Hawker 125 (Series 1 through 900XP)

Aileron Trim Position Indicator

1. 
   Aileron trim system is visually verified operative, and
   
2. 
   Aileron trim is visually verified to be neutral.
   

1. 
   Operate aileron trim while observing LH aileron trim tab for appropriate movement prior to each departure.
   

2. 
   With controls in neutral position, confirm the aileron trim tab is centered.
   

Rudder trim Position Indicator

1. 
   Rudder trim system is visually verified operative, and
   
2. 
   Rudder trim is visually verified to be neutral.
   

1. 
   Operate rudder trim while observing rudder trim tab for appropriate movement prior to each departure.
   
2. 
   With controls in neutral position, the rudder trim tab is centered.
   

Check requires coordinated effort of both crew to perform.

Rudder Pedal Adjustment Systems

1. 
   Remove the crew seat and flight compartment carpets from affected side.
   

2. 
   Remove flight compartment floor panels as necessary.
   
3. 
   Disconnect the rudder pedal assembly adjustment cable at the lever.
   
4. 
   Pull up on cable to disengage locking pin and move rudder pedals to desired position.
   
5. 
   Check that the pin is fully engaged in locked position and that spring force will maintain lock.
   
6. 
   Disconnect adjustment cable from rudder pedal adjustment assembly.
   
7. 
   Install flight compartment floor panels using correct screw length.
   
8. 
   Install flight compartment carpets and the crew seat.
   

Electrical Elevator Trim

1. 
   Associated circuit breakers are pulled and collared,
   
2. 
   Mechanical Elevator Trim System is verified operative,
   
3. 
   Autopilot is considered inoperative, and
   
4. 
   For 750, 800XP, 850XP, and 900XP aircraft, the mach trim system is considered inoperative and appropriate AFM speed limitations observed.
   

RVSM is not authorized.

1. 
   Locate ELEC PITCH TRIM Circuit Breaker.
   
2. 
   Pull and Collar ELEC PITCH TRIM circuit breaker.
   

1. 
   Operate mechanical elevator trim throughout full range before departure, and
   
2. 
   Verify that trim is set in normal position prior to takeoff, and
   
3. 
   Plan for flight without autopilot, and
   
4. 
   Do not exceed AFM speed limitation of Mach 0.73 (750, 800XP, 850XP and 900XP Only)
   
5. 
   Plan flight to avoid RVSM operation.
   

Stall Warning Identification System

1. 
   Remaining stall detector pneumatic system is verified operative, and
   

2. 
   Remaining stall test channel is verified operative.
   

1. 
   Inoperative channel is inhibited by pulling and collaring the associated STALL IDENT circuit breaker (SSU and STALL IDENT amber annunciators illuminated if IDENT 1 or 2 is inhibited),
   
2. 
   Before each departure, normal operation of the remaining channels is verified by independently pressing the cockpit TEST buttons,
   
3. 
   Before each departure, normal operation of the stick pusher is verified (stall valves A and B OPEN with red annunciators illuminated) by pressing the two operative TEST buttons simultaneously, and
   
4. 
   Lights erroneously ON due to system failure are deactivated.
   

1. 
   Pull and collar associated STALL IDENT circuit breaker.
   

2. 
   Remove light bulb from any annunciator which is erroneously illuminated.
   

1. 
   Prior to each departure, confirm both remaining stall channels operate normally by independently pressing associated TEST buttons, and
   

2. 
   Confirm normal operation of pusher by pressing both operational TEST buttons.
   

Stick Shaker Motors (Series 750, 800, 800XP, 850XP and 900XP Only)

1. 
   Both stall warning channels are operative, and
   
2. 
   Remaining stick shaker system is verified operative.
   

Stall Warning Autopilot Disconnect System (Series 800 without Mod. 253146 Installed Only)

1. 
   Prior to each departure, perform the following checks:
   
2. 
   Engage Autopilot and hold light force on control yoke.
   
3. 
   Push and hold No. 1 STALL button
   

1. 
   Confirm that stick shaker motors are operative and autopilot disengages.
   
2. 
   Confirm IDENT 1 (both sides) and STALL IDENT annunciators illuminate after 4 or 5 seconds.
   

4. 
   Release No. 1 STALL button.
   
5. 
   Engage autopilot and hold light force on control yoke.
   
6. 
   Push and hold No. 2 STALL button.
   

3. 
   Confirm that stick shaker motors operate and autopilot disengages.
   
4. 
   Confirm IDENT 2 (both sides) and STALL IDENT annunciators illuminate after 4 or 5 seconds.
   

7. 
   Release No. 2 STALL button.
   

Mach Trim System (Series 750, 800XP, 850XP and 900XP Only)

1. 
   Mechanical Elevator Trim System is verified operative before each departure, and
   
2. 
   AFM Speed Limitation of 0.73 Indicated Mach Number (IMN) is not exceeded unless Auto Pilot verified operative and is used.
   

1. 
   Operate mechanical elevator trim throughout full range before departure, and
   
2. 
   Confirm that trim is set in normal position prior to takeoff, and
   
3. 
   Do not exceed AFM speed limitations with autopilot disengaged.
   

Flap Position Indicator (On Center Instrument Panel)

1. 
   Flap position is visually verified to be at 0° before each departure,
   
2. 
   AFM procedures for flap 0° take-off and landing are observed, and
   
3. 
   Flaps remain in the retracted position for the entire flight.
   

1. 
   Visually confirm that flaps are at 0° prior to each departure by checking the position of the rig marks on the wing and flap assembly.
   
2. 
   0° flap performance will be used for takeoff and landing.
   
3. 
   Flaps will not be used in flight.
   
4. 
   AFM FLAPLESS LANDING procedures will be followed.
   

Flap Handle Select Position Indicator (On Control Pedestal)

1. 
   Flap position Indicator (On Center Instrument Panel) is operative, and
   
2. 
   Before each departure, flap position indication is visually verified for each flap selection.
   

1. 
   Flap position is visually verified to be 0° before each departure,
   
2. 
   AFM procedures for flap 0° take-off and landing are observed, and
   
3. 
   Flaps remain in the retracted position for the entire flight.
   

1. 
   Visually confirm that flaps are at 0° prior to each departure by visual use of marks on flaps.
   
2. 
   0° flap performance will be used for takeoff and landing.
   
3. 
   Flaps will not be used in flight.
   
4. 
   AFM FLAPLESS LANDING procedures will be followed.
   

Flap Position Switches

1. 
   LH and RH Flap Bias Switches are bypassed to position flaps in 0° position,
   
2. 
   Flaps are verified to be in the 0° position and are not used.
   
3. 
   AFM procedures for flap 0° take-off and landing are observed, and
   
4. 
   Repairs are made within one flight day.
   

1. 
   Confirm LH and RH Flap Bias Switches are bypassed to position flaps in 0° position.
   
2. 
   Visually confirm that flaps are at 0° prior to each departure by visual use of marks on flaps.
   
3. 
   0° flap performance will be used for takeoff and landing.
   
4. 
   Flaps will not be used in flight.
   
5. 
   AFM FLAPLESS LANDING procedures will be followed.
   

Air Brake Position Indicator(s)

1. 
   Airbrakes are visually verified operative,
   
2. 
   Takeoff Warning System is verified operative with Air Brake deployment, and
   
3. 
   Airbrakes are visually verified retracted.
   

1. 
   Extend and retract airbrakes and visually confirm normal operation.
   
2. 
   Confirm Takeoff Warning system is operative by advancing the throttles to 40% to 60% and pull back on the airbrake handle to slightly deploy the airbrake. The warning horn should sound.
   
3. 
   Airbrakes are visually confirmed retracted prior to departure by observation through cabin windows. Trailing edge of Air Brakes should fair smoothly with wing.
   

Control Column Lock System

1. 
   Procedures are established and used to prevent damage from gusts while aircraft is on the ground, and
   
2. 
   Throttle Lever Baulks are verified disengaged prior to each departure.
   

1. 
   A suitable alternate means is provided to secure controls to prevent ground gust induced damage to control system when aircraft is parked.
   
   
   

Note

Assure that any alternate means employed are prominent in display, so they will not be inadvertently left in place when the aircraft is dispatched. Such means shall be effectively secured to prevent slippage under gust load conditions.

2. 
   Advance each throttle lever through full range of movement noting travel limits.
   
3. 
   Confirm throttle lever baulks are disengaged by advancing both throttle levers simultaneously through full range of movement without travel restriction.
   

Rudder Gust Lock Flapper Door