Steve Blonstein CFI West Valley Flying Club March

Steve Blonstein, CFI West Valley Flying Club March 2004 The All-Glass Cockpit

Agenda §Current Systems §Thought Provoking Questions §Terminology §Systems Overview §Primary Flight Display §Multifunction Display §GNS 430 §STEC 55 x Autopilot §Discussion March 2004 The All-Glass Cockpit

CURRENT SYSTEMS Diamond DA 40 – Garmin G 1000 March 2004 The All-Glass Cockpit

CURRENT SYSTEMS Diamond DA 40 – Avidyne March 2004 The All-Glass Cockpit

CURRENT SYSTEMS Eclipse Personal Jet – Avio March 2004 The All-Glass Cockpit

CURRENT SYSTEMS Chelton Flight Systems - HITS March 2004 The All-Glass Cockpit

CURRENT SYSTEMS Cirrus SRV/SR 20/SR 22 - Avidyne March 2004 The All-Glass Cockpit

5 Thought Provoking Questions • Is an all-glass panel safer than a conventional panel ? • As a community, are we prepared for such rapid innovation ? • How much training is required to be competent and safe ? • What happens in the event the panels go dark? • How should one manage database currency ? We’ll come back to discuss these important questions later on March 2004 The All-Glass Cockpit

Terminology • TAA – Technically Advanced Aircraft (e. g. All Glass Cockpit, GPS, A/P) • PFD – Primary Flight Display (1 display with AS, Altimeter, VSI, HSI, TC) • MFD – Multi-Function Display (1 display with maps, engine, wx, traffic) • HITS – Highway In The Sky (like Chelton Flight Systems) • FITS – FAA Industry Training Standards (e. g. TAA with PFD/MFD/HITS) • ADAHRS or ADAHARS – Air Data Altitude Heading and Reference System • GPS – Global Positioning System • GPSS – GPS Steering March 2004 The All-Glass Cockpit

ADAHRS System Structure Air Data Heading Attitude GPS 1 MFD Crossfill PFD GPS 2 GPSS relay S-TEC 55 X March 2004 The All-Glass Cockpit T/C

Electrical Components • Alternator 1 – 75 amp, 28 volts – Belt driven – Internally rectified • Alternator 2 – 20 amp, 28. 75 volts – Gear driven – Internally rectified March 2004 The All-Glass Cockpit

Electrical Components • Battery 1 – 24 volt, 10 amp-hour – Lead Acid • Battery 2 – 2, 12 volt, 7 amp-hour connected in series – Lead Acid – Sealed in an acid resistant container – Located at FS 222 below parachute canister March 2004 The All-Glass Cockpit

Avidyne PFD • The Avidyne PFD incorporates the functionality of: – – – Airspeed Indicator Attitude Indicator Altimeter VSI HSI (HI & VOR/LOC) March 2004 The All-Glass Cockpit

Avidyne – PFD(2) • The display is integrated with an Air Data / Attitude Heading Reference System (ADAHRS) • Three axis solid state gyro system • Provides: – Pitch – Roll – Heading March 2004 The All-Glass Cockpit

Avidyne – PFD(3) • Turn Coordinator – Scale show extending from either side of digital heading representation – Graduations for half and full standard rate turn – Blue bar extends into scale as turn is entered March 2004 The All-Glass Cockpit

Avidyne – PFD(4) • Inclinometer – Represented as black trapezoid below angle of bank indicator March 2004 The All-Glass Cockpit

PFD - Initialization • Requires approximately 3 minutes to align • Countdown begins when unit is 40 seconds from completing the initialization process • Air data will become valid prior to attitude information • Red X’s indicate invalid data • Brightness Default: 75% March 2004 The All-Glass Cockpit

PFD - Initialization • Default configuration: – HDG Bug: 360° – Altitude Bug: Nearest hundred feet – VSI Bug: 0 – Baro Set: 29. 92 in. Hg – Nav: GPS 1 – Bearing: Off – Aux: Off – View: 360° March 2004 The All-Glass Cockpit

PFD – Failures (1) • Air Data Failure • Refer to standby instrumentation March 2004 The All-Glass Cockpit

PFD – Failures (2) • Recoverable Attitude Data Failure • Occurs when: – Attitude change exceeds 90° per second – Small power fluctuation • Gyros are reset by pressing “Fast Erect” line select key March 2004 The All-Glass Cockpit

PFD - Failures (3) • Non-recoverable Failure – Cannot be corrected in flight – Must refer to standby instruments March 2004 The All-Glass Cockpit

PFD – Failures (4) • Lamp or LCD failure – Keys are lit no display – Take system off line by use of CB, this will ensure that you have predictable autopilot operations. March 2004 The All-Glass Cockpit

PFD - Limitations • Avidyne PFD Pilot Guide must be immediately available in flight • PFD must be aligned with no flags for takeoff • All standby instruments must be working for takeoff • PFD may be inoperative for VFR operations March 2004 The All-Glass Cockpit

Avidyne MFD • The Avidyne MFD supports: – Map/Terrain/Nearest – Engine Management – Fuel Management • Lean Assist – Traffic – Stormscope March 2004 The All-Glass Cockpit

MFD - Nearest Page • Separate Avidyne database to support this March 2004 The All-Glass Cockpit

MFD – Engine Management • All important engine, fuel, and electrical information on a single page • Use in run-up • Use on takeoff March 2004 The All-Glass Cockpit

MFD – Lean Assist • Do not lean in climb • Lean at altitude using the lean assist function • After reaching Best Power try using “Normalize” March 2004 The All-Glass Cockpit

MFD - Limitations • • • The moving map display must not be used as the primary navigation instrument. Use of map page during IFR flight requires an IFR approved GPS receiver installation operated in accordance with applicable limitations. Under no circumstances should the Map page terrain representations be used as a basis for terrain avoidance. The electronic checklists are supplements to the POH checklists and is advisory only. These must not be used as the primary set of onboard airplane checklists. The Avidyne Flight. Max EX-Series Pilot’s Guide must be available to the pilot during flight operations. March 2004 The All-Glass Cockpit

GPS – GNS 430 • Acts as a communications and navigation management system • Integrates radio transceiver, navigation receiver, and GPS navigation capability into a single unit • WAAS upgrade ? March 2004 The All-Glass Cockpit

GNS 430 - Chapter & Page Selection March 2004 The All-Glass Cockpit

Autopilot – STEC 55 x • Rate autopilot • Two axis control system – Roll axis controlled by aileron trim motor and spring cartridge – Pitch axis controlled by pitch trim motor • Powered by Essential Bus March 2004 The All-Glass Cockpit

STEC 55 x - System March 2004 The All-Glass Cockpit

Approach Procedures • ILS Approach – – – Ensure a reliable Localizer signal exists Select the desired course using the CDI Select APR mode on the autopilot mode controller Verify illumination of NAV and APR annunciators Glide-slope Coupling • APR and ALT modes must be selected • Aircraft must be within ½ scale deflection of localizer • Aircraft must be 60% or more below the glide-slope * – Condition must exist for 10 seconds for GS mode to arm – Arm indicated by illumination of ALT and GS annunciators • ALT annunciator extinguishes at glide-slope intercept • GS mode may be manually engaged by pressing ALT once when in ALT mode and a glideslope signal exists * On or below glide-slope in later revisions of software. March 2004 The All-Glass Cockpit

Thought Provoking Questions • Is an all-glass panel safer than a conventional panel ? • As a community, are we prepared for such rapid innovation ? • How much training is required to be competent and safe ? • What happens in the event the panels go dark? • How should one manage database currency ? March 2004 The All-Glass Cockpit