Flight controls laboratory

Move the yokes, pedals, trim and flap handle to connect cockpit inputs with control-surface movement.

Piper PA-44 Seminole

PA-44 / Flight controls laboratory

Move a cockpit control. Follow the connection to the aircraft, then inspect what changed.

Educational illustration
Geometry and claims pending review

Static diagram available. Interactive 3D loads with JavaScript.

In the cockpit

Input → surface → explanation

PA-44-inspired illustration. Instrument screens and engine controls are static context. Drag either yoke or use the inputs below.

Cockpit inputs

Yoke roll0%Yoke pitch0%Rudder pedals0%Stabilator trim0%Rudder trim0%Flap handle

At the aircraft

Trailing-edge direction relative to neutral. Tab angles are relative to their parent surface.

Left Aileron: 0.0° · neutral
Right Aileron: 0.0° · neutral
Stabilator: 0.0° · neutral
Rudder: 0.0° · neutral
Stabilator Tab: 0.0° · neutral
Rudder Tab: 0.0° · neutral
Flaps: 0.0° · neutral

Center retains trim and flaps. Reset study restores everything.

Surface angles use unverified values from the supplied file. Tab coupling is qualitative. No aerodynamic response, airspeed, control force, or flight path is calculated.

Field notes

8 connections

Review draft · supplied aircraft-specific statements and illustrations need verification against the applicable aircraft and manual revision.

Control systems

Differential ailerons

The ailerons provide roll control through the dual control wheels and cable-operated system. Differential travel means the upward-moving aileron has greater angular travel than the downward-moving aileron. This can help reduce adverse yaw; the greater upward deflection is not intended to increase drag on the up-going wing. There is no cockpit aileron trim control.

Try & observe

Move Yoke roll in either direction. Compare the up-going surface with the down-going surface and their unequal angle readouts.

Supplied reference

Up travel: 23° ± 2°
Down travel: 17° ± 2°
Control: Yoke roll / mechanical cables, pulleys and bellcranks
Source as supplied: Maintenance manual Chapter 27, aileron rigging / Figure 27-10; user-supplied rigging diagram.
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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Maintenance manual Chapter 27, aileron rigging / Figure 27-10; user-supplied rigging diagram.

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Control systems

Rudder

The rudder controls yaw. The dual rudder pedals operate a cable-controlled rudder. The rudder includes a combined anti-servo and trim tab. Rudder pedals also participate in nosewheel steering on the ground, a separate mechanical steering function.

Try & observe

Move Rudder pedals left and right. Watch the rudder rotate about its vertical hinge.

Supplied reference

Rudder travel: 37° (+1° / −0°) each direction
Rudder tab travel: 26° ± 2°
Trim: Manual rudder trim control on center console
Source as supplied: Maintenance manual Figure 27-14; POH Section 7.15.
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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Maintenance manual Figure 27-14; POH Section 7.15.

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Control systems

All-moving stabilator

The horizontal tail is an all-moving stabilator, rather than a fixed stabilizer with a separate elevator. Moving the yoke fore and aft changes stabilator incidence. The trailing-edge anti-servo tab moves in the same direction as the stabilator, with greater travel, increasing control feel.

Try & observe

Pull the Yoke pitch slider toward positive values, then push toward negative values. The whole horizontal tail moves.

Supplied reference

Up travel: 15° ± 1°
Down travel: 3° ± 1°
Type: All-moving horizontal tail
Source as supplied: Maintenance manual Figure 27-19; POH Section 7.15 and Section 7.3.
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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Maintenance manual Figure 27-19; POH Section 7.15 and Section 7.3.

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Control systems

Stabilator trim tab (anti-servo tab)

The stabilator trailing-edge tab performs both anti-servo and longitudinal trim functions. Anti-servo movement is in the same direction as the stabilator and helps increase control forces. Trim action shifts the tab neutral position to reduce the force the pilot must hold. The POH identifies the trim control on the center console; equipment-specific electric trim availability must be checked for the aircraft.

Try & observe

Center the yoke, then change Stabilator trim. Compare the tab with the whole stabilator; their angles use different reference frames.

Supplied reference

Tab up travel: 4° ± 1°
Tab down travel: 9° ± 1°
Functions: Anti-servo and trim
Source as supplied: PA-44 maintenance manual, PDF page 311
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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PA-44 maintenance manual, PDF page 311

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Control systems

Rudder trim tab (anti-servo tab)

The rudder incorporates a combination trim and anti-servo tab. Manual rudder trim is controlled from the center console. Trim is used to relieve sustained rudder pressure; it does not substitute for required pedal input.

Try & observe

Center the pedals, then change Rudder trim. The illustrative tab moves relative to the rudder.

Supplied reference

Rudder tab travel: 26° ± 2°
Control: Manual center-console trim
Source as supplied: PA-44 maintenance manual, PDF page 301
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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PA-44 maintenance manual, PDF page 301

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Control systems

Single-slotted flaps

The Seminole uses mechanically operated flaps with a four-position handle between the front seats. The flaps are spring loaded toward the retracted position. The wing rear spar provides the flap mounting structure. Use the detents to explore the discrete positions.

Try & observe

Choose each flap detent. Both inboard flaps move together; the ailerons remain independently controlled.

Supplied reference

Detents: 0°, 10°, 25°, 40°
Rigging tolerances: 0° ± 1°, 10° ± 2°, 25° ± 2°, 40° ± 2°
Maximum flap speed: 111 KIAS (POH)
Source as supplied: PA-44 maintenance manual, PDF page 320
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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PA-44 maintenance manual, PDF page 320

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Control systems

Electric stall warning

The stall-warning system provides an alert as the wing approaches stall angle of attack. Your course material identifies separate inboard and outboard switches associated with flap settings. Verify switch-to-flap mapping for the specific aircraft configuration before treating it as an aircraft-specific fact.

Try & observe

This lab does not calculate stall onset or operate stall-warning switches. Inspect the supplied reference for configuration questions.

Supplied reference

Course slide: outboard: 0° and 10° flaps
Course slide: inboard: 25° and 40° flaps
Source as supplied: User-supplied lesson notes; configuration-dependent details require verification against the applicable maintenance manual.
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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User-supplied lesson notes; configuration-dependent details require verification against the applicable maintenance manual.

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Control systems

Static wicks and bonding

Static discharge wicks and electrical bonding help manage accumulated static electricity and reduce radio interference. These are not primary flight controls, but are located on or near control surfaces and should be checked during preflight.

Try & observe

Inspect the supplied photograph. Static wicks are reference content here, not separately articulated parts of the 3D illustration.

Supplied reference

Purpose: Static discharge and electrical continuity
Inspection: Security and condition
Source as supplied: User-supplied photograph of static discharge wicks
Unverified reference values; these are not approved operating limits or calibrated rigging measurements.

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User-supplied photograph of static discharge wicks

Source revision and reuse permission unverified.

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A little context.

Explore the whole, then understand the parts.

What you'll learn

Connect roll, pitch and yaw inputs to the corresponding control surfaces.
Compare differential aileron movement and discrete flap positions.
Separate trim input from primary control input in an illustrative model.

Before you begin

Recognize the wing, stabilator and rudder.

Move one control at a time. Watch the connected surface and compare the text readout. Both cockpit yokes show the same input. Use the labeled sliders as the keyboard alternative to dragging.

Center yoke & pedals retains trim and flap settings. Reset study restores every input, selection and camera to its starting state. This is an educational control demonstrator, not an approved flight-training device.

Sources & further reading

FAA: Flight Controls
Pilot’s Handbook of Aeronautical Knowledge, FAA-H-8083-25C (2023), chapter 6. General control relationships only; does not validate PA-44 travel limits or installations.
Piper: Technical Publications
Locate the aircraft-specific POH and maintenance manual. The supplied HTML cites chapter 27 figures 27-10, 27-14 and 27-19, PDF pages 301, 311 and 320, and POH sections 7.3 and 7.15 without a verified revision. Exact values and configuration remain unverified.

About this draft & its limitations

Adapted from Moyo’s supplied flight-controls HTML. Inputs are normalized percentages; readouts use unverified supplied travel values and are not approved rigging or operating limits. Anti-servo coupling is qualitative. No forces, aerodynamic response, airspeed or aircraft motion are calculated. Manual applicability, image reuse rights and technical claims remain unverified.