Source: https://manualzz.com/doc/10872231/citation-xls--spec-dec
Timestamp: 2019-07-18 19:20:30
Document Index: 649519553

Matched Legal Cases: ['art 135', 'art 25', 'art 91', 'art 25', 'art 25', 'art\n25']

Citation XLS+ Spec Dec | manualzz.com
Citation XLS+ Spec Dec
Units 560XLS-6172 to TBD
UNITS 560XL-6172 TO TBD
C e ssna A irc raft C ompany
P.O. B ox 7 7 06
W ic hita, Kansas 6 7 27 7 -7 7 06
This Specification and Description is published for the purpose of providing general information for the evaluation of
the design, performance, and equipment of the Cessna Citation XLS+, Units 560XL-6172 to TBD. This document supersedes all previous Specification and Description documents and describes only the Cessna Citation XLS+ Model
560XL, its powerplants and equipment.
Due to the time span between the date of this Specification
and Description and the scheduled delivery date of the Aircraft, Cessna reserves the right to revise the Specification
whenever occasioned by product improvements, government regulations or other good cause as long as such revisions do not result in a material reduction in performance.
Wichita, Kansas 67277-7706
Telephone: 316-517-6449
Telefax: 316-517-6640
In the event of any conflict or discrepancy between this
document and the terms and conditions of the Purchase
Agreement to which it is incorporated, the terms and conditions of the Purchase Agreement govern.
WARNING: This product contains Halon 1211 and Halon 1301. Furthermore, the product is manufactured with 1-1-1 Trichloroethane, substances which harm public health and environment by destroying ozone in the upper atmosphere.
Oc tober 2015, Revision F
CESSNA CITATION XLS+ SPECIFICATION AND DESCRIPTION
General Description ...........................................................................................................................................................
Certification ..........................................................................................................................................................
Approximate Dimensions .................................................................................................................................
Design Weights and Capacities ......................................................................................................................
2. Performance ..........................................................................................................................................................................
Structural Design Criteria ...................................................................................................................................................
Fuselage .................................................................................................................................................................................
5. Wing ........................................................................................................................................................................................
6. Empennage ...........................................................................................................................................................................
Landing Gear .........................................................................................................................................................................
8. Powerplants ...........................................................................................................................................................................
Systems...................................................................................................................................................................................
Flight Controls .....................................................................................................................................................
Fuel System .......................................................................................................................................................... 9.3
Hydraulic System ................................................................................................................................................
Electrical System .................................................................................................................................................
Pressurization and Environmental System ...................................................................................................
Oxygen System ..................................................................................................................................................
Ice and Rain Protection .....................................................................................................................................
10. Avionics ..................................................................................................................................................................................
General ..................................................................................................................................................................
Instrument and Control Panels ........................................................................................................................
Avionics .................................................................................................................................................................
Miscellaneous Cockpit Equipment .................................................................................................................
11. Interior .....................................................................................................................................................................................
Standard Interior Configuration ......................................................................................................................
Baggage Compartments ..................................................................................................................................
12. Exterior ....................................................................................................................................................................................
13. Additional Equipment .........................................................................................................................................................
14. Emergency Equipment .......................................................................................................................................................
15. Documentation and Technical Publications ..................................................................................................................
16. Computerized Maintenance Record Service ................................................................................................................
Limited Warranties ..............................................................................................................................................................
Cessna Citation XLS+ Limited Warranty .......................................................................................................
New Engine Warranty ........................................................................................................................................
Summary of Honeywell APU Warranty .........................................................................................................
18. Citation XLS+ Crew Training Agreement .......................................................................................................................
FIGURE I — CITATION XLS+ EXTERIOR DIMENSIONS .............................................................................................................
FIGURE II — CITATION XLS+ INTERIOR DIMENSIONS .............................................................................................................
FIGURE III — CITATION XLS+ INSTRUMENT PANEL AND PEDESTAL LAYOUT .................................................................
FIGURE IV — CITATION XLS+ STANDARD FLOORPLAN .........................................................................................................
The Cessna Citation XLS+ is a low-wing aircraft with retractable tricycle landing gear and a conventional tail. A
pressurized cabin accommodates a crew of two and up to
12 passengers (nine is standard). An interior configuration
of ten or more passenger seats is not available for 14 CFR
Part 135 operations. Two Pratt & Whitney Canada (P&WC)
PW545C turbofan engines are pylon-mounted on the rear
fuselage. Fuel stored in the wings offers generous range
for missions typical of this class aircraft. Space for baggage is provided in the cabin and tailcone.
The Model 560XL is certified to the requirements of U.S.
14 CFR Part 25, Transport category, including day, night,
VFR, IFR, flight-into-known icing conditions and steep approach. Optional certifications include Part 91 Category II.
The Citation XLS+ is compliant with all RVSM certification
requirements. (Note: specific approval is required for operation within RVSM airspace; Cessna offers a no charge
service to assist with this process.)
Multiple structural load paths and system redundancies
have been built into the aluminum airframe. Metal bonding techniques have been used in many areas for added
strength and reduced weight. Certain parts with noncritical loads such as the nose radome and fairings are
made of composite materials to save weight. The airframe
design incorporates anti-corrosion applications and lightning protection.
The Purchaser is responsible for obtaining aircraft operating approval from the relevant civil aviation authority. International certification requirements may include modifications and/or additional equipment; such costs are the
Cessna offers a third-party training package for pilots and
mechanics, and various manufacturers’ warranties as described in this book. Cessna’s worldwide network of company-owned and authorized service facilities provides a
complete source for all servicing needs.
56 ft 4in (17.17 m)
FIGURE I — CITATION XLS+ EX TERIOR DIMENSIONS
(0.97 m)
(4.67 m)
(.51 m)
(.36 m)
(.28 m)
(.91 m)
FIGURE II — CITATION XLS+ INTERIOR DIMENSIONS
1.2 APPROXIMATE DIMENSIONS
Overall Height ........................................................................................................................................................................... 17 ft 2 in (5.23 m)
Overall Length ........................................................................................................................................................................ 52 ft 6 in (16.00 m)
Overall Width ........................................................................................................................................................................
Span (does not include tip lights) ....................................................................................................................................... 55 ft 8 in (16.97 m)
Area ......................................................................................................................................................................................... 369.7 ft2 (34.35 m2)
Sweepback (at 25% chord) ...........................................................................................................................................................
Span (overall) ............................................................................................................................................................................ 21 ft 6 in (6.55 m)
Area ............................................................................................................................................................................................... 84.8 ft2 (7.89 m2)
Sweepback (at 25% chord) .............................................................................................................................................................
Height ........................................................................................................................................................................................... 9 ft 0 in (2.74 m)
Area ............................................................................................................................................................................................... 50.9 ft2 (4.73 m2)
Sweepback (at 25% chord) .............................................................................................................................................................. 33 degrees
Height (maximum over aisle) ......................................................................................................................................................... 68 in (1.73 m)
Width (trim to trim) ............................................................................................................................................................................ 66 in (1.68 m)
Length (forward pressure bulkhead to aft pressure bulkhead) .................................................................................... 24 ft 0 in (7.32 m)
Tread (main to main) ................................................................................................................................................................. 14 ft 11in (4.55 m)
Wheelbase (nose to main) ...................................................................................................................................................... 21 ft 11 in (6.68 m)
1.3 DESIGN WEIGHTS AND CAPACITIES
Maximum Ramp Weight .................................................................................................................................................... 20,400 lb (9,253 kg)
Maximum Takeoff Weight .................................................................................................................................................. 20,200 lb (9,163 kg)
Maximum Landing Weight .................................................................................................................................................. 18,700 lb (8,482 kg)
Maximum Zero Fuel Weight .............................................................................................................................................. 15,100 lb (6,849 kg)
Standard Empty Weight* ................................................................................................................................................... 12,300 lb (5,579 kg)
Useful Load .............................................................................................................................................................................. 8,100 lb (3,674 kg)
Fuel Capacity (useable) at 6.70 lb/gal ............................................................................................................................. 6,740 lb. (3,057 kg)
* Standard empty weight includes unusable fuel, full oil, standard interior, and standard avionics.
All performance data is based on a standard aircraft configuration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing field lengths are based on a level, hard surface, dry runway. Actual performance
will vary with individual airplanes and other factors such as environmental conditions, aircraft configuration, and operational/
Takeoff Runway Length ............................................................................................................................................................ 3,190 ft (972 m)
(Maximum Takeoff Weight, Sea Level, ISA
Balanced Field Length per Part 25, 15° Flaps)
Climb Performance ......………………...................................................…..............................................………….. 29 min to 45,000 ft (13,716 m)
(Maximum Takeoff Weight, Sea Level, ISA)
Maximum Altitude ............................................................................................................................................................... 45,000 ft (13,716 m)
Maximum Cruise Speed (± 3%)
........................................................................................................ 451 KTAS (836 km/hr or 519 mph)
(Mid-Cruise Weight, 31,000 ft (9,449 m), ISA)
NBAA IFR Range (100 nm alternate) (± 4%) ......................................................................................... 1,920 nm (3,556 km or 2,209 mi)
(Maximum Takeoff Weight, Full Fuel, Optimal Climb
and Descent, Maximum Cruise Thrust at 45,000 feet)
Landing Runway Length .............................................……....................................................................................................... 2,740 ft (835 m)
(Maximum Landing Weight, Sea Level, ISA, per Part 25)
Certified Noise Levels
Takeoff ..........................................................................................................................................................................
72.7 EPNdB
Sideline ...........................................................................................................................................................................
86.3 EPNdB
92.8 EPNdB
Landing .........................................................................................................................................................................
3. STRUCTURAL DESIGN CRITERIA
The Citation XLS+ airframe is conventional in design, incorporating aluminum alloys, steel and other materials as appropriate. Engineering principles using multiple load paths, low stress levels and small panel size are incorporated in all primary
VMO 8,000 ft (2,438 m) to 26,515 ft (8,082 m) ........................................................................ 305 KIAS (565 km/hr, 351 mph)
26,515 ft (8,082 m) and above ........................................................................................................... Mach 0.75 (indicated)
VFE 0° to 15° Extension .................................................................................................................. 200 KIAS (370km/hr, 230 mph)
VFE 15° to 35° Extension ................................................................................................................ 175 KIAS (324 km/hr, 201 mph)
Landing Gear Operating and Extended Speeds
VLO (retracting) ............................................................................................................................... 200 KIAS (370 km/hr, 230 mph)
VLO (extending) .............................................................................................................................. 250 KIAS (463 km/hr, 288 mph)
VLE .................................................................................................................................................... 250 KIAS (463 km/hr, 288 mph)
A circular fuselage section is utilized with a maximum internal cabin width of 66 inches (1.68 m). A dropped aisle in the
passenger cabin provides 68 inches (1.73 m) of headroom
(measurements represent distance between softgoods).
power brake systems, external power, the battery, and the
externally serviceable toilet.
The nose section includes a composite radome, high resolution radar and the avionics bay. The windshields are designed to meet bird resistance requirements of 14 CFR Part
25. Openable side windows are provided for the pilot and
copilot. The cabin door is located on the forward left-hand
side of the fuselage and is 54 inches (1.37 m) high with a
maximum width of 24 inches (0.61 m). A plug-type emergency exit is located on the aft right-hand side of the cabin.
A baggage compartment is located in the tailcone and is
accessed through a door on the left hand side. The tailcone
also contains an equipment bay which houses the APU
and the major components of the hydraulic, environmental,
electrical distribution, flight controls and engine fire extinguishing systems. External access to the equipment bay is
provided through a door on the RH side of the tailcone. The
APU is accessed through a panel above the right engine
pylon. Additional equipment may also be accessed through
removable panels inside the baggage compartment.
Various systems are housed or accessed through the wing/
fuselage fairing. Removable or openable panels are provided for single point refueling, servicing of the hydraulic and
The aft fuselage is equipped with small strakes on both
sides. The strakes are of a conventional construction and
extend the usable C.G. range of the aircraft.
The straight wing design is of conventional, all metal construction. The wing incorporates fuselage attachment
points and a dropped carry-through which permit a continuous dropped aisle in the passenger cabin and lavatory. The
wing structure has a two-cell torque box formed by spars,
stringers, ribs and skin. Four degrees dihedral contributes
to lateral stability. Integral fuel tanks are located in each
wing forward of the aft spar and in the wing carry through
section which passes under the fuselage.
Control surfaces on the wing include an outboard aileron
with a trim tab on the left side, two flap sections per wing,
and an upper and lower speed brake on each wing. The
wing tips include navigation lights, strobe lights and flush
mounted recognition/landing lights. Aileron, flap and speed
brake gaps are sealed to reduce drag. The flaps utilize
graphite composite materials.
6. E M P E N N A G E
The empennage consists of a vertical stabilizer, horizontal stabilizer and a dorsal fin. The dorsal fin is attached to
the top side of the rear fuselage and has two ram air ducts
to provide air for use in the aircraft heat exchangers. The
horizontal stabilizer incorporates a nine-degree dihedral for
minimum sonic fatigue and thrust effects. Control surfaces
include the elevators with a trim tab on each elevator and a
rudder with a rudder servo/trim tab.
The horizontal stabilizer has two position settings, a takeoff
and landing position, and a cruise position. Stabilizer position is controlled by flap position and airspeed.
A red flashing beacon is provided at the top of the rudder
7. L A N D I N G G E A R
Both the main and nose landing gears use a single wheel
assembly. The nose gear has a chined tire for water and
slush deflection. The main landing gear is a trailing link type.
The landing gear retraction system is electrically controlled
and hydraulically actuated. The main gear retracts inboard
into the wing. When retracted, the main gear strut is covered by a door. Wing mounted fairings aerodynamically
blend the retracted tires. The nose gear retracts forward
into the fuselage nose section and, when retracted, is enclosed by three doors. All three doors remain open with the
nose gear fully extended.
The gear actuators incorporate an internal lock to hold the
gear in the extended position. Mechanical uplocks are used
to hold the gear in the retracted position.
manually operated system which releases the landing gear
for free-fall extension. In the case of an unsuccessful manual release, a pneumatic system releases the uplocks and
extends/locks the gear.
The nose gear is mechanically steered by the rudder pedals
to 20° either side of center. For maximum maneuverability
during ground handling, maximum deflection of the nosewheel is 90° either side of center.
Toe-actuated multiple disc carbon brakes are installed on
the main gear wheels. Anti-skid protection is available at
speeds above approximately 12 knots. Braking can be accomplished by either of two independent systems: the power brake hydraulic system or a back-up pneumatic system.
Normal braking can be applied from either cockpit seat.
Emergency landing gear extension is accomplished by a
8. POWERPLANTS
Two Pratt & Whitney Canada PW545C turbofan engines are
installed on the Citation XLS+, one on each side of the rear
fuselage in easily accessible nacelles. The PW545C produces a static takeoff thrust of 4,119 pounds (18.32 kN) at
sea level, up to 77°F (25°C) and has a bypass ratio of 3.8 to 1.
Major maintenance intervals are 2,500 hours for hot section
inspection and 5,000 hours for overhaul.
(FADECs) provide automation and efficiency in engine management. Detents in the throttle quadrant (takeoff, climb,
cruise) permit optimal power settings based on ambient
conditions for each phase of flight. The system also provides time-limited dispatch (TLD), engine protection, synchronization, and diagnostic capability.
A continuous loop fire detection system monitors the nacelle area to detect and warn if a fire occurs. A two-shot fire
extinguishing system is supplied.
The Honeywell RE100(XL) APU is installed in the tailcone
equipment bay. The APU supplies bleed air for pressurization and air conditioning, electrical power for engine assisted starts, and other benefits. It is certified for use in flight up
to 30,000 feet (9,144 m).
Hydraulically actuated, target-type thrust reversers are attached to each engine. The effect of the thrust reversers
on runway performance is accounted for under various
9.1 FLIGHT CONTROLS
Dual controls are provided and comprise control wheel columns, adjustable rudder pedals, anti-skid power brakes and
mechanical nose gear steering. Pushrod and cable systems
are used to actuate the rudder, elevator and ailerons, each
of which is of metal construction. An integral control lock is
provided in the cockpit for the flight controls and throttles.
9.3 HYDRAULIC SYSTEM
Trim wheels, installed on the pedestal, control mechanical
trim tabs for each elevator, the left aileron, and a servo/trim
tab for the rudder. Pitch trim is also electrically powered
through a split switch mounted on the pilot’s and copilot’s
control wheel.
The flap system consists of two panels on each wing which
are hydraulically actuated. The flap panels are Fowler-type
and are constructed of graphite composites. The flap actuation system includes a position select lever and a flap position indicator. Infinite positioning is provided with detents
at the takeoff (7°), takeoff/approach (15°) and landing (35°)
Speed brakes are installed on the upper and lower surfaces
of each wing. The speed brakes are electrically controlled
and hydraulically actuated by a switch on the side of the
throttle handles.
A rudder bias system is provided to assist the pilot in the
event of an engine failure and improves the balanced field
length for wet runways. The rudder bias system utilizes engine bleed air to power a pneumatic actuator.
Two independent fuel systems consisting of an integral tank
in each wing are provided. System operation is fully automatic throughout the normal flight profile with each engine
receiving fuel from its respective wing tank. Crossfeed capability is provided and, when selected, enables both engines to receive fuel from a single tank.
A capacitance-type fuel gauging system provides direct
reading of fuel on board in pounds. Usable fuel capacity is
6,740 pounds (3,057 kg). Fueling is accomplished through
a lockable filler port on each wing or single point pressure
An open-center hydraulic system operates the two position
horizonal stabilizer, landing gear, flaps, speed brakes, and
thrust reversers. All hydraulic control valves are consolidated into a main manifold and two thrust reverser control
manifolds. A separate independent system is used for the
main wheel anti-skid/power brake system.
Basic aircraft hydraulic pressure is provided by two positive
displacement, engine-driven pumps. Either pump can supply enough flow to operate the system.
An electric motor-driven hydraulic pump charges an accumulator to power the independent system used for the
When activated, the basic aircraft system pressurizes to
1,500 psi (103 bar). Ground connections are provided to service the hydraulic system. Approved hydraulic fluids include
Skydrol and Hyjet. Flare-type fittings, aluminum tubing and
flex-hoses are used throughout the system.
9.4 ELECTRICAL SYSTEM
Electrical power is supplied by two 28-volt DC, 300 ampere,
engine-driven starter/generators and by a 28-volt DC, 300
ampere, APU mounted starter/generator. Generator control
units provide static regulation, overvoltage, feeder fault, and
ground fault protection for each generator. An AC system is
included and dedicated to support the electric windshield.
A separate 500 watt inverter supplies 110 volt AC power to
three outlets: one in the cockpit and two in the cabin.
A 24-volt, 44-amp-hour, nickel-cadmium battery is mounted inside an access panel on the left side of the fuselage
just behind the wing fairing to supply power for starting
and emergency requirements. A receptacle is provided for
connection of an external power unit. Battery temperature
monitoring and battery disconnect systems are provided.
The electrical system incorporates a dual parallel main bus
distribution system, designed so that essential equipment
operation will not be interrupted in the event of a single
power source or distribution system failure.
Exterior lighting consists of one red flashing beacon, two
anti-collision strobes, two wing inspection lights, navigation
lights, two wing recognition/landing lights, two fuselage belly
fairing recognition/landing lights, and the tail flood light system consisting of two external flood lights mounted on top of
the horizontal stabilizer illuminating the vertical fin.
9.5 PRESSURIZATION AND ENVIRONMENTAL SYSTEM
A pneumatic boot ice protection system is used on the horizontal tail leading edge surfaces. Windshield ice detection
lights are mounted on the glareshield and wing inspection
lights are mounted on the fuselage to assist in detection of
ice buildup during night flights.
A fan mounted in the nose avionics bay is available to assist
with rain removal from the windshields during taxi operations.
The pressurization and air conditioning systems utilize APU
or engine bleed air to pressurize and air condition the cabin
and defog the cabin and cockpit side windows. Pressurization is controlled by two outflow valves located in the aft
pressure bulkhead. Cabin altitude and rate of change are automatically scheduled by the pressurization controller.
The system provides a 6,800 foot (2,073 m) cabin altitude at
45,000 feet (13,716 m) (9.3 psi (0.64 bar) nominal maximum
working pressure). Sea level cabin altitude can be maintained
to 25,230 feet (7,690 m).
Air conditioning for the cabin is provided by routing APU or
engine bleed air through the air cycle machine which conditions the air prior to distribution to the cabin. The cabin air
distribution system consists of overhead air ducts and outlets,
and underfloor and armrest air ducts. A separate cockpit air
distribution system is ducted forward through the underfloor
from the aft cabin. Dual thermostats provide independent
sensing for automatic temperature control in both zones.
9.6 OXYGEN SYSTEM
A 77.1 cubic foot (2.18 m3) oxygen bottle is provided with a
high pressure gauge and bottle-mounted pressure reducer.
Automatic dropout, constant-flow oxygen masks are provided for each passenger. Pressure demand masks are provided for the crew.
9.7 ICE AND RAIN PROTECTION
Engine bleed air is used for anti-ice protection of the engine inlets and wing leading edges. The windshields, pitot
tubes, static ports, and angle of attack probe are electrically
anti-iced.
FIGURE III — CITATION XLS+ INSTRUMENT PANEL AND PEDESTAL LAYOUT
10.2 INSTRUMENT AND CONTROL PANELS
The Collins Pro Line 21 is the featured avionics suite on the
Citation XLS+. It includes an integrated Flight Director/ Autopilot and EFIS system utilizing four 8 x 10 inch (20 x 25
cm) color, Active Matrix Liquid Crystal Displays (AMLCD) in
portrait orientation. The two outer displays are Primary Flight
Displays (PFDs) and the two inner are Enhanced Multi-Function Displays (MFDs) including a flexibly displayed Engine
Indicating and Crew Alerting System (EICAS). Because each
display is capable of providing critical flight, navigation, and
engine indications in reversion mode, dispatch is possible
with one display inoperative.
The instrument layout includes a tilt panel below the vertical instrument panel across the width of the cockpit. The tilt
panel improves visibility of instruments mounted low in the
panel. In addition, the pedestal has been designed to ease
crew ingress/egress and to improve maintenance technician interface.
Described in this section are standard XLS+ avionics features such as turbulence Doppler weather radar, Traffic Collision Avoidance System (TCAS), Terrain Awareness Warning
System (TAWS), XM Broadcast Weather, electronic charts
and maps, and EICAS. An L-3 Avionics GH-3000 and EHSI4000 provide standby flight instrumentation with an Ametek
N1/N2/ITT instrument for standby engine display.
A variety of information is available to the crew through a
graphical menu system on the EFIS. PFD functions are controlled via two Display Control Panels (DCPs). The MFD functions are primarily controlled by dual Cursor Control Panels
(CCPs). Dual Control Display Units (CDUs) forward of the
throttle quadrant are a means for radio tuning and the interface with the Flight Management System (FMS). A second
FMS is available as an option.
Two complete crew stations are provided with dual controls
including control columns, adjustable rudder pedals, and
brakes. The crew seats are fully adjustable and include fivepoint restraint harnesses.
Electroluminescent panels, instrument floodlights, and bluewhite background lighting illuminate all cockpit instruments
and switches. Illuminated LED pushbutton switches, overhead map lights and floodlights are also provided. The pitotstatic system includes three heated pitot sources and six
heated static sources to drive the pilot’s and copilot’s flight
instruments and the secondary air data display. The emergency oxygen system provides two pressure demand masks
with microphones for the crew members. Circuit breakers
are installed on circuit breaker panels located on the pilot’s
and copilot’s sidewalls.
A. Installed in Center Glareshield Panel:
LH Pilot’s Digital Audio Control Panel
Master Warning / Master Caution Lights
B. Installed on Right-Hand Panel (copilot):
C. Installed on Center Panel:
Electronic Standby Horizontal Situation Indicator Standby Engine Display with N1, N2, ITT
D. Installed in Glareshield:
Thrust Reverser Indications and Engine Fire
E. Installed on LH Tilt Panel:
F. Installed on RH Tilt Panel:
Anti-Ice / De-Ice Controls
Cabin Pressurization System Controller with Digital Cabin Rate of Climb
Copilot’s AHRS and ADC Reversion Switches
G. Installed on Pedestal:
Landing / Recognition / Taxi Light Controls
Described Described below is the Citation XLS+ standard
avionics suite as referred to in section 17, Limited Warranties.
A. ELECTRONIC FLIGHT DISPLAYS
The Collins Pro Line 21 Avionics System is an integrated
Flight Director/Autopilot and EFIS system utilizing four 8
x 10 inch (.20 x .25 m) color, Active Matrix Liquid Crystal
Displays (AMLCD). The Primary Flight Displays (PFD) are located on the pilot’s and copilot’s panel with two Enhanced
Multi-Function Displays (MFD) on the center panel. All displays are capable of providing compass, radar information,
and engine parameters in reversion mode.
Dual Display Control Panels (DCP) and a Flight Guidance
Panel (FGP) are the primary pilot interfaces with the PFDs.
The DCPs provide dedicated controls for BARO setting,
map range, and radar antenna tilt. The FGP (in the firetray)
provides the means to control selected course, selected
heading, and pre-selected altitude.
Each PFD displays an edge to edge attitude display graphic
with respect to an aircraft symbol, and incorporates a pilot
selectable single cue or cross pointer flight director command bar presentation. Dual digital air data computers
supply information to the PFDs for presentation of altitude,
airspeed, and vertical speed. Altimeter settings may be
displayed in either inches or hectopascals and altitude in
either feet or meters. Dual attitude heading reference systems supply attitude and magnetic heading information.
The PFDs display either a full compass rose, a partial compass arc, or a present position map format (PPOS). Situational awareness presentations (weather detection, TAWS
and TCAS) may be overlaid on either the arc or PPOS map
formats for both the PFDs and the MFDs. The PFDs also
display lateral navigation information in conjunction with the
bearings and compass information. COMM 1 and COMM 2
selected frequencies, ATC transponder code, RAT and UTC
are displayed at the bottom of each PFD. Various annunciations are presented for autopilot/flight director, display,
vertical deviation, and distance.
The pilot’s MFD is able to display a variety of graphical information. Engine parameters will be displayed at the top of
the MFD, including N1, N1 reference, thrust mode, ITT, ignition selected annunciation, N2, oil temp, oil pressure, fuel
quantity, fuel flow and fuel temperature. Below the engine
display is a window which may display extended FMS data
or an integrated electronic checklist. The lower portion of
the MFD displays navigation information in either a full compass rose, partial compass arc, PPOS map format or a planning map format. TCAS and TAWS may also be overlaid on
the navigation information.
The copilot’s MFD displays CAS messages on the upper
portion of the display with the remainder typically used for
electronic chart display. The copilot’s MFD also has the capability to display video for optional enhanced vision systems or surveillance systems.
B. CREW ALERTING SYSTEM (CAS)
The integrated Crew Alerting System provides messages
displayed on the copilot’s MFD. The CAS display consists
of text messages integrated with the master warning/master caution as appropriate and also with aural voice or tone
C. FLIGHT GUIDANCE SYSTEM
The integrated Collins Pro Line 21 Flight Guidance System
(FGS) consists of dual flight guidance computers and a single, three-axis autopilot. Flight director modes consist of
selected heading, lateral navigation capture and track, Go
Around (GA) attitude, altitude hold, preselected altitude capture and track, vertical speed, IAS or Mach hold, and vertical
navigation capture and track. In the absence of a vertical or
lateral selected mode, the system will maintain pitch or roll
attitude. Mode references can be synchronized to current
aircraft parameters with a control wheel mounted SYNC
switch. Flight director commands from either the pilot’s or
copilot’s side may be coupled to the autopilot/yaw damper
system, which consists of three electric servos in the primary flight control system along with an integral automatic
or manual pitch trim system.
D. EMERGENCY DESCENT MODE (EDM)
EDM is a flight director mode that provides an automatic
aircraft descent should the aircraft cabin become depressurized at altitude. EDM is automatically armed when the
autopilot is engaged and aircraft altitude is over 30,000
feet. When EDM is activated, the autopilot generates commands to descend at a speed not exceeding Vmo/Mmo until
reaching 15,000 feet. The pilot is required to retard throttles
manually prior to descent to minimize descent times. Upon
reaching the target altitude, the autopilot will capture and
hold 15,000 feet.
E. ATTITUDE HEADING REFERENCE SYSTEM (AHRS)
Dual Collins AHC-3000 solid-state Attitude/Heading Computers independently supply attitude and heading information to the EFIS and flight guidance system. Either AHC may
be selected for display on each PFD via a cockpit switch.
The heading reference may be slaved to a magnetic flux
detector or may be operated in the free-gyro mode.
F. AIR DATA COMPUTER (ADC)
Dual Collins ADC-3000 digital air data computers independently supply altitude, airspeed, vertical speed and temperature information to each pilot’s PFD. Pressure altitude
information is supplied to each Mode-S transponder, as well
as to the Collins FMS and FGS for vertical mode computations. In addition, a third ADC is dedicated to the Electronic
Standby Instrument System.
G. INTEGRATED FLIGHT INFORMATION
SYSTEM (IFIS)
The Collins IFIS-5000 is integrated with the Collins FMS to
provide a significant increase in situational awareness. The
heart of the system is the line replaceable Collins FSU-5010
File Server Unit. The FSU contains the storage, memory, and
processing power to display Enhanced Map Overlays on an
MFD using high speed Ethernet connections. The cursor
control device allows pilots to place overlays on the Collins FMS navigation presentation such as worldwide political
boundaries including state and national borders; geographical features such as lakes, rivers, and oceans; high and low
enroute airways; and controlled, restricted, and prohibited
airspace. In addition, the XM WX Satellite Weather Data Service (Broadcast Weather) and Jeppesen Electronic Charts
are channeled through the IFIS and may be selected for display on a MFD. See respective descriptions in this section.
The IFIS Enhanced Map Overlay database is updated by
subscription through Collins on a 28 day cycle. The database may be uploaded from a customer-supplied laptop
computer or a USB flash drive through the Database Loading Unit (DBU-5000) located on the pedestal. Inherent flexibility in the Collins IFIS allows for future expansion and/or
upgrades to options currently available such as Interactive
Graphical Weather and Flight Services.
H. CURSOR CONTROL PANEL (CCP)
Two Collins CCP-3310 cursor control panels are provided
for use in conjunction with the IFIS. Three Quick Access
Keys are included which allow rapid selection of pilot defined, pre-stored MFD formats. Other knobs and buttons
support electronic checklist functions and menu functions
for Enhanced Map Overlays, Broadcast Weather, and Electronic Charts. The CCP-3310 also has a radio tuning knob
that may be used to change radio frequencies displayed on
the FMS CDU.
I. INTEGRATED ELECTRONIC CHECKLIST
Capability for display of pilot-defined electronic checklists
is included on an MFD. Control of the checklists is through
the integral Cursor Control Panel, installed in the pedestal.
Windows compatible software is provided for customized
generation of checklist text pages.
J. ELECTRONIC CHARTS
The worldwide Electronic Charts function allows high resolution Jeppesen SID, STAR, and Approach charts as well as
airport taxi diagrams to display on an MFD. This IFIS-driven
feature includes dynamic integration with the Collins FMS
to allow the aircraft’s present position to be shown on all
geo-referenced charts. The ever-growing list of such charts
includes most of the U.S. and many areas outside the U.S.
Collins’ Chartlink feature automatically loads the appropriate charts based on the flight plan data from the Collins
FMS. Using the CCP, the pilot may zoom and pan a chart or
map. The database must be updated by subscription on a
14 day cycle.
K. COLLINS FLIGHT MANAGEMENT SYSTEM (FMS)
A single Collins FMS-3000 with dual CDU displays mounted
in the forward pedestal is standard equipment on the XLS+.
The single FMS standard equipment also includes wiring
provisions for a second FMS-3000. The second FMS-3000
is offered as optional equipment. The single Collins FMS3000 combines the Satellite-Based Augmentation System
(SBAS) enabled GPS-4000S and provides multiple waypoint
navigation solutions blended from GPS, VOR, and DME
sources, suitable for enroute, terminal, and approach navigation. Both lateral and vertical modes may be displayed on
the Flight Director and may be fully coupled to the autopilot.
Airway flight planning, plain language identifiers and airport
communication and navigation frequency lookup features
are included. Present position referenced geopolitical, airspace, and major water boundaries as well as airways may
be overlaid on any of the FMS map formats. Updated software adds Localizer Performance with Vertical Guidance
(LPV) approach capability. The FMS-3000 CDU provides
tuning capability for the radio sensors and transponders.
A performance database specific to the Citation XLS+ is
included in the FMS. It permits flight-planning calculations
prior to departure based on predicted fuel burn. It also allows calculation of aircraft weight, V-speeds, and required
field length based on specific runway conditions. V-speeds
may be automatically posted on the airspeed tape.
The FMS database requires updates by subscription
through Collins on a 28 day cycle. The database may be
uploaded from a customer-supplied laptop computer or a
USB flash drive through the Database Loading Unit (DBU5000) located on the pedestal. The DBU features two USB
ports for FMS navigation database and FSU electronic chart
database upload.
L. GLOBAL POSITIONING SYSTEM (GPS)
The single Collins GPS-4000S is a 12-channel receiver providing satellite-based position data and SBAS-based data
(where available) for use by the Collins FMS-3000. The second GPS-4000S is offered as optional equipment.
M. TERRESTRIAL NAVIGATION RECEIVERS
R. STANDBY RADIO TUNING CONTROL
Dual Collins NAV-4500 navigation receivers provide integrated ground-based navigation functions. Dual VOR, Localizer, Glideslope, and Marker Beacon receivers are standard. A single ADF receiver may be ordered as an option.
Navigation information is displayed on the EFIS. Tuning
and management is accomplished through the CCPs or the
FMS-3000.
The Collins CTL-23D remote VHF radio tuning head is installed in the pedestal and provides a backup tuning source
for COMM 1 and NAV 1 radios. The CTL-23D is functional in
normal and emergency power.
N. DISTANCE MEASURING EQUIPMENT
A single Collins DME-4000 provides the ability to monitor
as many as three active DME stations simultaneously. This
allows full time distance display of pilot-selected VHF navaids, along with the enhancement of FMS position determination through the use of the non-displayed DME channel. Tuning and management is accomplished through the
CCPs or the FMS-3000. The second DME-4000 is offered
O. RADIO ALTIMETER
The Collins ALT-4000 Radio Altimeter system provides
height above the terrain from 2,500 feet (762 m) to touchdown. This information is integrated with functions in the
EFIS, TCAS II, and TAWS and is presented on the PFDs.
P. VHF COMMUNICATION TRANSCEIVERS
The dual Collins VHF-4000 Transceivers provide a minimum
of 16 watts power output and digital receiver and exciter
technology, which will provide growth capability to support
future VHF data link modes of operation. They are compliant with European 8.33 kHz spacing requirements. Tuning
Q. PROVISIONS FOR COLLINS HF-9031A
WITH SELCAL
All wiring, racks, and hardware necessary to accommodate
future installation of the Collins HF-9031A High Frequency
radio with selective calling feature are included as standard.
S. AUDIO CONTROL PANEL
Dual Collins digital audio control panel amplifiers provide
transmitter selection for microphone inputs and direct audio outputs from all receivers to either the speaker or headphones at each crew station. Crew sidetone may be adjusted independently. Collins Variable Audio Level feature
automatically adjusts the overhead speaker audio levels
to compensate for cockpit environmental changes such as
flight with the gear down, flaps extended, or speed brakes
extended. Seven audio levels are selected based on aircraft
T. COCKPIT SPEAKER MUTE SWITCHES
Switches on both LH and RH tilt panels allow the crew to
mute all audio and aural warnings to the cockpit overhead
speakers including TCAS and TAWS. (Note: This system
may not be approved by some international regulation authorities, in which case, it may be disabled.)
U. TRANSPONDERS
Dual Collins TDR-94D Mode S Diversity solid-state transponders include Enhanced Surveillance capability. Altitude
reporting information is supplied from the digital ADCs.
Each transponder is remotely mounted and tuned through
the CCPs or the FMS-3000.
V. TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS II)
The Collins TCAS-4000 system provides traffic awareness
by tracking all Mode C or S aircraft within 35 nm. This system, which meets all ICAO ACAS II (Change 7.1) requirements, selects for display only those aircraft (up to 30) that
pose the greatest collision threat. Traffic Alerts (TAs) and
Resolution Advisories (RAs) are given aurally through the
aircraft audio system and visually on the PFDs. When other
TCAS II-equipped aircraft are encountered, complementary
RA maneuvers are coordinated by each system.
W. PULSE LIGHTS
Z. BROADCAST WEATHER
The system utilizes a soft-start feature to cycle on and off
both taxi and recognition lights to improve own aircraft
visibility in flight. Activation is tied to the recognition light
switch and weight-on-wheels logic. A switch on the panel
allows the TCAS-4000 (TCAS II) to automatically activate
the Pulselight system in the event of a Traffic Advisory (TA)
or Resolution Advisory (RA).
The XM WX Satellite Weather Data Service adds long range
comprehensive situational awareness by providing constantly updated broadcast weather information, channeled
through the IFIS for display on the MFD. By using the CCP,
pilots may select and manipulate site specific products such
as high resolution NEXRAD; graphical echo tops, METARs,
and SIGMETs; and textual METARs, SIGMETs, AIRMETs, and
TAFs. Because of IFIS integration, the aircraft’s present
position is shown on the graphical images. Upgraded software features the capability to have satellite imagery with
NEXRAD overlays, see TFRs both in graphical and textual
formats, view winds aloft, and view cloud-to-cloud lightning
with strikes refreshed every five minutes. Images and data
are available at any altitude and are processed through a
receiver supplied by Heads Up Technologies and stored in
the FSU for recall on demand. This service requires a subscription through XM and is currently available only within
X. TERRAIN AWARENESS WARNING SYSTEM (TAWS)
The Honeywell Mark V is a Class A TAWS providing visual
and aural warning alerts for terrain avoidance. It features the
Honeywell terrain awareness and display system (TADS) and
may be displayed on the MFDs and the PFDs. It includes six
basic alert and warning modes such as excessive descent
rate, altitude loss after takeoff, and inadvertent descent below glideslope. In addition, Mode 7 provides reactive windshear warning and windshear caution.
The Mark V uses GPS input and a worldwide terrain database to display an enhanced graphical plan view of terrain,
color coded in relation to the aircraft’s position. Terrain is
shown in higher resolution around all runways longer than
2,000 feet. Within North America and certain other areas,
manmade obstacles greater than 100 feet are shown and
included in the alert and warning modes. The Mark V also
includes a terrain clearance floor exceedence mode and a
“look-ahead” cautionary mode. Subscribed operators will
be notified by Honeywell of database updates as required.
Y. WEATHER AVOIDANCE RADAR
The Collins TWR-850 Turbulence Doppler weather radar
unit is a stabilized, solid state, X-band color radar system.
The depiction can be overlaid on the arc or present-position
map displays on either the PFDs or MFDs and corresponds
to the map/radar range selected. The radar has a 120 degree scan angle over a selectable range of five to 300 nm.
In addition, the TWR-850 provides turbulence detection
to 50 nm, sector scan (reduced sweep angle for rapid updates), target alert (notifies the pilots of hazardous targets
outside the selected range), and auto-tilt (maintains angle
during altitude or range changes).
AA. ELECTRONIC STANDBY INSTRUMENT
SYSTEM (ESIS)
The L-3 Communications GH-3000 ESIS features solid-state
internal sensors for attitude cues and an independent, dedicated air data computer (remotely mounted) for airspeed
and altitude information. Flight reference information including heading is presented in an EFIS-matched format on
a full-color AMLCD.
BB. ELECTRONIC STANDBY HORIZONTAL
SITUATION INDICATOR (EHSI)
The L-3 Communications EHSI-4000 Electronic Horizontal
Situation Indicator (EHSI) uses a dedicated magnetometer
and signals from the navigation radio to present heading,
range, navigation, and course deviation data in a HSI format. A standby slave switch on the panel may be used to
select directional gyro mode when necessary.
CC. STANDBY ENGINE INDICATOR
Standby engine indications include N1, N2, and ITT for each
engine and are displayed in digits on the standby engine
indicator on the center panel. Exceedances cause the respective digits to flash.
DD. EMERGENCY LOCATOR TRANSMITTER (ELT)
The Artex C406-N provides a three frequency ELT that
transmits on the emergency frequencies of 121.5 and 243.0
MHz and the satellite frequency of 406 MHz. It interfaces
with the onboard Collins FMS and is capable of transmitting
the last known aircraft position on the satellite frequency if
EE. COCKPIT VOICE RECORDER (CVR)
The L-3 Communications FA2100 consists of three major
components: the recorder with ULB (Underwater Locator
Beacon) located in the aircraft tailcone, the control panel
located in the pedestal and a remote microphone located in
the instrument panel glareshield. The recorder continuously records both pilot and copilot audio communications as
well as the cabin PA system. The remote area mic records
all cockpit sound information. The recorder stores the last
120 minutes of data prior to system shutdown.
FF. MAINTENANCE DIAGNOSTIC SYSTEM
The Collins Maintenance Diagnostic System has the ability
to collect, store, and display diagnostic data, service, and
fault messages for many Collins Pro Line 21 Line Replaceable Units (LRUs). The Collins Pro Line 21 system diagnostics provides a listing of current faults, advanced diagnostics information for each current fault, currently failed LRUs,
and fault history. The MDS assists in the diagnosis of aircraft
CAS messages by recording specific relevant parameters
for each CAS message, records engine trend data on every
flight and also interfaces with various aircraft logic modules
and parameters for display of live data. The system can
store fault history for up to 500 faults occurring during the
previous 100 flights and also provides maintenance reports
which may be downloaded in ASCII format to a USB storage device. The maintenance data is available through the
copilot’s MFD and can only be accessed when the aircraft
GG. MAINTENANCE DATA RECORDER
Additional data storage is provided by the Maintenance
Data Recorder to be used for advanced troubleshooting. It
records aircraft logic module and FGC data busses.
Purchaser agrees that Seller has a perpetual license to use
all information contained in the Aircraft recording and/or diagnostic systems for any reason, including maintenance and accident investigation. Purchaser expressly provides Seller with
licensed permission to download, use, and/or read such information at any time. Purchaser further agrees this perpetual
license runs with and is automatically transferred with the title
to the Aircraft and is binding on any and all subsequent purchasers of the Aircraft.
HH. AVIONICS DISPATCH GROUND POWER
The Avionics dispatch ground power switch provides power
to minimal avionics to allow obtaining clearances and FMS
preparation while minimizing aircraft battery drain prior to
starting engines. Avionics dispatch ground power is not
available in flight or when the aircraft battery switch is in
the ON or EMER position. Avionics dispatch ground power
provides power to FMS 1, CDU 1&2 (Control Display Unit for
the FMS), COMM 1, Audio 1&2, and DBU (Database Unit)
equipment. CDU 1 allows for FMS 1 functionality while CDU
2 allows for radio tuning.
10.4 MISCELLANEOUS COCKPIT EQUIPMENT
Seat Belts, Shoulder Harnesses with a Five-
point Restraint System
Generic Seat Tailoring
Monorail Sunvisor (2)
Flight Deck Dividers with a One-Piece Curtain
Ventilation Air Outlets
Overwater Life Vest (2) (TSO-C13)
Three-Book Navigation Chart Case (2)
Emergency Gear Extend Control
FIGURE IV — CITATION XLS+ STANDARD FLOORPLAN
The The XLS+ fuselage is sized to minimize drag while offering passenger comfort and flexibility for a variety of interior
arrangements. The constant section of the cabin provides a
continuous width of 66 inches (1.68 m). The cabin is 18 ft 6
in (5.64 m) long from the flight compartment to the aft pressure bulkhead. The cabin is separated from the flight compartment by the storage cabinet and refreshment center. A
one-piece half-length cockpit curtain is mounted on the RH
forward side of the cabinets and may be pulled across the
aisle and fastened on the LH side.
ing are consistent with this category of aircraft, its operating
speeds and environment. Dropout, constant-flow oxygen
masks are furnished for each passenger for emergency
use. Certified burn resistant materials are used throughout
the cockpit and cabin.
11.2 STANDARD INTERIOR CONFIGURATION
The standard interior configuration of the Citation XLS+ includes the following:
LH Forward Refreshment Center featuring one hot tank,
bottled water storage, two disposable cup dispensers,
beverage can rack, wine bottle storage, divided ice
chest with removable wine caddy, drip tray connected
to a manual overboard drain, trash container, miscellaneous general storage, catering drawer and accent
RH Forward Closet with removable/adjustable shelves,
switch panel for couch occupant and accent lighting,
and a flush-mounted 10.4” monitor for the RosenviewLX
passenger information system. This system provides a
moving map presentation as well as flight information
parameters, such as altitude, distance to destination,
and ground speed. Worldwide satellite map imagery
is included. The system permits the user to configure
specific display settings, and includes audio passenger
briefing capability along with a cockpit-located controller for activating the briefings.
A 13 inch (0.33 m) wide dropped aisle, extending from the
cockpit divider aft to the aft pressure bulkhead, provides a
cabin height of 68 inches (1.73 m) (measurements represent
distance between softgoods).
Passenger seats track forward and aft 7 inches (0.18 m) and
track 4 inches (0.10 m) laterally on the seatbase with 360°
swiveling capability. Seats recline to an infinite number of
positions, with full reclining capability. All passenger seats
are equipped with seat belts, shoulder harness straps with
inertia reel, and an overwater life vest stored in the seatbase shroud.
Eleven elliptical windows are provided in the cabin with
pleated manual window shades. Individual air outlets and
reading lights are provided for each passenger. Indirect
LED lights with full dimming capability, dropped aisle lighting, entrance and emergency exit lights are also provided
in the passenger cabin. Bagged insulation and soundproof-
Two-place side facing couch with stowable center
armrest with dual cup holders, aft armrest cabinet with
dual cup holders and two overwater life vests stored in
LH aft retractable coat rod with hangers
Plated hardware finish
Selected wood veneer cabinetry
Six pedestal seats (four forward and two aft facing) with
dual flip-down armrests, an adjustable headrest, seat
back pocket, and seat restraints. Seats #5 and #6 have
Fasten seat belt, no smoking, emergency exit signs with
chimes (Note: The no smoking sign remains illuminated
at all times unless the optional smoking configuration
Two executive and two slimline tables with leather table
Single insertable ashtray
Fireblocking on all passenger seats
Two cupholders in sideledge at each seat location
Axxess II Iridium Satellite Telephone – Includes two Iridium satellite telephone channels. The system offers PBX
functionality, including call waiting, call forwarding, and
conference calling capability. Service charges apply.
11.3 BAGGAGE COMPARTMENTS
An unpressurized, unheated baggage compartment is
located in the tailcone. The compartment is accessible
through a 25 x 29 inch (0.64 x 0.74 m) lockable door with
an integral step. Anchors for the cargo tie-down straps and
cargo net are built into the compartment walls. In addition,
the cabin accommodates baggage in the 9 inch (0.23 m) RH
forward closet and the aft centerline closet. The following
Overhead panels containing an air vent, reading light,
and oxygen mask for each passenger and the aft lavatory area
Manual pleated window shades
Aft cabin dividers with mirror/veneer and sliding privacy doors
Tailcone Baggage Compartment: 700 lb, 80 ft3 (318 kg, 2.27 m3)
Removable, belted, LH aft side facing seat with restraint
system and fold down seat back cushion for storage
with cargo net and overwater life vest stored in seat
RH Forward Closet: 56 lb, 3.6 ft3 (25 kg, 0.10 m3)
Aft Centerline Closet: 44 lb, 6.6 ft3 (20 kg, 0.19 m3)
RH non-belted externally serviceable flushing toilet
Aft centerline closet with vanity sink, temperature controlled water, coat rod and hooks, and general storage
Distinctive exterior styling featuring polyurethane paint in a variety of colors is provided.
13. ADDITIONAL EQUIPMENT
Two Telex Airman 850 ANR Headsets
Fuel Sump Sample Cup
Emergency Escape Hatch Ground Locking Pin
Thrust Reverser Stow Locks
Emergency Tow Straps (MLG)
Cabin Door Eccentric Adjustment Tools
Static Discharge Wick Covers
APU Cover Kit
14. EMERGENCY EQUIPMENT
Fire Extinguisher in Cockpit and Cabin
Individual Life Preservers (TSO-C13 Overwater)
Two Flashlights (Maglite)
15. DOCUMENTATION AND TECHNICAL PUBLICATONS
U.S. Standard Airworthiness Certificate FAA81002; Export Certificate of Airworthiness FAA8130-4;
or Special Airworthiness Certificate FAA8130-7 as
Abbreviated Procedures Checklist
Cabin Operating Manual
Log Books (aircraft and engines)
Service Bulletins and Service Letters - Engine **
Maintenance Manual - Airframe *
Maintenance Manual - Interior *
Maintenance Manual - Engine **
Maintenance Manual - APU **
Illustrated Parts Catalog - Airframe *
Illustrated Parts Catalog - Interior *
Illustrated Parts Catalog - Engine **
Illustrated Parts Catalog - APU **
Wiring Diagram Manual - Airframe *
Avionics Wiring Booklet *
Component Maintenance Manual *
Structural Repair Manual *
Nondestructive Testing Manual *
Illustrated Tool and Equipment Manual *
CESNAV ***
Seller will provide Service Bulletins, Service Letters and
manual revisions for documents published by Seller for five
years beginning from the start date of airframe warranty.
* These publications are provided on CD-ROM or DVD.
** These publications are provided directly from the applicable supplier.
***CESNAV software provides an integrated FAA approved performance calculator, weight & balance calculator, and operating manual performance data.
16. COMPUTERIZED MAINTENANCE RECORD SERVICE
Seller will provide an online computerized maintenance record service for one full year from the date of delivery of a
Citation XLS+ to the Purchaser.
This service will provide management and operations personnel with the reports necessary for the efficient control
of maintenance activities. The service provides an accurate
and simple method of keeping up with aircraft components,
inspections, service bulletins and airworthiness directives
while providing permanent aircraft records of maintenance
Reports, available on demand, show the current status, upcoming scheduled maintenance activity and the history of
the aircraft maintenance activity in an online format which is
printable locally. Semi-annual reports concerning projected
annual maintenance requirements, component removal
history and fleet-wide component reliabity are provided as
Services are provided through a secure Internet Site requiring a computer with Internet connectivity. A local printer is
required to print paper versions of the online reports and
documentation. If receiving these services through the Internet is not feasible for an operation, a paper based service delivered through the U.S. mail is available at an additional fee.
The standard Citation XLS+ Aircraft Limited Warranty which
covers the aircraft, other than Pratt & Whitney Canada
(P&WC) engines and associated engine accessories and
the Honeywell auxiliary power unit (APU) and associated
APU accessories which are separately warranted, is set
forth below. Seller specifically excludes vendor subscription services and the availability of vendor service providers
from Seller’s Limited Aircraft Warranty. Following Seller’s
Limited Warranty, the engine and engine accessory warranty of P&WC and the APU and APU accessory warranty
of Honeywell are set forth. All warranties are incorporated
by reference and made part of the Purchase Agreement.
All warranties are administered by Seller’s Citation Warranty
17.1 CESSNA CITATION XLS+ LIMITED WARRANTY (LIMITED WARRANTY)
Seller expressly warrants each new Citation XLS+ Aircraft
(exclusive of engines and engine accessories supplied by
P&WC and APU and APU accessories supplied by Honeywell which are covered by their separate warranty), including factory-installed avionics and other factory-installed optional equipment to be free from defects in material and
workmanship under normal use and service for the followOc tober 2015, Revision F
ing periods after delivery:
(a) Five years or 5,000 operating hours, whichever
occurs first, for Aircraft components manufactured by
(b) Five years or 5,000 operating hours, whichever occurs first, for Collins’ standard avionics;
(c) Two years for all other Standard Avionics;
(d) One year for all Optional Avionics;
(e) One year for Actuators, ACMs, Brakes, GCUs, Oleos,
Starter Generators, Valves, Windshields, and Vendor
items including engine accessories supplied by Seller
unless otherwise stated in the Optional Equipment and
Selection Guide; and
(f) One year for Customer (CRQs), Interior Components,
Interior Furnishings, and Paint.
Any remaining term of this Limited Warranty is automatically
transferred to subsequent purchasers of the aircraft.
Seller’s obligation under this Limited Warranty is limited to
repairing or replacing, at Seller’s sole discretion, any part or
parts which:
(1) within the applicable warranty period,
(2) are returned at the owner’s expense to the facility,
from which the replacement part is procured, whether
through Textron Aviation Service Parts & Programs or
a Textron Aviation-owned Citation service facility or a
Citation service facility authorized by Seller to perform
service on the aircraft (collectively “Support Facility”) or
as directed by Seller,
(3) are accompanied by a completed claim form containing the following information: aircraft model, aircraft
serial number, customer number, failed part number
and serial number if applicable, failure date, sales order
number, purchased part number and serial number if
applicable, failure codes, any diagnostic data, and action codes, and
(4) are found by Seller or its designee to be defective.
Replacement parts must be procured through a Support Facility and are only warranted for the remainder of the applicable original aircraft warranty period. A new warranty period is not established for replacement parts. The repair or
replacement of defective parts under this Limited Warranty
will be made by any Textron Aviation-owned Citation service facility or a Citation service facility authorized by Seller
to perform service on the aircraft without charge for parts
and/or labor for removal, installation, and/or repair. All expedited freight transportation expenses, import duties, customs brokerage fees, sales taxes, and use taxes, if any, on
such warranty repairs or replacement parts are the warranty
recipient’s sole responsibility. (Location of Textron Aviationowned and Textron Aviation-authorized Citation service facilities will be furnished by Seller upon request.)
This Limited Warranty applies to only items detailed herein
which have been used, maintained, and operated in accordance with Seller and other applicable manuals, bulletins,
and other written instructions. However, this Limited Warranty does not apply to items that have been subjected to
misuse, abuse, negligence, accident, or neglect; to items
that have been installed, repaired, or altered by repair facilities not authorized by Seller; or to items that, in the sole
judgment of Seller, have been installed, repaired, or altered
by other than Textron Aviation-owned service facilities con-
trary to applicable manuals, bulletins, and/or other written
instructions provided by Seller. Limited Warranty does not
apply to normal maintenance services (such as engine adjustments, cleaning, control rigging, brake and other mechanical adjustments, and maintenance inspections); or to
the replacement of service items (such as brake linings,
lights, filters, de-ice boots, hoses, belts, tires, and rubberlike items); or to normal deterioration of appurtenances
(such as paint, cabinetry, and upholstery), corrosion or structural components due to wear, exposure, and neglect.
WITH THE EXCEPTION OF THE WARRANTY OF TITLE
AND TO THE EXTENT ALLOWED BY APPLICABLE LAW,
THIS LIMITED WARRANTY IS EXPRESSLY IN LIEU OF
ANY OTHER WARRANTIES, EXPRESSED OR IMPLIED,
IN FACT OR BY LAW, APPLICABLE TO THE AIRCRAFT.
SELLER SPECIFICALLY DISCLAIMS AND EXCLUDES ALL
OTHER WARRANTIES, INCLUDING, BUT NOT LIMITED
TO, ANY IMPLIED WARRANTY OF MERCHANTABILITY
OR FITNESS FOR A PARTICULAR PURPOSE. THE AFOREMENTIONED REMEDIES OF REPAIR OR REPLACEMENT
ARE THE ONLY REMEDIES UNDER THIS LIMITED WARRANTY. SELLER EXPRESSLY AND SPECIFICALLY DISCLAIMS ALL OTHER REMEDIES, OBLIGATIONS, AND LIABILITIES, INCLUDING, BUT NOT LIMITED TO, LOSS OF
AIRCRAFT USE, LOSS OF TIME, INCONVENIENCE, COMMERCIAL LOSS, LOSS OF PROFITS, LOSS OF GOODWILL,
AND ANY AND ALL OTHER CONSEQUENTIAL AND INCIDENTAL DAMAGES. SELLER NEITHER ASSUMES NOR
AUTHORIZES ANYONE ELSE TO ASSUME ON ITS BEHALF ANY FURTHER OBLIGATIONS OR LIABILITIES PERTAINING TO THE AIRCRAFT NOT CONTAINED IN THIS
LIMITED WARRANTY. THIS LIMITED WARRANTY SHALL
BE CONSTRUED UNDER THE LAWS OF THE STATE OF
KANSAS AND ANY DISPUTES AND/OR CLAIMS ARISING
THEREFROM SHALL BE EXCLUSIVELY RESOLVED IN THE
STATE AND/OR FEDERAL COURTS LOCATED IN WICHITA, KANSAS. THE PARTIES HERETO CONSENT TO PERSONAL JURISDICTION IN THE FORUM CHOSEN.
17.2 NEW ENGINE WARRANTY
The following is an outline of the P&WC warranty for new
PW545C engines.
P&WC warrants that at the time of delivery all parts of a new
engine comply with the relevant specification and are free
This warranty shall take effect immediately upon acceptance of the engine by the operator, either installed in an
aircraft or delivered as a spare, and shall remain in force
until the expiration of 5 years or the completion of 2,500
operating hours, whichever occurs first. Notice of warranty
defect must be provided to P&WC within 30 days of the occurrence, and P&WC reserves the right to refuse any warranty claim received more than 180 days after the removal
from operation of any engine or engine part.
This is the only warranty applicable to a new PW545C engine and is given and accepted in place of all other warranties or remedies express or implied including without
limitation any warranties as to merchantability or fitness for
purpose. In no event shall P&WC be responsible for incidental or consequential damages.
This warranty is applicable only to engines operated on
non-military aircraft used for commercial, corporate, or private transportation service.
P&WC will repair or replace any parts found to be defective
(including resultant damage to the engine) during the warranty period. Replacement parts may be new parts or serviceable parts. P&WC will pay reasonable engine removal
and reinstallation costs and transportation costs (excluding
insurance, duties and taxes) to and from a facility designated by P&WC warranty administration.
After expiration of the new engine warranty, P&WC will provide commercial support to assist an operator in the event
of extensive damage to an engine resulting from a chargeable defect. This maximum event cost will be based on total
engine hours and cycles run since new, or since last overhaul, adjusted for engine age, as well as environmental and
operating conditions. P&WC reserves the right to cancel or
change this extended coverage at any time.
The operator is responsible for operating and maintaining
the engine in accordance with P&WC’s manuals and recommendations. All repairs to the engines must be carried out
at a facility designated by P&WC warranty administration.
P&WC shall not be responsible for defects or damages resulting from improper use, improper maintenance, normal
wear and tear, accident or foreign object damage (FOD).
For complete information on how this warranty may apply
to you, please write:
1000 Marie-Victorin
Longueuil, Quebec J4G-1A1
17.3 SUMMARY OF HONEYWELL APU WARRANTY:
New APU Warranty:
The following is an outline of the Honeywell warranty for
the new RE100(XL) APU.
Each RE100(XL) APU sold for installation as original equipment on new aircraft will, at the time of delivery, be free
from defects in material and workmanship and shall conform to the applicable specifications. Warranty shall expire
5 years from date of shipment to Owner or 2,500 APU operating hours, whichever first occurs.
The above APU warranty outline is provided as a general
description only; specific terms and conditions are available
through Honeywell (Engines, Systems & Services Division)
and for more complete warranty details, please write to:
Post Office Box 29003
Phoenix, Arizona, 85038-9003.
18. CITATION XLS+ CREW TRAINING
Training will be furnished to First Retail Purchaser (hereinafter called the “Purchaser”), subject to the following:
ing for any of Purchaser’s crew not conversant with the
1. A crew shall consist of up to two (2) licensed pilots with
current private or commercial, instrument and multiengine ratings and a minimum of 1,000 hours total airplane pilot time and up to two (2) mechanics with A&P
licenses or equivalent experience.
c. Payment to Trainer for additional simulator or flight
training beyond that required to attain proficiency in
accordance with Trainer’s standards for the course in
which the pilot is enrolled.
2. Training shall be conducted by Seller or by its designated training organization, at Seller’s option.
a. A simulator shall be utilized which is FAA certified to
provide training for the CE-560XL FAA type rating.
b. In lieu of a model specific simulator, training may be
provided in the most appropriate type simulator available capable of accomplishing the FAA type rating, with
differences training provided.
c. Additional training as requested by the customer,
shall be conducted in the customer’s aircraft.
d. Location of training to be Wichita, Kansas, or unless
mutually agreed otherwise. The organization conducting the training is hereinafter called the “Trainer.”
3. Training furnished shall consist of the following:
a. Flight training to flight proficiency in accordance with
Trainer’s standards aimed toward type certification of
two (2) Captains under applicable Federal Air Regulations not to exceed five (5) total hours for the two (2)
b. Flight simulation training to simulator proficiency in
accordance with Trainer’s standards but not to exceed
thirty (30) total hours for both pilots.
c. Ground School training for each pilot and theoretical
classroom instruction for each mechanic in accordance
with Trainer’s standards.
4. Purchaser shall be responsible for:
a. Transportation of crew to and from training site and
for living expenses during training.
b. Providing an interpreter during the course of train-
d. All aircraft required for flight training as well as all
landing fees, fuel costs, aircraft maintenance and insurance and all other direct costs of operation, including
applicable taxes required in connection with the operation of said aircraft during such flight training.
e. Extra charges, if any, for scheduling pilots in separate
f. Reimbursing to Seller the retail rate for training in the
event of training before actual sale/delivery, if sale/delivery is cancelled.
g. Due to TSA regulations, all current United States citizens must present a current United States passport before training will be able to commence.
5. Seller or Trainer shall schedule all training, furnish Purchaser schedules of training and endeavor to schedule
training at a convenient time for Purchaser. A cancellation fee of Two Hundred Dollars ($200) will be paid to
Seller by Purchaser if crew fails to appear for scheduled training, except for reasons beyond its reasonable
control, unless Purchaser gives Seller written notice of
cancellation received at Wichita, Kansas, at least seven
(7) days prior to scheduled training. In the event of such
cancellation Seller shall reschedule training for the next
available class.
6. Neither Seller nor Trainer shall be responsible for the
competency of Purchaser’s crew during and after training. Trainer will make the same efforts to qualify Purchaser’s crew as it makes in training of other Citation
XLS+ crews; however, Seller and Trainer cannot guarantee Purchaser’s crew shall qualify for any license, certificate or rating.
7. Neither Seller nor Trainer shall be responsible for any
delay in providing training due to causes beyond its or
AGREEMENT (CONTINUED)
their reasonable control.
8. All Training furnished to Purchaser under the Agreement will be scheduled to commence no earlier than
three (3) months prior to delivery and will be completed
within twelve (12) months after delivery of the Aircraft
unless mutually agreed otherwise.
Signature of the Purchaser to the Purchase Agreement to
which this Training Agreement is attached as a part of the
Specification and Description shall constitute acceptance
by Purchaser of the foregoing terms and conditions relative to training to be furnished by Seller. Purchaser agrees
that Seller can provide Purchaser’s name and address to
the training organization for the purpose of coordinating
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