Document:

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               GUARANTEED MINIMUM WITHDRAWAL BENEFIT ENDORSEMENT

Notwithstanding any provision in the Contract or Certificate ("Contract") to the
contrary, this Endorsement becomes a part of the Contract to which it is
attached. Should any provision in this Endorsement conflict with the Contract,
the provisions of this Endorsement will prevail.

Subject to the terms and conditions set forth herein, this optional Endorsement
provides a Guaranteed Minimum Withdrawal Benefit that guarantees an amount
available for Withdrawal not to exceed a maximum annual dollar amount to be
distributed over a specified number of years, even if the Contract Value has
been reduced to zero due to unfavorable investment performance ("GMWB"). This
GMWB may be purchased [on the date the Contract is issued], provided that all
Owner(s) are age [80] or younger on the date of election of the GMWB.

EFFECTIVE DATE:  [DATE]

BENEFIT AVAILABILITY DATE:  [DATE]

                                   DEFINITIONS

Terms not defined in this Endorsement shall have the same meaning given to them
in the Contract.

BENEFIT AVAILABILITY DATE

The date shown above which is the earliest date on which You can begin to take
Withdrawals pursuant to the terms of this Endorsement.

BENEFIT YEAR

Each consecutive one year period beginning on the Benefit Availability Date.

EFFECTIVE DATE

The date shown above when this Endorsement becomes effective. If this
Endorsement is elected at Contract issue, the Effective Date is the date Your
Contract is issued. [If this Endorsement is elected after Your Contract has been
issued, the Effective Date is the [Contract Anniversary following] Your
election.]

ELIGIBLE PURCHASE PAYMENTS

The Purchase Payments or portion thereof that are used in the calculation of the
Withdrawal Benefit Base ("WBB").

MAXIMUM ANNUAL WITHDRAWAL AMOUNT ("MAWA")

The maximum amount available for withdrawal, each Benefit Year, under the GMWB.

MINIMUM WITHDRAWAL PERIOD ("MWP")

The minimum period of time over which You may take Withdrawals under the GMWB.

SPOUSAL BENEFICIARY

Your spouse, if designated as Your primary Beneficiary on the date of Your
death, who elects to continue the Contract as the new Owner or Participant
("Owner") upon Your death.

STEPPED-UP BENEFIT BASE ("SBB")

A component of the calculation of the GMWB, which is used to determine the total
amount of the guaranteed Withdrawals under the GMWB and the minimum time period
over which You may take Withdrawals under the GMWB.

STEP-UP

A percentage of the Withdrawal Benefit Base ("WBB"), which when added to the WBB
results in the SBB.

WITHDRAWAL

The amount of any full or partial surrender of Contract Value and any fees or
charges attributable to the surrendered amount.

WITHDRAWAL BENEFIT BASE ("WBB")

A component of the calculation of the GMWB, which is used to determine the
amount of guaranteed Withdrawals and the initial maximum amount available for
withdrawal annually, under the GMWB.

                                       1
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WITHDRAWAL PERIOD

The period of time during which You are taking withdrawals under the GMWB, which
begins on the Benefit Availability Date and ends upon the earlier of a
termination of the Endorsement or You when the SBB is reduced to zero. This
period may not be shorter than the MWP but may be longer than the MWP.

                GUARANTEED MINIMUM WITHDRAWAL BENEFIT PROVISIONS

This Endorsement provides a GMWB subject to the terms and conditions described
herein.

GMWB CHARGE

The charge deducted from Your Contract Value on a [quarterly] basis beginning
one [quarter] following the Effective Date and ending upon the earliest of (a) a
termination of the Endorsement; or, (b) reduction of the SBB to zero; or (c) the
time at which the Contract Value is reduced to zero. [The full [quarterly]
charge will also be deducted upon full surrender or annuitization of Your
Contract.]

The amount of the charge will equal:

<TABLE>
<CAPTION>
-------------------------------------------------------------------------------------------------
                   TIME PERIOD                      ANNUALIZED GMWB CHARGE     AS A PERCENTAGE OF
-------------------------------------------------------------------------------------------------
<S>                                                 <C>                        <C>
     [Prior to the Benefit Availability Date]               [0.60%]                   [WBB]
-------------------------------------------------------------------------------------------------
   [During the Withdrawal Period [Years 0-30]]              [0.60%]                   [WBB]
-------------------------------------------------------------------------------------------------
   [During the Withdrawal Period [Years 0-30]]              [0.45%]                   [WBB]
-------------------------------------------------------------------------------------------------
</TABLE>

The GMWB Charge is calculated as [one-fourth] of the annualized GMWB Charge,
which is deducted [quarterly] as a percentage of the [WBB], as described above.

CALCULATION OF THE COMPONENTS OF THE GMWB

The GMWB is not available for withdrawal until the Benefit Availability Date and
must be withdrawn at least over the MWP. If You need to take Withdrawals or are
required to take minimum required distributions ("MRD") under the IRC from this
Contract, prior to the Benefit Availability Date, You should know that
Withdrawals taken before the Benefit Availability Date will negatively impact
the value of the GMWB. The amount of and time period over which You can take
Withdrawals under the GMWB may change over time as a result of withdrawal
activity within the Contract. Withdrawals made pursuant to this Endorsement are
treated like any other withdrawal under the Contract for purposes of calculating
Contract Value, Withdrawal Charges, and any other benefits under the Contract.
Withdrawals in excess of the Penalty Free Withdrawal amount will be assessed a
Withdrawal Charge, if applicable. We reserve the right to limit the investment
options available under Your Contract if You elect the GMWB.

To determine the GMWB, We calculate each of the following components: WBB, SBB,
MAWA and MWP. The calculations for each component are detailed below.

WITHDRAWAL BENEFIT BASE ("WBB")

The initial WBB is equal to (a) if the GMWB is elected on the Contract Date or
(b) if the GMWB is elected after the Contract Date minus (c) where:

      (a)   is the Eligible Purchase Payments received on the Effective Date and
            any subsequent Eligible Purchase Payments multiplied by the
            percentage as specified in the table below; and

      (b)   is the Contract Value on the Effective Date and any subsequent
            Eligible Purchase Payments multiplied by the percentage as specified
            in the table below; and

      (c)   is a proportionate adjustment for each partial Withdrawal taken
            subsequent to the Effective Date but prior to the Benefit
            Availability Date. A proportionate adjustment is an amount equal to
            the WBB immediately prior to a Withdrawal multiplied by the
            percentage by which the Contract Value is reduced at the time of
            that Withdrawal.

                                       2
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The table below identifies the Eligible Purchase Payments used to calculate the
initial WBB, as determined by the time elapsed between the Effective Date and
the day on which [Gross] Purchase Payments are received by Us and deposited into
Your Contract. Payment Enhancements are not considered Purchase Payments and
therefore are not included in the Eligible Premiums.

<TABLE>
<CAPTION>
----------------------------------------------------------------------------------------------
        TIME ELAPSED SINCE EFFECTIVE DATE          PERCENTAGE INCLUDED IN THE WBB CALCULATION
----------------------------------------------------------------------------------------------
<S>                                                <C>
                  [0-[90] Days]                                      [100%]
               [91 Days to 1 Year]                                   [80%]
                [More than 1 Year]                                    [0%]
----------------------------------------------------------------------------------------------
</TABLE>

The amount of the WBB will change over time due to withdrawal activity within
the Contract. Withdrawals in excess of MAWA may reduce the WBB by more than the
amount of the Withdrawal. See IMPACT OF WITHDRAWALS below. The WBB is not used
in the calculation of Contract Value or any other benefits under this Contract.
We reserve the right to limit the WBB to a maximum of [$1,000,000].

STEPPED-UP BENEFIT BASE ("SBB")

The Step-Up amount is added to the WBB to arrive at the SBB, which is used to
determine the maximum amount available for Withdrawal under the GMWB and the
minimum time period over which You may take Withdrawals under the GMWB. The
Step-Up is [20%] of the WBB on the Benefit Availability Date. The Step-Up amount
is only available to You by taking Withdrawals under the GMWB.

The amount of the SBB will change over time due to withdrawal activity within
the Contract. Withdrawals in excess of MAWA may reduce the SBB by more than the
amount of the Withdrawal. See IMPACT OF WITHDRAWALS below. The SBB is not used
in the calculation of Contract Value or any other benefits under this Contract.

MAXIMUM ANNUAL WITHDRAWAL AMOUNT ("MAWA")

The MAWA is an amount calculated as a percentage of the [WBB]. The applicable
percentage for the initial MAWA will equal:

<TABLE>
<CAPTION>
------------------------------------------------------------------------------------------
  TIME ELAPSED SINCE THE EFFECTIVE DATE           PERCENTAGE       MAWA AS A PERCENTAGE OF
------------------------------------------------------------------------------------------
<S>                                               <C>              <C>
               [0-3 years]                           [0%]*                  [WBB]
------------------------------------------------------------------------------------------
                [3+ years]                           [8%]                   [WBB]
------------------------------------------------------------------------------------------
               [0-30 years]                          [0%]                   [WBB]
------------------------------------------------------------------------------------------
</TABLE>

* There is a [3] year waiting period prior to the Benefit Availability Date.

 If You are taking minimum required distributions ("MRD") from the Contract, the
MAWA is the greater of the MAWA as described above or the annual MRD amount.

The MAWA can be withdrawn periodically throughout each Benefit Year during the
Withdrawal Period. If You do not withdraw the entire MAWA in a Benefit Year, the
amount not withdrawn will extend Your MWP, but cannot be used to increase future
MAWA. Withdrawals in excess of the MAWA in any Benefit Year will reduce Your
future MAWA. See IMPACT OF WITHDRAWALS section below.

MINIMUM WITHDRAWAL PERIOD ("MWP")

      (a)   The MWP is the minimum period of time during which You may take
            Withdrawals under the GMWB. The initial MWP equals the SBB divided
            by the initial MAWA.

We calculate a new MWP after each Withdrawal during the Withdrawal Period.
Withdrawals in excess of the MAWA will reduce the MWP. See IMPACT OF WITHDRAWALS
section below.

                                       3
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IMPACT OF WITHDRAWALS

Withdrawals under this Endorsement reduce the Contract Value and the amount
available for Withdrawal under the GMWB. Withdrawals equal to or less than the
MAWA generally reduce these values by the amount of the Withdrawal. Withdrawals
in excess of the MAWA may deplete these values based on the relative size of the
Withdrawal in relation to the Contract Value at the time of the Withdrawal. This
means that when investment performance is down, Withdrawals greater than the
MAWA will result in a greater depletion of these values. We further explain this
impact and the effect on each component of the GMWB through the mathematical
calculations below:

WITHDRAWALS IMPACT CONTRACT VALUE AND THE COMPONENTS OF THE GMWB CALCULATION AS
FOLLOWS:

      1.    CONTRACT VALUE: Any Withdrawal reduces the Contract Value by the
            amount of the Withdrawal.

      2.    WBB: Withdrawals prior to the Benefit Availability Date reduce the
            WBB proportionately in an amount equal to the WBB immediately prior
            to a Withdrawal multiplied by the percentage by which the Contract
            Value is reduced at the time of that Withdrawal.

            Withdrawals during the Withdrawal Period will not reduce the WBB
            until the sum of Withdrawals exceeds the Step-Up amount. Any
            Withdrawal or portion thereof that causes total Withdrawals during
            the Withdrawal Period to exceed the Step-Up amount, but is less than
            or equal to the MAWA, will reduce the WBB by the amount of the
            Withdrawal. Any such Withdrawal in excess of the MAWA reduces the
            WBB to the lesser of (a) or (b), where:

                a.      is the WBB immediately prior to the Withdrawal minus the
                        amount of the Withdrawal, or;

                b.      is the WBB immediately prior to the Withdrawal minus the
                        amount of the Withdrawal that is equal to the current
                        MAWA, and further reduced proportionately by the same
                        amount by which the Contract Value is reduced by the
                        amount in excess of the MAWA.

      3.    SBB: Since Withdrawals prior to the Benefit Availability Date reduce
            the WBB proportionately, the SBB will likewise be reduced
            proportionately during that period of time.

            During the Withdrawal Period, any Withdrawal in a Benefit Year,
            which does not cause total Withdrawals in that Benefit Year to
            exceed the MAWA, reduces the SBB by the amount of the Withdrawal.
            During the Withdrawal Period, any Withdrawal in a Benefit Year which
            causes total Withdrawals in that Benefit Year to exceed the MAWA,
            reduces the SBB to the lesser of (a) or (b) where:

                a.      is the SBB immediately prior to the Withdrawal minus the
                        amount of the Withdrawal, or;

                b.      is the SBB immediately prior to the Withdrawal minus the
                        portion of any Withdrawal which does not cause total
                        Withdrawals in that Benefit Year to exceed the current
                        MAWA and further reduced proportionately by the same
                        amount by which the Contract Value is reduced by the
                        Withdrawal amount in excess of the MAWA.

      4.    MWP: After each Withdrawal a new MWP is calculated. For Withdrawals
            in a Benefit Year that are less than or equal to MAWA the new MWP
            equals the SBB after the Withdrawal divided by the current MAWA.

            After any Withdrawal that causes the sum of Withdrawals in a Benefit
            Year to exceed the MAWA, the new MWP equals the MWP calculated at
            the end of the prior Benefit Year reduced by one year.

      5.    MAWA: If the sum of Withdrawals in a Benefit Year does not exceed
            the MAWA for that Benefit Year, the MAWA does not change for the
            next Benefit Year. If total Withdrawals in a Benefit Year exceed the
            MAWA, the MAWA will be recalculated at the start of the next Benefit
            Year.

            The new MAWA will equal the SBB on that Benefit Year anniversary
            divided by the MWP on that Benefit Year Anniversary

            The new MAWA may be lower than Your previously calculated MAWA.

IF YOUR CONTRACT VALUE IS REDUCED TO ZERO

If Your Contract Value is reduced to zero and the SBB has not been reduced to
zero, subsequent Purchase Payments will no longer be accepted and a Death
Benefit will not be payable upon the death of the Owner. You can receive the
remaining value of the GMWB under one of the following options:

                                       4
<PAGE>
                a.      A lump sum equal to the discounted present value of any
                        remaining guaranteed payments under the GMWB; or,

                b.      Periodic payments during each Benefit Year that in total
                        are equal to the MAWA until the SBB has been reduced to
                        zero. If You do not select a specific frequency for
                        these payments, We will pay the current MAWA in
                        [quarterly] payments; or,

                c.      Any payment option that is mutually agreeable.

TERMINATION OF THE GMWB

Once elected the GMWB Endorsement and its corresponding charge [cannot] be
terminated by the Owner. [If terminated by the Owner, the cancellation is
effective [on the Contract Anniversary following the election to terminate].]
The Endorsement and the related charge will terminate automatically if:

                1.      Withdrawals that exceed the MAWA in a Benefit Year
                        reduce the SBB by [50%] or more; or,

                2.      The SBB has been reduced to zero; or,

                3.      A Spousal Beneficiary elects to continue the Contract
                        without this Endorsement; or,

                4.      A Death Benefit is paid (as described under the [Death
                        Provisions or Death Benefit] section of Your Contract);
                        or,

                5.      The Contract is fully withdrawn or surrendered; or,

                6.      The Contract is annuitized.

SPOUSAL CONTINUATION

Upon election to continue the Contract and this Endorsement, Your Spousal
Beneficiary will be subject to the terms and conditions described herein with
respect to the GMWB. The Effective Date and Benefit Availability Date will not
change as a result of Spousal Continuation. A Continuation Contribution paid
under the Spousal Continuation provision of this Contract is not considered an
Eligible Purchase Payment for purposes of this Endorsement.

Signed for the Company to be effective on the Effective Date.

AIG SUNAMERICA LIFE ASSURANCE COMPANY

/s/ CHRISTINE A. NIXON                  /s/ JANA W. GREER
-----------------------------------     ----------------------------------------
      Christine A. Nixon                             Jana W. Greer
           Secretary                                   President

                                       5exv10w40

 

	 	 	 
	 

	 	EXHIBIT 10.40

AIRCRAFT PURCHASE AGREEMENT

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

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
	 

	 	PO Box 50228
	400 Cote-Vertu Road West

	 	Bellevue, WA 98015
	Dorval, Quebec H4S 1Y9 Canada

	 	 
	Telephone:514-855-5000

	 	Telephone:
	Facsimile: 514-855-7806

	 	Facsimile:

	 	 	 	 	 	 	 
	BY:

	 	/s/ GARY L. DOLSKI
	 	BY:
	 	/s/ HOWARD LESTER
	

	 	
 
	 	 	 	
 
	TITLE:

	 	General Manager: Contracts
	 	TITLE:
	 	Chairman
	DATE:

	 	4-30-03
	 	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.

 

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.

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

I. AMEND THE PURCHASE AGREEMENT AS FOLLOWS:

ARTICLE 1. AIRCRAFT DESCRIPTION

	 	 	In the second line following "described in" insert "this
Agreement, the addendum,".

ARTICLE 2. PRICE, PAYMENT SCHEDULE AND DELIVERY

	2.3	 	[**]

ARTICLE 4. GENERAL PROVISIONS

	4.1	 	In the first line following “IN” insert “THIS AGREEMENT AND”.
	 
	4.1	 	In the second line after “SPECIFICATION” insert “AND THE WARRANTY OF
TITLE INCLUDING ANY WARRANTY OF TITLE INCLUDED IN ANY BILL OF SALE ISSUED
BY THE SELLER”.
	 
	4.1	 	Insert the following at the end of this Article [**]
	 
	4.2	 	In the first line replace [**]
	 
	4.2	 	In the fourth line insert “OR THE TERMINATION OF THIS AGREEMENT” before the period.
	 
	4.2	 	At the end of this Article add the following: [**]
	 

ARTICLE 5. DELIVERY AND INSPECTION

	5.1	 	In the first line replace “reasonable” with “30 days prior”.
	 
	5.1	 	In the third line replace 10 hours duration” with “15 hours duration,
including a “cold soak” flight of at least 10 hours in duration to verify
the operational status of the Aircraft in cold soak conditions and
provided, however, that Buyer may extend the test flight of the Aircraft
if Buyer, in good faith, believes that such extension is necessary to
confirm that there is no defect in the Aircraft.”
	 
	5.1	 	Insert the following sentence at the end of the section: “All flights
prior to Delivery Time (including any flight to the delivery location)
shall be at Seller’s expense”.
	 
	5.2	 	In the second line, after the words “flight test” insert the words
“(including those described in Schedule D hereto which have been
identified by Buyer at the execution of this Agreement)”
	 
	5.2	 	In the second line following “before” insert “Delivery Time or, subject to the parties mutual 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.
	1/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	5.2	 	In the second line delete “or”
	 
	5.2	 	In the sixth line, replace “3 days after any” with “3 business days after all”.
	 
	5.2	 	In the sixth line following “corrected,” insert “unless otherwise mutually agreed”.
	 
	5.3	 	In the first line after “Aircraft” insert “when tendered in accordance
with this Agreement and following satisfactory completion of the
inspection in accordance with Article 5.1 and 5.2 of this Agreement”.
	 
	5.3	 	In the third line replace “bill of sale” with “FAA Bill of Sale and shall
deliver to Buyer at the delivery location a warranty bill of sale in the
form of Schedule “C””.

ARTICLE 6. PAYMENT AND TAXES

	6.2	 	In the third line replace “LIBOR” with “Prime”.
	 
	6.2	 	In the fourth line following “Journal” insert “(“Interest”)”.
	 
	6.3	 	Delete Article 6.3 in its entirety and replace with the following “Buyer
shall pay to and indemnify Seller for, and hold Seller harmless from and
against, all franchise, gross receipts, sales, use, excise, personal
property, ad valorem, value added, stamp, landing, airport use or other
taxes, levies, imposts, duties, charges, fees, asset tax or withholdings
of any nature, together with any penalties, fines or interest thereon
(except to the extent such penalties and interest arise from Seller’s
failure to timely notify Buyer (collectively “Taxes”) arising out of the
transactions contemplated by this Agreement and imposed against the
Seller, the Buyer or the Aircraft, or any part thereof, by any federal or
foreign government, any state, municipal or local subdivision, any agency
or instrumentality thereof or other taxing authority, or upon the
ownership, delivery, possession, or transfer thereof, or upon or with
respect to this Agreement.
	 
	 	 	Notwithstanding the foregoing, Buyer shall not be responsible for any
Taxes assessed on the sale to or importation by Seller of materials or
equipment for incorporation into the Aircraft (including without
limitation brokerage fees and customs processing fees) and any personal
property taxes assessed against the Aircraft or any part thereof on or
prior to Delivery Time with respect to periods on or prior to such date,
for which Taxes Seller shall be solely responsible. For the avoidance of
doubt, Seller shall also be responsible for any taxes imposed on or
measured by its net income resulting from the sale of the Aircraft.
Seller represents that according to current Canadian law, there are no
Canadian (whether federal, provincial or local) taxes, assessments or
duties payable with respect to the Aircraft or any part or component
thereof that Buyer would be obligated to pay pursuant to this Article 6.

ARTICLE 7. LOSS OR DESTRUCTION

	7.1	 	Replace the current 7.1 with the following: “If before Delivery Time the
Aircraft to be manufactured, sold and delivered hereunder is lost or
destroyed, damaged beyond repair, suffers material damage, the repair of
which requires issuance of an FAA Form 337 or would result in operational
limitations or changes to the inspection or maintenance program, Buyer’s
sole right and remedy at its own discretion shall be to either a) accept
delivery of the next available aircraft meeting the requirements of this
Agreement (“Replacement Aircraft”) under the same terms and conditions
specified in this Agreement, or b) to terminate this Agreement. Buyer
shall notify Seller of its decision within 10 days after receipt by Buyer
of written notice from Seller of the loss or destruction of or material
damage to such Aircraft and all relevant information concerning the
Replacement Aircraft and its sale to Buyer reasonably required by Buyer to
make its decision. Should Buyer elect to terminate this Agreement,
Seller’s sole obligation and liability shall be to return to Buyer all
payments made in accordance with

	 	 	 
	 	[**] 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.
	2/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	 	 	this Agreement with Interest on all such
payments from the dates of each such payments to the date on which Seller
returns such payments with such Interest. If Buyer shall not elect to
terminate this Agreement, the price of the replacement aircraft shall be
(i) the Purchase Price, to the extent there are available aircraft of the
same configuration and specification as the Aircraft or (ii) the Purchase
Price plus the cost of any material enhancements or modifications
incorporated in the replacement aircraft that were not incorporated (or
required by this Agreement to be incorporated) in the Aircraft.
	 
	 	 	Notwithstanding the foregoing, in the event that before Delivery Time the
Aircraft suffers material damage, the repair of which requires issuance
of an FAA Form 337 or would result in material operational limitations or
material changes to the inspection or maintenance program and the
Aircraft is not otherwise lost, destroyed or damaged beyond repair, then,
in lieu of Buyer’s option to terminate this Agreement or purchase another
aircraft as set forth in the paragraph immediate above, Buyer may in its
sole discretion elect to accept delivery of the Aircraft in which case
Buyer’s sole right and remedy shall be that the Purchase Price shall be
reduced by the amount of the reduction in the value of the Aircraft on
account of such damage. For this purpose, the reduction in the value of
the Aircraft shall be the average of the reduction in the values of the
Aircraft as reflected in an appraisal obtained by each of Buyer and
Seller from independent appraisers, unless the lower of such values is
less than 95% of the higher of such values, in which case, the two
appraisers shall jointly appoint a third appraiser and the average of the
two closest appraisals shall be used.

ARTICLE 8. EXCUSABLE DELAY

	8.1	 	In the third line replace “directly or indirectly to” with “to causes beyond its reasonable control which may include events of”.
	 
	 	 	In the sixth line following “labour trouble,” [**]
	 
	8.2	 	Delete entire Article and replace with the following:
	 
	 	 	[**]

ARTICLE 9. TERMINATION

	9.1	 	In the fourth line following “creditors,” insert [**]
	 
	9.1	 	In the ninth line after “the other party” insert [**]
	 
	9.1	 	In the thirteenth line following “issue or levy” insert [**]
	 
	9.1	 	At the end of this Article insert the following “For the purposes of this
Article 9.1, the above terminating events affecting Seller, the term
Seller shall refer either to Bombardier Inc. or its subsidiary, Bombardier
Aerospace Corporation.”
	 
	9.2	 	In the second line following “not” delete [**]
	 
	9.2	 	In the fifth line following “default or breach” delete [**]
	 
	9.3	 	In the third line following “Purchase Price” add “plus Interest from the date such payment was made”.
	 
	9.3	 	Article 9.3, line 3, add after “Buyer” [**]

	 	 	 
	 	[**] 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.
	3/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	9.4	 	In the second line following “Article 5” add “when tendered in accordance with this Agreement”.
	 
	9.4	 	In the fourth line following “not” delete “act to”.
	 
	9.4	 	In the sixth line following “default or breach” delete the remainder of the sentence.
	 
	9.5	 	In the third line following “stipulated date” insert “and Buyer fails to
cure such payment default or breach within 5 business days after receipt
of written notice by Seller”.
	 
	9.5	 	In the fifth and sixth line delete [**] and replace with [**]
	 
	9.5	 	[**]

ARTICLE.10 MISCELLANEOUS

	10.1	 	In the fifth line following “Aircraft” insert “or to a qualified
intermediary for the purpose of effecting a like-kind exchange”.
	 
	10.1	 	Insert “and provided Seller shall remain the sole party responsible to
Buyer for all of Seller’s obligations hereunder” before the last period.
	 
	10.1	 	In the eight line following “Agreement”, insert the following: “Buyer
will not be held jointly and severally liable if Seller provides its
consent to assignment (which shall not be unreasonably withheld) to any
wholly owned subsidiary provided that Buyer demonstrates to Seller’s
satisfaction that the Assignee is able to meet the financial obligations
of this Agreement.”
	 
	10.1	 	In the tenth line following “financial institution or” insert “immediately
prior to Delivery Time”.
	 
	10.1	 	At the end of this Article following “of securing financing” insert “and
upon assignment to a wholly owned subsidiary of Seller, Seller
(Bombardier, Inc.) shall remain jointly and severally obligated to perform
all obligations of Seller including those that survive Delivery Time
(including without limitation the warranty provisions included in Section
15 of Schedule A hereto) and shall provide a warranty of title described
in Schedule C hereto.”
	 
	10.2	 	On the third and fourth line delete “or facsimile number as shown on page
1 hereof unless such address is changed by notice given to the other party
in accordance herewith” and replace with the following: “as follows
Williams-Sonoma, Inc. c/o Aero Law Group pllc 11120 NE 2nd Street, Suite
210, Bellevue Washington, 98004 or to the facsimile as shown on page 1.”
	 
	10.4	 	In the first line after “Agreement” insert “(including the Specification,
Addendum, Schedules and Exhibits)”. For avoidance of doubt, in the event of any
discrepancy in the Specification (not including the Completion Work), the
order of precedence shall be the Aircraft Flight Manual, Maintenance
Manual and Schedule A.
	 
	10.6	 	Insert the following:
	 
	 	 	Like-kind Exchange. Buyer may structure the transaction herein
contemplated as the receipt of replacement property pursuant to a
like-kind exchange under the provisions of Section 1031 of the Internal
Revenue Code of 1986, as amended and the Treasury Regulations issued
pursuant thereto. Seller agrees to cooperate to structure the
transaction in such manner, including, without limitation, the execution
of any documents, including an amendment to this Agreement or an
assignment of this Agreement to a qualified intermediary or exchange
accommodation titleholder. Buyer may assign its rights to this Agreement
pursuant to an “Assignment of Rights Under Contract” to be executed by

	 	 	 
	 	[**] 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.
	4/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	 	 	Buyer (as “Exchangor” thereunder) and Seller prior to receipt of any FAA
Bill of Sale or Warranty Bill of Sale transferring legal title to the
Aircraft. The provisions of such Assignment may include the substitution
of the word “Exchangor” for the word “Buyer” under this Agreement.

ARTICLE 11. CONFIDENTIALITY

Delete Article 11 and replace with the following:

	11.1	 	Seller and Buyer hereby agree to keep this Agreement and its contents
confidential and each party hereto agrees that it shall not disclose, or
permit to be disclosed, the same to any person or entity, except:

	(a)	 	to permitted assignees or transferees of a party per the
provisions of Article 10.1 or to such party’s or their permitted
assignee’s or transferee’s counsel, accountants, auditors and Boston
Jetsearch, Inc., on a “need to know” basis, all of whom shall have
agreed to keep the same confidential;
	 
	(b)	 	as may be required by statute, court, subpoena or
administrative order or decree or governmental ruling or regulation
of the United States or Canada or other applicable jurisdiction on
the condition that prompt notice of the requirement for such
disclosure is given to the other party to allow such party to resist
such disclosure or seek confidential treatment;
	 
	(c)	 	to the extent that such information is published, is publicly
available or is in the public domain, through no fault of the
disclosing party; or
	 
	(d)	 	as may be necessary for Seller or Buyer to carry out their
obligations under the Agreement.

	11.2	 	Seller shall ensure that no photographs, videos or any other type of
visual replication of the Aircraft or any materials as installed, or to be
installed, in or on the Aircraft, is taken by Seller or its employees and
shall use commercially reasonable efforts to ensure that no such no
photographs, videos or any other type of visual replication are taken by
anyone other than by Buyer or its representatives, or displayed or used by
Seller for any purpose at any time or under any circumstances without
Buyer’s prior written consent, except for photographs, videos or such
other replications which include the exterior of the Aircraft, without
identifying (or allowing third parties to identify) the Aircraft as
belonging to Buyer or as required to allow Seller to perform its
obligations under this Agreement.
	 
	11.3	 	Seller shall ensure that the Aircraft and the materials installed therein
are not at any time or under any circumstances used by Seller or anyone
subject to its control for or in connection with any promotional,
publicity, media or other type of marketing or advertising work except for
promotional, publicity, media or other type of marketing or advertising
work other than as would be allowed under Article 11.2.
	 
	11.4	 	Only authorized employees or representatives of Seller or employees or
representatives of Buyer including Consultants (as defined in Article 17
of Schedule A) will be permitted access to the Aircraft. Visitors other
than those who need access to the Aircraft in order to allow Seller or
Buyer to perform their obligations hereunder shall not be permitted to
view or tour the Aircraft interior without prior consent of the Buyer or
its Consultant. In the event authorization is granted, visitors will be
accompanied at all times by a Seller representative.

	 	 	 
	 	[**] 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.
	5/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	II.	 	INSERT THE FOLLOWING NEW ARTICLES INTO THE PURCHASE AGREEMENT

ARTICLE 12. INTENTIONALLY LEFT BLANK

ARTICLE 13. SELLER’s REPRESENTATIONS AND WARRANTIES

Seller represents and warrants as follows:

	13.1	 	[**]
	 
	13.2	 	[**]
	 
	13.3	 	[**]
	 
	13.4	 	[**]
	 
	13.5	 	[**]
	 
	13.6	 	[**]
	 
	13.7	 	[**]
	 
	13.8	 	[**]
	 
	13.9	 	[**]
	 
	13.10	 	[**]
	 
	13.11	 	[**]
	 
	13.12	 	[**]
	 
	13.13	 	[**]
	 
	13.14	 	[**]
	 
	13.15	 	[**]
	 
	13.16	 	[**]
	 
	13.17	 	[**]
	 
	13.18	 	[**]
	 
	13.19	 	[**]

	 	 	 
	 	[**] 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.
	6/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	ARTICLE 14. 	 	[**]
	 
	ARTICLE 15. 	 	[**]
	 
	15.1	 	[**]
	 
	ARTICLE 16. 	 	[**]

	III.	 	AMEND SCHEDULE A TO THE AIRCRAFT PURCHASE AGREEMENT AS FOLLOWS:

	 	 	For avoidance of doubt, unless otherwise noted the definitions contained
herein shall have the same meaning as those set forth in the Agreement.
	 
	1.0	 	INTRODUCTION
	 
	 	 	In the third paragraph at the end of the first sentence before the period
insert “arising after the date hereof (“Governmental Requirements”)”.
	 
	 	 	In the fifth line of the third paragraph replace “changes” with
“Governmental Requirements”.
	 
	 	 	In the tenth line of the third paragraph replace “changes” with
“Governmental Requirements”.
	 
	 	 	In the eighth and ninth line of the third paragraph replace [**]
	 
	2.0	 	GENERAL DESCRIPTION
	 
	 	 	Under the definition of “Engines – Make/Model” delete “Make”.
	 
	4.0	 	CERTIFICATION
	 
	 	 	In the third line delete “256” and replace with “25” and delete
“American” and replace with “United States”.

	•	 	At the end of the first paragraph, before the period, insert
“, and approved for operations to Category II minima”.
	 
	•	 	At the end of the second paragraph, before the period, insert “, with no restrictions or limitations”.
	 
	•	 	Insert the following at the end of section 4.0
	 
	 	 	“Seller shall maintain a reasonable stock
of suitable and interchangeable spare parts for the Aircraft for
routine repairs and replacements for a period of 10 years after
the date that Seller delivers its last production model of the
Bombardier Global Express BD-700-1A10 aircraft.”

	13.0	 	INSTRUMENTATION AND AVIONICS
	 
	 	 	In the “Communications” section, in the second line of the first bullet after the word “RTUs” add [**]

	 	 	 
	 	[**] 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.
	7/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	14.0	 	CUSTOMER SUPPORT SERVICES
	 
	 	 	Inspection and Acceptance Procedures
	 
	 	 	Delete the first sentence.
	 
	 	 	In the fifth line replace “inspection and acceptance” with “inspections
and acceptances”.
	 
	 	 	Flight Operations Support
	 
	 	 	In the first line of clause ii), replace “days from” with “consecutive
days following”.
	 
	 	 	Training
	 
	 	 	In the last sentence replace “1 year” with “2 years”
	 
	 	 	In clause ii), a “.” shall be added at the end of the sentence.
	 
	 	 	In the second line of the second paragraph replace the word “on” with the
word “of”.
	 
	 	 	Technical Data and Services
	 
	 	 	At the end of the Manual Description, in the first line, delete
“delivered” and replace with “available”.
	 
	 	 	At the end of the Manual Description, in the second line, delete
“delivered in hard copy” and replace with “available in hard copy. Buyer
shall be provided with such manuals in any available media as requested
by Buyer.”.
	 
	 	 	Computer Integrated Maintenance Management System (CIMMS)
	 
	 	 	In the fourth and fifth lines delete “the induction of the Aircraft at
the Completion Center” and replace with “Delivery Time”.
	 
	 	 	At the end of the section, insert the following: “Subject to Seller’s
training schedule and provided Buyer schedules its training with
reasonable advance notice, Seller shall make reasonable efforts to ensure
that all of the training courses described in this section are provided
to Buyer in accordance with Buyer’s scheduling preferences. Furthermore,
Buyer shall have the option by co-ordinating with Seller’s training
co-ordinators to substitute the aforementioned training allotment for
alternative equal value training options.”
	 
	15.0	 	WARRANTY
	 
	15.1	 In the second line after “Aircraft” insert “shall conform to the
Specification and”.
	 
	15.1	 In the seventh line after “item(s)” add “including all required
disassembly and reassembly to gain access to or to remove and replace
such item(s) and functional testing”.

	 	 	 
	 	[**] 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.
	8/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	15.1	 	In the eight line after “facilities,” insert “any Bombardier
Aviation Services facility, any Global Express Authorized Service
Facility,”.
	 
	15.1	 	In the ninth line after “Seller”, insert “and reasonably acceptable
to Buyer”.
	 
	15.1	 	At the end of the first sentence, delete the period and add the
following: “, except that for a period of 10 days following expiration
of a Warranty period, Buyer may present a claim for a defect that
existed prior to the expiration of such Warranty period provided that
Seller had previously received notice of such a defect.”
	 
	15.1	 	At the end of the Article, add the following: “Any matters stated
in the Specification as type characteristics, estimates,
approximations, objectives, design objectives, design criteria are
excluded from the Warranty.”
	 
	15.4	 	In the first line of clause i), replace [**]
	 
	15.4	 	In the first line of clause ii) before “installation” insert [**]
	 
	15.4	 	In the second line of clause ii), after “party” insert “(other than an affiliate of Seller)”.
	 
	15.4	 	At the end of clause ii), add the words “to the extent of such contribution.”
	 
	15.4	 	Delete the period at the end of clause iii) and add the following:
“in accordance with Bombardier’s Ground Handling and Service
Information Manual referenced in Article 14.0 of Schedule “A”, by any
person other than Seller or any party related to Seller, to the extent
such misuse, abuse, accident or improper storage is a cause of the
defect.”
	 
	15.5	 	At the end of the first sentence before the period, add the
following: “but the Warranty does apply to Seller’s installation of the
Powerplant on the Aircraft, including the design of such installation”.
	 
	15.5	 	Insert the following at the end of Section 15.5:
	 
	 	 	[**]
	 
	15.6	 	At the end of the Article before the period, add the following: “or any amendment to this Agreement”.
	 
	15.7	 	Add the following at the end of this Article: [**]
	 
	15.8	 	In the fourth line following “records” insert “to the extent Buyer
fails to maintain such records and such failure prevents Seller from
determining if a claim should be covered under this Warranty”
	 
	16.0	 	PATENT, COPYRIGHT AND TRADEMARK PROTECTION
	 
	 	 	In the fifth line following “Canadian patent” insert [**]
	 
	 	 	In the fifth line following “foreign Patent” insert [**]
	 
	 	 	In section i) delete in its entirety and replace with the following “
Buyer notifies Seller in writing within 20 days or such shorter period
as provided by law to file an appearance, a defense, preliminary
motions or other similar court proceedings provided that the failure
to give such

	 	 	 
	 	[**] 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.
	9/10

 

 

	 	 	 
	 

	 	BOMBARDIER
	 

	 	AEROSPACE

ADDENDUM ONE TO THE GLOBAL EXPRESS PURCHASE AGREEMENT BETWEEN

WILLIAMS-SONOMA, INC. AND BOMBARDIER AEROSPACE CORPORATION

	 	 	notice shall be a bar to Buyer’s indemnification rights
hereunder only to the extent it is prejudicial to Seller.”
	 
	 	 	In section iii) replace the word [**] with the word [**]
	 
	 	 	After the second ii), after the word thereof on the second line, add the
words [**]
	 
	 	 	In the fourth paragraph following “Subject to the foregoing provisions
of this Patent” insert [**]
	 
	 	 	Add the following new paragraphs to Article 16.0:
	 
	 	 	[**]

	IV.	 	AMEND SCHEDULE A-1 TO THE AIRCRAFT PURCHASE AGREEMENT AS FOLLOWS:
	 
	2.0	 	SOUNDPROOFING
	 
	 	 	Replace this article in its entirety and replace with the following:
	 
	 	 	[**]
	 
	 	 	[**]

IN WITNESS HEREOF, the parties hereto have caused this Addendum to be duly
executed by authorized representatives as of the day and year indicated below.

	 	 	 	 	 	 	 	 	 
	BOMBARDIER INC.	 	WILLIAMS-SONOMA, INC.
	SELLER	 	BUYER
	 
	 	 	 	 	 	 	 	 
	By:

	 	Bombardier Inc.
	 	By:
	 	WSI	 	 
	 
	Name:

	 	/s/ GARY L. DOLSKI
	 	Name:
	 	/s/ W. HOWARD LESTER	 	 
	 
	Title:

	 	General Manager: Contracts
	 	Title:
	 	Chairman	 	 
	 
	Date:

	 	30 April 03
	 	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.
	10/10

 

 

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 +20°C
	 
	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,
180° 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
	B. Maximum
gross take-off weight *
	 	95,000 lb.	 	43,091 kg
	
C. Maximum landing weight
	 	78,600 lb.	 	35,653 kg
	D. Maximum
zero fuel weight
	 	56,000 lb.	 	25,401 kg
	
E. Basic operating weight**
	 	50,300 lb.	 	22,816 kg
	F. Maximum fuel weight
	 	43,350 lb.	 	19,663 kg
	Maximum payload (D-E)
	 	5,700 lb.	 	2,585 kg
	Payload with
maximum fuel (A-E-F)
	 	1,600 lb.	 	726 kg
	
Fuel with maximum payload (A-D)
	 	39,250 lb.	 	17,804 kg
	
NBAA IFR fuel reserve (8 pax)
	 	3,100 lb.	 	1,406 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	 	 	 	 	 	 	± 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 -30oC (-22oF) to +45oC
(+113oF). 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,
multi-function 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:

	•	 	Inboard, mid and outboard fowler
flaps, incorporated into the
trailing edge.
	 
	•	 	Slats mounted on forward spar from
the wing leading edge. Thermal
anti-icing is provided inside the
slats.
	 
	•	 	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.
	 
	•	 	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 ge ar
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 35°C (ISA+20°C) 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 thrust reverser levers on the
throttle quadrant are operated. For
maintenance, the thrust reverser can be
locked open.

The engine has been designed for “on
condition” type maintenance which
requires periodic inspection of specific
major components. Only those parts that
show distress are replaced or
overhauled. The periodic maintenance
checks are established utilizing the
MSG-3 process.

The complete power plant assembly is
detachable from the pylon as a unit.

Auxiliary Power Unit (APU)

A Honeywell RE220 gas turbine APU is
installed in the Aircraft tail cone to
provide bleed air and electrical power
on the ground and in flight. Control of
APU speed and temperature is automatic.
APU starting is initiated by a single
switch located in the cockpit.

The APU supplies bleed air for cabin
cooling and heating, as well as engine
starting. The APU also drives a 40/45
kVA generator, which provides electrical
power on the ground and as back-up to
the main engine driven generators
in-flight.

11.0 EQUIPMENT & FURNISHINGS

The Aircraft has a flight compartment
and main cabin. The flight compartment
includes the following equipment and
furnishings:

	•	 	All instruments and control panels
	 
	•	 	A checklist holder and letdown sheet holder
	 
	•	 	A map holder on each control wheel
	 
	•	 	Storage for flight handbooks and
maps adjacent to each pilot
	 
	•	 	Storage compartments in the
cockpit side consoles for the
stowage of clip boards, charts,
etc.

January 2002 (BAC)

 4

 

 

Schedule “A”

	•	 	16g pilot and copilot reclining
seats (adjustable vertically and
horizontally) with five point
shoulder harnesses and inertia
reels.

12.0 SYSTEMS

Flight Controls

Flight controls consist of two separate
elevators, two ailerons, a single
rudder, a trimmable horizontal
stabilizer, eight multi-function
spoilers and four ground spoilers. Six
segments of Fowler flaps and eight
segments of leading edge slats are also
installed.

The primary flight controls are
conventional, mechanically controlled
and hydraulically operated. Cockpit
surface position indications are
displayed on EICAS. Primary lateral
control is accomplished by hydraulically
powered ailerons and assisted by
multi-function spoilers. The aileron
control is a dual system with anti-jam
protection. Pitch control is provided
by a dual mechanical control system
activating two separate hydraulically
operated elevators. Yaw control is
provided by means of three power control
units hydraulically powering the rudder.

The flap/slat system is controlled by an
integrated flap/slat selector located in
the cockpit with positions displayed on
EICAS.

Eight multi-function, electrically
controlled spoilers are installed, with
simplex hydraulically powered PCU’s, one
per surface. These spoilers provide roll
control to assist the ailerons, in
particular for crosswind landing cases.
The spoilers can also be symmetrically
controlled by the pilot, to be used as
speed brakes, via the flight spoiler
control lever. On the ground, these
spoilers act as lift dumpers, and are
automatically deployed similarly to the
ground spoilers. Spoiler position is
disp layed on EICAS. To provide ground
lift dumping, four ground retract/extend
spoilers (inboard/outboard) with simplex
actuators are installed. They are
controlled in pairs by a hydraulic
manifold and are automatically commanded
to deploy by their dual controllers,
along with the multi-function spoilers,
upon Aircraft touchdown or rejected
take-off. Status and positioning is
displayed on EICAS.

Lateral and directional trim is
accomplished by controls on the center
console that operate electric trim
actuators. Longitudinal trim is
accomplished by switches on the pilots’
control wheels, which command changes in
the horizontal stabilizer angle through
flight control units. Mach trim is also
provided by the flight control units.
Trim indication is provided on EICAS. To
provide ground lift dumping, four ground
retract/extend spoilers
(inboard/outboard) with simplex actuators
are installed. They are controlled in
pairs by a hydraulic manifold and are
automatically commanded to deploy by
their dual controllers, along with the
multi-function
spoilers, upon Aircraft touchdown or
rejected take-off. Status and
positioning is displayed on EICAS.

Fuel System

Fuel is contained in a wet wing box
structure sealed to form three main
separate wing tanks. An aft fuel tank
is located to the aft side of the rear
pressure bulkhead.

Each engine is supplied with fuel from
its respective feed tank, which contains
two AC primary, and one DC backup
electric boost pumps. Crossfeed between
engines is provided by controlling an
isolation valve. Fire shut-off valves
are installed on each engine and APU
feed line. The scavenge and transfer
systems maintain the feed tanks full
during nose up attitudes and provide
automatic transfer of fuel from the
central tank to the wing tanks.

A vent system to control the pressure in
the fuel tanks is provided, terminating
in two underwing mounted ram air scoops.
Also provided are two fuselage fuel
vent surge boxes to prevent fuel
spillage. Cockpit control is provided
on the overhead panel and fuel quantity
and warnings are displayed on EICAS.

A single point pressure refuel/defuel
manifold containing shut-off valves is
provided.

A fuel re-circulation system is provided
to ensure continued operation of the
fuel system even during flights of long
duration at extreme temperatures.

Hydraulic System

Three fully independent and isolated
hydraulic systems provide power to the
flight controls and other systems in the
Aircraft. All three systems operate at
a nominal pressure of 3,000 psi, and use
phosphate ester Type IV low density
hydraulic fluid.

System #1 powers flight controls and
left hand thrust reversers. System #2
powers flight controls, right hand
thrust reversers, brakes and main
landing gear emergency extension.
System #3 supplies pressure to flight
controls, landing gear, nose steering
and brakes. In case of emergency, a ram
air turbine (RAT) system incorporates a
hydraulic pump, which provides essential
power to the systems through System #3.

Visual and aural indication regarding
the system status, including system
pressure, quantity and temperature,
pumps and shut-off valve status, is
given in the cockpit via EICAS.

Electrical System

Primary electrical power is provided by
four 40 kVA alternating current (AC)
generators. Two generators are
coupled to each engine auxiliary gearbox.
Also, electrical power may be provided
by a 45 kVA generator coupled to the APU.
Direct current (DC) electrical power is
provided by four 150A transformer
rectifier units (TRU), powered from the
AC power sources. In case of emergency,
electrical power is provided by a 9 kVA
ram air turbine (RAT) generator and by
two nickel-cadmium batteries. (1-25
Amp-hr and 1-42 Amp -hr).

On the ground, electrical power can be
provided either via the AC or the DC
external power receptacle.

The AC power distribution system is
divided in four independent and isolated
distribution systems/buses, which are
normally fed by different power sources
and are virtually interrupt free.

Power distribution to user equipment is
handled by the electrical management
system (EMS) providing automatic

January 2002 (BAC)

 5

 

 

Schedule “A”

system reconfiguration, optimizing
availability of electrical power to user
equipment and minimizing pilot workload.
Two EMS control and display units are
located in the cockpit for monitoring and
control by the pilots. As required.

Environmental Control System

The dual environmental control system
(ECS) provides the following:

	•	 	A supply of conditioned air to the cabin and cockpit;
	 
	•	 	Cabin pressurization;
	 
	•	 	Hot air anti-icing for the wing and engine air intake;
	 
	•	 	Ventilation and cooling air for the avionics equipment;
	 
	•	 	Emergency pressurization.

Each ECS consists of an engine bleed
management system and an air cycle
machine.

Conditioned air supply to the cabin and
cockpit is provided by two separate
systems; one system responding to the
temperature selection of the cockpit and
the other to the cabin. Cabin air
temperature is sensed in two locations
and the signals input to the ECS
temperature controller. Conditioned air
to the cabin is distributed from a duct
on each side of the cabin. Conditioned
air for the cockpit is supplied to the
roof, side console panels and to the
forward cockpit panel. Individual
adjustable overhead air vents (gaspers)
are installed at each pilot’s position.

The cabin pressure system consists of two
independent controllers, interfacing with
EICAS. The controllers automatically
command the cabin altitude through their
auto schedule, by regulating the
electrically actuated outflow valves.
Landing altitude is set via the FMS,
however, a cockpit panel mounted selector
provides an alternate means of choosing
landing altitude if the FMS is not used.
An independent protection is provided to
automatically close the outflow valves,
should cabin altitude exceed 15,000 ft.
In automatic mode the system controls and
maintains a cabin pressure altitude not
to exceed 6,000 ft. up to 45,000 ft.
and 7,230 ft. at 51,000 ft., providing
appropriate cabin pressure control
performance during steady and transient
conditions. Cabin differential pressure,
cabin pressure altitude and cabin
pressure altitude rate of change are
indicated on EICAS. A warning is
displayed if the cabin pressure altitude
exceeds 9,000 ft.

The wing and engine inlet anti-ice is an
evaporative thermal bleed air system.
It utilizes engine bleed air supplied
from the intermediate or high stage
engine bleed port according to the
flight conditions. Each slat leading
edge is comprised of a
telescopic duct and flex joints.
Piccolo tubes are provided to distribute
the hot air inside the slat leading
edge. The anti-ice system control and
components status is displayed on EICAS.

The Aircraft windshields and cockpit
side windows are electrically anti-iced.
The pitot heads, static ports, angle of
attack sensors and temperature probe are
also electrically anti-iced.

Oxygen System

A gaseous oxygen system for flight crew
protection in the event of a emergency
decompression is installed in the
Aircraft. Quick-donning pressure demand
type masks with
mask mounted regulators are provided for
each pilot. A crew system pressure
indication and low pressure warning is
provided on EICAS.

Four oxygen supply cylinders with
capacity of 50 cu.ft. each are
installed to serve the flight crew and
passengers.

Fire Protection

A fire detection and warning system with
fault discrimination is installed, with
fire detectors located in each engine
nacelle and in the APU compartment.
Three red fire warning lights are
installed in the cockpit fire handles,
one each for each engine nacelle and one
for the APU compartment. An element in
the wheel well warns of an overheat
condition in either of the main wheel
wells. Indication and test switches are
provided in the cockpit.

A two-shot Halon fire extinguishing
system for each engine and a two-shot
system for the APU are installed in the
fuselage aft section. The fire
extinguisher bottle is fitted with a
low-pressure switch, which provides an
annunciation in the cockpit when
pressure drops below a predetermined
pressure setting.

One Halon type fire extinguisher is
installed in the flight crew
compartment.

Maintenance System

A Central Aircraft Information and
Maintenance System (CAIMS) is installed
in the Aircraft and uses a Portable
Maintenance Access Terminal (PMAT) to
access and monitor Aircraft system
status. Each Aircraft system performs
continuous self test and reports its
current status to the PMAT, in addition
to internally storing fault data along
with time of occurrence and flight
information.

The PMAT interprets the fault data and
displays fault information in plain
English along with flight deck effects.
The fault information is linked to the
aircraft maintenance
manual (AMM) that is contained on a CD
ROM incorporated in the PMAT, providing
immediate access to maintenance and
trouble shooting information.

The PMAT is also used to interrogate
systems to download flight fault
information and to initiate built in
test functions.

The capability to interrogate CAIMS
in-flight is available as an option and
provides some of the maintenance
features such as flight deck effects and
fault correlation with a direct link to
the AMM.

13.0 INSTRUMENTATION & AVIONICS

General Description

The Aircraft is equipped with a six-tube
Honeywell Primus 2000 XP avionics suite.
The six displays are laid out in a
six-across configuration. Two displays
in front of each pilot provide Primary
Flight Display (PFD) and
Multi-Functional Display (MFD)
information. The PFD presents flight
director, airspeed, altitude, attitude,
heading, as well as Horizontal Situation
Indication (HSI). The MFD provides
moving map and weather radar information
as well as traffic warnings from the
Traffic and Collision Avoidance System
(TCAS). The MFD may be manually
reverted to either a PFD or EICAS.

January 2002 (BAC)

 6

 

 

Schedule “A”

The Engine Indication and Crew Alerting
System (EICAS) system is installed
consisting of a primary EICAS display, a
secondary EICAS display (both installed
on the center instrument panel), data
acquisition units and a control panel.
The functions provided by the EICAS are
as follows:

	•	 	Engine parameter display
	 
	•	 	Crew alerting messages
	 
	•	 	Aural warnings
	 
	•	 	Aircraft synoptics pages for

	•	 	Flight Controls
	 
	•	 	Electrical Systems
	 
	•	 	Hydraulics Systems
	 
	•	 	Fuel System
	 
	•	 	Anti-Ice System
	 
	•	 	Environmental Control System

	•	 	Aircraft systems
indications for

	•	 	Gears
	 
	•	 	Doors
	 
	•	 	FDR
	 
	•	 	Lamp Driving
	 
	•	 	APU
	 
	•	 	Brake Temperature
	 
	•	 	Cabin Pressurization.

EICAS displays can be displayed on
either or both of the Multi-Function
Displays (MFD) by manually switching in
the event of a failure. Master caution
and warning indications are located on
the glareshield at both crew positions.

A digital flight data recorder (FDR)
system is installed to provide a record
of Aircraft parameters required by the
FAA and includes an underwater location
device.

The following standby
instruments are installed in the
Aircraft:

	•	 	Attitude indicator
	 
	•	 	Combined airspeed/indicator/altimeter
	 
	•	 	Compass

Auto Flight

The Aircraft is equipped with an
autoflight system, which provides the
following major functions:

	•	 	Flight Director
	 
	•	 	Autopilot
	 
	•	 	Yaw Damper
	 
	•	 	Autothrottle

The flight director modes
are selected on the flight control panel
or via the go-around switches on the
throttles. The flight director commands
and mode selection is displayed on the
PFD. The flight director modes include:

Flight Director Modes

	 	 	 	 	 
	Lateral	 	Vertical	 	Multi-Axis
	- Heading Select
	 	- Altitude Hold	 	- Approach
	- Navigation
	 	-Altitude Select	 	- Go Around
	- Approach
	 	- Vertical Speed Select	 	- Takeoff
	- Back Course
	 	- Flight Level Change	 	- Windclear Guidance
	 
	 	- VNAV	 	 

The dual autopilot system outputs pitch
and roll steering commands to the
autopilot servos. The autopilot engage
status is displayed on the PFD.

The dual yaw damper system provides yaw
damping and turn coordination functions.

The autothrottle computations are
performed within two integrated avionics
computers. Each computer is capable of
independently driving both throttle
servos to move the throttles and
provides inputs to the engine full
authority digital engine control
(FADEC). Autothrottle modes are
integrated with autopilot modes. The
autothrottle performs the engine
synchronization function.

Communications

The Aircraft communication system is comprised of:

	•	 	Two VHF communication systems.
Transceiver tuning is achieved
through either of two RTU’s. Space
and power provisions are made for a
third VHF system.
	 
	•	 	A dual digital HF communication
system. Tuning is achieved through
either of the two RTU’s or the two
FMS CDU’s.
	 
	•	 	A single SELCAL system which provides
an aural annunciation and an EICAS
message when a preset code is received
by either the VHF or HF radios. The
system is capable of monitoring three
VHF and two HF radios.

Provisions are
made in the Aircraft for the following:

	•	 	SATCOM (6-channel) — space and power provisions
	 
	•	 	Datalink — Space and power provisions
	 
	•	 	Flight phone in the cockpit.
	 
	•	 	Passenger Address Amplifier Unit.

A two channel interphone system with
hand held microphones and individual
controls for pilot and co-pilot is
installed in the Aircraft. Radio
transmission press-to-talk buttons are
located on the control wheels. An
intercom/hot mic switch is incorporated
in each audio control panel.

A Cockpit Voice Recorder system is
installed to record area voice
communication, as well as pilot and
co-pilot communication. The unit
records continuously and retains the
last thirty minutes of voice data.

Indicating/Recording Systems

All instrument presentations are
graduated in United States units of
measure for land planes (fuel quantity
in lb., fuel flow in lb./hr., altitude
in ft.), except temperature indicators
(in degrees Celsius) and airspeed
indicators (in knots or Mach number as
applicable). All placards read in the
same units as the instruments affected.

The arrangement of the controls and
instruments allow the pilots to fly the
Aircraft from the LH or RH seat. A
center console is installed between the
pilot and co-pilot, on which the engine
and system controls and trim controls
are mounted.

Two clocks are installed, one on the
pilot’s side panel, the other on the
co-pilot’s side panel.

Navigation

The navigation system includes the following components:

January 2002 (BAC)

 7

 

 

Schedule “A”

Air Data System (ADS) - The ADS consists
of three digital air data computers
(ADC’s). Three total air temperature
probes are installed to provide
temperature inputs to the ADC’s. The
ADC’s use pitot, static and temperature
inputs to compute altitude, vertical
speed, airspeed, and Mach number data

Electronic Flight Instrument System
(EFIS) - An EFIS is provided with the
Aircraft utilizing the PFD, the MFD and
a display control panel for each pilot.
The processing and symbol generation is
part of the integrated avionics
computer.

Weather Radar - A digital color radar
system with dual radar controller is
installed. Radar data is displayed on
the MFD’s. The system also has
turbulence detection capability. Space
and power provisions are present for an
optional lightning sensor system.

Radio Altimeter - Two radio altimeters
are installed with data displayed on
both PFD’s.

Inertial Reference System (IRS) - Three
inertial reference units are installed
each providing attitude and heading,
rate, acceleration and position data for
use by EFIS, AFCS and other systems.
IRS position data is utilized by the
FMS’s for navigation. Integrated mode
select units coupled to each inertial
reference unit allow selection of IRS
modes (NAV or ATT). IRS initialization
is via either FMS or the Lasertrak unit,
which can also act as a back-up
navigator. One inertial navigation
display unit (INDU) is installed to
provide basic navigation capabilities as
back-up to the FMS.

Very High Frequency (VHF) Navigation -
Two VOR/ILS/MKR VHF navigation systems
are installed in the Aircraft. Both
systems are tuned by the RTU’s.

Automatic Direction Finder (ADF) - Two
digital ADF systems are installed in the
Aircraft. The ADF receivers are tuned
by the RTU’s.

Distance Measuring Equipment (DME) - Two
6-channel DME systems are installed.
Channel 1 and 2 are manually tuned,
while the remaining channels are tuned
by the FMS.

Air Traffic Control (ATC) Transponder -
Two Mode-S transponders are installed in
the Aircraft. Transponder control and
selection are performed via the RTU’s.

Traffic Collision Avoidance system
(TCAS) — A TCAS is installed comprising
of a TCAS processor, one top mounted
directional antenna and one bottom
mounted omnidirectional antenna. The
system is controlled by the RTU’s.

Flight Management System (FMS) - The
Aircraft is equipped with two FMS’s
comprising of two color CDU’s flight
management computers and a fixed data
loader, installed on the pilot’s side
console, which can interface with the
FMS. The FMS includes the following
features:

	 	•	 	Flight plans
	 
	 	•	 	Lateral and vertical navigation
	 
	 	•	 	Dual operation
	 
	 	•	 	Map data outputs for EFIS
	 
	 	•	 	Worldwide database, including airways, SIDS and
STARS
	 
	 	•	 	Holding pattern specification for any waypoint and a
present position hold at any time
	 
	 	•	 	Back-up radio tuning
	 
	 	•	 	Progress data display
	 
	 	•	 	Autothrottle interface
	 
	 	•	 	Fuel leak detection
	 
	 	•	 	Space and power provisions are present for a third
FMS.

Global Positioning System (GPS) - A
single GPS system is installed. GPS
data is fed to the FMS. Space and power
provisions are present for the
installation of an optional second GPS.

Enhanced Ground Proximity Warning System (EGPWS)
- A GPWS system with wind shear
detection is installed. Warnings are
displayed in the PFD, enhanced terrain
avoidance is displayed on the MFD’s.

In addition to the above, provisions are
made for the following optional
equipment:

	•	 	Head-up Guidance System
	 
	•	 	Cockpit printer
	 
	•	 	Emergency Locator Transmitter (ELT)

14.0 CUSTOMER SUPPORT SERVICES

Inspection and Acceptance Procedures

Seller will advise Buyer when the
Aircraft will be available for Buyer’s
inspection and acceptance in accordance
with the Agreement. Buyer will be
entitled to have as many representatives
as it deems required to participate in
the inspection and acceptance of the
Aircraft; however, only 2
representatives of Buyer may participate
in flight tests due to safety, insurance
and regulatory requirements.

Flight Operations Support

Upon request by Buyer, Seller will
provide, at no additional cost, the
services of its pilots for the following
activities:

	i)	 	One pilot to assist Buyer during
acceptance of the Completion Work from
the interior completion center.
	 
	ii)	 	One pilot, for a period of up to 14
days from Delivery Time, to familiarize
Buyer’s flight crews with day-to-day
Aircraft operations

In addition, Seller will provide, at no
additional cost, the services on one
dedicated, on-site, field service
representative (FSR) to assist with the
start-up of flight operations of the
Aircraft for an initial period of 14
days. Buyer will be responsible to
reimburse the reasonable travel and
living expenses of Seller’s pilots and
FSR.

Training

As part of the Purchase Price, Seller
shall make available, at its designated
facilities, the following courses:

	•	 	A ground and simulator
flight-training program for four
qualified pilots to type rating;
	 
	•	 	Ground maintenance-training
program for two mechanics; and
	 
	•	 	Training for two flight attendants.

January 2002 (BAC)

 8

 

 

Schedule “A”

Buyer shall be responsible for all
travel and living expenses of Buyer’s
personnel. Seller recommends that all
training be completed before placing the
Aircraft into service, but, in any
event, all training must 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 the
following documentation and the
technical publications that are included
in the Purchase Price of the Aircraft:

	 	 	 	 	 
	Manual Description	 	Quantity
	Service Bulletins
	 	 	1	 
	Airplane Flight Manual
	 	 	2	 
	Quick Reference Handbook
	 	 	2	 
	Flight Crew Operating Manual
	 	 	2	 
	Flight Planning and Cruise Control Manual
	 	 	1	 
	Ground Handling & Service Information
	 	 	1	*
	Maintenance Manual
	 	 	1	*
	Wiring Diagram Manual
	 	 	1	*
	Wiring List Manual
	 	 	1	*
	System Schematic Manual
	 	 	1	*
	Illustrated Parts Catalog
	 	 	1	*
	Time Limits/Maintenance Checks
	 	 	1	*
	Structural Repair Manual
	 	 	1	*
	Weight & Balance Manual
	 	 	1	*
	Non-Destructive Test Manual
	 	 	1	*
	Illustrated Tool & Equipment Manual
	 	 	1	*
	Component Maintenance Manual
	 	 	1	*
	Maintenance Planning Document
	 	 	1	*
	Fault Isolation Manual
	 	 	1	*
	Fault Reporting Manual
	 	 	1	*
	Rolls-Royce Service Bulletins
	 	 	1	 
	Rolls-Royce Time Limits Manual
	 	 	1	 
	Rolls-Royce Power Plant Build-Up
	 	 	1	 

The manuals identified with an asterisk
(*) are delivered in CD-ROM format. All
others are delivered in hard copy.

In addition, commencing at Delivery Time,
Seller shall make available, from time
to time, to Buyer at its last address
provided by Buyer in writing to Seller,
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 10 years after
delivery of the last BD-700-1A10
aircraft manufactured by Seller. Seller
shall provide this service at no
additional cost to Buyer for a period of
5 years from Delivery Time.

Computer Integrated Maintenance Management System (CIMMS )

In order to facilitate the performance
of maintenance of the Aircraft at
required intervals, Seller provides
Bombardier’s Computer Integrated
Maintenance Management System (CIMMS)
free of charge for one year commencing
at the induction of the Aircraft at the
Completion Center and, upon
subscription, renewable annually
thereafter.

Any 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.

Bombardier Smart Parts Plus Program

Buyer will have the option of enrolling
the Aircraft in Bombardier’s Smart Parts
Plus program applicable to the Aircraft.
These programs provide aircraft parts
and components replacement coverage at a
fixed dollar rate per flight hour.

15.0 WARRANTY

15.1 Seller 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”).
Seller’s sole obligation and liability
under this Warranty is a) expressly
limited to correction by repair,
replacement or rework of the item(s) by
Seller (or its affiliates) at its
facilities, or at such other facility as
may be designated by Seller, of any
defect specified above and b) subject to
Buyer giving notice to Seller of a claim
under this Warranty as soon as
practicable but in no event later than
expiration of the Warranty periods set
forth below. Any item(s) (excluding the
Aircraft) found defective shall be
returned to Seller at Seller’s expense.

15.2 The Warranty in respect to the
Aircraft shall be for 5,000 flight hours
or 5 years from Delivery Time, whichever
first occurs except that for the
Completion Work, the Warranty shall be
for 2,000 flight hours or 2 years from
Delivery Time, whichever first occurs.

15.3 Notwithstanding the above, the
Warranty period applicable to airframe
primary metal structures as defined in
Section 51 and as detailed in Sections
53 (Fuselage), 55 (Stabilizers) and 57
(Wings) of the Aircraft Structural
Repair Manual in effect as of the date
of this Agreement shall be for 20,000
flight hours or for 20 years from
Delivery Time, whichever first occurs;
provided, however, that such extended
Warranty period does not apply to doors,
fairings, covers and systems/equipment
support structure, for which specific
items the Warranty period shall be as
stated in Article 15.2.

January 2002 (BAC)

 9

 

 

Schedule “A”

15.4 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 Seller’s Approved Flight
Manual, Maintenance Manual and Service
Bulletins, and as each thereof may be
amended from time to time by Seller;
	 
	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.

15.5 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 (Rolls-Royce Deutschland)
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 Seller 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.

15.6 Seller does not warrant any
accessory, equipment or part
incorporated in the Aircraft, which is
not furnished pursuant to this
Agreement.

15.7 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 15 remaining at the time of such
repair, replacement or rework.

15.8 Buyer shall maintain reasonably
complete records of operations and
maintenance of the Aircraft and shall
make such records available to Seller as
Seller may reasonably require. If Buyer
fails to maintain those records Seller
shall be relieved of its Warranty
obligations.

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

16.0 PATENT AND TRADEMARK PROTECTION

Subject to the provisions set out below,
Seller 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 a) U.S. or Canadian patent or
trademark, or b) foreign patent or
trademark having a United States or
Canadian counterpart and issued by any
country which has ratified and is at the
time of any such actual or alleged
infringement a contracting party to the
Convention on International Civil
Aviation and the International
Convention for the Protection of
Industrial Property provided that:

	i)	 	Buyer notifies Seller in writing of
the claim within 10 days after Buyer’s
receipt of the claim;
	 
	ii)	 	Upon Seller’s written request, Buyer
immediately gives to Seller control over
the defense and/or settlement of the
claim;
	 
	iii)	 	Buyer fully cooperates with Seller in such defense and/or settlement; and
	 
	iv)	 	Buyer does not prejudice Seller’s
conduct of such defense and or
settlement.

In no event shall Seller
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 Seller 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 Seller or
which was not manufactured exclusively
pursuant to Seller’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 Seller 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,
Seller 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 Seller or
any damages that may be awarded against
Buyer in respect of such claim. At its
own expense, Seller 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 Seller to take
action in accordance with the foregoing,
provided that it shall be Seller’s sole
option as to which alternative action it
takes. Except as expressly provided
above, Seller does not provide any other
representation, warranty or protection
concerning patents or trademarks with
respect to the Aircraft.

17.0 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
Seller’s standard non-disclosure
agreement.

January 2002 (BAC)

 10

 

 

Schedule A-1

	 	 
	BOMBARDIER
AEROSPACE

	
	 
	 

COMPLETION SPECIFICATION

For The

GLOBAL EXPRESS

Prepared For:

Williams-Sonoma, Inc.

S/N 9120

	 	 	 	 	 
	 

	 	Specification No.
	 	:   BCC-GX-302
	

	 	Date
	 	:   June 20, 2002
	

	 	Customer Specific	 	 
	

	 	Amendment 2
	 	:   April 29, 2003

 

 

	 	 	 	 	 
	 
	 	Specification No.	 	:   BCC-GX-302
	
	 	Date	 	:   June 20, 2002
	
	 	Customer Specific	 	 
	
	 	Amendment 2	 	:   April 29, 2003
	
	 	Page No.	 	:    i

	 	 	 	 	 	 	 	 	 
	1.0
	 	 	GENERAL STATEMENTS AND CONDITIONS	 	 	1	 
	 
	 	1.1	 	SCOPE	 	 	1	 
	 
	 	1.2	 	DEFINITIONS	 	 	1	 
	 
	 	1.3	 	QUALITY AND CERTIFICATION	 	 	2	 
	 
	 	1.4	 	INCOMING INSPECTION	 	 	4	 
	 
	 	1.5	 	FERRY EQUIPMENT	 	 	4	 
	 
	 	1.6	 	PRESERVATION AND PROTECTION	 	 	4	 
	 
	 	1.7	 	ADDITIONAL WORK	 	 	4	 
	 
	 	1.8	 	EQUIPMENT AND SYSTEM(S) AT RISK	 	 	5	 
	 
	 	1.9	 	PROGRAM STATUS/CUSTOMER ACCESS	 	 	5	 
	 
	 	1.10	 	FLIGHT TESTING	 	 	5	 
	 
	 	1.11	 	PRE-DELIVERY	 	 	5	 
	 
	 	1.12	 	DOCUMENTATION	 	 	6	 
	 
	 	1.13	 	CUSTOMER APPROVALS	 	 	7	 
	 
	 	1.14	 	DESIGN AND INSTALLATION PRACTICES	 	 	8	 
	2.0
	 	 	SOUNDPROOFING	 	 	9	 
	3.0
	 	 	OXYGEN SYSTEM	 	 	10	 
	 
	 	3.1	 	PURITAN BENNETT “SWEEP ON” 2000 MASKS	 	 	10	 
	 
	 	3.2	 	ADDITIONAL QUICK DONNING MASK (MC-20)	 	 	10	 
	4.0
	 	 	ENVIRONMENTAL CONTROL SYSTEM (AIR CONDITIONING)	 	 	11	 
	 
	 	4.1	 	ENTRY AREA HEATER	 	 	11	 
	5.0
	 	 	POTABLE WATER SYSTEM	 	 	12	 
	6.0
	 	 	COCKPIT	 	 	13	 
	 
	 	6.1	 	COCKPIT HEADLINER	 	 	13	 
	 
	 	6.2	 	COCKPIT HOLDERS AND POUCHES	 	 	13	 
	 
	 	6.3	 	INSTRUMENT PLACARD	 	 	13	 
	 
	 	6.4	 	JEPPESEN STORAGE BOX	 	 	13	 
	 
	 	6.5	 	COCKPIT FLASHLIGHTS	 	 	13	 
	 
	 	6.6	 	COCKPIT FOOTRESTS	 	 	13	 
	 
	 	6.7	 	ILLUMINATED APPROACH CHART HOLDERS	 	 	13	 
	 
	 	6.8	 	115V/60HZ OUTLETS	 	 	13	 
	7.0
	 	 	ENTRY AREA	 	 	14	 
	 
	 	7.1	 	HEADLINER	 	 	14	 
	 
	 	7.2	 	COCKPIT CURTAIN	 	 	14	 
	 
	 	7.3	 	ACOUSTIC CURTAIN	 	 	14	 
	 
	 	7.4	 	AlRSTAIR	 	 	14	 
	 
	 	7.5	 	JUMPSEAT	 	 	14	 
	 
	 	7.6	 	FORWARD LAVATORY	 	 	15	 
	 
	 	7.7	 	LH ENTRANCE ENCLOSURE	 	 	16	 
	 
	 	7.8	 	GALLEY	 	 	17	 
	 
	 	7.9	 	GALLEY ANNEX	 	 	18	 
	 
	 	7.10	 	CREW AREA	 	 	19	 
	8.0
	 	 	PASSENGER MAIN CABIN	 	 	21	 
	 
	 	8.1	 	BULKHEADS	 	 	21	 
	 
	 	8.2	 	DOORS	 	 	21	 
	 
	 	8.3	 	HEADLINER	 	 	21	 
	 
	 	8.4	 	PASSENGER SERVICE UNITS (P.S.U.)	 	 	22	 
	 
	 	8.5	 	SIDEWALL	 	 	22	 
	 
	 	8.6	 	SIDE LEDGES	 	 	22	 
	 
	 	8.7	 	DADO PANELS	 	 	22	 
	 
	 	8.8	 	FLOOR COVERING	 	 	22	 
	 
	 	8.9	 	MAGAZINE RACK	 	 	23	 
	 
	 	8.10	 	PULL-OUT TABLES	 	 	23	 
	 
	 	8.11	 	CONFERENCE H1-LO TABLE	 	 	23	 
	 
	 	8.12	 	SINGLE SEAT- NARROW	 	 	23	 
	 
	 	8.13	 	WIDE SEATS	 	 	24	 
	 
	 	8.14	 	DOUBLE SEATS	 	 	24	 
	 
	 	8.15	 	16G DIVAN	 	 	25	 

 

 

	 	 	 	 	 
	 
	 	Specification No.	 	:   BCC-GX-302
	
	 	Date	 	:   June 20, 2002
	
	 	Customer Specific	 	 
	
	 	Amendment 2	 	:   April 29, 2003
	
	 	Page No.	 	:   ii

	 	 	 	 	 	 	 	 	 
	 
	 	8.16	 	DIVAN END CABINETS	 	 	25	 
	 
	 	8.17	 	CREDENZA AND ENTERTAINMENT CABINET	 	 	26	 
	 
	 	8.18	 	LOW CABINET	 	 	26	 
	9.0
	 	 	AFT LAVATORY COMPARTMENT AND WARDROBE	 	 	27	 
	 
	 	9.1	 	BULKHEADS	 	 	27	 
	 
	 	9.2	 	DOOR	 	 	27	 
	 
	 	9.3	 	HEADLINER	 	 	27	 
	 
	 	9.4	 	PASSENGER SERVICE UNIT	 	 	27	 
	 
	 	9.5	 	SIDEWALL	 	 	27	 
	 
	 	9.6	 	VANITY CABINET	 	 	28	 
	 
	 	9.7	 	SANITATION SYSTEM (MAGAIR)- AFT LAVATORY	 	 	28	 
	 
	 	9.8	 	AFT WARDROBE AND STORAGE CABINET	 	 	28	 
	10.0
	 	 	BAGGAGE COMPARTMENT	 	 	29	 
	11.0
	 	 	AVIONICS - ELECTRICAL SYSTEMS	 	 	30	 
	 
	 	SERVICE BULLETINS	 	 	30	 
	 
	 	11.1	 	HONEYWELL MCS6000 SATELLITE COMMUNICATIONS (SATCOM) SYSTEM (SERVICE BULLETIN)	 	 	30	 
	 
	 	11.2	 	TELEDYNE C2000 MAGNASTAR TELECOMMUNICATION SYSTEM “OFFICE IN THE SKY” (SERVICE BULLETIN)	 	 	30	 
	 
	 	11.3	 	GLOBAL POSITIONING SYSTEM (GPS)-ADDITION OF A SECOND GPS (GPS 2) (SERVICE BULLETIN)	 	 	30	 
	 
	 	11.4	 	FLIGHT DATA RECORDER MODIFICATION (FDR/CFMS 2002)- INSTALLATION ADDITION OF FORCE TRANSDUCERS	 	 	30	 
	 
	 	11.5	 	INCREASE MAXIMUM TAKE-OFF WEIGHT (MTOW) TO 98,000 LBS	 	 	31	 
	 
	 	11.6	 	EMERGENCY LOCATION TRANSMITTER (ELT) SYSTEM (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.7	 	CAIMS IN-FLIGHT PRINTING CAPABILITY (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.8	 	COMMUNICATION ADDRESSING AND RECORDING SYSTEM (ACARS) TELEDYNE DATALINK SYSTEM (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.9	 	HONEYWELL RCZ-833 3RD VHF TRANSCEIVER (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.10	 	MILTOPE COCKPIT PRINTER (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.11	 	HONEYWELL LSZ-860 LIGHTING SENSOR SYSTEM - LSS (SERVICE BULLETIN)	 	 	31	 
	 
	 	11.10	 	THALES/SEXTANT HEAD-UP FLIGHT DISPLAY SYSTEM (HFDS) CAT II OPERATIONS (SERVICE BULLETIN)	 	 	32	 
	 
	 	MISCELLANEOUS AVIONIC SYSTEMS	 	 	33	 
	 
	 	11.11	 	JUMPSEAT AUDIO PANEL	 	 	33	 
	 
	 	11.12	 	PASSENGER ADDRESS SYSTEM	 	 	33	 
	 
	 	11.13	 	CABIN BUS DISCONNECT	 	 	33	 
	 
	 	11.14	 	GROUND SERVICE CABIN POWER	 	 	33	 
	 
	 	11.15	 	CABIN/LAVATORY CALL SYSTEM	 	 	33	 
	 
	 	11.16	 	GALLEY/CABIN CIRCUIT BREAKER PANEL	 	 	33	 
	 
	 	11.17	 	ELECTRICAL POWER	 	 	33	 
	 
	 	11.18	 	ELECTRICAL OUTLETS	 	 	33	 
	 
	 	11.19	 	CABIN PRINTER/FAX	 	 	34	 
	 
	 	11.20	 	ADDITIONAL TRU	 	 	34	 
	 
	 	11.21	 	COCKPIT AUXILIARY ANNUNCIATION PANEL	 	 	34	 
	 
	 	11.22	 	THALES INTEGRATED ELECTRONIC STANDBY INSTRUMENT (IESI)	 	 	34	 
	 
	 	11.23	 	HONEYWELL FMS CDU-820’S (FULL INSTALLATION OF 2 PRIMARY UNITS)	 	 	34	 
	12.0
	 	 	SWITCH PANELS AND ENTERTAINMENT	 	 	35	 
	 
	 	12.1	 	EXTERIOR SWITCHES	 	 	35	 
	 
	 	12.2	 	AUDIO SYSTEM	 	 	35	 
	 
	 	12.3	 	VIDEO SYSTEM	 	 	35	 
	 
	 	12.4	 	THE “AIRSHOW NETWORK” FLIGHT INFORMATION SYSTEM	 	 	36	 
	13.0
	 	 	LIGHTING	 	 	37	 
	 
	 	13.1	 	AIRSTAIR AND BOARDING LIGHTS	 	 	37	 
	 
	 	13.2	 	COCKPIT LIGHTS	 	 	37	 
	 
	 	13.3	 	ENTRANCE AREA HEADLINER LIGHTS	 	 	37	 
	 
	 	13.4	 	LH ENTRANCE ENCLOSURE LIGHT	 	 	37	 
	 
	 	13.5	 	FORWARD LAVATORY LIGHTS	 	 	37	 
	 
	 	13.6	 	GALLEY LIGHTS	 	 	37	 
	 
	 	13.7	 	CREW AREA LIGHTS	 	 	37	 
	 
	 	13.8	 	CABIN UPWASH AND DOWNWASH LIGHTS	 	 	38	 
	 
	 	13.9	 	CABIN READING AND TABLE LIGHTS	 	 	38	 
	 
	 	13.10	 	FLOOR ACCENT LIGHTS	 	 	38	 
	 
	 	13.11	 	ENTERTAINMENT COMPARTMENT LIGHT	 	 	38	 
	 
	 	13.12	 	AFT LAVATORY LIGHTS	 	 	38	 
	 
	 	13.13	 	WARDROBE LIGHT	 	 	38	 
	 
	 	13.14	 	BAGGAGE COMPARTMENT LIGHTS	 	 	38	 
	 
	 	13.15	 	CABIN ORDINANCE SIGNS	 	 	39	 
	 
	 	13.16	 	CABIN EMERGENCY LIGHTS	 	 	39	 
	 
	 	13.17	 	ESCAPE PATH LIGHTS	 	 	39	 

 

 

	 	 	 	 	 
	 
	 	Specification No.	 	:   BCC-GX-302
	
	 	Date	 	:   June 20, 2002
	
	 	Customer Specific	 	 
	
	 	Amendment 2	 	:   April 29, 2003
	
	 	Page No.	 	:   iii

	 	 	 	 	 	 	 	 	 
	 
	 	13.18	 	EXTERIOR SERVICE PANEL LIGHTING	 	 	39	 
	 
	 	13.19	 	PYLON LIGHTS	 	 	39	 
	 
	 	13.20	 	PULSE LANDING LIGHT SYSTEM	 	 	39	 
	 
	 	13.21	 	WHEEL WELL MAINTENANCE LIGHTS	 	 	40	 
	 
	 	13.22	 	WINGTIP TAXI LIGHTS	 	 	40	 
	14.0
	 	 	MISCELLANEOUS INSTALLATIONS	 	 	41	 
	 
	 	SERVICE BULLETINS	 	 	41	 
	 
	 	14.1	 	ADDITIONAL REFUEL/DE-FUEL PANEL (SERVICE BULLETIN)	 	 	41	 
	 
	 	14.2	 	TAIL LOGO LIGHT ILLUMINATION (SERVICE BULLETIN)	 	 	41	 
	 
	 	14.3	 	SINGLE ADDITIONAL AFT CABIN WINDOW (SERVICE BULLETIN)	 	 	41	 
	 
	 	OTHER MISCELLANEOUS INSTALLATIONS	 	 	41	 
	 
	 	14.4	 	EXTERNAL TOILET SERVICING	 	 	41	 
	 
	 	14.5	 	TOWBAR ASSEMBLY	 	 	41	 
	 
	 	14.6	 	LADDER STORAGE	 	 	41	 
	 
	 	14.7	 	AFT EQUIPMENT BAY STORAGE BOX	 	 	41	 
	 
	 	14.8	 	CATWALK BATTERY ACCESS	 	 	42	 
	 
	 	14.9	 	HANDRAIL EXTENSION	 	 	42	 
	 
	 	14.10	 	COMMON KEY PANELS	 	 	42	 
	 
	 	14.11	 	AFT EQUIPMENT BAY ACCESS LADDER	 	 	42	 
	 
	 	14.12	 	EXTERNAL BAGGAGE DOOR LOCK OVERRIDE	 	 	42	 
	 
	 	14.13	 	COCKPIT TRIM PANELS	 	 	42	 
	15.0
	 	 	EMERGENCY EQUIPMENT	 	 	43	 
	 
	 	15.1	 	COCKPIT	 	 	43	 
	 
	 	15.2	 	LH ENTRANCE ENCLOSURE	 	 	43	 
	 
	 	15.3	 	CREW AREA	 	 	43	 
	 
	 	15.4	 	GALLEY	 	 	43	 
	 
	 	15.5	 	CABIN	 	 	43	 
	 
	 	15.6	 	LAVATORIES	 	 	43	 
	 
	 	15.7	 	AFT WARDROBE/STORAGE	 	 	43	 
	 
	 	15.8	 	BAGGAGE AREA	 	 	43	 
	16.0
	 	 	LOOSE EQUIPMENT AND SPARES	 	 	44	 
	 
	 	16.1	 	LOOSE EQUIPMENT	 	 	44	 
	 
	 	16.2	 	SPARES	 	 	44	 
	17.0
	 	 	EXTERIOR PAINT	 	 	46	 
	18.0
	 	 	WEIGHT AND BALANCE AND CENTER OF GRAVITY	 	 	47	 
	19.0
	 	 	ANNEX “A” LIST OF BOMBARDIER FORMAT LAYOUT AND TRIM DRAWINGS	 	 	48	 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	1

	1.0	 	GENERAL STATEMENTS AND CONDITIONS
	 
	1.1	 	Scope

	 	 	This Completion Specification in conjunction with the documentation
explicitly referenced herein, defines the technical and management
requirements as well as the Work to be performed for design, manufacture,
installation, integration, test, and certification of an executive
interior of a Global Express Aircraft. It also defines the manner in
which the Work is to be conducted and controlled by Bombardier Completion
Center.
	 
	 	 	Deliverables (Loose Equipment and Spares)
	 
	 	 	All contracted deliverables that can not accompany the aircraft at
delivery owing to space constraints will be shipped (FOB Dorval/Tucson)
to the required destination via a transportation mode acceptable to the
customer.
	 
	 	 	Contracted deliverables will be defined as any loose equipment, spares,
or components (divans, seats, tables, etc.) designed to accommodate a
convertible (alternate) floor plan as identified within the
specification.

	1.2	 	Definitions

	 	 	The following definitions are provided for use in reference to this
specification.
	 
	 	 	“Space Provisions” for a specific installation means that the space only
is allocated for a defined unit or installation. There are no brackets,
bolt holes, wiring, fluid lines or other requirements, including
structural provisions.
	 
	 	 	“Structural Provisions” for a specific installation means that primary
structure is structurally adequate for installation. The brackets, bolt
holes, wiring and fluid lines are not supplied or included as items in
the normal weight of the aircraft.
	 
	 	 	“Power Provisions” for a specific installation, which means that primary
electrical power and distribution systems are of sufficient capacity to
permit later incorporation of specific equipment without modification to
the primary power and distribution system. Power provisions do not
include electrical wiring, hydraulic or pneumatic lines, brackets, bolt
holes, etc. The installation weight for the equipment is not included in
the weight of the aircraft.
	 
	 	 	“Wiring Provisions” for a specific installation means that primary
wiring only is provided and installed (capped and stowed) in the
aircraft. This does not include connector or circuit breaker
installations unless otherwise specified. The weight of wiring
installation will be included in the aircraft weight.
	 
	 	 	“Complete Provisions” for an item of equipment, assembly or installation
means that all detail supports, brackets, fluid lines, tubes and
fittings, electrical wiring and connectors, etc. have been provided so
that the specific equipment can be installed, without alteration or
additional parts. A full continuity check of the system wiring will be
done prior to delivery. The installation weight for equipment used for
testing is not included in the weight of the aircraft.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	2

	1.3	 	Quality and Certification

	 	 	Quality Control (QC) department personnel including Transport Canada (TC)
authorized inspectors will be responsible for all inspection activities
on the aircraft from the initial receiving inspection to final Customer
inspection and delivery. In this capacity, QC will verify that all
measures to preserve the aircraft, fabricate and install the interior to
an approved design, workmanship and safety standards are maintained
during the completion program.
	 
	 	 	The QC department will ensure that the systems, processes and procedures
utilized are in accordance with the TC regulations for proper execution
of the completion activities by all personnel working on the aircraft.
The aircraft and installed assemblies will comply with the relevant
requirements of the certification basis defined as per Transport Canada
Type Certificate A-177.
	 
	 	 	A TC approved Quality Assurance and Quality Control system will be
maintained by the Completion Center and applied to the work performed on
the aircraft.
	 
	 	 	All installations will be approved under TC Supplemental Type
Certificate. The Completion Center will be responsible for obtaining
approval for the interior completion modifications and any required
negotiations with the regulatory authorities.
	 
	 	 	The following configurations** will be approved:

	a.	 	Configuration A: thirteen (13) passenger configuration featuring a mid cabin door at
Fuselage Station 647.08
	 	 	The airplane will be limited to private use only or, if the final
country of registration is the United States, the airplane may not
be used for hire or common carriage;
	 
	b.	 	Configuration B: ten (10) passenger configuration featuring a mid cabin curtain at
Fuselage Station 647.08 which replaces the mid cabin door as a
divider (end cap installed on LHS partition prevents use of mid cabin
door) –
	 	 	There are no limitations on the kinds of operations permitted; and
	 
	c.	 	Configuration C: eight (8) passenger configuration featuring
a mid cabin door at
Fuselage Station 647.08 –
	 	 	There are no limitations on the kinds of operations permitted. The
aft cabin divan and seats will be placarded to indicate they may
not be occupied during takeoff or landing.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	3

	 	 	Note that Transport Canada and FAA exemptions which permit installation
of a mid cabin door and side facing divan(s) limit the kinds of
operations permitted. The above configurations take these limitations
into consideration and are designed to facilitate in-service conversion
by the operator of the airplane to meet FAR Part 135 operations.

The registration information, specifying the aircraft’s final country of
registration, and kind of operations to applicable operating rules for which
approval is required (applicable operating rule) will be customer supplied
during the initial specification definition. This information is also required
to initiate any application for the aircraft’s certification subsequent to
Contract Award. In addition, the customer must identify the configuration of
the airplane (Configuration A, B or C as defined above) to be installed at the
time of delivery.

**Note that modifications to
this Specification may be required in order
to comply with national requirements if the final country of
registration is not the United States or Canada.

This Specification meets the airworthiness requirements of FAR Part 25 and the
equipment requirements necessary for private category operation of the
airplane (FAR Part 91 or CAR 604).

All Completion Center installations will comply with the applicable
requirements for private category operations (FAR Part 91 or Transport Canada
CAR 604) and be capable of flights of 10 hours or less under Part 135
operational requirements.

The airplane will feature wiring provisions only for an in-service conversion
by the operator of the aft cabin to a flight crew sleeping quarters.

The Completion Center will provide a Canadian C of A for export to the United
States.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	4

	1.4	 	Incoming Inspection

	 	 	Upon arrival of the aircraft at the Completion Center, before performing
any work on the aircraft, the following incoming inspection activities
will be performed in accordance with Completion Center standard
practices. The result of any discrepancy or observations on the condition
of the aircraft and equipment therein will be reported to the Customer
and/or the factory.

	A.	 	Documentation of any marred items and/or any discrepancies,
including flight squawks reported by flight crew during ferry flight to the Completion Center.
	 
	B.	 	A visual inspection and detailed inventory of all loose
equipment. The loose equipment will be appropriately stored during completion.
	 
	C.	 	Verification and record of Aircraft fuel and oil quantity at arrival.
	 
	D.	 	System operational and calibration checks.
	 
	E.	 	Measurement of aircraft weight (de-fueled).

	1.5	 	Ferry Equipment

	 	 	The ferry equipment, excluding Customer property, and any other
temporary equipment will be removed from the aircraft upon arrival,
packed and shipped to Bombardier in accordance with the furnished
instructions.

	1.6	 	Preservation and Protection

	 	 	The airframe, engines and APU will be preserved by the Completion Center
in accordance with the manufacturers’ (Bombardier, BMW/Rolls Royce and
Allied Signal) recommended procedures. The Completion Center’s Quality
Control department will verify that all necessary measures to preserve
the aircraft will be suitably maintained during the period of the
aircraft’s inactivity. The Customer will be provided with the documentary
evidence that this has been accomplished.

	1.7	 	Additional Work

	 	 	In the event the Customer wishes to have additional work performed or a
modification made to the approved package, the Completion Center
reserves the right to decide whether it will proceed or not with the
additional work request quotation. If the Completion Center decides to
proceed with the additional work request quotation, the Completion
Center will advise the Customer of the cost, weight and impact on the
schedule that are associated with the additional work request via a
Change Order. The Customer or Representative will provide written
authorization, in signing the Change Order, prior to the Completion
Center proceeding with the work.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	5

	1.8	 	Equipment and System(s) at Risk

	 	 	Any equipment or system(s) that the Customer wishes to have incorporated
in the Specification that is still in a development stage with the
vendor(s), our engineering or the Regulatory Authorities will be
considered “At Risk” and will be/is listed in Annex “D”. The Bombardier
Completion Center reserves the right to determine, at its entire
discretion, if the available data and/or equipment is sufficiently mature
to proceed with the installation of any “At Risk” equipment or system(s).
If and when the Bombardier Completion Center decides to proceed with the
installation of the “At Risk” equipment or system(s), whether it is a
partial or complete installation, it will present to the Customer a
Change Order showing the impact on pricing, weight and delivery schedule,
if applicable. If the Bombardier Completion Center determines that it
will not proceed with the installation of an “At Risk” equipment or
system(s), a Change Order will be issued to delete such equipment or
system(s) from the Specification. Furthermore, the Bombardier Completion
Center reserves the right, at its entire discretion, to delete and/or
disable any “At Risk” equipment or system(s) at the time of delivery of
the Aircraft should such equipment or system(s) not function as intended
and/or are not deemed certifiable by the applicable regulatory agencies.

	1.9	 	Program Status/Customer Access

	 	 	The Completion Center will regularly provide a status report and review
it with the Customer. In addition, the Customer’s representative will
have access to the premises during regular working hours from 8:00 A.M.
to 4:30 P.M. in order to inspect the aircraft and observe the progress
of the work. The Completion Center’s regulations concerning employees
and facilities will be observed by the Customer or Representative.

	1.10	 	Flight Testing

	 	 	Testing/Inspection/Certification for ground and flight tests will be the
responsibility of the Completion Center. The aircraft will be operated
under TC regulations during flight tests. The test program will be
conducted in accordance with Completion Center approved test procedures.
All testing results will be reviewed and/or approved by the Completion
Center. During the flight test program, the Completion Center will
provide the necessary flight crews and ground support equipment that is
required to perform all required certification flight tests.
	 
	 	 	BCC shall assume the cost of fuel and oil consumption during the
completion flight test program that are needed to verify operational
status of Completion Center ‘work’.

	1.11	 	Pre-Delivery

	 	 	The following will be accomplished immediately prior to delivery:

	A.	 	A night lighting check.
	 
	B.	 	Fill the water system and service the lavatories.
	 
	C.	 	Supply the loose equipment/spares referenced in section 16.0.
	 
	D.	 	The Quality Control Certification documents will be reviewed
by both the Customers’ Representative and the Completion Center’s Quality Control
Representative.
	 
	E.	 	Supply documentation referenced in paragraph 1.12.
	 
	F.	 	The aircraft, including the windows, will be cleaned and the interior
groomed.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	6

	1.12	 	Documentation

	 	 	Two (2) sets of the following documentation will be provided to the
Customer by the Completion Center upon delivery of the aircraft. The
overall depth and detail of the information will be to the level necessary
to properly service and maintain items installed by the Completion Center
as part of this Specification, in accordance with Chapter 5 “Global
Express/ Time Limits / Maintenance Checks.”

	A.	 	Documentation (2 books)
	 
	 	 	Contents of Document Binders (2 copies):

	1.	 	Supplemental Type Certificate
	 
	2.	 	Drawing List (Modification List)
	 
	3.	 	Ground Test Procedures
	 
	4.	 	Flight Test Procedures
	 
	5.	 	Flight Manual Supplements
	 
	 	 	Maintenance Manual Supplements
	 
	 	 	Electrical Load Analysis
	 
	6.	 	Material Specification / Interior Accessories List

	B.	 	Drawings – Mechanical Installations (1 book)
	 
	 	 	Contents of Drawing Binders (2 copies):

	1.	 	Layouts
	 
	2.	 	General Arrangements
	 
	3.	 	Placards
	 
	4.	 	Splice Installation / Floor Cuts
	 
	5.	 	Schematics (oxygen and water)
	 
	6.	 	Light Installation – Exterior Access Panel

	C.	 	Wiring Diagrams – Sorted Lists (3 books)
	 
	 	 	Contents of Sorted Lists (2 copies):

	1.	 	Drawing List alphabetically sorted (all drawings)
	 
	2.	 	Drawling List for Wiring Diagrams numerically sorted (criteria WDB/GW)
	 
	3.	 	Wiring Diagrams

	D.	 	Technical Publications

	1.	 	Component Maintenance Manual (1 hardcopy)
	 
	2.	 	Pilots Guide (1 hardcopy) of:
	 
	 	 	Honeywell Primus II Radio System
	 
	 	 	Honeywell Flight Management System
	 
	 	 	Honeywell Digital Weather Radar System
	 
	 	 	Honeywell Lightning Sensor System
	 
	3.	 	Operators & User Guides (1 hardcopy) of:
	 
	 	 	Magnastar C-2000 Airborne Telephone
	 
	 	 	Honeywell SATCOM System
	 
	4.	 	Cabin Handbook Manual (2 CD ROM & 1 hardcopy)
	 
	5.	 	Supplementary Maintenance Manual (2 CD ROM & 1 hardcopy)
	 
	6.	 	Wiring Diagrams (2 CD ROM)
	 
	7.	 	BCC Illustrated Parts Catalog (2 CD ROM)
	 
	8.	 	Grooming Guide (2 hardcopies)

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	7

	B.	 	Quality Assurance/Quality Control Data
	 
	 	 	Two (2) copies (excluding items 8-13) of the following:

	1.	 	Transport Canada 24-0045 Form – Conformity Certificate
	 
	2.	 	Supplemental Type Certificate (STC) / Limited Supplemental Type Certificate (LSTC)
	 
	3.	 	Work Report
	 
	4.	 	Flammability Test Matrix GR26000009, Issue 1 and Fire blocking Test Results (FAA
8110-3) dated TBD Skandia test plan TBD Rev. TBD
	 
	5.	 	BICCM Serialized Equipment List
	 
	6.	 	Weight & Balance Report Appendix A – Equipment List
	 
	7.	 	Time Limits / Maintenance Checks
	 
	8.	 	Compass Deviation Cards (on aircraft)
	 
	9.	 	Update entries for the following (aircraft logbooks):

	•	 	Journey Log Book
	 
	•	 	Engine Log Books (R/H TBD & L/H TBD)
	 
	•	 	Aircraft Battery Log Books (Main TBD & APU TBD)
	 
	•	 	Garrett (Allied Signal) A.P.U. Log Book Serial #TBD
	 
	•	 	Aircraft Technical Log Section 1 – Airframe
	 
	•	 	Aircraft Technical Log Section 2 – Record of Installations & Modifications
	 
	•	 	Serialized List ATA sort (green aircraft)
	 
	•	 	Weight and Balance Report No. RAW-C700-TBD dated TBD (green aircraft)

	10.	 	Flight Manual Supplements added to Flight Manual

	•	 	G-FM35000005 REV NC Gaseous Oxygen System
	 
	•	 	G-FM26000005 REV NC Smoke Detection System, Aft Cabin
	 
	•	 	G-FM25000004 REV NC Interior Completion
	 
	•	 	G-FM24000004 REV NC Cabin Master Power Switch
	 
	•	 	G-FM25280009 REV NC Side Facing Divan
	 
	•	 	G-FM53240005 REV NC Mid Cabin Door

	11.	 	Certificate of Airworthiness {C of A} (country of registration)
	 
	12.	 	Certificate of Registration {C of R} (country of registration)

	C.	 	Contracts Deliverables

	1.	 	Warranty validation cards for third party warrantable equipment.
	 
	2.	 	Six (6) sets of color photographs of the exterior and interior (provided after delivery).
	 
	3.	 	Sound Survey Report.

	1.13	 	Customer Approvals

	 	 	In addition to this Specification, the documents listed in Annex “A” shall
be approved by the Customer.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	8

	1.14	 	Design and Installation Practices

	A.	 	All interior finish materials will be selected for quality,
durability and ease of maintenance with weight as a prime consideration.
The Completion Center reserves the right to substitute components of equal quality should a lack of availability be
documented by the chosen supplier. The Completion Center is not responsible for
variations in dye lots of fabrics or variations in grain and color from the Customer approved
sample, due to the natural properties of these items. Should the Customer select exotic or
custom materials, these upgrades will be processed as additional costs or as a change
order.
	 
	B.	 	The material cost for this specification is based on the guidelines
described in Annex “C”.
	 
	C.	 	Design engineering and the choice of construction materials and
fabrication techniques will be the responsibility of the Completion Center and will be in
accordance with the accepted current aircraft procedures and practices. The size of storage areas
and drawers will be determined by the Completion Center based on available space and
standard size of such items as video cassettes, compact discs, meal trays, flatware, china,
crystal, etc.
	 
	D.	 	The design of all lighting fixtures will be directed toward ease of
lamp replacement.
	 
	E.	 	All passenger information signs, placard instructions related
to seat position, armrests and other instructions, will meet all TC requirements.
	 
	F.	 	All placards will be in the English language and applied on clear
stickers.
	 
	G.	 	In the cockpit, switches, annunciators, controls and
instruments, added as a result of Completion Center installations will be arranged in accordance with the
customer approved cockpit layout.
	 
	H.	 	The interior will be installed in such a manner as to allow
reasonable access to maintenance and inspection items where
practical. All areas requiring inspection will be made accessible
with minimum disturbance to the interior furnishings, based on the
following guidelines:
	 
		 	1. Six (6) month inspection items - access is to be thirty 30 minutes
or less.
	 
	 	 	2. Twelve (12) month inspection items - access is to be sixty 60
minutes or less.
	 
	 	 	3. Line replaceable units - access is to be thirty 30 minutes or less.
	 
	I.	 	Attachment and support structures will be shock mounted where
applicable for acoustical purposes throughout the aircraft. Trim panel fasteners will not be
visible.
	 
	J.	 	Exposed hardware will be plated with 24-Karat gold or
equivalent. Hardware in the category of drawer slides; rollers, door latches, etc. will be
selected and installed to minimize resonance rattling, and to maximize durability and ease of
operation. Hinges on cabinet doors will be concealed . Minimal exposed surface will not
be plated.
	 
	K.	 	Unless otherwise noted, all hard wood and veneer will have a hi-gloss
finish. Custom moldings, murals and artwork are not included in this specification.
Should the customer specify custom moldings, murals and artwork, these items will be
estimated and quoted for approval and/or change order.
	 
	L.	 	All fabrics and materials not inherently flame resistant will be
treated with a fire-retardant protection process. All seat cushions will be fire blocked. The
Completion Center will be responsible for flammability certification of all materials.
	 
	M.	 	The interior of drawers and compartments will be suitably lined and/or
painted per the trim drawings or material specification.
	 
	N.	 	Secondary internal latches will be installed as required by
certification.
	 
	O.	 	Aerospace grade touch-sensitive switches and/or touch-screen LCD
monitors will be used in the cabin. All switches will have symbolic icons where possible;
otherwise the English language will be used.
	 
	P.	 	Any product used in completion of the aircraft for sound dampening,
flame resistance, soil resistance or for any other purpose will be non-corrosive on aircraft
structure and systems.

 

 

	 	 	 	 
	

	Specification No.
	:
	BCC-GX-302

	

	Date
	:
	June 20, 2002

	

	Customer Specific

Amendment 2
	:
	April 29, 2003

	

	Page No.
	:
	9

	2.0	 	SOUNDPROOFING

	 	 	The aircraft will be soundproofed utilizing vibro-acoustic materials and
techniques developed by the Completion Center. The acoustical package
will be designed to achieve the minimum sound levels attainable based on
the selected cabin layouts, trim finishing and within the operating
weight parameters of the aircraft. The aircraft interior shall have
average sound level targets of 52 db SIL (Speech Interference Level) and
70 dBA and average not to exceed levels of 54 db SIL and 72 dBA.
	 
	 	 	The aircraft will be surveyed at FL 450 and at a speed of 0.80 Mach. The
aircraft configuration will be in accordance with the Completion Center
document “Instructions for Aircraft Preparation — Sound Survey” (INS
9000-0233). The aircraft will be serviced in a typical operating
conditions (water-serviced, life rafts on board, galley, wardrobe,
vanities and cabinets stocked, air conditioning on and gaspers turned
off).
	 
	 	 	Noise will be measured at each cabin seat and linear average of all seats
will be calculated to determine the average cabin noise levels. The SIL
measurement will be based upon the arithmetic average of the sound
pressure levels in the 1000, 2000 and 4000 Hz octave bands.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	10

	3.0	 	OXYGEN SYSTEM
	 
	 	 	The aircraft is equipped with four (4) factory installed 50 cu ft oxygen
bottles and an external fill station. The Gaseous Oxygen System is
certified for three (3) crewmembers and nineteen (19) passengers. The
system is approved for cabin altitude up to 40,000 feet. The “green”
aircraft is outfitted with a flight crew supplemental oxygen system. A
passenger distribution system will be installed.

	A.	 	Cockpit Crew System
	 
	 	 	The factory installed crew system with quick donning demand type
full-face masks will be retained.
	 
	B.	 	Oxygen Drop Box
	 
	 	 	Oxygen drop boxes will be installed for each cabin and crew area
seat, jumpseat, the galley area, and lavatories as required. Each
oxygen drop box is equipped with constant flow masks and an
instruction placard.
	 
	C.	 	Oxygen Test Switch
	 
	 	 	An oxygen test switch will be installed in the cockpit on the RHS of
the FS 280 bulkhead. The switch will enable testing of the oxygen
warning system without deploying the passenger oxygen masks.
	 
	D.	 	Therapeutic Oxygen System
	 
	 	 	A therapeutic oxygen shut-off valve will be installed to control
oxygen flow to the outlet. The valve will be activated with an
electrically illuminated switch located on the Oxygen Control panel.
Two (2) therapeutic oxygen outlets will be located on the RHS side of
the aircraft.
	 
	E.	 	Oxygen Warning System
	 
	 	 	An interface with the existing pressure switch will activate the
emergency lights, the “NO SMOKING” sign in the cabin and aural warning
in the cockpit when the oxygen masks are deployed.

	3.1	 	Puritan Bennett “Sweep On” 2000 Masks
	 
	 	 	Two (2) Puritan Bennett “Sweep On” 2000 masks with non-invasive
communication and comfort control harness shall be provided to supplement
existing onboard flight crew oxygen mask system. New disconnect outlets,
two (2) oxygen, two (2) microphones and two (2) mask storage cups shall
be installed in the flight deck to support oxygen equipment. The existing
factory installed full-face masks must be retained.
	 
	3.2	 	Additional Quick Donning Mask (MC-20)
	 
	 	 	An additional MC-20 quick donning mask and storage box will be
installed in the upper section area of the LH entrance enclosure,
complete with disconnect outlets, for one (1) oxygen mask, one (1)
microphone for the jumpseat occupant.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	11

	4.0	 	ENVIRONMENTAL CONTROL SYSTEM (AIR CONDITIONING)
	 
	 	 	The factory-installed air conditioning ducts will be retained and
extended to accommodate the interior and headliner/valance configuration.
All necessary risers and air outlets for the jumpseat, cabin and
lavatories will be installed to complete the conditioned air system and
ensure even cabin air distribution for maximum passenger comfort and
minimum temperature variation within each temperature zone. The system
provides three (3) independently controlled temperature zones: cockpit,
forward cabin and aft cabin.

	A.	 	Cockpit
	 
	 	 	The cockpit air supply system will be retained as installed by the
factory.
	 
	B.	 	Fwd and Aft Cabin-Main Supply
	 
	 	 	The two (2) existing duct’s and distribution systems will be an
integral part of the floor duct design. These systems supply
conditioned air from a floor duct located on each side of the
aircraft. The ducts will direct the airflow either to the appropriate
outflow valves or the ECS system for re-circulation.
	 
	C.	 	Individual Air Outlets
	 
	 	 	Individual adjustable air gaspers will be installed for each seat
position in the passenger service units and will be connected to the
existing air duct. Outlets will also be installed at the jumpseat,
crew area and in both lavatories.
	 
	D.	 	Conditioned Air System Controller
	 
	 	 	The green aircraft conditioned air control will be retained. The
cockpit “master” controller has full temperature and flow range
control over every cabin zone. The cabin temperature controls have
limited control capable of varying around the cockpit set
temperature. Actual cabin temperature will be shown digitally on the
galley control screen. Sensors will be located as per approved layout
drawings.
	 
	 	 	The cabin temperature controls will be located as follows:

	1.	 	For forward cabin, at the forward master seat location control
panel.
	 
	2.	 	For aft cabin, at the aft master seat location control panel.
	 
	3.	 	For both the forward and aft cabin, on the galley control panel.

	E.	 	Galley and Lavatories
	 
	 	 	Conditioned air is supplied through extensions from the main cabin
floor level conditioned air ducts.
	 
	F.	 	Crew Area

Conditioned air is supplied to areas through extensions from the main
cabin floor level air ducts.
	 
	G.	 	Exhaust Fans
	 
	 	 	Exhaust fans will be installed in the following locations:

	1.	 	Outboard of the galley to exhaust heat and odors from the galley
appliances.
	 
	2.	 	Under the floor in the aft step well to remove cold air
from behind the acoustical
curtain.
	 
	3.	 	In both toilet cabinets to exhaust odors from the lavatories.

	H.	 	Gasper Booster Fan
	 
	 	 	A booster fan will be added to the gasper air system.

	4.1	 	Entry Area Heater
	 
	 	 	An entry area heater will be installed to provide additional warm air to
the entry area.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	12

	5.0	 	POTABLE WATER SYSTEM
	 
	 	 	Water will be supplied from the water tanks with two (2) independent
electrical pumps, [one (1) fwd and one (1) aft]. The system will be
designed with heaters installed to avoid freezing. Drainage of the waste
water lines and the fresh water lines (when purging) will be provided
through heated drain masts. The system will provide filtered cold and hot
water to the galley and both lavatories and will incorporate the
following:

	A.	 	Servicing
	 
	 	 	A single exterior service panel will be provided on the right-hand
fuselage for filling both tanks as well as purging both lines and
tanks. A water level indicator will be provided (with lamp test switch
for fwd and aft tanks). An instruction placard for water system
servicing with quantity in liters and gallons will be installed at this
external panel.
	 
	B.	 	Tanks
	 
	 	 	Two (2) tanks will be installed; one (1) thirteen (13) U.S. gallon fwd
and one (1) thirteen (13) U.S. gallon aft. It will also be possible to
fill the tanks manually from inside of the aircraft. Tank assemblies
will each contain a heater blanket to prevent in-flight condensation
from freezing.
	 
	C.	 	Filters
	 
	 	 	Two (2) ultra violet water filters will be installed: one (1) fwd and
one (1) aft located in the galley and aft vanity and will be installed
for easy servicing.
	 
	D.	 	Controls
	 
	 	 	The following controls and indication for the operation of the potable
water system will be accessible through the galley touch screen LCD
monitor:

	1.	 	Water level indicator for each tank.
	 
	2.	 	Two (2) power pump control switches.
	 
	3.	 	Switches for purging of tanks or lines (in-flight and on-ground).
	 
	4.	 	Purging annunciation.

	E.	 	Pressure Sensitive Mats
	 
	 	 	Two (2) pressure sensitive mats (one in each lavatory) will shut off
the water supply when the lavatory is vacant.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	13

	6.0	 	COCKPIT
	 
	 	 	The cockpit area will encompass the area from the forward pressure
bulkhead to the FS 280 bulkhead. The factory outfitted furnishings,
trims, and flight crew seating upholstery will be retained as delivered
to the Completion Center (with the addition of BCC supplied sheepskin
slipcovers as loose equipment). The factory finish will include all
cockpit peripheral (glareshield, trim panels, side consoles).
	 
	6.1	 	Cockpit Headliner
	 
	 	 	A pre-formed one-piece headliner panel extending from the cockpit
bulkhead at FS 280 to the windshield will be retained from the factory
and covered with Customer approved material.
	 
	 	 	The headliner will incorporate:

	A.	 	Lighting (Ref. Section 13.0).
	 
	B.	 	One (1) air gasper.

	6.2	 	Cockpit Holders and Pouches
	 
	 	 	Amenities for the crew will be installed with the following conveniences:

	A.	 	Two (2) leather pencil holders will be installed on the bottom of the
glareshield.
	 
	B.	 	One (1) soft leather pouch will be installed on each side console.
	 
	C.	 	A quickly removable certificate holder attached with Velcro
will be installed on the LHS
FS280 bulkhead.
	 
	D.	 	One (1) pop-out cup holder in each side console will be retained.

	6.3	 	Instrument Placard
	 
	 	 	The following will be engraved and mounted on the instrument panel in
clear view of the pilot and co-pilot:

	A.	 	Aircraft registration number.
	 
	B.	 	SELCAL number.
	 
	C.	 	Aircraft phone numbers.

	6.4	 	Jeppesen Storage Box
	 
	 	 	A hard case box for Jeppesen Stowage will be semi-recessed in the center
access panel at the cockpit entrance.
	 
	6.5	 	Cockpit Flashlights
	 
	 	 	The factory-installed flashlights will be relocated from the side
consoles to the cockpit bulkhead FS 280.
	 
	6.6	 	Cockpit Footrests
	 
	 	 	The existing decorative trim along the base of the instrument panel will
be modified to be a fixed footrest. A block non-skid material shall cover
it.
	 
	6.7	 	Illuminated Approach Chart Holders
	 
	 	 	Illuminated approach chart holders will be mounted on the control yoke
for the pilot and co-pilot.
	 
	6.8	 	115V/60Hz Outlets
	 
	 	 	Two outlets will be installed in the cockpit (one each on the pilot and
co-pilot side consoles) for computer use.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	14

	7.0	 	ENTRY AREA
	 
	 	 	The entrance is defined as the area aft of the FS280 bulkhead,
encompassing the forward crew wardrobe, forward lavatory, entry door,
crew area, and galley.
	 
	7.1	 	Headliner
	 
	 	 	A pre-formed one-piece headliner panel will be installed and covered
with Customer approved materials. The headliner will extend from FS 280
to the forward cabin bulkhead, and will incorporate the following:

	A.	 	Lighting (Ref. Section 13.0).
	 
	B.	 	Galley oxygen drop-box.
	 
	C.	 	Jumpseat oxygen drop-box.
	 
	D.	 	PA speaker.

	7.2	 	Cockpit Curtain
	 
	 	 	A curtain will be installed on a “U” shaped track. The curtain will
track across the cockpit FS 280 bulkhead. The curtain may also be
tracked around the side of the jumpseat and across the aisle behind the
jumpseat. Retainer straps to hold the curtain in the stowed position
will be installed.
	 
	7.3	 	Acoustic Curtain
	 
	 	 	An acoustic curtain will be installed and housed in the LH entrance
enclosure. The curtain will be suspended from a semi-flush-mounted track
recessed in the headliner. The curtain will be secured on the full
length when in the deployed position.
	 
	7.4	 	Airstair
	 
	 	 	The airstair will be completed and will incorporate the following items:

	A.	 	One (1) 4.0” diameter storage compartment for landing gear pins and
flags.
	 
	B.	 	Finishing trims on the lower doorframe.
	 
	C.	 	Ribbed non-skid material on each step.
	 
	D.	 	Lighting (Ref. Section 13.0).

	7.5	 	Jumpseat
	 
	 	 	A vertical stowing jumpseat and approved for take-off and landing will
be installed. The jumpseat will incorporate recline, height and tracking
adjustments capabilities. A safety belt and shoulder harness with a
twist release will be provided.
	 
	 	 	The jumpseat cushions will be upholstered with Customer approved
material. A sheepskin slipcover will be provided as loose equipment.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	15

	7.6	 	Forward Lavatory
	 
	 	 	The forward lavatory will be installed in the entry area, aft of the RHS
cockpit bulkhead. The bulkheads will be covered per the material
specification. A towel bar will be installed on the fwd bulkhead (Ref.
Section 13.0) and a mirror on the aft bulkhead.

	A.	 	Privacy Door and Partition
	 
	 	 	A hinged door with decompression blow out capabilities will be
installed. The door lock will incorporate “break in” emergency
capabilities. A symbolic “No smoking” placard will be installed on the
aisle side. A flush-mounted flip-down ashtray will be installed on
aisle side of the lavatory partition.
	 
	B.	 	Headliner
	 
	 	 	A lavatory headliner will be installed and will incorporate the
following:

	1.	 	One (1) oxygen drop box.
	 
	2.	 	One (1) P/A speaker.
	 
	3.	 	Lighting (Ref. Section 13.0).
	 
	4.	 	Emergency equipment (Ref. Section 15.0).

	C.	 	Lavatory Sidewall
	 
	 	 	The lavatory sidewall will incorporate
the following:

	1.	 	Lighting (Ref.
Section 13.0).

	D.	 	Vanity
	 
	 	 	A vanity with a sink and storage area
will be installed.

 The vanity will
incorporate the following:

	1.	 	One (1) sink and faucet.
	 
	2.	 	A solid surfacing countertop and splashguard.
	 
	3.	 	One (1) soap dispenser.
	 
	4.	 	One (1) hidden 115VAC 60Hz duplex outlet (GFI).
	 
	5.	 	One (1) switch panel with one (1) separate toilet flush switch.
	 
	6.	 	One (1) sealed waste container.
	 
	7.	 	Miscellaneous storage as space permits.
	 
	8.	 	One (1) air gasper.
	 
	9.	 	One (1) facial tissue dispenser.
	 
	10.	 	One (1) concealed toilet paper dispenser.
	 
	11.	 	Conditioned air.
	 
	12.	 	Lighting (Ref. Section 13.0).

	E.	 	Toilet and Enclosure
	 
	 	 	An eight (8) gallon angled chemical toilet will be installed. A
toilet enclosure will be manufactured incorporating the following
features:

	1.	 	One (1) hinged, padded lid with hold open provisions.
	 
	2.	 	One (1) exhaust fan to duct fumes under the floor.
	 
	3.	 	Lighting (Ref. Section 13.0).

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	16

	7.7	 	LH Entrance Enclosure
	 
	 	 	The LH entrance enclosure encompasses the area from the aft cockpit LHS
bulkhead to the main entry door. The aft side of the enclosure will
incorporate an emergency exit sign and a handrail extension.

	A.	 	The upper enclosure will incorporate:

	1.	 	Switch panels.
	 
	2.	 	One (1) compartment with briefcase-style combination lock.
	 
	3.	 	Emergency equipment (Ref. Section 15.0).
	 
	4.	 	Three (3) miscellaneous storage areas.
	 
	5.	 	One (1) oxygen quick donning mask with smoke goggles, for the
jumpseat occupant.
	 
	6.	 	Fuel defuel panel
	 
	7.	 	Jumpseat audio panel

	B.	 	The lower enclosure will incorporate:

	1.	 	One (1) jumpseat and storage area.
	 
	2.	 	One (1) bi-fold nesting door for the jumpseat storage area.
	 
	3.	 	One (1) coat rod.
	 
	4.	 	One (1) bi-fold to close off the wardrobe.
	 
	5.	 	One (1) pop-out drink holder.
	 
	6.	 	Storage for four (4) umbrellas with drip tray.
	 
	7.	 	One (1) 115V dual AC power outlet.
	 
	8.	 	One (1) storage with clip for headset.
	 
	9.	 	Lighting (Ref. Section 13.0).
	 
	10.	 	One (1) acoustic curtain storage behind door.
	 
	11.	 	Emergency equipment (Ref. Section 15.0)
	 
	12.	 	One (1) conformal water tank behind an access panel.
	 
	13.	 	Jumpseat mic jack and PTT switch panel.
	 
	14.	 	Passenger briefing cards storage compartment.
	 
	15.	 	One (1) miscellaneous storage.
	 
	16.	 	One (1) jumpseat reading light switch panel.
	 
	17.	 	Ventilation grille.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	17

	7.8	 	Galley
	 
	 	 	The galley will extend from the forward lavatory aft bulkhead to the
forward cabin bulkhead.

	A.	 	The upper galley will contain:

	1.	 	Crystal storage as space permits for customer furnished crystal.
	 
	2.	 	One (1) galley touch-screen control panel.
	 
	3.	 	One (1) emergency exit sign.
	 
	4.	 	Lighting (Ref. Section 13.0).

	B.	 	The middle galley area will contain:

	1.	 	One (1) microwave oven (0.6 cu. ft.) [black].
	 
	2.	 	One (1) TIA (1601) 10-cup, manual-fill, carafe
coffee maker on pullout tray with
water level indicator.
	 
	3.	 	One (1) 115V AC 60HZ duplex outlet (GFI).
	 
	4.	 	One (1) paper towel dispenser.
	 
	5.	 	Three (3) tambour doors.
	 
	6.	 	One (1) switch for sink drainage.
	 
	7.	 	Linen storage.
	 
	8.	 	Chiller light indicator.
	 
	9.	 	Two (2) slide-out drawers.
	 
	10.	 	Lighting (Ref. Section 13.0).
	 
	11.	 	Two (2) miscellaneous storage shelves.

	C.	 	The lower galley will contain:

	1.	 	A solid surfacing countertop.
	 
	2.	 	One (1) stainless steel sink, faucet and sink cover with cutting
board on reverse.
	 
	3.	 	One (1) miscellaneous drawer under the sink.
	 
	4.	 	One (1) electrical solenoid drain valve with strainer.
	 
	5.	 	One (1) water heater and miscellaneous water system components.
	 
	6.	 	Two (2) pullout work surfaces.
	 
	7.	 	One (1) trash container.
	 
	8.	 	One (1) bottle storage and clean ice drawer with drainage
provision.
	 
	9.	 	One (1) laminated cold storage compartment with
three (3) removable composite
trays/shelves.
	 
	10.	 	One (1) wine and liquor storage drawer with customs seals and
removable insert.
	 
	11.	 	One (1) soda storage drawer with divider in cold storage.
	 
	12.	 	China and flatware storage drawers as space permits for
customer furnished china and
flatware.
	 
	13.	 	Miscellaneous storage as space permits.
	 
	14.	 	One (1) ultraviolet filter.
	 
	15.	 	Conditioned air.
	 
	16.	 	Lighting (Ref. Section 13.0).
	 
	17.	 	One (1) removable dirty dish bin in drawer.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	18

	D.	 	Additionally the galley will include:

	1.	 	One (1) air chiller unit for cooling of selected galley areas.
	 
	2.	 	The window outboard of the galley will have a shade
installed that is identical to the
rest of the cabin shades but will be permanently fixed in the
closed position.

	7.9	 	Galley Annex
	 
	 	 	The galley annex will incorporate the following:

	A.	 	One (l)TIA high temperature oven.
	 
	B.	 	One (1) digital oven controller.
	 
	C.	 	Miscellaneous storage behind a touch latch door.
	 
	D.	 	Miscellaneous storage behind hinged doors.
	 
	E.	 	Tray storage.
	 
	F.	 	One (1) pull-out work surface.
	 
	G.	 	Emergency equipment (Ref. Section
15.0).
	 
	H.	 	Two (2) china storage drawers.
	 
	I.	 	Lighting (Ref. Section
13.0).
	 
	J.	 	Water bottle
storage drawer.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	19

	7.10	 	Crew Area
	 
	 	 	A crew area will be installed aft of the main entry door to the forward
cabin LHS bulkhead.

	A.	 	Bulkheads
	 
	 	 	A bulkhead will be installed to separate the main entry door from the
crew area.
	 
	B.	 	Headliner
	 
	 	 	The headliner will be separate from the entry area headliner and will
incorporate a curtain track for the crew area curtain.
	 
	C.	 	Crew Area Partition and Curtain
	 
	 	 	A crew area partition and curtain will be installed to separate the
area for privacy. The curtain will stow outboard of the partition
against the cabin bulkhead when not in use. The partition will have
an access panel for PMAT cable storage behind the crew area seat.
	 
	D.	 	Passenger Service Unit
	 
	 	 	A passenger service unit (PSU) will be installed between the side
panel and headliner panel and will incorporate the following:

	1.	 	One (1) oxygen drop box.
	 
	2.	 	One (1) P/A speaker.
	 
	3.	 	One (l) air gasper.
	 
	4.	 	Lighting (Ref. Section 13.0).
	 
	5.	 	A handrail along the upper edge.

	E.	 	Sidewall
	 
	 	 	A sidewall will be installed from the PSU to the side ledge and
incorporate manual accordion-type window shades. The windows will
have the slide levers located on the lower edge of the window reveal.
	 
	F.	 	Side Ledge
	 
	 	 	A side ledge will be installed and will incorporate the following:

	1.	 	One (1) switch panel.
	 
	2.	 	Two (2) drink holders.
	 
	3.	 	One (1) storage compartment under a flip-up lid.
	 
	4.	 	One (1) handset under a flip-up lid.
	 
	5.	 	Miscellaneous electrical connectors for PC interface (Ref. Section
11.0).
	 
	6.	 	One (1) receptacle for a 6.5” plug-in touch screen LCD
monitor in the forward drink
holder. {This monitor shall have the same functions as the galley
touch screen.}

	G.	 	Dado Panel
	 
	 	 	The dado panel will extend down from the side ledge and contain the
following:

	1.	 	Hinged storage for PMAT unit.
	 
	2.	 	Lighting (Ref. Section 13.0).

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	20

	H.	 	Storage Cabinet
	 
	 	 	A storage cabinet incorporating shelving will be installed on the aft face
of the forward bulkhead. Shelving of the storage cabinet will be accessible
from the aisle. The cabinet will include the following equipment:

	1.	 	Lighting (Ref. Section 13.0).
	 
	2.	 	Miscellaneous storage as space permits.
	 
	3.	 	A fold-down table.
	 
	4.	 	PMAT connector.

	I.	 	Single Seat-Narrow
	 
	 	 	One (1) forward facing single seat with appropriate emergency equipment
(Ref. Section 15.0) as described in passenger main cabin seating definition
will be installed in the crew area. Floor tracking for berthing capabilities
will be provided.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	21

	8.0	 	PASSENGER MAIN CABIN
	 
	 	 	The approved cabin floor plan outlines the area between the entry area
aft bulkheads and the aft lavatory forward bulkheads.
	 
	8.1	 	Bulkheads
	 
	 	 	Bulkheads will be installed in the following areas of the main cabin:

	A.	 	A RHS bulkhead incorporating a sliding door and one (1)
magazine rack with subwoofer
will be installed to separate the entry area from the main cabin.
	 
	B.	 	A LHS bulkhead incorporating one (1) flush mounted monitor with
IR sensor, one (1)
emergency exit sign, one (1) magazine rack including two (2)
temperature sensors and one
(1) fire extinguisher will be installed to separate the entry area from
the main cabin.
	 
	C.	 	A RHS mid cabin removable upper bulkhead will be installed.
	 
	D.	 	A LHS mid cabin bulkhead incorporating a sliding door, a fire
extinguisher and an exit
sign will be installed.

	 	Note:  	 A removable wood molding cap, that will fit on the
inboard edge of the LH mid cabin bulkhead will be provided as
loose equipment.

	E.	 	A LHS bulkhead incorporating one (1) flush mounted monitor with
IR sensor, two (2)
temperature sensors will be installed to separate the aft wardrobe and
storage cabinet from
the main cabin.
	 
	F.	 	A RHS bulkhead with a hinged door and a retractable header will
be installed to separate
the cabin from the aft lavatory.

	8.2	 	Doors
	 
	 	 	Doors incorporating breakaway and decompression blowout capabilities
will be installed in the following areas of the main cabin.

	A.	 	A sliding pocket door incorporating a retractable footer with
a closeout flapper to be
mounted to the structural bulkhead will be located at the forward
cabin bulkhead. Two (2)
release buttons to close the door will be installed.
	 
	B.	 	A frangible sliding pocket door incorporating a retractable
footer with a closeout flapper
to be mounted to the structural bulkhead will be located at the mid
cabin bulkhead. An
indicator will be shown on the EICAS instrument to show door position.
Two (2) release
buttons to close the door will be installed.
	 
	C.	 	A hinged door with a retractable header will be located at
the aft cabin bulkhead to close
out the lavatory. A positive latch will be installed to hold the door
in the open position. A
door handle and a door lock for privacy with “break in” emergency capabilities will be
installed. A symbolic “NO SMOKING” placard will be installed on cabin side of the
cabin/lavatory door.

	8.3	 	Headliner
	 
	 	 	The headliner will extend from the forward cabin bulkhead to the aft
cabin bulkhead with a split at approximately mid-cabin to facilitate
maintenance. A recessed curtain track will be installed at approximately
F.S 748.00 between the mid cabin bulkheads.
	 
	 	 	Note: A curtain complete with stowing straps will be provided as loose
equipment.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	22

	8.4	 	Passenger Service Units (P.S.U.)
	 
	 	 	A PSU will be installed between the upper sidewall and the headliner,
extending from the forward cabin bulkhead to the aft cabin bulkhead, with
a split to accommodate maintenance access. It will incorporate the
following:

	A.	 	A handrail along the upper edge.
	 
	B.	 	Oxygen masks for each seating position.
	 
	C.	 	Cabin/entertainment system speakers.
	 
	D.	 	Emergency exit sign.
	 
	E.	 	Lighting (Ref. Section 13.0).
	 
	F.	 	Individual adjustable air gasper.

	8.5	 	Sidewall
	 
	 	 	A sidewall will be installed from the PSU to the side ledge and will
incorporate manual accordion-type window shades. The sidewall will
extend from the forward cabin bulkhead to the aft cabin bulkhead, with a
split to accommodate maintenance and removal.
	 
	 	 	A slide lever will be located at the lower edge of each assembly to
operate the shade. The window shades behind the divan will have a slide
lever located at the upper edge of the assembly to operate the shade.

	8.6	 	Side Ledges
	 
	 	 	A side ledge will be installed between the forward cabin bulkhead and
the aft cabin bulkhead and split to accommodate maintenance removal. The
side ledge will incorporate the following:

	A.	 	Two (2) drink holders at each single seat.
	 
	B.	 	One (1) switch panel at each single seat location including outboard
double seat.
	 
	C.	 	One(l) therapeutic oxygen outlet.

	8.7	 	Dado Panels
	 
	 	 	The dado panels will be installed between the lower edge of the side
ledge to the air duct, extending from the forward cabin bulkhead to the
aft cabin bulkhead. The dado will be split to accommodate maintenance
and removal. It will incorporate the following:

	A.	 	Miscellaneous electrical connectors for PC interface (Ref. Section
11.0).
	 
	B.	 	Two (2) telephone handsets: one each at the RHS #2 and LHS #6 master
seat locations.
	 
	C.	 	Emergency equipment (Ref. Section 15.0).

	8.8	 	Floor Covering
	 
	 	 	Custom carpet will be supplied for the entire aircraft, with the
exception of the cockpit area. Floors in the entryway, into the fwd cabin
(to protect avionics bay), lavatories and baggage will be sealed with
protective sheeting to prevent liquids from leaking below onto critical
areas. All floor carpeting will be 100% wool. Weight and design shall be
in accordance with the approved carpet sample. The carpet will be
pre-shrunk and sealed before cutting. It will incorporate an anti-static
backing and it will be serged where required. A carpet underlay will be
installed.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	23

	8.9	 	Magazine Rack
	 
	 	 	Two (2) magazine racks will be installed on each of the RHS and LHS aft
face of the forward cabin bulkheads. The LHS unit will contain the
forward cabin temperature sensors and the forward cabin fire extinguisher
concealed in an enclosure. The RHS unit will house the forward cabin
subwoofer.
	 
	8.10	 	Pull-Out Tables
	 
	 	 	Three (3) bi-fold retractable side ledge tables (27” x 27”) will be
installed per the approved floor plan. The tables will be finished in
accordance with approved material specification.
	 
	8.11	 	Conference Hi-Lo Table
	 
	 	 	One (1) manually operated double pedestal Hi-Lo table (28” x 43”) will
be installed between the double seats. The table will incorporate four
(4) drink holders on the underside of two (2) folding leaves.
	 
	8.12	 	Single Seat – Narrow
	 
	 	 	One (1) AMP single seats with structural approval to 16G will be
installed per the approved floor plan drawing. The seats will
incorporate:

	A.	 	A total of 8.5” in-base fwd and aft tracking and 4.5” in-base lateral
tracking.
	 
	B.	 	Full swiveling capability.
	 
	C.	 	Fully berthable/recline capability.
	 
	D.	 	“Lazy-Boy” legrest.
	 
	E.	 	Storage under flip-up lids located in both armrests.
	 
	F.	 	Color-coordinated approved lap belts and shoulder harnesses.
	 
	G.	 	Overall seat width is 25.5” (upholstered).
	 
	H.	 	Seat width between armrests is 19” (upholstered).
	 
	I.	 	Low back style seat with “breadboard” headrest.
	 
	J.	 	Emergency equipment (Ref. Section 15.0).
	 
	K.	 	Electric inflatable lumbar support.
	 
	L.	 	Lumbar controls on the inboard armrest will incorporate the following
switches:

	1.	 	Off.
	 
	2.	 	Inflate.
	 
	3.	 	Deflate.
	 
	4.	 	Cycle.

	 	Note: 	 The single seat located in the fwd crew area requires
floor tracking for berthing with lever in the outboard armrest. The
main passenger cabin # 2 RHS and # 6 LHS seats will be the Master
Seat Locations. The Customer will be invited for a comfort check of
the seat, at the location of seat buildup and upholstery. The
Customer will be advised of the date four weeks in advance. If the
Customer declines the invitation to participate at the proposed
date, the seat will be upholstered in accordance to the layout and
material specification.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	24

	8.13	 	Wide Seats
	 
	 	 	Six (6) AMP single seats with structural approval to 16G will be installed
per the approved floor plan drawing. The seats will incorporate the
following:

	A.	 	Lazy-boy footrests.
	 
	B.	 	A total of 8.5” in-base fwd and aft tracking and 4.5” in-base lateral
tracking.
	 
	C.	 	Full swiveling capability.
	 
	D.	 	Fully berthable/recline capability.
	 
	E.	 	Color-coordinated approved lap belts and shoulder harness.
	 
	F.	 	Overall seat width is 28.25” (upholstered).
	 
	G.	 	Seat width between armrests is 21.25”
(upholstered).
	 
	H.	 	Low back style seat with “breadboard”
headrest.
	 
	I.	 	Emergency equipment (Ref. Section 15.0).
	 
	J.	 	Electric inflatable lumbar support.
	 
	K.	 	Lumbar controls on the inboard armrest will incorporate the following
switches:

	1.	 	Off.
	 
	2.	 	Inflate.
	 
	3.	 	Deflate.
	 
	4.	 	Cycle.

	 	 	 
	L.	 	Armrest storage under flip-up lids.

	8.14	 	Double Seats
	 
	 	 	Two (2) sets of AMP double seats (one facing forward, one facing aft)
with structural approval to 16G will be installed. The seats will
incorporate the following:

	A.	 	A total of 8.5” in-base forward and aft tracking and 4.5” in-board
lateral tracking.
	 
	B.	 	Swivel capability, inboard seat only.
	 
	C.	 	Full reclining capability.
	 
	D.	 	Color-coordinated lap belts and shoulder harnesses.
	 
	E.	 	Overall seat width is 43” (upholstered).
	 
	F.	 	Retractable 2.00” center armrest.
	 
	G.	 	Low back style seats with “breadboard”
headrest.
	 
	H.	 	Emergency equipment (Ref. Section
15.0).
	 
	I.	 	Electric inflatable lumbar support.
	 
	K.	 	Lumbar controls on the inboard and outboard armrests will
incorporate the following switches:

	1.	 	Off.
	 
	2.	 	Inflate.
	 
	3.	 	Deflate.
	 
	4.	 	Cycle.

	L.	 	Inboard seat switch panels will be installed
under a flip-up lid.
	 
	M.	 	Headset jack in the inboard
armrest below lever.

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	25

	8.15	 	16G Divan
	 
	 	 	One (1) 16G rated berthing divan will be installed per customer approved
drawings. The divan will have an overall frame length of 80.0”. The divan
will have take-off and landing seating for two (2) passengers when the
removable bulkhead is installed and three (3) passengers when it is
removed.
	 
	 	 	The divan will incorporate the following:

	A.	 	Three (3) seat and shoulder harness assemblies.
	 
	B.	 	Berthable to center of aircraft.
	 
	C.	 	Emergency equipment (Ref. Section 15.0).

	8.16	 	Divan End Cabinets
	 
	 	 	Two (2) cabinets will be installed, one at each end of the divan. The
lower edge will have adequate space for conditioned air outlets.

	A.	 	The forward cabinet will have the following:

	1.	 	Two (2) drink holders.
	 
	2.	 	One (1) storage area behind a hinged door with removable shelf.
	 
	3.	 	One (1) switch panel.
	 
	4.	 	One (1) therapeutic oxygen outlet.
	 
	5.	 	One (1) electrical outlet.
	 
	6.	 	Emergency equipment (Ref. Section 15.0).
	 
	7.	 	Lighting (Ref. Section 13.0).
	 
	8.	 	Groove and removable bulkhead attachment.

	B.	 	The aft cabinet will have the following:

	1.	 	One (1) drink holder.
	 
	2.	 	One (1) storage area behind hinged door with removable shelf.
	 
	3.	 	One (1) switch panel.
	 
	4.	 	One (1) permanent ashtray.
	 
	5.	 	One (1) electrical outlet.
	 
	6.	 	Lighting (Ref. Section 13.0).

 

 

	 	 	 	 	 	 	 
	 

	 	Specification No.
	 	:
	 	BCC-GX-302
	

	 	Date
	 	:
	 	June 20, 2002
	

	 	Customer Specific	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003
	

	 	Page No.
	 	:
	 	26

	8.17	 	Credenza and Entertainment Cabinet
	 
	 	 	The credenza and entertainment cabinet will be installed per the approved
floor plan. The lower toe kick area will have adequate space for
conditioned air outlets. The cabinet will have the following:

	A.	 	Entertainment equipment (Ref. section 12.0).
	 
	B.	 	Entertainment control panel on a pullout drawer.
	 
	C.	 	One (1) printer/fax machine (plain paper, NT compatible) on slide-out
tray.
	 
	D.	 	Storage for videocassette’s, DVD and CD disks.
	 
	E.	 	Miscellaneous storage area with drawer.
	 
	F.	 	Miscellaneous storage in the low portion of the credenza.
	 
	G.	 	One (1) fax paper drawer.
	 
	H.	 	Lighting (Ref. Section
13.0).

	8.18	 	Low Cabinet
	 
	 	 	The low cabinet will be installed directly underneath the emergency exit
and will incorporate the following.

	A.	 	Miscellaneous storage.
	 
	B.	 	Lighting (Ref. Section 13.0).

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003
	

	 	Page No.
	 	:
	 	27

	9.0	 	AFT LAVATORY COMPARTMENT AND WARDROBE

	 	 	An aft lavatory and LHS aft wardrobe will extend from the aft cabin
bulkhead to the baggage area bulkhead.

	9.1	 	Bulkheads
	 
	 	 	The aft cabin bulkhead and forward baggage bulkhead will serve as the
lavatory bulkheads. They will incorporate the following:

	 	A.	 	A mirror with contoured vanity lights on the fwd bulkhead.
	 
	 	B.	 	A towel bar on the aft bulkhead.

	9.2	 	Door

	 	 	A hinged door with a fixed header and incorporating blowout capabilities
will be located at the aft lavatory/baggage bulkhead. The door will be
acoustically sealed along the edges to reduce sound transmission. A
positive latch will be installed to hold the door in the open position.

	9.3	 	Headliner
	 
	 	 	The headliner will incorporate two (2) dome lights.
	 
	9.4	 	Passenger Service Unit

	 	 	The passenger service unit (PSU) will incorporate the following:

	 	A.	 	Lighting (Ref. Section 13.0).
	 
	 	B.	 	One (1) dual oxygen drop box.
	 
	 	C.	 	One (1) P/A speaker.
	 
	 	D.	 	One (1) air gasper.
	 
	 	E.	 	Emergency equipment (Ref. Section 15.0).

	9.5	 	Sidewall
	 
	 	 	A sidewall will be installed from the PSU to the vanity and will
incorporate two (2) manual accordion-type window shades. The lavatory
window shades will have a slide lever located at the upper edge of the
assembly to operate the shade.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003
	

	 	Page No.
	 	:
	 	28

	9.6	 	Vanity Cabinet
	 
	 	 	The vanity cabinet will incorporate the following:

	 	A.	 	One (1) stainless steel sink with faucet.
	 
	 	B.	 	A solid surfacing countertop and splash guard.
	 
	 	C.	 	One (1) soap dispenser.
	 
	 	D.	 	One (1) facial tissue dispenser.
	 
	 	E.	 	One (1) concealed toilet paper dispenser.
	 
	 	F.	 	One (1) concealed 115VAC 60Hz duplex outlet (GFI).
	 
	 	G.	 	One (1) switch panel and one (1) separate toilet flush switch.
	 
	 	H.	 	Miscellaneous storage.
	 
	 	I.	 	One (1) water heater.
	 
	 	J.	 	One (1) sealed waste container.
	 
	 	K.	 	One (1) outboard storage under a flip-up lid.
	 
	 	L.	 	Water system.
	 
	 	M.	 	Conditioned air.
	 
	 	N.	 	Magair indicator behind tissue box.
	 
	 	O.	 	Lighting (Ref. Section 13.0).

	9.7	 	Sanitation System (Magair) — Aft Lavatory
	 
	 	 	A Magair vacuum toilet and enclosure with a waste tank capacity of
fifteen (15) gallons will be installed. The following will be
incorporated into the design:

	 	A.	 	A hinged, padded lid with hold open provisions.
	 
	 	B.	 	Storage area with access from the aisle as space permits.
	 
	 	C.	 	Lighting (Ref. Section 13.0).

	9.8	 	Aft Wardrobe and Storage Cabinet
	 
	 	 	An aft wardrobe and storage compartment will be located on the LHS of the
lavatory. The wardrobe and storage cabinet will be enclosed by hinged
doors and incorporate the following:

	 	A.	 	The storage area will contain:

	 	1.	 	One (1) switch panel in the header.
	 
	 	2.	 	Two (2) adjustable shelves.
	 
	 	3.	 	Three (3) fixed shelves.
	 
	 	4.	 	Miscellaneous storage as space permits.
	 
	 	5.	 	Ventilation grill.
	 
	 	6.	 	Lighting (Ref. Section 13.0).

	 	B.	 	The wardrobe will contain:

	 	1.	 	One (1) switch panel in header.
	 
	 	2.	 	One (1) coat rod.
	 
	 	3.	 	Lighting (Ref. Section 13.0).
	 
	 	4.	 	Emergency equipment (Ref. Section 15.0).
	 
	 	5.	 	One (1) fixed shelf.
	 
	 	6.	 	Ventilation grille.
	 
	 	7.	 	Access panel.
	 
	 	8.	 	The windows will have a shade installed that is
identical to the rest of the cabin
window shades but will be permanently fixed in the closed position.

 

	 	 	 	 	 	 	 	 	 
	
	 	Specification No.	 	:	 	BCC-GX-302
	
	 	Date	 	:	 	June 20, 2002
	
	 	Customer Specific	 	 	 	 	 	 
	
	 	Amendment 2	 	:	 	April  29,  2003
	
	 	Page No.	 	:	 	29

	10.0	 	BAGGAGE COMPARTMENT
	 
	 	 	The baggage compartment will extend from the aft lavatory bulkhead to the FS 861 bulkhead.
	 
	 	 	The compartment will incorporate the following:

	 	 	A.	 	Two (2) fold-down shelves with support gussets.
	 
	 	 	B.	 	One (1) baggage net across door.
	 
	 	 	C.	 	One (1) 60” removable hang-up bar.
	 
	 	 	D.	 	Lighting (Ref. Section 13.0).
	 
	 	 	E.	 	Emergency equipment (Ref. Section 15.0).
	 
	 	 	F.	 	One (1) flip-out baggage door flap protective cover for the
floor area and outer fuselage
skin at the loading door with a stainless steel threshold plate.
	 
	 	 	G.	 	One (1) conformal water tank with drip tray behind an access
panel, with miscellaneous
storage inboard.
	 
	 	 	H.	 	A miscellaneous storage area aft of ACPC (depending on options
installed).
	 
	 	 	I.	 	External baggage door lock override (as per section 14.10).
	 
	 	 	J.	 	One (1) LH fold-up hang-up bar.
	 
	 	 	K.	 	An ACPC access panel.
	 
	 	 	L.	 	Conditioned air outlet.
	 
	 	 	M.	 	Storage provisions for removable mid cabin bulkhead.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	30

	11.0	 	AVIONICS - ELECTRICAL SYSTEMS
	 
	 	 	Any new equipment installed to supplement the factory avionics package
will conform to all applicable TC requirements and will be accomplished
in a quality and in a manner which, will meet or exceed industry
standards.
	 
	 	 	SERVICE BULLETINS
	 
	11.1	 	Honeywell MCS6000 Satellite Communications (SATCOM) System (Service
Bulletin)
	 
	 	 	A Honeywell MCS6000 six (6) channel (5 voice, 1 data) satellite
communication system shall be supplied and installed in accordance with
Bombardier Service Bulletin (SB 700-23-001). The system shall provide air
to ground /ground to air telecommunication capabilities using the INMARSAT
satellite network.
	 
	 	 	The installation Service Bulletin shall be carried out in conjunction
with SB 700-23-003 (Office in the Sky) to provide telecommunication/PBX
management functions. Handsets and peripheral equipment facilitating
cabin occupants and crew shall be outfitted as detailed in the “Office
in the Sky” section of the specification.
	 
	 	 	An antenna subsystem shall be installed on the upper rib of the
vertical stabilizer under a radome specifically designed to provide
maximum signal transparency.
	 
	11.2	 	Teledyne C2000 MagnaStar Telecommunication System “Office in the Sky”
(Service Bulletin)
	 
	 	 	Bombardier Service Bulletin (SB 700-23-003) will be installed and
supplemented to provide a functional telecommunications suite to both
the crew and cabin occupants. The system will support up to nine (9)
independent lines (voice, facsimile, PC) positions as identified in the
approved floor plan and provide two (2) UHF air to ground channels via
the GTE Airfone North American ground station network.
	 
	 	 	Four (4) handsets and sonalerts will be installed. One (1) in the
cockpit center pedestal (the volume is to be reduced upon installation),
one (1) in the crew area dado and one (1) each in the dado panel at the
RHS #2 and the LHS #6 seat location.
	 
	 	 	Data ports (RJ11) will be located at each seat grouping on escutcheon
panels per the approved floor plan for fax/modem operation from a
laptop.
	 
	11.3	 	Global Positioning System (GPS)-Addition of a second GPS (GPS 2) (Service
Bulletin)
	 
	 	 	A second Honeywell GPS550 GPS will be installed in accordance with
Bombardier Service Bulletin SB 700-34-005. The #2 GPS will provide
precise a three directional position and velocity data to the on board
Flight Management System(s) (FMS) maintaining FMS integrity in the event
of single GPS failure.
	 
	11.4	 	Flight Data Recorder Modification (FDR/CFMS 2002)- Installation Addition
of Force Transducers
	 
	 	 	This Service Bulletin accomplishes the necessary modifications to flight
data recorder and aircraft, including the installation of additional
force transducers, allowing the flight data recorder (FDR) to record
additional parameters, as required for aircraft manufactured after August
19, 2002 and for those operators who intend to operate their aircraft
under a Far Part 135 Operating Certificate.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	31

	11.5	 	Increase Maximum Take-Off Weight (MTOW) To 98,000 Lbs.
	 
	 	 	This Service Bulletin provides enhanced operational flexibility and allows
increased payload to operators whose interiors are well above an average
completion weight. The service bulletin allows an increase MTOW from
96,000 Ibs to 98,000 Ibs.
	 
	11.6	 	Emergency Location Transmitter (ELT) System (Service Bulletin)
	 
	 	 	An Artex ELT 110-406 will be installed in accordance with Bombardier
Service Bulletin SB 700-25-004. The ELT system will provide search and
rescue (SAR) authorities with an encoded digital message (via satellite)
for 24 hours and an AM frequency locator beacon for approximately 72
hours in the event that the self contained G-switch is activated. The
service bulletin kit will include an exchange cockpit panel that
introduces a switch enabling the flight crew to manually activate (test)
and de-activate the system.
	 
	11.7	 	CAIMS In-Flight Printing Capability (Service Bulletin)
	 
	 	 	The CAIMS in-flight printing capability through the PMAT Bombardier
Service Bulletin SB 700-45-001 is to allow crew access to fault data
while in-flight, and obtain a hard copy of active faults from the cockpit
printer. On the ground, a hard copy of the CAIMS information displayed on
the PMAT can be printed.
	 
	11.8	 	Communication Addressing and Recording System (ACARS) Teledyne Datalink
System (Service Bulletin)
	 
	 	 	One (1) Teledyne data link full aircraft communication addressing and
recording system (ACARS) shall be installed in accordance with
Bombardier Service Bulletin SB 700-23-005. This system shall be used to
display airborne information on the flight management system (FMS)
control display unit (CDU), using either SATCOM, or 3rd very high
frequency (VHF) radio, if installed.
	 
	11.9	 	Honeywell RCZ-833 3rd VHF Transceiver (Service Bulletin)
	 
	 	 	One (1) 3rd RCZ-833 shall be installed in accordance with Bombardier
Service Bulletin SB 700-23-002. This option shall supplement the baseline
dual VHF communication system by providing primary data and standby VHF
voice capability (8.33 MHz). It shall be controlled through FMS CDU and
P-II RMU/AV-850A on primary RSB.
	 
	11.10	 	Miltope Cockpit Printer (Service Bulletin)
	 
	 	 	A cockpit printer will be installed in accordance with Bombardier
Service Bulletin SB 700-23-004 to allow in-flight printing of
active faults accessed through the PMAT.
	 
	11.11	 	Honeywell LSZ-860 Lightning Sensor System – LSS (Service Bulletin)
	 
	 	 	One (1) Honeywell LSZ-860 lightning sensor system, fully integrated
within the Honeywell avionics system shall be installed as per Bombardier
Service Bulletin SB 700-34-003. The lightning sensor system shall be
activated by the LSS switch on the weather radar control panel. Lightning
strike symbols will be used to reflect a lightning activity in an area
and does not reflect a single lightning strike. Lightning strikes symbols
shall be displayed in terms of intensity, range and bearing on the pilot
and co-pilot Multi-Function Display units (MFD) and can be superposed on
a weather map

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003

	

	 	Page No.
	 	:
	 	32

	11.10	 	Thales/Sextant Head-Up Flight Display System (HFDS) CAT II Operations
(Service Bulletin)
	 
	 	 	A Thales/Sextant HFDS shall be installed in accordance with Bombardier
Service Bulletin SB 700-34-002. The installation shall provide a
certifiable system capable of supporting all phases of flight including
manual precision approaches down to CAT II minima with a decision height
of 100 ft. Guidance information shall be echoed by the HGS, using the
modes and commands provided by the existing Automatic Flight Control
System (AFCS).

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	33

	 	 	MISCELLANEOUS AVIONIC SYSTEMS
	 
	11.11	 	Jumpseat Audio Panel
	 
	 	 	A factory supplied jumpseat audio panel will be installed in the LH entrance enclosure.
	 
	11.12	 	Passenger Address System
	 
	 	 	A PA amplifier will be installed to provide announcements and “NO
SMOKING/SEAT BELT” chimes in the cabin. Whenever the PA system is in use,
the entertainment system audio will be muted.
	 
	11.13	 	Cabin Bus Disconnect
	 
	 	 	A cabin power master switch will be installed in the cockpit overhead
panel to shed power to the cabin non-essential systems.
	 
	11.14	 	Ground Service Cabin Power
	 
	 	 	When AC power is provided to the aircraft via the external AC receptacle,
it will be possible to energize the cabin interior by using the ground
service switch at the external service panel and the cabin power switch
on the cockpit overhead panel.
	 
	11.15	 	Cabin/Lavatory Call System
	 
	 	 	A call system will be installed as described below:

	 	A.	 	Chime will ring at the galley position. The galley touch
screen control panel will
graphically indicate the position of the call.
	 
	 	B.	 	A visual annunciation in cockpit for cabin, fwd lavatory and aft
lavatory calls.
	 
	 	C.	 	The crew will be able to reset calls through an annunciator
switch in the cockpit and at the galley.

	11.16	 	Galley/Cabin Circuit Breaker Panel
	 
	 	 	A circuit breaker panel will be installed in the cockpit at LHS FS 280
bulkhead compartment. It will provide power to various systems in the
galley and throughout the cabin.
	 
	11.17	 	Electrical Power
	 
	 	 	One (1) 3500 VA/115VAC/60Hz power converter will be installed in the
avionics bay to provide power for interior installations.
	 
	11.18	 	Electrical Outlets
	 
	 	 	The following 115V AC 60Hz utility outlets will be installed:

	 	A.	 	Two (2) outlets in the cockpit for computer use.
	 
	 	B.	 	Two (2) GFI type outlets rated for hairdryer use, one (1) in each
lavatory.
	 
	 	C.	 	One (1) duplex GFI type outlet will be installed in the galley.
	 
	 	D.	 	Five (5) rated for personal computer use, one (1) in crew
area ledge and four (4) in the
cabin at each seat grouping in the dado panel at the fwd facing seat
position.

	 
	 	E.	 	
One (1) on fwd divan end cabinet.
	 
	 	F.	 	One (1) GFI in fwd crew wardrobe.
	 
	 	G.	 	One (1) on the aft divan end cabinet.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003
	

	 	Page No.
	 	:
	 	34

	11.19	 	Cabin Printer/Fax
	 
	 	 	An NT compatible plain paper printer/fax (HP K80) will be installed in the
credenza on a pullout drawer to enable printing from each selected seat
position. Receptacles will be installed at the crew area dado and at each
of the four (4) seat groupings in the dado on escutcheon panels for
printing from the customer-supplied laptop.
	 
	11.20	 	Additional TRU
	 
	 	 	One (1) additional TRU will be installed to complement required DC power.
	 
	11.21	 	Cockpit Auxiliary Annunciation Panel
	 
	 	 	The cockpit auxiliary annunciation panel shall contain the following:

	 	A.	 	Fax received.
	 
	 	B.	 	Lavatory call.
	 
	 	C.	 	Cabin call.
	 
	 	D.	 	Crew area PA.

	11.22	 	Thales Integrated Electronic Standby Instrument (IESI)
	 
	 	 	The Thales Integrated Electronic Standby Instrument replaces the current
mechanical standby altimeter/airspeed indicator and standby horizon
indicator. The 2.4-inch, 480 millimeter by 480 millimeter high-resolution
display single LRU IESI provides the following information:

	 	•	 	Attitude indicator
	 
	 	•	 	Standard or Baro-corrected altitude
	 
	 	•	 	ILS deviation (LOC and G/S scales)
	 
	 	•	 	Indicated Mach number
	 
	 	•	 	Vmo Information
	 
	 	•	 	Slip/Skid information
	 
	 	•	 	Baro pressure in hPa and/or Hg
	 
	 	•	 	Standby battery

	11.23	 	Honeywell FMS CDU–820’s (Full Installation of 2 Primary units)
	 
	 	 	The two(2) FMS CDU 810’s will be upgraded to FMS CDU 820 status.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	35

	12.0	 	SWITCH PANELS AND ENTERTAINMENT
	 
	 	 	The Baker Electronics Inc., Cabin Management System (CMS) will
incorporate “The Next Generation” aerospace grade control switch panels
and LCD touch screen monitors. All “The Next Generation” switches and the
touch screen panels will be designed to facilitate the passenger and crew
operational and functional tasks with regard to entertainment and cabin
amenities (lighting, call, etc.). All specific functions will be in
accordance with the approved floor plan and switch panel layout drawing.
	 
	12.1	 	Exterior Switches
	 
	 	 	The following switches will be installed in the external AC ground power
panel:

	 	A.	 	A switch for the baggage lighting.
	 
	 	B.	 	A switch for the ground service (pylon) lights.

	 	 	 	The following switch will be installed on the main door
closure access panel:

	 	A.	 	A switch for the airstair lights.

	12.2	 	Audio System
	 
	 	 	An audio system will be installed to present audio through cabin
speakers and/or stereo headsets from all available audio sources, which
will incorporate a digital graphic equalizer. Speakers will be wired
such that the cabin is divided into forward and aft sections at
approximately the emergency exit area and controlled separately for
volume. The system will incorporate the following:

	 	A.	 	Eight (8) speakers.
	 
	 	B.	 	Three (3) subwoofers.
	 
	 	C.	 	One (1) headphone distribution amplifier.
	 
	 	D.	 	One (1) integrated chime/page amplifier.
	 
	 	E.	 	One (1) CD multi-disk changer.
	 
	 	F.	 	Audio power amplifier(s) to suit cabin configuration.
	 
	 	G.	 	Two (2) infrared remote controls; one (1) stowed at each master seat.
	 
	 	H.	 	Four (4) PA speakers will be located in both lavatories, crew area and
galley areas.

	12.3	 	Video System
	 
	 	 	A video system will be installed to display movies and other video
information. Each of the monitors will be able to independently display
any available video source. The video system will incorporate:

	 	A.	 	Two (2) 21.3” LCD monitors:

	 	1.	 	One (1) aft facing on the LHS forward cabin bulkhead.
	 
	 	2.	 	One (1) fwd facing on the LHS aft cabin bulkhead.

	 	B.	 	One (1) 5.6” LCD monitor (cockpit).
	 
	 	C.	 	One (1) 10.4” touch screen LCD monitor (galley).
	 
	 	D.	 	One (1) plug-in 6.5” touch screen LCD monitor.
	 
	 	E.	 	One (1) VHS Video Cassette Player (multi standard format).
	 
	 	F.	 	One (1) DVD player.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	36

	12.4	 	The “Airshow Network” Flight Information System
	 
	 	 	An Airshow Network cabin display system will be installed. The system
combines the graphic capabilities of the installed Data Communications
Unit (DCU) with onboard avionics and telecommunication systems to provide
updated flight, business, and leisure information over the video display
system to the cabin occupants.
	 
	 	 	Information (business, weather, etc.) requested on the Airshow Network
will be transmitted from the subscription supported Airshow
Communication Center (ACC) ground station to the aircraft via the
onboard telephone systems.
	 
	 	 	A single Airshow Flight Deck Controller will be installed in the cockpit
in accordance with the cockpit layout drawing. The controller will
provide the crew with time to destination updating capabilities and audio
briefing cueing. The crew can access NEXRAD radar summaries from WSI
Corporation to be displayed on the 5.6” cockpit monitor. An infrared
mouse will be provided as part of each Baker Electronics remote control,
stored in the ledge at the two (2) master seat locations under flip-up
lids.
	 
	 	 	The DCU incorporates a customized CD-ROM to provide the following
presentation:

	 	A.	 	Flight information data (maximum 6 pages x 4 lines maximum per page - English text).
	 
	 	B.	 	Worldwide map coverage (6 geographical regions - English text).
	 
	 	C.	 	Relative location indicator (RLI - closest cities look-up).
	 
	 	D.	 	Static graphic logo (customized artwork required).
	 
	 	E.	 	3D perspective maps (horizontal “edge-view” terrain).
	 
	 	F.	 	Aural audio briefing (4 standard briefings).
	 
	 	G.	 	One (1) Metropolitan area super high-resolution map.
	 
	 	H.	 	“No Smoking” and “Fasten Seat Belt” graphics.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003

	

	 	Page No.
	 	:
	 	37

	13.0	 	LIGHTING
	 
	13.1	 	Airstair and Boarding Lights
	 
	 	 	Boarding lights, powered by the battery direct bus, will be powered if the
main cabin door is open. The boarding light system will activate the
following:

	 	A.	 	One (1) recessed light on each of airstair step riser (factory installed).
	 
	 	B.	 	Two (2) flush-mounted lights in the airstair step-well.
	 
	 	C.	 	One (1) entry area headliner light.
	 
	 	D.	 	One (1) aft lavatory headliner light.
	 
	 	E.	 	Two (2) cockpit dome lights.

	13.2	 	Cockpit Lights

The cockpit headliner will incorporate the following lights:

	 	A.	 	Three (3) dome lights in the cockpit headliner controlled by
the boarding light switch or
by integral switches powered from the main DC bus.
	 
	 	B.	 	One (1) jump seat reading light.
	 
	 	C.	 	Two (2) dimmable map lights in the cockpit headliner.

	13.3	 	Entrance Area Headliner Lights
	 
	 	 	Entry area headliner will incorporate the
following lights:

	 	A.	 	Three (3) dome lights:

	 	1.	 	The fwd and mid dome lights are also connected to the emergency
lighting system.
	 
	 	2.	 	The dome lights will be powered by cabin DC feed and
controlled by a switch in the
LH entrance enclosure.
	 
	 	3.	 	The mid dome light will also be connected to the boarding lights.

	13.4	 	LH Entrance Enclosure Light

	 	A.	 	The lower portion of LH entrance enclosure will incorporate
one (1) flush-mounted dome light.

	13.5	 	Forward Lavatory Lights

	 	A.	 	Mirror lights (BRT/DIM).
	 
	 	B.	 	One (1) dome light in headliner.
	 
	 	C.	 	Upwash lights (BRT/DIM).

	13.6	 	Galley Lights

	 	A.	 	Work lights (white) to illuminate counter top (BRT/DIM).
	 
	 	B.	 	Work lights (red) to illuminate counter top (ON/OFF).
	 
	 	C.	 	Effect lights outboard of crystal storage.
	 
	 	D.	 	Upper lights located in the headliner (BRT/DIM).

	13.7	 	Crew Area Lights

	 	A.	 	One (1) reading light in the PSU.
	 
	 	B.	 	Two (2) table lights in the PSU.
	 
	 	C.	 	Downwash lights concealed outboard of the PSU lower portion.
	 
	 	D.	 	Upwash lights concealed outboard of the PSU upper portion.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	38

	13.8	 	Cabin Upwash and Downwash Lights
	 
	 	 	Forward and aft cabin lighting will be separately controlled. Cabin
upwash and downwash lights will consist of two (2) rows of fluorescent
tubes, installed on both sides of the cabin.

	 	A.	 	Upper lights will be concealed between the upper portion of the PSU and
headliner.
	 
	 	B.	 	Lower lights will be concealed between the lower portion of the
PSU panel and the sidewall.

	13.9	 	Cabin Reading and Table Lights
	 
	 	 	Individually controlled reading lights and table lights will be located in
PSU’s.

	 	A.	 	One (1) reading light for each seat position.
	 
	 	B.	 	One (1) reading light for each divan seat location.
	 
	 	C.	 	Two (2) table lights for each table.
	 
	 	D.	 	Three (3) lights for the credenza.

	13.10	 	Floor Accent Lights

	 	A.	 	Fwd vanity and toilet enclosure toe kick space.
	 
	 	B.	 	Aft vanity and toilet enclosure toe kick space,
	 
	 	C.	 	Aft wardrobe and storage cabinet.
	 
	 	D.	 	In galley and galley annex toe kick space.
	 
	 	E.	 	Along the air ducts on both sides of the cabin.
	 
	 	F.	 	Along the air duct of the crew area.
	 
	 	G.	 	In the credenza and low cabinet toe kick space.
	 
	 	H.	 	Divan end cabinets.

	13.11	 	Entertainment Compartment Light
	 
	 	 	A light will be installed to illuminate the entertainment equipment area.
The light will be controlled by opening the entertainment compartment
door.

	13.12	 	Aft Lavatory Lights

	 	A.	 	Two (2) dome lights will be installed in the headliner
centerline. The aft dome light will
be wired to the boarding light system.
	 
	 	B.	 	Fluorescent light tubes will be installed in the mirror light
enclosure (BRT/DIM).
	 
	 	C.	 	Upwash lights concealed between upper portion of the PSU and headliner
(BRT/DIM).
	 
	 	D.	 	Downwash lights concealed between of lower portion of the PSU
and the sidewall (BRT/DIM).

	13.13	 	Wardrobe Light
	 
	 	 	One (1) flush-mounted dome light will be installed in the wardrobe enclosure.
	 
	13.14	 	Baggage Compartment Lights
	 
	 	 	Three (3) caged dome lights will be installed in the baggage headliner.
The lights will be controlled by a switch on the aft wardrobe header. The
lights will also be controlled by a switch in the AC ground power panel.
Each of these switches will turn on the baggage lights indefinitely
unless the aircraft is on battery power, at which time, after twenty (20)
minutes, they will automatically turn-off.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	39

	13.15	 	Cabin Ordinance Signs

	 	A.	 	Six (6) illuminated “NO SMOKING/FASTEN SEAT BELT” ordinance
signs will be
installed in the main cabin. Three on each side between seat groupings.
	 
	 	B.	 	One (1) “RETURN TO SEAT” and one (1) permanently lighted “NO
SMOKING”
ordinance sign will be installed in the forward lavatory.
	 
	 	C.	 	One (1) “RETURN TO SEAT” and one (1) permanently lighted “NO
SMOKING”
ordinance sign will be installed in the aft wardrobe header.
	 
	 	D.	 	One (1) illuminated “NO SMOKING/FASTEN SEAT BELT” ordinance
sign will be installed in the crew area.

	13.16	 	Cabin Emergency lights
	 
	 	 	Power supplies/battery packs and emergency lights will be installed as
required by FAR.

	 	A.	 	Exit signs (at exits and on bulkheads as locators).
	 
	 	B.	 	Lighting in the PSU (general cabin illumination).
	 
	 	C.	 	Lighting in the fwd and mid entry dome lights.

	13.17	 	Escape Path Lights
	 
	 	 	Emergency escape path lighting will be installed to meet TC
requirements. They will be installed on the inboard face of selected
seat bases as well as selected bulkheads in the cabin, the entry area
and at the emergency exit.

	13.18	 	Exterior Service Panel Lighting
	 
	 	 	Exterior service panel lighting will be installed to the following
location:

	 	A.	 	Fwd and aft lavatory service station panels.
	 
	 	B.	 	Fresh water fill station panel.
	 
	 	C.	 	Hydraulic access panel.
	 
	 	D.	 	Fuel fill service station panel.
	 
	 	E.	 	Oxygen service panel.
	 
	 	F.	 	Fwd ground service comm. panel.
	 
	 	G.	 	AC ground power panel.

	13.19	 	Pylon Lights
	 
	 	 	Lights will be installed on the underside of the engine pylons. The
lights will be controlled by switches in the following locations: the AC
ground power panel and the aft lavatory wardrobe header. Each switch will
turn on both pylon lights indefinitely unless the aircraft is on battery
power at which time, after twenty (20) minutes they will automatically
turn off.

	13.20	 	Pulse Landing Light System
	 
	 	 	One (1) landing light pulse system, that pulsates the existing landing
lights to enhance aircraft recognition, shall be installed. Pulsating
lights attract attention and can be a key factor in collision avoidance.
The crew shall be able to select the landing light control switch either
in STEADY or PULSE mode.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	40

	13.21	 	Wheel Well Maintenance Lights
	 
	 	 	The production installed system comprised of nose landing gear light and
external switch with timer will be modified to add one (1) light in each
main landing gear well (LHS and RHS) incorporating connection to the
existing external switch.
	 
	13.22	 	Wingtip Taxi Lights
	 
	 	 	Wingtip taxi lights to illuminate the taxiway on forward and downward
focus will be installed under the wing at the outboard edge, next to the
strobe light. These lights will be controlled by a separate switch in the
cockpit overhead panel.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	41

	14.0	 	MISCELLANEOUS INSTALLATIONS
	 
	 	 	SERVICE BULLETINS
	 
	14.1	 	Additional Refuel/De-fuel Panel (Service Bulletin)
	 
	 	 	A refuel/de-fuel panel will be relocated in the lower position of the LHS
entrance enclosure.
	 
	14.2	 	Tail Logo Light Illumination (Service Bulletin)
	 
	 	 	Two (2) lights will be installed on the lower horizontal stabilizer in
accordance with Bombardier Service Bulletin SB 700-33-001. One (1) light
will be installed on each side of the vertical stabilizer.
	 
	 	 	The service bulletin kit will include an exchange cockpit panel to
introduce a logo on/off switch to the flight crew on the “External
Lights” panel.
	 
	14.3	 	Single Additional Aft Cabin Window (Service Bulletin)
	 
	 	 	An additional cabin window will be installed at RS FS788 in accordance
with Bombardier Service Bulletin SB 700-56-001 (Service Bulletin Kit
700K56-001 A).
	 
	 	 	OTHER MISCELLANEOUS INSTALLATIONS
	 
	14.4	 	External Toilet Servicing
	 
	 	 	An overboard-servicing system for each toilet will be connected to
enable the operator to service the unit from outside the aircraft. The
systems will incorporate quick disconnects. The external outlets will be
of the appropriate size to enable utilization of a standard airline
service cart.
	 
	 	 	An instruction placard (in liters and gallons) for servicing the
lavatory systems will be installed in the lavatory servicing
compartments.
	 
	14.5	 	Towbar Assembly
	 
	 	 	Complete provisions will be installed in the aft equipment bay for a
three piece Tronair towbar assembly including a 2 3/16” diameter towing
eye.
	 
	14.6	 	Ladder Storage
	 
	 	 	Complete provisions for an “Echellex” ladder will be incorporated in the
aft equipment bay.
	 
	14.7	 	Aft Equipment Bay Storage Box
	 
	 	 	A storage box (maximum 30 Ibs.) shall be installed on the aft
equipment bay catwalk. The box will be 8”(wide) x 10”(high) x
19”(long).

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April 29, 2003

	

	 	Page No.
	 	:
	 	42

	14.8	 	Catwalk Battery Access
	 
	 	 	Access will be made available through the catwalk in order to disconnect
the main battery easily.
	 
	14.9	 	Handrail Extension
	 
	 	 	A handrail extension will be installed on the fwd side of the airstair in
accordance with the Supplemental Type Certificate.
	 
	14.10	 	Common Key Panels
	 
	 	 	The external doors will have a common key for all locks:

	 	 	 	 	 
	Main entry

	 	Baggage
	 	Aft equipment compartment
	Ground communication

	 	Aft hydraulic access
	 	Oxygen service
	Refuel/de-fuel

	 	AC external power
	 	Aft water service
	Fwd lavatory service

	 	DC external power
	 	Aft lavatory service
	

	 	 	 	High pressure pneumatic door

	14.11	 	Aft Equipment Bay Access Ladder
	 
	 	 	An access ladder to gain entry to the aft equipment bay will be installed.
	 
	14.12	 	External Baggage Door Lock Override
	 
	 	 	When the door is locked from the outside, it can be opened from the
inside by depressing and holding a button near the handle. This allows
the door operating mechanism to bypass the locking feature, thereby
opening the door. When the door is then shut and the handle closed the
button springs out and the door remains locked. The door will always be
locked until unlocked from the outside.
	 
	14.13	 	Cockpit Trim Panels
	 
	 	 	Existing cockpit trim panels will be reinforced and reupholstered in
leather in accordance with SRPSA#TBD.

 

 

	 	 	 	 	 	 	 	 	 
	

	 	Specification No.
	 	:
	 	BCC-GX-302

	

	 	Date
	 	:
	 	June 20, 2002

	

	 	Customer Specific	 	 	 	 	 	 
	

	 	Amendment 2
	 	:
	 	April  29, 2003
	

	 	Page No.
	 	:
	 	43

	15.0	 	EMERGENCY EQUIPMENT
	 
	15.1	 	Cockpit

	 	A.	 	One (1) Halon fire extinguisher (factory supplied) will be
installed on fwd face of RHS
FS280 bulkhead.
	 
	 	B.	 	One (1) portable breathing equipment PBE (factory supplied).
	 
	 	C.	 	One (1) crash axe (factory supplied) with a leather cover will
be installed on the fwd face
of the RHS FS280 bulkhead.
	 
	 	D.	 	Two (2) crew life vests will be retained, one (1) under pilot
and one (1) under co-pilot
seat.
	 
	 	E.	 	Two (2) flashlights with holders retained from factory and relocated to
FS280.

	15.2	 	LH Entrance Enclosure
	 
	 	 	One (1) laminated emergency equipment location card.

	 	A.	 	One (1) first aid kit.
	 
	 	B.	 	One (1) crew life vest with storage pouch.
	 
	 	C.	 	One (1) engraved Maglite flashlight.

	15.3	 	Crew Area

	 	A.	 	One (1) crew life vest with storage pouch.

	15.4	 	Galley

	 	A.	 	One (1) life raft located in the lower galley annex.

	15.5	 	Cabin

	 	A.	 	One (1) passenger life vest located at each seat base.
	 
	 	B.	 	Three (3) passenger life vests for the divan occupants.
	 
	 	C.	 	One (1) life raft (Winslow, 12-man) located under the divan.
	 
	 	D.	 	One (1) over wing emergency escape lanyard.
	 
	 	E.	 	Two (2) therapeutic masks and 12 ft oxygen hoses each with a
nebulizer and an adjustable
flow meter will be stowed in RHS forward divan armrest cabinet.
	 
	 	F.	 	Two (2) Halon fire extinguisher: one (1) under the fwd LHS
magazine rack and one (1) on the FS 647 blkd fwd face LHS.

	15.6	 	Lavatories

	 	A.	 	Two (2) smoke detectors (same type as Section 15.6).

	15.7	 	Aft Wardrobe/Storage
	 
	 	 	The aft wardrobe will contain:

	 	A.	 	One (1) Halon fire extinguisher.
	 
	 	B.	 	One (1) portable breathing equipment (PBE).
	 
	 	C.	 	One (1) smoke detector (same as Section 15.7).

	15.8	 	Baggage Area
	 
	 	 	An electronic type smoke amplifier/detector will be installed, which will
provide an aural and visual warning to cockpit and allow preflight
testing from cockpit prior to flight. The crew will be able to silence
aural warning (push-to-mute); however, visual warning must remain
illuminated until unit resets itself.

 

 

	 	 	 	 	 	 	 
	Specification No.

	 	:
	 	BCC-GX-302

	Date

	 	:
	 	June 20, 2002

	Customer Specific
	 	 	 	 	 	 
	Amendment 2

	 	:
	 	April 29, 2003

	Page No.

	 	:
	 	44	 	 

	16.0	 	LOOSE EQUIPMENT AND SPARES
	 
	16.1	 	Loose Equipment
	 
	 	 	The following items will be provided as loose equipment:

	 	A.	 	Twenty-five (25) passenger briefing cards.
	 
	 	B.	 	One (1) oxygen demo unit and one (1) seat belt demo unit.
	 
	 	C.	 	Three (3) seat belt extensions, one (1) sleeping belt.
	 
	 	D.	 	Three (3) lap trays.
	 
	 	E.	 	Four (4) golf size umbrellas.
	 
	 	F.	 	Eighteen (18) coat hangers.
	 
	 	G.	 	Eighteen (18) stereo headsets with 90 degree connectors
and pouches.
	 
	 	H.	 	One (1) self-inflating air mattress for conference
group.
	 
	 	I.	 	One (1) self-inflating air mattress for crew rest seat.
	 
	 	J.	 	Ten (10) throw rugs will be provided. Four (4) for the
entry area and six (6) for use between the single seats.
	 
	 	K.	 	Maintenance runners for entry area, passenger cabin and aft
lavatory. The runners will be secured in place.
	 
	 	L.	 	Maintenance covers for all crew and passenger seating.
	 
	 	M.	 	One (1) water filling station adapter hose with pouch.
	 
	 	N.	 	Three (3) keyed locking fuel caps will be provided.
	 
	 	O.	 	One (1) emergency exit lock pin and warning flag.
	 
	 	P.	 	One (1) ladder.
	 
	 	Q.	 	One (l) towbar assembly.
	 
	 	R.	 	Two (2) Rosen cockpit sunvisors factory supplied).
	 
	 	S.	 	Two (2) crew headsets (factory supplied).
	 
	 	T.	 	One (1) jumpseat headset (factory supplied).
	 
	 	U.	 	One (1) jumpseat sheepskin slipcover.
	 
	 	V.	 	Two (2) crew seat sheepskin slipcovers.
	 
	 	W.	 	One (1) electric pump (115VAC/60Hz) for the manual fill of water tanks
with pouch.
	 
	 	X.	 	Two (2) cabin management systems (CMS) infrared remote controllers.
	 
	 	Y.	 	One (l)PMAT unit.
	 
	 	Z.	 	One (1) PMAT cable storage will be provided in a leather pouch.
	 
	 	AA.	 	One (1) removable wood molding cap, that will fit on the
inboard edge of the LH mid cabin bulkhead.
	 
	 	BB.	 	One (1) curtain complete with stowing straps, that will fit
between the mid cabin bulkheads.
	 
	 	CC.	 	One (1) plug-in 6.5” touch screen LCD monitor in a leather pouch.
	 
	 	DD.	 	One (1) four button monitor adjustment tool for each type of monitor.

	16.2	 	Spares
	 
	 	 	The following spares will be provided by the Completion Center:

	 	A.	 	One (1) interior spares kit consisting of:

 

	 	 	 	 	 	 	 
	Specification No.

	 	:
	 	BCC-GX-302

	Date

	 	:
	 	June 20, 2002

	Customer Specific
	 	 	 	 	 	 
	Amendment 2

	 	:
	 	April 29, 2003

	Page No.

	 	:
	 	45	 	 

	 	1.	 	One (1) switch repair kit.
	 
	 	2.	 	Two (2) latches of each type with an installed quantity greater
than two.
	 
	 	3.	 	Two (2) sets of material to cover airstair steps.

	 	B.	 	One (1) interior cleaning and grooming kit.

	 	1.	 	Two (2) bulbs of each type.
	 
	 	2.	 	Two (2) fluorescent tubes of each type with an installed quantity
greater than two.
	 
	 	3.	 	Twenty (20) additional rubber inserts for drink holders.

	 	C.	 	Touch-up kits for the following:

	 	1.	 	Wood finishes.
	 
	 	2.	 	Interior finishes.
	 
	 	3.	 	Exterior paints.

	 	D.	 	Eight (8) sets of keys for the aircraft.

 

 

	 	 	 	 	 	 	 
	Specification No.

	 	:
	 	BCC-GX-302

	Date

	 	:
	 	June 20, 2002

	Customer Specific
	 	 	 	 	 	 
	Amendment
2

	 	:
	 	April 29, 2003

	Page No.

	 	:
	 	46	 	 

	17.0	 	EXTERIOR PAINT
	 
	 	 	The paint application process shall be carried out as per the Completion
Center procedures and handbook in line with the recognized manufacturer
and/or industry practices and certification requirements. The aircraft
detailed paint shall be done in accordance with the approved drawings.
	 
	 	 	The following provisions and/or requirements are still TBD:

	 	A.	 	The aircraft exterior paint will be one (1) single color,
non-metallic base paint with two
(2) additional straight stripes shown on fuselage nacelles and
winglets.
	 
	 	B.	 	The paint will consist of an Epoxy primer and a Polyurethane topcoat.
	 
	 	C.	 	Registration marking shall be painted in one (1) color.
	 
	 	D.	 	The aerodynamic sealant on all leading edges (except on engines
leading edges as per
O.E.M) will be removed before paint. The sealant will be reinstalled
after the paint
process and painted where it does not come into contact with the
leading edge.
	 
	 	E.	 	The landing gear shall be retained as received from the factory (Grey).
	 
	 	F.	 	Composite materials coated with an anti-static paint shall be
retained as received from the
factory.
	 
	 	G.	 	The main entrance door, the baggage door, edges and frames will be
painted.
	 
	 	H.	 	The latches on any access panel i.e., the avionics compartment,
radome, engine, hydraulic
pump access covers shall be retained as original finish.
	 
	 	I.	 	The airstair at the main entrance will be painted as the same color
of the bottom of the
fuselage.
	 
	 	J.	 	The inside of all service door panels, the inside of all modified
fairing and compartments
shall be painted in the same color as the aircraft fuselage.
	 
	 	K.	 	The original bright work on the aircraft exterior will be highly
polished. This includes the
vertical stabilizer, wing, engines and horizontal stabilizer leading
edges.
	 
	 	L.	 	The cockpit window surrounds will remain as delivered per
manufacturer finish.
	 
	 	M.	 	A 3M plastic erosion protective plastic will be installed over the
radome after paint,
winglet leading edges and lenses and the
horizontal tips.
	 
	 	N.	 	All exterior markings will be done by
the silk-screen method.

 

 

	 	 	 	 	 	 	 
	Specification No.

	 	:
	 	BCC-GX-302

	Date

	 	:
	 	June 20, 2002

	Customer Specific
	 	 	 	 	 	 
	Amendment 2

	 	:
	 	April 29, 2003

	Page No.

	 	:
	 	47	 	 

	18.0	 	WEIGHT AND BALANCE AND CENTER OF GRAVITY
	 
	 	 	Aircraft will be weighed during Incoming Inspection in accordance with
approved procedures to verity incoming (empty fuel) weight and balance.
Any significant deviations will be submitted to the Customer.
	 
	 	 	The aircraft will be weighed upon completion. A Weight and Balance Report
including loading charts and an equipment listing will be provided as
required by regulations.
	 
	 	 	The completion weight allowance outlined in this specification will not
exceed the estimated weight and balance and is based on a plus or minus
five percent tolerance in accordance with the Weight and Balance
Estimate, Document No. TBD dated TBD.
	 
	 	 	Full Fuel Loading
	 
	 	 	Will consist of all operating items as specified in the estimated weight
and balance document, allowable forward seated passengers and a baggage
allowance of 30 Lbs. per passenger with the full fuel to maximum ramp
weight.
	 
	 	 	Full Passenger Loading
	 
	 	 	Will consist of all operating items as specified in the estimated weight
and balance document, full passengers, and jumpseat occupant, a baggage
allowance of 30 Lbs. per passenger and allowable fuel to maximum ramp
weight.

 

 

	 	 	 	 	 	 	 
	Specification No.

	 	:
	 	BCC-GX-302

	Date

	 	:
	 	June 20, 2002

	Customer Specific
	 	 	 	 	 	 
	Amendment 2

	 	:
	 	April 29, 2003

	Page No.

	 	:
	 	48	 	 

	19.0	 	ANNEX “A” LIST OF BOMBARDIER FORMAT LAYOUT AND TRIM DRAWINGS

	 	 	 	 	 
	 	 	DRAWING	 	 
	TITLE
	 	NUMBER
	 	ISSUE

	Floorplan

	 	GP 1305-0001
	 	D
	Fwd Lavatory

	 	GP 1305-0002
	 	A
	LH Entrance Enclosure

	 	GP 1305-0003
	 	B
	Galley Layout

	 	GP 1305-0004
	 	A
	Crew Area

	 	GP 1305-0005
	 	C
	Aft Wardrobe Layout

	 	GP 1305-0006
	 	A
	Aft Lavatory Layout

	 	GP 1305-0007
	 	C
	Credenza Cabinet Layout

	 	GP 1305-0008
	 	C
	Bulkhead Sections

	 	GP 1305-0010
	 	C
	Divan Layout

	 	GP 1305-0011
	 	A
	Sideledge, Table & Dado Layout

	 	GP 1305-0012
	 	B
	Seats

	 	GP 1305-0017
	 	B
	PSU, Headliner & Sidewall Layout

	 	GP 1305-0019
	 	A
	Cockpit Instrument Layout

	 	GP 1305-0020
	 	A
	Cabin Switch Panel Layout

	 	GP 1305-0021
	 	B
	Cockpit Trim

	 	GP 1305-0022
	 	A
	External Paint Layout

	 	GP 1305-0024
	 	A
	Carpet Detail Layout

	 	GP 1305-0025
	 	B
	Material Specification

	 	FSB1305-0601
	 	B
	Accessories List

	 	FSB 1305-0623
	 	A
	Loose Equipment List

	 	FSB1305-0624
	 	A
	Pillows

	 	FSB 1305-0625
	 	A
	Baggage Finish Specification

	 	FSB9800-2000
	 	D
	Cockpit Finish Specification

	 	FSB9800-0108
	 	E
	Baggage Layout

	 	GP9800-2001
	 	D

 

 

Schedule “B” to

Aircraft Purchase Agreement

BOMBARDIER AEROSPACE CORPORATION

RECEIPT OF AIRCRAFT

                        
HEREBY ACKNOWLEDGES TO HAVE RECEIVED
FROM BOMBARDIER AEROSPACE CORPORATION, AT
                    
      , ON THE            
      DAY
OF                  , ONE (1)
                        MODEL AIRCRAFT BEARING SERIAL NUMBER
                    ,
INCLUDING WITH THE AIRCRAFT THE            ENGINES BEARING
MANUFACTURER’S SERIAL NUMBERS
            AND      , COMPLETED IN
ACCORDANCE WITH
SPECIFICATION            DATED      
            ,
ATTACHED AS SCHEDULE A-l TO THE AIRCRAFT PURCHASE AGREEMENT
BETWEEN BOMBARDIER AEROSPACE CORPORATION AND            
            
DATED                         .

	 	 	 
	

	 	

	

	 	NAME
	 
	 	 
	

	 	

	

	 	TITLE

	 	 
	WILLIAMS-SONOMA, INC.	3.

 

 

Schedule “C” to

Aircraft Purchase Agreement

WARRANTY BILL OF SALE

KNOW ALL MEN BY THESE PRESENTS:

     THAT BOMBARDIER AEROSPACE CORPORATION, having an office at 3400 Waterview Parkway Suite
400, Richardson, Texas, 75080 (“Seller”), is the owner of
the full legal and beneficial title to that certain 
            
Aircraft
model
             
(“Airframe”) bearing Manufacturer’s Serial
Number
                    
and registration number                 
together with the two (2)                 
  engines installed thereon, bearing
Manufacturer’s Serial Numbers
                
 and           (the “Engines”), respectively, together with the following (the
“Equipment”): (a) all
equipment, appliances, parts, instruments, appurtenances, accessories,
furnishings, and other property installed in or attached to the Airframe or
Engines on the date hereof; and (b) all documents, logbooks, manuals,
certificates, data
equipment and spare parts listed on Exhibit “A” of that certain Purchase
Agreement
dated                   
  2002 (the
Airframe, the Engines and the Equipment are collectively hereinafter referred
to as the “Aircraft”).

     THAT for and in consideration of good and valuable consideration, the
receipt of which is hereby acknowledged,
Seller does this
            
day of       , 2002 grant, convey, transfer, bargain and sell,
deliver and set over, all right, title and
interest in and to the Aircraft
unto              
           (“Buyer”), and unto Buyer’s successors and
assigns, forever.

     THAT Seller hereby warrants to Buyer and its successors and assigns that,
immediately prior to the delivery of this Warranty Bill of Sale, Seller had
good and lawful right to sell the same, and that there is hereby conveyed to
Buyer on the date hereof, good title to the Aircraft free and clear of all
liens, claims, encumbrances and rights of others (including those resulting
from any and all taxes), and that it will warrant and defend such title
forever against all claims and demands whatsoever by persons claiming by or
through Seller or relating to events occurring prior to the date hereof.

     IN WITNESS WHEREOF, the undersigned has caused this Warranty Bill of Sale
to be executed and delivered
this
            
day of       , 2002.

BOMBARDIER AEROSPACE CORPORATION (Seller)

	 	 	 
	By:
	 	 
	

	 	

	 
	 	 
	Name:
	 	 
	

	 	

	 
	 	 
	Title:
	 	 
	

	 	

BOMBARDIER INC. WARRANTY

     BOMBARDIER INC. hereby warrants to Buyer and its successors and assigns
that, immediately prior to the delivery of this Warranty Bill of Sale, Seller
had good and lawful right to sell the same, and that there is hereby conveyed
to Buyer on the date hereof, good title to the Aircraft free and clear of all
liens, claims, encumbrances and rights of others (including those resulting
from any and all taxes) created by or through Seller, and that BOMBARDIER INC.
will warrant and defend such title forever against all claims and demands
whatsoever by persons claiming by or through Seller or BOMBARDIER INC. or
relating to events occurring prior to the date hereof.

BOMBARDIER INC.

	 	 	 
	By:
	 	 
	

	 	

	 
	 	 
	Name:
	 	 
	

	 	

	 
	 	 
	Title:
	 	 
	

	 	

	 	 
	WILLIAMS-SONOMA, INC.	4.

 

 

Schedule “D” to

Aircraft Purchase Agreement

BUYER OBSERVATIONS

	1.	 	Forward Lavatory- Show access to shut off valve on layout to confirm
accessibility.
Layout will be “red marked” and signed to reflect access.
	 
	2.	 	Cabin Management System- Monitors to be flush with bulkhead per standard.
	 
	3.	 	Cabin Management System- Water heaters to come on automatically, with
pre-sets.
	 
	4.	 	Cockpit- Loudness of Magnastar Sonalert to be adjustable. One
time only
adjustment.
	 
	5.	 	Galley Annex- Provide easy access to water shut off valves. Layout
will be “red
marked” and signed to reflect access.
	 
	6.	 	Aft Lavatory- Show access to shut off valve on layout to confirm
accessibility.
Layout will be “red marked” and signed to reflect access.
	 
	7.	 	Seats, Divans and Tables- Make headset jacks inboard double armrests
angled, so it is easier to see when plugging in jack (if at all possible).
As discussed, the headsets
will be ordered with 90 degree connectors.

	 	 
	WILLIAMS-SONOMA, INC.	5.

 

 

Schedule “E” to

Aircraft Purchase Agreement

IRREVOCABLE STANDBY LETTER OF CREDIT

This new schedule is incorporated into the Agreement.

	 	 
	WILLIAMS-SONOMA, INC.	6.

 

 

APPENDIX “B” to

Aircraft Purchase Agreement

	 	 	 
	PART DESCRIPTION
	 	PART NUMBER

	EMS
CDU

	 	GL542-3101-11
	MADC

	 	7014700-623
	ACPC CONTACTOR

	 	5911740-1

	 	 
	WILLIAMS-SONOMA, INC.	7.

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