Table 3-4, HUMS Data Elements.

Table 3-4 HUMS Data Elements

Parameter Rate (Hz) Resolution Pitch Attitude 5 0.1 deg

Roll Attitude 5 0.1 deg

Sideslip (yaw) angle 5 0.1 deg

Pitch Rate 5 0.1 deg/sec

Roll Rate 5 0.1 deg/sec

Yaw rate 5 0.1 deg/sec

Nz (G) 5 0.1G

Nx (G) 5 0.1G

Ny (G) 5 0.1G

Magnetic Heading 5 0.1 deg

Ground track 1 0.1 deg

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Barometric Altitude 1 5ft

Radar Altitude 1 1 ft

Indicated Airspeed 1 0.5 kt

Ground speed 1 0.5 kt

True Airspeed 1 0.5 kt

Outside Air Temp (OAT) 1 1 deg

Vertical Speed 1 5 ft/min

Cyclic pitch position 5 0.5 deg

Cyclic roll position 5 0.5 deg

Collective position 5 0.5 deg

Anti-torque pedal position 5 0.5 deg

Twist grip position 5 0.5 deg

Flight idle stop switch position 1 --

All trim positions, as applicable 1 0.5 deg

All failure/warning/caution lights 1 --

Battery switch position 1 --

Power turbine Speed (Nf/N2) 1 0.50% Gas Producer/Compressor Speed (Ng/N1) 1 0.50%

Compressor discharge temperature 5 1 deg C

Compressor discharge pressure 5 1 PSI

Main Rotor Speed 1 0.50%

Tail Rotor Speed 1 0.50%

Transmission oil temperature 1 1 deg C

Transmission oil pressure 1 1 PSI

Engine oil temperature 1 1 deg C

Engine oil pressure 1 1 PSI

Turbine Outlet Temperature (TOT) 5 1 deg C

Torque 1 0.50%

Hydraulic pressure 1 1 PSI

Fuel flow 1 PPH

Fuel Qty 1 8 lbs

Fuel pressure 1 1 PSI

Fuel shutoff valve position 1 --

Fuel filter delta pressure 1 1 PSI

Engine anti-ice switch position 1 --

Hydraulic switch On/Off position 1 --

Cargo release button position 1 --

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Engine vibration (X, Y, Z) 1 *sampled over freq. applicable to engine

Transmission vibration (X, Y, Z) 1 *sampled over freq. applicable to transmission

Accessory Gearbox vibration (X, Y, Z) 1 *sampled over freq. applicable to gearbox

Engine bleed valve position 5 0.5 deg

Fuel pump(s) switch position 1 --

Starter switch position 1 --

Ignition/exciter switch positions 1 --

Oil cooler valve position (if electric) 1 0.5 deg

Engine inlet air temp 1 1 deg C

Rotor brake engage (on/off) 1 --

Date 1 1 day

Greenwich mean time 16 1 sec

Aircraft serial number 15 mins Lattitude 1 0.1 deg

Longitude 1 0.1 deg

Volts battery 1 0.5V

Volts primary buss 1 0.5V

Volts generator (primary and secondary) 1 0.5V

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4 Verification Section 4 specifies the initial government recommendations for verification of requirements delineated in Section 3 of this PBS.

The following verification methods are used in this section:

- Inspection (I) - examination of documents, certificates of compliance, report or hardware. No testing conducted.

- Analysis (A) - technical evaluation of data, analysis, or reports not based on testing to determine compliance with requirements.

- Demonstration (D) - the exercise of hardware, software, and/or operations to determine by observation, with no specific instrumentation or data collection, that qualitatively specified functions can be performed.

- Simulation (S) - the use of established technical or mathematical/computer models, algorithms, charts, graphs, circuit diagrams, or other scientific principles and procedures to provide evidence that stated requirements are met.

- Test (T) - the exercise of hardware, software, and/or operations using procedures and instrumentation/measuring equipment to verify compliance with quantitatively-specified requirements. Specific instrumentation or data collection is required and post-test analysis is performed.

- Non-Verifiable (NV) - not a requirement that can be verified (e.g. a definition).

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Req ID Text Method Document

AV-001

The TH-XX shall have a current Federal Aviation Administration (FAA) Type Certification (TC) that authorizes single-pilot and dual-pilot operations under day and night VFR 14 Code of Federal Regulations (CFR) Part 27 or Part 29 and 14 CFR Part 91.

Inspection (I) FAA TC or STC

AV-002

The TH-XX shall have a current FAA TC or STC that authorizes single-pilot IFR operations in accordance with 14 CFR Part 27, 14 CFR Part 27- Appendix B, and 14 CFR Part 91.

Inspection (I) FAA TC or STC

AV-004

The TH-XX shall implement all requirements in this PBS in a single aircraft configuration to be implemented in a single military Type/Model/Series (T/M/S) in accordance with NAVAIRINST 13100.16.

Non-Verifiable

(NV)

AV-005

The following definitions shall apply throughout this specification:

Cold Day – Temperature -40ºF (-40ºC) at 10,000 feet PA Standard Day – Temperature 59ºF (15ºC) at 0 feet PA Operational Day – Temperature 95ºF (35ºC) at 3,000 feet PA High Hot Day – Temperature 95ºF (35ºC) at 6,000 feet PA

AV-006

The TH-XX shall be capable of continuous operations in temperatures ranging from -2ºF (-19ºC) to +102ºF (39ºC) OAT at NAS Whiting Fld, FL.

Inspection (I) FAA TC Limitations

AV-007

The TH-XX MTGW shall be calculated by adding Helicopter Basic Weight, Mission Fuel, Mission Equipment Weight, Fuel Reserve, and Mission Payload.

AV-008

The TH-XX shall be capable of executing APPENDIX B profiles in Operational Day environmental conditions at or below MTGW and with

ECS-ON.

AV-009

The TH-XX shall be capable of 115 KTAS cruise airspeed in accordance with the Appendix B profiles in Operational Day environmental conditions with ECS-ON.

Demonstration (D) OEM Manual Limitations or

GAT

AV-010

The TH-XX shall be capable of 80 KTAS cruise airspeed with the doors open or removed in Operational Day environmental conditions.

Inspection (I) OEM Manuals Restrictions

AV-011

The TH-XX shall have a Service Ceiling greater than or equal to 15,000 feet

MSL.

Inspection (I) FAA TC Limitations

AV-012

The TH-XX shall be capable of Hover Out of Ground Effect (HOGE) at 5500 feet MSL at MTGW in Standard Day environmental conditions with

ECS-ON.

Inspection (I) OEM Manuals Limitations

AV-013

The TH-XX shall be capable of 2 hour and 30 minutes endurance from takeoff at MTGW to landing in Operational Day environmental conditions with Mission Fuel equal to Endurance Fuel; and Reserve Fuel available over destination.

Analysis (A) OEM Performance Charts

AV-014

The TH-XX shall be capable of flight operations in steady state winds of 40 kts to include rotor engagement, taxi, take-off, and landing. It is understood that re-orienting the helicopter into the wind for rotor engagement, takeoff and landing may be necessary to remain within helicopter operating parameters and limitations.

Inspection (I) FAA TC Limitations

FAA 27.143

4(c)

AV-017 All flying quality requirements shall apply to both pilot stations. Inspection (I) AV-018 The TH-XX shall incorporate independent, mechanically linked controls. Inspection (I) AV-134 The TH-XX shall have an Environmental Control System. Inspection (I) AV-020 The TH-XX AFCS controls shall be accessible from either pilot position. Demonstration (D)

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AV-023 The TH-XX main rotor shall rotate counter-clockwise. Inspection (I) AV-024 The TH-XX shall have a tail rotor. Inspection (I) AV-025 The TH-XX rotor brake shall be capable of completely stopping the rotor. Demonstration (D)

AV-027 The TH-XX shall be capable of conducting power recovery autorotations with engines disengaged from the rotor system.

Demonstration (D)

AV-029 The TH-XX shall have a particle separator or inlet barrier filter. Inspection (I) AV-135 The TH-XX shall have a skid landing gear. Inspection (I) AV-030 The TH-XX shall have blade fold. Demonstration (D)

AV-136

The TH-XX shall comply with requirements under paragraphs (1), (2), (3), (5), and (6) of section 27.952(a), section 27.952(c), section 27.952(f), section 27.952(g), section 27.963(g) (but allowing for a minimum puncture force of 250 pounds if successfully drop tested in-structure), and section 27.975(b) of title 14, Code of Federal Regulations.

Inspection (I) SAIB SW-17- 31R1

AV-032 The TH-XX shall be authorized to use all fuels specified in Table 3-1. Inspection (I) OEM Manual

AV-033

The TH-XX fuel subsystem shall allow the helicopter to be refueled by a SAE-AS5877, Type D 1, locking pressure refueling nozzle or MIL-PRF- 52747F, Closed Circuit Refueling (CCR) nozzle.

Demonstration (D) OEM Manual

AV-034

The TH-XX shall be capable of hot refueling during ground operations with the engines operating and rotors turning in accordance with FAA SAFO 10020.

Demonstration (D) OEM Manual Limitations

AV-035

The TH-XX shall be capable of refueling and gravity refueling during ground operations with engines off, rotors stationary, and no external power supplied.

Demonstration (D) OEM Manual Limitations

AV-036

The TH-XX shall have the ability to gravity defuel the main tanks on the ground and/or suction defuel the main tanks through the helicopter's refueling adapter designed to 7 psi suction pressure.

Demonstration (D) OEM Manual Limitations

AV-037 The TH-XX shall accept external power. Demonstration (D)

AV-039 The TH-XX external power monitor function shall protect in accordance FAA 14 CFR Part 27.1357.

Inspection (I) FAA 27.1357

AV-040

The TH-XX external power receptacle shall be in accordance with SAE-

AS35061A.

Inspection (I) SAE-AS35061

AV-043

The TH-XX shall be capable of hoist operations. Inspection (I) OEM Manual

AV-044

The TH-XX shall be capable of external load operation. Inspection (I) OEM Manual

AV-045

The TH‐XX shall provide a hard point to restraint mobile aircrew located in the cabin capable of withstanding the structural component design criteria of FAA 14 CFR Part 27 for 500 lb nominal load (8.5 kN (1900 lb) ultimate load).

Analysis (A)

AV-046

The TH-XX shall have approved TC, STC, or Technical Standard Order (TSO) for all installed avionics equipment.

Inspection (I) FAA TC, STC, or TSO

AV-047 The TH-XX avionics equipment shall be accessible from either pilot position.

Demonstration (D) FAA 27.1321

AV-048 The TH-XX cockpit shall provide an integrated crew vehicle interface through independent, digital cockpit Multi-Function Displays (MFD).

Inspection (I)

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AV-049

The TH-XX avionics equipment output displays shall be within the Field of View (FOV) for both pilots.

Inspection (I) FAA 27.1321

AV-051 The TH-XX shall be equipped with two independent radios. Inspection (I) FAA TC or STC

AV-137

The TH-XX minimum radio configuration shall be one VHF radio and one independent UHF radio.

Inspection (I)

AV-138 As a minimum, each independent TH-XX radio shall have a dedicated antenna.

Inspection (I)

AV-052 The TH-XX shall be equipped with a VHF radio using 8.33 kHz channel spacing.

Inspection (I) FAA TC or STC

AV-053

The TH-XX shall be equipped with a UHF radio using 50 kHz or less channel spacing.

Inspection (I) FAA TC or STC

AV-139 The TH-XX ICS shall be available to pilot and passenger stations. Inspection (I) AV-055 The TH-XX shall be equipped with a TACAN. Inspection (I) FAA TC or STC AV-056 The TH-XX shall be capable of executing TACAN approaches. Inspection (I) FAA TC or STC AV-057 The TH-XX shall have air-to-air capability. Inspection (I) FAA TC or STC AV-058 The TH-XX shall be equipped with a VOR. Inspection (I) FAA TC or STC AV-059 The TH-XX shall be capable of executing VOR approaches. Inspection (I) FAA TC or STC

AV-060 The TH-XX shall be capable of enroute navigation utilizing VOR-DME radio navigation aids.

Inspection (I) FAA TC or STC

AV-061 The TH-XX shall be capable of executing VOR-DME approaches. Inspection (I) FAA TC or STC AV-062 The TH-XX shall be capable of executing localizer (LOC) approaches. Inspection (I) FAA TC or STC

AV-063 The TH-XX shall be capable of executing ILS approaches in accordance with FAA standards for Category (CAT) I Weather Minima.

Inspection (I) FAA TC or STC

AV-064 The TH-XX shall be equipped with a GPS WAAS reciever. Inspection (I) FAA TC or STC

AV-065 The TH-XX shall be capable of executing GPS approaches to Localizer Performance with Vertical Guidance (LPV) minima.

Inspection (I) FAA TC or STC

AV-066

The TH-XX shall be equipped with Automatic Dependent Surveillance Broadcast (ADS-B) Out and In capability for traffic information.

Inspection (I) FAA TC or STC

AV-067 The TH-XX ADS-B shall allow the user to mute traffic alerts. Demonstration (D)

AV-068

The TH-XX shall be equipped with a midair collision avoidance capability which provides cues and warning to aircrew of conflicting air traffic.

Inspection (I)

AV-069 The collision avoidance system shall allow the user to mute traffic alerts. Demonstration (D)

AV-070 The TH-XX shall be equipped with a crash survivable cockpit voice and flight data recorder system.

Inspection (I)

AV-071 The TH-XX shall be equipped with a 406MHz ELT integrated with GPS geolocation data.

Inspection (I)

AV-072

The TH-XX shall be equipped with a Helicopter Terrain Awareness and Warning System (HTAWS) for Controlled Flight Into Terrain (CFIT) avoidance.

Inspection (I)

AV-073

The TH-XX HTAWS shall reduce nuisance alerts in accordance with RTCA

DO-309.

Inspection (I)

AV-074 The TH-XX shall be equipped with a radar altimeter that is functional and displays from zero to a minimum of 2000 ft AGL.

Inspection (I)

AV-075 The TH-XX System shall include a mission planning system capable of uploading flight plan waypoints from an offline system to the helicopter.

AV-076 The TH-XX shall incorporate an integrated FMS. Inspection (I)

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AV-077

The TH-XX FMS shall retain the navigation data settings after loss or interruption of electrical power without manually saving to a removable data storage medium.

Demonstration (D)

AV-078

The TH-XX FMS shall determine steering commands necessary to maintain the defined path for all supported flight plan legs in an active flight plan.

Demonstration (D)

AV-079 The TH-XX FMS shall determine steering commands necessary to fly coupled VOR, ILS, and GPS approaches.

Demonstration (D)

AV-081 The TH-XX FMS shall provide steering commands to the AFCS and displayed to both pilots.

Demonstration (D)

AV-082

The TH-XX FMS shall have the capability to transfer, hold, process, and update data contained within the aeronautical navigation database.

Demonstration (D)

AV-084

The TH-XX FMS shall provide the capability for the pilots to build, modify and update user defined navigation data manually while on the ground and while airborne.

Demonstration (D)

AV-085

The TH-XX FMS shall accept and use navigation data from the authorized aeronautical database that is compliant with FAA AC 20-153B and RTCA

DO-200B.

Inspection (I)

AV-086

The TH-XX shall have the ability to display DOD Flight Information Program (FLIP) instrument approach plates or supplement commercial package that includes military approach plates.

Demonstration (D)

AV-087 The TH-XX shall have the ability to display information from the FAA Digital Obstacle File (DOF).

Demonstration (D)

AV-088

The TH-XX FMS shall have the capability to create and store flight plans, including flight plans loaded through electronic media or wireless device.

Demonstration (D)

AV-090 Each TH-XX flight plan database shall be capable of holding, at a minimum, 500 waypoints.

Demonstration (D)

AV-091

The TH-XX FMS shall have the capability to store user defined reference points, hospital waypoints, and markpoints, independent of the flight plans, in addition to those contained in the aeronautical database, and includes points loaded from the FMS.

Demonstration (D)

AV-092 The TH-XX FMS shall allow a user database to be created and uploaded. Demonstration (D)

AV-093 The TH-XX shall provide a Digital Moving Map (DMM) system to store, select, and display map data, and graphics.

Demonstration (D)

AV-094 The TH-XX DMM shall provide each pilot the capability to independently configure a separate digital map display.

Demonstration (D)

AV-097 The TH-XX FMS shall provide each pilot the ability to declutter the display. Demonstration (D)

AV-098

All requirements of this specification shall be satisfied with Mission Aircrew equipped with the following personal aircrew equipment:

• Flight gloves

• HGU-84 Helmet

• Flight Vests-CMU-33 (vest) and LPU-37 (flotation)

• ANVS-9 Night Vision Devices

• Air Vest with survival equipmet and Helicopter Air Breathing Device

(HABD)

• Aircrew Restraints

Demonstration (D)

AV-100

The TH-XX shall meet FAA 14 CFR Part 27.805 and 14 CFR Part 27.807 emergency egress requirements for Mission Aircrew and passengers equipped with personal aircrew gear.

Inspection (I) FAA 27.805

FAA 27.807

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AV-102 The TH-XX shall provide sliding passenger doors. Inspection (I)

AV-103 The TH-XX shall accommodate pilots wearing helment mounted ANVS-9 NVDs.

Analysis (A)

AV-104 The TH-XX shall provide exterior Class B NVD compatible lighting. Demonstration (D) AV-105 The TH-XX shall provide IR position lights and IR formation lights. Inspection (I)

AV-106 The TH-XX shall be capable of being piloted with Class B NVDs while all cabin lights and instrument lights are fully illuminated.

Demonstration (D)

AV-108 The TH-XX shall provide side-by-side seating for the pilots. Inspection (I)

AV-109

The TH-XX shall be capable of being piloted from either pilot seats by pilots with anthropometric attributes shown in Table 3-2.

Analysis (A)

AV-112

The TH-XX pilot and passenger seats shall meet the requirements of TSO- C114 and Type 3 Restraints of SAE-AS8043.

Inspection (I) TSO-C114

SAE-AS8043

AV-118

The…