Excerpts from Textron Aviation Aircraft Operating Manuals - Chapter 16 - Avionics (Citation CJ4 & Cessna Mustang)

Oct 23, 2026

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Extracted manual passages from Textron Aviation Aircraft Operating Manuals focus on Chapter 16 avionics, especially attitude and flight guidance displays in the Citation CJ4 and the flight control architecture in the Cessna Mustang. The excerpts explain how attitude indicators present sky/ground cues, how PFD declutter logic responds to pitch and bank limits, and how integrated flight director, autopilot, and yaw damper systems compute and display active or armed modes. They also describe control-panel functions and behavior on GIA failures and system engagement.

LanguageEnglish

CategoryTechnology

FormatPDF

Pages5

Reading Time13 min

AccessFree to download

Chapter 16 – Avionics

Citation CJ4 Operating Manual

Attitude and PFD declutter logic

Flight guidance system overview and modes

Flight guidance computer (FGC) behavior and transfers

Flight guidance panel controls (FD, YD, APXFR, AP, disconnect)

Cessna Mustang Operating Manual

Attitude and turn coordination indications

Automatic flight control system (AFCS) description

Excerpts from Textron Aviation Aircraft Operating Manuals Page 16-7, Chapter 16 – Avionics, Citation CJ4 Operating Manual “Attitude—Indicator shows cyan over brown with pitch marks aligned in the center and bank indices at the top. The lower portion of the sky pointer is the slip/skid indicator. The PFD declutters (removes unnecessary information) automatically if pitch exceeds 30° nose up, 20° nose down, or 65° of bank. Only attitude and heading are displayed in the declutter mode. As pitch and/or bank is reduced (5° less than declutter onset), all normal displays return.” Page 16-15, Chapter 16 – Avionics, Citation CJ4 Operating Manual “FLIGHT GUIDANCE SYSTEM The flight guidance system is an integrated flight director, autopilot, andyaw damper (Figure 16-16). All computations are performed by a pair of FGCs. The FGC computes pitch and roll commands for the flight director and can be coupled to the autopilot shown on the PFDs. The pitch and roll commands are based on the active modes. Mode messages are shown on the PFD if the autopilot is engaged or if the onside flight director is on. Two channels offlight guidance are provided. The primary controls for the flight guidance system are on the FGP. Additional controls consist of yoke-mounted buttons for autopilot synchronization (SYNC), autopilot (AP) disconnect (DISC), and throttle lever go around (GA) buttons. The system uses lateral navigation signals and vertical inputs to maintain desired courses or tracks (top of the PFD). The flight director window shows which FGC is in control of the command bars and autopilot, whether the autopilot or yaw damper is on, and what lateral and/or vertical commands are active and/or armed and the values for some modes of operation. Pilots should look at this window to determine what mode the aircraft is actively engaged in and what mode has been armed to do in the future… …FLIGHT GUIDANCE COMPUTER (FGC) The FGC takes mode selections and NAV information to command the flight director to arm, capture, and track lateral and vertical guidance. If the autopilot is on, the FGC drives the pitch and roll servos. The system powers up with the left side in control and a solid arrow in the flight director window points left. One FGC controls the autopilot and the other controls monitoring capabilities; however, both FGCs must be operating for the autopilot to function. The pilot can manually transfer to the other FGC, when needed, by pressing the APXFR button on the flight director panel. This action points the solid arrow to the right and removes all flight director modes. The FGC in control also defines which ADC altitude encoder is normally used by the active transponder. When the TO/GA button on either throttle is pushed, both FGCs are active with each driving its own side command bars. The solid arrow points to the side driving the autopilot; a stick arrow points to the opposite side. When any lateral mode is active, other than APPR LOC, a single solid arrow is displayed. When APPR LOC and GS are active both arrows are shown (both FGCs commanding their own set of bars)… FLIGHT GUIDANCE PANEL The flight guidance panel, on the glareshield, allows the pilot to select manual or autopilot guidance for aircraft control in lateral and/or vertical direction (see Figure 16- 16). The flight guidance panel has the following controls and functions: • FD button—Displays or removes the FGC on the PFD. Deselecting the FGC (FD off) does not disengage the autopilot and any active and armed modes continue to show and function. If the autopilot is turned on while the flight director is off, basic roll and pitch modes are active with no other mode armed or active. If the autopilot is turned on while flight director modes are active, the command bars move to the aircraft symbol, and then the autopilot attempts to fly the selected modes. This may cause small excursions away from desired course. Always display command bars and have the ai

FAQs

What triggers PFD declutter mode in the Citation CJ4 attitude display?

The PFD declutters automatically when pitch exceeds 30° nose up, 20° nose down, or when bank reaches 65°.

What is the flight guidance system composed of in the Citation CJ4 manual excerpt?

It is an integrated system consisting of a flight director, autopilot, and yaw damper, with computations performed by a pair of FGCs.

How does the AFCS operate in the Cessna Mustang when a GIA fails?

If either GIA fails, the other GIA performs the flight director functions. If both GIAs fail, the AFCS is not operational.

Oct 23, 2026

Upload by dhado