Cessna C525 Citation, CJ1 / CJ1+

Two Williams International FJ44-1A medium-bypass (3.3 to 1) turbofan engines, installed on rear fuselage pylons, produce 1900 pounds of static thrust each, flat rated to 72°F (22°C) at sea level. Ice protection and fire detection and extinguishing systems are incorporated. Thrust attenuators, consisting of panels which extend into the engine exhaust stream, are controlled by an AUTO/STOW/TEST switch and the throttle levers. An optional engine synchronization system is available. Fuel is carried in two integral wing tanks with each engine normally supplied from its respective side. Fuel can be balanced with the fuel transfer system. Fueling is accomplished through an overwing port in each wing tank.
FADEC is NOT incorporated.
1.2.2Avionics / Cockpit Layout
The Collins Pro Line 21 Avionics System incorporates dual VHF COMM transceivers, dual VHF navigation receivers with glideslope, ADF receiver and dual Mode S transponders. Detailed operating instructions are provided in the Bendix/King CNI 5000 Integrated Avionics System, Pilot’s Guide. Navigation equipment includes a GPS receiver with IFR approach capability, one automatic direction finder (ADF), a single distance measuring equipment (DME) system, two very high frequency omnidirectional radio range VOR/localizer/glideslope receivers (the number one [pilot’s] system having a standby NAV indicator), and a marker beacon receiver. The standard two-display flight guidance system consists of an integrated display which includes an electronic flight instrument system (EFIS) for the pilot. The left PFD displays attitude, navigation/compass, flight control, primary air data (altitude, airspeed, and vertical speed), and TCAS advisory functions for the pilot. The Multifunction Display (MFD) provides engine

indicating displays, navigation/compass, flight management, checklist, diagnostic, and optional TCAS pictorial information for the pilot. Weather radar is available on both the PFD and MFD. The optional right PFD displays attitude, navigation/compass, flight control, primary air data, and TCAS advisory functions for the co-pilot. Weather radar and dual transponders with altitude reporting and mode S capabilities are also included in the standard package. Instead of the Bendix King Avionics, one or two Garmin 500 series GPS/RTU.
For Bendix King Avionics see Citation Jet.
For Collins Pro Line 21 Avionics see CJ1+.
For Garmin 500 GPS/RTU see CJ1+.
• Two AFD-3010 Adaptive Flight Displays (Pilot's Primary Flight Display (PFD) and Multifunctional Display (MFD)
• ONE ADC-3000 Air Data Computer and associated temperature probe
In the optional second PFD configuration, additional subsystems included are:
• Copilot's PFD
• Copilot's ADC-3000
Long Range Navigation:
Either an AlliedSignal KLN 900 GPS Receiver or a GNS-XLS Flight Management System is installed.
The AlliedSignal KLN 900 is a single-unit panel or pedestal mounted, long range, Global Positioning System (GPS) based airborne navigation system with a database. Besides the panel or pedestal mounted GPS receiver, the system is comprised of a KLN 900 configuration module and a KA 92 antenna mounted on top of the forward fuselage. All output data is read from the unit front panel display, and all input to the unit is via the front panel controls. The primary purpose of the equipment is to provide the pilot with present position information and to display guidance information with respect to a flight plan defined by the pilot.
Flight plan information is entered by the pilot via various knobs and buttons on the front panel. The screen display normally is divided into five segments defined by vertical and horizontal lines on the screen. The larger top left segment is called the left page and the larger top right segment is the right page. The lower left segment displays the name of the left page being displayed while the small lower right segment displays the name of the right page being displayed. The lower middle segment displays the mode of operation, for example "ENG-LEG" is enroute-Leg mode which is the normal mode for enroute operations. There are eight types of pages tht may be displayed on the left side of the screen and 10 types of pages that may be displayed on the right side. The abbreviations for these page types are displayed around the outside of the left and right outer knobs. Some types of pages, such as NAV, have more than one page. Once the type of page is selected using the outer knob, the inner knob is used to select the specific page.

The GNS-XLS Flight Management System is a comprehensive navigation management system which integrates multiple systems and sensors into an integrated whole, which is capable of precise navigation and aircraft performance computations. The system takes information from various navigation sources (DME and GPS sensors), considers the strengths, weaknesses and signal strengths of each system and sensor in use, and computes a most likely position for the airplane. The GPS sensor has priority unless degraded sensor accuracy has been detected by the system. It accomplishes these computations with a minimum of attention by the flight crew, and advises them of components or systems requiring attention, as well as other irregularities such as loss of enough sensors to compute a valid position. In the latter situation, if sensor loss endures over a set length of time, the system will enter DR (dead reckoning) mode and so inform the pilot through a message on the control display unit (CDU) and display a red boxed "FMS" on the MFD.
The GNS-XLS provides steering information to the pilot through the primary flight display (PFD). When connected to the autopilot, it provides roll steering commands. The NAV computer additionally computes fuel flow information, providing a current fuel status and airplane gross weight throughout the flight, if the fuel and gross weight are updated prior to take-off.
The system also provides navigation data outputs which enable the active flight plan to be displayed on the multifunction display (MFD).
The following components comprise the GNS-XLS system: a control display unit (CDU) which houses its own global positioning system (GPS) sensor, a configuration module unit, and an antenna. The GPS antenna is mounted on top of the fuselage near the cabin door.
The CDU is the heart of the system, possessing the computer, the navigation data bank, and the memory capability, as well as the GPS receiver. The NDB maintains 50,000 navigation points in its data base as well as up to 999 operator generated waypoints. Fifty- six flight plans with up to fifty waypoints each may be stored. The NAV data base must be updated every twenty-eight days by means of a memory card. The card is inserted into in a personal computer memory card International Association (PCMCIA) slot under the lower portion of the alpha keyboard on the CDU.

1.2.4Weight & Balance
Refer to AFM, Weight and Balance Data, Section VI.
Max Ramp Weight: 10.800 lbs
Max Take Off Weight: 10.700 lbs
Max Landing Weight: 9.900 lbs
Max Zero Fuel Weight: 8.400 lbs
Standard Empty Weight: 6.670 lbs
Useful Load: 4.030 lbs
Useful Fuel Capacity: 3.220 lbs
1.2.5Flight Controls
For more information refer to chapter 1.4 – CJ1+
1.2.6Hydraulic System
For more information refer to chapter 1.4 – CJ1+
1.2.7Fuel System
For more information refer to chapter 1.4 – CJ1+