January 2004
Schedule ‘A’
B o m b a r d i e r L e a r j e t 45
XR
(45-232 and Subsequent)
Description
And
Customer Support Services Manual
TABLE OF CONTENTS
1.0 Introduction........................................................................... 1
2.0 General Description.............................................................. 2
3.0 Performance......................................................................... 4
4.0 Certification .......................................................................... 4
5.0 Structural Design .................................................................. 5
6.0 Fuselage Group.................................................................... 5
7.0 Wing Group .......................................................................... 6
8.0 Empennage Group ............................................................... 6
9.0 Landing Gear........................................................................ 6
10.0 Power Plant .......................................................................... 6
11.0 Systems................................................................................ 7
12.0 Instrumentation and Avionics ............................................... 9
13.0 Interior ................................................................................ 12
14.0 Exterior ............................................................................... 15
15.0 Special Equipment.............................................................. 15
16.0 Emergency Equipment ....................................................... 15
17.0 Customer Support Services................................................ 16
18.0 Warranty............................................................................. 18
19.0 Patent and Trademark Protection....................................... 19
20.0 Consultants ........................................................................ 19
1
1.0 INTRODUCTION
This document describes the Aircraft, including its
power plant, systems, equipment and standard
interior provisions.
Also included are descriptions of Learjet’s customer
support services that are provided to the Buyer as
part of the sale of the Aircraft, including technical
publications, crew training and the maintenance
management program.
The Aircraft may be subject to changes during the
course of the design, manufacture and certification
process or as the result of any legislation, act, order,
directive or regulation, or any interpretation thereof,
of or by any government or governmental body. If
such changes take place and apply to all aircraft in
general or to all aircraft of the same category as the
Aircraft and are effective after the date of the
Agreement but before Delivery Time, Buyer shall
pay Learjet’s reasonable cost for such changes. If
the incorporation of such changes delays the
delivery of the Aircraft, that delay shall be an
Excusable Delay under the Agreement.
This document is published for the purpose of
providing general information on the standard
baseline Aircraft configuration. No options, foreign
certification requirements or Aircraft customization
are included or accounted for.
2
2.0 GENERAL DESCRIPTION
The Aircraft is a pressurized, low-wing monoplane
with provisions for up to 9 persons plus a minimum
crew of two. Allowance for luggage and optional
equipment is provided.
Two Honeywell TFE731-20BR turbofan engines
are pylon-mounted on the rear fuselage.
APPROXIMATE DIMENSIONS
Overall Height 14.13 ft 4.31 m
Overall Length 57.60 ft 17.56 m
Wing
Span (overall) 47.78 ft 14.56 m
Area 311.62 sq ft 28.95 sq m
Sweep (@25% chord) 13.4°
Dihedral 2.5°
Aspect Ratio 6.75
Mean Aerodynamic Chord 7.3 ft 2.23 m
Horizontal Tail
Span (overall) 17.19 ft 5.24 m
Area 67.02 sq ft 6.23 sq m
Sweep (@25% chord) 25°
Aspect Ratio 4.41
Vertical Tail
Span 6.00 ft 1.83 m
Area 39.00 sq ft 3.62 sq m
Sweep (@25% chord) 39°
Aspect Ratio 0.92
Landing Gear
Tread 9.33 ft 2.84 m
Wheel Base 25.82 ft 7.87 m
Tire Pressure – Main 159 psi 1,096 kPa
– Nosewheel 105 psi 724 kPa
Tire Size – Main 22.00 x 5.75 in 0.56 x 0.15 m
– Nosewheel 18.00 x 4.40 in 0.46 x 0.11 m
Cabin (Finished Dimensions)
Height (maximum over aisle) 4.92 ft 1.50 m
Length (between forward and aft pressure bulkheads) 25.68 ft 7.83 m
Width (maximum) 5.12 ft 1.56 m
Door Width 2.50 ft 0.76 m
Design Weights and Capacities
Maximum Ramp Weight 21,750 lb 9,866 kg
Maximum Takeoff Weight 21,500 lb 9,752 kg
Maximum Landing Weight 19,200 lb 8,709 kg
Maximum Zero Fuel Weight 16,000 lb 7,257 kg
Standard Basic Operating Weight (± 5%)* 13,435 lb 6,094 kg
Approximate Fuel Capacity (usable @ 6.7 lb/gal) 6,062 lb 2,750 kg
*Standard Basic Operating Weight includes unusable fuel, oil, standard interior, standard avionics, paint and 2 crew.
3
2.0 GENERAL DESCRIPTION
Aircraft Three-View
14.13 ft
(4.31 m)
9.33 ft
(2.84 m)
57.60 ft
(17.56 m)
47.78 ft
(14.56 m)
25.82 ft
(7.87 m)
4
3.0 PERFORMANCE
Conditions
All performance is based on a standard Aircraft
certified to U.S. 14CFR Part 25 requirements,
standard (ISA) day conditions. Options, Aircraft
customization and foreign certification requirements
requested by Buyer may result in a change in
performance.
Takeoff Field Length (± 5%)
1
5,060 ft 1,542 m
14CFR 91 Landing Distance (± 5%)
1
2,660 ft 811 m
14CFR 36 Noise Levels
Takeoff (thrust cutback) 75.5 EPNdB
Sideline 85.1 EPNdB
Approach 93.4 EPNdB
Long Range Cruise Speed @ 47,000 ft
2
421 KTAS 484 mph 780 km/hr
Maximum Cruise Speed
2
@ 37,000 ft 464 KTAS 534 mph 859 km/hr
@ 41,000 ft 464 KTAS 534 mph 859 km/hr
@ 45,000 ft 457 KTAS 526 mph 846 km/hr
Maximum Operating Speed M 0.81
Maximum Operating Altitude 51,000 ft 15,545 m
Initial Cruise Ceiling @ MTOW 45,000 ft 13,716 m
VFR Range (± 5%)
3
2,231 nm 2,568 sm 4,132 km
Notes:
1. Maximum takeoff/landing weight, sea level, standard (ISA) day conditions. Field lengths are based on a level hard surface,
dry paved runway with zero wind.
2. At 17,250 lb (7,824 kg) cruise weight, standard (ISA) day conditions.
3. Range with 2 crew, 4 passengers and 45 minutes reserve. Includes climb, cruise and descent with zero wind and standard
(ISA) day conditions en route.
4.0 CERTIFICATION
The Aircraft is certified to the requirements of U.S.
Federal Aviation Regulations 14CFR Part 25 and
Joint Aviation Authorities JAR 25 Airworthiness
Standards: Transport Category Aircraft, as specified
in the type certificate data sheet, including day,
night, VFR, IFR and flight into known icing. The
aircraft is also RVSM capable.
Learjet will provide Buyer with a Federal Aviation
Administration (FAA) Standard Airworthiness
Certificate at Delivery Time.
5
5.0 STRUCTURAL DESIGN
The Aircraft is an all-metal, pressurized, low-wing
monoplane. The high-aspect ratio, fully cantilevered,
swept wings with winglets are of conventional riveted
construction except for the upper section of the
winglets, which utilizes full-depth honeycomb core
bonded to the outer skin. The fuselage is of semi-
monocoque construction. Two inverted “V” ventral
fins (delta fins) are fitted to the aft section of the
tailcone.
Design load factors are –1.0 G to +3.0 G (flaps
retracted) and 0.0 G to +2.0 G (flaps extended).
At the maximum altitude of 51,000 feet (15,545 m),
a nominal maximum cabin pressure differential of
9.4 psi (64.8 kPa) provides an 8,000-foot (2,438 m)
cabin altitude.
Maximum Operating Speeds
Vmo 330 KIAS 380 mph 611 km/hr
Mmo M 0.81
Flap Extension Speeds (Vfe)
Flaps 8° 250 KIAS 288 mph 463 km/hr
Flaps 20° 200 KIAS 230 mph 370 km/hr
Flaps 40° 150 KIAS 173 mph 278 km/hr
Landing Gear Operating and Extended Speed
VLO (extend or retract) 200 KIAS 230 mph 370 km/hr
VLE (maximum with gear extended) 260 KIAS 299 mph 482 km/hr
C.G. Range
Forward Limit at 14,000 lb (6,350 kg) to 15,000 lb (6,804 kg) 1.0% MAC
Forward Limit at 18,000 lb (8,165 kg) 7.0% MAC
Forward Limit at 19,500 lb (8,845 kg) 12.0% MAC
Forward Limit at 21,750 lb (9,866 kg) 19.5% MAC
Aft Limit to 14,000 lb (6,350 kg) 25.0% MAC
Aft Limit at 15,000 lb (6,804 kg) to 21,500 lb (9,752 kg) 28.0% MAC
Aft Limit at 21,750 lb (9,866 kg) 25.3% MAC
6.0 FUSELAGE GROUP
The fuselage section is of conventional semi-
monocoque construction. Maximum internal cabin
width is approximately 5.1 feet (1.55 m) and cabin
height is approximately 4.9 feet (1.49 m) in the center
aisle.
The nose section includes a composite radome, high-
resolution radar, and the avionics bay.
The windshields meet bird-strike requirements of
14CFR Part 25 up to 330 knots calibrated airspeed.
The 30-inch wide (75 cm), two-piece, clamshell, main
cabin entry door is located on the forward left-hand
side of the fuselage. The upper half of the entry door
can be opened independently to serve as a forward
emergency escape hatch.
Steel pins secure the door in the closed position and
make the door an integral part of the cabin structure
under pressurization loads. A Type III, plug-type,
emergency escape hatch is located on the aft right-
hand side of the cabin.
The aft fuselage tailcone has an equipment bay,
which contains the major components of the
hydraulic, environmental, electrical distribution
and engine fire extinguishing systems. A hinged
door on the right side of the tailcone provides
access to the tailcone equipment section.
The aft fuselage tailcone also contains a heated
baggage compartment accessed by a hinged door
on the left-hand side of the tailcone.
An anti-collision light is located on the underside of
the fuselage.
6
7.0 WING GROUP
The swept, fully cantilevered wing consists of a three-
spar internal structure covered by machine-milled
wing skins. Both upper and lower wing skins are
tapered in thickness from root to tip to minimize
weight and optimize strength. The wing is attached to
the fuselage by six machined fittings.
The wing incorporates supercritical winglets and a
cambered leading edge. Control surfaces on the
wing trailing edge include ailerons outboard and
flaps and spoilerons inboard. Both the left and right
ailerons incorporate mechanical, geared balance
tabs. The left aileron also incorporates an
electrically actuated trim tab. The wing leading
edge is anti-iced using engine bleed air.
Navigation lights are located on the outboard side
of each winglet and trailing edge of the vertical fin.
8.0 EMPENNAGE GROUP
The T-tail consists of a fixed vertical fin, a dorsal fin,
two delta fins, a movable one-piece horizontal
stabilizer, two elevators and a rudder with trim tab.
An electrically operated screw jack pivots the three-
spar horizontal stabilizer for pitch trim. The horizontal
stabilizer’s leading edge is anti-iced using engine
bleed air.
The vertical fin is of three-spar construction. An
anti-collision light is mounted on the top aft end of
the vertical fin bullet fairing. The front edge of the
dorsal fin incorporates a ram air scoop to provide
ram air to the environmental control system.
9.0 LANDING GEAR
The Aircraft is equipped with a fully retractable tricycle
landing gear. The landing gear extension and
retraction system is electrically controlled and
hydraulically actuated. Extension is accomplished
with normal electrical control and hydraulics or
alternatively with a manually controlled free-fall
system.
The main gear is equipped with air-oil, trailing link
shock struts and dual wheels with individual high
energy capacity carbon brakes and a fully modulated
anti-skid control system.
The nose gear utilizes a single wheel and chine tire
mounted on a conventional air-oil shock strut.
Both main and nose gear actuators incorporate
mechanical locks to hold the gear in the extended
position.
A digital steer-by-wire system provides nosewheel
steering through the rudder pedals. The maximum
steering angle is 60 degrees each side of center
with full rudder deflection for low-speed taxi. As
ground speed increases, the maximum steering
angle reduces.
10.0 POWER PLANT
Two Honeywell TFE731-20BR engines are located on
the rear fuselage, one on each side. Each engine is
mounted at three attachment points and is controlled
by an N1 Digital Electronic Engine Control (DEEC)
system, which includes an Engine Condition Trend
Monitoring (ECTM) system as standard equipment.
The engines are rated to produce 3,500 pounds (15.6
kN) Takeoff (TO) Thrust and 3,650 pounds (16.2 kN)
Automatic Power Reserve (APR) Thrust at sea level
and 104°F (40°C).
A continuous cable direct-current fire detection
system with three loops is installed in each engine
nacelle. A dual bottle fire extinguishing system
provides fire-extinguishing capabilities for either or
both engines.
Electrically controlled and hydraulically operated
target-type thrust reversers, which employ a
clamshell door design are standard equipment.
7
11.0 SYSTEMS
Flight Controls
Dual control columns are provided in the cockpit. The
primary flight controls (ailerons, elevators, and
rudder) are mechanically operated through the control
wheels, control columns, and rudder pedals.
Movement of the control surfaces is accomplished
through systems of cables, pulleys, bell cranks and
push rods. The elevators incorporate dual, redundant
control circuits. In the event of a jammed elevator, a
means of disconnection is provided in the cockpit for
the continued safe flight and landing on the
unjammed control circuit. In the event of a jammed
aileron, the variable position spoilers operate as
spoilerons to provide continued safe flight and
landing. Elevator and rudder cable runs are
separated in the aft fuselage for rotor burst protection.
Nosewheel steering, when engaged, is
electronically controlled by the rudder pedals.
Braking is accomplished by depressing the upper
portion of the pedals.
The single-slotted flaps are electrically controlled
and hydraulically/mechanically actuated. The flap
control system includes a position preselect lever,
control electronics and a flap position indicator.
Flap positions of UP (0°), 8°, 20° and DN (40°) can
be selected by the flap preselector lever located on
the right side of the pedestal.
Spoilers are installed on the upper surface of the
wing forward of the flaps. The variable position
spoilers are electrically controlled and hydraulically
actuated. Autospoiler operation can be utilized for
maximum deceleration on landing.
Fuel System
An independent fuel system is provided in each wing
for its respective engine. The aircraft fuel system
consists of a fuel transfer system, an engine feed
system, a fuel quantity indicating system, two wing
and one fuselage fuel tanks. The three fuel tanks are
connected with expansion and transfer lines and act
as one tank. A single gravity fuel fill port is located on
top of the aft fuselage to fill the wings and fuselage
tanks. A single-point pressure refueling system,
accessed from the right-hand side of the aircraft, is
installed as standard equipment. The aircraft may
be defueled through the pressure refueling adapter.
During normal operation, each wing tank supplies
fuel to its respective engine. Fuselage fuel is
automatically transferred to both wing tanks as fuel
is used by the engines. Crossflow capability is
provided and permits equalization of fuel between
both wing tanks and also makes fuel on board the
aircraft transferable to either engine.
Hydraulic System
The hydraulic system provides pressure to operate
the landing gear, main gear inboard doors, brakes,
flaps, thrust reversers and spoilers. Two engine-
driven, variable-volume piston-type pumps and an
electrically driven, variable-volume piston-type
auxiliary pump provide a system pressure of 3,000
psi (20,684 kPa). Conventional MIL-H-5606
hydraulic fluid is used.
8
Electrical System
The electrical power distribution system consists of
dual rear batteries, left and right, a nose-mounted
emergency battery, dual engine-driven starter/
generators, power distribution panels and an
electrical control panel.
The generating system consists of two 30 VDC, 400
ampere (limited to 300 ampere) engine-driven
starter/generators, two generator control units and
associated forward and aft power distribution panels.
Two aft 24 VDC, 27 ampere-hour NiCad main
batteries and the nose emergency battery provide DC
power for engine starting and emergency bus
operation. Two main (L and R) battery switches
and the emergency battery switch provide
individual battery control for source application bus
isolation.
Exterior lighting consists of two landing, two
recognition, and two taxi lights; navigation lights
installed on each wing tip and in the vertical
stabilizer fairing aft end; and two anti-
collision/strobe lights, one mounted on top of the
vertical stabilizer and the other on the bottom of the
fuselage. A wing inspection light is located on the
right-hand forward fuselage.
Pressurization and Environmental System
Environmental control utilizes engine bleed air
sources to provide cabin ventilation, heating, cooling
and pressurization. Cabin pressure is automatically
maintained by the digital cabin pressure control
system. Control is achieved electro-pneumatically,
with pneumatic redundancy for backup. Either
engine is adequate to maintain pressurization. The
pressurization system provides a maximum pressure
differential of 9.4 psi (64.8 kPa) which provides a
sea level cabin altitude to 25,700 feet (7,833 m) and
a maximum 8,000-foot (2,438 m) cabin altitude at
51,000 feet (15,545 m).
Cabin and cockpit temperature control is completely
automatic with provisions for manual override. An
air cycle system is provided for cooling, heating and
dehumidification of the cabin and cockpit, on the
ground or in flight.
Oxygen System
A 22.8 cubic foot (670 l) oxygen storage cylinder is
installed in the nose compartment. Pressure
demand masks are provided for both pilot and
copilot. Automatic dropout, constant flow oxygen
masks are provided for each passenger.
Ice and Rain Protection
Engine bleed air is used to prevent ice formation on
the wing and horizontal stabilizer leading edges and
nacelle inlet lip. Electrical heaters are used on the
pitot static masts and angle-of-attack transducer
vanes. An electrically heated element in each
windshield provides windshield anti-ice and
defogging. An ice detection system with a probe
mounted on the lower portion of the nose provides
crew alert when icing conditions exist. A passive
hydrophonic coating provides windshield rain
removal.
9
12.0 INSTRUMENTATION AND AVIONICS
General Description
Honeywell’s Primus 1000 system includes Engine
Instrument/Crew Alerting System (EICAS) and
Electronic Flight Instrument System (EFIS). The
system features four 8- by 7-inch (20 x 18 cm) display
tubes including dual Primary Flight Displays (PFD)
plus one Multifunction Display (MFD) and one EICAS
display.
The heart of the Primus 1000 is Honeywell’s dual
integrated avionics computers (IC-600 #1 and #2),
which provide redundant flight directors and EFIS/
EICAS processors in each Line Replacement Unit
(LRU). A digital autopilot is provided in IC-600 #2.
Also included are two rear mounted dual-channel
Data Acquisition Units (DAU) and two forward
mounted solid-state Micro Air Data Computers
(MADC).
A dual Litef LCR 93 Attitude Heading Reference
System (AHRS) is standard. This system is based on
fiber optic motion detection and features small size,
lightweight and extensive built-in test capabilities.
Dual Honeywell Primus II navigation/communication/
identification radios are standard. The fully
integrated radio system features central tuning with
dual Radio Management Units (RMU). A liquid-
crystal “flat panel” display for the RMUs also
provide back-up navigation and engine displays.
The Primus II system features dual VHF comms,
dual VHF navs, single ADF, dual DMEs, dual
Mode-S transponders, and a single radio altimeter.
Honeywell’s Primus 660 weather radar features
Rain Echo Attenuation Compensation Technique
(REACT). The radar information can be displayed
on the MFD and is pilot-selectable on either PFD.
Flight Management System (FMS)
The flight management system (Universal Avionics
UNS-1E) is a master computer that processes
multiple sensor inputs to provide a best computed
position for en route and terminal navigation. The
system incorporates a navigation computer,
12 channel GPS receiver and control/display
functions in one compact, lightweight system and
includes a 5 inch (13 cm) active matrix LCD display
unit and a data transfer unit (DTU) for updating the
worldwide database. Meets navigation
qualifications for North Atlantic tracks (GPS primary
means of navigation). Complies with MNPS.
Standby Mach Airspeed
A 2-inch (5.1 cm) Mach airspeed indicator is provided
as a backup to the dual Air Data System (ADS). The
unit is a panel-mounted pneumatic instrument and is
located in the center of the instrument panel. Input
is provided by the third dedicated pitot static probe.
10
Standby Altimeter
A 2-inch (5.1 cm) altimeter is provided as a backup
to the dual ADS. The unit is a panel-mounted
pneumatic instrument and is located in the center of
the instrument panel. Input is provided by the third
dedicated pitot static probe.
Standby Attitude Indicator
A 2-inch (5.1 cm) attitude gyro is provided as backup
to the dual AHRS/EFIS display system. The unit is a
panel-mounted electric attitude instrument and is
located in the center of the instrument panel.
Standby Magnetic Compass
A lighted, compensated standby magnetic compass is mounted on the windshield center post.
Enhanced Ground Proximity Warning System (EGPWS) with windshear
Provides state-of-the-art “Look-Ahead” warnings to
reduce Controlled Flight Into Terrain (CFIT) through
audio and visual means. Other features include
ground proximity warning, glideslope alerting,
display of threatening terrain and / or obstacles on
EFIS, windshear detection and alerting, and
configurable altitude callouts. Escape guidance for
windshear is not provided.
Traffic Collision Avoidance System (TCAS 2000)
Monitors airspace around the aircraft and, by
interrogating an “intruding” aircraft’s transponder,
determines if a potential conflict exists. Visual and
audio alerts are given with Traffic Advisories (TA)
and Resolution Advisories (RA) as required.
Includes dual Mode S Transponders with diversity
and complies with Change 7 requirements (ACAS II
in Europe).
Emergency Locator Transmitter
An Emergency Locator Transmitter (ELT), which is
actuated manually or by impact. This ELT transmits
on 121.5, 243.0 and 406.025 MHz frequencies. The
406.025 MHz transmission carries the serial number,
country code and manufacturer name of the ELT.
This information is decoded and provides the
owner’s name, address, telephone number and type
of aircraft. This signal is received by the
COSPAS/SARSAT low altitude orbiting satellites.
The location of the aircraft can be determined with
an accuracy better than 1.6 nautical miles (3 km).
Cockpit Voice Recorder (CVR)
11
A solid-state unit records voice signals transmitted or
received in the cockpit for a maximum period of
30 minutes. The unit is a solid-state recorder
assembly with controls for operation and an
underwater locator beacon.
Additional Instruments and Avionics Systems
The following additional instruments and systems are installed on the Aircraft:
• Digitally-controlled anti-skid braking system
• Master warning/caution annunciation system
mounted in the glareshield
• System test switch panel
• Aural/voice tone warning systems
• Engine Sync
• Dual avionics master switches
• Dual digital clocks
• Single-point pressure refueling
• Triple heated pitot static probes
• Wing ice detection light
12
Typical Instrument Panel
13.0 INTERIOR
The cockpit extends from the forward pressure
bulkhead approximately 5.93 feet (1.81 m) to the
cabin divider. The passenger cabin extends from
the cabin divider approximately 19.75 feet (6.02 m)
to the aft pressure bulkhead.
The passenger cabin offers a maximum height of
4.92 feet (1.50 m) and a maximum width of 5.12 feet
(1.56 m). Sixteen cabin windows with sun shades
are provided.
13
Cabin Features
The standard cabin configuration includes the following:
• Eight passenger seats in a double club configuration
with swivel and reclining features. Seats include inboard
armrest.
• LED Cabin lighting package
• Armledge storage with master control panel (MCP)
• Cabin PA system
• Satin nickel plating is standard
• Complete side panel cover with soundproofing
insulation and carpeting
• Convenience panel with reading lights, air vents and
cabin speakers (Oxygen masks are in headliners)
• Window shades
• Drink holders
• Four folding tables
• Coat closet
• Galley
• Aft lavatory
• Curtain closeout to cockpit
• One maintenance runner for center aisle
• Selection of carpets (80 ounces per square yard
(2.26 Kg/m
2
) used for Standard Basic Operating
Weight calculations)
• Curtain closeout to cockpit
Galley Features
The standard galley includes:
• Liquid warmer
• Ice drawer
• Trash storage
• Miscellaneous storage
Cockpit
The following items are included in the standard cockpit configuration:
• Two crew seats with sheepskin covers
• Two life vests
• Fire extinguisher
• Headliner
• Electronically-heated footwarmers
• Rail-mounted sunvisors
• Two dome lights
• Two speakers
• Electrically adjustable rudder pedals
• Crew oxygen masks with comfort control
• Two standard Mag-Light flashlights
• Hobbs hour meter
Lavatory Features
Standard lavatory features include:
• Externally serviced flushing toilet
• Tissue dispenser and miscellaneous storage
• Solid panel doors
• Coat rod
• Baggage net
14
Plating
• Satin nickel
Shell
• Headliner: ultrasuede, vinyl or stretch-knit fabrics
• Sidewall: ultrasuede, vinyl or stretch-knit fabrics
• Cabin armrest (upper): leather or vinyl
• Cabin armrest (lower): leather, vinyl or selected
fabric
• Table insert: high-pressure laminate
• Carpet: selected cut or loop styles
Cabinetry
• Interior: high-pressure laminate
• Exterior: high-pressure laminate
• Vanity countertop: faux finish
Seating
• Selected fabric or leather
Baggage
The Aircraft is equipped with two baggage
compartments. Inside the Aircraft, an aft lavatory
baggage compartment provides 15 cubic feet
(0.42 cu m) of storage space and can accommodate
up to 170 pounds (77 kg) of baggage. A heated
tailcone baggage compartment provides
approximately 50 cubic feet (1.42 cu m) of storage
space and can accommodate up to 500 pounds
(227 kg) of baggage.
Cabin Configuration
15
14.0 EXTERIOR
The Aircraft will be provided with non-metalic
polyurethane paint consisting of an overall base
color and a choice of paint schemes. Frequently
used access panel screws will be painted separately
from the fuselage.
15.0 SPECIAL EQUIPMENT
The Aircraft will be delivered with the following standard special equipment:
• Pitot covers
• Dorsal inlet cover
• Two engine covers
• Gust locks
• Maintenance interphone
• Standard lock package
• Illinois lock in the entry door, and Medeco locks in
the baggage bay door and tailcone door. All
three door locks have different key codes
• Three jack pads
• Tail stand
The Aircraft also includes the MCOS II ground support software and Maintenance Computer Interface Adapter
(MCIA). The MCOS along with the MCIA can communicate with most of the Aircraft’s onboard systems, and
acquire and display aircraft information from them in real time.
16.0 EMERGENCY EQUIPMENT
The Aircraft will be delivered with the following standard emergency equipment:
• Fire extinguisher
• Individual flotation devices
• Emergency exit signs
MedAire Program: Free of charge for one year and, upon subscription, renewable annually thereafter with
MedAire. MedAire provides the following services:
• Medlink Worldwide: 24-hour pilot to physician
hotline for immediate medical consultation while in
flight or on the ground.
• Training: 2-day course on management of In-flight
Illness and Injury Training designed to help flight
crews.
• Aircraft First Aid Kit: Comprehensive first aid kit
designed specifically for handling in-flight medical
incidents.
16
17.0 CUSTOMER SUPPORT SERVICES
Training
As part of the Purchase Price, Learjet shall make
available at its designated training facility:
• A ground and simulator flight-training program for
two qualified pilots to type rating; and
• A ground maintenance-training program for two
mechanics.
Buyer shall be responsible for all travel and living
expenses of Buyer's pilots and mechanics. Learjet
recommends that all training be completed before
placing the Aircraft into service, but, in any event, all
training shall be completed no later than 1 year from
Delivery Time or Buyer's rights to training at no
additional cost shall expire.
Technical Data and Services
The Aircraft will be delivered with one (1) copy of
each of the following documentation and the
technical publications that are included in the
Purchase Price of the Aircraft:
• U.S. Standard Airworthiness Certificate, Export
Certificate of Airworthiness or Special
Airworthiness Certificate as appropriate
• Aircraft Flight Manual
• Pilot's Manual
• Logbooks (airframe and engines)
• Weight and Balance Report
• Maintenance Manuals (airframe and engines)
• Illustrated Parts Catalog (airframe and engines)
• Wiring Manuals
• Component Manuals
• Passenger Information Cards
• Also included is a one year subscription to the CD-
ROM Maintenance Manual which includes
maintenance manual, parts catalog, wiring manual
and service bulletins. It also features interactive
links between manual and key word searches.
Operates on standard computer CD-ROM reader.
In addition, commencing at Delivery Time, Learjet
shall make available, from time to time, to Buyer at
its last address provided by Buyer in writing to
Learjet, service bulletins and general information
applicable to the Aircraft, as well as any
amendments to the documentation and technical
publications referred to above applicable to Buyer's
Aircraft for a period of ten (10) years after delivery of
the last Learjet 45 aircraft manufactured by Learjet.
Learjet shall provide this service at no additional cost
to Buyer for a period of one (1) year from Delivery
Time. It is understood that the documentation and
publications provided under this paragraph and any
other software, data, drawings or information related
to the Aircraft, including any copies thereof, shall not
be reproduced or disclosed without Seller’s
authorization and are proprietary to Seller and that
all rights to patent, copyright, trademark, trade secret
and other intellectual property rights therein belong
to Seller. Buyer agrees not to modify, translate,
reverse assemble, reverse engineer or decompile
such documentation, publication, software, data,
drawings or other information. Further, Buyer agrees
to use such documentation, publications, software,
data, drawings or other information solely to
maintain, operate or repair the Aircraft.
Computer Integrated Maintenance Management Program (CIMMS)
In order to facilitate the performance of maintenance of the Aircraft at required intervals, Learjet provides the
Learjet Computer Integrated Maintenance Management System (CIMMS) program free of charge for one year and,
upon subscription, renewable annually thereafterAny computer software (“Software”) delivered by Seller to Buyer in
connection with the CIMMS program or the Aircraft, excluding any Software covered by separate license
17
agreements (whether shrink-wrap or otherwise), is being licensed to Buyer and not sold. Seller hereby grants to
Buyer (who for this purpose is a mere licensee) a personal, non-exclusive, and non-transferable (except in
connection with a transfer of the Aircraft) license to use the Software solely for its intended purpose and solely in
connection with the intended operation of the Aircraft. The Software, all copies thereof, and all derivative works
based thereon, in whole or in part, and all copyright, patent, trade secret, and other intellectual and proprietary
rights therein (whether arising under the laws of Canada, the United States, or under other foreign laws or
international treaties), are and shall remain the property of Seller. All copyright, patent, trademark, and other
similar notices shall be displayed as designed. Buyer shall not duplicate or permit the duplication of the Software.
Buyer shall not modify, translate, reverse assemble, reverse engineer, or decompile the Software, in whole or in
part. The license shall terminate when the Software is no longer being used as intended in connection with the
CIMMS program or the Aircraft.
18
18.0 WARRANTY
18.1
Learjet warrants to Buyer that at Delivery Time, the
Aircraft shall be free from: i) defects in material, ii)
defects in manufacture and iii) defects in design,
having regard to the state-of-the-art as of the time of
design of the Aircraft (“Warranty”). Learjet’s sole
obligation and liability under this Warranty is a)
expressly limited to correction by repair, replacement
or rework of the item(s) by Learjet at Learjet’s
facilities, or at such other facility as may be
designated by Learjet, of any defect specified above
and b) subject to Buyer giving notice to Learjet of a
claim under this Warranty within 90 days of discovery
of the defect. The Aircraft or any item(s) found
defective shall be returned to Learjet at Buyer’s
expense.
18.2
The Warranty in respect to the Aircraft shall be for 60
months from Delivery Time except that the Warranty
in respect to the Completion Work shall be for 24
months from Delivery Time.
18.3
Buyer shall be entitled to claim a repair, replacement
or rework pursuant to this Warranty provided:
i) The Aircraft has not been operated or maintained
in material violation of the provisions of Learjet’s
approved Flight Manual, Maintenance Manual
and Service Bulletins, and as each thereof may
be amended from time to time by Learjet;
ii) An installation, repair, alteration or modification to
or of the Aircraft made by Buyer or a third party
has not been the cause or a contributing cause of
the defect;
iii) The Aircraft has not been subjected to misuse,
abuse or accident or has not been improperly
stored and protected against the elements when
not in use.
18.4
Notwithstanding any other provisions herein, the
Warranty shall not apply to any engines installed on
the Aircraft. The engine warranty shall be provided
directly by the engine manufacturer (Honeywell Inc.)
to Buyer, shall be the sole responsibility of the engine
manufacturer, and the rights of Buyer with respect to
the engines shall be a matter as between the engine
manufacturer and Buyer. Buyer agrees that Learjet
shall have no obligation or liability for any engine
warranty including, without limitation, any lack of
performance, reliability or maintainability of the
Aircraft as a result of the engines.
18.5
Learjet does not warrant, and is hereby relieved of
any obligation to warrant, any accessory,
equipment or part incorporated in the Aircraft,
which is not furnished pursuant to this Agreement.
Life-limited components (e.g. batteries, brakes,
etc.) will be covered under this Warranty on a pro-
rata basis.
18.6
This Warranty excludes the following:
• Scheduled maintenance
• All fuel, landing fees, applicable taxes,
tariffs, duties, freight, crew expenses and
insurance
• Supplies necessary for airplane cleaning,
servicing and replenishment of toilet
supplies, fuel, oil, hydraulic fluids, liquid
deicing systems, oxygen system, and other
consumables.
• Silk covered items, metallic paint or interior
plating (other than brushed nickel plating)
• Light bulbs, lenses, filters, gaskets, o-rings,
fasteners and tires
•
Normal deterioration of soft trim and
appearance items, such as paint,
upholstery and rubber-like items, due to
wear and exposure
18.7
Any repair, replacement or rework under the
Warranty shall be covered to the extent of the
unexpired portion of the Warranty periods set forth
in this Article 18 remaining at the time of such
repair, replacement or rework.
18.8
Buyer shall be responsible for any expenses or
costs related to items submitted under this
Warranty that are later determined to have no
defect (No Fault Found).
18.9
Buyer shall maintain reasonably complete records
of operations and maintenance of the Aircraft and
shall make such records available to Learjet as
Learjet may reasonably require. If Buyer fails to
maintain those records Learjet shall be relieved of
its Warranty obligations.
18.10
The Warranty is for the benefit of Buyer, its
successors and all persons to whom title to the
Aircraft may be transferred during the Warranty
periods set forth herein, provided that any
successor or owner shall remain subject to the
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BOMBARDIER Learjet 45XR Description And Customer Support Services Manual
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