GLOBAL VISION SCHEDULE A1 COMPLETION SPECIFICATION The ... · Bombardier Global Completion Center approved test procedures. All testing results shall be reviewed and/or approved by

SCHEDULE A1

COMPLETION SPECIFICATION The Limited Edition

GLOBAL VISION

Global 5000TM Global Vision Schedule A1 5000V1LE-0501 Revision A 2011-02-01

1-2 Global 5000TM Global Vision Schedule A1 5000V1LE-0501 Revision A 2011-02-01

TABLE OF CONTENTS

1. GENERAL................................................................................................................................................ 4 1.1. SCOPE ............................................................................................................................................... 4 1.2. DEFINITIONS AND ACRONYMS .............................................................................................................. 4 1.3. CERTIFICATION ................................................................................................................................... 5 1.4. GENERAL STATEMENTS AND CONDITIONS ............................................................................................ 5 1.5. DESIGN AND INSTALLATION PRACTICES ................................................................................................ 6

2. SOUNDPROOFING ................................................................................................................................. 8

3. OXYGEN SYSTEM .................................................................................................................................. 9

4. ENVIRONMENTAL CONTROL SYSTEM (AIR CONDITIONING AND COOLING) .............................. 10

5. WATER SYSTEM .................................................................................................................................. 11

6. WASTE SYSTEM .................................................................................................................................. 13

7. COCKPIT............................................................................................................................................... 14

8. ENTRANCE AREA ................................................................................................................................ 16 8.1. RH AVIONIC EQUIPMENT RACK.......................................................................................................... 16 8.2. RH FORWARD LAVATORY.................................................................................................................. 16 8.3. LH ENTRANCE ENCLOSURE............................................................................................................... 17 8.4. RH GALLEY ...................................................................................................................................... 18 8.5. LH GALLEY ANNEX ........................................................................................................................... 19

9. PASSENGER MAIN CABIN .................................................................................................................. 20

10. AFT LAVATORY COMPARTMENT AND WARDROBE.................................................................... 24 10.1. RH AFT LAVATORY........................................................................................................................ 24 10.2. AFT WARDROBE AND STORAGE CABINET........................................................................................ 25

11. BAGGAGE COMPARTMENT............................................................................................................ 26

12. AVIONIC SYSTEMS .......................................................................................................................... 27

13. COMMUNICATION & ELECTRICAL SYSTEMS ............................................................................... 28

14. CABIN ELECTRONIC SYSTEM (CES).............................................................................................. 31

15. MISCELLANEOUS INSTALLATIONS............................................................................................... 35

16. LIGHTING .......................................................................................................................................... 37

17. EMERGENCY EQUIPMENT .............................................................................................................. 40

Belen Heredia

1-3 Global 5000TM Global Vision Schedule A1 5000V1LE-0501 Revision A 2011-02-01

18. EXTERIOR PAINT ............................................................................................................................. 41

19. WEIGHT AND CENTER OF GRAVITY.............................................................................................. 42

20. ANNEX "A” - AESTHETIC AND COST GUIDELINES...................................................................... 43

21. ANNEX "B” - LOOSE EQUIPMENT.................................................................................................. 44

22. ANNEX "C” - SPARE EQUIPMENT .................................................................................................. 45

23. ANNEX "D” – COMPLETION DOCUMENTATION LIST................................................................... 46

24. ANNEX "E” - AIRCRAFT FLOORPLAN ........................................................................................... 48

Belen Heredia

1. GENERAL

1.1. Scope

This Global 5000™ Global Vision aircraft Completion Specification (the “Schedule A1”) 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 a Global 5000™ Global Vision aircraft interior. It also defines the manner in which the work is to be conducted and controlled by Bombardier Global Completion Center. Customer understands and acknowledges that the addition of the items in this Completion Specification and/or any other work that is supplemental to the

aircraft configuration in Schedule "A" shall impact the performance specified in Section 3 of Schedule "A". Deliverables (Loose Equipment and Spares) All contracted deliverables that cannot accompany the aircraft at delivery due to space constraints shall be shipped to the required destination via a transportation mode acceptable to and paid for by the Customer. Contracted deliverables shall include but not be limited to 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 and Acronyms

“Global Completion Center” or “GCC” - The Bombardier designated Global interior completion center.

“Factory installed” Items – Items installed as part of the aircraft in its “green” configuration, including its power plant, systems and equipment.

“Complete Provisions” - 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.

“Wiring Provisions” - Primary wiring only 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.

”RH” or “RHS” - Right hand side or starboard side of the aircraft

“LH” or “LHS” - Left hand side or port side of the aircraft

“Contract Change Order” - Written document issued by Bombardier Global Completion Center

specifying a modification to the Completion Specification and outlining the cost, weight, sound and schedule impact, if any, associated with such Completion Specification modification.

”TC” - Transport Canada or Department of Transport of the Government of Canada

”FAA” - Federal Aviation Administration of the United States of America

“FAR” - Federal Aviation Regulations promulgated by the FAA under the Federal Aviation Act

“EASA” - European Aviation Safety Agency

”JAR” - Joint Aviation Regulations

“TT&L” - Taxi, Takeoff and Landing

“EICAS” - Engine Indication and Crew Alerting System

“PA” - Public Address

“MSL” - Master Seat Location

“CES” - Cabin Electronic System

“PCU” - Passenger Control Unit

“HD” - High Definition

4 Global 5000TM Global Vision Schedule A1 5000V1LE-0501 Revision A 2011-02-01

1.3. Certification

This specification meets the airworthiness requirements of FAR Part 25 and the equipment requirements necessary for FAR Part 91 operations. This specification requires modification during initial completion definition if the airplane is to be exported to a country other than the United States and/or if certification for commercial operations is required (FAR Part 135 or JAR-OPS 1 for example). Bombardier Global Completion Center is responsible for obtaining approval for the interior completion modifications and any required negotiations with the regulatory authorities. The following configuration is approved: Thirteen (13) passenger configuration features a frangible mid cabin sliding pocket door. The aircraft may not be operated for hire or common carriage (i.e. limited to FAR Part 91 operation only). Note: The removable RH mid cabin bulkhead must be removed if the forward seating position of the 16G divan is to be occupied for taxi, take-off and landing. If the removable mid cabin bulkhead is installed, then the fwd seating position of the divan must not be

occupied for taxi, take off and landing and the passenger capacity is reduced to twelve (12). This specification includes wiring provisions to support a future interior modification enabling the aft cabin to be used as a flight crew sleeping quarter as required under FAA rules for FAR Part 135 operations for flights less then ten (10) hours of duration, as well as a means to disable the frangible mid cabin sliding pocket door and a privacy curtain. The device used to disable the mid cabin sliding pocket door and the privacy curtain is provided as loose equipment. Note: Service Bulletin 700-1A11-31-001 Crew Force Measuring System (FDR upgrade), which is required for FAR Part 135 operation, has not been included. This specification includes life rafts that meet the airworthiness requirements for certification of the aircraft for ditching. Bombardier Global Completion Center shall provide a Canadian Certificate of Airworthiness (C of A) for Export to the United States.

1.4. General Statements and Conditions

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

1. Documentation of any marred items and/or any discrepancies, including flight squawks reported by flight crew during ferry flight to Bombardier Global Completion Center.

2. A visual inspection and detailed inventory of all loose equipment that shall be appropriately stored during completion.

3. Verification and record of aircraft fuel and oil quantity at arrival.

Ferry Equipment The ferry equipment, excluding Customer property and any other temporary equipment shall be removed from the aircraft upon arrival, packed and shipped to Bombardier in accordance with the furnished instructions. Preservation and Protection The airframe, engines and APU shall be preserved by Bombardier Global Completion Center in accordance with the manufacturers’ (Bombardier, BMW / Rolls Royce and Rockwell Collins) recommended procedures. Bombardier Global Completion Center’s Quality Control department shall verify that all necessary measures to preserve the aircraft shall be suitably maintained during the period of the aircraft’s inactivity. The Customer shall be provided with the documentary evidence that this has been accomplished. Bombardier Global Completion Center shall ensure that all reasonable efforts shall be made to protect


the aircraft during the completion process: protection of all cabinets, reflective synthetic glass, seats, carpets, synthetic glass, floor boards, etc. shall be carried out during transport and storage (or whenever the item is not in the process of manufacture). Program Status Bombardier Global Completion Center shall provide a monthly status report and review it with the Customer. Customer Access The Customer’s representative shall 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. Global Completion Center’s regulations concerning employees and facilities shall be observed by the Customer or Representative. The use of protective safety equipment shall be observed as defined by Bombardier GCC. Flight Testing Testing/Inspection/Certification for ground and flight tests shall be the responsibility of Bombardier Global Completion Center. The aircraft shall be operated under TC regulations during flight tests. The test program shall be conducted in accordance with Bombardier Global Completion Center approved test

procedures. All testing results shall be reviewed and/or approved by Bombardier Global Completion Center. During the flight test program, Bombardier Global Completion Center shall provide the necessary flight crew and ground support equipment that is required to perform all required certification flight tests. Bombardier Global Completion Center shall assume the cost of fuel and oil consumption during the completion flight test program that is needed to verify operational status of Bombardier Global Completion Center ‘work’. Pre-Delivery The following shall be accomplished immediately prior to delivery:

1. A night lighting check. 2. Fill the water system and service the

lavatories. 3. Supply the loose equipment/spares referenced

in Section 21. 4. The quality documents shall be reviewed by

both the Customer’s representative and Bombardier Global Completion Center’s Quality Control representative.

5. Supply documentation referenced in Section 23, except as noted.

6. The aircraft, including the windows, shall be cleaned and the interior groomed.

1.5. Design and Installation Practices

A. All passenger information signs, placard instructions related to seat position, armrests, emergency exit signs, and all other instructions are in English and meet TC and export to FAA requirements.

B. Unless otherwise noted, all hardwood and veneer have a hi-gloss finish. Custom moldings, murals and artwork are not included in this specification and, if selected, shall be estimated and quoted for approval via a Contract Change Order.

C. All placards are in the English language and applied on clear stickers or icons, wherever possible. Placards finish matches the finish on veneer/ hardwood (i.e. hi-gloss placards on hi-gloss veneer, or matt/satin placards on matt/satin veneer). Quantities of individual placards with common text (e.g. “for taxi, take-off and landing”) are reduced as much as possible. Instructions are grouped together and then followed by the common text.

D. Aerospace grade switches and touch-screen HD monitors are used and have symbolic icons where possible; otherwise, the English language is used.

E. All interior finish materials are selected for quality, durability, ease of maintenance and with weight as a prime consideration. Bombardier Global Completion Center reserves the right to substitute components of equal quality should a lack of availability be documented by the chosen supplier. Bombardier Global Completion Center is not responsible for variations in dye lots of fabrics or leathers or variations in grain and color of wood from the Customer approved sample, due to the natural properties of these items. Should the Customer select exotic or custom materials, these upgrades shall be processed as additional costs via a Contract Change Order.

F. The material cost for this specification is based on the guidelines described in Section 20. Customer


selected upgrades shall be processed as additional cost via a Contract Change Order.

G. Design engineering and the choice of construction materials and fabrication techniques shall be the responsibility of Bombardier Global Completion Center and shall be in accordance with the accepted current aircraft procedures and practices. The size of storage areas and drawers shall be determined by Bombardier Global Completion Center based on available space and standard size of such items as Blu-ray, DVDs, CDs, meal trays, flatware, china, crystal, etc.

H. Light emitting diode (LED) type lights are used for all interior lighting. The design of all lighting fixtures is directed toward ease of lamp replacement.

I. Cockpit switches, annunciators, controls and instruments, added as a result of Bombardier Global Completion Center installations, shall be arranged in accordance with the customer approved cockpit layout.

J. The interior is installed in such a manner as to allow reasonable access to maintenance and inspection items where practical. All areas requiring inspection are accessible with minimum disturbance to the interior furnishings, based on the following guidelines: 1. “A” check inspection items - access is to be

thirty 30 minutes or less. 2. “C” check inspection items - access is to be

sixty 60 minutes or less.

K. Customer specific configurations may affect seat movement and berthing capabilities due to surrounding installations.

L. Attachment and support structures are shock mounted where applicable for acoustical purposes throughout the aircraft. Trim panel fasteners are not visible wherever possible.

M. Exposed hardware (except in the baggage compartment) is plated in accordance with the Material Specification document. Hardware in the category of drawer slides, rollers, door latches, etc. is selected and installed to minimize resonance rattling, and to maximize durability and ease of operation. Hinges on cabinet doors are concealed. Minimally exposed surfaces are not plated.

N. All installed fabrics and materials not inherently flame resistant are treated with a fire-retardant protection process. All seat cushions are fire blocked. Bombardier Global Completion Center shall be responsible for flammability certification of all materials.

O. The interior of drawers and compartments are suitably lined and/or painted per the trim drawings or material specification.

P. Any products used in completion of the aircraft for sound dampening, flame resistance, soil resistance or for any other purpose are non-corrosive on aircraft structure and systems.


2. SOUNDPROOFING

The aircraft is soundproofed utilizing vibro-acoustic materials. The enhanced shell treatment acoustical package is designed to achieve the minimum sound levels attainable based on the Limited Edition cabin layout, trim finishing and within the operating weight parameters of the aircraft. The Limited Edition aircraft interior has average sound level targets of 52 db SIL (Speech Interference Level) and 70 dBA and average levels not to exceed 54 db SIL and 72 dBA. A target sound level shall be identified by Bombardier Global Completion Center upon final Customer approval of the aforementioned interior.

The aircraft configuration is in accordance with Bombardier Global Completion Center document “Instructions for Aircraft Preparation - Sound Survey”. The aircraft is surveyed at FL 450 and at a speed of 0.80 Mach, and in typical operating conditions (ex. water-serviced, life rafts on board, galley, wardrobe, vanities and cabinets stocked, air conditioning on and gaspers turned off). Noise is measured at each cabin seat and linear average of all seats is calculated to determine the average cabin noise levels. The SIL measurement is based upon the arithmetic average of the sound pressure levels in the 1000, 2000 and 4000 Hz octave bands.


3. OXYGEN SYSTEM

The aircraft is equipped with four (4) factory installed 50 cu ft (1.415 liters) 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 oxygen distribution system is installed. Cockpit Crew System The factory installed crew system with quick donning demand type full-face masks is retained. Oxygen Drop Box Oxygen drop boxes are installed for each cabin seat, Flight Observer Seat, the galley area and lavatories, as required. Each oxygen drop box is equipped with two constant flow masks. Oxygen Test Switch An oxygen test switch is factory installed in the cockpit on the RH cockpit bulkhead. The switch enables testing of the oxygen system without deploying the passenger oxygen constant flow masks. Therapeutic Oxygen System A factory installed therapeutic oxygen valve is factory installed within the cockpit to enable flow of

oxygen to the therapeutic oxygen outlets. The valve is activated by a Push Button Annunciator (PBA) located on the Passenger Oxygen Control Panel. Two (2) therapeutic oxygen outlets are installed in the main cabin, on the RHS of the aircraft in the following locations:

1. One (1) in the RH forward cabin – sideledge. 2. One (1) in the RH aft cabin – sideledge.

Two (2) therapeutic oxygen masks are provided as loose equipment. Oxygen Warning System An interface with the factory installed oxygen pressure switch activates the dedicated oxygen lights throughout the cabin, the "NO SMOKING" sign in the cabin and an aural warning in the cockpit and cabin when the oxygen masks are deployed. Quick Donning Flight Observer Seat Oxygen Convertible Mask with Goggles (MLD20-508) One (1) EROS MLD20-508 series Quick Donning Mask is supplied for the Flight Observer Seat occupant. A mask and storage box is installed in the upper area of the LH entrance enclosure. This mask is a full-face, quick-donning oxygen mask, with microphone and removable smoke goggles. The new mask provides additional comfort features and meets TSO C78, C89 and C99. The PTT, headset and mike jacks are installed on the RH cockpit bulkhead.


4. ENVIRONMENTAL CONTROL SYSTEM (AIR CONDITIONING AND COOLING)

Conditioned cabin air is provided to the forward and aft cabin via dado ducts, diffuser ducts and galley, lavatories and gasper ducts. All necessary risers and air outlets for the Flight Observer Seat, cabin and lavatories are installed to complete the factory installed conditioned air system and are designed to 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:

1. Zone A: FS 202.00 + 32.00 – FS 280.00 + 32.00 - Cockpit.

2. Zone B: FS 280.00 + 32.00 – FS 649.00 - Entry area and forward cabin.

3. Zone C: FS 649.00 – FS 799.00 - Aft cabin and aft lavatory area.

Cockpit The cockpit air supply system is retained as installed by the factory. Cockpit Air Deflector One (1) air deflector is added to the factory installed RH cockpit bulkhead air vent to re-direct the conditioned air away from the co-pilot’s head and neck. Forward and Aft Cabin - Main Distribution Factory installed ECS ducts and distribution systems are an integral part of the floor duct design. The system supplies conditioned air from floor ducts located on each side of the aircraft. The ducts direct the airflow either to the exhaust through outflow valves, or for re-circulation. Individual Air Outlets Individual adjustable air gaspers are installed for each seat position within the Passenger Service Units and connected to the factory installed air duct. Air gaspers are also installed at the Flight Observer Seat (factory installed) and in both lavatories. Conditioned Air System Controller The factory installed conditioned air control is retained. The cockpit “master” controller has full temperature and flow range control over every cabin zone. The cabin temperature controls have limited authority (+/- 2°Celcius, +/- 5°Fahrenheit) capable of varying around the cockpit set temperature. Actual cabin temperature is shown digitally on the galley touch-screen, MSL wireless PCUs and MSL plug-in

touch-screen HD monitors. Temperature sensors are installed as per approved layout drawings. The cabin temperature controls are available as follows:

1. For the forward cabin, at the forward MSL. 2. For the aft cabin, at the aft MSL. 3. For both the forward and aft cabin, on the

galley touch-screen. Galley and Lavatories Conditioned air is supplied through extensions from the main cabin floor level conditioned air ducts through the toe kick areas. Exhaust Fans Exhaust fans are installed in the following locations:

1. In the entryway to draw cold air outboard of acoustic curtain to the under floor area.

2. Outboard of the RH galley and LH galley annex to exhaust heat and odors from the installed galley appliances.

3. Under the floor in the aft step well to remove cold air from behind the acoustic curtain (Factory installed).

4. In both toilet cabinets to exhaust odors from the lavatories (privacy latch activated). The exhaust fans remain functioning for five minutes subsequent to privacy latch disengagement.

Cooling Fans Cooling fans are installed in the cabinets containing In-flight Entertainment Equipment (IFE) and Cabin Electronic System (CES) components to prevent overheating of the installed electronic equipment as follows:

1. RH galley (bulkhead HD monitor). 2. LH galley annex (touch-screen HD monitor). 3. Credenza (IFE equipment). 4. Aft wardrobe (bulkhead HD monitor).

Ice Filter An ice filter assembly is factory installed at the mix manifold (Ref. Section 15). Entry Area Heater The entry area heater, which is installed in the avionics bay, provides additional warm air to the entrance zone area. The heated area is ducted to the toe kick space of the LH galley annex.


5. WATER SYSTEM

The Potable Water System (PWS) is a dual water pump re-circulating system. The PWS provides filtered cold and hot water to the RH galley and the lavatories. The PWS utilizes heated hose assemblies and component heaters to inhibit water from freezing in static lines. Drainage of the gray water lines and the fresh water lines (when purging) is provided through the forward and the aft heated drain masts. Pressurized lines and components are installed within shrouds to protect critical aircraft systems in the unlikely event of water leakage. External Water Servicing A single external water service panel, located on the right aft wing fairing, provides a means for external PWS servicing. The service panel incorporates an external fill port of the appropriate size to enable utilization of a standard airline service cart. An instruction placard for servicing the PWS is installed in the external water service panel cavity. The external control panel has the following functionality:

1. Tank filling. 2. Lines draining. 3. System purging (tank, lines and system

components). 4. Water tank level indication. 5. Basic water service fault indication.

Water Tank The water tank has a storage capacity of 24.7 US gallons (93.5 liters) of usable water. The water tank is installed outboard of the LH entrance enclosure. The water tank assembly is covered with a heater blanket to prevent water freezing and condensation build up. An integral drip tray is installed below the water tank and routed to the static drain of the aircraft. Internal Tank Fill The water tank assembly includes a manual fill port (when PWS is in ON or OFF mode). While cabin power is available, an LED annunciator installed in the tank vicinity and / or indication on the Galley touch-screen display alerts when the level is near Full. LH Galley Annex Touch-Screen HD Monitor At the galley touch-screen HD monitor, the PWS modes that can be selected are: System On, System Purge, Off / Line Drain and Off / Line No Drain. The

touch-screen display also provides a means of viewing PWS fault, service and status information. Electronic Interface Box (EIB) The Electronic Interface Box, which is installed in the under floor avionics bay, receives commanded mode information from the CES, backup control panel and external water service panel and provides the appropriate control of the water system components. Component fault and status information is reported by the Electronic Interface Box to the CES. The Electronic Interface Box monitors the water system tank water level for indication at the CES galley touch-screen HD monitor and external water service panel. Backup Control Panel The Backup Control Panel is installed outboard of the LH entrance enclosure behind an access panel. In the event of a Cabin Electronic System (CES) / Electronic Interface Box (EIB) communication failure, the Backup Control Panel provides control of the PWS to the Operator. The backup control panel provides the following PWS modes: System On, Purge and Off / Line Drain. Water Filter Water filtration is accomplished by using a high quality ultraviolet water filter (NPS-A6). The filter is installed behind aft wardrobe and storage cabinet, “in line” on the supply line and is easily removable. A drip tray is installed under the water filter and connected to the static drain to prevent overfill. The filter is capable of supporting a water flow rate of 2.0 GPM. Water Heaters Three (3) water heaters are installed: one (1) in the forward lavatory vanity, one (1) in the RH lower galley and one (1) in the aft lavatory vanity. Monument Motorized Water Valves Each monument (to which water is supplied) contains a motorized valve which is installed on the monument water supply line to control water flow. Each valve has a manual override lever to allow for an override of the current state of the valve.


Pressure Sensitive Mats Two (2) pressure sensitive mats are installed (one in each lavatory) to enable the water supply to the lavatory faucets when the lavatories are occupied. The mats are installed under the carpet adjacent to the lavatory sinks.

RH Galley Water Activation A micro switch, activated by the tambour door in front of the sink, controls the motorized valve installed on the water supply line to the galley faucet. The water will be available when the tambour door is in the open position.



6. WASTE SYSTEM

The waste system comprises a single waste tank that services a two-vacuum toilet system in the forward lavatory and in the aft lavatory. The vacuum waste system utilizes differential pressure between the inside and the outside of the aircraft to transport waste from the toilets to the waste tank when the aircraft is in flight at altitudes above 16,000 feet. A vacuum generator is used to generate differential pressure for waste transport when the aircraft is below 16,000 feet or on ground. External Waste Servicing A single external service panel is provided on the right aft wing fairing for servicing and rinsing the waste tank. The system incorporates quick disconnects. The external waste drain valve enables utilization of a standard airline service cart. An instruction placard (in liters and gallons) for servicing of the waste system is installed on the external waste service panel. Waste Tank A factory installed single waste tank of 16 US gallons (60.6 liters) is installed in the right aft wing fairing.

The waste tank assembly is covered with a heater blanket to prevent freezing. Vacuum Toilet Assembly Each vacuum toilet assembly is equipped with a manual override feature. In the unlikely event that the flush valve fails, the override feature located on the vacuum toilet assembly may be used to manually activate (close) the flush valve. Logic Control Module (LCM) The Logic Control Module (LCM) provides vacuum waste system monitoring and control and is linked to the Cabin Electronic System (CES) for fault reporting and tank level indication. The Logic Control Module (LCM) is located within the aft lavatory vanity. Heater Interface Unit (HIU) The Heater Interface Unit (HIU) is linked to the Cabin Electronic System (CES) and provides monitoring system only for waste system heaters failures. The Heater Interface Unit (HIU) is located within the aft lavatory vanity.

7. COCKPIT

The cockpit area encompasses the area from the forward pressure bulkhead to the cockpit bulkheads. The factory outfitted equipment, furnishings, trims, and flight crew seating upholstery are retained as delivered to Bombardier Global Completion Center. The factory finish includes all cockpit peripherals (glareshield, trim panels, side consoles). The factory installed equipment includes:

14 Global 5000TM Global Vision Schedule A1

1. A Jeppesen manual storage hard case box with a center access panel at the cockpit entrance (in floor).

2. Footrests, covered in non-skid material. 3. Third audio panel for Flight Observer Seat in

center pedestal. 4. Flight Observer Seat (jumpseat). 5. Flight observer control panel with the following

features: i. Headset and microphone jacks; ii. Push-To-Talk switch; iii. Light control.

6. One (1) CES maintenance switch (guarded). 7. Telephone handset (Ref. Section 13). 8. Emergency equipment (Ref. section 17).

The following equipment is also installed: 1. Electrical outlets (Ref. Section 13). 2. RJ-45 outlets (Ref. Section 14). 3. Emergency equipment (Ref. section 17). 4. One (1) certificate holder on LH cockpit

bulkhead.

Headliner A three-piece headliner panel extending from the windshield to the cockpit bulkheads is factory installed. The headliner incorporates:

1. Two (2) air gaspers. 2. Grab bar, on the central headliner panel. 3. HUD and Combiner Unit on the LHS. 4. Lighting (Ref. Section 16).

Amenity Holders Amenities for the crew are installed with the following conveniences:

1. Two (2) pencil holders, one for each pilot position.

2. Two (2) permanent cup holders, one (1) on each side console.

Instrument Placard The following placards are installed:

1. Two (2) aircraft registration placards, silk-screened on a decal, mounted on the glare shield panel in clear view of the pilot and co-pilot.

ollowing information:

2. One (1) aircraft phone numbers placard made from photosensitive aluminum sheet is applied on the windshield center post above the eye reference. The placard includes the fa. SELCAL number. b. Aircraft phone numbers

(Iridium,SATCOM). c. Medlink phone number (MedAire).

Roller Screens Two (2) sun filter type roller screens are installed hidden in the upper side console panel on each side of the cockpit. When deployed, the roller screens attach to the visor rail above. RH Multifunction Touch-Screen Display - EFB #2 DU (Display Unit) and AIU (Aircraft Interface Unit) One (1) removable 8.4-inch DU is installed on the forward RH side of the cockpit. One (1) AIU is installed in the RH console. Cabin Systems Panel One (1) backlit Cabin Systems Panel that includes Cabin Power (OFF) and Cabin Outlets (OFF) PBAs will be installed on the cockpit overhead panel. Cabin Miscellaneous Systems Panel One (1) backlit Cabin Miscellaneous Systems Panel that includes Crew Area PA (OFF) will be installed on the cockpit center pedestal. Cabin Circuit Breaker Panel One (1) backlit Cabin Circuit Breaker Panel (CCBP) will be installed on LH cockpit bulkhead. LH Side Console Storage Bin One (1) storage bin is installed FWD in the LH side console between the oxygen mask box and the nose

5000V1LE-0501 Revision A 2011-02-01

wheel steering, replacing factory installed blanking plate. LH Side Console Storage Bin with Flip-Up Lid One (1) storage bin is installed in the LH side console in the provisional location of the optional LH Multifunctional Touch-screen Display, EFB #1. The storage bin will include a lid. RH Side Console Storage Bin with Flip-Up Lid One (1) storage bin is installed FWD in the RH console between the oxygen mask box and the cup holder, replacing factory installed blanking plate. The storage bin will include a lid and a paper retention device. The lid will act as a rigid writing surface.

Cockpit Printer A thermal, aircraft certified printer is installed on the LH cockpit bulkhead behind the pilot seat. The printer may be used on the ground or in-flight and enables the user to print datalink messages from the datalink, maintenance data from On-board Maintenance System (OMS), charts from Integrated Flight Information System (IFIS), Flight Log and Weight/Balance data from FMS, and on-board documents. Sunvisors Storage Storage for sunvisors (Qty 2) and a HUD combiner shade (Qty 1) is provided on the RH side and LH side consoles.


8. ENTRANCE AREA

The entrance area is defined as the zone aft of the cockpit bulkheads, encompassing the RH avionics rack, RH forward lavatory, LH entrance enclosure, main entry door, RH galley and LH galley annex. Entrance Area Headliner A two-piece headliner panel is installed extending from the cockpit bulkheads to the forward cabin bulkheads and incorporates the following:

1. Galley oxygen drop-box. 2. Flight Observer Seat oxygen drop-box. 3. One (1) PA speaker. 4. One (1) chime speaker. 5. Emergency exit sign (Ref. Section 16). 6. Lighting (Ref. Section 16).

Cockpit Curtain A ¾ length curtain is installed on a “U” shaped track. The curtain tracks across the cockpit entrance at cockpit bulkheads. The curtain may also be tracked around the side of the Flight Observer Seat and across the aisle behind it. The curtain is held by concealed magnets when deployed and by restraint straps in the stowed position.

Entryway Acoustic Curtain An acoustic curtain is installed and housed in the LH entrance enclosure. The curtain is suspended from a semi-recessed track in the headliner. The curtain is secured through full length of curtain on the fwd LH galley bulkhead when in deployed position. Airstair The airstair incorporates the following items:

1. Two (2) 7.0” diameter storage compartments for landing gear pins (factory installed) and flags.

2. Finishing trims on the lower doorframe. 3. Non-skid material on each step and inside the

storage compartment. 4. One (1) handrail extension, on the forward

side of the airstair. 5. Lighting (Ref. Section 16).

Flight Observer Seat A Flight Observer Seat approved for take-off and landing is installed. The Flight Observer Seat folds vertically for outboard storage inside LH entrance enclosure and incorporate recline, height and tracking adjustments capabilities. A safety belt and shoulder harnesses with a twist release are provided. A sheepskin slipcover is provided as loose equipment.

8.1. RH Avionic Equipment Rack

The RH avionics equipment rack extends from the RH cockpit bulkhead to the RH forward lavatory and incorporates the following:

1. Access cover panels, closing off the avionics equipment rack while maintaining accessibility for maintenance.

2. Decompression and smoke seals, incorporated within the access cover panels.

8.2. RH Forward Lavatory

The RH forward lavatory is installed in the entry area, between the RH avionics equipment rack and the RH galley. Bulkheads A forward and an aft bulkhead are installed and include the following:

1. One (1) towel ring, mounted on the aft bulkhead.

2. Lighting (Ref. Section 16). Privacy Door and Partition A hinged door with fixed header and decompression blow-out capabilities is installed. The door lock incorporates emergency break-in capabilities. One (1) privacy latch is installed on the door. A symbolic “NO SMOKING” placard and a flip-down ashtray are installed on aisle side of the lavatory


door. The door jam incorporates a seal to minimize light bleed. Headliner A lavatory headliner is installed and incorporates the following:

1. One (1) oxygen drop box. 2. One (1) PA speaker. 3. One (1) air gasper. 4. Lighting (Ref. Section 16). 5. Emergency equipment (Ref. Section 17).

Sidewall The lavatory sidewall incorporates the following:

1. Handrail. 2. One (1) electric accordion-type window shade. 3. Lighting (Ref. Section 16).

Vanity A vanity cabinet is installed and incorporates the following:

1. A countertop with splashguard. 2. One (1) sink and faucet. 3. One (1) soap dispenser.

4. One (1) facial tissue dispenser. 5. One (1) toilet paper dispenser. 6. One (1) removable sealed waste container. 7. One (1) switch panel. 8. One (1) toilet flush switch panel. 9. Miscellaneous storage as space permits. 10. Conditioned air with decompression grille. 11. Water system components. 12. Electrical outlet (Ref. Section 13). 13. Lighting (Ref. Section 16).

Toilet and Enclosure A vacuum toilet assembly is installed on the forward side of the lavatory. The toilet enclosure is installed and incorporates the following:

1. One (1) hinged, padded lid with hold-open provisions.

2. One (1) exhaust fan to duct odors under the floor.

3. Access panel for toilet manual override feature.

4. Decompression grille. 5. Lighting (Ref. Section 16).

8.3. LH Entrance Enclosure

The LH entrance enclosure is installed in the entry area, between the LH cockpit bulkhead and the main entry door. Aft Cabinet Side The aft side of the LH entrance enclosure incorporates the following:

1. Forward handrail extension attachment. 2. One (1) acoustic curtain and storage area with

hinged door and restraint straps. 3. Emergency exit sign (Ref. Section 16).

Upper Cabinet Section The upper portion of the LH entrance enclosure incorporates the following:

1. One (1) switch panel. 2. One (1) refuel/de-fuel panel. 3. One (1) lockable storage compartment. 4. Miscellaneous storage. 5. Emergency equipment (Ref. Section 17).

Lower Cabinet Section

The lower portion of the LH entrance enclosure incorporates the following:

1. One (1) Flight Observer Seat storage area. 2. One (1) closeout bi fold nesting door for the

Flight Observer Seat storage area. 3. One (1) removable coat rod. 4. Two (2) hinged doors to close off the

wardrobe. 5. One (1) pop-out cup holder. 6. One (1) miscellaneous storage and headset

storage area. 7. Miscellaneous storage. 8. Access panels. 9. Fwd Maintenance Panel that includes three (3)

RJ-45 jacks – one (1) for OMS (On-board Maintenance System) and two (2) for AFDX download.

10. Strapping provisions for OMS Laptop. 11. Emergency light power supply (ELPS) behind

a removable panel.


12. One (1) water fill access panel and maintenance access panel.

13. Ventilation grille. 14. Electrical outlet (Ref. Section 13). 15. Lighting (Ref. Section 16).

16. Emergency equipment (Ref. Section 17). 17. Storage provisions with straps for four (4)

umbrellas with drip tray (Ref. section 18). 18. Passenger briefing cards storage

compartment (Ref. section 18).

8.4. RH Galley

The RH galley is installed in the entry area, between the RH forward lavatory and the RH forward cabin bulkhead. Inserts for china, crystal and flatware will be installed within galley drawers and storage areas. Customer can choose inserts for any of the five (5) pre-engineered china, crystal and flatware sets – one (1) default and four (4) optional sets.

Customer can also select to install inserts for a custom china, crystal and flatware set, in which case the Customer shall be responsible to supply to Bombardier GCC three (3) samples for each piece of china, crystal and flatware, as well as desired quantities to fit in the cabinets, within four (4) weeks from the “Specification Date”, as mentioned in the Article 3 of the Purchase Agreement. These samples shall be used to customize inserts within galley drawers and storage areas in order to determine quantities and ensure proper fit and sizing for the crystal, china and flatware, based on the galley space and weight limitations. In the event the samples are not received by Bombardier GCC within above specified timeline, Bombardier GCC will install the inserts that will accommodate a default china, crystal and flatware selection.

If the Customer provides samples other than a default selection at a date later then four (4) weeks from the above referenced “Specification Date”, Bombardier GCC will provide a Contract Change Order, in accordance with the Purchase Agreement, to identify the cost, weight and schedule impact to the Customer.

China, crystal and flatware sets are not included as part of this Schedule A1. Upper Cabinet Section The upper galley section incorporates the following:

1. Crystal storage area, accessible via two (2) synthetic glass sliding doors.

2. Emergency exit sign (Ref. Section 16). 3. Lighting (Ref. Section 16).

Middle Cabinet Section The middle galley section incorporates the following:

1. One (1) AEROLUX (NESPRESSO) manual fill espresso coffee maker – The unit is installed on an open sided pull-out tray with two (2) locking positions. Sliders are designed so that the coffee maker with tray can be removed for cleaning. The coffee maker can also provide hot water or steam.

2. Two (2) tambour doors. 3. One (1) paper towel holder. 4. One (1) sink drainage switch panel. 5. One (1) exhaust fan to duct odors under the

floor. 6. Miscellaneous storage. 7. Electrical outlet (Ref. Section 13). 8. Lighting (Ref. Section 16).

Lower Cabinet Section The lower galley section incorporates the following:

1. Countertop. 2. One (1) stainless steel sink, faucet and sink

cover with cutting board on reverse side. 3. One (1) motorized valve, with manual override

lever. 4. One (1) miscellaneous storage drawer

concealed under the sink. 5. Water system components. 6. One (1) sealed waste container with a

garbage bag retainer ring. 7. One (1) divided clean ice/bottle storage

drawer with a manual plunger for drainage. 8. One (1) flatware and one (1) utensil storage

drawer. 9. One (1) chilled soda can drawer. 10. One (1) laminated and insulated chilled

storage compartment with three (3) removable composite trays/shelves.

11. Conditioned air at the toe kick area. 12. One (1) cold air chiller unit for cooling the cold

storage compartment. 13. Decompression diaphragm panels within the

galley base panel. 14. Exhaust fans (Ref. Section 4).


15. Lighting (Ref. Section 16). Note: The window outboard of the RH galley is installed with a false accordion type window shade in permanently closed position (non-operational).

8.5. LH Galley Annex

The LH galley annex is installed aft of the main entry door to the LH forward cabin bulkhead. Upper Cabinet Section The upper galley section incorporates the following:

1. Crystal storage, accessible via two (2) synthetic glass sliding doors.

2. One (1) galley HD touchscreen control panel. 3. Lighting (Ref. Section 16).

Middle Cabinet Section The middle galley annex section incorporates the following:

1. One (1) digital oven controller. 2. One (1) TIA microwave oven. 3. Two (2) tambour doors. 4. Two (2) miscellaneous storage drawers. 5. One (1) exhaust fan to duct odors under the

floor.

6. Miscellaneous storage. 7. Electrical outlets (Ref. Section 13). 8. Lighting (Ref. Section 16).

Lower Cabinet Section The lower galley annex section incorporates the following:

1. Countertop. 2. Two (2) pull-out work surfaces, with removable

Teflon cutting board inserts. 3. One (1) TIA high temperature oven, behind a

nesting door. 4. Five (5) china storage drawers. 5. Conditioned air with decompression grille,

including entry area heater duct. 6. One (1) exhaust fan to duct odors under the

floor. 7. Lighting (Ref. Section 16). 8. Emergency equipment (Ref. Section 17).


9. PASSENGER MAIN CABIN

This section in conjunction with the approved cabin floor plan outlines the area between the forward cabin bulkheads and the aft cabin bulkheads. Bulkheads Bulkheads are installed in the following areas of the main cabin:

1. A RH forward bulkhead is installed to separate the entry area from the main cabin. It includes one (1) 24” HD monitor and one (1) magazine rack.

2. A LH forward bulkhead, incorporating a manual sliding pocket door with footer, is installed to separate the entry area from the main cabin. It includes an emergency exit sign (Ref. Section 16) and one (1) magazine rack.

3. A RH removable bulkhead is installed on top of the aft divan fwd end cabinet to separate the forward and mid cabins from the aft cabin. Concealed magnets are installed beneath the veneer, for use with a removable mid cabin curtain.

4. A LH bulkhead, incorporating a manual sliding pocket door, is installed to separate the forward and mid cabins from the aft cabin. It includes an emergency exit sign (Ref. Section 16). Concealed magnets are installed beneath the veneer, for use with a removable mid cabin curtain.

5. A RH aft bulkhead, incorporating a hinged door with a retractable header, is installed to separate the aft cabin from the aft lavatory.

6. A LH aft bulkhead is installed to separate the main cabin from the aft wardrobe and storage cabinet. It includes one (1) 24” HD monitor and one (1) temperature sensor.

Doors Doors incorporating breakaway and decompression blowout capabilities are installed in the following areas of the main cabin:

1. Forward: A manual sliding pocket door, incorporating a retractable footer and a closeout flapper, is mounted to the LH structural bulkhead and located at the forward cabin bulkhead. Two (2) manual release buttons, which release the door from its stowed position, are installed. This door includes EICAS annunciation to provide cockpit crew with validation if the door is not properly stowed during TT&L.

2. Mid: A frangible, manual sliding pocket door is mounted to the LH mid cabin bulkhead. The door incorporates a retractable footer with a closeout flapper and is mounted to the structural bulkhead. Two (2) manual release buttons, which release the door from its stowed position, are installed. This door includes EICAS annunciation to provide cockpit crew with validation if the door is not properly stowed during TT&L. The veneer is scored. Note: When a removable curtain is used in lieu of the sliding pocket door, straps, sewn to the curtain, and concealed magnets hold the curtain in the stowed position against the RH bulkhead. When deployed, concealed magnets hold the curtain against the LH and RH bulkheads.

3. Aft: A hinged door with a retractable header is located at the aft cabin bulkhead to close out the lavatory. A hold-open device, to retain the door in the open position, is installed. A door handle and a door lock for privacy with “break in” emergency capabilities are installed. A symbolic “NO SMOKING” placard is installed on cabin side. A flush-mounted coat hook is installed on the lavatory side. The door jam incorporates a seal to minimize light bleed.

Cabin Headliner The cabin headliner extends from the forward cabin bulkheads to the aft cabin bulkheads and from LH PSU to RH PSU. The headliner incorporates a flush mounted curtain track between the mid cabin bulkheads and is split at that location to facilitate maintenance. Passenger Service Units (PSU) A PSU is installed on the LH and the RH sides, between the upper sidewall and the headliner, extending from the forward cabin bulkheads to the aft cabin bulkheads. It is split at the mid cabin bulkheads to facilitate maintenance. The PSU incorporates the following:

1. A handrail along the upper edge. 2. Oxygen masks for each seating position. 3. Cabin entertainment system speakers. 4. PA speakers. 5. Individual adjustable air gaspers. 6. Emergency exit sign (Ref. Section 16). 7. Lighting (Ref. Section 16).


Sidewall A sidewall is installed on the LH and RH sides, from the PSUs to the sideledges and incorporates electric accordion-type window shades. The sidewall extends from the forward cabin bulkheads to the aft cabin bulkheads. It is split at the mid cabin bulkheads to facilitate maintenance. A switch located at the lower edge of the window reveal controls each window shade. The following exception applies: the window shades behind the 16G divan, which are controlled by a switch located at the upper edge of the window reveal. Sideledges A sideledge is installed between the forward cabin bulkheads and the aft cabin bulkheads and is split to accommodate maintenance. The sideledge incorporates the following:

1. Two (2) cup holders at each single seat location.

2. One (1) storage box at each single seat location – qty six (6).

3. Two (2) therapeutic oxygen outlets on the forward and aft RH side.

4. One (1) receptacle for a plug-in touch-screen HD monitor at each outboard double seat location under a separate flip-up lid.

5. Telephone handsets (Ref. Section 13). 6. One (1) switch panel at each single seat and

outboard double seat location. 7. Each single seat location has under a nesting

lid the following: a. One (1) audio jack. b. One (1) wireless PCU charging cradle

(Ref. Section 14). c. One (1) receptacle for a plug-in touch-

screen HD monitor (Ref. Section 14). d. RJ-45 outlets (Ref. Section 14).

8. Each double seat location has under a flip-up nesting lid the following:

a. One (1) audio jack. b. Two (2) wireless PCU charging cradles

(Ref. Section 14). c. RJ-45 outlets (Ref. Section 14).

Dado Panels The dado panels are installed on the LH and RH side between the lower edge of the sideledge and the air duct, extending from the forward cabin bulkhead to the aft cabin bulkhead. The dado panel

is split to accommodate maintenance and removal. It incorporates the following:

1. Electrical outlets (Ref. Section 13). 2. Emergency equipment (Ref. Section 17).

Floor Covering Two (2) custom carpets (includes one (1) spare) are supplied for the entire aircraft, with exception of the cockpit and baggage area. Factory standard materials are used for the cockpit and baggage carpet. Floors in the entrance area, cabin, lavatories and baggage compartment are sealed with protective sheeting to prevent liquids from leaking below onto critical areas (to protect avionics bay). All floor carpeting is 100% wool unless otherwise specified in the Material Specification. Weight and design are in accordance with the approved carpet sample. The carpet is pre-shrunk and sealed before cutting. It incorporates an anti-static backing. A carpet underlay is installed. Concealed threshold plates are installed at the forward cabin, aft lavatory and baggage compartment interior door. Stainless steel threshold plate is installed at the main entrance door. Mounting provisions are installed for the attachment of the maintenance runner. Throw rugs are provided as loose equipment (Ref. Section 21). Magazine Racks Two (2) magazine racks are installed as follows:

1. One (1) on the aft face of the RH forward cabin bulkhead, containing a subwoofer.

2. One (1) on the aft face of the LH forward cabin bulkhead, containing a cabin temperature sensor and a fire extinguisher.

Pull-Out Tables Three (3) bi-fold, sideledge deployed, pull-out tables (27” x 27”) are installed, one (1) in each single seat configuration. Mid–Cabin Hi-Lo Conference Table One (1) manually operated Hi-Lo table (30” x 41”) is installed between the double seats. The table is capable of being stowed in the down position for taxi, take-off and landing. The table incorporates the following:

1. Four (4) cup holders on the underside of two folding leaves.

2. Two (2) shin guards, one (1) at each folding leaf location.


3. Two (2) switch panels for each inboard double seat location.

Single Seats – Wide Six (6) single wide seats that have structural approval to 16G are installed and incorporate the following:

1. Approximate dimensions (upholstered): a. Height: 41” (104 cm) b. Width between armrests: 21” (53 cm) c. Overall seat width: 28 ¼” (72 cm) d. Armrests width: 3 ǫ” (9 cm)

2. Integrated headrest with adjustable height. 3. Berthing and recline (limited by surrounding

installations). 4. Articulating seat pan for enhanced berthing

comfort. 5. Manual in-base tracking and swiveling,

initiated via electrically assisted release button:

a. In-base forward/aft tracking: 9” (23 cm) b. In-base lateral tracking:

i. 4 ½” (11 cm) for forward cabin aft facing seats.

ii. 6 ½” (16 cm) forward cabin forward facing seats and aft cabin seats.

c. Swiveling: 345º 6. Manual floor tracking (forward cabin only). 7. Electric inflatable lumbar support. 8. Recliner style legrest. 9. Storage in armrests, accessible via front

latching doors. 10. Emergency equipment (Ref. Section 17).

Note: The main passenger cabin RH forward facing seat in the forward section and LH forward facing seat in the aft section are the Master Seat Locations. The Customer shall be invited for a comfort check of the seat, at Bombardier Aerospace facility in Dorval, Quebec. The Customer shall be advised of the date four (4) weeks in advance. If the Customer declines the invitation to participate at the proposed date, all seats shall be upholstered in accordance with the first sample seat. Seat Track Covers Seat track covers are installed as follows:

1. In front of each single wide seat in the forward zone.

2. Behind the two (2) forward facing single wide seats in the forward zone.

Double Seats Two (2) sets of double seats that have structural approval to 16G are installed and incorporate the following:

1. Approximate dimensions (upholstered): a. Height: 41” (104 cm) b. Width between armrests: 18” (46 cm) c. Overall seat width: 43” (109 cm) d. Inboard and outboard armrests width: 2

Ǫ” (6 cm) e. Center drop-down armrest: 2 ¼” (6 cm)

2. Integrated headrest with adjustable height. 3. Berthing and recline (limited by surrounding

installations). 4. Articulating seat pan for enhanced berthing

comfort. 5. Manual in-base tracking and swiveling,

initiated via electrically assisted release button:

a. In-base forward/aft tracking: 9” (23 cm) b. In-base lateral tracking:

i. Inboard seat: 5” (13 cm) ii. Outboard seat: 5” (13 cm)

c. Swiveling: 180º 6. Electric inflatable lumbar support. 7. Audio jack on front face of inboard armrests,

concealed behind hinged doors. 8. Emergency equipment (Ref. Section 17).

16G Divan One (1) 16G rated berthing divan equipped with telescopic shoulder harness posts is installed. The divan has take-off and landing seating for two (2) passengers when the removable bulkhead is installed, and three (3) passengers when the bulkhead is removed. The divan incorporates the following:

1. Overall frame length of 80.0”. 2. Upholstered width between end cabinets of

approximately 82”. 3. Three (3) color-coordinated telescopic seat

and shoulder harness assemblies. 4. Fire blocked cushions. 5. Berthing capability with release lever. 6. One (1) subwoofer under the forward section

of divan.


7. Storage space below the divan and accessible via drop-down doors (storage capacity is subject to life raft storage location).

8. Provisions for a sleeping belt, stored within the divan storage space (loose equipment).

9. Cabin emergency lighting (Ref. Section 16). 10. Emergency equipment (Ref. Section 17).

Divan End Cabinets Two (2) cabinets are installed, one at each end of the divan. The tow kick area has adequate space for conditioned air. ¾ The forward cabinet includes the following:

1. Two (2) cup holders. 2. One (1) miscellaneous storage compartment

behind hinged door with a removable/adjustable shelf with lip.

3. One (1) switch panel. 4. One (1) wireless PCU charging cradle and

one (1) audio jack, under a nesting lid. 5. Removable bulkhead groove and

attachment. 6. Lighting (Ref. Section 16).

¾ The aft cabinet includes the following: 1. Two (2) cup holders, one with a removable

plug-in ashtray. 2. One (1) miscellaneous storage compartment

behind hinged door with a removable/adjustable shelf with lip.

3. One (1) switch panel. 4. One (1) wireless PCU charging cradle and

one (1) audio jack, under a nesting lid.

5. Lighting (Ref. Section 16). 6. Emergency equipment (Ref. Section 17).

Credenza A credenza is installed in the RH mid cabin. The lower toe kick area has adequate space for conditioned air. The cabinet includes the following:

1. Miscellaneous storage. 2. Media storage in the lower portion of the

cabinet. 3. Nesting and hinged doors. 4. One (1) cabin color Printer / Copier / Scanner

machine on a slide-out tray. 5. One (1) paper storage drawer. 6. One (1) wireless PCU charging cradle. 7. One (1) switch panel. 8. Decompression grill. 9. Exhaust fan (Ref. Section 4). 10. Electrical outlets (Ref. Section 13). 11. Entertainment equipment (Ref. Section 14). 12. Lighting (Ref. Section 16).

Low Cabinet A low cabinet is installed aft of the credenza cabinet and adjacent to the over wing emergency exit. The lower toe kick area has adequate space for conditioned air. The low cabinet includes the following:

1. Hinged, flip-up lid with hold-open device. 2. Emergency exit sign (Ref. Section 16). 3. Lighting (Ref. Section 16). 4. Emergency equipment (Ref. Section 17).


10. AFT LAVATORY COMPARTMENT AND WARDROBE

10.1. RH Aft Lavatory

The aft lavatory is defined as the area aft of the aft cabin bulkheads and forward of the RH baggage bulkhead, encompassing the RH toilet and vanity. Bulkheads The aft cabin bulkhead and baggage bulkhead serve as the aft lavatory bulkheads. The bulkheads incorporate the following:

1. A towel bar on the forward bulkhead. 2. A reflective synthetic glass on the aft

bulkhead. 3. Lighting (Ref. Section 16).

Doors

1. See Section 9 for the aft lavatory, forward compartment door.

2. A hinged door with a fixed header, decompression blow-out capability and full-length reflective synthetic glass on the forward face, separates the aft lavatory and the baggage compartment. The door is acoustically sealed along the edges to reduce sound transmission. A hold-open device to retain the door in the open position is installed.

Headliner The headliner extends from the aft cabin bulkheads to the baggage bulkheads and incorporates the following:

1. One (1) PA speaker. 2. Lighting (Ref. Section 16).

PSU The PSU is installed on the RH side of the aft lavatory zone above the aft toilet enclosure. It extends from the RH aft cabin bulkhead to the RH baggage bulkhead and incorporates the following:

1. A handrail. 2. One (1) air gasper. 3. One (1) dual oxygen drop box. 4. Lighting (Ref. Section 16). 5. Emergency equipment (Ref. Section 17).

Sidewall A sidewall is installed on the RH side, from the PSUs to the vanity and incorporates one (1) electric accordion-type window shade. The sidewall extends from the aft cabin bulkhead to the baggage bulkheads. The lavatory window shade has a switch located at the upper edge of the assembly to operate the shade. Note: The forward window is installed with a fixed shade in the closed position. Vanity A vanity cabinet is installed and incorporates the following:

1. A countertop with splashguard. 2. One (1) sink and faucet. 3. One (1) soap dispenser. 4. One (1) facial tissue dispenser. 5. One (1) toilet paper dispenser. 6. One (1) removable sealed waste container. 7. One (1) switch panel. 8. One (1) toilet flush switch panel. 9. Miscellaneous storage as space permits. 10. Conditioned air with decompression grille. 11. Water system components. 12. Electrical outlet (Ref. Section 13). 13. Lighting (Ref. Section 16).

Toilet and Enclosure A vacuum toilet assembly is installed on the forward side of the lavatory. The toilet enclosure is installed and incorporates the following:

1. One (1) hinged, padded lid with hold-open provisions.

2. One (1) exhaust fan to duct odors under the floor.

3. Access panel for toilet manual override feature.

4. Decompression grille. 5. One (1) tissue dispenser. 6. One (1) miscellaneous storage compartment

behind removable backrest (hidden). 7. Lighting (Ref. Section 16).


10.2. Aft Wardrobe and Storage Cabinet

An aft wardrobe and storage cabinet are installed on the LHS of the lavatory compartment. The aft wardrobe and storage cabinet are enclosed by hinged doors and incorporate the following: Header The header of the cabinet incorporates the following:

1. Two (2) switch panels. 2. Lighting (Ref. Section 16).

Wardrobe (Fwd Section) The forward wardrobe section incorporates the following:

1. One (1) removable coat rod. 2. One (1) fixed shelf. 3. Access panels. 4. Conditioned air with decompression grille.

5. Exhaust fan (Ref. Section 4). 6. Lighting (Ref. Section 16). 7. Emergency equipment (Ref. Section 17).

Storage (Aft Section) The aft storage cabinet section incorporates the following:

1. Three (3) removable/adjustable shelves. 2. Two (2) fixed shelves. 3. Access panels. 4. Conditioned air with decompression grille. 5. Lighting (Ref. Section 16).

Note: The window outboard of the aft wardrobe is installed with a false accordion type window shade in permanently closed position (non-operational).


11. BAGGAGE COMPARTMENT

The baggage compartment extends from the baggage bulkheads to the aft pressure bulkhead. It is lined with factory installed materials. The compartment incorporates the following:

1. Two (2) fold-down shelves with support gussets and restraint straps.

2. One (1) baggage net across door. 3. One (1) 60” removable hang-up bar. 4. One (1) LH fold-up hang-up bar. 5. ACPC access panel. 6. Storage provisions for the removable mid

cabin bulkhead.

7. Miscellaneous storage (depending on options installed).

8. One (1) net to prevent bags from falling against external baggage door.

9. One (1) flip-out baggage door flap protective cover for the outer fuselage skin with a stainless steel threshold plate.

10. Conditioned air outlet. 11. External baggage door lock override (Ref.

Section 15). 12. Lighting (Ref. Section 16). 13. Emergency equipment (Ref. Section 17).


12. AVIONIC SYSTEMS

Factory installed avionic equipment is listed in “Schedule A”. The Completion installed equipment follows. LCD Head-Up Flight Display System The HUD is an optical and electronic LCD system which generates and displays information in the pilots’ forward field of view. The installation provides a system capable of supporting all phases of flight including manual precision approaches down to CAT II Minima with a Decision Height (DH) of 100 ft. Guidance information is echoed by the HGS, using the modes and commands provided by the factory installed Automatic Flight Control System (AFCS). Enhanced Vision System (EVS) The Enhanced Vision System (EVS) provides the flight crew with improved situational awareness during the critical flight phases such as take-off, approach and landing. The EVS provides increased visual range and may allow the pilot to acquire reference cues at Decision Height (DH) to continue an approach. The Infra Red (IR) image is available head up on the HUD and head down on the main displays. The EVS system consists of an IR Camera, an aerodynamic fairing with window and a de-icing heat controller. Cockpit Multifunction Touch-Screen Display One (1) 8.4-inch Multifunctional Touch-screen Display, EFB #2, is installed on the fwd RH side of the cockpit and one (1) Aircraft Interface Unit (AIU) is installed in the RH side console. This installation provides the flight crew with a variety of display information, including:

� Passenger briefing. � Cabin / Lavatories call Display & Reset. � Internet Access via Cabin Wireless LAN. � Entrance light control. � Cabin Presets.

� Back-up to the galley touch-screen (except for local video touch-screen ‘Off’ and touch-screen brightness control).

� Navigation charts (airport, approach) [1] � Graphical weather application [2] � Aircraft Flight Manuals [1] � Camera Video Inputs (if option selected).

System can host other software packages. [1]: Chart application and associated Jeppesen charts subscription to be obtained by the operator. [2]: Weather subscription to be obtained by the operator. Weather information is received from the subscription supported Airshow Network Operations Center (NOC) ground station via the onboard Iridium telephone system. Lightning Detection System The LDS finds, calculates and displays the location of lightning 360 degrees around the aircraft and operates out to a range of 200 nautical miles. It is made up of an antenna, a processor and related system wiring. The antenna detects the magnetic and the electrical fields produced by lightning and convert these magnetic fields into electrical signals that can be used by the processor. The processor processes the electrical signals from the antenna to calculate the following data: intensity, range and bearing of the lightning. The lightning data derived from the processor is sent to the Primary Flight Displays (PFD) and Multi Function Displays (MFD) for display.


13. COMMUNICATION & ELECTRICAL SYSTEMS

Any new equipment installed by Bombardier Global Completion Center to supplement the factory avionics package conforms to all applicable TC or FAA requirements. These systems are accomplished in a quality and manner that meet or exceed industry standards. ARINC 781 Satellite Communication (SATCOM) System (SAT-2200) The Collins SAT-2200 allows simultaneous multi-channel access through the Inmarsat satellite system. One (1) channel (maintenance channel) is dedicated to Aircraft Earth Station - Ground Earth Station (AES-GES) management and data transmissions. Note: The maintenance channel on the SAT-2200 handles ACARS communications. The remaining channel (Aero H+) is available for voice and data transmission from the cockpit or the cabin. A separate low cost voice channel and a Broadband Data channel at speed up to 432 kbps data transfer rate are provided by the Swift Broadband channel. The Inmarsat classic services provide communication coverage over non-polar regions of the earth when using a high gain antenna. The SAT-2200 supports direct access to the cockpit Audio Integrated system, on the three (3) ACPs. It also provides CEPT-E1 interface to the Aerocom-3000 Cabin Telecommunications Unit for voice calls and one (1) SBB channel, which interfaces with the CES Ethernet Backbone. The SAT-2200 system interfaces with the green aircraft maintenance system. The fault reporting is done through the eCDU and the galley touch-screen. The eCDU also allows system setup and troubleshooting. SAT-2200 advanced troubleshooting is performed through a service connector via a laptop. The SAT-2200 baseline configuration includes the following:

� Arinc 781 Satellite Receiver Transmitter � AMT-700 SATCOM Antenna � Diplexer / Low Noise Amplifier, type F

Iridium Telephone System The Iridium based telephone system from International Communications Group (ICG) provides a seamless global access to high quality voice communication through the Iridium satellite constellation. The Iridium telephone system is designed around the Aerocom 3000 CTU (Cabin Telecommunications Unit). The CTU allows multiple devices to be connected and acts as a PBX using both cabin onboard transceivers (Iridium ICS and SAT-2200). The Iridium System fault reporting is done through the galley touch-screen. The baseline Iridium Telephone System includes the following:

1. CTU. 2. Iridium Transceiver. 3. Iridium Antenna.

Note: In specific conditions related to aircraft heading and the location of the Inmarsat and Iridium satellites in use, interference between the Inmarsat system and the Iridium system have been noticed.

This interference can have a negative impact on the quality of the Iridium communication, including denial of service, and is related to the proximity of the frequency ranges used by the two L-Band Satellite Communication systems. However, it is possible to disable the Inmarsat system in the event there is interference between the two systems.

Bombardier is not responsible in any manner for any loss of use or any resulting damages, due to poor quality of communication, lack of service or other inconvenience as a result of the possible interference between the Inmarsat and Iridium systems. Telephone Handsets Telephone handsets access both telecom systems (Iridium and SATCOM). The default system is the Inmarsat (low cost) system. If the Inmarsat (low cost) system is unavailable, the CTU automatically routes the call through the Iridium system. Handsets and ringers are installed as follows:


1. One (1) Sigma 7 corded backlit handset in the cockpit center pedestal.

2. Three (3) corded backlit handsets in the cabin sideledges under nesting lids:

a. One (1) in the RH forward cabin at the forward facing seat location.

b. One (1) in the LH forward cabin at the forward facing seat location.

c. One (1) in the LH mid cabin outboard of the conference table under a flip-up lid.

3. One (1) cordless handset and charging cradle in the LH aft cabin at the forward facing seat location under a flip-up lid.

4. Five (5) external ringers, installed as follows: a. One (1) in the cockpit. b. Four (4) in the cabin sideledges.

Cabin Printer/Copier/Scanner A plain paper color inkjet printer/copier/scanner is installed in the credenza on a pull-out drawer, to enable printing from each seat position. Printing access from the customer-supplied laptop is achieved through the RJ-45 network ports and through the Wireless LAN system. Passenger Address (PA) System A PA amplifier is installed to provide announcements and “NO SMOKING / SEAT BELT” chimes in the cabin. Whenever the PA system is in use, the entertainment system audio is muted. The system incorporates the following:

1. One (1) integrated chime / page amplifier. 2. Ten (10) PA speakers - One (1) in each

lavatory, one (1) in the entry area and six (6) in the cabin PSU.

Cabin Bus and Cabin Outlets Disconnect A PBA is installed in the cockpit overhead panel to shed power to the cabin systems, except cabin systems related to flight safety. A cabin outlets PBA is installed in the cockpit overhead panel to shed power to the cabin electrical outlets. Ground Service Cabin Power When AC power is provided to the aircraft via the external AC receptacle, it is possible to energize the cabin interior by using:

1. Battery master switch and cabin power PBA located on the cockpit overhead panel – All cabin systems are powered (available).

2. Ground service switch located on the external service panel and cabin power PBA located on the cockpit overhead panel – All systems will be powered (available) except: A. Units/systems powered from DC 1 Cabin

Feed 2: - Passenger monitors. - Security system (if option selected). - Electric Hi/Lo Table (if option selected). - Multimedia Ports Encoder (if option

selected). - Pop-up monitor (if option selected). - Camera system (if option selected). - Floor mat heaters in Fwd Cabin

(if option selected). - Satellite TV system (if option selected). - IPOD (if option selected). - CNX Accelerator (if option selected).

B. Systems that require green aircraft systems input or powered by green aircraft busses: - Telephone system. - Satcom system. - PA system. - Weight-On-Wheels Relay. - Ordinance signs. - Galley/Galley Annex exhaust fans. - Satellite TV system (if option selected).

Cabin Circuit Breaker Panel A circuit breaker panel is installed on the cockpit at LH cockpit bulkhead. It provides fixed frequency power to cabin outlets installed throughout the cabin, to cockpit outlets and to all essential cabin systems directly connected to aircraft power buses. Electrical Power One (1) factory installed 3500 VA / 115 VAC / 60 Hz power converter is installed in the avionics bay to provide power for interior installations. Electrical Outlets The following GFCI protected 115 VAC / 60 Hz electrical outlets are installed:

1. Two (2) single electrical outlets in the cockpit, one (1) on the fwd face of each cockpit bulkhead, rated for personal computer use.

2. Two (2) dual electrical outlets, one (1) in each lavatory, rated for hairdryer use.


3. One (1) dual electrical outlet in the LH entrance enclosure.

4. One (1) dual electrical outlet in the RH galley. 5. One (1) dual electrical outlet in the LH galley. 6. Eight (8) single electrical outlets in the cabin

dado panels, behind a spring loaded door,

rated for personal computer use - one (1) at each single seat location and each outboard double seat location.

7. One (1) dual electrical outlet in the credenza, behind a touch-latch door.


14. CABIN ELECTRONIC SYSTEM (CES)

The Rockwell Collins Cabin Electronic System (CES) incorporates aerospace grade switch panels; wireless Passenger Control Units (PCUs), plug-in touch-screen HD monitors and HD Source & display equipment (including Blu-ray/CD/DVD combined units with MP3 capability and HD bulkhead monitors).


(Note: English Language only) All wireless PCUs, switch panels and touch-screen HD monitors are designed to facilitate passenger and crew operational or functional tasks and controls in regards to the Global Office, Entertainment, Cabin Utilities, Displays, Maintenance and Diagnostics. The CES also controls, displays and monitors cabin systems such as temperature (limited control), lighting, , Interactive Airshow system, wireless PCU MSL assignment (on ground/in-flight), selected galley systems (oven, galley exhaust fan), Attendant Call system, oxygen, water and waste systems. All specific functions are in accordance with the approved floor plan and switch panel document. The CES system design is based on the following concepts:

� Centralized processing. � Centralized data concentration. � 10 / 100 / 1000 Base T Ethernet network. � Network distribution equipment. � Power Distribution Equipment. � Relay Distribution equipment. � On-Board Wireless LAN.

The CES integrates the control, display and maintenance of all interior cabin systems. The CES is separated into the following functional groups:

A. Global Office. B. Cabin utilities. C. Entertainment. D. Control and Display. E. Maintenance and Diagnostics.

Note: The Customer must define their CES requirements within 90 days of final Contract Change Order approval. The default selections shall be deemed acceptable, if selections have not been made.

DEFAULT

SELECTION ALTERNATE SELECTION

Rockwell Collins & Bombardier Logo on GTSE

With "Logos" Without "Logos"

Temperature Display Type

Fahrenheit Celsius

Global Office The Global Office functionality is divided as follows:

� Local area network (LAN). � Printer / Copier / Scanner. � Email and Internet access. � Off aircraft connectivity. � Network security.

The heart of the Global Office is the Ethernet network. This Local Area Network (LAN) is equipped with RJ-45 outlets at each seat grouping, as well as a wireless access point. The wireless LAN unit provides wireless connectivity throughout the aircraft cabin to devices that have wireless capability. The heart of the Ethernet network is the Ethernet Switch Equipment (ESE) located within each of the central processing cabinets. The Global Office, accessed through the RJ45 ports or Wireless LAN, offers the following features:

� Wireless local area network (LAN) access, in addition to the RJ-45 network ports.

� Access to the Printer / Copier / Scanner. � Off aircraft connectivity (E-mail & internet). � Network security. � File sharing. � On-board Maintenance System (OMS)

access. Thirteen (13) RJ-45 outlets are installed as follows:

1. Two (2) in the cockpit, one (1) on the fwd face of each cockpit bulkhead, for CES maintenance purposes.

2. Three (3) in the LH entrance enclosure – one (1) for OMS (On-board Maintenance System) and two (2) for AFDX download.

3. Eight (8) in the cabin sideledges at each cabin seat location - under a nesting lid for single seats and under a flip-up lid for double seats.

Cabin Utilities The CES provides control, display and monitoring of the cabin utility functions. Cabin utilities include the following:

� Cabin Temperature Control. � Door control main entrance (Local control

only). � Power Distribution system. � Galley systems. � Lighting systems. � Ordinance signs. � Oxygen system. � Waste system. � Water system.

Entertainment System

Audio System An audio system is installed to present audio through cabin speakers and/or stereo headphones from all available audio sources, which incorporates a digital graphic equalizer. Speakers are 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 incorporates the following:

1. Ten (10) speakers in the cabin PSU. 2. Four (4) subwoofers in the cabin. 3. Two (2) dual Blu-ray disk players, providing

four (4) simultaneous independent Blu-ray/CD/DVD/MP3 operations.

4. Cabin audio power amplifier.

Note: For DVD playback functions (only), the player has some limitations for multi-regions support: a maximum of 4 region changes are allowed (per slot) from the initial Region Code (Region No.1) before the individual disc player slot will lock to the last DVD region selected.

The Galley HD Touchscreen will provide status on current configuration and remaining changes. It will also provide guidance as how to change the region on an individual disc player slot.

All Blu-ray playback functions remain multi-region, without any limitation.

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

1. Two (2) 24” HD monitors: a. One (1) aft facing on the RH forward

cabin bulkhead. b. One (1) forward facing on the LH aft

cabin bulkhead. 2. One (1) 10.6” touch-screen HD monitor (galley

annex) 3. Two (2) Blu-ray dual disk Blu-

ray/CD/DVD/MP3 players. 4. Eight (8) receptacles for 10.6” plug-in touch-

screen HD monitors in the cabin sideledges. Two (2) 10.6” plug-in touch-screen HD monitors in pouches are provided as loose equipment (Ref. Section 21).

Airshow ASXi Interactive Flight Information System An Airshow ASXi Interactive Moving Map and Flight Information system is installed to complement the entertainment system. The system combines the graphic capabilities hosted in the MCE with onboard avionics to provide updated flight, business, and leisure information in the English language over the video display system to the cabin occupants. The flight crew interface for the Airshow system, including audio briefing cueing is via the cockpit touch-screen equipment (CTSE). Airshow Interactive incorporates the following presentations:

1. Worldwide Map (Topographic with Borders). 2. No Smoking” and “Fasten Seat Belt” overlay

graphics. 3. Static logo (Customer supplied customized

artwork required in the form of 800 X 600 JPEG digital file).

4. Relative Location Indicator. (Two Closest Cities)

5. Information Display The flight information on the dislay toggles between metric / imperial in the case of units, and between 12H / 24H in the case of the clock.


6. Audio Breifing Four standard briefings are provided in the English language.

x Pre Departure x Over Water x Turbulance x Landing

7. Airshow Ticker Information The Airshow Ticker will scroll six lines of information. Each line contains three flight

information parameters such as altitude, speed, time to destination etc (total 18).

Note 1: Subscription to Intellicast Cabin Weather is required for the crew to access NEXRAD radar summaries from WSI Corporation for display on the CTSE. Note 2: The Customer must define any Airshow requirements or changes within 30 days of final Specification approval..

Control and Display The CES provides multiple control display devices to allow cabin crew, passengers, and flight crew to interact with various cabin systems. Control / display devices are located in the galley, each seat in the cabin, various other cabin locations, and in the cockpit.

1. One (1) cockpit RH multifunction touch-screen Display - EFB #2.

2. One (1) galley annex 10.6” touch-screen HD monitor.

3. Switch panels. 4. Touch-screen activated Wireless Passenger

Control Units (PCUs), including two (2) VIP configured units, one (1) entertainment configured unit and one (1) spare unit in the cabin (Ref. Section 21).

5. 10.6” plug-in touch-screen HD monitors (Ref. Section 21).

Maintenance and Diagnostics The CES provides a central maintenance function for all integrated cabin systems that is equivalent to the maintenance computer function typically associated with avionics systems. The cabin maintenance function for the Global 5000™ Global Vision is capable of providing a variety of maintenance reports such as:

1. Top level basic health status (i.e normal, inoperable or unavailable) for all integrated subsystems.

2. Detailed fault data report. 3. Fault data history. 4. Results of initiated self test.

Maintenance diagnostic data (reports) can be viewed on the Galley TSE, downloaded to a portable processing device such as a laptop computer, or

routed to the network printer to generate a hard copy. The quality and resolution of maintenance diagnostic data received from the various cabin subsystems varies greatly. Some of the systems, such as the water system, which utilize a digital controller, should be capable of providing detailed diagnostic data to the CES. Other cabin systems may simply report a single top-level basic health status discrete or possibly a series of discretes. For those units that comprise the CES itself, each unit is expected to implement robust self-test features. At a minimum, all units are expected to report on the status of their processor (if applicable) as well as all active I/O ports. All units report their status to each processor cabinet directly when such a communication path is possible. The maintenance functions in each cabinet should exchange information as well. All maintenance diagnostic messages from both cabin subsystems as well as CES equipment are periodic transmissions. Thus the absence of a fault message is, itself, a fault condition. The processor cabinets exchange “status” messages between them to allow for master / slave operation. All maintenance diagnostic information is displayed in plain English messages. The Galley TSE provides specific control screens to perform all standard maintenance activities. These specific control screens are “hidden” from the user during normal operations. Cabin/Lavatories Call System The cabin/lavatories call system is integrated into the CES and provides the following functions:

1. Call buttons are located at each passenger switch panel in the cabin and in both lavatories.


2. Chime rings at the galley position. The galley touch-screen control panel graphically indicates the position of the call.

3. A visual annunciation on the Cockpit EFB #2 for cabin, forward lavatory and aft lavatory calls.

4. The crew is able to reset calls through the touch-screens in the cockpit and at the galley.


15. MISCELLANEOUS INSTALLATIONS

Addition of Refuel/Defuel Control Panel A refuel/defuel panel is located in the upper portion of the LH entrance enclosure. This additional panel allows the flight crew to perform refueling/de-fueling operations from the interior of the aircraft. Commands from this panel override commands from the standard external panel. Increase Maximum Take-Off Weight (MTOW) to 88,700 lbs (SB 700-1A11-11-005) This option replaces the two airspeed limitation placards in the flight compartment and introduces new exterior placards for the main landing gear (MLG) doors and nose landing gear (NLG) door to permit operation of the aircraft with the increased MTOW from 87,700 lbs (39,780 kg) to 88,700 lbs (40,233 kg). Towbar Assembly Complete provisions are installed in the aft equipment bay for a three-piece Tronair towbar assembly, including a 2 3/16” diameter towing eye. The towbar assembly is provided as loose equipment (Ref. Section 21). Aft Equipment Bay Storage Box A storage box (maximum weight limit of 60 lbs) is installed on the aft equipment bay catwalk. The box is 8” (wide) x 10” (high) x 19” (long). Catwalk Battery Access Access is made available through the catwalk in order to disconnect the main battery easily. Handrail Extension One (1) handrail extension is installed on the forward side of the airstair and attaches to the LH entrance enclosure. Common Key Panels The external doors have a common key for the following locks:

1. Main entry passenger door. 2. Ground communication access door. 3. Refuel/de-fuel panel access door. 4. Baggage door.

5. Aft hydraulic access door. 6. AC external power access door. 7. DC external power access door. 8. Aft equipment compartment door. 9. Oxygen service panel access door. 10. Water service panel access door. 11. Waste system access door. 12. High pressure pneumatic system access door. 13. Forward LH avionics bay door. 14. Forward RH avionics bay door.

Note: The locks are installed in the same, keyed direction on all locks. Multi-Purpose Ladder One multi-purpose ladder is installed in aft equipment bay. It enables access to aft equipment bay and freestanding access to other locations, such as the baggage compartment. This is the one and only ladder in aircraft. External Service Door Hold-Open Feature A hold-open feature is installed to the following external service doors:

1. Aft equipment bay door (Factory installed). 2. Hydraulic manifold door (Factory installed). 3. Aft overboard service door (Factory installed). 4. Refueling point access door (Factory

installed). 5. AC external power door (Factory installed). 6. Aft water service door (Factory installed).

External Baggage Door Lock Override (Factory Installed) 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 is always locked until unlocked from the outside. EICAS Door Open “SMALL SERV DOOR” Annunciation


The factory installed annunciation is provided on the EICAS when any of the following access door panels are left open:

1. Oxygen service panel door. 2. Water system service panel door. 3. Ground communication service panel door.

4. Waste system service panel door. 5. AC external power panel door. 6. DC aft external power panel door. 7. Avionic bay access door.


16. LIGHTING

Interior L.E.D. lighting is installed as follows: Airstair and Boarding Lights Boarding lights, powered by the battery direct bus, are powered only if the main cabin door is open. A switch on the main door control panel and on the LH entrance enclosure also provides control to these lights. The boarding lighting system activates the following:

1. One (1) recessed light on each of the airstair step riser (factory installed).

2. Two (2) flush-mounted lights in the airstair step-well (factory installed).

3. One (1) cockpit dome light (factory installed). 4. One (1) entry area headliner dome light. 5. One (1) aft lavatory headliner dome light.

Cockpit Lights

1. One (1) dome light in the cockpit headliner controlled by a local switch powered from the main DC bus.

2. One (1) flight observer seat reading light (dimmable 0-100%).

3. Two (2) map lights in the cockpit overhead panel (dimmable 0-100%). These lights are in addition to production-installed map lights on the windshield post (pilot and co-pilot), which are retained.

4. One (1) area light, factory installed, is retained, forward of the dome light.

Entrance Area Headliner Lights

1. One (1) dome light powered by the DC cabin feed and controlled (On/Off) by the switch panel located on the LH entrance enclosure header and by the galley touch-screen HD monitor. Boarding Lights function controls the entry area dome light as well.

2. RH and LH galley dome lights. 3. Emergency lights.

LH Entrance Enclosure Lights

1. One (1) strip light (door activated). 2. Emergency lights.

Forward Lavatory Lights

1. Mirror lights.

2. One (1) dome light in headliner. 3. Upwash lights.

Galley and Galley Annex Lights

1. Effect wash lights outboard of crystal storage. 2. Work lights and night lights to illuminate

counter top. 3. Floor accent lights. 4. Emergency lights.

Cabin Upwash and Downwash Lights Forward and aft cabin wash lights are separately controlled and include variable dimming and color presets. The variable dimming is from 0% to 100%. Cabin upwash and downwash lights consist of two (2) rows each of “White/Amber/White/Red LED lights”. Ten (10) presets colors are stored in the CES system. Upper and lower wash lights are concealed behind the cabin PSU on both sides. Cabin Reading and Table Lights Individually controlled, reading lights and table lights are located in PSUs and incorporate the following:

1. One (1) reading light for each seat location. 2. One (1) reading light for each divan seat

location. 3. One (1) table light for each pull-out table. 4. Two (2) table lights for the conference table. 5. Three (3) table lights for the credenza. 6. One (1) table light for the low cabinet.

Floor Accent Lights

1. Forward vanity and toilet enclosure toe kick space (privacy latch activated).

2. Galley and galley annex toe kick space. 3. Forward cabin: Along the air ducts on the LHS

and RHS, and credenza and low cabinet toe kick space.

4. Aft cabin: Along the air ducts on LHS and divan end cabinets toe kick space on the RHS.

5. Aft vanity and toilet enclosure toe kick space. 6. Aft wardrobe and storage cabinet toe kick

space.


Credenza Lights 1. Five (5) compartment lights (door activated).

Low Cabinet Lights 1. Emergency lights.

Aft Lavatory Lights

1. Mirror lights. 2. Upwash and downwash lights concealed

behind the PSU. 3. One (1) dome light in the headliner. 4. One (1) reading light in the PSU.

Aft Wardrobe and Storage Cabinet Lights

1. Two (2) strip lights (door activated). Baggage Compartment Lights Three (3) caged dome lights are installed in the baggage headliner. A switch on the aft wardrobe header controls the lights. A switch in the AC ground power panel also controls the lights. Each of these switches turns on the baggage lights for twenty (20) minutes at which time they automatically turn off. Ordinance Signs

1. One (1) “NO SMOKING (permanently illuminated) / RETURN TO SEAT" ordinance sign on the forward lavatory aft bulkhead.

2. Six (6) illuminated “NO SMOKING / FASTEN SEAT BELT” ordinance signs in the main cabin PSUs.

3. One (1) “NO SMOKING (permanently illuminated) / RETURN TO SEAT" ordinance sign in the aft wardrobe header.

Emergency Lights Emergency lights are powered by the factory installed Emergency Lighting Power Supply units (ELPSs) without any connection to the CES. Emergency lighting system incorporates the following:

1. One (1) dome light in the entrance headliner. 2. Reading lights in the cabin for general cabin

illumination, as required for certification. 3. Exit signs:

a. One (1) exit sign (horizontal) in the entrance headliner above the main passenger door.

b. One (1) exit sign (vertical) in the RH galley forward bulkhead (aft face).

c. One (1) exit sign (vertical) in the LH forward cabin bulkhead (aft face).

d. One (1) exit sign (wedged) in the forward RH PSU above the emergency exit door.

e. One (1) exit sign (vertical) in the LH mid cabin bulkhead (aft face).

4. Low-level exit signs: a. One (1) exit sign (vertical) on the LH

entrance enclosure bulkhead (aft face). b. One (1) exit sign (horizontal) in the low

cabinet toe kick space. 5. Escape path lights are installed on the inboard

face of the seat bases, divan base and at the galley toe kick space, as required for certification.

Exterior Service Panel Lighting Exterior service panels lighting system incorporates the following (opening the specific door controls the light):

1. Aft lavatory service station panels. 2. Fresh water fill station panel. 3. Hydraulic access panel. 4. Fuel fill service station panel. 5. Oxygen service panel. 6. Forward ground service communication panel. 7. AC ground power panel.

Pylon Lights Lights are installed on the underside of the engine pylons. Switches in the following locations control the lights:

1. AC ground power panel (factory installed). 2. Aft wardrobe header.

Each switch turns on both pylon lights indefinitely unless the aircraft is on battery power at which time, after twenty (20) minutes they automatically turn off. Service Light Timer Cabin Power Override System This installation provides direct 28 VDC, via cabin feed, to illuminate the basic aircraft maintenance lights (service panel lighting, wheel well, baggage, and pylon lights). This installation overrides the basic aircraft 20-minute maintenance light timers, which are fed by the batteries. 28 VDC cabin power is available by using an external power cart, or with the APU or engines running. If the service lights are inadvertently left on before take-off, the 28 VDC


cabin feed to these lights is cut upon weight off wheels. Wheel Well Maintenance Lights

The factory installed system, comprised of nose landing gear light, main landing gear wheel well lights (LHS and RHS) and external switch with timer, is modified to incorporate control from cabin power override system.


17. EMERGENCY EQUIPMENT

This aircraft is equipped with emergency equipment that meets the FAR Part 135 requirements. Cockpit

1. Two (2) rechargeable flashlights kits, engraved with the aircraft registration, one (1) on each cockpit bulkhead.

2. One (1) factory installed emergency equipment box containing the following: a. One (1) Halon fire extinguisher on the

RH cockpit bulkhead. b. One (1) crash axe on the RH cockpit

bulkhead. c. One (1) portable breathing equipment

(PBE) (protecting the eyes, nose and mouth and providing breathing oxygen for not less than fifteen (15) minutes) on the RH cockpit bulkhead.

3. Two (2) crew life vests, one (1) under pilot and one (1) under co-pilot seat (factory supplied).

LH Entrance Enclosure

1. One (1) laminated emergency equipment location placard.

2. One (1) first aid kit. 3. One (1) crew life vest. 4. One (1) rechargeable flashlight kit, engraved

with the aircraft registration number. 5. One (1) quick donning oxygen mask with

smoke goggles for the flight observer seat occupant.

Galley and Galley Annex

1. One (1) FAR Part 135 compliant life raft (5-man) with a 406 MHz ELT in the LH galley annex.

Cabin 1. Ten (10) passenger life vests (in pouches)

for seat occupants – one (1) at each single seat legrest and each double seat bucket shroud.

2. Three (3) passenger life vests (in pouches) for divan occupants – one (1) at each divan seat base storage compartment.

3. Two (2) FAR Part 135 compliant life rafts (6-man) with a 406 MHz ELT - one (1) in the low cabinet and one (1) under the divan.

4. One (1) over wing emergency escape lanyard.

5. Two (2) Halon fire extinguishers – one (1) in the forward LH magazine rack and one (1) in the aft divan end cabinet.

Lavatories

1. Two (2) smoke detectors with EICAS annunciation – one (1) in each lavatory.

Aft Wardrobe/Storage

1. One (1) Halon fire extinguisher. 2. One (1) portable breathing equipment (PBE)

(protecting the eyes, nose and mouth and providing breathing oxygen for not less than fifteen (15) minutes).

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


18. EXTERIOR PAINT

The paint application process is carried out as per Bombardier Global Completion Center procedures in line with the recognized manufacturer and/or industry practices and certification requirements. The aircraft detailed paint is done in accordance with the Customer approved drawing. Note: The customer must provide the aircraft registration 90 days prior to the aircraft’s scheduled paint slot in Bombardier Global Completion Center. The following provisions and/or requirements are provided: A. The aircraft exterior paint is one (1) single color,

non-metallic base paint with two (2) straight stripes shown on fuselage nacelles and winglets.

B. The paint consists of an Epoxy primer and a Polyurethane topcoat.

C. Registration marking is painted in one (1) color. D. All exterior markings are done by the silk-screen

method. E. An aerodynamic sealant on inboard wing leading

edge around the navigation light cover and the stabilizer fixed leading edge is removed before paint. The sealant is reinstalled after the paint process and painted where it does not come into contact with the leading edge.

F. Composite materials coated with an anti-static paint are retained as received from the factory.

G. The main entrance door, baggage door, edges and frames are painted.

H. The airstair at the main entrance is painted the same color as the bottom of the fuselage.

I. The inside of all service door panels, inside of all modified fairing and compartments are painted the same color as the aircraft fuselage.

J. The landing gear is retained as received from the factory (white).

K. A 3M plastic erosion protective plastic is installed over the radome after paint, winglet leading edges and lenses and the horizontal tips.

L. The original bright work on the aircraft exterior is highly polished. This includes the vertical stabilizer, wings, winglets, engines (cowl and pylon) and horizontal stabilizer leading edges.

M. The following features are polished: a. Cabin window surrounds (1-inch); b. Section around and aft of the APU exhaust,

to prevent discoloration of the paint from the hot exhaust;

c. APU access door cowling latches; d. Baggage door handle; e. Winglets; f. Engine pylon leading edges; g. Surround of the grill under pylon; h. Main entrance door kickplate; i. Baggage door kickplate; j. Kidney panels (qty 2) and camlock

fasteners; N. The latches on any access panel i.e., the

avionics compartment, radome, engine, hydraulic pump access covers, are retained as per the original finish.


19. WEIGHT AND CENTER OF GRAVITY

The aircraft is weighed upon completion. A Weight and Balance Report including loading charts and an equipment listing are provided as required by regulations. The Delivered Weight Empty (DWE) for the configuration outlined in this specification will not exceed the estimated DWE, with a tolerance of plus or minus one percent tolerance in accordance with the Weight and Balance Estimate.

Full Fuel Loading ¾ Consists of all operating items as specified

in the estimated weight and balance document, allowable forward seated passengers and a baggage allowance of 30 lb. per passenger with the full fuel to maximum ramp weight.

Full Passenger Loading

¾ Consists of all operating items as specified in the estimated weight and balance document, full passengers, a flight observer, a baggage allowance of 30 lb per passenger and allowable fuel to maximum ramp weight.


20. ANNEX "A” - AESTHETIC AND COST GUIDELINES

Aesthetic Trim Detail Guidelines to include: ¾ One (1) specie (type) of hi-gloss veneer on

cabinetry shipset (galley, vanity, enclosures, furniture, magazine racks, tables, cabin ledges, PSU handrails, bulkheads and doors).

¾ Veneer on bulkheads and doors (with an exception of full fabric on two (2) aft cabin bulkheads).

¾ Simple hardwood molding complementing veneer where applicable. Choice of up to eight (8) routered moldings (bullnoses) where applicable (refer to Design Book for specific profiles).

¾ Flat synthetic glass glassware closeout in upper galley area (no curves or radius).

¾ Plated appointments in the main passenger area only (refer to Design Book for specific colors).

¾ 100% wool, 3/8” pile (approximately 95 oz face-weight) handmade custom carpet in entrance area, main cabin and aft lavatory (limited to three (3) colors, simple overall pattern and texture).

¾ 100% wool, 5/16” pile (approximately 52 oz face-weight) machine quality custom carpet on cabin air duct (limited to three (3) colors, simple overall pattern and texture).

¾ Common stitched fabric, leather or combination single fabric / single leather passenger seating dress covering in a choice of six (6) standard design styles.

¾ Leather on passenger seat bases. ¾ Common stitched fabric or leather divan dress

covering in a choice of ten (10) standard design styles.

¾ Common stitched fabric, leather, or single fabric / single leather combination on lower dado (no box pleating or decorative stitching).

¾ Fabric finished periphery (headliner, PSUs and sidewall overlays).

¾ Fabric interior curtains where applicable complete with fabric / leather acoustic entry curtain.

¾ Durable grospoint fabric lining in utilitarian area (wardrobes and storage areas).

¾ Solid surface (Corian, etc.), Aeroquest or Polystone galley and lavatory countertops complete with stainless steel galley sink and plated or integrally molded vanity sink as applicable (no granite tile).

¾ One (1) style of galley tapset. ¾ Choice of two (2) fwd lavatory tapsets and seven

(7) aft lavatory tapsets with coordinating towel ring / towel bar design options.

¾ Choice of four (4) SAM latch design styles (plated).

¾ Combination of paint and plastic laminate drawer linings in the galley, lavatory and various other monuments.

¾ Grospoint lined divan armrest shelves / storage areas.

¾ Standard factory cockpit with headliner to match interior aesthetics.

¾ Standard factory baggage finishes.

Aesthetic Material Price Guidelines to allow: (US Dollar Values) Veneers $ 70.00/sq. foot Plastic laminates (drawer linings, etc.) $ 4.00/sq. foot Hardwood (moldings, etc.) $ 5.00/board foot Plating $ 6.00/sq. inch Plating (Shipset) $ 70,000.00/Lot Carpet (3/8” pile, 95 oz. face-weight) $ 1,100.00/sq. yard Carpet (5/16” pile, 52 oz face-weight) $ 450.00/sq. yard Leathers $ 18.00/sq. foot Fabric (divan and seat) $ 270.00/lin. yard Fabric (periphery ultra suedes and vinyls) $ 185.00/lin. yard Fabric (curtains) $ 214.00/lin. yard Fabric (linings) $ 105.00/lin. yard Fabric grospoint (wardrobe linings) $ 105.00/lin. yard Countertop (Solid Core, Corian, Polystone, or equivalent) $ 550.00/sq.foot


21. ANNEX "B” - LOOSE EQUIPMENT

Description Quantity



1. Cockpit Equipment: a. Crew headset (factory supplied) 2 b. Flight Observer Seat headset

(factory supplied) 1 c. Flight Observer Seat sheepskin slipcover 1

2. CES Equipment: a. Stereo headphones with manufacturer supplied

case 18 b. 10.6” plug-in touch-screen HD

monitor with pouch 2 c. Wireless PCU with charger 13

3. Emergency Equipment: a. Passenger briefing card 25 b. Oxygen demo unit 1 c. Therapeutic mask with 12 ft oxygen hoses,

a nebulizer, an adjustable flow meter and pouch 2

4. Cabin Equipment:

a. Cup holder inserts 20 b. Golf size umbrella 4 c. Coat hanger 18 d. Teflon cutting board inserts 2 e. Throw pillow 8 f. Low cabinet cushion 1 g. Seat belt demo unit 1 h. Seat belt extension 3 i. Divan sleeping belt 1 j. Lap tray with pouch 3 k. Throw rug for entry area 1 l. Throw rug for single seats grouping 3 m. Leveling self-inflating mattress for conference

grouping (two (2) pieces) 1 n. Curtain, complete with stowing straps, that

fits between the mid cabin bulkheads 1 o. Removable bulkhead pouch 1

5. Maintenance Equipment: a. Maintenance Laptop and all accessories

needed for aircraft maintenance tests, provided in a hard case (stored in LH Entrance Enclosure) 1

b. Set of keys for the aircraft 6 c. Tow bar assembly 1 d. Maintenance runner for entry area 1 e. Maintenance runner for passenger cabin 1 f. Maintenance runner for aft lavatory (with

attachment provisions) 1 g. Maintenance covers for all crew

and passenger seats and divans a/r* h. Water filling station adapter hose with pouch 1 i. Keyed locking fuel cap 3 j. Electric pump (115VAC/60Hz) for the manual

fill of water tank with support plate, hose and pouch 1

k. Mid cabin door cap 2 l. Interior cleaning and grooming kit 1 m. Touch-up kit

(Wood & Interior finishes, exterior paints) 1 * a/r = as required

22. ANNEX "C” - SPARE EQUIPMENT




a. Latch of each type (with an installed quantity greater than two) 2 each

b. Set of material to cover airstair steps 2 c. Cup holder inserts 20

d. Complete custom carpet (covering approx. FS 250+32 to FS 799) 1

e. Throw rug for entry area 1 f. Throw rug for single seats grouping 3

23. ANNEX "D” – COMPLETION DOCUMENTATION LIST

The following documentation is provided to the Customer by Bombardier Global Completion Center upon delivery of the aircraft (except as noted). The overall depth and detail of the information are to the level necessary to properly service and maintain

items installed by Bombardier Global Completion Center as part of this specification, in accordance with Chapter 5 “Global 5000¥ Global Vision / Time Limits / Maintenance Checks”.

Manual Description Quantity (# of set)


Completion Documentation – Certification & IFCA:

STCs / LSTCs / Foreign STCs 2* Instructions for Continued Airworthiness for all installed STCs 2*

Master Document List (MDL) for Interior STC 2*

Electrical Load Analysis 2* Specifications 2* (Includes IFCA Cover Sheet, STLMC, AWL/MMMS (if applicable), SIPC, and SMM)

Completion Documentation – General Arrangements, Layouts, & Schematics:

General Arrangements and Layouts 2* Placard Drawings 2* Schematics (Oxygen System and Water System) 2*

Floor Modifications (Floor Cuts/Splices and Floorboard Mods (if applicable)) 2*

Completion Documentation – Wiring Diagrams:

Drawing List, Sorted By Number 2* Drawing List, Sorted By Title 2* Wiring Diagrams 2*

Completion Documentation – Supplemental Maintenance Manual: Supplemental Maintenance Manual (SMM) for Interior IFCA 2*

(Initial SMM provided at aircraft delivery. Revised SMM provided approximately 90 days after aircraft delivery)

Completion Documentation – Supplemental Illustrated Parts Catalog: Supplemental Illustrated Parts Catalog 2* (IPC provided approximately 90 days after aircraft delivery)


Completion Documentation – Vendor Manuals: Vendor Manuals (Operators Guides, CMMs, etc.) 2*

Completion Documentation – Rockwell Collins Manuals: Cabin Electronic System (CES) Installation Manual 1*

Cabin Electronic System (CES) Operator’s Guide 1*

Cabin Electronic System (CES) Diagnostic Guide 1*

Cabin Electronic System (CES) Fault Isolation Manual 1*

CES Wireless Passenger Control Unit (WPCU) Quick Start Guide 4*

CES Touch-screen Equipment (TSE) Quick Start Guide 6*

SATCOM SAT 2200 Satellite Communications System User’s Guide (optional)

1*

SATCOM 2200 Satellite Communications System Installation Manual (optional) 1*

L3 Electronic Flight Bag Operators Guide (optional) 1*

Airshow Interactive (optional) 1* Airshow TV Commissioning Form (optional) 1*

Airshow Network (optional) 1* SAT TV Tailwind Installation Manual (optional) 1*

Manual Description Quantity

(# of set)


Completion Documentation – Rockwell Collins Manuals (continued): SAT TV Tailwind User Guide (optional) 1* Tailwind 500 Marketing Bulletin - TV Programming for Europe (optional) 1*

Tailwind 500 Marketing Bulletin - TV Programming for Middle East (optional) 1*

Tailwind 500 Marketing Bulletin - TV Programming for Contiguous United States (optional)

1*

Additional Completion Manuals / Documents: Cabin Handbook 2* Grooming Guide 2* Completion CD-ROM 2** Weight and Balance Report 2**

Rockwell Collins Pilot Guides for the following equipment: TBD

Contract Deliverables: Sound Survey Report


Quality Control Data: Bombardier Conformity Report Form (QA 373) or Major Repair or Alteration Form (FAA 337) Supplemental Type Certificate (STC) / Limited Supplemental Type Certificate (LSTC) as applicable Work Report Flammability Test Matrix and Fire Blocking Test Result GCC Serialized Equipment List Final Weight & Balance Report including an equipment list (Appendix A) Compass Deviation Cards (on aircraft) Update entries for the following aircraft logbooks: x Journey Log Book x Engine Log Books (R/H & L/H ) x Aircraft Battery Log Books (Main & APU) x A.P.U. Log Book x Aircraft Technical Log Section 1 – Airframe x Aircraft Technical Log Section 2 – Record of

Installations & Modifications x Serialized List (green aircraft) x Weight and Balance Report (green aircraft) Flight Manuals: Airplane Flight Manual and Flight Crew Operating Manual supplements (as required) inserted in the respective basic airplane manuals. Canadian Certificate of Airworthiness {C of A} for Export to the United States.

Notes:

1. The manuals identified with an asterisk (*) are delivered in Hard Copy and CD-ROM format. The manuals identified with two (2) asterisks (**) are delivered in CD-ROM. All others are delivered in hard copy.

24. ANNEX "E” - AIRCRAFT FLOORPLAN

Title Drawing Number

General Notes and Legend 5000V1LE-0000 Floorplan and Elevations 5000V1LE-0001 Forward Lavatory and Avionics Rack 5000V1LE-0002 LH Entrance Enclosure 5000V1LE-0003 RH Galley and LH Galley Annex 5000V1LE-0004 Aft Wardrobe 5000V1LE-0006 Aft Lavatory 5000V1LE-0007 Credenza and Low Cabinet 5000V1LE-0008 Bulkhead Sections 5000V1LE-0010 Divan and End Cabinets 5000V1LE-0011 Sideledge and Tables 5000V1LE-0012 Seats 5000V1LE-0017 Cockpit 5000V1LE-0020 Baggage Compartment 5000V1LE-2004 Material Specification 5000V1LE-0601 Accessories List 5000V1LE-0623 Loose Equipment List 5000V1LE-0624 Standard Global 5000 & XRS Global Vision Cockpit Finish Specification RAF-BI700-003 Standard Global 5000 Global Vision Baggage Finish Specification RAF-BI700-002 CES Control Devices Specification 5000V1LE-0630
