BOMBARDIER Learjet 45-232 Description And Customer Support Services Manual

Brand: BOMBARDIER

Model: Learjet 45-232

Type: Description And Customer Support Services Manual

This manual is also suitable for

Learjet 45XR

BOMBARDIER Learjet 45-232 is a state-of-the-art aircraft designed for exceptional performance and versatility. With its powerful Honeywell TFE731-20BR turbofan engines, it boasts an impressive maximum cruise speed of 484 mph (780 km/hr), enabling you to travel swiftly and efficiently. The long-range cruise speed of 421 KTAS (780 km/hr) allows you to cover vast distances with ease.

The Learjet 45-232 features a spacious cabin with a maximum height of 4.92 ft (1.5 m) and a length of 25.68 ft (7.83 m), providing ample space for passengers and crew. The standard interior includes seating for up to 9 persons, ensuring a comfortable and convenient travel experience.

January 2004

Schedule ‘A’

B o m b a r d i e r L e a r j e t 45

(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

1.0 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.

2.0 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.

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)

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%)

5,060 ft 1,542 m

14CFR 91 Landing Distance (± 5%)

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

421 KTAS 484 mph 780 km/hr

Maximum Cruise Speed

@ 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%)

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.

5.0 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.

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.

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.

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.

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.

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)

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

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.

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

) 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

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

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.

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

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.

18.0 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 45-232 Description And Customer Support Services Manual

Brand: BOMBARDIER

Model: Learjet 45-232

Type: Description And Customer Support Services Manual

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BOMBARDIER Learjet 45-232 Description And Customer Support Services Manual

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BOMBARDIER Learjet 45-232 Description And Customer Support Services Manual

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