arh performspecifications

Attachment 5AVNS-PRF-10239CAGE Code 81996

8 June 2005 Amendment 0007

ITEM PERFORMANCE SPECIFICATION

FOR THE

ARMED RECONNAISSANCE HELICOPTER

Prepared for:U.S. Army Aviation and Missile CommandRedstone Arsenal, Alabama 35898-5000

Prepared by:Armed Reconnaissance Helicopter Product Manager’s Office

Building 5681Redstone Arsenal, AL 35898-5000

RFP W58RGZ-05-R-0005AVNS-PRF-10239

8 June 2005

Table of Contents

1 SCOPE....................................................................................................................................15

2 APPLICABLE DOCUMENTS............................................................................................15

2.1 General................................................................................................................................15

2.2 Government Documents....................................................................................................152.2.1 Specifications, Standards, and Handbooks...............................................................152.2.2 Other Government Documents, Drawings, and Publications.................................17

2.3 Non-Government Publications.........................................................................................19

2.4 Order of Precedence..........................................................................................................20

3 SYSTEM REQUIREMENTS..............................................................................................20

3.1 General Requirements.......................................................................................................203.1.1 Start Timeline..............................................................................................................20

3.1.1.1 Normal Temperature Start..................................................................................203.1.1.2 Cold Weather Start..............................................................................................213.1.1.3 Cold Weather Start – Displays............................................................................213.1.1.4 Display of Critical Start Parameters..................................................................213.1.1.5 Wind Impact.........................................................................................................21

3.1.2 Crew Equipment Stowage..........................................................................................213.1.2.1 Items to be Stowed................................................................................................213.1.2.2 Impact to Specification........................................................................................21

3.1.3 Wire Strike...................................................................................................................213.1.3.1 Forward Flight Protection...................................................................................213.1.3.2 Area of Protection................................................................................................223.1.3.3 Wire Parameters...................................................................................................22

3.1.4 Airframe Growth Capability.....................................................................................223.1.5 Ozone Depleting Chemicals........................................................................................223.1.6 Data Plates and Product Marking.............................................................................22

3.1.6.1 Identification and Markings................................................................................223.1.6.2 Aircraft Data Plate...............................................................................................223.1.6.3 Finish.....................................................................................................................223.1.6.4 Component Markings..........................................................................................223.1.6.5 Part Serialization..................................................................................................22

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3.1.7 Transparencies............................................................................................................233.1.8 Shipboard Operations.................................................................................................23

3.1.8.1 Capability on Navy Ships.....................................................................................233.1.8.2 Service....................................................................................................................23

3.1.9 Reconfigurable............................................................................................................23

3.2 Performance Characteristics............................................................................................233.2.1 Configuration..............................................................................................................23

3.2.1.1 Weights..................................................................................................................233.2.1.2 Weight and Balance..............................................................................................23

3.2.1.2.1 Empty Weight..................................................................................................243.2.1.2.2 Basic Weight – Standard Armed Reconnaissance Configuration...............243.2.1.2.3 Operating Weight – Standard Armed Reconnaissance Configuration......243.2.1.2.4 Gross Weight - Standard Armed Reconnaissance Configuration..............243.2.1.2.5 Unit Weights.....................................................................................................24

3.2.1.2.5.1 Standard Crew...........................................................................................243.2.1.2.5.2 Fluids (per gallon).....................................................................................243.2.1.2.5.3 Ordnance....................................................................................................243.2.1.2.5.4 Stores Equipment......................................................................................24

3.2.1.3 Center of Gravity Normal Limitations...............................................................253.2.2 Cruise Airspeed...........................................................................................................253.2.3 Hover Out of Ground Effect (HOGE).......................................................................253.2.4 Range............................................................................................................................253.2.5 Operational Radius.....................................................................................................253.2.6 Endurance....................................................................................................................25

3.3 Air Vehicle..........................................................................................................................263.3.1 Usage Spectrum...........................................................................................................263.3.2 Handling Qualities......................................................................................................30

3.3.2.1 Rough Field Operations.......................................................................................313.3.2.2 Autorotation..........................................................................................................31

3.3.3 Human Systems Integration.......................................................................................313.3.3.1 Pilot Accommodation...........................................................................................313.3.3.2 Controls and Displays..........................................................................................31

3.3.3.2.1 Image Intensification (I²) Compatibility........................................................313.3.3.2.2 Standards..........................................................................................................313.3.3.2.3 Display Configuration.....................................................................................323.3.3.2.4 Visibility............................................................................................................323.3.3.2.5 Readability........................................................................................................32

3.3.3.3 Lighting.................................................................................................................323.3.3.3.1 Uniformity........................................................................................................323.3.3.3.2 Luminance Balance.........................................................................................323.3.3.3.3 Luminance........................................................................................................32

3.3.3.4 Emergency Egress................................................................................................323.3.4 Engine/Fuel System.....................................................................................................32

3.3.4.1 Engine....................................................................................................................32

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3.3.4.1.1 Engine Inlet Sand and Dust Protection.........................................................333.3.4.1.1.1 Filtration.....................................................................................................333.3.4.1.1.2 Characteristics...........................................................................................33

3.3.4.1.2 Exhaust Subsystem..........................................................................................333.3.4.1.2.1 Collection....................................................................................................333.3.4.1.2.2 Drainage.....................................................................................................333.3.4.1.2.3 Exhaust Gases............................................................................................333.3.4.1.2.4 Induced Loads............................................................................................33

3.3.4.1.3 Engine Drains-Nacelle.....................................................................................333.3.4.1.3.1 Fluid Entrapment......................................................................................333.3.4.1.3.2 Drains.........................................................................................................34

3.3.4.1.4 Vibration...........................................................................................................343.3.4.2 Fuel System...........................................................................................................34

3.3.4.2.1 Fuel Compatibility...........................................................................................343.3.4.2.2 Refueling / Defueling.......................................................................................343.3.4.2.3 Single Point Refueling / Defueling..................................................................343.3.4.2.4 Fuel Quantity Gauging....................................................................................343.3.4.2.5 Fuel Tanks........................................................................................................34

3.3.4.2.5.1 Construction...............................................................................................343.3.4.2.5.2 Drop Test....................................................................................................353.3.4.2.5.3 Fuel Tank Removal/Installation...............................................................353.3.4.2.5.4 Fuel Cell Ballistic Capability....................................................................35

3.3.4.2.6 Fuel Line Ballistic Capability.........................................................................353.3.4.2.7 Auxiliary Fuel System.....................................................................................35

3.3.4.2.7.1 Fuel Transfer System................................................................................353.3.4.2.7.2 Management...............................................................................................353.3.4.2.7.3 Crashworthiness........................................................................................35

3.3.4.3 Engine Control Subsystem..................................................................................353.3.4.3.1 Controls............................................................................................................353.3.4.3.2 Rotor Speed......................................................................................................353.3.4.3.3 Start and Abort................................................................................................353.3.4.3.4 Motoring...........................................................................................................363.3.4.3.5 Control System Single Failure........................................................................36

3.3.4.4 Fire Extinguishing System (Dual Engine Only).................................................363.3.5 Drive Subsystem..........................................................................................................36

3.3.5.1 Life Limits.............................................................................................................363.3.5.1.1 Gears.................................................................................................................363.3.5.1.2 Bearings............................................................................................................36

3.3.5.2 Lubrication System..............................................................................................373.3.5.2.1 Lubrication.......................................................................................................373.3.5.2.2 Loss of Lubrication..........................................................................................373.3.5.2.3 Pumps................................................................................................................373.3.5.2.4 Filtration...........................................................................................................383.3.5.2.5 Cooling Fans.....................................................................................................383.3.5.2.6 Grease Fittings.................................................................................................383.3.5.2.7 Sensors..............................................................................................................38

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3.3.5.3 Vibrations and Dynamics....................................................................................383.3.5.4 Overrunning Clutches..........................................................................................383.3.5.5 Accessory Drives...................................................................................................383.3.5.6 Mechanical Gust Lock.........................................................................................393.3.5.7 Rotor Brake...........................................................................................................393.3.5.8 Drive Shaft Subsystem.........................................................................................39

3.3.5.8.1 Drive Shafting..................................................................................................393.3.5.8.2 Couplings..........................................................................................................393.3.5.8.3 Bearings............................................................................................................39

3.3.5.9 Dynamic System Mean-Time-Between-Removal (MTBR)...............................393.3.6 Hydraulic Subsystem..................................................................................................40

3.3.6.1 General Subsystem Performance........................................................................403.3.6.2 Hydraulic Fluid.....................................................................................................403.3.6.3 Redundancy..........................................................................................................403.3.6.4 Fail Safe.................................................................................................................403.3.6.5 Proof and Burst Pressures...................................................................................403.3.6.6 Removal of Entrapped Air..................................................................................413.3.6.7 Fluid Level Indicator............................................................................................413.3.6.8 Filtration................................................................................................................413.3.6.9 Quick Disconnects................................................................................................413.3.6.10 Temperature Monitor..........................................................................................413.3.6.11 Sampling Port.......................................................................................................41

3.3.7 Environmental Systems..............................................................................................413.3.8 Mechanical Stability...................................................................................................413.3.9 Flutter...........................................................................................................................423.3.10 Structural Design Criteria......................................................................................42

3.3.10.1 General Strength Requirements.........................................................................423.3.10.2 Armament.............................................................................................................423.3.10.3 Fatigue Strength...................................................................................................42

3.3.10.3.1 Critical Dynamic Component Fatigue.........................................................423.3.10.3.2 Airframe System Fatigue..............................................................................42

3.3.10.4 Crash Strength.....................................................................................................423.3.11 Aircraft Mooring.....................................................................................................423.3.12 Electrical Power System..........................................................................................433.3.13 Air Vehicle Vibration..............................................................................................433.3.14 Internal Noise...........................................................................................................433.3.15 Drainage Collection.................................................................................................433.3.16 Exterior Lighting.....................................................................................................43

3.3.16.1 Navigation Lights.................................................................................................433.3.16.2 Anti-Collision Lighting........................................................................................433.3.16.3 Daylight High-Intensity Anti-Collision Light....................................................443.3.16.4 Night High-Intensity Anti-Collision Light.........................................................443.3.16.5 Searchlight/Landing Light..................................................................................44

3.3.17 Pilot Operability.......................................................................................................44

3.4 Mission Equipment Package (MEP)................................................................................44

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3.4.1 Advanced Cockpit Management................................................................................443.4.1.1 Digital Cockpit......................................................................................................443.4.1.2 Flight Crewmember Station Controls................................................................443.4.1.3 Redundancy..........................................................................................................443.4.1.4 Single-Pilot Operable...........................................................................................453.4.1.5 Workload...............................................................................................................453.4.1.6 MFD Presentation................................................................................................453.4.1.7 Compatibility with Laser Eye Protection...........................................................45

3.4.2 System Software and Processing...............................................................................453.4.2.1 Software Design....................................................................................................453.4.2.2 Software in Firmware..........................................................................................453.4.2.3 Software Redundancy Management...................................................................453.4.2.4 Software Partitioning...........................................................................................453.4.2.5 Software Programming Languages....................................................................463.4.2.6 Software Code Constraints..................................................................................463.4.2.7 Software Initialization..........................................................................................463.4.2.8 Software Security and Classification..................................................................463.4.2.9 Software Fault Detection / Fault Isolation (FD/FI)...........................................463.4.2.10 Software Modularity............................................................................................463.4.2.11 Field Software Reprogrammability....................................................................463.4.2.12 Software Undesired Functions and Anomalies.................................................463.4.2.13 Software Configuration Display.........................................................................473.4.2.14 Memory and Throughput....................................................................................473.4.2.15 Bus Partitioning....................................................................................................473.4.2.16 Mobile Code..........................................................................................................473.4.2.17 Development Environment..................................................................................473.4.2.18 COTS and GOTS Information Assurance (IA) and IA-enabled Software.....473.4.2.19 Out of Cycle Revisions.........................................................................................473.4.2.20 Software Blocking................................................................................................473.4.2.21 Anti-Tamper.........................................................................................................47

3.4.3 System Security Classification Level.........................................................................473.4.4 Zeroize..........................................................................................................................48

3.4.4.1 Onboard Data.......................................................................................................483.4.4.2 Encryption Codes.................................................................................................483.4.4.3 Mode Codes...........................................................................................................483.4.4.4 Code Hold..............................................................................................................48

3.4.5 Information Assurance...............................................................................................483.4.6 Mission Planning/Data Transfer System (DTS).......................................................48

3.4.6.1 Pre-Mission Planning...........................................................................................483.4.6.2 Compatibility........................................................................................................483.4.6.3 Automation............................................................................................................483.4.6.4 Cartridge Media...................................................................................................483.4.6.5 Onboard Mission Rehearsal................................................................................483.4.6.6 Data/Audio/Video Memory Storage/Retrieval..................................................49

3.4.7 Sensors..........................................................................................................................493.4.7.1 Target Acquisition Sensor Suite (TASS) Functionality....................................49

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3.4.7.2 TASS Modes..........................................................................................................493.4.7.3 Slew Rate...............................................................................................................493.4.7.4 TASS Startup Timeline........................................................................................503.4.7.5 Boresight................................................................................................................50

3.4.7.5.1 Automation.......................................................................................................503.4.7.5.2 Crew Interface.................................................................................................503.4.7.5.3 Outside Targets................................................................................................503.4.7.5.4 Alignment Retention........................................................................................503.4.7.5.5 Safety Features.................................................................................................503.4.7.5.6 Drift Recognition.............................................................................................50

3.4.7.6 Target Acquisition Sensor Suite (TASS)............................................................503.4.7.6.1 Infrared Sensor................................................................................................51

3.4.7.6.1.1 Output.........................................................................................................513.4.7.6.1.2 Display Viewability....................................................................................513.4.7.6.1.3 Polarity (black/white hot).........................................................................513.4.7.6.1.4 Future Growth...........................................................................................51

3.4.7.6.2 CTV...................................................................................................................513.4.7.6.2.1 Sun Viewing Protection.............................................................................513.4.7.6.2.2 CTV Display...............................................................................................51

3.4.7.6.3 Laser Rangefinder/Designator.......................................................................513.4.7.6.3.1 Safety..........................................................................................................513.4.7.6.3.2 Fail-Safe......................................................................................................523.4.7.6.3.3 Firing Limits..............................................................................................523.4.7.6.3.4 Safety Interlocks........................................................................................523.4.7.6.3.5 Notification.................................................................................................523.4.7.6.3.6 Codes...........................................................................................................523.4.7.6.3.7 Range..........................................................................................................523.4.7.6.3.8 Accuracy.....................................................................................................523.4.7.6.3.9 Compatibility.............................................................................................523.4.7.6.3.10 Selectability..............................................................................................523.4.7.6.3.11 Interface with Avionics...........................................................................523.4.7.6.3.12 Modes of Operation.................................................................................523.4.7.6.3.13 Laser Range Requirements....................................................................523.4.7.6.3.14 Laser to Sensor LOS Coincidence.........................................................53

3.4.7.6.4 Laser Pointer....................................................................................................533.4.7.6.4.1 Target Location Error..............................................................................53

3.4.7.6.5 Laser Spot Tracker..........................................................................................533.4.7.7 Image Fusion.........................................................................................................53

3.4.7.7.1 Image Selection................................................................................................533.4.7.7.2 Adjustment.......................................................................................................533.4.7.7.3 Fused Image Display........................................................................................53

3.4.7.8 Imagery Controls..................................................................................................533.4.7.8.1 Gain and Level.................................................................................................533.4.7.8.2 Focus.................................................................................................................53

3.4.7.9 Image Auto-Tracker.............................................................................................543.4.7.9.1 Acquisition and Tracking of Targets.............................................................54

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3.4.7.9.2 Interoperability................................................................................................543.4.7.9.3 Track Gates......................................................................................................543.4.7.9.4 Display..............................................................................................................543.4.7.9.5 Break Track.....................................................................................................543.4.7.9.6 Reacquisition of Targets..................................................................................54

3.4.7.10 Symbology.............................................................................................................543.4.7.10.1 Display............................................................................................................543.4.7.10.2 Selection..........................................................................................................54

3.4.7.11 TASS Field of Regard..........................................................................................543.4.7.12 TASS Field of View (FOV)..................................................................................55

3.4.7.12.1 Infrared Sensor Fields of View.....................................................................553.4.7.12.1.1 Narrow Field of View (NFOV)...............................................................553.4.7.12.1.2 Medium Field of View (MFOV).............................................................553.4.7.12.1.3 Wide Field of View (WFOV)..................................................................55

3.4.7.12.2 CTV Fields of View........................................................................................553.4.7.12.2.1 CTV Super Narrow Field of View (SNFOV)........................................55

3.4.7.12.3 Switching and Settling Times.......................................................................553.4.7.12.4 FOV Center....................................................................................................55

3.4.7.13 Electro-Optics Counter Countermeasure (EOCCM).......................................553.4.7.14 TASS Open System Architecture.......................................................................553.4.7.15 Anti-Ice..................................................................................................................56

3.4.8 Battlefield Interoperability.........................................................................................563.4.8.1 Net Centric............................................................................................................563.4.8.2 Network Protocol..................................................................................................563.4.8.3 System Interoperability.......................................................................................563.4.8.4 Communication System.......................................................................................58

3.4.8.4.1 Joint Tactical Radio System (JTRS)..............................................................583.4.8.4.2 Compatibility....................................................................................................583.4.8.4.3 GATM...............................................................................................................583.4.8.4.4 Range................................................................................................................59

3.4.8.4.4.1 Civil Airspace Entry Communications....................................................593.4.8.4.4.2 Nap of Earth (NOE) Communications....................................................593.4.8.4.4.3 Line-of-Sight (LOS) Communications.....................................................593.4.8.4.4.4 NOE SINCGARS Communications.........................................................593.4.8.4.4.5 Non Line-of-Sight Communications........................................................593.4.8.4.4.6 Link 16 Communications..........................................................................59

3.4.8.4.5 Identification and Combat ID.........................................................................593.4.8.4.5.1 Identification..............................................................................................593.4.8.4.5.2 Combat Identification (ID).......................................................................593.4.8.4.5.3 Enhanced ID..............................................................................................60

3.4.8.4.6 Voice and Data Communication.....................................................................603.4.8.4.7 Modes / Status Indications..............................................................................603.4.8.4.8 Simultaneous Communications......................................................................603.4.8.4.9 Receive/Transmit Capability..........................................................................603.4.8.4.10 Preset Channels..............................................................................................603.4.8.4.11 Still / Live Imagery........................................................................................60

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3.4.8.4.12 UHF-AM.........................................................................................................613.4.8.4.12.1 Jam Resistance.........................................................................................613.4.8.4.12.2 Joint Service Interoperability.................................................................613.4.8.4.12.3 Secure Communication...........................................................................613.4.8.4.12.4 Secure Voice and Data, UHF SATCOM...............................................613.4.8.4.12.5 Data from Improved Data Modem (IDM)............................................613.4.8.4.12.6 Continuous Guard...................................................................................61

3.4.8.4.13 VHF-FM.........................................................................................................613.4.8.4.13.1 Jam Resistance.........................................................................................613.4.8.4.13.2 Joint Service Interoperability.................................................................623.4.8.4.13.3 Secure Communications.........................................................................623.4.8.4.13.4 UAV Level 2 Data and Still Image Display...........................................623.4.8.4.13.5 UAV Level 2 Control...............................................................................623.4.8.4.13.6 Data from the IDM..................................................................................62

3.4.8.4.14 VHF-AM Communication............................................................................623.4.8.4.14.1 IDM Interface..........................................................................................623.4.8.4.14.2 Channel Spacing......................................................................................623.4.8.4.14.3 Continuous Guard...................................................................................62

3.4.8.4.15 Ultra High Frequency (UHF) – EPLRS.......................................................623.4.8.4.15.1 Secure Communication...........................................................................62

3.4.8.4.16 L-Band - BFT Data Communication...........................................................623.4.8.4.16.1 Secure BFT...............................................................................................633.4.8.4.16.2 Data from IDM........................................................................................63

3.4.8.4.17 L-Band – Link-16 Voice and Data Communication...................................633.4.8.4.17.1 Secure Link-16.........................................................................................633.4.8.4.17.2 Data from IDM........................................................................................63

3.4.8.4.18 Ku Band – TCDL Data Communication.....................................................633.4.8.4.18.1 Secure TCDL...........................................................................................633.4.8.4.18.2 Data Display.............................................................................................633.4.8.4.18.3 Control of UAVs......................................................................................633.4.8.4.18.4 Video.........................................................................................................63

3.4.8.4.19 Multiple Frequency Bands (WNW, NDL, SRW) Communication...........633.4.8.4.19.1 Secure Communications.........................................................................643.4.8.4.19.2 Data from IDM........................................................................................643.4.8.4.19.3 Video.........................................................................................................64

3.4.8.4.20 Command, Control, Communications, Computers, Identification, Surveillance, and Reconnaissance (C4ISR) Interface....................................................643.4.8.4.21 Retransmission / Crossbanding....................................................................643.4.8.4.22 Integrated Broadcast Services (IBS)............................................................643.4.8.4.23 Intercommunication Subsystem...................................................................64

3.4.8.4.23.1 Simultaneous Communication...............................................................643.4.8.4.23.2 Interface Capability................................................................................643.4.8.4.23.3 Secure and Clear Voice...........................................................................643.4.8.4.23.4 Interface with DTS..................................................................................653.4.8.4.23.5 Intercommunication Subsystem Controls.............................................653.4.8.4.23.6 Intercommunication Subsystem Audio Intelligibility..........................65

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3.4.8.5 TEMPEST.............................................................................................................653.4.8.6 Visual Flight Rules/Instrument Flight Rules (VFR/IFR).................................653.4.8.7 Navigation.............................................................................................................65

3.4.8.7.1 Radio Navigation.............................................................................................653.4.8.7.2 Area Navigation (RNAV) Systems.................................................................66

3.4.8.7.2.1 Sensors/Accuracy.......................................................................................663.4.8.7.2.2 Flight Management...................................................................................66

3.4.8.7.3 GATM Compliance.........................................................................................663.4.8.7.4 GPS IFR Requirement....................................................................................663.4.8.7.5 Absolute Altitude.............................................................................................66

3.4.8.7.5.1 Accuracy.....................................................................................................663.4.8.7.5.2 Drift Rate....................................................................................................66

3.4.8.8 Tactical Situational Awareness...........................................................................673.4.8.8.1 Digital Map System..........................................................................................673.4.8.8.2 Digital Map Civil Capabilities........................................................................673.4.8.8.3 Inputs................................................................................................................673.4.8.8.4 Latency..............................................................................................................67

3.4.8.9 Map Display..........................................................................................................673.4.8.9.1 Capabilities.......................................................................................................673.4.8.9.2 Terrain and Feature Data...............................................................................673.4.8.9.3 Data Source......................................................................................................68

3.4.8.9.3.1 Digital Map Products................................................................................683.4.8.9.3.2 Compliancy................................................................................................68

3.4.8.9.4 Storage Capacity..............................................................................................683.4.8.10 Command and Control (C2) Interface...............................................................68

3.4.8.10.1 Variable Message Format (VMF)................................................................683.4.8.10.2 VMF................................................................................................................683.4.8.10.3 TADIL-J.........................................................................................................683.4.8.10.4 Common Message Format............................................................................68

3.4.8.11 Crash Survivable Memory Unit (CSMU)..........................................................683.4.8.11.1 Record Capability..........................................................................................683.4.8.11.2 Storage............................................................................................................693.4.8.11.3 Crashworthy...................................................................................................693.4.8.11.4 System Parameters........................................................................................693.4.8.11.5 Compatibility with US Army Safety Center...............................................69

3.4.8.12 DISR Compliance.................................................................................................693.4.8.13 Central Test Support Facility Certification.......................................................693.4.8.14 Joint Interoperability Test Center (JITC) Certification..................................693.4.8.15 Spectrum Management........................................................................................69

3.4.9 Lethality.......................................................................................................................693.4.9.1 Employment..........................................................................................................693.4.9.2 Air-to-Ground Missiles / Rockets.......................................................................69

3.4.9.2.1 Hellfire..............................................................................................................703.4.9.2.2 Rockets..............................................................................................................703.4.9.2.3 Armament Trajectory/Aircraft Clearance....................................................703.4.9.2.4 Armament /Aircraft Compatibility................................................................70

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3.4.9.2.5 Armament Boresight.......................................................................................713.4.9.3 Self-Protection......................................................................................................713.4.9.4 Weapons Mounting Station.................................................................................713.4.9.5 Emergency Release of Stores...............................................................................713.4.9.6 Arm/Rearm...........................................................................................................713.4.9.7 Open Weapon System Architecture...................................................................71

3.5 Survivability.......................................................................................................................713.5.1 Radar Detection...........................................................................................................713.5.2 Infrared (IR)................................................................................................................72

3.5.2.1 IR Countermeasures............................................................................................723.5.2.2 IR Suppression......................................................................................................72

3.5.3 Laser Detection............................................................................................................723.5.4 Ballistic Protection......................................................................................................723.5.5 Seats..............................................................................................................................723.5.6 Airframe Crashworthiness.........................................................................................733.5.7 Major Component Displacements.............................................................................733.5.8 Blade Strikes................................................................................................................73

3.6 Environmental Conditions................................................................................................733.6.1 Physical Environment.................................................................................................73

3.6.1.1 Low Pressure (Altitude).......................................................................................733.6.1.2 Temperature.........................................................................................................73

3.6.1.2.1 Operating..........................................................................................................733.6.1.2.2 Non-Operating.................................................................................................743.6.1.2.3 Temperature Shock.........................................................................................74

3.6.1.3 Rain........................................................................................................................743.6.1.3.1 General Requirements.....................................................................................743.6.1.3.2 Blades................................................................................................................74

3.6.1.4 Icing/Freezing Rain..............................................................................................743.6.1.5 Humidity................................................................................................................743.6.1.6 Fungus...................................................................................................................743.6.1.7 Salt Fog..................................................................................................................753.6.1.8 Sand and Dust.......................................................................................................75

3.6.1.8.1 General Requirements.....................................................................................753.6.1.8.2 Blades................................................................................................................75

3.6.1.9 Explosive Atmosphere..........................................................................................753.6.1.10 Shock.....................................................................................................................75

3.6.1.10.1 Functional Shock...........................................................................................753.6.1.10.2 Bench Handling Shock..................................................................................753.6.1.10.3 Crash Hazard Shock......................................................................................76

3.6.1.11 Induced Vibration................................................................................................763.6.1.12 Solar Radiation.....................................................................................................763.6.1.13 Acceleration..........................................................................................................76

3.6.2 Electromagnetic Environmental Effects (E³)............................................................763.6.2.1 Electromagnetic Interference (EMI)..................................................................76

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3.6.2.2 Electromagnetic Compatibility (EMC)..............................................................763.6.2.3 Electromagnetic Vulnerability (EMV)...............................................................763.6.2.4 Electromagnetic Pulse (EMP).............................................................................773.6.2.5 Hazards of Electromagnetic Radiation to Ordnance (HERO)........................773.6.2.6 Hazards of Electromagnetic Radiation to Fuel (HERF)...................................773.6.2.7 Hazards of Electromagnetic Radiation to Personnel (HERP).........................773.6.2.8 Aircraft Discharge................................................................................................773.6.2.9 Precipitation Static...............................................................................................773.6.2.10 Personnel Handling of Ordnance.......................................................................773.6.2.11 Lightning Protection............................................................................................773.6.2.12 Electrical Bonding................................................................................................773.6.2.13 Life Cycle E³ Hardness........................................................................................77

3.7 Sustainability......................................................................................................................773.7.1 Maintenance Concept.................................................................................................783.7.2 Computer Resources Support....................................................................................783.7.3 Packaging, Handling, Storage....................................................................................783.7.4 Publications..................................................................................................................78

3.8 Reliability............................................................................................................................783.8.1 Mean Time Between Essential Function Failure (MTBEFF).................................793.8.2 Mean Time Between System Aborts (MTBSA)........................................................79

3.9 Maintainability...................................................................................................................793.9.1 Direct Maintenance Man-Hour per Flight Hour (DMMH / FH)...........................793.9.2 Mean Time To Repair- Essential (MTTRe)..............................................................80

3.10 Battle Damage Assessment and Repair (BDAR).........................................................803.10.1 BDAR Time..............................................................................................................803.10.2 BDAR Duration.......................................................................................................80

3.11 Diagnostics......................................................................................................................803.11.1 Detection and Isolation............................................................................................803.11.2 False Alarm Rate.....................................................................................................81

3.12 Facilities...........................................................................................................................81

3.13 Training...........................................................................................................................813.13.1 Integrated Training Program (ITP).......................................................................813.13.2 Operational Training Engagement System...........................................................81

3.13.2.1 Tactical Engagement Simulation System (TESS).............................................813.13.2.2 Embedded Instrumentation................................................................................82

3.14 MANPRINT General.....................................................................................................823.14.1 Personnel..................................................................................................................823.14.2 Human Factors Engineering...................................................................................823.14.3 Soldier Survivability................................................................................................82

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3.14.4 System Safety...........................................................................................................82

3.15 Transportability..............................................................................................................833.15.1 Embark Operations.................................................................................................833.15.2 Debark Operations..................................................................................................833.15.3 Intra-Theatre Transportability..............................................................................833.15.4 Strategic Transportability.......................................................................................83

3.16 Other Transportability Requirements.........................................................................83

3.17 Recovery..........................................................................................................................83

4 VERIFICATION...................................................................................................................84

4.1 Requirements Verification................................................................................................84

4.2 Verification Methods.........................................................................................................84

5 PACKAGING........................................................................................................................85

6 NOTES...................................................................................................................................85

6.1 Change in Design Envelope and Usage Spectrum..........................................................856.1.1 U.S. Army Qualified Aircraft.....................................................................................856.1.2 Other Aircraft.............................................................................................................86

6.2 Commonality......................................................................................................................86

6.3 Information Exchange Requirements..............................................................................86

6.4 Air Warrior Configurations.............................................................................................86

6.5 Fuel Quantity Gauging......................................................................................................87

6.6 Acronyms and Abbreviations..............................................................................................87

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List of Tables

Table I Usage Spectrum................................................................................................................26

Table II Average MTBR / MTBRRDR for Dynamic Components.............................................39

Table III Sample Requirements Verification Matrix....................................................................84

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1 SCOPE

This document provides the performance, qualification, and verification requirements for the Armed Reconnaissance Helicopter (ARH). The ARH will conduct armed reconnaissance to gain actionable combat information enabling joint/combined air-ground maneuver execution of Mobile Strike, Close Combat and Vertical Maneuver operations across the full-spectrum of military operations. The ARH will replace the current fleet of OH-58D reconnaissance aircraft upon retirement. Initial delivered aircraft will be a combination of Off the Shelf (OTS) and Non-Development Items (NDI) capable of operating with current and Stryker-equipped forces. Follow on lots of aircraft will provide Future Force capabilities.

The document defines the requirements in terms of Threshold (T), Threshold Tradeable 1, 2, and 3 (TT1, TT2, and TT3), and Objective (O) requirements and are defined as follows:

(T) Threshold requirements and specific parameters are mandatory.

(TT1) Threshold requirements are mandatory; specific parameters are highly desirable but not mandatory.

(TT2) Threshold requirements are mandatory; specific parameters are desirable but not mandatory.

(TT3) Threshold requirements are desired.

(O) Objective requirements are desired requirements which describe capabilities that will enable the ARH to fully address deficiencies identified in the currently fielded reconnaissance aircraft. Objective requirements as written specifically address the delta parameters of the threshold requirement. Any parameter not addressed in the objective requirement remains as written in the threshold requirement.

2 APPLICABLE DOCUMENTS

2.1 General Documents listed in this section are specified in sections 3, 4, or 5 of this specification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they shall meet all specified requirements of documents cited in sections 3, 4, or 5 of this specification, whether or not they are listed.

2.2 Government Documents

2.2.1 Specifications, Standards, and HandbooksThe following specifications, standards, and handbooks of the exact revision listed below form a part of this document to the extent specified herein.

MIL-DTL-27422C 14 Jan 02 Tank, Fuel, Crash-Resistant, Ballistic-Tolerant, Aircraft

MIL-DTL-5624U 5 Jan 04 Turbine Fuel, Aviation, Grades JP-4 and JP-5

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8 June 2005

MIL-DTL-83133E 1 Apr 99 Turbine Fuels, Aviation, Kerosene Types, NATO F-34 (JP-8), NATO F-35, and JP-8+100

MIL-E-52031D 05 Sep 79 Extinguisher, Fire, Vaporizing Liquid, CF#BR, 2 3/4 pound, With Bracket

MIL-F-8815 23 Jun 95 Filter and Filter elements, Fluid Pressure, Hydraulic, Line, 15 Micron Absolute, Type II Systems; General Specification for

MIL-L-6503H 25 Mar 96 Lighting Equipment, Aircraft, General Specification for Installation of

MIL-PRF-23699F 21 May 97 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base, NATO Code Number O-156

MIL-PRF-7808L 2 May 97 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base

MIL-PRF-83282D 30 Sep 97 Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Metric, NATO Code Number H-537

MIL-PRF-87257B 22 Apr 04 Hydraulic Fluid, Fire Resistant; Low Temperature, Synthetic Hydrocarbon Base, Aircraft and Missile

MIL-STD-130L 10 Oct 03 Identification Markings of U.S. Military Property

MIL-STD-188-181B 20 Mar 99 Interoperability Standard for Access to 5-Khz and 25-Khz UHF Satellite Communications Channels

MIL-STD-188-182A 31 Mar 94 Interoperability Standard for UHF SATCOM DAMA Orderwire Messages and Protocols

MIL-STD-188-183 18 Sep 92 Interoperability Standard for Multiple-Access 5-Khz and 25-Khz UHF Satellite Communications Channels

MIL-STD-188-184 20 Aug 93 Interoperability and Performance Standard for the Data Control Waveform

MIL-STD-188-185(2) 9 Sep 98 Interoperability UHF MILSATCOM DAMA Control System

MIL-STD-461E 20 Aug 99 Requirements for the Control of Electromagnetic Interference Characteristics of Subsystems and Equipment

MIL-STD-704F 12 Mar 04 Aircraft Electrical Power Characteristics

MIL-STD-1425A 30 Aug 91 Safety Design Requirements for Military Lasers and Associated Support Equipment

MIL-STD-1472F(1) 5 Dec 03 Human Engineering

MIL-STD-1474D 29 Aug 97 Noise Limits

MIL-STD-1787C 5 Jan 01 Aircraft Display Symbology

MIL-STD-2073-1D(1) 10 May 02 DOD Standard Practice for Military Packaging

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MIL-STD-2361C 15 Oct 04 Interface Standard, Digital Publications Development

MIL-STD-2525B 30 Jan 99 Common Warfighting Symbology

MIL-STD-3005 20 Dec 99 Analog-to-Digital Conversion of Voice by 2,400 Bit/Second Mixed Excitation Linear Prediction (MELP)

MIL-STD-3009 4 Oct 02 Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible

MIL-STD-3011 30 Sep 02 Interoperability Standard for the Joint Range Extension Application Protocol (JREAP)

MIL-STD-6016C 31 Mar 04 Tactical Data Link (TDL) 16 Message Standard

MIL-STD-6017 1 Apr 04 Variable Message Format (VMF)

MIL-STD-704F 12 Mar 04 Aircraft Electric Power Characteristics

MIL-STD-810F 5 May 03 Department of Defense Test Method Standard for Notice 3 Environmental Engineering Considerations and Laboratory Tests

MIL-STD-40051-1 15 Oct 04 Preparation of Digital Technical Information for Interactive Electronic Technical Manuals (IETM)

MIL-T-81259B 11 Oct 91 Tie-Downs, Airframe Design, Requirements for

Copies of these documents are available online at http://assist.daps.dla.mil/quicksearch/ or www.dodssp.daps.mil or from the Standardization Document Order Desk, 700 Robbins Avenue Building 4D, Philadelphia, PA, 19111-5094.

2.2.2 Other Government Documents, Drawings, and Publications. The following other Government documents, drawings, and publications of the exact revision level shown form a part of this document to the extent specified herein.

DOD Directive 8500.1 24 Oct 02 Information Assurance

AC 20-136 5 Mar 90 Protection of Aircraft Electrical/Electronic Systems against the Indirect Effects of Lightning

ADS-27 Jun 93 Requirements for Rotorcraft Vibration Specifications, Modeling and Testing

ADS-33E-PRF 21 Mar 02 Handling Qualities Requirements for Military Rotorcraft

ADS-37A-PRF 28 May 96 Electromagnetic Effects (E3) Performance and Verification Requirements

ADS-50-PRF 15 Apr 96 Rotorcraft Propulsion Performance and Qualification Requirements and Guidelines

17

http://www.dodssp.daps.mil/

http://assist.daps.dla.mil/quicksearch/


8 June 2005

ADS-69-PRF 27 Oct 04 Hydraulic Fluid, Petroleum Base; Aircraft, Missile, and Ordnance

AR 5-12 01 Oct 97 Army Management of the Electromagnetic Spectrum

AR 95-1 01 Sep 97 Flight Operations

14 CFR, Part 27 Airworthiness Standards: Normal Category Rotorcraft

14 CFR, Part 33 Airworthiness Standards: Aircraft Engines

21 CFR, 1040 Performance Standards for Light-Emitting Products

DOD-PRF-85734A 29 Jun 04 Lubricating Oil, Helicopter Transmission System, Synthetic Base

RTCA/DO-160D 29 Jul 97 Environmental Conditions and Test Procedures for Airborne Equipment

RTCA/DO-178B 1 Dec 92 Software Considerations in Airborne Systems and Equipment Certification

RTCA/DO-181C 12 Jun 01 Minimum Operational Performance Standards for Air Traffic Control Radar Beacon System / Mode Select (ATCRBS / Mod S) Airborne Equipment

RTCA/DO-254 19 Apr 00 Design Assurance Guidance for Airborne Electronic Hardware

TM 55-1500-345-23 12 Jun 86 Painting and Marking of Army Aircraft

TR 89/044 Mar 89 1988 Anthropometric Survey of U.S. Army Personnel: Methods and Summary Statistics

TR 89-D-22E Dec 89 Aircraft Crash Survival Design Guide, Vol. 5 Aircraft Post Crash Survival

TSO C-115b 30 Sep 94 Airborne Area Navigation Equipment Using Multi-Sensor Inputs

TSO C-129a 20 Feb 96 Airborne Supplemental Navigation Equipment Using the Global Positioning System (GPS)

Copies of these documents may be obtained from:

AC documents: http://www.gofir.com/fars/advisory_circulars/

ADS documents: http://www.redstone.army.mil/amrdec/sepd/tdmd/StandardAero.htm

CFR documents: http://www.access.gpo.gov/nara/cfr/waisidx_04/14cfrv1_04.html

RTCA DO documents: http://www.rtca.org/

TM documents: https://www.logsa.army.mil/etms/find_etm.cfm

TSO documents: http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgTSO.nsf/MainFrame?OpenFrameSet

18

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgTSO.nsf/MainFrame?OpenFrameSet

http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgTSO.nsf/MainFrame?OpenFrameSet

https://www.logsa.army.mil/etms/find_etm.cfm

http://www.rtca.org/

http://www.access.gpo.gov/nara/cfr/waisidx_04/14cfrv1_04.html

http://www.redstone.army.mil/amrdec/sepd/tdmd/StandardAero.htm

http://www.gofir.com/fars/advisory_circulars/


8 June 2005

2.3 Non-Government PublicationsThe following documents of the exact revision listed below form a part of this document to the extent specified herein.

AIR-STD-15/6E(1) 27 Aug 99 Guide Specification (Minimum Quality Standards) For Aviation Fuels: NATO F-34, F-35, F-40, and F-44

AIR-STD-15/7G(1) 3 Mar 98 Guide Specification for Petroleum Base (H-515,H-520 AND C-635) and Polyalphaolefin Base (H-537, H-538 AND H-544) Aviation Hydraulic Fluids

AIR-STD-25/3B 8 Dec 00 Aircraft Servicing, Hazard, and Emergency Markings

AIR-STD-25/11B 23 Jun 95 Diameters for Aircraft Gravity Filling Orifices

AIR-STD-25/12A(2) 24 Aug 91 Picketing or Tiedown Fittings for Shipborne Aircraft (Including Helicopters)

ANSI Z136.1-2000 Safe Use of Lasers

IEEE C95.1- 1999 IEEE Standard for Safety Levels with Respect to Human Exposure to Radio Frequency Electromagnetic Fields, 3 kHz to 300 GHz

SAE-AS5440 1 Apr 98 Hydraulic Systems, Aircraft, Design and Installation Requirements For

SAWE RP7C 18 May 02 Mass Properties Management and Control for Military Aircraft

SAWE RP8A 1 Jun 97 Weight and Balance Data Reporting Forms for Aircraft (including Rotorcraft)

STANAG-2946 ED.1(4) 21 Oct 86 Forward Area Refueling Equipment

STANAG-3104 ED.6(6) 7 Oct 98 Identification of Aircraft and Missile Pipelines and Electrical Conduits

STANAG-3109 ED.5(6) 14 Oct 98 Symbol Marking of Aircraft Servicing and Safety/Hazard Points

STANAG-3212 ED.6(1) 20 Nov 98 Diameters for Gravity Filling Orifices

STANAG-3294 ED.4(1) 17 Feb 98 Aircraft Fuel Caps and Fuel Cap Access Covers

STANAG-3516 ED.5 27 Jan 03 Electromagnetic Interference, Test Methods for Aircraft Electrical and Electronic Equipment

STANAG-3614 ED.5 7 Jan 02 Electromagnetic Environmental Effects Requirements for Aircraft Systems and Equipment

STANAG-3632 ED.5 30 Dec 85 Aircraft and Ground Support Equipment Electrical Connections for Static Grounding

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STANAG-3766 ED.3(1) 9 Sep 97 Grease Nipples

STANAG-3856 ED.1 9 Oct 98 Protection of Aircraft, Crew and Sub-Systems in Flight against Electrostatic Charges –AEP-29

STANAG-4198 ED.1(4) 8 Mar 94 Parameters and Coding Characteristics that must be Common to Assure Interoperability of 2400 BPS Linear Predictive Encoded Digital Speech

STANAG-4209 ED.2 4 Aug 95 NATO Multi-Channel Tactical Digital Gateway – Standards for Analogue to Digital Conversion of Speech Signals

Copies of AIR-STD and STANAG documents may be obtained from:


Copies of the ANSI and IEEE documents may be obtained from:

http://webstore.ansi.org/ansidocstore/default.asp?

Copies of the Society of Allied Weight Engineers (SAWE) documents may be obtained from:

http://www.sawe.org/docs/rec_pract/rp.html

2.4 Order of PrecedenceIn the event of a conflict between the text of this document and the references cited herein, (except for related specification sheets) the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained.

3 System Requirements

3.1 General Requirements

3.1.1 Start Timeline

3.1.1.1 Normal Temperature Start(TT1) All systems, except the Target Acquisition Sensor Suite (TASS), shall be fully operational (meets all requirements) within 5 minutes of engine (or Auxiliary Power Unit (APU) if installed) start initiation when ambient temperature is between 0oF and 122oF.

(O) All systems, except TASS, shall be fully operational within 1 minutes of engine (or APU, if installed) start initiation when ambient temperature is between 0oF and 140oF.

3.1.1.2 Cold Weather Start(TT1) All systems except displays shall be fully operational within 5 minutes of engine (or APU, if installed) start initiation when ambient temperature is between -40oF and 0oF.

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(O) All systems except displays shall be fully operational within 1 minutes of engine (or APU, if installed) start initiation when ambient temperature is between -40oF and 0oF.

3.1.1.3 Cold Weather Start – Displays(TT1) Multifunction displays shall be fully operational within 10 minutes of engine (or APU, if installed) start initiation when ambient temperature is between -40oF and 0oF.

(O) Multifunction displays shall be fully operational within 3 minutes of engine (or APU, if installed) start initiation when ambient temperature is between -40oF and 0oF.

3.1.1.4 Display of Critical Start Parameters(T) Critical start parameters, such as engine turbine temperature and speed, shall be viewable to the pilot prior to main engine start initiation when ambient temperature is between -40oF and 122oF.

(O) Critical start parameters, such as engine turbine temperature and speed, shall be viewable to the pilot prior to main engine start initiation when ambient temperature is between -40oF and 140oF.

3.1.1.5 Wind Impact(TT2) The system shall startup, shutdown and be operable in winds < 35 knots, from any direction.

3.1.2 Crew Equipment Stowage

3.1.2.1 Items to be Stowed(TT2) The ARH shall provide sufficient space for mounting or storage of critical crew equipment including a survival kit, NSN 1680-01-362-6323, first aid kit, NSN 6545-01-094-8412 (accessible by both flight crewmembers in flight), a fire extinguisher IAW MIL-E-52031D (accessible by both flight crewmembers in flight), 2 Meals Ready-to-Eat (MREs), 4 of quarts water, and mission publications and charts. Space is required to store 2 kit bags (one each per aviator) with 2 Kevlar helmets, not to exceed 4 ft3.

3.1.2.2 Impact to Specification(T) Equipment stowage shall not prevent conformance to this specification of any onboard system, reduce crashworthiness, or impede aircrew safety.

3.1.3 Wire Strike

3.1.3.1 Forward Flight Protection(T) The ARH shall have a wire strike protection system which provides protection against wire strikes to the aircraft in forward flight.

3.1.3.2 Area of Protection(TT2) Protection shall be provided for CFI% (Contractor Furnished Information) of the projected forward area of the aircraft (excluding the main and tail rotors).

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3.1.3.3 Wire Parameters(TT2) The system shall deflect and/or cut a taut wire up to the size and strength of a 10 mm steel wire rope with an ultimate breaking strength of 11,000 lbs., at a strike angle of 60-90 degrees (cable axis to aircraft centerline in the plane which contains the aircraft longitudinal and lateral axes) and for airspeeds in excess of 40 kts.

3.1.4 Airframe Growth Capability(TT1) The ARH shall have the capability to accept engines with increased shaft horsepower and associated airframe structural and dynamic component improvements to include the rotor and drive-train system, resulting in an overall power growth of at least 8%.

3.1.5 Ozone Depleting Chemicals(T) The ARH program (design, components, testing, production, installation, maintenance, support and disposal) shall not introduce ozone depleting chemicals.

3.1.6 Data Plates and Product Marking

3.1.6.1 Identification and Markings (TT1) The ARH shall include identification on major structural assemblies and spare parts IAW MIL-STD-130L.

3.1.6.2 Aircraft Data Plate(TT1) The ARH shall be provided with an aircraft data plate that is viewable from outside of the cockpit IAW MIL-STD-130L.

3.1.6.3 Finish (TT1) The exterior finish of the ARH shall be in accordance with TM 55-1500-345-23.

3.1.6.4 Component Markings(T) System components and documentation shall display warnings and cautions to prevent soldier injury or component/system damage.

(TT3) Symbol marking of aircraft service and safety/hazard points shall comply with the requirements of STANAG 3109 (Symbol Marking of Aircraft Servicing and Safety/Hazard Points) and AIR STD 25/3B (Aircraft Servicing Hazard and Emergency Markings). The identification of aircraft and missile pipelines and electrical conduits shall comply with requirements of STANAG 3104 (Identification of Aircraft and Missile pipelines and Electrical Conduits).

3.1.6.5 Part Serialization(T) All Critical Safety Item (CSI) parts, life limited parts, and or parts requiring traceability shall be serialized. This includes but is not limited to gears, bearings, shafts, flanges, and major housing assemblies. Records shall be maintained so that each serialized component is traceable to the forging and heat treatment lot identification number, where applicable.

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3.1.7 Transparencies(TT1) All windshield panels shall be shatterproof, defoggable, and shall be able to withstand air loads imposed by flight within the structural design envelope.

3.1.8 Shipboard OperationsShipboard operations include landing, tie down, takeoff, rearm, and refueling.

3.1.8.1 Capability on Navy Ships(TT1) The ARH shall navigate and operate from Landing Helicopter Dock (LHD) and Landing Helicopter Assault (LHA) classes of US. Navy amphibious assault ships while complying with applicable sections of the Electromagnetic Environmental Effects (E3) requirements of this document, rotor stop timeline requirements, rotor flap stop, rotor stowage, blade fold, and use of shipboard support equipment (e.g. tugs).

(TT2) The ARH shall be capable of safe secure tie down in sea state 6 conditions (moderate weather) and operations up to sea state 4. Sea states are defined in the Navy Dive Manual, Figure 6-7, Sea State Chart. Main rotor blade removal shall be permissible. MIL-T-81259B shall be used as a guide for tie down.

(TT3) The ARH shall be capable of safe secure tie down when using hooks as defined in AIR-STD-25/12A(2).

(O) The ARH shall be fully compatible with shipboard operation without restrictions.

3.1.8.2 Service(TT1) The ARH shall be compatible with standard U.S. Navy ship pressure and gravity refueling facilities and electrical service normally used for aviation.

3.1.9 Reconfigurable(TT2) The ARH shall be reconfigurable within 30 minutes to meet operational needs including reconfiguration for extended range / endurance missions.

(O) The ARH shall be reconfigurable within 15 minutes.

3.2 Performance Characteristics

3.2.1 Configuration

3.2.1.1 Weights

3.2.1.2 Weight and BalanceThe aircraft weight and balance classification shall be determined according to AR 95-1, paragraph 7-3. If no classification, then aircraft is class 2.

3.2.1.2.1 Empty Weight The empty weight used for performance shall be as defined in Society of Allied Weight Engineers (SAWE) Recommended Practices (RP) 7 and SAWE RP 8, Part I. The weight empty shall include the weights of all armament and

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Aircraft Survivability Equipment (ASE) provisions as well as sensor assemblies.

3.2.1.2.2 Basic Weight – Standard Armed Reconnaissance ConfigurationThe basic weight shall consist of the empty weight plus trapped and unusable fuel, full hydraulic and oil systems, and all fixed equipment including crew station armor, non-expendable active and passive countermeasures, weapons pylons, two M-260 seven-shot rocket launchers, and auxiliary fuel tanks (if required).

3.2.1.2.3 Operating Weight – Standard Armed Reconnaissance Configuration The operating weight shall consist of the basic weight, plus standard crew of two with basic combat Air Warrior ensemble, emergency equipment not included in the basic weight, aircrew baggage and other required equipment (e.g. Survival Kit (32 lbs), NSN 1680-01-362-6323 and Air Warrior Microclimatic Unit A-Kit).

3.2.1.2.4 Gross Weight - Standard Armed Reconnaissance ConfigurationThe Standard Armed Reconnaissance Configuration gross weight shall consist of operating weight plus the weights of all expendable countermeasures, fourteen (14) 2.75 inch rockets, full main useable fuel (JP-8), and full auxiliary fuel (if any quantity of auxiliary fuel is required to meet the range or endurance requirements below).

3.2.1.2.5 Unit WeightsThe following weights shall be used for useful loads.

3.2.1.2.5.1 Standard Crew

250 lbs each -- Standard crew weight is based on 75th percentile male, including Air Warrior basic combat ensemble with two quarts water, one Kevlar helmet, one MRE, and mission publications and charts.

3.2.1.2.5.2 Fluids (per gallon)

Fuel: MIL-DTL-83133 JP-8 -- 6.7 lb

Oil: MIL-PRF-23699 – 8.4 lb

Hydraulic: MIL-PRF-83282 – 7.1 lb

3.2.1.2.5.3 Ordnance

2.75 inch rocket -- 30.4 lb each

3.2.1.2.5.4 Stores Equipment

M260 seven (7) shot Rocket Launcher (empty) – 68.6 lb for two.

3.2.1.3 Center of Gravity Normal Limitations(TT1) The operational longitudinal and lateral center of gravity ranges for normal loading shall fall within the aircraft design structural, and stability

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and control limitations. The aircraft shall remain within the normal center of gravity limits during all missions IAW the Pilot Accommodations requirement of this specification.

3.2.2 Cruise Airspeed(TT1) The ARH, at the standard armed reconnaissance configuration gross weight, shall achieve a cruise airspeed of at least 100 knots true airspeed (KTAS), at 4,000 ft pressure altitude and 95o

Fahrenheit (4k/95oF), using no more than maximum continuous power (MCP).

(O) The ARH, at the standard armed reconnaissance configuration gross weight, shall achieve a cruise airspeed of at least 120 KTAS, at 6,000 ft pressure altitude and 95o Fahrenheit (6k/95F), using no more than MCP

3.2.3 Hover Out of Ground Effect (HOGE)(T) At take-off using Intermediate Rated Power (IRP- 30 minute rating), the ARH, at the standard armed reconnaissance configuration gross weight, shall perform an out-of-ground effect hover (A skid or wheel height of at least one and one half (1.5) main rotor diameters above ground level) at 4k/95.

(O) At take-off using IRP, the ARH, at the standard armed reconnaissance configuration gross weight shall perform an out-of-ground effect hover at 6k/95.

3.2.4 Range(T) The ARH, in the standard armed reconnaissance configuration, shall achieve a range of 212 km at 4k/95 using a 1-minute takeoff, cruise at .99 best range airspeed (Vbr), with 20-minute reserve at best endurance airspeed (Vbe), profile. Auxiliary fuel may be used to meet this requirement.

(O) The ARH, in the standard armed reconnaissance configuration, shall achieve a range of 424 km at 6k/95 using a 1-minute takeoff, cruise at .99 Vbr, with 20-minute reserve at Vbe, profile. Auxiliary fuel may be used to meet this requirement.

3.2.5 Operational Radius(TT1) The ARH, in the standard armed reconnaissance configuration, shall achieve an operational radius of 75 km at 4k/95 using a 1-minute takeoff, cruise at .99 Vbr to objective area, 1 hour station time while cruising at Vbe, cruise at .99 Vbr to return, with 20 minute fuel reserve at Vbe, profile. Auxiliary fuel may be used to meet this requirement.

(O) The ARH, in the standard armed reconnaissance configuration, shall achieve an operational radius of 150 km at 6k/95 using a 1-minute takeoff, cruise at .99 Vbr to objective area, 1 hour station time while cruising at Vbe, cruise at .99 Vbr to return, with 20 minute fuel reserve at Vbe, profile. Auxiliary fuel may be used if required.

3.2.6 Endurance(T) The ARH, in the standard armed reconnaissance configuration, shall achieve an endurance of 2.2 hours at 4k/95 using a 1-minute takeoff, cruise at Vbe, with 20-minute fuel reserve at Vbe, profile. Auxiliary fuel may be used to meet this requirement.

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(O) The ARH, in the standard armed reconnaissance configuration, shall achieve an operational endurance of 3.0 hours at 6k/95 using a 1-minute takeoff, cruise at Vbe, with 20-minute fuel reserve at Vbe, profile. Auxiliary fuel may be used to meet this requirement.

3.3 Air Vehicle

3.3.1 Usage Spectrum

Table I Usage Spectrum

CONDITIONS PERCENT LIFE

NORMAL START 1.0000

NORMAL SHUTDOWN 1.0000

IDLE 1.0000

TAKEOFF normal 0.8000

vertical 0.1000

HOVERING steady 7.6000

hover turns left 0.3300

right 0.3300

control reversals longitudinal 0.0100

lateral 0.0100

rudder 0.0100

sideward flight stabilized left 0.4000

left acceleration 0.0250

left deceleration 0.0250

stabilized right 0.4000

right acceleration 0.0250

right deceleration 0.0250

rearward flight 0.4500

normal landing 0.5050

auto to power recovery 0.1300

full auto landing 0.0050

.1 %VH 5.0500

.2 5.0500

.3 5.0500

.4 4.1400

.5 3.7100

.6 1.6400

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.7 2.4900

.8 4.5600

.9 3.7100

1.0 1.0400

1.11 0.0600

ACCELERATION normal hover to climb A/S 0.6000

climb A/S to .9VH 0.4000

max rate hover to climb A/S 0.2400

climb A/S to .9VH 0.1600

DECELERATION normal hover to descent A/S 0.3360

descent A/S to .9VH 0.5040

max rate hover to descent A/S 0.2240

descent A/S to .9VH 0.3360

CLIMB

max continuous

power 1.8200

max engine power 0.2800

PARTIAL POWER DESCENT 3.4000

CONTROL REVERSALS AT VH longitudinal 0.0100

lateral 0.0100

rudder 0.0100

NORMAL TURNS to the left .3 VH 1.5 G 0.3350

2.0 G 0.0074

.7 VH 1.5 G 1.2293

2.0 G 0.2162

MAX G 0.0079

.9 VH 1.5 G 1.0364

2.0 G 0.0611

MAX G 0.0072

1.11 VH 1.5 G 0.1429

2.0 G 0.0066

to the right .3 VH 1.5 G 0.3350

2.0 G 0.0074

.7 VH 1.5 G 1.2293

2.0 G 0.2162

MAX G 0.0079

.9 VH 1.5 G 1.0364

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2.0 G 0.0611

MAX G 0.0072

1.11 VH 1.5 G 0.1429

2.0 G 0.0066

SYMMETRIC PULLUP .3 VH 1.5 G 0.4832

2.0 G 0.0107

.7 VH 1.5 G 1.7733

2.0 G 0.3122

MAX G 0.0113

.9 VH 1.5 G 1.4950

2.0 G 0.0882

MAX G 0.0103

1.11 VH 1.5 G 0.2062

2.0 G 0.0096

ROLLING PULLUP to the left .3 VH 1.5 G 0.0604

2.0 G 0.0014

.7 VH 1.5 G 0.2216

2.0 G 0.0390

MAX G 0.0014

.9 VH 1.5 G 0.1868

2.0 G 0.0110

MAX G 0.0014

1.11 VH 1.5 G 0.0258

2.0 G 0.0012

to the right .3 VH 1.5 G 0.0604

2.0 G 0.0014

.7 VH 1.5 G 0.2216

2.0 G 0.0390

MAX G 0.0014

.9 VH 1.5 G 0.1868

2.0 G 0.0110

MAX G 0.0014

1.11 VH 1.5 G 0.0258

2.0 G 0.0012

PUSHOVERS.3 VH (.50 - .75G's) 0.0450

.7 VH 0 - .25G's 0.0014

.25 - .50G's 0.0105

.50 - .75G's 0.1785

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.9 VH 0 - .25G's 0.0009

.25 - .50G's 0.0051

.50 - .75G's 0.1390

1.11 VH .25 - .50G's 0.0005

.50 - .75G's 0.0191

YAWED FLIGHT .9 VH to the left 0.0500

to the right 0.0500

POWER TO AUTOROTATIONS .5 VH 0.0300

VH 0.0100

AUTOROTATION TO POWER AT VNE (autorotation) 0.0300

STABILIZED AT VNE (autorotation) 0.1500

TURNS AT VNE (autorotation) to the left 0.0500

to the right 0.0500

PULLUP AT VNE (autorotation) 0.0500

HOVERING

360 degree clearing turn

left 0.8251

360 degree clearing turn

right 0.8251

control reversals longitudinal 0.0277

lateral 0.0277

rudder 0.0277

steady 1.5320

RUN-ON LANDING 0.2475

LATERAL AGILITY35KTS left to

quick stop 0.2863

35KTS right to quick stop 0.2863

35KTS left with kickout and accel 0.2863

35KTS right with kickout and accel 0.2863

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POP UP at 20KTS 0.4288

at 40KTS 0.4288

SIDE FLARE WITH KICKOUT to the left At 40KTS 0.2863

at 60KTS 0.2863

to the right At 40KTS 0.2863

at 60KTS 0.2863

MAXIMUM YAW to the left At 40KTS 0.1426

at 60KTS 0.1426


at 60KTS 0.1426

TERRAIN TURNS to the left at 20KTS 1.1431

At 40KTS 1.6431

at 60KTS 1.6431

to the right at 20KTS 1.1431

At 40KTS 1.6431

at 60KTS 1.6431

PEDAL TURNS to the left At 40KTS 0.4288

at 60KTS 0.4288


at 60KTS 0.4288

TERRAIN PULLUPS at 40KTS 1.3931

at 60KTS 1.3931

TERRAIN PUSHOVERS at 40KTS 1.3931

at 60KTS 1.3931

DASH/QUICK STOP

accel to 60KTS to quick stop 2.8586

accel to VH to quick stop 2.2840

TOTAL 100.0000

3.3.2 Handling Qualities(T) The ARH shall have at least level 2 handling qualities for all Scout Rotorcraft Category Mission Task Elements as defined by ADS-33E-PRF, Table I.

(O) The ARH shall have level 1 handling qualities for all Scout Rotorcraft Category Mission Task Elements as defined by ADS-33E-PRF, Table I.

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3.3.2.1 Rough Field Operations(TT2) The ARH shall be capable of performing all combat missions from unprepared sod and clay/dirt fields on slopes of up to 10 degrees.

3.3.2.2 Autorotation(TT1) The ARH shall be capable of entering power-off autorotation at any speed from hover to maximum forward speed up to maximum gross weight, including jettisonable stores, and land safely (no further damage to aircraft nor injury to the aircrew) minus jettisonable stores. The transition from powered flight to autorotative flight shall be established smoothly, with adequate controllability, and with a minimum loss of altitude. It shall be possible to make this transition safely when initiation of the manual collective pitch control motion has been delayed for at least 1 second following loss of power without exceptional piloting skill or exceptionally favorable conditions. At no time shall the rotor speed fall below a safe minimum transient autorotative value. At a touchdown speed of 35 knots on a level paved surface it shall be possible to bring the helicopter to a stop in less than 200 ft.

(O) The ARH shall be capable of entering power-off autorotation at any speed from hover to maximum forward speed up to maximum gross weight, including jettisonable stores, and land safely (no further damage to aircraft nor injury to the aircrew) with jettisonable stores. It shall be possible to make this transition safely when initiation of the manual collective pitch control motion has been delayed for at least 2 second following loss of power without exceptional piloting skill or exceptionally favorable conditions.

3.3.3 Human Systems Integration

3.3.3.1 Pilot Accommodation(TT2) The ARH shall accommodate the 5th percentile female to 95th percentile male soldier IAW NATICK TR 89-044 attired in all personal and protective clothing/equipment to include the Air Warrior integrated ensemble for critical body dimensions including flexible body armor, microclimatic cooling system, survival gear carrier, over-water equipment carrier, and flotation collar assembly, MOPP gear, and antiexposure equipment (target Army Aviator population).

3.3.3.2 Controls and Displays

3.3.3.2.1 Image Intensification (I²) Compatibility(T) Aircraft displays and cockpit lighting shall be compatible with Type 1 Class A image intensification devices and systems as defined in MIL-STD-3009. Aircraft and cockpit lighting and markings shall be adequate to perform all mission requirements while minimizing detection by light intensification devices and systems.

(TT1) Image Intensification Devices shall provide a means for display of heads up symbology to include the major modes of the Vertical Situation Display (e.g., Normal, Hover, and Hover Bob-up) and provide display of weapons status.

3.3.3.2.2 Standards(TT2) New and / or modified controls and displays shall be IAW MIL-STD-1472 and MIL-STD-2525.

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3.3.3.2.3 Display Configuration(TT2) The system’s primary flight instruments, i.e. Attitude Direction Indicator (ADI), Horizontal Situation Indicator (HSI), Airspeed Indicator, Altimeter, and Vertical Speed Indicator (VSI), shall be displayed in identical configurations at each flight crew station.

3.3.3.2.4 Visibility(TT1) The system displays shall be visible and readable from the flight crewmember’s design eye position under direct and indirect sunlight (up to 10,000 foot candles), reduced light and unaided night conditions, and shall not affect external vision.

3.3.3.2.5 Readability(TT1) Displays shall be readable to the degree of accuracy required by the flight crewmembers to perform the intended mission without requiring the flight crewmember to assume an uncomfortable, awkward or unsafe position.

3.3.3.3 Lighting (TT2) The ARH shall provide lighting uniformity and balance of all displays.

3.3.3.3.1 Uniformity (TT2) Lighting across individual displays shall meet the following uniformity standard: the ratio of the standard deviation of the indicator element luminances to mean indicator luminance shall be not more than 0.25, using eight or more equally spaced test measurements.

3.3.3.3.2 Luminance Balance (TT2) Display luminance on individual dimming circuits shall be balanced such that the mean indicator luminances of any two instruments shall not vary by more than 33% (balance) across the range of full ON to full OFF.

3.3.3.3.3 Luminance (TT2) The luminance of all markings on the displays and panels shall be 1.0+/-0.5 foot lamberts when illuminated by the integral lighting system and at the rated voltage only.

3.3.3.4 Emergency Egress (TT1) The ARH shall accommodate the emergency egress of the crew, as defined in the Pilot Accommodation paragraph above, in no more than 20 seconds while aircraft is resting on its side assuming fuselage and structure deformation has not occurred.

3.3.4 Engine/Fuel System

3.3.4.1 Engine(T) The engine shall be either military (Army Rotorcraft) qualified to AV-E-8593, certified to 14 CFR, Part 33 and currently operating on US Army aircraft under an Airworthiness Release (AWR) / Interim Statement of Airworthiness Qualification (ISAQ) authority, or certified to 14 CFR, Part 33 with the following additional testing/analysis performed to satisfy the requirements for an AWR:

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1. Electromagnetic Environmental Effects (E3)/Electromagnetic Interference (EMI)/Electromagnetic Pulse (EMP) verified by analysis and test IAW ADS-37-PRF

2. Vibration IAW MIL-STD-810, Method 514.5, Procedure I, and Method 519.5, Procedure IV.

3. Power Turbine Overspeed Control System Analysis IAW the Airworthiness Qualification Plan (AQP).

4. Engine Ingestion IAW the AQP.

5. Engine Component Lifing IAW the AQP.

3.3.4.1.1 Engine Inlet Sand and Dust Protection

3.3.4.1.1.1 Filtration

(TT3) The engine inlet shall have a sand and dust filtration system that removes greater than 98% of AC Fine and AC Coarse sand.

3.3.4.1.1.2 Characteristics

(TT3) The variation in total pressure and total temperature at the engine inlet face shall not be greater than that established by the engine manufacturers specification.

3.3.4.1.2 Exhaust Subsystem

3.3.4.1.2.1 Collection

(TT2) The exhaust subsystem shall not collect fuel, oil, rain, snow, or Foreign Object Debris (FOD).

3.3.4.1.2.2 Drainage

(TT2) The exhaust subsystem shall provide for drainage outside the aircraft structure.

3.3.4.1.2.3 Exhaust Gases

(TT1) Exhaust gases shall be directed away from the crew and troop/cargo compartment, fluid drains, air intakes, flammable aircraft components, and ground vegetation and shall not impinge upon any portion of the aircraft.

3.3.4.1.2.4 Induced Loads

(TT1) The exhaust subsystem shall not induce loads or moments to the engine in excess of the engine qualification limits.

3.3.4.1.3 Engine Drains-Nacelle

3.3.4.1.3.1 Fluid Entrapment

(TT2) The subsystem shall be free of traps or configurations that could accumulate vapor and fluid.

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3.3.4.1.3.2 Drains

(TT1) Drains for the engine compartment shall be provided which drain fuel at a rate equal to or greater than the maximum fuel flow rate that could result from a severed fuel line.

3.3.4.1.4 Vibration(TT1) The air vehicle shall not induce vibration to the engine that exceeds the engine qualification limits.

3.3.4.2 Fuel System (TT1) The fuel system shall prevent flammable fluid spillage or ignition during survivable crash impacts as defined in the Crash Survival Design Guide, TR 89-D-22E.

3.3.4.2.1 Fuel Compatibility (TT1) The system shall meet all operating requirements with fuel conforming to MIL-DTL-5624, Grade JP-4 / JP-5, or JP-8 / JP-8 +100 per MIL-DTL-83133, or commercial equivalents, at fuel temperatures to 135o F.

(TT3) The system shall comply with the requirements of AIR STD 15/6E-Guide Specifications (Minimum Quality Standards) for Aviation Fuels: NATO F-34, F-35, F- 40, and F-44.

3.3.4.2.2 Refueling / Defueling(T) The main fuel system shall perform both gravity and pressure-refueling and defueling operations with or without engine(s) operating. Pressure refueling shall not require electrical power. The system shall prevent tank over pressurization in the event of a refueling system malfunction. Pressure refueling capability shall not restrict hot-refueling at Forward Arming and Refuel Points.

(TT3) The ARH shall interface with standardized refueling equipment as defined in STANAG-2946.

3.3.4.2.3 Single Point Refueling / Defueling(TT3) All fuel tanks, both internal and external, shall be single point refuelable / defuelable.

3.3.4.2.4 Fuel Quantity Gauging(TT1) The system shall display to the flight crew fuel quantity in pounds. A low fuel level warning system entirely independent of the gauging system shall be provided to indicate when the fuel quantity is at a reserve of approximately 20 minutes at normal cruise. See paragraph 6.5.

3.3.4.2.5 Fuel Tanks

3.3.4.2.5.1 Construction

(TT1) The main and any internal or external auxiliary fuel tanks shall be crashworthy IAW MIL-DTL-27422.

(TT3) The diameters of the system gravity filling orifices shall comply with the requirements of STANAG 3212 (Diameters for Gravity Filling Orifices) and AIR STD 25/11 (Diameters for Aircraft Gravity Filling Orifices). The system fuel access caps covers and fuel cap access covers

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shall comply with the requirements of STANAG 3294 (Aircraft Fuel Caps and Fuel Cap Access Covers).

3.3.4.2.5.2 Drop Test

(TT1) The tanks shall withstand a drop from a height of 65 feet while filled with water to normal capacity with all air removed and exhibit no subsequent leakage.

3.3.4.2.5.3 Fuel Tank Removal/Installation

(TT2) All fuel tank support structures shall be separate from landing gear structure. Provisions shall be made for removal and installation of each tank without disturbing any major component of the structure and without the use of peculiar ground support equipment.

3.3.4.2.5.4 Fuel Cell Ballistic Capability

(TT1) Internal fuel cells shall be self-sealing when penetrated by a fully-tumbled 12.7 mm projectile except for the 20 minute fuel level which shall be self-sealing to 14.5 mm projectiles.

3.3.4.2.6 Fuel Line Ballistic Capability(TT2) All internal fuel feed lines shall be self-sealing when penetrated by a 12.7 mm projectile.

3.3.4.2.7 Auxiliary Fuel SystemIf an auxiliary fuel system is provided it shall meet the following:

3.3.4.2.7.1 Fuel Transfer System

(TT1) A non-pressurized fuel transfer system shall be used.

3.3.4.2.7.2 Management

(TT2) A fuel management system shall provide both automatic and manual fuel transfer with fully integrated and accurate quantity measurement for all internal and/or external main and auxiliary tanks. The system shall be operable and readable by both flight crewmembers.

3.3.4.2.7.3 Crashworthiness

(TT1) All auxiliary (internal and external) hoses, fittings, and connections shall be crashworthy IAW ADS-50-PRF.

3.3.4.3 Engine Control Subsystem

3.3.4.3.1 Controls(TT1) The subsystem shall provide automatic and manual engine controls.

3.3.4.3.2 Rotor Speed(TT1) The subsystem shall automatically maintain rotor speed (rpm) and provide automatic engine load (torque) equalization if dual-engine equipped.

3.3.4.3.3 Start and Abort(TT1) The subsystem shall start with automatic sequencing and shall provide abort capability of the start sequence and/or provide starter assist beyond normal cutout speed.

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3.3.4.3.4 Motoring(TT2) The subsystem shall provide motoring sequencing for engine cooling and water washing.

3.3.4.3.5 Control System Single Failure(TT1) No single failure or malfunction in any propulsion control shall cause the failure of any other subsystem.

3.3.4.4 Fire Extinguishing System (Dual Engine Only)(TT2) If a dual engine installation, the subsystem shall provide a multiple-shot fire extinguishing capability for the engines and the APU. The system shall automatically activate the fire extinguishing capability in event of crashes that exceed 14.5 g's for a duration of at least 12 milliseconds. The system shall indicate the charge status of the fire extinguishing units on the aircraft to facilitate inspection.

3.3.5 Drive Subsystem

3.3.5.1 Life Limits(TT1) All drive subsystem components shall have a minimum CFI hour life, based on fatigue related failures, when operated in accordance with the usage spectrum. The contractor shall define the power and time limits associated with usage spectrum operation at powers above the gearbox power rating up to the maximum input power. There shall be no fatigue or wear related failure to gearbox dynamic components for operation at any power level (and its associated duration) which can be input (on a one-time basis) by the engine(s) or through the rotor system. Fatigue calculations shall be based on 3 working curves.

(TT3) All drive subsystem components shall have a minimum 4500 hours life, based on fatigue- related failures, when operated in accordance with the usage spectrum.

3.3.5.1.1 Gears(TT1) At the gearbox rated power, all gears shall have a minimum life of CFI cycles in tooth bending, and CFI hour minimum life in tooth contact, using standard gear life calculation methodologies. The influence of gearbox deflections shall be included in the life analysis. Gears shall be insensitive to scoring for all possible combinations of load and temperature.

(TT3) At the gearbox rated power, all gears shall have infinite life (>107 cycles) in tooth bending, and 4500 hours life in tooth contact, using standard gear life calculation methodologies. For dual-engine drive gearboxes, the gears located before the gear which combines the load from each engine shall have infinite life in tooth bending, and 4500 hours life in tooth contact, at the gearbox one engine inoperative (OEI) rating.

3.3.5.1.2 Bearings(TT1) Unless otherwise specified, all rolling element bearings shall have a minimum B10 life of CFI hours based on operation at 71 % of the gearbox power rating.

(TT3) Unless otherwise specified, all rolling element bearings shall have a minimum B10 life of 4500 hours based on operation at 71% of the gearbox power rating. Unless otherwise specified for dual-engine drive gearboxes, the bearings located before the gear which combines the load from each engine shall have a minimum B10 life of 4500 hours based on operation at 71% of the

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gearbox OEI rating. Rolling element bearings in magnesium, aluminum, or composite housings shall be installed in liners which are retained or locked by a positive method to prevent rotational and axial motion.

3.3.5.2 Lubrication System(TT1) Lubrication shall be provided at the required pressure and flow rate to all required components and accessories at all allowed gearbox attitudes. Suitable means shall be provided for setting the gearbox internal pressure and flow to the required level during steady state ground operation, and for maintaining required gearbox internal pressures under all operating conditions and gearbox attitudes. Breathers shall be equipped with filtration devices which remove air-borne particles.

(TT3) Breathers shall be equipped with filtration devices which remove air-borne particles of 10-microns or larger. Breathers shall be arranged to prevent loss of oil from the gearbox under all operating conditions and gearbox attitudes.

3.3.5.2.1 Lubrication(TT1) The system gearboxes shall incorporate a lubrication system using oil conforming to DOD-PRF-85734, MIL-PRF-23699, or, for cold weather operation below -20OF, MIL-PRF-7808. The lubrication system shall provide lubricant to all required components and accessories under all attitude conditions which may be imposed by operation of the aircraft as allowed by the aircraft specification. Gearboxes and accessories which are lubricated by the gearbox lubrication system shall be adequately lubricated during autorotation. Failure of a gearbox-driven accessory or an accessory lubricated by the gearbox lubrication system shall not cause failure of the gearbox, and shall not contaminate the gearbox lubrication system with debris from the accessory.

(TT3) All oil passages connecting points in the same gearbox shall be located within the gearbox and shall incorporate jet-protection screens which prevent the lubricating jets from becoming clogged with debris.

3.3.5.2.2 Loss of Lubrication(TT1) All transmissions and gearboxes, including clutch mechanisms, shall function for a minimum of 30 minutes after complete loss of the lubricant from the primary lubrication system. Operational conditions shall be such that the loss of lubricant occurs at maximum continuous power, followed by transition to maximum range cruise and a vertical landing, at sea level standard conditions. For dual-engine applications, the drive subsystem shall be capable of safe operation in the overrunning mode for at least 30 minutes with complete loss of gearbox lubrication. For single engine aircraft, the drive subsystem shall be capable of safe operation in the overrunning mode for at least 5 minutes.

3.3.5.2.3 Pumps(TT2) No air traps shall exist at the lubrication pump inlet(s). The pump(s) shall provide the required oil flow rate and pressure without degradation of performance at all altitudes up to and including the helicopter’s maximum operating altitude.

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3.3.5.2.4 FiltrationFiltration size and capacity shall be CFI.

(TT1) Oil filters shall be utilized on all pressurized lubrication systems. An integral bypass shall be provided to bypass the filter element in the event the filter element becomes clogged. Suitable indications shall be provided in the event of impending and actual bypass conditions. The impending bypass indication shall be set such that a minimum of 10 hours of gearbox operation is possible before actual bypass occurs.

(TT3) The filtration ratio shall be Beta 3 > 200 and Beta 2 > 100. Filter elements shall be non-cleanable, throw-away type. Dirt holding capacity shall be sufficient to hold 25 grams AC fine test dust.

3.3.5.2.5 Cooling Fans(TT1) Failure of heat exchanger blowers shall not cause failure of the drive system or any of its components.

3.3.5.2.6 Grease Fittings(TT3) The system grease nipples shall comply with the requirements of STANAG 3766 (Grease Nipples).

3.3.5.2.7 Sensors(T) Debris sensors and oil pressure (if pressurized oil distribution system) and temperature sensors shall be provided for all oil lubricated gearboxes. The operating oil temperature and pressure shall be continuously monitored, and provisions shall be made for display of the oil pressure and temperature, as well as the operating limits, on cockpit instrumentation. Caution and warning indications for all sensors shall be provided for cockpit display to the pilot.

3.3.5.3 Vibrations and Dynamics(T) The drive subsystem and individual components shall be free of destructive vibration at all operating speeds and powers, including steady-state, autorotation, and transient operation. When the engines, accessories, rotor systems, and drive subsystem dynamic components are operated as a combined dynamic system, there shall be no dynamic coupling modes or instabilities that are destructive or limit the air vehicle for all ground and flight modes.

3.3.5.4 Overrunning Clutches(TT1) The drive subsystem shall, during autorotation and single-engine operations, immediately and automatically decouple the engine(s) not supplying torque, from the main rotor, tail rotor, and accessories. During single-engine operation, the engine not supplying torque shall be disengaged and shall permit operation of the main rotor, tail rotor, and accessories for a minimum of two hours without damage to the clutch mechanism.

3.3.5.5 Accessory Drives(TT1) A failure of the accessories that results in loss of rotation of those accessories shall not prevent the main gear box from meeting the requirements of this specification. Gears shall not have any resonances which affect the strength of the gear at all possible operating conditions. Failure of accessories shall not cause failure of the rotor drive system.

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3.3.5.6 Mechanical Gust Lock(TT2) The system shall provide mechanical locking to prevent rotation of the rotor in a horizontal 30 kt wind, or with one engine operating at ground idle. For aircraft configured with a rotor brake, the rotor brake may be used to provide mechanical locking of the rotor.

(TT3) The system shall provide mechanical locking to prevent rotation of the rotor in a horizontal 45 kt wind.

3.3.5.7 Rotor Brake (T) If a rotor brake is not installed, a rotor brake kit shall be available for ARH. Provisions for incorporation of the rotor brake kit must enable full installation at the unit level.

(TT3) A rotor brake shall be provided for ARH. With the engine(s) off, the rotor brake shall stop the main rotor from 50% speed in not more than 50 seconds and hold the rotor in the stopped position.

3.3.5.8 Drive Shaft Subsystem

3.3.5.8.1 Drive Shafting (T) Margin shall be provided between shaft whirling critical speeds and aircraft steady-state operating speeds, including idle, all flight conditions, and autorotation, to preclude any damaging vibrations or stress amplifications that exceed the design limitations. Damping of supercritical shafts shall be provided such that stress amplifications do not exceed the design limitations.

(TT1) The shafts shall be dynamically balanced and shall accommodate installation misalignment and aircraft frame deflections.

3.3.5.8.2 Couplings(T) The torque and misalignment capabilities of drive shaft couplings shall be suitable for all operational combinations of torque and speed when installed in the aircraft at the maximum permissible misalignment. Couplings shall be fail-safe.

(TT3) Replacement of couplings shall not be cause for realignment of the associated shafting.

3.3.5.8.3 Bearings(TT1) Grease-lubricated bearings shall incorporate methods for field checking, servicing, and replacement of the lubricant as required.

(TT3) A self-aligning feature shall be provided for the bearing component of each hanger bearing assembly.

3.3.5.9 Dynamic System Mean-Time-Between-Removal (MTBR) (TT2) The inherent values of MTBR and Mean-Time-Between-Removal-Requiring-Depot Return (MTBRRDR) for the major dynamic components and the inherent values of major non-dynamic component MTBR and MTBRRDR shall be as specified in Table II .

Table II Average MTBR / MTBRRDR for Dynamic Components

Average Average

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Dynamic Component MTBR (Hours) MTBRRDR (Hours)

Swashplate CFI CFI

Main Gearbox Input Module (per module) CFI CFI

Main Gearbox Accessory Module (per module) CFI CFI

Main Gearbox CFI CFI

Intermediate Gearbox CFI CFI

Tail Gearbox CFI CFI

Drive Shafts CFI CFI

Couplings (per coupling) CFI CFI

Other CFI CFI

3.3.6 Hydraulic SubsystemIf a hydraulic subsystem is provided it shall meet the following:

3.3.6.1 General Subsystem Performance (TT2) Hydraulic subsystem design and performance criteria shall be in accordance with ADS-50-PRF. Hydraulic subsystems and components thereof shall meet the performance requirements of this specification under all conditions that the aircraft may encounter within the structural limitations of the aircraft, including forces or conditions caused by acceleration, deceleration, zero gravity, negative g, or any flight attitudes obtainable with the aircraft, structural deflection, vibration, or other environmental conditions.

3.3.6.2 Hydraulic Fluid (TT1) The hydraulic subsystem and associated ground support equipment shall use MIL-PRF-83282, MIL-PRF-87257, and ADS-PRF-69 hydraulic fluid. MIL-PRF-83282 shall be the primary fluid.

(TT3) The hydraulic subsystem and associated ground support equipment shall use hydraulic fluids which comply with the requirements of AIR STD 15/7G -Guide Specification for Aviation Hydraulic Fluids (H-515, H-537, and H-538).

3.3.6.3 Redundancy(TT3) Two independent hydraulic power systems for flight control systems No. 1 and No. 2 shall be provided. Failure of one system shall not adversely affect the functioning of the other system. A single failure in another aircraft subsystem shall not incapacitate both primary power operated control systems simultaneously. Surviving system(s) should provide sufficient control for return to the intended landing area (including shipboard areas and land).

3.3.6.4 Fail Safe(T) Control sufficient to maintain emergency aircraft control shall be retained in the event of a hydraulic power failure.

3.3.6.5 Proof and Burst Pressures(TT2) Proof and burst pressures of the hydraulic systems components shall be as specified in Table II of SAE-AS5440. Operating pressure is the peak of the system pressures required to

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provide satisfactory operation of the hydraulic system under all conditions described in the General Subsystem Performance paragraph.

3.3.6.6 Removal of Entrapped Air (T) System shall provide for removal of entrapped air.

(TT3) A means shall be provided to remove entrapped air without the disconnection of lines or loosening of tubing nuts.

3.3.6.7 Fluid Level Indicator(TT1) The reservoir shall include a visual fluid level indicator that is readily accessible.

(TT3) A fluid level transducer shall be incorporated in the reservoir for continuous fluid level sensing. A cockpit indication of low fluid level warning shall be provided.

3.3.6.8 Filtration(TT1) Filtration shall be provided. The filter assemblies shall be of the disposable type and contain differential pressure indicators on the filter housing. The warning indicator shall be observable and visual access shall be gained without use of tools. Indication shall remain visible until manually reset after filter element replacement. Pressure and return filter elements shall be per MIL-F-8815, maximum 5 micron absolute and disposable. The pressure filter shall be a non-bypass type. The return filter shall be a bypass type.

(TT3) A cockpit indication of the differential pressure indicator warning shall be provided

(TT3) Reservoir fill circuit shall include a maximum 25 micron filter absolute.

3.3.6.9 Quick Disconnects(TT3) Quick disconnect couplings shall be provided for operation and external servicing of the subsystem.

3.3.6.10 Temperature Monitor(TT3) Hydraulic fluid temperature monitoring shall be provided.

3.3.6.11 Sampling Port(TT3) An inline sampling port shall be provided for each hydraulic subsystem. Sampling port shall be used for on-line hydraulic contaminant particle counters.

3.3.7 Environmental Systems(TT2) The system shall provide for the heating and ventilating of the crew station. Crew station heating shall be provided such that with an ambient temperature of -40oF an inside compartment temperature of +40oF shall be attained within 15 minutes.

3.3.8 Mechanical Stability(T) The system shall be free of critical mechanical instability at all operating conditions and configurations within the operational flight envelope.

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3.3.9 Flutter(TT1) The system including rotors, shall be free of flutter, divergence, and any other aeroelastic instability, within the operational flight envelope, at speeds up to 1.15 times the design limit speed, with and without power. The most adverse mass imbalance of the blade allowable within contractor’s production tolerances shall be accounted for in substantiating freedom from flutter and divergence.

3.3.10 Structural Design Criteria

3.3.10.1 General Strength Requirements (T) Strength and rigidity requirements shall be IAW 14 CFR, Part 27 and/or structural design criteria of the baseline aircraft. The ARH structural design criteria document shall be used for structural design of the aircraft to address structural integrity requirements.

3.3.10.2 Armament (T) The ARH shall not sustain structural damage due to firing, hang-fire and jettison recoil loads of Hellfire missiles, 2.75” rockets, or .50 caliber or 7.62mm machine guns.

3.3.10.3 Fatigue Strength

3.3.10.3.1 Critical Dynamic Component Fatigue (TT2) Components shall have retirement lives of at least 1200 hours when used in accordance with the Usage Spectrum. Component lives shall be conservatively derived so that an expected failure of less than one in the fleet life can be projected.

(TT3) Components shall have a retirement life of at least 2400 hours when used in accordance with the Usage Spectrum..

3.3.10.3.2 Airframe System Fatigue (TT2) Design service life of the airframe shall be CFI flight hours when used in accordance with the Usage Spectrum. This life requirement shall be substantiated by a safe life or damage tolerant approach. The ARH shall have adequate defect-tolerant design to meet a minimum depot inspection interval of CFI flight hours. The inspection interval shall be set so that no major damage occurs prior to the depot inspection with the specified method.

3.3.10.4 Crash Strength (T) The design crash load factors of airframe structural components shall be maintained IAW 14 CFR, Part 27 or structural design criteria. Material mechanical properties shall be based on “B” basis allowables, composite material properties shall be based on room temperature dry allowables.

3.3.11 Aircraft Mooring(TT2) A method to moor and secure the aircraft, including rotor blades, to prevent damage in 100 kt winds shall be provided.

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3.3.12 Electrical Power System(T) The ARH electrical power system shall provide power IAW any version of MIL-STD-704 or equivalent. The ARH electrical components shall have acceptable power IAW MIL-STD-704 power quality. The electrical power system shall provide backup power for flight critical functions. The ARH shall provide circuit protection for all circuits to ensure that the maximum wire temperatures do not exceed allowable temperature for all wiring.

(TT3) The ARH electrical power system shall provide power IAW MIL-STD-704F.

3.3.13 Air Vehicle Vibration(TT1) The ARH air vehicle vibration levels shall be IAW ADS-27, Section 3, Flight Regions I, II and III.

(TT3) The ARH air vehicle shall incorporate on-board vibration monitoring and diagnostics for (as a minimum) rotor track and balance functions and drive system components. The on-board system shall (as a minimum) provide diagnostic data and corrective actions to the maintainer post-flight.

3.3.14 Internal Noise(TT2) The ARH air vehicle internal noise levels shall be IAW MIL-STD-1474 requirement 7.

3.3.15 Drainage Collection(TT3) A drainage collection system shall be provided, which is sized to collect residual flammable or hazardous fluids to assure compatibility with shipboard operation and environmental requirements.

3.3.16 Exterior Lighting(T) The exterior lighting shall be installed IAW 14 CFR, Part 27, Subpart F, or MIL-STD-3009. MIL-L-6503 may be used as a guide.

(TT1) Covert lighting shall be provided IAW MIL-STD-3009.

3.3.16.1 Navigation Lights(T) Ruggedized navigation lights shall be installed IAW 14 CFR, Part 27, Subpart F, or MIL-STD-3009. MIL-L-6503 may be used as a guide, regarding field of coverage, shielding and color. The navigation lights shall have an Off mode, a Night Vision Imaging System (NVIS) compatible mode, and an Infrared (IR) mode. A function selector shall be provided and shall be operable by the flight crew.

3.3.16.2 Anti-Collision Lighting(T) Daylight and night high-intensity lights shall be installed. Lights shall be omni-directional, shall flash in alternating pattern, and shall be distinctly visible on a clear day. A switch shall be provided for the selection of daylight, night, and IR modes of anti-collision lighting. The controls shall be accessible to the flight crew.

(TT1) Ruggedized one or more anti-collision lights shall be installed IAW MIL-STD-3009. An Infrared (IR) anti-collision light subsystem shall be installed.

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3.3.16.3 Daylight High-Intensity Anti-Collision Light (TT3) The daylight high-intensity anti-collision light shall provide a minimum of 3,500 effective candlepower white light. The subsystem shall consist of one or more lights. The field of coverage must extend in each direction within 30 degrees above and below the horizontal plane of the aircraft, except that there may be solid angles of obstructed visibility totaling not more than 0.5 steradians.

3.3.16.4 Night High-Intensity Anti-Collision Light(T) The ARH shall have one or more installed and operable night high-intensity anti-collision lights. The lights shall comply with the requirements of 14 CFR, Part 27, Subpart F, or MIL-STD-3009. MIL-L-6503 may be used as a guide, regarding field of coverage (except for occlusions caused by wing-mounted stores, wing structure, and/or empennage structure), shielding, flash rate, and color.

3.3.16.5 Searchlight/Landing Light(T) One retractable rotatable landing/search light shall be installed IAW 14 CFR, Part 27, Subpart F, or MIL-STD-3009. MIL-L-6503 may be used as a guide.

3.3.17 Pilot Operability (T) The ARH shall be a dual crewstation, single-pilot operable aircraft with all systems operable from either crewstation.

(TT3) The aircraft shall be capable of single-pilot IFR operation

3.4 Mission Equipment Package (MEP)The ARH incorporates a combination off-the-shelf (OTS) and/or non-developmental item (NDI) technologies into a MEP that provides enhanced situational awareness and survivability, target acquisition, organic lethality, and robust joint interoperability.

3.4.1 Advanced Cockpit Management

3.4.1.1 Digital Cockpit(TT2) The system shall incorporate a cockpit with a digital, integrated cockpit management system with aural and visual caution and warning advisory annunciation.

(O) The system shall provide cockpit components that maximize commonality with existing Army Aviation assets.

3.4.1.2 Flight Crewmember Station Controls(T) The system shall provide control and display at each flight crewmember station for mission management, sensors, and control of installed avionics.

3.4.1.3 Redundancy(TT1) Redundant controls and displays of all flight critical systems as defined in ADS-37-PRF shall be provided. In the event of the failure of one system, the other system shall automatically assume control of all interconnected avionics and provide display information to both flight crewmembers.

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3.4.1.4 Single-Pilot Operable(T) All navigation, communication, and weapons management systems shall support single-pilot operation precluding the need for the aircrew to release flight controls and view or focus downward away from the direction of flight for prolonged periods of time.

3.4.1.5 Workload(TT2) The management system shall provide a low workload environment for the crew with a Bedford workload, or equivalent, rating not to exceed 6.5.

(O) The management system shall provide a low workload environment for the crew with a Bedford workload, or equivalent, rating not to exceed 5.0.

3.4.1.6 MFD Presentation(TT1) The color Multifunction Displays shall allow the presentation of imagery, alphanumeric characters and symbols per MIL-STD-1472 and MIL-STD-2525B, digital map display.

3.4.1.7 Compatibility with Laser Eye Protection(TT3) For compatibility with laser eye protection, displays shall use a phosphor other than P-43.

3.4.2 System Software and Processing(T) New system software development or modifications to legacy software shall be IAW RTCA/DO-178B or equivalent based on the criticality level(s) assigned or as determined through the safety assessment process.

3.4.2.1 Software Design (T) The ARH system software shall incorporate safety critical design features IAW RTCA/DO-178B or equivalent based on the criticality level(s) assigned or as determined through the safety assessment process.

3.4.2.2 Software in Firmware(T) New firmware shall meet the design assurance requirements of RTCA/DO-254, based on the criticality level(s) assigned or as determined through the safety assessment process.

3.4.2.3 Software Redundancy Management(TT1) Software shall support the use of redundant components in order to meet the system and subsystem reliability requirements.

3.4.2.4 Software Partitioning(T) New software on the aircraft shall be partitioned IAW DO-178B, or equivalent. All software resident in a given partition, such as a Flight Safety Critical Software (FSCS) partition, shall be required to meet the design and coding standards for the most critical software (highest assigned criticality level, DO-178 Level A) within that partition. Software-controlled portals separating FSCS partitions from non-FSCS partitions shall be robust enough to prevent the non-FSCS from crashing the FSCS processors.

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3.4.2.5 Software Programming Languages(T) Third generation or higher programming languages (such as Ada, C/C++) shall be used for new ARH software.

3.4.2.6 Software Code Constraints(TT1) The following programming language features shall not be used in new software code:

a. Any feature which is non-deterministic in nature (e.g. recursion)

b. Any feature, which requires dynamic memory allocation other than stack usage when allocated at compile time.

3.4.2.7 Software Initialization(T) The ARH shall execute initialization to automatically configure hardware and software components into a safe state upon initial application / reapplication of electrical power.

3.4.2.8 Software Security and Classification(T) Every configured release of ARH software source code which implements security policy shall establish trust during development that the release contains only that code necessary to meet requirements. Any portion of a software program permanently residing in any system end item shall be unclassified.

3.4.2.9 Software Fault Detection / Fault Isolation (FD/FI)(T) Failure of FD/FI-unique hardware/software in the ARH shall not degrade performance of the monitored equipment.

3.4.2.10 Software Modularity(TT3) Modular software shall facilitate compilation of individual modules and maintenance or updates. The ARH operational flight programs shall use these modular components in an effort to maximize software commonality.

3.4.2.11 Field Software Reprogrammability(TT3) Software shall be field reprogrammable. All mission equipment that contains an Operational Flight Program (OFP) shall be field programmable, that is, able to receive an upgraded or new OFP (mission-specific software). This requirement does not include embedded firmware. Software reprogramming shall not require removal of any of the ARH components from the aircraft. Software reprogramming shall not require the use of unique cables, connectors or adapters. Software reprogramming shall use one of the existing busses that the ARH communicates on. The ARH shall incorporate security features to prevent unauthorized or unintended changes. All new ARH versions will have a security authentication code keyed to aircraft serial number that will be verified by the ARH before reprogramming begins.

3.4.2.12 Software Undesired Functions and Anomalies(TT3) The ARH software shall prevent undesired function execution. Data anomaly management design features shall be implemented in the software.

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3.4.2.13 Software Configuration Display(TT3) The ARH shall make available for display the software and hardware (which includes firmware) configuration of each of the aircraft computers to either or both flight crew stations while on the ground. Such identification shall be available to maintenance personnel while utilizing external power upon request.

3.4.2.14 Memory and Throughput(TT2) System processing, memory, timing, bus loading, and input/output shall be sized to provide 25 % reserve capacity.

(TT3) System processing, memory, timing, bus loading, and input/output shall be sized to provide 100% growth capacity.

3.4.2.15 Bus Partitioning(TT3) An aircraft data bus shall incorporate all flight safety critical and essential flight control system sensor data and shall be independent of the mission equipment bus.

3.4.2.16 Mobile Code(T) Mobile Code shall not be used.

3.4.2.17 Development Environment(T) ARH shall have a controlled development and integration environment in order to mitigate the software risk associated with malicious code.

3.4.2.18 COTS and GOTS Information Assurance (IA) and IA-enabled Software(T) Should COTS and/or GOTS IA and IA-enabled software be part of the ARH design, only that software approved by a National Information Assurance Partnership (NIAP) process for COTS software or an NSA process for GOTS software shall be used.

3.4.2.19 Out of Cycle Revisions(T) The ARH mission equipment shall accept out of cycle software updates.

3.4.2.20 Software Blocking (T) The ARH shall be compliant with the Army Software Blocking Policy IAW DA Memorandum, SUBJECT: Software Blocking Policy, dated 18 Sept 2001, which impacts platform information exchange requirements, software/hardware development, and program execution. Examples include, but are not limited to the evolution of the VMF, versions of the Improved Data Modem (IDM), and versions of Force XXI Battle Command Brigade and Below (FBCB2)-Air.

3.4.2.21 Anti-Tamper(TT3) The ARH shall incorporate anti-tamper architecture to protect all critical information/technologies to include software and hardware.

3.4.3 System Security Classification Level(T) The system shall process information / data up to the SECRET level.

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3.4.4 Zeroize

3.4.4.1 Onboard Data (T) A fail-safe means of zeroizing or erasing all electronic classified information shall be provided, and once initiated the zeroizing or erasing process shall be self-executing, nonreversible, and unstoppable to completion.

(TT3) All data shall be zeroized with one action.

3.4.4.2 Encryption Codes(T) Equipment that does not offer secure storage of cryptovariables shall cause automatic zeroization of cryptovariables upon extraction from the aircraft.

3.4.4.3 Mode Codes(T) The IFF Mode 4 code shall be automatically zeroized on orderly system shutdown.

3.4.4.4 Code Hold(T) The system shall have an IFF Mode 4 code hold capability.

3.4.5 Information Assurance(T) The system shall be in full compliance with Information Assurance requirements according to DODD 8500.1, DODI 8500.2, and AR 25-2.

3.4.6 Mission Planning/Data Transfer System (DTS)

3.4.6.1 Pre-Mission Planning(T) The ARH shall use the Aviation/Joint Mission Planning System (defined by the AMPS System Acquisition Management Plan, Revision 8, dated January 2003) for a pre-mission planning system that loads all ARH mission planning, rehearsal, and data elements for the aircraft.

3.4.6.2 Compatibility(TT1) The ARH shall have an Aviation / Joint Mission Planning System (AMPS/JMPS) compatible DTS that stores a minimum of 600 Megabytes of mission and map data and sends and receives data within the ARH architecture at a minimum rate of 1 Megabit per second.

3.4.6.3 Automation(TT3) The DTS subsystem shall provide the necessary interfaces to the communications, navigation, aircraft survivability equipment (ASE), and mission equipment subsystems to automate data input to the mission management subsystem to include a minimum of two days of presets, frequencies/nets, and channel identifiers.

3.4.6.4 Cartridge Media(T) The cartridge media for the DTS shall be defined by the Personal Computer Memory Card International Association (PCMCIA) standard.

3.4.6.5 Onboard Mission Rehearsal(O) The ARH shall provide an onboard mission rehearsal capability.

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3.4.6.6 Data/Audio/Video Memory Storage/Retrieval(TT1) The DTS shall store/retrieve selected data and video required/generated by ARH subsystems for all modes of aircraft operation, including operational, maintenance, and diagnostic data. The DTS shall provide the crew the ability to record at least 2 hours of data, voice, sensor imagery, and symbology on a solid state recording device compatible with AMPS.

3.4.7 Sensors

3.4.7.1 Target Acquisition Sensor Suite (TASS) Functionality(T) The TASS shall be mounted in a slewable, stabilized turret with servo control, video processing, digital data processing, and signal conditioning to display infrared and television imagery on multifunction displays (MFDs).

3.4.7.2 TASS ModesThe TASS shall have at a minimum the following operator selectable modes:

(T) Off: No power shall be applied to the TASS. When the system is placed in off mode, the turret and optics shall be placed in stow during the power-down sequence.

(T) Standby: Power shall be applied to the TASS for thermal conditioning.

(TT2) Stow: TASS apertures shall be placed in position for protection from debris.

(T) Fixed Forward: The TASS turret shall be placed in the zero degree azimuth and elevation position.

(T) Manual Track: The operator shall have control of the TASS turret in both azimuth and elevation to maintain the selected sensor Line-of-Sight (LOS) on an object of interest.

(TT1) Auto Track: The TASS shall provide three (3) auto track modes consisting of scene correlation, centroid, and contrast. The TASS shall automatically select the track mode that provides the best track.

(TT1) Laser Track: The TASS shall be pointed with reference to azimuth and elevation data provided by the laser spot tracker.

(T) Boresight: The TASS shall align the LOS of the imaging sensors with the laser rangefinder / designator.

(TT2) Geolocation Track: The ARH MEP shall provide the commands to point the TASS to a waypoint/target via navigation data.

(TT1) IBIT: The TASS shall provide the operator or maintainer the ability to initiate a Built In Test (BIT). The results of BIT shall be provided on ARH displays.

(TT1) Scan Mode: The TASS shall automatically perform an operator selected scan in any combination of azimuth and elevation.

3.4.7.3 Slew Rate(TT2) The TASS shall have a slew rate of at least 2.5 rad/sec in each axis and slew acceleration of at least 7 rad/sec2

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3.4.7.4 TASS Startup Timeline(TT1) The TASS shall be fully operable within 5 minutes of TASS startup initiation including any sensor cool-down time when TASS heat soak temperatures are below 122oF.

(TT1) The TASS shall be fully operable within 10 minutes of TASS startup initiation including any sensor cool-down time when TASS heat soak temperatures are above 122oF.

(O) The TASS shall be fully operable within 1 minute of TASS startup initiation including any sensor cool-down time when TASS heat soak temperatures are below 140oF.

(O) The TASS shall be fully operable within 3 minutes of TASS startup initiation including any sensor cool-down time when TASS heat soak temperatures are above 140oF.

3.4.7.5 Boresight

3.4.7.5.1 Automation(T) The TASS shall have a completely automated, internal boresight capability, executable in less than 1 minute, which will align the laser to other sensors with a degree of accuracy to meet performance requirements consistent with laser designation requirements listed in the classified annex.

3.4.7.5.2 Crew Interface(T) The TASS shall provide the crew a function to initiate and terminate automatic boresight alignment.

3.4.7.5.3 Outside Targets(T) No outside targets shall be required for boresight.

3.4.7.5.4 Alignment Retention(TT2) The TASS shall retain alignments throughout a 4-hour flight with not more than 2 in-flight boresight alignments, throughout the aircraft flight envelope, to include gunfire.

3.4.7.5.5 Safety Features(TT1) Boresighting shall have safety features such that the procedure can be accomplished at any time, including on the ground, in flight, and in enclosed buildings, with no restrictions on the close proximity of personnel.

3.4.7.5.6 Drift Recognition(TT2) The TASS shall indicate to the crew when the sensor alignments have drifted outside of the limits required to maintain laser designation accuracy.

3.4.7.6 Target Acquisition Sensor Suite (TASS)(TT1) The ARH shall have a slewable Target Acquisition Sensor Suite (TASS) controllable from both flight crew stations.

The TASS shall consist of the following:

(T) Infrared Imaging Sensor

(T) Color Television (CTV)

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(O) Low Light Color TV (LLCTV)

(T) Laser Rangefinder / Designator

(O) Eyesafe Rangefinder

(T) Laser Spot Tracker

(T) Laser Pointer

3.4.7.6.1 Infrared Sensor(T) The TASS shall include an Infrared Sensor that allows the crew to manually detect, classify, recognize, and identify vehicular and man sized targets with at least the probabilities and ranges listed in the classified annex.

3.4.7.6.1.1 Output

(T) Infrared imagery shall be output for display on the MFDs.

3.4.7.6.1.2 Display Viewability

(TT1) The infrared imagery combined with symbology, shall interface and be viewable on either or both crewmembers' displays.

3.4.7.6.1.3 Polarity (black/white hot)

(T) A crew selectable control shall be provided to allow the crew to select between display white hot and black hot FLIR imagery.

3.4.7.6.1.4 Future Growth

(O) Infrared imagery shall be output as 12 bit digital to allow growth for a future Aided Target Recognition capability.

3.4.7.6.2 CTV(TT1) The CTV shall meet the requirements specified in the classified annex.

(O) The Low Light Color TV shall provide color output at lighting conditions down to at least 1.0 lux.

3.4.7.6.2.1 Sun Viewing Protection

(TT1) The CTV shall be protected from damage due to inadvertent viewing of the Sun.

3.4.7.6.2.2 CTV Display

(T) CTV imagery shall be output for display on the MFDs. The CTV, combined with symbology, shall interface and be viewable on either or both flight crewmembers' displays.

3.4.7.6.3 Laser Rangefinder/Designator

3.4.7.6.3.1 Safety

(T) When the laser is armed or firing, the TASS shall warn the pilot and co-pilot via symbology on the MFDs.

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3.4.7.6.3.2 Fail-Safe

(T) The laser shall include a fail-safe system that does not allow accidental firing of the non-eyesafe wavelength during eyesafe operations or maintenance.

3.4.7.6.3.3 Firing Limits

(T) All lasers shall have laser firing limits to prevent self lasing of the airframe or rotor system.

3.4.7.6.3.4 Safety Interlocks

(T) The laser system shall have safety interlocks to prevent inadvertent firing when on ground.

3.4.7.6.3.5 Notification

(T) The system shall provide notification to the crew when laser firing is inhibited.

3.4.7.6.3.6 Codes

(T) The laser designation mode shall provide Pulse Repetition Frequency (PRF) codes and Pulse Interval Modulation (PIM) codes for precision guided munitions against stationary and moving targets.

3.4.7.6.3.7 Range

(T) The rangefinder mode shall provide full range capability for all ARH laser guided weapon systems. Laser performance requirements IAW the classified annex.

3.4.7.6.3.8 Accuracy

(T) The laser performance and accuracy shall be IAW the classified Annex.

3.4.7.6.3.9 Compatibility

(T) Laser pulse codes shall correspond to all Pulse Repetition Interval (PRF) and Pulse Interval Modulation (PIM) as described in CR-RD-MG-98-2.

3.4.7.6.3.10 Selectability

(T) The laser pulse codes shall be crew selectable while in flight.

3.4.7.6.3.11 Interface with Avionics

(T) The laser rangefinder / designator (LRF/D) shall provide turret azimuth and elevation and laser range data to onboard avionics systems for the geolocation of targets.

3.4.7.6.3.12 Modes of Operation

(T) The LRF/D system shall operate in the following modes as a minimum: Laser Off Mode, Laser Standby Mode, Laser Range Mode, Laser Designate Mode.

(O) Eyesafe Laser Range Mode

3.4.7.6.3.13 Laser Range Requirements

(T) See classified annex.

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3.4.7.6.3.14 Laser to Sensor LOS Coincidence

(TT1) The Laser LOS and Sensor LOS shall be aligned in the narrowest field of view. In this view, 90% of the laser energy shall be placed with a 95% probability (2.237 sigma each axis) on a 2.3 meter by 2.3 meter target at distances as specified in the classified annex. (For the laser designator, 90% of laser energy refers to the beam divergence diameter, centered about the center of the laser beam; laser energy that falls outside of the beam divergence shall not be considered part of the 90% energy requirement.)

3.4.7.6.4 Laser Pointer(T) The system shall provide the capability to illuminate a specific point with the laser pointer that is viewable with image intensification devices and not to the unaided eye.

3.4.7.6.4.1 Target Location Error

(TT1) See classified annex.

3.4.7.6.5 Laser Spot Tracker(T) The system shall have a Laser Spot Tracker (LST) to acquire and track PRF and PIM laser codes and provide symbology and steering data to the crew on the MFDs.

3.4.7.7 Image Fusion(TT1) The CTV shall provide imagery that is registered with the infrared sensor imagery for the purpose of fusing infrared sensor and CTV imagery in the FOVs common between the infrared sensor and the CTV .

3.4.7.7.1 Image Selection(TT1) The crew shall be able to select image fusion within each FOV.

3.4.7.7.2 Adjustment(TT1) The image fusion mode shall be selectable between fully automated or manual adjustment of the image fusion algorithm.

3.4.7.7.3 Fused Image Display(TT1) The fused image shall be combined with symbology, shall interface with and be viewable on either or both flight crewmembers MFDs.

3.4.7.8 Imagery Controls

3.4.7.8.1 Gain and Level(T) A gain and level control shall be provided to adjust gain and level of the FLIR. The gain and level control shall be crew selectable and have two modes: a manual and automatic.

3.4.7.8.2 Focus(T) A crew selectable focus control shall be provided allowing manual and automatic focus adjustment of all imaging sensors.

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3.4.7.9 Image Auto-Tracker

3.4.7.9.1 Acquisition and Tracking of Targets(T) The TASS shall provide an image auto-tracker that acquires and tracks one target, moving or stationary while the ARH is at speeds from a hover to maximum forward flight speed.

(O) The TASS shall provide an image auto-tracker that acquires and tracks up to six targets, a combination of moving and stationary, while the ARH is at speeds from a hover to maximum forward flight speed.

3.4.7.9.2 Interoperability(T) The auto tracker shall function with all imaging sensors.

3.4.7.9.3 Track Gates(T) Track gates shall be adjustable by the crew.

3.4.7.9.4 Display(T) The TASS shall display, “lock-on” and automatically track target images.

3.4.7.9.5 Break Track(TT1) The auto-tracker shall not break track during own-ship weapons employment, during changes in sensor FOV, during aircraft maneuvering throughout the established maneuvering envelope of the airframe, due to target motion, or while electro-optic countermeasures are employed against the ARH.

3.4.7.9.6 Reacquisition of Targets(TT1) When break track occurs due to target obscuration, the auto-tracker shall enter a coast mode and attempt to reacquire the target. The attempt to reacquire the target shall not be less than 5 seconds.

3.4.7.10 Symbology

3.4.7.10.1 Display (TT1) The ARH shall provide symbology for concurrent display with TASS imagery, IAW MIL-STD-1787, on the MFD which at a minimum includes aircraft position, heading, time, date, turret azimuth and elevation, laser range, emitting laser status, laser spot tracker, active FOV, track gates, BIT status, operating mode, and image fusion percentage.

3.4.7.10.2 Selection(TT1) The symbology displayed shall be crew selectable and shall range from no symbology (sensor imagery only) being displayed, a partial set of crew selected symbology, and the full symbology set.

3.4.7.11 TASS Field of Regard (TT1) The TASS shall have an unvignetted Field of Regard (FOR) in all fields of view from a fixed forward position mounted on the airframe of (reference to aircraft center line):

Azimuth: +/- 180 degrees

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Elevation +/- 30 degrees

(O) Azimuth: +/- 210 degrees

(O) Elevation +60/-180 degrees

3.4.7.12 TASS Field of View (FOV)

3.4.7.12.1 Infrared Sensor Fields of View (TT1) The infrared sensor shall have a minimum of 3 optical FOVs.

3.4.7.12.1.1 Narrow Field of View (NFOV)

(TT1) The infrared sensor shall have an optical NFOV no wider than 0.8o horizontal x 0.6o vertical.

3.4.7.12.1.2 Medium Field of View (MFOV)

(TT1) The infrared sensor shall have an optical MFOV no narrower than 6.0o horizontal x 4.5o

vertical to achieve the sensor performance specified in the classified annex.

3.4.7.12.1.3 Wide Field of View (WFOV)

(TT1) The infrared sensor shall have an optical WFOV no narrower than 20o horizontal x 15o vertical.

3.4.7.12.2 CTV Fields of View(TT1) The CTV shall have a minimum of 3 optical FOVs; two of which shall match the MFOV and NFOV of the infrared sensors.

3.4.7.12.2.1 CTV Super Narrow Field of View (SNFOV)

(TT1) The CTV shall have a SNFOV no wider than 0.4o horizontal x 0.3o vertical.

3.4.7.12.3 Switching and Settling Times(TT1) The switching and settling times for FOV changes shall not exceed 0.5 seconds.

3.4.7.12.4 FOV Center(TT1) When changing FOV, the centers of the FOV shall remain coincident within 10% of the FOV being selected.

3.4.7.13 Electro-Optics Counter Countermeasure (EOCCM)(TT1) The TASS shall incorporate protection against laser damage, jamming, and exploitation from counter measures.

3.4.7.14 TASS Open System Architecture(TT2) The TASS shall provide space and power for incorporation of the emerging technologies of third generation Forward Looking Infrared (FLIR) (2 color FLIR with mid-wave and long-wave infrared in the same focal plane assembly) and Aided Target Recognition (ATR) software.

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3.4.7.15 Anti-Ice(TT1) The TASS shall have an anti-ice capability that keeps external optical surfaces unobstructed by ice during operation.

3.4.8 Battlefield Interoperability

3.4.8.1 Net CentricThe ARH shall be Net-Centric and meet all of the requirements of the Net Ready KPP per CJCSI 6212.01C, which requires all activity interfaces, services, policy-enforcement controls, and information exchange of the Net Centric Operations and Warfare-Reference Model (NCOW-RM) and Global Information Grid (GIG)-Key Interface Points (KIPs) be satisfied to the requirements of the supporting Joint integrated architecture products, (including data correctness, data availability and data processing), and information assurance accreditation.

(T) The ARH shall be Net-Centric and meet the applicable requirements of the Net Ready KPP per CJSCI 6212.01C, which include:

a) Interfacing with the Teleport GIG KIP via SATCOM,

b) Supporting the DoD vision of “post before process” by interfacing with the GIG via alignment with the NCOW-RM service entitled “Interact with the Net-Centric Information Environment – A1” using formatted VMF radio messages to/from supported operations centers,

c) Incorporating Internet Protocol Version 6 via the IDM in conjunction with the Army Software Blocking Plan schedule,

d) Providing the necessary architecture Technical View-1 (TV-1) to be compliant with the most current version of the DISR and ensure interoperability among systems within the Joint battlefield,

e) Incorporating the standards applicable for small weapons systems from the Department of Defense Information Technology Standards Registry (DISR),

f) Meeting the Information Assurance requirements of DoD Directive 8500.1.

3.4.8.2 Network Protocol (T) The ARH shall be compliant with the DoD policy for Enterprise-wide deployment of Internet Protocol Version 6 IAW DoD Memorandum For Secretaries of the Military Departments, Subject: Internet Protocol Version 6 (IPv6), dated 9 June 2003, and DoD Memorandum For Secretaries of the Military Departments, Subject: Internet Protocol Version 6 (IPv6) Interim Transition Guidance, dated 29 Sept 2003.

3.4.8.3 System Interoperability The ARH shall provide information exchange interoperability with the following Army, Joint, and Allied/Coalition systems via the communications systems functions / capabilities indicated below.

(T) Very High Frequency- Amplitude Modulation (VHF-AM), Nonsecure Voice: Other Airspace Users Air Traffic Control agencies

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(T) UHF-AM, HAVEQUICK, Secure and Nonsecure Voice: Naval Ships Tactical Air Traffic Services Air Force Intelligence Aircraft (Airborne Warning and Control Station (AWACS), Joint Service and Target Attack Radar System (JSTARS) Army and Joint Aircraft

UHF-AM HAVEQUICK, Secure Data:(T) Alternate Point-to-Point Army Aviation Variable Message Format (VMF) Message Link(TT3) Unmanned Air Vehicle (UAV) Level 2 Control Link

(T) Very High Frequency-Frequency Modulation (VHF-FM), Single Channel Ground and Airborne Radio System (SINCGARS), Secure and Nonsecure Voice: Allied / Coalition Command and Control (C2) USMC C2 Army Maneuver C2 Aviation Brigade / Battalion Tactical Operations Center Army and Joint Aircraft

(T) VHF-FM, SINCGARS, Secure Data (Variable Message Format): USMC C2 Maneuver C2 Army Aviation and Fire Support Point-to-Point VMF Message Link Aviation Brigade/Battalion Tactical Operation Center Tactical Internet (Army Battle Command Systems) Army and Joint Aircraft UAV Level 2 Control Link

(T) L-Band Blue Force Tracking, Secure Data (Variable Message Format) Tactical Internet (Army Battle Command Systems) Beyond Line of Sight (BLOS) Link

UHF SATCOM DAMA, Secure Voice and Data (Variable Message Format & Common Message Format)(T) Stryker Brigade Combat Team TOC (Voice and Variable Message Format) BLOS Link

(O) Integrated Broadcast System Intelligence Broadcast Monitor (Common Message Format – Binary)

(TT3) Enhanced Precision Location Reporting System (EPLRS), Secure Data (Variable Message Format) Army Maneuver C2 Tactical Internet (Army Battle Command Systems) Army Airborne Command and Control System (A2C2S)

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(O) Link-16, Secure Voice and Data, (Tactical Digital Information Link-Joint TADIL-J Format) Air Force Intelligence Aircraft (AWACS, JSTARS) Joint and Allied /Coalition Aircraft Naval Ships Army Air Defense Systems Supports Combat ID (O) Tactical Common Data Link, Secure Data (TCDL format) UAV Level 4 Control Link Receipt of UAV Live Video Transmission of ARH Live Video to Distributed Common Ground Station-Army (DCGS-A)

(T) Transponder, Mode 1, 2, 3 A/C: Air Traffic Control Agencies

(T) Transponder, Mode S: Air Traffic Control Agencies

(T) Transponder, Mode 4: Tactical Air Traffic Services Air Force Intelligence Aircraft (AWACS, JSTARS) Joint / Coalition Aircraft Supports Combat ID

(T) Transponder, Mode 5: Tactical Air Traffic Services Air Force Intelligence Aircraft (AWACS, JSTARS) Joint/Coalition Aircraft Supports Combat ID

3.4.8.4 Communication System

3.4.8.4.1 Joint Tactical Radio System (JTRS)(O) The system shall communicate on the battlefield with the JTRS communications suite that ensures connectivity with Army, Joint, and Coalition forces with both clear and secure voice and with secure data.

3.4.8.4.2 Compatibility(T) The ARH communication system shall be compatible with FAA and ICAO regulations.

3.4.8.4.3 GATM(O) The system shall comply with Global Air Traffic Management (GATM) Capstone Requirements Document Annex II as set forth in the US Army GATM Operational Requirements Document (ORD).

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3.4.8.4.4 Range

3.4.8.4.4.1 Civil Airspace Entry Communications

(TT1) The aircraft shall have clear voice communications via VHF LOS radios at 8,000 feet above ground level (AGL) and 100 nautical miles (nm) distance for compliance with VHF civil aviation in order to ensure worldwide airspace access.

3.4.8.4.4.2 Nap of Earth (NOE) Communications

(TT1) During NOE operations the range of all radios, except SINCGARS, shall be a minimum of 12 nm at 100 feet AGL.

3.4.8.4.4.3 Line-of-Sight (LOS) Communications

(TT1) The omnidirectional air-to-ground line-of-sight range of the HAVEQUICK, VHF-AM Voice, UHF-AM, and SINCGARS, operating in the single-channel and non-secure voice modes, shall be at least 35 nm at 1,200 feet AGL.

3.4.8.4.4.4 NOE SINCGARS Communications

(TT1) The omnidirectional air-to-ground line-of-sight range of the SINCGARS radio, operating in the single-channel and non-secure voice modes, shall be at least 13.5 nm at 100 feet AGL.

3.4.8.4.4.5 Non Line-of-Sight Communications

(TT1) SATCOM connectivity shall be maintained within 58 degrees North and South latitudes at 38.4kbs data rate for dedicated channel SATCOM and 19.2kbs data rate for DAMA SATCOM. Connectivity shall be maintained at lesser data rates for both dedicated channel and DAMA SATCOM at latitudes above 58 degrees North and South.

3.4.8.4.4.6 Link 16 Communications

(TT3) The omnidirectional air-to-air line-of-sight range of the Link 16 communications shall be at least 75 nm (138.9 km).

3.4.8.4.5 Identification and Combat ID

3.4.8.4.5.1 Identification

(T) The system shall have an identification capability, with the capability to transmit/receive in secure mode that provides spherical coverage under all civil and military interoperable interrogation, including Modes 1, 2, 3A/C, 4. Modes 1, 2, 3A/C, and 4 IFF performance is defined by International Bureau (IB) 4943. This system shall comply with Air Traffic Control Radar Beacon System Identification Friend or Foe Mark XII Systems (AIMS) Program Office Standards (03-900, 97-1000 with addendums, 03-1000 with addendums) and test plans.

3.4.8.4.5.2 Combat Identification (ID)

(T) Combat ID shall be provided by a combination of IFF and other Tactical Internet capabilities.

(O) Combat ID shall be provided by Link 16.

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3.4.8.4.5.3 Enhanced ID

(T) Mk XII ATCRBS/IFF units installed to meet identification requirements shall be upgradeable to Mk XIIA compliance (Mode S and Mode 5 capability) via software and/or retrofit kits During SDD, integration and test of Mode S and Mode 5 capability shall be peroformed if the capabilities are available. Mode S performance is defined by RTCA/DO-181. Mode 5 performance is defined in AIMS Program Office Standards 03-1000, with addendums.

3.4.8.4.6 Voice and Data Communication(TT3) All voice capabilities over digital networks shall support 2.4 (Kilobit Per Second) Kbps and 16 Kbps voice. It shall also support Continuously Variable Slope Delta-Modulation (CVSD) IAW Standards Agreement STANAG 4209, Mixed Excitation Linear Predictive (MELP) IAW MIL-STD-3005, and Linear Predictive Coding (LPC)-10e IAW STANAG 4198.

3.4.8.4.7 Modes / Status Indications(T) The system shall provide for setup and modes control, and shall provide normal and secure status indications to the flight crewmembers.

3.4.8.4.8 Simultaneous Communications(T) The system shall provide simultaneous voice and data communications (not on the same radio and channel).

3.4.8.4.9 Receive/Transmit Capability(TT1) The system shall receive six channels plus guards and transmit four channels simultaneously based on the requirement for two UHF receiver transmitters (including SATCOM), two VHF receiver transmitters, EPLRS, and Blue Force Tracking (BFT).

(O) The system shall receive seven channels plus guards and transmit five channels simultaneously based on the requirement for two UHF receiver transmitters (including SATCOM), two VHF receiver transmitters, Link 16, EPLRS, and BFT.

3.4.8.4.10 Preset Channels(TT1) A minimum of 20 communications preset channels for each band shall be provided that allows for data entry, modification and selection. Preset definitions shall include as a minimum frequency/net for voice and digital, and call sign parameters for digital nets.

3.4.8.4.11 Still / Live Imagery(TT1) The system shall transmit / receive still imagery over SINCGARS and/or SATCOM using Joint Photographic Experts Group (JPEG) images in an NITFS wrapper inserted within VMF messages.

(O) The system shall transmit/receive live imagery over Tactical Control Data Link (TCDL) and Network Data Link (NDL) and communicate with the Future Combat System over Wideband Network Waveform (WNW), NDL, and Soldier Radio Waveform (SRW) which requires additional transmit and receive channels.

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3.4.8.4.12 UHF-AM (T) The system shall provide UHF-AM communication and shall communicate, both voice and data using VMF messages IAW MIL-STD-6017 with external systems using qualified Army aviation UHF-AM radios. The system shall have the following functions, at a minimum:

(O) The system shall provide UHF-AM communication and shall communicate using CMF-B messages for Integrated Broadcast Service (IBS) receive over SATCOM.

3.4.8.4.12.1 Jam Resistance

(T) Jam resistant UHF-AM Communication shall be accomplished using the HAVEQUICK II waveform.

3.4.8.4.12.2 Joint Service Interoperability

(T) Joint Service UHF-AM Communication shall be accomplished using the HAVEQUICK II waveform.

3.4.8.4.12.3 Secure Communication

(T) Secure UHF-AM communication shall be accomplished using an encryption device.

3.4.8.4.12.4 Secure Voice and Data, UHF SATCOM

(T) Secure voice and data UHF SATCOM Demand Assigned Multiple Access (DAMA) shall be accomplished IAW MIL-STDs 188-181B, 188-182A, 188-183, and 188-184, and associated encryption device. The SATCOM data capability shall utilize VMF messages IAW MIL-STD-6017.

(TT3) The SATCOM data capability shall utilize the Joint Range Extension (JRE) Protocol IAW MIL-STD-3011 to utilize TADIL-J messages IAW MIL-STD-6016.

3.4.8.4.12.5 Data from Improved Data Modem (IDM)

(T) Data from the IDM MD-1359/A, IAW Multiplex Interface Control Document (MICD) for the IDM Version 8, shall be displayed to the crew.

3.4.8.4.12.6 Continuous Guard

(T) Continuous UHF-AM Guard monitoring at 243.0 megahertz (MHz) shall be provided.

3.4.8.4.13 VHF-FM (T) The system shall provide dual VHF-FM communication that shall be capable of both voice and data (using VMF messages), with external systems using qualified Army aviation radios. In addition, the system shall have the following functions, at a minimum:

3.4.8.4.13.1 Jam Resistance

(T) Jam resistant VHF-FM communications shall be accommodated with the SINCGARS- Enhanced System Improvement Program (ESIP) waveform.

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3.4.8.4.13.2 Joint Service Interoperability

(T) Joint Service VHF-FM communications shall be accommodated with the SINCGARS-ESIP waveform.

3.4.8.4.13.3 Secure Communications

(T) Secure VHF-FM communications shall be accomplished with an encryption device.

3.4.8.4.13.4 UAV Level 2 Data and Still Image Display

(TT1) Capability to directly receive and display data and still images from UAV’s shall be provided .

3.4.8.4.13.5 UAV Level 2 Control

(TT1) Capability up to and including Level 2 control of UAVs shall be provided.

3.4.8.4.13.6 Data from the IDM

(T) Data from the IDM, IAW MD-1359/A, shall be displayed to the crew.

3.4.8.4.14 VHF-AM Communication(T) The system shall communicate, in voice, with external systems using qualified Army aviation radios.

3.4.8.4.14.1 IDM Interface

(T) The IDM shall be connected to the VHF-AM radio.

3.4.8.4.14.2 Channel Spacing

(T) The system shall provide 8.33 KHz channel spacing.

3.4.8.4.14.3 Continuous Guard

(T) Continuous VHF-AM Guard monitoring at 121.5 Megahertz (MHz) shall be provided.

3.4.8.4.15 Ultra High Frequency (UHF) – EPLRS(TT3) The system shall communicate via data (VMF messages) with the Army Tactical Internet using a certified Army aviation radio. The IDM shall be connected to the EPLRS radio. In addition, the system shall have the following functions, as a minimum:

3.4.8.4.15.1 Secure Communication

(T) If EPLRS is provided data from the IDM MD-1359/A, IAW MICD for the IDM Version 8, or some other digital interface shall be displayed to the crew.

3.4.8.4.16 L-Band - BFT Data Communication(T) The system shall communicate; both receive and transmit, in data (VMF messages) with the Army Tactical Internet. The IDM shall be connected to the BFT radio. In addition, the system shall have the following functions, at a minimum:

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3.4.8.4.16.1 Secure BFT

(TT3) Secure BFT communications shall be accomplished with an encryption device.

3.4.8.4.16.2 Data from IDM

(T) Data from the IDM MD-1359/A, IAW MICD for the IDM Version 8, shall be displayed to the crew.

3.4.8.4.17 L-Band – Link-16 Voice and Data Communication(T) The ARH shall provide space, weight, and power to incorporate federated Link 16.

(O) The system shall communicate, in voice and data (using TADIL-J messages), with external systems using a certified DoD radio. In addition, the system shall have the following functions, at a minimum: A certified Interference Protection Feature (IPF), frequency remapping capability, voice – 2.4 and 16 Kbps, imagery – utilizing the EagleEye compression algorithm, Time Slot Reallocation (TSR) and 200 Watt output as measured at the antenna port.

3.4.8.4.17.1 Secure Link-16

(TT3) Secure Link-16 communications shall be accomplished with an encryption device.


(TT3) Data from the IDM MD-1359/A, IAW MICD for the IDM Version 8, or another acceptable interface shall be displayed to the crew.

3.4.8.4.18 Ku Band – TCDL Data Communication(O) The system shall communicate, in data (using TCDL protocols and National Imagery Transmission Format Standard (NITFS) wrappers) with UAVs, their Ground Control Stations, and DCGS-A using a certified DoD data link radio. In addition, the system shall have the following functions at a minimum:

3.4.8.4.18.1 Secure TCDL

(O) Secure TCDL communications shall be accomplished with an encryption device.

3.4.8.4.18.2 Data Display

(O) Level 4 data shall be provided through an acceptable interface.

3.4.8.4.18.3 Control of UAVs

(O) Capability up to and including Level 4 control of UAVs shall be provided.

3.4.8.4.18.4 Video

(O) Capability to receive and transmit live video shall be provided.

3.4.8.4.19 Multiple Frequency Bands (WNW, NDL, SRW) Communication(O) The system shall communicate, in voice and data (using Future Combat System (FCS) protocols) with the FCS Family of Systems (FoS) using a certified Army Cluster 1 or equivalent JTRS radio. In addition, the system shall have the following functions, at a minimum:

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3.4.8.4.19.1 Secure Communications

(O) Secure communications shall be accomplished with an encryption device(s).


(O) Data from the IDM MD-1359/A, IAW MICD for the IDM Version 8, shall be displayed to the crew.

3.4.8.4.19.3 Video

(O) Provide capability to receive and transmit live video shall be provided.

3.4.8.4.20 Command, Control, Communications, Computers, Identification, Surveillance, and Reconnaissance (C4ISR) Interface

(T) The system shall communicate in the C4ISR environment using the above radio capabilities supported by the Army IDM. The IDM MD-1359/A shall be integrated into the avionics system IAW MICD for the IDM Version 8. The IDM baseline shall be software Version 8 and shall be updated as necessary to meet the Software Blocking requirements.

3.4.8.4.21 Retransmission / Crossbanding(TT2) The system shall provide switching and interconnections to enable retransmission/ crossbanding of voice and data (UHF and VHF). All information shall be at the same security level.

(TT3) The system shall provide switching and interconnections to enable retransmission / cross-banding of voice and data (UHF, VHF, and Link 16). All information shall be at the same security level.

3.4.8.4.22 Integrated Broadcast Services (IBS) (O) The system shall have the ability to receive standard IBS messages. The IBS messages shall be compliant with the Common Message Format – Binary (CMF-B).

3.4.8.4.23 Intercommunication Subsystem

3.4.8.4.23.1 Simultaneous Communication

(T) The Intercommunication Subsystem shall provide the aircrew with the capability to transmit and receive simultaneously on any VHF-AM, VHF-FM, or UHF radio and the ability to monitor all radios from all crew positions, as selected by individual crewmembers. (O) Link 16 shall also be able to transmit and receive simultaneously.

3.4.8.4.23.2 Interface Capability

(T) All Intercommunication Subsystem positions shall interface with navigation aids, IFF, and other avionics that provide audio caution and warning tones. The Intercommunication Subsystem shall provide an external communication port for ground maintenance personnel.

3.4.8.4.23.3 Secure and Clear Voice

(T) The Intercommunication Subsystem shall accommodate both secure and clear voice.

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3.4.8.4.23.4 Interface with DTS

(T) The Intercommunication Subsystem shall provide the required interfaces to the aircraft DTS.

3.4.8.4.23.5 Intercommunication Subsystem Controls

(T) Each Intercommunication Subsystem station, including ground crew, shall have the necessary controls for independently selecting equipment for monitoring, adjusting volume level for the various equipment, hot mike control, selection of interphone channel, audio on/off, adjustment of the signal level to the headset and growth capability for Link 16.

(TT3) In addition to the requirements listed above, each intercom Subsystem station, including ground crew, shall have VOX capability.

3.4.8.4.23.6 Intercommunication Subsystem Audio Intelligibility

(TT1) Audio transmissions shall be intelligible at all operational ambient noise levels. Modified Rhyme Tests shall yield scores of not less than 91 percent when performed through the worst case audio path (including speaker, transmitter, receiver, audio distribution, and listener) with both speaker and listener in (a) a pink noise environment of 105 Decibel (dB) Sound Pressure Level (SPL) and (b) an environment equivalent to worst case cockpit noise under normal operating conditions.

3.4.8.5 TEMPEST(T) The intent of National Communications Security Engineering Memorandum (NACSEM) 5112 (NONSTOP Evaluation Techniques) and KAG/TSEC (Compromising Emanations for Crypto Equipment- HIJACK) shall apply to the ARH in regard to handling of classified data.

3.4.8.6 Visual Flight Rules/Instrument Flight Rules (VFR/IFR)(TT1) The ARH shall operate day and night, in national and international airspace under FAA and ICAO Visual and Instrument Flight Rules (VFR/IFR) in both the surface and oceanic Air Traffic Control (ATC) environments. The ARH shall perform ground-based navigational aid (NAVAID) non-precision and Category I precision instrument approaches as well as GPS non-precision approaches with vertical guidance (including tactical VNAV).

(TT3) The ARH shall perform IFR enroute, terminal and approach navigation using GPS as the primary navigation means and shall include the capability to conduct GPS Category I precision instrument approaches.

3.4.8.7 Navigation

3.4.8.7.1 Radio Navigation(T) The radio navigation system shall include VHF Omni-directional Range (VOR).

(TT1) The radio navigation system shall include Distance Measuring Equipment (DME), and the Marker Beacon and Instrument Landing System (ILS).

(TT2) The radio navigation system shall include Tactical Air Navigation (TACAN) or equivalent.

(T) The VHF capability shall have FM immunity and the marker beacon audio shall be applied to the Intercommunication Subsystem (ICS).

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3.4.8.7.2 Area Navigation (RNAV) Systems(T) The ARH shall include a multi-sensor area navigation system that provides precise location accuracy for intelligence information, reporting accuracy, quick response to changes in mission, precise target handovers for engagement of targets. The area navigation system shall also support VFR/IFR enroute, terminal and approach flight operations.

3.4.8.7.2.1 Sensors/Accuracy

(T) An Inertial Navigation System (INS) sensor shall be provided and shall perform to the requirements of the inertial navigator in the Enhanced Embedded GPS/Inertial (EGI+). The RNAV system with the INS sensor shall meet the civil requirements for INS use enroute.

(T) A GPS sensor shall be provided and shall perform to the requirements of the GPS navigator in the EGI+ with anti-spoof and anti-jam capability. The RNAV system with the GPS sensor shall meet at least the requirements for FAA Technical Standard Order (TSO) C-115b and applicable parts of other TSO, advisory circulars, and orders for GPS use en-route, terminal, non-precision approach.

(T) The combined INS/GPS mode shall have navigational accuracy sufficient to meet required target location accuracy as defined in the classified annex.

(T) The INS sensor shall accept position updates from geographical positions.

3.4.8.7.2.2 Flight Management

(T) The flight management system shall comply with all applicable civil requirements.

(T) Non-corruptible database requirements shall be complied with using National Geospatial - Intelligence Agency (NGA) Digital Aeronautical Feature Information File (DAFIF) data.

3.4.8.7.3 GATM Compliance(O) The system, including receivers, transmitters, and antennas, shall comply with GATM Capstone Requirements Document Annex II as set forth in the US Army GATM ORD.

3.4.8.7.4 GPS IFR Requirement(T) The GPS shall be IFR qualified to the Class B1 requirements IAW FAA TSO C-129a.

3.4.8.7.5 Absolute Altitude

3.4.8.7.5.1 Accuracy

(TT1) The aircraft height above the nearest surface shall be provided within the lesser of +/- 3 ft. or ± 2 percent of actual height above the surface to a maximum altitude of 1500 feet.

3.4.8.7.5.2 Drift Rate

(TT1) The short-term drift rate shall not exceed ± 2.0 ft within 15 min for altitudes from 0 to 200 feet.

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3.4.8.8 Tactical Situational Awareness

3.4.8.8.1 Digital Map System (T) The ARH shall include a digital, moving map overlaid with friendly/enemy force symbols and tactical symbols IAW MIL-STD-2525B and control measures to ensure the crew is continuously aware of the situation.

3.4.8.8.2 Digital Map Civil Capabilities(TT1) The digital map system shall meet all applicable world wide civil requirements as the sole means of meeting civil airspace map requirements. NGA electronic products equivalent to the FAA approved NGA paper products shall be used as the source data.

3.4.8.8.3 Inputs(T) The digital map system shall accept tactical data from the AMPS / JMPS, IDM, radio communications, onboard sensor inputs, and by manual entry.

3.4.8.8.4 Latency(TT1) The digital map system shall introduce no more than 0.5 seconds latency from AMPS, IDM or manual entry to Situational Awareness data display.

3.4.8.9 Map Display(T) The digital map shall be multi-color and the system shall provide real-time updates (20 hertz minimum) of map position, orientation, and multiple-scale coverage ranging from optimum display of detail for NOE flight up to large-area coverage for mission planning.

3.4.8.9.1 Capabilities(T) The digital map shall display plan view in real time using in-flight crew selectable map sizes and interface with both internal and external data.

(TT1) The digital map shall calculate inter-visibility to aid in en-route mission planning or threat avoidance.

(O) The digital map shall display perspective view. The map database shall be integrated with DTED underlying CADRG, CIB, and FFD providing the crew various map views with a terrain elevation underlay. Pilot selectable combinations of the following features shall be simultaneously possible: (a) heading up, North-up, or any pilot selected orientation; (b) aircraft present position centered on the display or de-centered to bottom of display; (c) pilot-slewable or selectable map position; (d) elevation contour lines and slope or elevation shading; (e) color contrasting of all terrain above and below the current flight altitude or a pilot selected altitude; and (f) depiction of terrain covered during all sensor scans, including depiction of the terrain not viewed.

3.4.8.9.2 Terrain and Feature Data(T) The on-board digital map system shall use terrain and feature data provided by the AMPS/JMPS.

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3.4.8.9.3 Data Source(T) The primary source map data bases and standards for the digital map shall be NGA products: DTED Level 1 and 2, CADRG, CIB, DAFIF, and Foundation Feature Data (FFD) when available.

3.4.8.9.3.1 Digital Map Products

(TT2) The ARH shall use standard digital map products from a National System for Geospatial Intelligence (NSGI) provider, to include but not limited to the NGA.

3.4.8.9.3.2 Compliancy

(TT3) ARH navigation data and digital maps shall be compliant with all COE and Network Centric Enterprise Services (NCES) and geospatial information segments, including the Commercial Joint Mapping Toolkit (C/JMTK).

3.4.8.9.4 Storage Capacity(TT1) The on-board digital map data storage capacity shall accommodate the storage requirements for the highest resolution digital product or digitized paper map product for a coverage of 300 kilometers (km) x 300 km (162 nm x 162 nm) at 1:50,000 scale.

3.4.8.10 Command and Control (C2) Interface

3.4.8.10.1 Variable Message Format (VMF)(T) The system shall provide a Pilot Vehicle Interface (PVI) that will permit the reception, transmission and display of VMF C2 and Situational Awareness information.

3.4.8.10.2 VMF (T) The system shall incorporate the VMF minimum implementation defined IAW MIL-STD-6017, without degradation to the operation of the system. The IDM baseline shall be software Version 8 and shall be updated as necessary to meet the requirements defined in the Software Blocking paragraph.

3.4.8.10.3 TADIL-J(O) The system shall incorporate the minimum implementation TADIL-J message set IAW MIL-STD-6016 that provides awareness of the Joint fighter situation and target tracks.

3.4.8.10.4 Common Message Format(O) The system shall incorporate the minimum implementation CMF-Binary message set that permits reception of the enemy situation information broadcasted by the IBS.

3.4.8.11 Crash Survivable Memory Unit (CSMU)

3.4.8.11.1 Record Capability(TT3) The CSMU shall record a minimum of the most recent 30 minutes of cockpit voice, and aircraft performance data, and the last 13 hours of critical maintenance and diagnostic data.

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3.4.8.11.2 Storage(TT3) The voice, performance, maintenance, and diagnostic data shall be stored in crash protected non-volatile memory during all flight environments.

3.4.8.11.3 Crashworthy(TT3) The cockpit voice and data recorder shall be a crashworthy, fire hardened, tamper-proof module.

3.4.8.11.4 System Parameters(TT3) The CSMU shall record those system parameters necessary for playback to assist in recreating the events in an accident investigation or flight safety review. Parameters shall be approved by the Government.

3.4.8.11.5 Compatibility with US Army Safety Center(TT3) The CSMU shall be compatible with the accident investigation equipment at the US Army Safety Center.

3.4.8.12 DISR Compliance(T) The ARH shall incorporate the applicable standards defined in the DISR for each ARH subsystem/capability/function per DoD Memorandum Subject: Department of Defense Information Technology Standards Registry Baseline Release 04-1.0, dated 15 July 2004. Note the DISR replaces the DoD Joint Technical Architecture (JTA) and will incorporate the Army JTA-Army (JTA-A).

3.4.8.13 Central Test Support Facility Certification(T) The ARH weapon system shall be Army Tactical Internet certified by the Central Technical Support Facility (CTSF) for intra-Army certification.

3.4.8.14 Joint Interoperability Test Center (JITC) Certification(T) The ARH weapon system shall be certified for joint interoperability by the JITC for Joint interoperability in accordance with CJCSI 6212-01C.

3.4.8.15 Spectrum Management(T) The ARH shall be Spectrum Certified for unrestricted use in accordance with AR 5-12.

3.4.9 Lethality

3.4.9.1 Employment (TT1) The ARH shall provide for short and long-range engagement of moving and stationary ground and air targets and provide the capability to aim weapons heads-up/eyes-out both day and night.

3.4.9.2 Air-to-Ground Missiles / Rockets The missile/rocket targeting accuracy requirements are defined in classified annex.

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3.4.9.2.1 Hellfire(TT1) The ARH shall carry, control, and launch up to 4 Semi-Active Laser Hellfire Air-to-Ground Missiles.

3.4.9.2.2 Rockets(T) The ARH shall carry, control, and launch up to fourteen (14), 2.75 inch folding fin aerial rockets.

(O) The ARH shall carry, control, and launch up to thirty-eight (38), 2.75 inch folding fin aerial rockets.

(T) The ARH shall mount two M260 7 shot rocket launchers.

(O) The ARH shall mount two M261 19 shot rocket launchers.

(TT2) The ARH shall be capable of setting the fuses and launching rockets with the MK66 mod 4 motor and the following warhead configurations:

M261 Multi Purpose Sub-Munition (MPSM) High Explosive (HE)

M276 MPSM Practice

M264 Smoke Red Phosphorus (RP)

M255A1 Flechette

M257 Illuminating flare

M278 Illuminating Flare

M278 Infrared Flare

M229 High Explosive (17 pound)

M151 High Explosive (10 pound)

WTU-1/B (practice)

M274 (practice) Smoke Signature

3.4.9.2.3 Armament Trajectory/Aircraft Clearance(TT1) At least six (6) inches of clearance shall be maintained between the gun bullet trajectory and all rotor disk positions and all other aircraft and stores surfaces. The clearance for guided and unguided rocket/missiles shall be a five-degree half angle cone measured from the trajectory of the outermost surface of the ordnance to the worst-case rotor plane or aircraft surface. All armament trajectories shall account for worst-case position in the firing envelope and ordnance dispersion.

3.4.9.2.4 Armament /Aircraft Compatibility (TT1) The ARH shall have the capability to launch/fire armament throughout the operational flight envelope as long as the armament launch/firing inhibits are not exceeded. It shall have the capability to prevent launch/firing when the armament safety and performance inhibits are exceeded. Performance inhibits shall be capable of being overridden by the crew. The ARH

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shall have safeguards to prevent inadvertent firing of armament. Armament launch/firing shall not damage the aircraft, crew, onboard equipment, or adversely affect engine/transmission performance.

3.4.9.2.5 Armament Boresight(TT1) Armament boresight is required to meet the armament accuracy requirements defined in the classified annex. Boresight shall be retained for 250 flight hours.

3.4.9.3 Self-Protection(TT1) The ARH shall incorporate, when required by the mission, a .50 caliber machine gun or 7.62 mm machine gun. The ARH shall carry up to 500 rounds of ammunition for the .50 caliber machine gun and 2,000 rounds for the 7.62 mm machine gun.

3.4.9.4 Weapons Mounting Station(TT1) Weapons mounting stations shall be provided on the port and starboard sides of the aircraft. As a minimum, each mounting station shall be capable of carrying and employing any one of the following payloads:

(T) 2 x SAL Hellfire Missiles

(T) 7 x 2.75 inch folding fin rockets

(O) 19 x 2.75 inch folding fin rockets

(T) 1 x .50 caliber or 7.62mm machine gun

3.4.9.5 Emergency Release of Stores(T) Within the limits of the stores jettison envelope, the system shall allow for positive separation, and steadily increasing distance of the store from all components of the aircraft, including inadvertent releases while hands on grip.

3.4.9.6 Arm/Rearm(TT2) The ARH shall be armed/rearmed in no more than 30 minutes by a crew of 2.

3.4.9.7 Open Weapon System Architecture(TT2) The ARH shall have an open weapons architecture that allows for incorporation of future armament systems and munitions such as the Advanced Precision Kill Weapon System (APKWS) and Joint Common Missile (JCM).

3.5 Survivability(TT1) The ARH shall incorporate an integrated control and display for the ASE suite.

3.5.1 Radar Detection(TT1) The ARH shall have a radar warning receiver that provides detection, angle of arrival, and identification of radar threats.

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3.5.2 Infrared (IR)

3.5.2.1 IR Countermeasures(T) The ARH shall have a X% probability of successfully surviving a SA-XX missile engagement at a range of X meters by preventing successful lock-on or causing the missile to miss.

(O) The ARH shall have a X% probability of successfully surviving all Band XX missile engagements at a range of X minus meters by preventing successful lock-on or causing the missile to miss.

3.5.2.2 IR Suppression(O) The ARH shall have an infrared engine exhaust suppressor system.

3.5.3 Laser Detection(TT1) The ARH shall have a laser detection system that provides detection of laser threats to the flight crew.

3.5.4 Ballistic Protection(TT1) The ARH shall have crew station seat and floor armor that provides crew protection against impact from a single armor piercing incendiary (API) xxxx mm round as defined in the classified annex.

(O) The ARH shall have crew station seat and floor armor that provides crew protection as well as armor that provides protection for critical flight control systems and engine electronic controls against impact from a single API xxxx mm round as defined in the classified annex.

3.5.5 Seats(T) Crew seats requirements shall meet the FAR 27.562 Emergency Landing Dynamic Conditions.

(TT3) Crew seats shall meet the requirements of JSSG-2010-7 or equivalent.

(T) Crew seats shall meet the requirements of 14 CFR, Part 27, Amendment 27-25, Section 27.562.

(TT3) Crew seats shall meet the requirements of 14 CFR, Part 27, Amendment 27-25, Section 27.562 for the target Army Aviator population.

(TT1) The seats shall include self extinguishing padding and covers. Seat cushions shall be accounted for in the crashworthiness of the seat.

(TT1) The seat shall have a headrest that accommodates the target Army Aviator population with the HGU-56P helmet. The headrest shall accommodate the night vision goggle battery pack.

(TT2) There shall be a positive method of guarding against equipment under the seat.

(TT2) This seat shall support the target Army Aviator population attired in all personnel and protective gear to include the Air Warrior ensemble. A 5-point harness is acceptable and shall be used with a minimum of an MA-16 inertia reel. The seat release mechanism shall allow

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disconnect time in under 20 seconds. The release shall be of rotary type and shall be able to be operated with 1 finger. The release shall also work in every axis including full 180 degrees with the weight of the crew member resting on it.

3.5.6 Airframe Crashworthiness(TT2) The ultimate crash load factors of crew seats and seat installation, personnel restraint systems, fuel tank, equipment items, or any other object which would result in personnel injury in the event of a crash, shall be CFI.

3.5.7 Major Component Displacements(T) Major components, such as the transmission, engine, and sensor assembly, shall not be displaced into occupied space in the event of a crash.

3.5.8 Blade Strikes(TT2) The helicopter shall make a survivable landing when the main rotor blade impacts a CFI inch diameter hardwood branch at normal rotor speed or the tail rotor strikes a hardwood branch of CFI inch diameter.

3.6 Environmental Conditions

3.6.1 Physical EnvironmentThe ARH shall operate within the environmental conditions specified below.

3.6.1.1 Low Pressure (Altitude)(TT1) The ARH and/or its equipment/components shall be able to withstand the storage/air transport low pressure (altitude) conditions at altitudes to 50,000 feet above sea level as outlined in MIL-STD-810F, Method 500.4, Procedure I. The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to the operational low pressure (altitude) conditions at the altitudes to 20,000 feet as outline in MIL-STD-810F, Method 500.4, Procedure II.

3.6.1.2 Temperature

3.6.1.2.1 Operating(TT1) The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to high operational temperature conditions outlined in MIL-STD-810F, Method 501.4, Procedure II with an upper limit of 122oF. The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to low operational temperature conditions outlined in MIL-STD-810F, Method 502.4, Procedure II with an lower limit of -40oF. Winterization kits may be used below -20oF.

(O) The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to high operational temperature conditions outlined in MIL-STD-810F, Method 501.4, Procedure II with an upper limit of 140oF.

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3.6.1.2.2 Non-Operating(TT1) The ARH and/or its equipment/components shall be able to withstand the non-operating high temperature conditions outlined in MIL-STD-810F, Method 501.4, Procedure I with an upper limit of +160oF without degradation in performance or mission readiness. The ARH and/or its equipment/components shall be able to withstand the non-operating low temperature conditions outlined in MIL-STD-810F, Method 502.4, Procedure I with a lower limit of -65OF without degradation in performance or mission readiness.

3.6.1.2.3 Temperature Shock(TT1) The ARH and/or its equipment/components shall withstand the effects of movement to and from heated storage, maintenance, or other enclosures or a heated cargo compartment with a temperature range of +122oF to -40oF as outlined in MIL-STD-810F, Method 503.4, Procedure I.

(O) The ARH and/or its equipment/components shall withstand the effects of movement to and from heated storage, maintenance, or other enclosures or a heated cargo compartment with a temperature range of +140oF to -40oF as outlined in MIL-STD-810F, Method 503.4, Procedure I.

3.6.1.3 Rain

3.6.1.3.1 General Requirements(TT1) The ARH and/or its external equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of rain and blowing rain as outlined in MIL-STD-810F, Method 506.4, Procedure I. Internal equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of falling water as outlined in MIL-STD-810F, Method 506.4, Procedure III.

3.6.1.3.2 Blades(TT2) Main and tail rotor blades shall provide for erosion protection against a rainfall rate of 1 inch per hour for 6 hours. Raindrop sizes shall range from 0.5mm to 4.0mm with a median size of 2.5 mm.

3.6.1.4 Icing/Freezing Rain(TT1) The ARH and/or its external equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of icing/freezing rain as outlined in MIL-STD-810F, Method 521.2, Procedure I.

3.6.1.5 Humidity(TT1) The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to humid environmental conditions as outlined in MIL-STD-810F, Method 507.4.

3.6.1.6 Fungus(TT1) The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of fungus as outlined in MIL-STD-810F, Method 508.5.

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3.6.1.7 Salt Fog(TT1) Salt fog shall not cause clogging or binding of mechanical components or assemblies, electrical malfunctions, or corrosion that affects proper operation of structural integrity of the aircraft when exposed to the salt fog environmental conditions as defined in MIL-STD-810F, Method 509.4.

3.6.1.8 Sand and Dust

3.6.1.8.1 General Requirements(TT1) The ARH and/or its equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of sand and dust outlined in MIL-STD-810F, Method 510.4, Procedures I and II.

3.6.1.8.2 Blades(TT2) Both main and tail rotor blades shall withstand sand/dust erosion from 125 hours of continuous exposure to the environment which exists when the aircraft is hovering at primary mission gross weight and a 5 foot skid height above sand/dust consisting of crushed quartz with the total particle size distribution as follows:

Quantity (percent by Particle Size weight finer than

(microns) size indicated)1,000 100 900 98-99 600 93-97 400 82-86 200 46-50 125 18-22 75 3-7

3.6.1.9 Explosive Atmosphere(TT1) All ARH equipment/components located in a potential fuel/air explosive atmosphere environment, as outlined by MIL-STD-810F, Method 511.4, Procedure I, shall be capable of meeting all operational requirements without causing ignition via electrical, hot spot, or other means.

3.6.1.10 Shock

3.6.1.10.1 Functional Shock(TT1) All ARH equipment/components shall meet their individual performance requirements while exposed to the environmental conditions of functional shock as outlined in MIL-STD-810F, Method 516.5, Procedure I.

3.6.1.10.2 Bench Handling Shock(TT1) All ARH equipment/components shall meet their individual performance requirements after exposure to the environmental conditions of bench handling shock as outlined in MIL-STD-810F, Method 516.5, Procedure VI.

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3.6.1.10.3 Crash Hazard Shock(TT1) All ARH equipment/components determined to pose a crash hazard threat to the crew or reduce airworthiness of the aircraft shall maintain structural integrity after exposure to the environmental conditions of crash hazard shock as outlined in MIL-STD-810F, Method 516.5, Procedure V.

3.6.1.11 Induced Vibration(TT1) Subsystems, furnishings, and equipment shall be compatible with the air vehicle induced vibration environment and the gunfire vibration environment. Vibration environments may be defined using ADS-27 and MIL-STD-810 as guides.

3.6.1.12 Solar Radiation(TT1) All ARH external equipment/components directly exposed to solar radiation or sunlight sensitive internal components which may be exposed to sunlight for indefinite time periods shall meet their individual performance requirements and shall be able to withstand exposure to the environmental conditions of sunlight as outlined in MIL-STD-810F, Method 505.4, Procedure II.

3.6.1.13 Acceleration (TT1) Through analysis, all ARH equipment/components, whose structural integrity could be affected by exposure to inertia loads, shall withstand exposure to acceleration, deceleration and envelope maneuvers as outlined in MIL-STD-810F, Method 513.5, Procedure I.

(TT1) Through analysis, all ARH equipment/components, whose performance could be affected by exposure to inertia loads, shall meet their operational requirements while exposed to acceleration, deceleration and envelope maneuvers as outlined in MIL-STD-810F, Method 513.5, Procedure II.

3.6.2 Electromagnetic Environmental Effects (E³)

3.6.2.1 Electromagnetic Interference (EMI) (T) All electrical/electronic equipment not previously installed on the ARH COTS configuration shall meet the electromagnetic interference requirements as defined in MIL-STD-461 as modified by ADS-37A-PRF, paragraph 3.2.

(TT3) The ARH shall comply with the requirements of STANAG 3516.

3.6.2.2 Electromagnetic Compatibility (EMC)(T) The system shall not exhibit any EMC anomalies that would degrade flight critical, flight essential, mission critical and/or mission essential functions that preclude mission success IAW ADS 37A-PRF, paragraph 3.3.


3.6.2.3 Electromagnetic Vulnerability (EMV)(T) The system shall meet the EMV requirements of ADS-37A-PRF, paragraph 3.4.

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3.6.2.4 Electromagnetic Pulse (EMP)(TT1) The design of the ARH shall provide the aircraft the capability to land safely after exposure to the EMP environment as defined in ADS-37A-PRF paragraph 3.5.

3.6.2.5 Hazards of Electromagnetic Radiation to Ordnance (HERO)(T) The ARH shall meet the HERO requirements of ADS-37A-PRF, paragraph 3.6.1.

3.6.2.6 Hazards of Electromagnetic Radiation to Fuel (HERF)(T) The ARH shall meet the HERF requirements of ADS-37A-PRF, paragraph 3.6.2.

3.6.2.7 Hazards of Electromagnetic Radiation to Personnel (HERP)(T) The ARH shall meet the HERP requirements of ADS-37A-PRF, paragraph 3.6.3.

3.6.2.8 Aircraft Discharge(T) The ARH shall meet the aircraft discharge requirement of ADS-37A-PRF, paragraph 3.7.1.


3.6.2.9 Precipitation Static(T) The ARH shall control static electricity (p-static) IAW ADS-37A-PRF, paragraph 3.7.2.

3.6.2.10 Personnel Handling of Ordnance(T) The ARH and its ordnance shall meet the electrostatic discharge requirements of ADS-37A-PRF, paragraph 3.7.3. Handling procedures may be required to prevent electrostatic discharge damage to equipment during maintenance.

(TT3) The ARH shall comply with the requirements of STANAG 3632

3.6.2.11 Lightning Protection(TT1) The rotor blade shall withstand a 200,000 amp lightning strike without catastrophic damage with attachment occurring at any part of the blade.

(TT3) The ARH shall survive the direct and indirect effects of a lightning strike and shall be such that flight critical equipment allows a safe landing of the aircraft following a strike. The lightning environment shall be defined as specified in RTCA/DO-160D and FAA AC 20-136, tailored by ADS-37A-PRF, paragraph 3.8.

3.6.2.12 Electrical Bonding(T) The ARH shall meet the electrical bonding requirements of MIL-STD-464, except that the RF bonding of the electronics shall meet the 2.5 milliohm requirement of ADS 37A-PRF, paragraph 3.10, or the RF bonding requirements specified in the component ICD.

3.6.2.13 Life Cycle E³ Hardness(T) The ARH shall meet the Life Cycle E³ Hardness requirements of ADS-37A-PRF, paragraph 3.11.

3.7 Sustainability The support system for the ARH shall consist of all technical manuals, hardware, support equipment, software and documentation for each configuration required to sustain the ARH

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aircraft for both war-time and peace-time. The ARH shall be capable of being supported under the current Army logistical system.

3.7.1 Maintenance Concept(T) The ARH shall be compatible with the Army Aviation three level maintenance infrastructure. All components, systems, or subsystems developed uniquely for use on the ARH shall be maintainable under the two level maintenance concept.

(O) The ARH shall achieve a two level (user level and depot level) maintenance concept.

3.7.2 Computer Resources Support(TT1) The ARH shall be supported by existing and/or planned common computer resources. The ARH shall have an architecture that minimizes computer resource constraints (e.g. language, computer, database, architecture or inoperability), unique interface requirements, documentation needs or special software certification. The ARH shall provide the capability to digital transfer logistics data from the aircraft to the current Army Standard Army Information Management System (STAMIS) and future Global Combat Support System-Army (GCSS-A) network. The ARH and any maintenance instrumentation equipment shall be compatible with the Army’s automated logistics support system utilizing an electronic logbook. Interface and downloading device(s) and procedures shall be provided. The ARH support system shall provide a capability to update embedded air vehicle software at the Aviation Unit and Intermediate Maintenance Levels.

3.7.3 Packaging, Handling, Storage (T) Containers shall be designed or modified as required to provide Level A protection as specified in MIL-STD-2073-1.

3.7.4 Publications(T) The support system shall include an Interactive Electronic Technical Manuals (IETM) IAW MIL-STD-40051 and MIL-STD-2361.

(TT1) Specific IETM functionality shall be in accordance with CDRL A075, Preparation of Digital Technical Information for Multi-Output Presentation of Technical Manuals, and associated Functionality Matrix and Frame-Based TM Requirements Matrix.

3.8 ReliabilityThis section specifies the ARH system-level reliability performance parameters required to achieve mission success for the specified wartime operational mode summary / mission profile (OMS / MP), Attachment 1. Reliability will be assessed analytically using the US Army Training and Doctrine Command (TRADOC) approved Logistical/Operational Readiness Impacts of Maintainability and Reliability Requirements (LORIMRR) program and through demonstrations. The specified reliability performance parameters directly relate to either operational effectiveness or impact operating and support cost. For reliability, all maintenance actions are classified as scheduled or unscheduled. Scheduled maintenance actions include preventive maintenance actions. Failures resulting in unscheduled maintenance actions are categorized as: non-essential function failures (NEFF), essential function failures (EFF), and System Aborts (SA).

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3.8.1 Mean Time Between Essential Function Failure (MTBEFF) (TT1) The ARH shall achieve an MTBEFF of at least 3.5 hours. The MTBEFF is the average time between mission- essential functional failures. MEFF do not necessarily have to occur during a mission; they merely must or could cause mission impact. MTBEFF is calculated as follows:

MTBEFF = Operating Time / # EFF’s

(O) The ARH shall achieve an MTBEFF of at least 4.5 hours.

3.8.2 Mean Time Between System Aborts (MTBSA). (T) The ARH shall achieve a MTBSA of 10.0 hours. MTBSA is a measure of the ability of a single ARH to complete a mission. A system abort includes those malfunctions causing the termination of the mission prior to scheduled completion. MTBSA is calculated as follows:

MTBSA = Operating Time / # System Aborts

(O) The ARH shall achieve an MTBSA of 33.0 hours.

3.9 Maintainability This section specifies the ARH system-level maintainability performance parameters required to achieve mission success for the specified wartime Operational Mode Summary/Mission Profile OMS / MP. These parameters directly relate to either operational effectiveness or impact operating and support cost. All maintainability performance is based upon an operational tempo (OPTEMPO) of 80 flight hours per month per aircraft for 10 aircraft using an Administrative and Logistical Downtime (ALDT) of 3.4 hours.

3.9.1 Direct Maintenance Man-Hour per Flight Hour (DMMH / FH). (TT1) The ARH shall achieve a DMMH / FH of no more than 3.5 hours. This ratio reflects the total maintenance manpower burden required in an operational environment to maintain the system at the desired operational readiness levels. DMMH / FH is defined as the cumulative number of direct man-hours of maintenance expended in direct labor during a given period of time, divided by the cumulative number of flight hours during the same time period. DMMH /

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FH includes on-aircraft unscheduled and scheduled maintenance. DMMH / FH are calculated as follows:

DMMH / FH = direct maintenance man-hours expended / flight hours

(O) The ARH shall achieve a DMMH / FH of no more than 2.6 hours.

3.9.2 Mean Time To Repair- Essential (MTTRe). (TT1) The ARH shall achieve an MTTRe of 1.5 hours. MTTRe is used as an "on-system" maintainability index and is not used for the off-system repair of replaced components. For a particular interval, MTTRe is calculated as follows:

MTTRe = "on-system" Essential Maintenance Clock hours / # of EFFs

(O) The ARH shall achieve an MTTRe of 1.0 hours.

3.10 Battle Damage Assessment and Repair (BDAR)BDAR is rapid damage assessment and repair, bypassing or jury-rigging components, to restore minimum essential capability to support a combat mission or enable self-recovery. Such enabling repairs may be temporary or permanent, depending on the repair required. In many cases, they may not restore full mission capability. BDAR determines damage and reparability, the assets needed to make the repair, and where the repair should take place. BDAR includes any expedient action that returns a damaged part or assembly to mission-capable or limited mission-capable condition within the BDAR time and duration performance parameters stated below.

3.10.1 BDAR Time(TT2) BDAR component repair and line replaceable unit (LRU) replacement shall not exceed 3.0 hours 95% of the time.

3.10.2 BDAR Duration(TT2) BDAR shall be durable for > 80 hours of operation.

3.11 Diagnostics

3.11.1 Detection and Isolation (TT1) The ARH shall achieve a fault detection and isolation capability sufficient to meet the MTTRe threshold requirement.

(O) The ARH shall achieve a fault detection and isolation capability sufficient to exceed the MTTRe threshold requirement.

3.11.2 False Alarm Rate(TT1) The ARH shall achieve a 10% false alarm rate.

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(O) The ARH shall achieve a 5% false alarm rate.

3.12 Facilities(TT1) The ARH shall not require any unique fixed facilities or shelters.

EXISTING HANGER FACILITIES

Utilities;

120 VAC, 3 Phase, 400 Hz, 157 AMPS

220/440 VAC, 3 phase 60 Hz

28 VDC, 15 AMPS

120 PSI (compressed air)

3.13 Training

3.13.1 Integrated Training Program (ITP)(T) The ARH shall have an ITP developed IAW the Systems Approach to Training (SAT) process that supports individual and collective training, at the training institution, within live, virtual, and constructive environments.

(O) The ARH shall have an ITP developed IAW the SAT process that supports individual and collective training, at the training institution, within live, virtual, constructive, and embedded training environments. The embedded training capabilities shall utilize the same tactical hardware of the system while incorporating embedded training software.

3.13.2 Operational Training Engagement System

3.13.2.1 Tactical Engagement Simulation System (TESS)(T) The ARH ITP shall provide individual, crew, team and functional operator training interoperable with the Tactical Engagement Simulation System (TESS).

The TESS is a complete deployable Home Station Instrumentation (HSI). It consists of both air and ground components to provide realistic multi-echelon training for gunnery, collective and force-on-force training. The air component is designed to mount onto the aircraft and provide training capability and feedback to the aircrew, as well as the company and battalion. The ground component provides the capability for each battalion to create and train against an opposing force (OPFOR) with full, Force-on-Force (FoF) shoot-back capability. It also provides the telemetry to monitor the exercise in Real-time on color. It also provides the telemetry to monitor the exercise in Real-time on color digital map generated by the Mobile Command and Control (MCC) center that records the training events as they are occurring and then play them back for After Action Review (AAR).

3.13.2.2 Embedded Instrumentation(T) ARH shall have the capability to support the training systems planned for the National Training Center (NTC), JRTC and the Combat Maneuver Training Center must be provided. Embedded components (A-Kit) shall be used to the maximum extent practical.

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3.14 MANPRINT General (TT2) The ARH shall accommodate the 5th female through 95th male soldier in accordance with NATICK TR 089-044 for critical body dimensions and strength characteristics, attired in all personnel and protective clothing/equipment to include Air Warrior applicable to the full range of flight maneuvers including full aft cyclic position, all crew mission functions, personnel restraints, emergency egress, and maintenance and support functions.

(O) The ARH shall accommodate the Electronic Data Manager (EDM), ensuring that the EDM can be worn on either leg without cyclic/collective interference during flight.

3.14.1 Personnel(T) The ARH shall not exceed personnel skill levels of OMS personnel requirements of the OH-58D and the soldier characteristics identified in the Target Audience Description (TAD). The number of ARH OMS personnel shall not exceed the number of OH-58D OMS personnel.

3.14.2 Human Factors Engineering(TT1) Parts/component marking, interface, and required maintenance procedures shall be designed to minimize error induced malfunction or failure. Accessibility of subsystem assemblies for inspection, servicing, and maintenance shall be integrated with design to eliminate or control safety hazards. All system requirements shall be met with the soldier-in-the-loop while using appropriate combat gear and wearing protective clothing. Soldier/system interface shall minimize the requirement for: (1) Separate, one time use, component securing and/or locking devices, i.e., safety wire, lock(ing) tabs, and cotter pins; (2) The use of special tools and peculiar ground support equipment; (3)Components that can be installed incorrectly, i.e., backward, upside down, reversed, or wrong location; (4) Close-proximity connections which are interchangeable; (5) The removal of serviceable components to gain access to failed components; (6) The use of torque measuring devices.

3.14.3 Soldier Survivability(TT1) The ARH weapon system shall increase the probability of Operator, Maintainer, and Support (OMS) personnel survivability in all operational scenarios when compared to the current OH-58D fleet.

3.14.4 System Safety(T) All lasers shall be in accordance with Title 21, Part 1040 (21 CFR 1040), Performance Standards for Light-Emitting Products, and American National Standards Institute Z136.1-2000, Safe Use of Lasers (ANSI Z136.1-2000), unless a written exemption has been provided to the contractor by the Government. All exemption requests shall specify which provisions of 21 CFR 1040 and ANSI Z136.1-2000 are to be waived and the alternative hazard controls which will be applied. Microwave and radio frequency emissions shall comply with Institute of Electrical and Electronics Engineers C95.1- 1999, (IEEE C95.1- 1999), IEEE Standard for Safety Levels with Respect to Human Exposure to Radio Frequency Electromagnetic Fields, 3 kHz to 300 GHz, in areas of the aircraft which are accessible during flight and external areas in which personnel may be present during on-ground system(s) operation..

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3.15 Transportability

3.15.1 Embark Operations(T) The ARH shall have the ability to embark on a C130 in 15 minutes or less with no special equipment and a crew of 4. Embark operations shall be defined as disassembly, preparation, loading, tie-down and all removed components secured, and load-out support and soldier equipment, onboard the cargo aircraft.

(TT1) The ARH shall have the ability to embark on a C5, or C17, in 15 minutes or less with no special equipment and a crew of 4.

3.15.2 Debark Operations (T) The ARH shall have the ability to debark from a C130 in 15 minutes or less with no special equipment and a crew of 4. Debark operations include: unsecuring, off-loading, reassembling, refueling, rearming, and startup to the configuration defined in the Standard Armed Reconnaissance Gross Weight paragraph of this specification. No test flight shall be required.

(TT1) The ARH shall have the ability to debark from a C5, or C17, in 15 minutes or less with no special equipment and a crew of 4.

3.15.3 Intra-Theatre Transportability (T) The ARH shall be transportable with two (2) per C130.

(O) The ARH shall be transportable with three (3) aircraft per C130.

3.15.4 Strategic Transportability (TT1) The ARH shall be transportable with 8 aircraft per C17.

(TT1) The ARH shall be transportable with 16 aircraft per C5.

(O) The ARH shall be transportable with a minimum of 10 aircraft per C17.

(O) The ARH shall be transportable with a minimum of 20 aircraft per C5.

3.16 Other Transportability Requirements(TT1) The ARH shall be transportable by naval ships such as light assault ship helicopter (LASH) lighter ships; Seabee barge/ships, roll-on/roll-off (RORO) ships, seatrain ships, and fast sealift ship (FSS). ARH shall be capable of incorporating military standard lifting and tie down provisions.

(TT1) ARH shall be ground transportable by commercial semi-trailer or military NH-72 semi-trailer and US Army family of transport vehicles. The ARH shall meet US and North Atlantic Treaty Organization (NATO) highway limits. Transport of ARH aircraft must be accomplished without system damage or degradation in system performance.

3.17 Recovery(TT1) The ARH shall have an interface for rapid aerial recovery by CH-47 and UH-60 utilizing the Unit Maintenance Aerial Recovery Kit (UMARK).

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4 Verification

4.1 Requirements Verification

The verification methods shall be contractor provided and Government approved. The requirements shall be verified as in the verification matrix with content as shown in Table III.

Table III Sample Requirements Verification Matrix

Requirement

(Section 3.0)

Verification

(Section 4)

Verification Method Verification Level

3.2.1 4.2.1 See methods below System, assembly, LRU,component, etc.

3.2.1.1 4.2.1.1 See methods below System, assembly, LRU, component, etc.

3.2.1.2 4.2.1.2 See methods below System, assembly, LRU, component, etc

4.2 Verification Methods

Verification Methods are as follows:

a) Demonstration. Demonstration shall consist of a functional verification in which the observation of events is the predominant vehicle. Measurements are not usually required. When appropriate, it includes the actual exercise of software along with appropriate drivers, simulators, or integrated hardware to verify that requirements have been satisfied.

b) Inspection. Inspection shall consist of visual examination, physical manipulation, or measurement (as applicable) of documentation, hardware, or software to verify that requirements have been satisfied.

c) Analysis. Analysis shall consist of the examination of applicable attributes of the existing documentation, hardware, software, and recorded data to verify that requirements have been satisfied. Analysis includes verification by investigation, mathematical analysis, and sampling the collection of measured data and observing test results with calculated, expected values to establish conformance with stated requirements.

d) Test. Test shall consist of the collection of analysis of data obtained from the actual exercise of hardware and/or software in either a controlled or an operational environment as appropriate. Actual input stimuli and/or stimuli obtained from drivers or simulators

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are employed as deemed appropriate. Comparison of the tested characteristics with performance and operational requirements is the usual means employed to verify that requirements have been satisfied.

e) Simulation. Simulation includes verification through the use of mathematical models incorporated into a simulation which replicates the following: the operation or performance of the equipment being evaluated; the threat which the equipment must operate against; the environment in which the equipment must operate; and combinations of the equipment, threat, and environmental simulators.

f) Similarity. Similarity shall consist of verification requirements that are previously satisfied through other programs.

5 Packaging

For acquisition purposes, the packaging requirements shall be as specified in the contract or order. When actual packing of material is to be performed by DoD personnel, these personnel need to contact the responsible packaging activity to ascertain requisite packaging requirements. Packaging requirements are maintained by the Inventory Control Point's packaging activity within the Military DoD Agency, or within the Military Department's System Command. Packaging data retrieval is available from the managing Military Department's or Defense Agency's automated packaging files, CD-ROM products, or by contacting the responsible packaging activity.

6 Notes

This section contains information of a general or explanatory nature that may be helpful but not mandatory.

6.1 Change in Design Envelope and Usage SpectrumAny change in baseline Design Cruise Altitude, Maximum Altitude, Landing Speed, Landing Conditions, Operational Environments, and Usage Spectrum will change the loads that the aircraft experiences. The Design Envelope and Usage Spectrum are the baseline from which loads are developed. Any alteration in these will affect the original certification. The increase in altitude pressure loads may affect the certification and result in additional requirements for full-scale pressure load tests. Any change to the baseline aircraft Usage Spectrum may affect the engine certification and require additional analysis or testing to determine the impact to engine life. Increased SHP extraction may impact the qualification of the engine and the gearbox. Airworthiness Approval

6.1.1 U.S. Army Qualified AircraftAirworthiness for an existing U.S. Army aircraft will be based on a currently issued Airworthiness Release (AWR), an Interim Statement of Airworthiness Qualification (ISAQ) or a Statement of Airworthiness Qualification (SAQ). All modifications impacting airworthiness will subject the aircraft system, subsystem or allied equipment to re-qualification. An AWR, ISAQ or SAQ is required for all modifications impacting airworthiness of Army aircraft for which

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AMCOM has engineering cognizance. Airworthiness approval is based on technical data requirements established by AMCOM.

6.1.2 Other AircraftAirworthiness approval for other aircraft will come from recognized airworthiness authorities (the FAA, NASA, U.S. Air Force, U.S. Navy, or a foreign authority whose airworthiness approval has been accepted by a U.S. agency). The appropriate airworthiness authority is the one exercising engineering cognizance over the aircraft system for which the airworthiness approval is granted. This approval will result from a demonstrated capability to function satisfactorily when used within the prescribed limits and be in the form of any technical document that provides operating instructions and limitations necessary for safe operation and flight of an aircraft system, subsystem, or allied equipment. Modifications to other aircraft (system, subsystem, or allied equipment) will require an airworthiness assessment. Based on this assessment, a determination will be made by AMCOM of the extent of airworthiness qualification and appropriate documentation required for in-flight operation.

6.2 CommonalityContractor should maximize commonality with existing Army Aviation assets in selecting components. Maximized commonality will lead to reduced recurring hardware costs, reduced field support costs, and reduced schedule impacts.

6.3 Information Exchange RequirementsThe Net Ready KPP has replaced the IER-based Interoperability KPP; however, IERs are still an important part of the overall DoD plan for Net-Centric warfare. IERs are now the Operational View (OV)-3 which is one of the many required operational architecture views that the Attack / Recon TSM is responsible for. The ARH OV-3 is available for informational purposes on the ARH website.

6.4 Air Warrior Configurations(1)The following mission equipment configuration information is provided as Air Warrior (AW) anthropometric data for helicopter seat compatibility:

(a) Basic ensemble - The core worn clothing and mission equipment to include boots, socks, undergarments, aircrew battle dress uniform,HGU-56P helmet, first aid kit, survival kit, gloves, and survival vest. Total weight is 25 pounds.

(b) Basic ensemble, hot environment - Add a microclimatic cooling garment to the basic ensemble which can keep the aviator cool in extreme hot environments or when wearing NBC protective gear. Total weight is 27 pounds.

(c) Basic ensemble, hot environment, over water - Add an air bottle, water protection gear, and a backpack life raft. Total weight is 43 pounds.

(d) Basic ensemble, cold environment, over water - Add cold weather protection clothing. Total weight is 50 pounds.

(e) Basic ensemble, combat - Add soft and hard body armor to pilot/copilot, front only, add 9mm weapon, ammunition, and holster. Total weight is 44 pounds.

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(f) Basic ensemble, cold environment, over water, combat, chemical/biological protective gear - Add chemical protective undergarment, M45 Mask and blower, over-boots, decontamination kit. Total weight is 82 pounds.

(2) The AW ensemble places the over water kit in the backpack. The backpack replaces the seat’s rear cushion and permits the same occupant seat position as when the cushion is installed. The dimensions of the over water gear carrier (OWGC) are: 20" tall, 13" wide, with side pouches for the HEEDs bottle and gear pouch which increase width to 18 inches maximum. The OWGC does not exceed 2.5 inches in thickness.

(3) Placement for the attachment of the microclimatic cooling umbilical control block must be considered. The placement is to be at the aviator’s right hip.

(4) The following Air Warrior documents are available on the Government ARH Website:

(a) AVNS-PRF-10173, Performance Specification Item Specification for the Microclimate Cooling Unit (MCU) and Control/By-Pass Assembly (CBA)

(b) Interface Design Description (IDD), Microclimate Cooling Unit for Air Warrior

(5) As a minimum, the MCU A kit must be installed and included in the computation of the Standard Armed Reconnaissance Mission Configuration weight.

6.5 Fuel Quantity GaugingMIL-G-7940, Class 2, may be used as a guide for the main fuel tank(s), as well as any internal or external auxiliary fuel tanks (if required), and total fuel.

6.6 Acronyms and Abbreviations A2C2S Army Airborne Command and Control System ADI Attitude Direction Indicator AGL Above Ground LevelAIMS Air Traffic Control Radar Beacon System Identification Friend or Foe Mark XII Systems ALDT Administrative and Logistical Downtime AMCOM Aviation and Missile CommandAMPS Aviation Mission Planning SystemAPI Armor Piercing Incendiary APKWS Advanced Precision Kill Weapon SystemARH Armed Reconnaissance HelicopterASE Aircraft Survivability EquipmentATC Air Traffic ControlATCRBS Air Traffic Control Radar Beacon SystemATR Aided Target RecognitionAW Air WarriorAWACS Airborne Warning and Control System AWR Airworthiness ReleaseBDAR Battle Damage Assessment and RepairBFT Blue Force Tracking

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BIT Built in TestBLOS Beyond Line of SightC/JMTK Commercial Joint Mapping ToolkitC2 Command and Control CASS Common Avionics Architecture SystemCFI Contractor Furnished InformationCMF-B Common Message Format - BinaryCSI Critical Safety ItemCSMU Crash Survivable Memory Unit CSVD Continuously Variable Slope Delta-Modulation CTSF Central Technical Support FacilityCVR Cockpit Voice Recorder DAFIF Digital Aeronautical Feature Information FileDAMA Demand Assigned Multiple AccessDCGS-A Distributed Common Ground Station-ArmyDISR Defense Information Technology Standards Registry DME Distance Measuring Equipment DMMH / FH Direct Maintenance Man-Hour / Flight HourDoD Department of DefenseDTS Data Transfer SystemE3 Electromagnetic Environmental EffectsEFF Essential Function Failures EGI Enhanced GPS Inertial Navigation SystemEMP Electromagnetic Pulse EMV Electromagnetic Vulnerability EOCCM Electro-optical Counter Counter MeasuresEPLRS Enhanced Position Location Reporting SystemESIP Enhanced System Improvement ProgramFAA Federal Aviation AdministrationFBCB2 Force XXI Battle Command Brigade and BelowFCS Future Combat System FD/FI Fault Detection / Fault Isolation FLIR Forward Looking Infrared FOD Foreign Object Debris FOR Field of RegardFOV Field of ViewFSCS Flight Safety Critical SoftwareGATM Global Air Traffic Management GCSS-A Global Combat Support System-Army (replaces ULLS-A)

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GIG Global Information Grid GPS Global Positioning SystemGOTS Government Off The ShelfHE High Explosive HERF Hazards of Electromagnetic Radiation to Fuel HERO Hazards of Electromagnetic Radiation to Ordnance HERP Hazards of Electromagnetic Radiation to Personnel HOGE Hover Out of Ground EffectHSI Horizontal Situation IndicatorIAW In Accordance WithIB International BureauIBS Integrated Broadcast Services ICAO International Civil Aviation OrganizationICS Intercommunication Subsystem ID IdentificationIDM Improved Data ModemIER Information Exchange RequirementsIFF Identification Friend-or-FoeIFR Instrument Flight Rules ILS Integrated Logistics SupportIMC Instrument Meteorological ConditionsIPF Interference Protection Feature IR InfraredIRP Intermediate Rated Power ISAQ Interim Statement of Airworthiness Qualification ITP Integrated Training ProgramJCM Joint Common Missile JITC Joint Interoperability Test CommandJMPS Joint Mission Planning SystemJRTC Joint Readiness Training CenterJSSG Joint Service Specification GuideJSTARS Joint Service and Target Attack Radar System JTRS Joint Tactical Radio SystemKbps Kilobit per SecondKIP Key Interface Pointskm KilometerKPP Key Performance Parameterskts KnotsKTAS Knots True Airspeed LASH Light Assault Ship Helicopter

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LHA Landing Helicopter AssaultLHD Landing Helicopter DockLLCTV Low-Light Color Television

LORIMRRLogistical / Operational Readiness Impacts of Maintainability and Reliability Requirements

LOS Line-of-SightLPC Linear Predictive Coding LRF/D Laser Rangefinder / Designator LRU Line Replaceable UnitLST Laser Spot TrackerMCP Maximum Continuous Power MELPe Mixed Excitation Linear Predictive MEP Mission Equipment PackageMFD Multifunctional DisplayMHz MegahertzMIL-STD Military StandardMPSM Multi Purpose Sub-Munition MRE Meals ready-to-eat MTBEFF Mean Time Between Essential Function Failure MTBSA Mean Time Between System Aborts MTBR Mean-Time-Between-Removal MTBRRDR Mean-Time-Between-Removal-Requiring-Depot Return NACSEM National Communications Security Engineering Memorandum NATO North Atlantic Treaty OrganizationNCOW-RM Net Centric Operations and Warfare-Reference ModelNDI Nondevelopmental ItemNDL Network Data LinkNEFF Non-Essential Function Failures NFOV Narrow Field of ViewNGA National Geospatial - Intelligence AgencyNIAP National Information Assurance PartnershipNITFS National Imagery Transmission Format StandardNSA National Security Agencynm Nautical MilesNOE Nap of the EarthNSN National Stock NumberNTC National Training CenterNVIS Night Vision Imaging System(O) ObjectiveOEI One Engine Inoperative

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OMS Operator, Maintainer, and Support OMS / MP Operational Mode Summary / Mission Profile OPTEMPO Operational Tempo ORD Operational Requirements DocumentOTS Off The ShelfPCMCIA Personal Computer Memory Card International Association PIM Pulse Interval ModulationPRF Pulse Repetition FrequencyPVI Pilot Vehicle Interface RORO Roll-on / Roll-offRP Recommended PracticesSA Supportability AnalysisSAQ Statement of Airworthiness Qualification SAT System Approach to TrainingSATCOM Satellite CommunicationsSAWE Society of Allied Weight Engineers SINCGARS Single-Channel Ground Borne Radio SystemSRW Solider Radio WaveformSTAMIS Standard Army Information Management System(T) ThresholdTACAN Tactical Air NavigationTAD Target Audience Description TADIL-J Tactical Digital Information Link-JointTASS Target Acquisition Sensor SuiteTB Technical BulletinTCDL Tactical Common Data LinkTRADOC Training and Doctrine CommandTSR Time Slot Reallocation TV-1 Technical View-1 UAV Unmanned Air VehicleUMARK Unit Maintenance Aerial Recovery KitUS United StatesVbe Best Endurance Airspeed Vbr Best Range Airspeed VFR Visual Flight Rules VHF-AM Very High Frequency - Amplitude ModulationVHF-FM Very High Frequency - Frequency ModulationVMF Variable Message FormatVOR VHF Omni-directional Range VSI Vertical Speed Indicator

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WFOV Wide Field of ViewWNW Wideband Networking Waveform

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