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

January 2004

Schedule ‘A

’

TABLE OF CONTENTS

1.0 Introduction........................................................................... 1

3.0 Performance......................................................................... 4

4.0 Certification .......................................................................... 4

5.0 Structural Design .................................................................. 5

6.0 Fuselage Group.................................................................... 5

11.0 Systems................................................................................ 7

12.0 Instrumentation and Avionics ............................................... 9

13.0 Interior ................................................................................ 12

14.0 Exterior ............................................................................... 15

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

1 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

Overall Length

Wing

Span (overall)

Area

Sweep (@25% chord)

Dihedral

14.13 ft

57.60 ft

4.31 m

17.56 m

47.78 ft

311.62 sq ft

14.56 m

28.95 sq m

13.4°

2.5°

6.75

7.3 ft 2.23 m Mean Aerodynamic Chord

Horizontal Tail

Span (overall)

Area

Sweep (@25% chord)

17.19 ft

67.02 sq ft

25°

4.41

5.24 m

6.23 sq m

Vertical Tail

Span

Area

Sweep (@25% chord)

Landing Gear

Tread

Wheel Base

Tire Pressure – Main

Tire Size

– Nosewheel

– Main

– Nosewheel

Cabin (Finished Dimensions)

Height (maximum over aisle)

Length (between forward and aft pressure bulkheads)

Width (maximum)

Door Width

Design Weights and Capacities

Maximum Ramp Weight

Maximum Takeoff Weight

Maximum Landing Weight

Maximum Zero Fuel Weight

Standard Basic Operating Weight (± 5%)*

Approximate Fuel Capacity (usable @ 6.7 lb/gal)

6.00 ft

39.00 sq ft

39°

0.92

9.33 ft

25.82 ft

159 psi

105 psi

22.00 x 5.75 in

18.00 x 4.40 in

4.92 ft

25.68 ft

5.12 ft

2.50 ft

21,750 lb

21,500 lb

19,200 lb

16,000 lb

13,435 lb

6,062 lb

1.83 m

3.62 sq m

2.84 m

7.87 m

1,096 kPa

724 kPa

0.56 x 0.15 m

0.46 x 0.11 m

1.50 m

7.83 m

1.56 m

0.76 m

9,866 kg

9,752 kg

8,709 kg

7,257 kg

6,094 kg

2,750 kg

*Standard Basic Operating Weight includes unusable fuel, oil, standard interior, standard avionics, paint and 2 crew.

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2.0 GENERAL DESCRIPTION

Aircraft Three-View

25.82 ft

(7.87 m)

57.60 ft

(17.56 m)

47.78 ft

(14.56 m)

14.13 ft

(4.31 m)

3

9.33 ft

(2.84 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

Takeoff Field Length (± 5%) 1

14CFR 91 Landing Distance (± 5%)

1

14CFR 36 Noise Levels

Takeoff (thrust cutback)

Sideline

Approach

Long Range Cruise Speed @ 47,000 ft

2

Maximum Cruise Speed 2

@ 37,000 ft

@ 41,000 ft

@ 45,000 ft

Maximum Operating Speed

Maximum Operating Altitude

Initial Cruise Ceiling @ MTOW

VFR Range (± 5%)

3 customization and foreign certification requirements requested by Buyer may result in a change in performance.

75.5 EPNdB

85.1 EPNdB

421 KTAS

464 KTAS

464 KTAS

457 KTAS

M 0.81

2,231 nm

5,060 ft

2,660 ft

484 mph

534 mph

534 mph

526 mph

51,000 ft

45,000 ft

2,568 sm

1,542 m

811 m

780 km/hr

859 km/hr

859 km/hr

846 km/hr

15,545 m

13,716 m

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.

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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 semimonocoque 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

Mmo

Flap Extension Speeds (Vfe)

Flaps 8°

Flaps 20°

Flaps 40°

330 KIAS

250 KIAS

200 KIAS

150 KIAS

Landing Gear Operating and Extended Speed

VLO (extend or retract)

VLE (maximum with gear extended)

200 KIAS

260 KIAS

C.G. Range

Forward Limit at 14,000 lb (6,350 kg) to 15,000 lb (6,804 kg)

Forward Limit at 18,000 lb (8,165 kg)

Forward Limit at 19,500 lb (8,845 kg)

Forward Limit at 21,750 lb (9,866 kg)

Aft Limit to 14,000 lb (6,350 kg)

Aft Limit at 15,000 lb (6,804 kg) to 21,500 lb (9,752 kg)

Aft Limit at 21,750 lb (9,866 kg)

380 mph

288 mph

230 mph

173 mph

230 mph

299 mph

611 km/hr

463 km/hr

370 km/hr

278 km/hr

370 km/hr

482 km/hr

1.0% MAC

7.0% MAC

12.0% MAC

19.5% MAC

25.0% MAC

28.0% MAC

25.3% MAC

6.0 FUSELAGE GROUP

The fuselage section is of conventional semimonocoque 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, highresolution 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 righthand 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.

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7.0 WING GROUP

The swept, fully cantilevered wing consists of a threespar 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 threespar 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.

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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 enginedriven, 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.

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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 anticollision/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.

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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 liquidcrystal “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, 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.

9

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)

10

A solid-state unit records voice signals transmitted or received in the cockpit for a maximum period of 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 • Dual avionics master switches

• Dual digital clocks mounted in the glareshield

• System test switch panel

• Aural/voice tone warning systems

• Single-point pressure refueling

• Triple heated pitot static probes

• Wing ice detection light

• Engine Sync

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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.

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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 dome lights

• Two life vests • Two speakers

• Fire extinguisher

• Headliner

• Electronically-heated footwarmers

• Rail-mounted sunvisors

• 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

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Plating

• Satin nickel

• Headliner: ultrasuede, vinyl or stretch-knit fabrics

• Sidewall: ultrasuede, vinyl or stretch-knit fabrics

• Cabin armrest (upper): leather or vinyl

Shell

• Cabin armrest (lower): leather, vinyl or selected fabric

• Table insert: high-pressure laminate

• Carpet: selected cut or loop styles

• Interior: high-pressure laminate

• Exterior: high-pressure laminate

Cabinetry

• 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

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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

• 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

• Two engine covers

• Gust locks

• Three jack pads

• Tail stand

• Maintenance interphone

• Standard lock package

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.

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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

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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.

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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 prorata 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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applicable provisions of this Agreement to the same extent as Buyer.

19.0 PATENT AND TRADEMARK PROTECTION

Subject to the provisions set out below, Learjet agrees to indemnify and defend Buyer and save

Buyer harmless against any claim brought against

Buyer that Buyer’s use of the Aircraft constitutes an infringement of any U.S. or Canadian patent or trademark provided that: i) Buyer notifies Learjet in writing of the claim within ten (10) days after Buyer’s receipt of the claim; ii) Upon Learjet’s written request, Buyer immediately gives to Learjet control over the defense and/or settlement of the claim; iii) Buyer fully cooperates with Learjet in such defense and/or settlement; and iv) Buyer does not prejudice Learjet’s conduct of such defense and or settlement.

In no event shall Learjet have any obligation with respect to any liability, loss, damage or expense in respect of, arising out of or resulting from any lack or loss of use of the Aircraft.

The foregoing shall only create an indemnity obligation upon Learjet for claims which are solely and directly based upon the use, sale or offer for sale of the Aircraft. No indemnifying obligation shall arise or exist with respect to claims that are based upon the engines, avionics equipment, or any accessory, equipment or part thereof, or any other accessory, equipment or part which was not manufactured by

Learjet or which was not manufactured exclusively pursuant to Learjet’s detailed design, or which was included in the Aircraft either by Buyer, on behalf of

Buyer or at Buyer’s request, or which was supplied by Buyer or procured or manufactured by Learjet in accordance with Buyer’s specifications, nor shall any obligation arise or exist if the alleged infringement is based upon the use of the Aircraft in a manner prohibited by relevant directives or regulations issued by appropriate government agencies or instrumentalities.

Subject to the foregoing provisions of this Patent and Trademark Protection, Learjet shall pay court costs and its reasonable attorney’s fees for defending such claim, as well as the amount of any settlement deemed advisable by Learjet or any damages that may be awarded against Buyer in respect of such claim. At its own expense,

Learjet may at any time, at its option: i) procure for Buyer the right to continue to use the

Aircraft; or ii) modify the Aircraft, including modifying or replacing any part thereof to render the Aircraft non-infringing.

In the event the use of the Aircraft by Buyer has been enjoined, Buyer shall have the right to require

Learjet to take action in accordance with the foregoing, provided that it shall be Learjet’s sole option as to which alternative action it takes.

Except as expressly provided above, Learjet does not provide any other representation, warranty or protection concerning patents or trademarks with respect to the Aircraft.

20.0 CONSULTANTS

Should Buyer retain the services of a consultant or other third party representative (the "Consultant") in connection with this Agreement, Buyer agrees to have such Consultant sign Learjet’s standard nondisclosure agreement.

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