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AIRCRAFT PURCHASE AGREEMENT

This Aircraft Purchase Agreement (the " Agreement" ) is made by and between BOMBARDIER INC. (" Seller" ) and WILLIAMS-SONOMA, INC. (" Buyer" ) and shall be effective as of the date of its acceptance and execution by Seller.

ARTICLE 1. AIRCRAFT DESCRIPTION

Subject to the provisions of this Agreement, Seller agrees to manufacture, sell and deliver to Buyer, and Buyer agrees to take delivery of, and pay for, one Bombardier Global Express Aircraft Model BD-700-1A10 bearing manufacturers serial number 9120 (the " Aircraft" ) as described in the Specification number BCC-GX-302 dated 20 June 2002 amended 29 April 2003 (the " Completion Work" ), Description and Customer Support Services Manual dated January 2002 which are attached hereto as Schedule " A-1" and Schedule " A, and the Aircraft Flight Manual, Aircraft Maintenance Manual and the applicable Certificate of Airworthiness which are respectively made part of this Agreement by reference (collectively, the " Specification" ).

ARTICLE 2. PRICE, PAYMENT SCHEDULE AND DELIVERY

2.1 In consideration of Seller' s obligations to manufacture, sell and deliver the Aircraft to Buyer, Buyer shall pay to Seller the amount of $ [**] USD (the " Purchase Price" ) as follows: (i) 1st payment due upon Buyer' s execution of this Agreement (including that certain Deposit of $ [**]previously paid by Buyer to Seller on 25 March 2003, the (" Deposit" )): $[**]USD (ii) balance of Purchase Price due at the Delivery Time (as hereinafter defined): $[**]USD

2.2 The Aircraft shall be ready for [**] at Seller' s facility in the city of Dorval, Quebec no later than [**]

ARTICLE 3. COMPLETION WORK

The parties agree that Seller shall complete the Aircraft in accordance with Schedule " A-1" .

ARTICLE 4. GENERAL PROVISIONS

4.1 THE WARRANTY, OBLIGATIONS AND LIABILITIES OF SELLER AND THE RIGHTS AND REMEDIES OF BUYER SET FORTH IN THE SPECIFICATION ARE EXCLUSIVE AND ARE IN LIEU OF AND BUYER HEREBY WAIVES AND RELEASES ALL OTHER WARRANTIES, OBLIGATIONS, REPRESENTATIONS OR LIABILITIES, EXPRESS OR IMPLIED, ARISING BY LAW, IN CONTRACT, CIVIL LIABILITY OR IN TORT, OR OTHERWISE, INCLUDING BUT NOT LIMITED TO A) ANY IMPLIED WARRANTY OF MERCHANTABILITY OR OF FITNESS FOR A PARTICULAR PURPOSE, AND B) ANY OTHER OBLIGATION OR LIABILITY ON THE PART OF SELLER TO ANYONE OF ANY NATURE WHATSOEVER BY REASON OF THE DESIGN, MANUFACTURE, SALE, REPAIR, LEASE OR USE OF THE AIRCRAFT OR RELATED PRODUCTS AND SERVICES DELIVERED OR RENDERED HEREUNDER OR OTHERWISE.

4.2 SELLER SHALL NOT BE LIABLE FOR ANY INDIRECT, CONSEQUENTIAL, SPECIAL, INCIDENTAL AND/OR PUNITIVE DAMAGES OF ANY KIND OR NATURE UNDER ANY CIRCUMSTANCES OR, WITHOUT LIMITING THE FOREGOING, FOR ANY LOST PROFITS OR ANY OTHER LOSSES OR DAMAGES FOR OR ARISING OUT OF ANY LACK OR LOSS OF USE OF ANY AIRCRAFT, ANY EQUIPMENT, ANY ACCESSORY OR ANY SPARE PART FOR ANY REASON.

4.3 THE PARTIES HERETO HEREBY ACKNOWLEDGE AND AGREE THAT THE LIMITED WARRANTIES AND THE LIMITATION OF LIABILITY PROVISIONS CONTAINED HEREIN AND IN THE SPECIFICATION HAVE BEEN EXPRESSLY AGREED TO IN CONSIDERATION OF THE PURCHASE PRICE AND OTHER PROVISIONS OF THIS AGREEMENT FOR THE BENEFIT OF BOTH SELLER AND BOMBARDIER INC. (THE MANUFACTURER OF THE AIRCRAFT) TO HAVE EFFECT AS IF BOMBARDIER INC. WAS A PARTY TO THIS AGREEMENT FOR SUCH PURPOSES. TO THE EXTENT APPLICABLE LAWS DO NOT ALLOW THE LIMITATIONS SET OUT IN THIS ARTICLE 4, SUCH LIMITATIONS SHALL NOT BE APPLIED OR INVOKED.

4.4 This Agreement shall be governed by and interpreted in accordance with the internal laws of the State of New York, excluding any conflicts of law provisions thereof.

4.5 Seller and Buyer acknowledge that the term Agreement as used herein, shall include this Agreement, the Terms and Conditions on the reverse side, the Specification and Addendum. Buyer' s Initials ______ Seller' s Initials _____ BOMBARDIER INC. WILLIAMS-SONOMA, INC. c/o Aero Law Group pllc 400 Cote-Vertu Road West PO Box 50228 Dorval, Quebec H4S 1Y9 Canada Bellevue, WA 98015 Telephone:514-855-5000 Telephone: 415-616-8562 Facsimile: 514-855-7806 Facsimile: 415-616-8359 BY: /s/ GARY L. DOLSKI BY: /s/ W. HOWARD LESTER TITLE: General Manager: Contracts TITLE: Chairman DATE: 30 April 2003 DATE: 4-30-03

[**] Confidential treatment has been requested for the bracketed portions. The confidential redacted portion has been omitted and filed separately with the Securities and Exchange Commission.
WILLIAMS-SONOMA, INC. 1.


TERMS AND CONDITIONS

ARTICLE 5. DELIVERY AND INSPECTION

5.1 Seller shall give Buyer reasonable notice of the date on which the Aircraft will be ready for Buyer' s inspection and acceptance flight test of not more than 10 hours duration. Within 10 days of such date, Buyer agrees to perform such inspection and, if no defect or discrepancy is revealed, Buyer shall accept delivery of the Aircraft before the end of such 10 day period (the time of the acceptance of delivery of the Aircraft being the " Delivery Time" ).

5.2 Any defect or discrepancy revealed by Buyer' s inspection and/or acceptance flight test shall be corrected at no cost to Buyer before or after Delivery Time depending on the nature of the defect or discrepancy and time required for correction. If such correction requires an additional flight test, it shall be conducted in accordance with Article 5.1. Buyer shall accept delivery of the Aircraft within 3 days after any defect or discrepancy has been corrected.

5.3 Buyer shall accept delivery of the Aircraft by signing a receipt for delivery in the form of Schedule " B" , attached hereto. Upon receipt of all payments due at Delivery Time, Seller shall deliver to Buyer a bill of sale and title to the Aircraft shall pass to Buyer free and clear of all rights, prior claims, liens, charges and encumbrances (hereinafter " Liens" ), and risk of damage to or loss of the Aircraft shall pass to Buyer.

ARTICLE 6. PAYMENT AND TAXES

6.1 Seller shall remain exclusive owner of the Aircraft free and clear of all Liens until such time as all payments due for the Purchase Price have been made and Buyer has accepted the Aircraft in accordance with Article 5.

6.2 Buyer shall make all payments due under this Agreement by wire transfer in US dollars and shall pay interest on any late payments at the rate equal to the one year LIBOR rate as published in the " Money Rates" section of The Wall Street Journal commencing on the date the late payment was first due.

6.3 Buyer shall be responsible for the payment of any sales, use, personal property, excise, goods and services, value added, consumption, luxury, withholding or other similar taxes, duties or assessments and any related penalties and interest which may be levied, assessed, or imposed on Buyer or Seller or otherwise by any governmental authority or agency as a result of or in connection with this Agreement.

ARTICLE 7. LOSS OR DESTRUCTION

7.1 If the Aircraft is lost, destroyed or damaged beyond economic repair before Delivery Time, this Agreement shall automatically terminate upon Seller giving written notice of such occurrence to Buyer. Seller' s sole obligation and liability shall then be to promptly return to Buyer all amounts previously paid to Seller under this Agreement.

ARTICLE 8. EXCUSABLE DELAY

8.1 Seller shall not be liable for any failure to deliver or delay in delivery of the Aircraft or delay in performance of any of its other obligations under this Agreement, due directly or indirectly to force majeure, acts of God, violence, fire, explosion, action of the elements or weather conditions, or other catastrophe or accident, any legislation, act, order, directive, or regulation of any government or governmental body, labour trouble, delay or failure of carriers, subcontractors or suppliers, or any other cause beyond Seller' s reasonable control or without Seller' s negligence (" Excusable Delay" ).

8.2 In the event of any Excusable Delay, the time required for the performance of any obligation in this Agreement shall be extended for a period equal to the period during which any such cause and the effects thereof persist. If delivery of the Aircraft is delayed by reason of Excusable Delay for more than 6 months, either Buyer or Seller may terminate this Agreement upon giving written notice to the other party, which notice shall be given within 15 days immediately following such period of 6 months. Upon such termination, Seller' s sole obligation and liability shall be to promptly return to Buyer all amounts previously paid to Seller under this Agreement.

ARTICLE 9. TERMINATION

9.1 Either party may terminate this Agreement before Delivery Time by written notice of termination to the other party upon the occurrence of any of the following events: (i) the other party makes an assignment for the benefit of creditors, or admits in writing its inability to pay its debts; (ii) a receiver or trustee is appointed for the other party or for substantially all of such party' s assets and, if appointed without such party' s consent, such appointment is not discharged or stayed within 30 days; (iii) proceedings under any law relating to bankruptcy, insolvency or the reorganization or relief of debtors are instituted by or against the other party and, if contested by such party, are not dismissed or stayed within 30 days; or (iv) any writ of attachment or execution or any similar process is issued or levied against the other party or any significant part of its property and is not released, stayed, bonded or vacated within 30 days after its issue or levy

9.2 Buyer may terminate this Agreement before Delivery Time if Seller is in default or breach of any material term or condition of this Agreement and does not act to cure such default or breach within 10 days after receipt of written notice from Buyer specifying such default or breach and does not continue thereafter to diligently correct or cure the alleged default or breach.

9.3 Upon termination of this Agreement by Buyer pursuant to and in accordance with this Article 9, all amounts received by Seller on account of the Purchase Price shall promptly be reimbursed to Buyer and such reimbursement shall constitute Buyer' s sole right, remedy and recourse against Seller and Seller' s sole obligation and liability to Buyer.

9.4 Seller may terminate this Agreement before Delivery Time if Buyer does not accept delivery of the Aircraft in accordance with Article 5 or is in default or breach of any material term or condition of this Agreement (except for payment obligations that are covered by Article 9.5) and does not act to cure such default or breach within 10 days after receipt of written notice from Seller specifying such default or breach and does not continue thereafter to diligently correct or cure the alleged default or breach.

9.5 Upon termination of this Agreement by Seller pursuant to and in accordance with this Article 9 or if Buyer fails to make any of the payments provided for in Article 2 on or before the stipulated date, all rights which Buyer may have or may have had in or to this Agreement or the Aircraft shall be extinguished; and Seller shall be entitled to retain an amount equivalent to [**] of the Purchase Price, as liquidated damages for default and the parties shall thereafter be released from all further obligations to each other. Buyer agrees that such liquidated damages do not constitute a penalty and are a reasonable and agreed amount of the anticipated or actual harm or damages to be suffered by Seller as a result of or in connection with Buyer' s default. All other amounts received by Seller on account of the Purchase Price shall be promptly returned to Buyer.

ARTICLE 10. MISCELLANEOUS

10.1 Neither this Agreement nor any of the rights of Buyer hereunder shall be assignable by Buyer. Notwithstanding the foregoing, this Agreement shall be assignable by Buyer in whole or in part to a wholly-owned subsidiary or affiliate of Buyer or any financial institution which is providing financing to Buyer in connection with Buyer' s acquisition of the Aircraft provided that Buyer shall remain jointly and severally liable with the assignee for the fulfilment of all the obligations under this Agreement. Buyer hereby acknowledges that Seller shall have the right, without Buyer' s consent, to create a security interest or hypothec with respect to this Agreement or to assign or transfer this Agreement or any of its rights hereunder to any financial institution or to a wholly owned subsidiary or affiliate of Seller, provided that Seller' s assignment to a financial institution or creation of a security interest or hypothec shall be solely for the purpose of securing financing.

10.2 Any notice to be given hereunder shall be sent by registered or certified mail, courier or facsimile transmission to the party to which said notice is to be given at its address or facsimile number as shown on page 1 hereof unless such address is changed by notice given to the other party in accordance herewith. A notice shall be deemed given when received.

10.3 This Agreement shall inure to the benefit of and be binding upon each of Seller and Buyer and their respective successors and permitted assigns.

10.4 This Agreement and the matters referred to herein constitute the entire Agreement between Seller and Buyer and supersede and cancel all prior representations, alleged warranties, statements, negotiations, drafts, undertakings, letters, acceptances, agreements, understandings, contracts and communications, whether oral or written, with respect to or in connection with the subject matter hereof. This Agreement may only be amended or changed by a written instrument signed by both parties. In the event of any inconsistencies between this Agreement, any addendum, the Specification, the Schedules or other annexes stated to be part of this Agreement, the order of precedence shall be: any addendum, this Agreement, the Specification and other Schedules or annexes.

10.5 If any of the provisions of this Agreement are for any reason declared by judgement of a court of competent jurisdiction to be unenforceable or ineffective, those provisions shall be deemed severable from the other provisions of this Agreement and the remainder of this Agreement shall remain in full force and effect.

ARTICLE 11. CONFIDENTIALITY

11.1 This Agreement is confidential between the parties and shall not, without the prior written consent of the other party, be disclosed by either party in whole or in part to anyone except to assignees or transferees per the provisions of Article 10.1 or as may be necessary for either party to carry out its obligations under this Agreement.

[**] Confidential treatment has been requested for the bracketed portions. The confidential redacted portion has been omitted and filed separately with the Securities and Exchange Commission.
WILLIAMS-SONOMA, INC. 2.


SCHEDULE " A"


GLOBAL EXPRESS AIRCRAFT

DESCRIPTION
&
CUSTOMER SUPPORT SERVICES MANUAL

January 2002 (BAC)


Schedule " A"

1.0 INTRODUCTION

This document describes the Aircraft, including its power plant, systems and equipment.

Also included are descriptions of Seller' s Customer Support services that are provided to the Buyer as part of the sale of the Aircraft, including warranty, technical publications, crew training and the maintenance management system.

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 Seller' 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.

2.0 GENERAL DESCRIPTION Accommodation Crew (minimum) 2 Passengers (typical/maximum) 8/19 Engines Number 2 Make/model BR710A2-20 Thrust 14,750 lb. 65.6 kn Maintenance Program Task oriented Flat rated to ISA +20b0C Auxiliary Power Unit Make/model Honeywell RE220GX Maximum operational altitude 45,000 ft 13,716 m Pressurization Maximum differential 9.64 psi .67 kg/cm2 Emergency relief 9.92 psi .69 kg/cm2 Maximum altitude with sea level cabin pressure 26,500 ft 8,077 m Cabin at 45,000 ft altitude 6,000 ft 1,829 m Dimensions Exterior Length 99.4 ft 30.3 m Height 24.8 ft 7.6 m Wingspan 94.0 ft 28.6 m Wing area (basic, reference area) 1,022 ft2 94.9 m2 Sweep (@ 25% chord line) 35 degrees Wing aspect ratio 8.04 Fuselage maximum diameter 8.8 ft 2.7 m Wheel track 13.33 ft 4.06 m Wheelbase 42.83 ft 13.05 m Minimum pavement width, 180b0 turn 68 ft 20.7 m Hydraulic Systems Number of independent systems 3 Number of independent pumps 7 System pressure 3,000 psi 20.68 MPa Fluid Phosphate ester Type IV low density Electrical Power Systems Number of AC generators 6 Location and capacity L/H engine: 2 @ 40 kVA R/H engine: 2 @ 40 kVA APU: 45 kVA RAT: 9 kVA Transformer rectifier units (4) 150 amp units Fuel Capacity Wing, fuselage and tail tanks 6,422 gal 24,310 l Design limit load factor from 1.0g to +2.5 g Noise (EPNdB) GEX (Part 36, Stage 3) Take-off 82.4 (89) Approach 89.8 (98) Sideline 88.6 (94) Interior Cabin length excluding cockpit 48.35 ft 14.7 m Cabin width centerline 8.17 ft 2.49 m Cabin width floor line 6.92 ft 2.11 m Maximum height 6.25 ft 1.91 m Floor area 335 sq. ft 31.1 m2 Cabin volume excluding cockpit 2,140 cu ft 60.6 m3 Passenger door: height 6.17 ft 1.88 m width 3.0 ft 0.91 m height to sill 5.3 ft 1.63 m Baggage door: height 2.75 ft 0.84 m width 3.58 ft 1.09 m height to sill 6.58 ft 2.01 m Aft storage volume 185 cu ft 5.24 m3 January 2002 (BAC) 1


Schedule " A"

Weights A. Maximum ramp weight * 95,250 lb. 43,205 kg Maximum payload (D-E) 5,700 lb. 2,585 kg B. Maximum gross take-off 95,000 lb. 43,091 kg Payload with maximum fuel 1,600 lb. 726 kg weight * (A-E-F) C. Maximum landing weight 78,600 lb. 35,653 kg Fuel with maximum payload 39,250 lb. 17,804 kg D. Maximum zero fuel 56,000 lb. 25,401 kg (A-D) weight NBAA IFR fuel reserve (8 3,100 lb. 1,406 kg E. Basic operating weight** 50,300 lb. 22,816 kg pax) F. Maximum fuel weight 43,350 lb. 19,663 kg

* Standard Max Gross Take-off Weight of 93,500 lb, (42,411 kg). Also Optional Service Bulletin available increasing Max gross Take-off Weight 96,000 lb, (43,545 kg). ** MWE @ 41,500 lb (18,824 kg) plus operating items @ 1,890 lb (857 kg) plus completion allowance @ 6,910 lb (3,134 kg). January 2002 (BAC) 2


Schedule " A"

3.0 PERFORMANCE Take-off (SL, ISA, Max take-off weight) Take-off distance 5,820 ft 1,774 m Rotation speed Vr 125 kts NBAA, IFR Range Normal cruise speed of 0.85M 6,010 nm b1 1% Landing (SL, Max landing weight) Landing distance 2,670 ft 814 m Approach speed Vref 128 kts Cruise Mmo (above 30,870 ft) M 0.89 513 kts High speed M 0.88 505 kts Normal speed M 0.85 488 kts Long range speed M 0.80 459 kts Maximum certified operating
altitude 51,000 ft 15,545 m Maximum initial cruise altitude
after MTOW departure 43,000 ft 13,106 m

4.0 CERTIFICATION

The Aircraft is certified to chapter 525 change 6 of the Canadian Airworthiness Manuel by Transport Canada (TC), to FAR 256 of the American Federal Aviation Administration (FAA) up to and including Amendment 97 and to the Joint European Type Certification requirements of JAR 25 at Change 14 (as amended by any additional special conditions applied by the certifying authorities). The Aircraft is certified for operations in day and night, under VFR and IFR conditions and is RVSM compliant.

Seller will provide Buyer an FAA Standard Airworthiness Certificate.

5.0 STRUCTURAL DESIGN

The Aircraft is a swept-wing monoplane with a pressurized cabin and is capable of accommodating a pilot, a co-pilot, a third crewmember and up to 19 passengers.

The Aircraft structure, in general, is fabricated from aluminum alloy but also includes alloy steels, stainless steel, titanium and composites. Materials used are in accordance with standard U.S. aerospace industry specifications for aircraft quality materials.

The Aircraft structure and systems are designed and installed to facilitate inspection, maintenance and permit ready removal of appropriate items. Parts and assemblies subject to ready removal from the Aircraft are interchangeable and/or replaceable from one BD-700-1A10 aircraft to another where Seller considers this practical.

The Aircraft and its installed equipment is certified to operate at ground level ambient temperatures from -30baC (-22baF) to +45baC (+113baF). The Aircraft pressurization system is certificated for operations up to a maximum of pressure altitude of 51,000 ft.

6.0 FUSELAGE GROUP

The fuselage consists of nose, center and aft sections joined together. It incorporates attachments for the tail group, engine support structure, pylons and nose landing gear. Except for the nose and aft sections, the fuselage cross-section is a 106-inch diameter circle.

The fuselage is of semi-monocoque construction, utilizing chem-milled alloy skins with aluminum alloy frames and stringers. Areas adjacent to or affected by high heat sources are constructed of fire-resistant or fireproof materials as appropriate.

A radome of composite material and designed for use with a high resolution X band radar is installed on the fuselage nose.

The fuselage is designed for internal pressurization with the pressure-sealed area extending from the bulkhead forward of the flight station in the nose to the bulkhead aft of the cabin. The latter bulkhead forms the aft face of the baggage compartment.

7.0 WING GROUP

The wing is a swept unit mounted at the side of the fuselage and incorporates winglets, ailerons, ground spoilers, multifunction spoilers, inboard, mid and outboard single slotted Fowler flaps, integral fuel tanks, slat support and structures for the main landing gear. Access holes and covers are provided in the wing skin panels to permit access to the entire wing interior.

The wing is a two-piece unit consisting of spars covered top and bottom with stiffened skin panels of aluminum alloy. Shear web type ribs carry the air loads, act as contour support and fuel tank baffles. The tanks are compartmented and mechanically sealed using sealing compounds. The tanks have an overcoat of polyurethane.

Part-span slats mounted on the forward spar together with a fixed leading edge part form the leading edge, excluding the winglets. Thermal anti-icing is provided inside the slats and fixed leading edge.

The wing includes the following control surfaces:

ullet Inboard, mid and outboard fowler flaps, incorporated into the trailing edge. ullet Slats mounted on forward spar from the wing leading edge. Thermal anti-icing is provided inside the slats. ullet Ailerons, constructed of carbon fiber reinforced plastic skins and spar, with full depth honeycomb core, and metallic hinge fittings. They are sealed and are protected against lightning strikes. ullet Six spoilers mounted on hinges attached to the rear and auxiliary spar in the upper surface of each wing. The two inboard spoilers' function as ground spoilers, while the remaining four are multi-function. The spoilers are constructed of carbon fiber reinforced plastic and honeycomb. They are sealed and are protected against lightning strikes January 2002 (BAC) 3


Schedule " A"

8.0 EMPENNAGE GROUP

The empennage is of a " T" configuration, comprising an incidence adjustable horizontal stabilizer with elevators, mounted at the top of a vertical stabilizer and rudder.

The horizontal stabilizer is a one-piece sweptback unit mounted at the top of the vertical stabilizer. It incorporates pivot and actuation mounting fittings to allow incidence adjustments, hinges for elevators and provision for sealing at its interface with the vertical stabilizer.

The fully cantilevered sweptback-type vertical stabilizer is an all-metal construction unit and incorporates the rudder, also an all-metal construction unit. The leading edge incorporates the HF antenna.

9.0 LANDING GEAR

The Aircraft undercarriage is composed of one steerable nose landing gear (NLG) and two trailing-link type main landing gear units (MLG). Each nose and main gear assembly has twin wheels and tires. The main wheels are fitted with hydraulically powered and electrically actuated carbon brakes. Anti-skid protection and automatic braking is also provided.

The landing gear is of the tricycle type. The two MLG assemblies, one located on the inboard portion of each wing, retract inboard each into the MLG bay located in the central fuselage. The NLG assembly is located beneath the cockpit and retracts forward into the nose section of the fuselage. Normal extension and retraction is electrically controlled and hydraulically operated by the cockpit landing gear control handle located in the center console.

Landing gear position and status is visually displayed on EICAS and aurally annunciated in the cockpit. The anti-skid, brake control, nose wheel steering indications and status are also displayed on EICAS and interface with the central maintenance system for failure detection.

The Aircraft has four braked main wheels (two per main gear), and two free rolling nose wheels. The main wheels and nose wheel are fitted with tubeless tires incorporating fusible plugs for over temperature protection and metallic diaphragm plugs for over pressure protection.

Brake temperature is monitored with a system consisting of four sensors each mounted in a brake housing and a brake temperature-monitoring unit. Independent brake temperature is indicated in the cockpit on the EICAS.

The brake/anti-skid control system interfaces with a dual integrated digital electronic controller with autobrake capability. The control unit provides brake control with independent wheel anti-skid protection, locked wheel crossover protection, touchdown protection, gear retract braking and Built-In-Test-Equipment (BITE).

The steering system is comprised of an electronically controlled and hydraulically powered actuation of the nose landing gear steering actuators for taxi, take-off and landing operations. When the steering is not active due to pilot selection or failure conditions, the system continues to provide effective shimmy damping to ensure dynamic stability of the nose wheel.

Steering commands are input to the Electronic Control Unit (ECU) through the pilot' s hand wheel (full authority) and/or rudder pedals (limited authority).

Landing gear retracted, in travel, not safe or down-and-locked as well as gear doors open indication is provided to the crew via the EICAS system. " Gear not down" aural warning is provided.

10.0 POWER PLANT

Two Rolls-Royce Deutschland BR710A2-20/01 bypass turbofan engines power the Aircraft. The engines produce 14,750 lb. of thrust up to 35b0C (ISA+20b0C) at sea level. The engine is assembled from seven sub-assemblies: fan rotor, intermediate fan casing, HP compressor, combustor/HP turbine, LP turbine, exhaust case and accessory gearbox. It has a single stage low-pressure fan driven by a two stage shrouded low-pressure turbine. A ten-stage high-pressure compressor is driven by a two-stage high-pressure turbine. The first four stages of the compressor are equipped with variable-pitch stators controlled by the engine' s Full Authority Digital Engine Control (FADEC). The combustor is an annular conventional flow type designed for low emissions and smoke control. A forced mixer exhaust is integrated with a two-door full flow type thrust reverser. The hydraulically operated thrust reverser system, with weight on wheels or wheel spin-up available, will deploy when the th
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