SNC SIERRA FORCE UH-60A / A+ and UH-60L to L+ (Glass ...

Sierra Nevada Corporation Proprietary | © 2018 Sierra Nevada Corporation

PROPRIETARY: Sierra Nevada Corporation’s confidential and proprietary information may not be distributed or further disseminated without the express written permission of Sierra Nevada Corporation. Neither receipt nor possession of this data from any source constitutes such permission.WARNING: This document contains technical data that is subject to the International Traffic in Arms Regulations (ITAR) or the Export Administration Regulations (EAR). Export of this technical data to foreign persons or foreign entities inside or outside the United States requires prior written authorization by the U.S. Department of State or the U.S. Department of Commerce. Violations of these export regulations are subject to severe civil and criminal penalties.

2018

SNC SIERRA FORCE UH-60A / A+ and UH-60L to L+ (Glass Cockpit and Auto Pilot)

2Sierra Nevada Corporation Proprietary—Use or disclosure of data contained

on this sheet is subject to the restrictions on the title page.© 2018 Sierra Nevada Corporation

Purpose

Provide an overview of the Sierra Force L to L+ Cockpit and autopilot modifications

3SPACE SYSTEMSSierra Nevada Corporation Proprietary—Use or disclosure of data contained


Upgrade to Assist Pilot Workload



Technical Offer Approach for A to L+

UH-60A to UH-60L L+ STC Applied

Sierra ForceDelivered

ARC-210 X 3CMWS

AN/APX-119 IFF TACAN

SAASM

ArmorIntercom

MEP Examples

Test ProgramGenesys CockpitCargo Sling

IR SuppressionSeal-Sealing Tanks

Wire Strike ProtectionGun Mounts

ASE Structural ProvisionsSearchlight EO/IR

Hoist

Rotorcraft Design – Integration - Test

CCAD

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The proposed system provides the UH-60L+ aircraft with an avionics solution that is:

• Affordable to acquire and maintain

• Robust and proven in demanding environments around the world

• Low workload for the pilot with an excellent Human Machine Interface (HMI)

•Flexible for interfacing with legacy and mission equipment

• Highly capable with state-of-the-art functionality• Highly integrated for a low number of LRUs providing lower weight, reduced failures rates, and improved aircraft dispatch rate• Compliant FAA NexGen Area Navigation (RNAV), Required Navigation Performance (RNP) standards, and LPV approaches

• Night Vision compatible

•FAA-certified and in production

• Ideally suited for the special-mission environment

• Open architecture to facilitate growth

EXECUTIVE SUMMARY



An avionics modernization program to provide state-of-the-art digital avionics for primary flight, navigation, and engine/systems displays, solid-state sensors, and area navigation capability meeting FAA NextGen requirements.

• Large-format 6” x 8” (viewable area) portrait EFIS/MFD displays

• PFD/MFD pair for both pilot and copilot (4 or 5 displays)

• Each display includes built-in FMS (no separate LRUs)

• Each display includes built-in HTAWS (no separate LRU)

• Each display includes built-in digital flight recorder• Each display includes 1 EICAS page.

• Up to four additional EICAS pages can be added in accordance with customer requirements.

• 2x GPS/SBAS receivers with antennas

• 2x ADAHRS provide attitude source to cockpit system and AFCS

• 2x dual-channel Data Acquisition Units (DAU)

• 3x serial analog/digital converters (SAND) for airframe discrete inputs/outputs• Radio tuning will be accomplished through the PFD/MFD display to minimize weight, complexity, cost and failure probability.

SYSTEM DESCRIPTION



UH-60A/A+ and UH-60L+ Blackhawk Digital Cockpit

and Autopilot Solution



Autopilot

Delivers safety and workload reduction benefits withfully coupled autopilot and stability augmentation in a compact, lightweight package:• Weight – Approximately 25 pounds (this is based on the redundancy of the servos required, anticipate this weight to reduce) • Dramatically reduced pilot workload• Safer, more confident command...even under demanding conditions• Autopilot fully-coupled to FMS and navigation radios• Auto-recover to a neutral attitude in situations where pilot may lose visual reference• Pilots with no helicopter experience have successfully hovered a HeliSAS-equipped helicopter with very little practice

Currently provided with 3 axis (Heading, Pitch/Roll, and Yaw via AFCS) with 4th axis (collective) in design & test.

Autopilot Upgrade - HeliSAS®



SNC Glass Cockpit Modification

Completed Glass Cockpit ModificationAnalog Cockpit



Sierra Force Glass Cockpit w/ Avalex 15” center display in working Aircraft

SNC works with the end user specific configuration in order to integrate specific Radios and customer specific equipment.

Specific Aircraft Radios and Avionics



Sierra FORCE (GENESYS Cockpit w/ Avalex Center Display)

Certification Basis STC for Avionics, including A-Kit for SNC equipment STC for Sensor Provisions STC for GENESYS Autopilot



SIERRA FORCE Nose Modification

During ModificationNose Before

Modification Complete

Legacy Systems Removed:FOGS (Fiber Optic Gyro)RATE GYROs (TRU-2A/A)SDC (Signal Data Converters)GPS (Global Positioning System)CIS (Command Instrument System)



Sierra FORCE Upper Deck Modification

Completed Upper Deck Upper Deck Before



• Standard integration schedule for the first Genesys Cockpit and Autopilot is estimated at 8 weeks (plus 30 days for flight test / hangar ops)

• Integration of customer specific hardware may add additional schedule depending on system / hardware.

• Multiple aircraft can be done in parallel during production

Integration of Customer Standard Radios and Equipment



• l

COMPONENT DETAILED DESCRIPTION

Glass Cockpit UpgradeLightest, most comprehensive, integrated Electronic Flight Instrument System enhances safety, reduces pilot workload, and increases mission flexibility:• Redundant ADAHRS attitude source (replaces legacy attitude sensors)• Redundant GPS/SBAS receivers• Dual NAV/COM radios• Built-in, integrated radio/audio management• Mode-S ADS-B compliant transponder• Weather Radar control and display• Built-in support/interfaces for FLIR, Satcom, DF, HF/UHF, TACAN, Datalink, SELCAL,



Primary Flight DisplayThe primary flight display functional area of the IDU-680 can be configured by the pilot in a variety offormats from basic ADI to full synthetic vision, emulating HUD symbology.•Airspeed and altitude•Attitude•Heading•Ground track•Desired track•Single- and dual-cue flight director•CDI (RNP 0.3/BRNAV/PRNAV)•Localizer•Glideslope/VNAV•Speed trend•Digital or analog absolute altitude (radio, GPS, or baro)•Selected speed/VSI/altitude/heading bugs•Poll pointer or sky pointer•V-speeds•Selected engine parameters (Nr, etc.)•Autopilot Mode: Source indication•QNH/QFE/QNE•Baro setting in inches of mercury or millibars/hectoPascals•VSITRAS (TCAS-II)•Ground track and desired track•Waypoint information•RNP value and mode (auto or manual)•ANP value

FUNCTIONS



Synthetic Vision –Pilot SelectableThe synthetic vision PFD includes all EADIelements (except dual-cue flight director) plusforward-looking, real-time display of the worldahead of the aircraft, including:

•Terrain (worldwide)•Towers/antennas/obstructions (worldwideplus user-added)•Navigation aids•Perspective runway•Flight path marker (velocity vector)HSI•MiniMap•Traffic thumbnail•Highway-in-the-sky, and traffic•Cautions/warning/advisories•Relative altitude coronation SV with shading(selectable)Note: PFD terrain coloration matches movingmap terrain coloration.

FUNCTIONS (CONT.)



Datalink WeatherIf equipped with a datalink weather receiver, pilot selectabledisplay options include:• NEXRAD• Graphical METAR• Textual TAF• Lightning• Winds/temperature aloft• Echo tops• Convective SIGMETS• AIRMET Icing• AIRMET Turbulence• ARIMET IFR

FUNCTIONS (CONT.)



EHSIThe electronic horizontal situation indicator• Conventional HSI• Dual RMI• Desired track and ground track• Dual DME/TACAN• Dual ADF• Glideslope/VNAV indicator• Winds aloft• Cross-wind component• Density altitude• Outside air temperature• ISA temperature• True airspeed• Groundspeed• Zulu time• Count-up/count-down/flight timers• OBS mode• CDI scale• Fuel totalizer (if equipped)• Cautions/warnings/advisories• Helicopter, small airplane, or jet ownship position symbol• Waypoint type, bearing, distance, and ETA or ETE for active and

destination waypoints

FUNCTIONS (CONT.)



Moving MapThe real-time moving map (10Hz. update rate) includes all EHSI elements exceptglideslope and HSI, plus:•Worldwide 6 arc-second terrain with relative elevation coloring and shaded relief•Threatening terrain differentiation (only terrain generating a TAWS alert is colored redor yellow, thus allowing terrain and weather display on the same screen)•Projected path•Dead-stick glide area (fixed-wing only)•Hydrography•Altitude-coded special-use airspace•Towers and obstructions•Traffic•Political borders•Synthetic vision field-of-view indicator•Weather (datalink or radar)•Low-level (Victor) and high-level (Jet) airways•Navigation aids•Runways•Curvilinear routing supports all ARINC-424 leg type(FMS flight plan)•Top of descent•Lubber line•LAT/LON•Pan and zoom function

FUNCTIONS (CONT.)



Traffic Display

Traffic display function supports any ARINC-735A-compliant traffic detection system,including TAS, TIS-B, TCAS-I, TCAS-II, and ADS-B.

FUNCTIONS (CONT.)



Integrated Terrain Awareness and Warning System (HTAWS)Each display in a system provides TAWS functionality (no separate LRU):Terrain DisplayDisplay of terrain and obstacles on the PFD (synthetic vision) and moving map. A pop-up feature automaticallychanges the MFD to the moving map and sets the scale to highlight the threatening terrain.

Forward Looking Terrain Awareness (“FLTA”)A warning function that uses a terrain database and an obstruction database to alert the pilot to hazardous terrain orobstructions in front of the aircraft.

FUNCTIONS (CONT.)



Each display in a system contains a stand-alone integratedFMS that supports all ARINC-424 leg types. FMS functionsinclude:•Create and Store 100 Flight Plans•Activate a Stored Flight Plan•Edit a Stored Flight Plan•Reverse a Stored Flight Plan•Delete a Stored Flight Plan•Nearest Airport, VOR, NDB, ILS, intersection, userwaypoint, ARTCC, FSS•Direct to Any Waypoint•Re-center on Route•Flight Planning Using Airways (Vector and Jet Routes)•Published and Non-Published Holding Patterns•VNAV and Waypoint Offset•Activate a Waypoint within an Active Route•Add a Waypoint or Airway to an Active Route•Delete a Waypoint from an Active Route•Create a User Waypoint with lat/lon, rad/dist, and mark-on-target (overfly or pan map)•Create User-Defined Precision Approach to User Waypoint•Edit a User Waypoint

INTEGRATED FLIGHT MANAGEMENT SYSTEM

• Get Waypoint Information(Jeppesen NavData – runwayinfo, frequencies, etc.)

• Send Nav and ComFrequencies to Radios

• Select a VFR Approach• Select an IFR Approach• Select a DP or STAR• Missed Approach Arming

Procedure• Parallel Track Function• Area Navigation, RNP, and

LPV Procedures• Automatic OBS -- GPS• Manual OBS – GPS• HSI Source Selection• Search patterns

• USCG ParallelTrack/Creeping Line

• USCG ExpandingSquare

• USCG Sector• Orbit

• Race Track



• Each display provides all radio and audio control and distribution functions for up to 10ARINC-429 radios in almost any combination. All common control head functions areaccommodated.

• The Expand (EXPND) menu accesses an “options” page for each radio whereancillary functions (like entering Flight ID or specifying frequency spacing) aremanaged.

• Audio distribution and control and ICS functions are performed by a remote audiomanagement unit controlled by the Radio/Audio Management page

RADIO/AUDIO MANAGEMENT (RAM)



Engine indication and CAS messaging is developed in accordance withcustomer specifications and displayed on the IDU-680 with the followingtypical parameters:• Fuel quantity• Hydraulic oil temperature• Hydraulic system pressure• Transmission oil temperature and pressure• Gearbox oil temperature and pressure• Dual DC ammeter• Gas producer tachometer• ITT indicator• Engine oil temperature and pressure• Fuel pressure• Dual AC and DC voltmeter• Triple tachometer• Dual torque pressure• Chip detectors• Battery temperature• Others as required• Fuel quantity

ENGINE INDICATION AND CREW ALERTING SYSTEM (EICAS)



• Each display in a system incorporates an integratedauditory caution/warning/ advisory (CWA) systemthat monitors a wide variety of parameters andprovides auditory annunciations for conditions thatdemand pilot awareness or action. Auditoryannunciations take the form of either a voice warning,tone, or chime as appropriate. Annunciations aregrouped into three categories: warning, caution, andadvisory.

• Warnings are accompanied by a red flag and repeatuntil acknowledged by the pilot (by pushing the EFISMUTE button on yoke, cyclic/collective, or panel) orthe condition is corrected. Cautions areaccompanied by a yellow flag and are annunciatedonce. The flag is displayed until the condition iscorrected. Advisories are accompanied by a blue flagor no flag, depending on condition.

• Annunciation volume is based on level of threat andaudio is silenced immediately upon pressing theEFIS MUTE button. Overall volume can be adjustedduring installation. CWA Flags are stacked in thelower left corner of each display with warningsdisplayed on top, followed by cautions and thenadvisories.

• Conventional fixed-location CAS matrix:

CAUTION / WARNING / ADVISORY SYSTEM



Synthetic Vision / Moving Map Half-Screen Engine Display / Radio-Audio

Proprietary and ConfidentialThis document, and the information disclosed herein is proprietary and confidential information belonging to XP SERVICES, INC, Inc. and

shall not be duplicated, used or disclosed, nor shall the articles or subject matter contained herein be reproduced, without written permissionfrom XP SERVICES, INC. Final configuration may be subject to U.S. Government export approval.

Primary and Secondary Flight Displays



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SNC SIERRA FORCE UH-60A / A+ and UH-60L to L+ (Glass ...

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