Cirrus Sr-22 : Supplements

Front 1

Supplemental Flashcard Sections:

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GFC700 Automatic Flight Control, Cirrus Airframe Parachute, Oxygen, &Flight into Known Icing Conditions Systems

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GFC700 AFCS: GENERAL

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Three axis, dual channel, mode controlled Automatic Flight Control System (AFCS) composed of integrated Line Replacement Units (LRU’s). Communication between LRU’s provide situational awareness with critical aircraft information and reduce pilot loads with Auto Pilot/Flight Director activation

Front 3

GFC700 AFCS: FLIGHT DIRECTOR & AUTO PILOT DIFF

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• Flight Director –provides pitch and roll commands to the AFCS displayed on PFD. FD receives commands from IAU #1 with pitch/roll calculations, vertical control, and mode annunciations.
• Autopilot – controls the Flight Director to follow the operator commands for mode specific guidance.
* YD is third additional axis.

Front 4

GFC700 AFCS: LINE REPLACEMENT UNITS

Back 4

NEED DEF

Front 5

GFC700 AFCS: PFD & MFD LRU

Back 5

• PFD & MFD: LCD Screens with system integration to enable operator interpretation of critical flight & systems data. Redundancy provided by Fail safe reversionary mode.

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GFC700 AFCS: GIA LRU

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• GIA: Integrated Avionics unit acts as communication hub linking individual IAU’s with PFD. IAU’s contain: GPS/WAAS receivers, VHF COM/NAV/G.S. receivers, system intregation microprocessors, and Flight Director.

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GFC700 AFCS: AHRS LRU

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• AHRS: Attitude & Heading Reference System data provided to PFD and ADC. Contains sensors (accelerometer & rate) for attitude and Magetometer for HDG information. Also assists in updated GPS location data.

Front 8

GFC700 AFCS: ADC LRU

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• ADC: Air Data Computer processes information from Pitot Static and OAT systems. Provides: ALT, V/S., A/S, and OAT to GIA to display data on PFD. Critical flight data information is calculated in real-time to provide trends & adaptive operating ranges/approaching stall displays for safety.

Front 9

GFC700 AFCS: GEA LRU

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• GMA: Marker Beacon and Audio panel is integrated with GIA to support VHF external communication and receving/demodulating VOR/G.S./LOC signals.

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GFC700 AFCS: GMA LRU

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• GEA: Engine Airframe Unit receives/processes individual sensor information and displays in analog format.

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AFCS CONTROL MODES : HDG, NAV, APR, AP, LVL, & FD

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• HDG – heading commands for FD from pilot selection.
• NAV – activates enroute tracking & sensitivity, GPS approach guidance (MAP & GPS vert. guidance) and provides GPS coupling.
• APR – activates lateral approach mode sensitivity switches mode to capture precision approach guidance
• AP – Autopilot engagement/disengagement
• LVL – Engages AP, command level to capture 0 V/S
• FD – Command Bar activation

Front 12

AFCS LIMITATIONS

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• Speed: Min = 80 / Max =185
• Altitude: Min Engage = 400 / Min Enroute : 1000 (AGL) Presc Aprch = 200 or DA / Non Precs = 400 or MDA
• Attitude: Pitch = 30+/- Roll= 75+/- (AP) Pitch = 20+/15- Roll = 25+/- (FD)
• Other: YD not allowed on T/O or Landing

Front 13

ENGINE SYSTEMS INDICATIONS

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• RPM: 500-2700
• ALT: 2-100
• EGT: 500-1750
• CHT: 240-420
• MAP: 15- 29.5
• OIL PRESS: 30-60
• OIL TEMP: 100-240
• BATT/(BUS): 24.5 (-32 Max BUS)

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CREW ALERTING SYSTEM (CAS)

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Aural Callout/Chimes with additional visual Warning and Caution advisories appear on PFD in order depending on criticality from top to bottom.
• WHITE = Advisories/Alerts that require acknowledgment
• YELLOW = Immediate Awareness w/ future action required
• RED = Immediate Awareness/action required

Front 15

CAPS: Cirrus Airframe Parachute System

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Deployment of the aircraft parachute system, within design limitations, will greatly increases the percentage for crash impact survival. Engaging the system (through overhead T-handle) will activate rocket propelled attachment connected to parachute for inflation to begin within 2 seconds. Loads are supported by attachment of a 3-point harness imbedded within fuselage structure. Design intention is to save lives, not the airplane

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CAPS: LIMITATIONS

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• Speed: Max Deployment = 133 KIAS
• Altitude: Min Deployment = 400 AGL

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CAPS: CONSIDERATIONS

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• Considerations: Deployment = Min 2000 AGL Decision Alt for Terrain/Wind drift considerations. Deployment 1000 AGL (600 AGL Abs Min when terrain/obstacle avoidance necessary) Observed ALT loss w/ deployment in a developed spin = 920 FT. Crash impact positions and Door positions.

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CAPS : Deployment Scenarios

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• Mid-air Collision & Structural Failure: determination that airframe structure and/or control surface integrity safety compromised, deploy considered immediately.
• Terrain Unsuitable for power off landing: Deployment during IMC or inhospitable terrain will enable survivable crash impact forces in comparison to power off landing. Deployment over water should be avoided/minimized due to fact that gear will no longer assist in distribution of impact loads.
• Pilot Incapacitation: Passenger Briefing should include requirements information for deployment to get them to the ground in the event of operator incapacitation.

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Supplemental Oxygen Systems

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Aircraft equipped with integrated airframe Oxygen system or supplemental carry-on equipment required for Crew & Passengers. Supplumental equipment is beneficial for weight and balance considerations as it is only determined per individual trip specifications in accordance with FAR Part 91 criteria.

Front 20

Supplemental Oxygen Required Usage

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REQUIRED USAGE (91.211)
• <12,500-14,000* > 30 Min = Crew avail
• 14,000-15,000* = Crew Required
• > 15,000* = Avail to every occupant
*Unpressurized cabin altitude interpreted by MSL

Front 21

FLIGHT INTO KNOWN ICING CONDITIONS (FIKI) Protection System

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Continuation of Flight-Into-Known-Icing (FIKI) conditions, system and environmental operation limitations determine permissible continuation criteria established during the anti-icing certification approval process.

Front 22

FIKI: SYSTEM DESCRIPTION

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• System operation is used to remove and prevent formation of ice on critical aircraft load bearing and control surfaces, stall awareness systems, and provide adequate visibility.
• Accomplished through electrical heating and positive pressure porous panel weeping of TKS Anti-Ice fluid distribution. TKS fluid eliminates and prevents ice formation by lowering the respective surface temperature below that of the required precipitation freezing level.

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FIKI: SYSTEM OPERATION

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• Mode Operation: 5 switch bolster panel and 3 MFD soft-key allow system control of metering pumps activation and flow rate distribution in the following modes:
o NORM:Both pump operates in ¼ activation during 2 minute timer box controlled cycle. (30s On/90s OFF).
o PUMP BKUP:timing box by-passed for allowing for activation of 2nd metering pump, similar to ->
o HIGH: Both pumps operate continuously @ 100%. WndShld Pump activation, enables ops similar ->
o MAX: Both pumps operating continuously w/ max flow distribution provided via additional windshield/priming pump operations.

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FIKI: STORAGE

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• Storage: Two symmetrical, 4.25 capacity (4 usable), wet-sealed tank are integrated in the conventional wing design. Analog MFD displays QTY via float type sensors and Flow Rate calculations for visual remaining system limitations.

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FIKI: DISTRIBUTION

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• Initial Distribution flow: Pumps -> Filtration -> Dist. Units
o # of metering pumps ops determined by selected mode and establishes positive system pressure leading into the TKS fluid filtration. *Use WNDSHLD pump for system priming/purging O2 in system lines.
o Once filtered, distribution units will direct flow evenly to their selected surface areas/equipment.
 Empennage: HORZ/VERT STAB & ELEV Panels
 Floor FWD: IN/OUTBOARD Wing Panels and prop slinger rings.
 WNDSHLD: Individual distribution unit.
• Surface Distribution:
o Porous panels: perforated porous membrane outlets continually shrinking approaching the outer most surface. Even weeping distribution begins when surface resistance > membrane pressurization.
o Prop Slinger Rings: Centrifugal force distributes fluid onto rubber boots via individual outlets attached to spinner backing plate.

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FIKI: STALL AWARENESS

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Stall Warning System: Heated faceplate allows lift transducer sensing of increased slipstream pressures to connect the heated vane. Closing the electrical circuit to activate Aural and Visual CAS advisories with safety design for 5-10 Knt buffer for the approaching stall.

Front 27

FIKI: SYSTEM LIMITATIONS

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MIN Disptch: QTY = 5 Total with Mode
* at:
 NORM: 90 Min
 HIGH: 45 Min
 MAX: 22.5 Min
MAX Dispatch: QTY = 8 Useable with Mode
* at:
 NORM: 150 Min (Flow @ 3.2 GPH)
 HIGH: 75 Min (Flow @ 7.4 GPH)
 MAX: 37.5 Min (Flow @ 12.8 GPH)
*Endurance decrease with WND SHLD operations.
Speeds :
• Min = 90
• Maintain =95-177
• Max = 204
Approach
• Min = 95 with Vref Landing round out @ 88 KIAS
 Flap deployment limited to 50%
 No WNDSHLD Spray within 30 sec of landing
Weather:
• Flight into known icing conditions and/or encountering Freezing rain/drizzle or severe icing conditions are prohibited.
• Minimum System Operating Temp = -30C
*Immediately activate appropriate protection mode selection and exit icing conditions