Airframe Description and Limitations - PowerPoint PPT Presentation


Title: Airframe Description and Limitations


1
AirframeDescription and Limitations
  • Cirrus SR22

2
Dimensions
SR22 G1/G2
SR22 G3
3
Fuselage
  • Composite Materials
  • Composite roll cage integrated within fuselage
    structure
  • Floors constructed of foam core composite to
    increase structural integrity of structure
  • Connected to wing spar through four wing attach
    points
  • Two points under front seats
  • Two points aft of rear seats

4
Cabin
  • Accommodates four adults
  • Front seats
  • Adjustable fore and aft
  • Recline or fold forward
  • 4-point seat belts
  • Airbags (late models)
  • Aluminum honeycomb core to absorb downward impact
    loads
  • Rear seats
  • Can be unlatched via pins in baggage compartment
    to accommodate larger baggage loads

5
Cabin
  • Cabin Doors
  • Secured by two latching pins located on the upper
    and lower portions of the door
  • Gas charged struts provide assisted door
    operation
  • Windshield and Windows
  • Manufactured of acrylic
  • Refer to POH section 8 for cleaning instructions
  • Baggage Compartment
  • Door located on left side of fuselage
  • Accessed via cabin door key
  • Tie-down straps and hooks available

6
Safety Equipment
  • Emergency Egress Hammer
  • Used to fracture acrylic windows to provide an
    escape path if upside down or if doors will not
    open
  • Fire Extinguisher
  • Halon 1211/1301 extinguishing agent
  • Class B (liquid, grease) and Class C (electrical)
    approved
  • 20 year useful life

7
Wings
  • Conventional rib and spar construction
  • Main wing spar is a continuous span from tip to
    tip
  • G1/G2 Fiberglass
  • G3 Carbon Fiber
  • Composite construction produces smooth and
    seamless surfaces
  • Wing cross section is a blend of multiple high
    performance airfoils

8
Vortex Generator
  • Vortex Generators
  • Disrupt airflow over the inboard portion of each
    wing at high angles of attack
  • Helps the inboard portion of the wing to stall
    prior to the outboard portion

9
Empennage
  • Horizontal and vertical stabilizers are single
    composite structures
  • Vertical Stabilizer structure is integrated into
    the main fuselage shell for smooth transfer of
    flight loads
  • Control surfaces are constructed from aluminum
  • Two-piece elevator
  • Rudder

10
Flight Control
  • Controls actuated through use of side control
    yokes and conventional rudder pedals
  • System uses a combination of push rods, cables
    and bell cranks for control actuation

11
Elevator System
  • Two piece control surface
  • Constructed of aluminum
  • Single cable runs under cabin floor to elevator

12
Aileron System
  • Constructed of aluminum
  • Single cable system runs under cabin floor and
    aft of the rear wing spar

13
Rudder System
  • Constructed of aluminum
  • Single cable runs under cabin floor to fuselage
    tailcone
  • Rudder-aileron interconnect
  • G1/G2 aircraft only
  • Provides maximum of 5 down aileron with full
    rudder deflection
  • Aileron control movement does not cause rudder
    movement
  • Ailerons bank in direction of rudder movement
  • Helps with low speed control
  • Not needed with G3 wing due to increase in wing
    dihedral

14
Wing Flaps
  • Single-slotted, aluminum
  • Electronically controlled
  • Actuator mechanically connected to both flaps by
    a torque tube
  • Proximity switches limit flap travel and provide
    position indication
  • Three settings indicated by illumination of LEDs
    adjacent to control
  • Flaps Up (0)
  • Flaps 50 (16)
  • Flaps 100 (32)

15
Trim System
  • Electronically actuated via conical trim button
    mounted on each side yoke
  • Neutral positions (pitch roll) indicated by
    markings on control yoke
  • Trim is set by adjusting the neutral position of
    the spring cartridge of the appropriate flight
    control (elevator or aileron)
  • Provides a secondary method of control actuation
    in the event of a linkage failure
  • It is possible to easily override full trim or
    autopilot inputs by using normal control inputs
  • Red A/P DISC button will interrupt trim in the
    event of a runaway trim incident

16
Main Gear
  • Constructed of composite material
  • Wheel pants are bolted to the struts and easily
    removable
  • Main gear tire
  • 15 x 6.00 x 6
  • Inner tube type

17
Nose Gear
  • Constructed of tubular steel
  • Attached to the engine mount
  • Free castering
  • 216 of travel (108 either side of center)
  • Aircraft is controlled directionally through
    differential braking
  • Nose wheel tire
  • 5.00 x 5
  • Inner tube type

18
Brake System
  • Hydraulically actuated, single-disc type brakes
  • Brakes are actuated through toe brakes on each
    rudder pedal
  • Parking Brake control closes valve holding
    hydraulic pressure against calipers
  • Do not activate the Parking Brake in flight
  • Temperature sensors are mounted on each brake
    assembly
  • Cirrus Perspective aircraft also display brake
    temperature warning annunciators on the PFD

19
Taxiing and Braking Techniques
  • Cirrus aircraft use a castering nose wheel
  • Directional control is accomplished with rudder
    deflection and intermittent braking (toe taps) as
    necessary
  • Normal braking during landing will not damage
    brakes
  • If aggressive braking is required, allow brakes
    to cool down prior to setting parking brake or
    performing more aggressive braking procedures
  • Use only as much power as is necessary to achieve
    forward movement
  • Reduce power to slow down and then apply brakes
    as necessary
  • Most common cause of brake damage and/or failure
    is due to improper braking practices
  • Riding the brakes while taxiing causes a
    continuous buildup of heat energy and increases
    the chance of brake failure or fire

20
Takeoff and Landing Techniques
  • Takeoff
  • At low airspeeds and power settings differential
    braking is required for directional control
  • At higher airspeeds and power settings rudder
    control is sufficient to provide directional
    control on the takeoff roll
  • Landing
  • Upon touchdown the rudder is initially used to
    maintain directional control
  • Once the aircraft stabilized on the runway apply
    even pressure to both brakes for directional
    control and brake as necessary
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Title:

Airframe Description and Limitations

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... elevator Rudder Flight Control Controls actuated through use of side control yokes and conventional rudder pedals System ... aircraft only Provides ... Egress ... – PowerPoint PPT presentation

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Transcript and Presenter's Notes

Title: Airframe Description and Limitations


1
AirframeDescription and Limitations
  • Cirrus SR22

2
Dimensions
SR22 G1/G2
SR22 G3
3
Fuselage
  • Composite Materials
  • Composite roll cage integrated within fuselage
    structure
  • Floors constructed of foam core composite to
    increase structural integrity of structure
  • Connected to wing spar through four wing attach
    points
  • Two points under front seats
  • Two points aft of rear seats

4
Cabin
  • Accommodates four adults
  • Front seats
  • Adjustable fore and aft
  • Recline or fold forward
  • 4-point seat belts
  • Airbags (late models)
  • Aluminum honeycomb core to absorb downward impact
    loads
  • Rear seats
  • Can be unlatched via pins in baggage compartment
    to accommodate larger baggage loads

5
Cabin
  • Cabin Doors
  • Secured by two latching pins located on the upper
    and lower portions of the door
  • Gas charged struts provide assisted door
    operation
  • Windshield and Windows
  • Manufactured of acrylic
  • Refer to POH section 8 for cleaning instructions
  • Baggage Compartment
  • Door located on left side of fuselage
  • Accessed via cabin door key
  • Tie-down straps and hooks available

6
Safety Equipment
  • Emergency Egress Hammer
  • Used to fracture acrylic windows to provide an
    escape path if upside down or if doors will not
    open
  • Fire Extinguisher
  • Halon 1211/1301 extinguishing agent
  • Class B (liquid, grease) and Class C (electrical)
    approved
  • 20 year useful life

7
Wings
  • Conventional rib and spar construction
  • Main wing spar is a continuous span from tip to
    tip
  • G1/G2 Fiberglass
  • G3 Carbon Fiber
  • Composite construction produces smooth and
    seamless surfaces
  • Wing cross section is a blend of multiple high
    performance airfoils

8
Vortex Generator
  • Vortex Generators
  • Disrupt airflow over the inboard portion of each
    wing at high angles of attack
  • Helps the inboard portion of the wing to stall
    prior to the outboard portion

9
Empennage
  • Horizontal and vertical stabilizers are single
    composite structures
  • Vertical Stabilizer structure is integrated into
    the main fuselage shell for smooth transfer of
    flight loads
  • Control surfaces are constructed from aluminum
  • Two-piece elevator
  • Rudder

10
Flight Control
  • Controls actuated through use of side control
    yokes and conventional rudder pedals
  • System uses a combination of push rods, cables
    and bell cranks for control actuation

11
Elevator System
  • Two piece control surface
  • Constructed of aluminum
  • Single cable runs under cabin floor to elevator

12
Aileron System
  • Constructed of aluminum
  • Single cable system runs under cabin floor and
    aft of the rear wing spar

13
Rudder System
  • Constructed of aluminum
  • Single cable runs under cabin floor to fuselage
    tailcone
  • Rudder-aileron interconnect
  • G1/G2 aircraft only
  • Provides maximum of 5 down aileron with full
    rudder deflection
  • Aileron control movement does not cause rudder
    movement
  • Ailerons bank in direction of rudder movement
  • Helps with low speed control
  • Not needed with G3 wing due to increase in wing
    dihedral

14
Wing Flaps
  • Single-slotted, aluminum
  • Electronically controlled
  • Actuator mechanically connected to both flaps by
    a torque tube
  • Proximity switches limit flap travel and provide
    position indication
  • Three settings indicated by illumination of LEDs
    adjacent to control
  • Flaps Up (0)
  • Flaps 50 (16)
  • Flaps 100 (32)

15
Trim System
  • Electronically actuated via conical trim button
    mounted on each side yoke
  • Neutral positions (pitch roll) indicated by
    markings on control yoke
  • Trim is set by adjusting the neutral position of
    the spring cartridge of the appropriate flight
    control (elevator or aileron)
  • Provides a secondary method of control actuation
    in the event of a linkage failure
  • It is possible to easily override full trim or
    autopilot inputs by using normal control inputs
  • Red A/P DISC button will interrupt trim in the
    event of a runaway trim incident

16
Main Gear
  • Constructed of composite material
  • Wheel pants are bolted to the struts and easily
    removable
  • Main gear tire
  • 15 x 6.00 x 6
  • Inner tube type

17
Nose Gear
  • Constructed of tubular steel
  • Attached to the engine mount
  • Free castering
  • 216 of travel (108 either side of center)
  • Aircraft is controlled directionally through
    differential braking
  • Nose wheel tire
  • 5.00 x 5
  • Inner tube type

18
Brake System
  • Hydraulically actuated, single-disc type brakes
  • Brakes are actuated through toe brakes on each
    rudder pedal
  • Parking Brake control closes valve holding
    hydraulic pressure against calipers
  • Do not activate the Parking Brake in flight
  • Temperature sensors are mounted on each brake
    assembly
  • Cirrus Perspective aircraft also display brake
    temperature warning annunciators on the PFD

19
Taxiing and Braking Techniques
  • Cirrus aircraft use a castering nose wheel
  • Directional control is accomplished with rudder
    deflection and intermittent braking (toe taps) as
    necessary
  • Normal braking during landing will not damage
    brakes
  • If aggressive braking is required, allow brakes
    to cool down prior to setting parking brake or
    performing more aggressive braking procedures
  • Use only as much power as is necessary to achieve
    forward movement
  • Reduce power to slow down and then apply brakes
    as necessary
  • Most common cause of brake damage and/or failure
    is due to improper braking practices
  • Riding the brakes while taxiing causes a
    continuous buildup of heat energy and increases
    the chance of brake failure or fire

20
Takeoff and Landing Techniques
  • Takeoff
  • At low airspeeds and power settings differential
    braking is required for directional control
  • At higher airspeeds and power settings rudder
    control is sufficient to provide directional
    control on the takeoff roll
  • Landing
  • Upon touchdown the rudder is initially used to
    maintain directional control
  • Once the aircraft stabilized on the runway apply
    even pressure to both brakes for directional
    control and brake as necessary
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