The following is reproduced verbatim from the Qantas Boeing 707-138B Operations Manual dated 22 April 1968. It should be noted that these specifications do not necessarily apply to VH-XBA in its present configuration.

AIRCRAFT GENERAL

The model 707-138B principal dimensions are: wing span 130 feet 10 inches, total wing area 2521 square feet, vertical fin height 41 feet 8 inches, body length 128 feet 10 inches. The approximate weight empty is 115,000 pounds with a structural design gross weight (for taxi and takeoff conditions) of 258,000 pounds.

Four Pratt & Whitney JT3D-1 turbofan engines are installed beneath the wing in individual strut mounted pods.

The primary electric system is 3 phase, 400 cycles, 115/200 volt AC. Power is generated by four 30 KVA engine driven generators. A synchronising bus-tie loop makes it possible for any generator to supply power to any load bus, in addition to its own load bus, and any combination of generators can be operated in parallel to share the total power demand. The 28 volt DC power is derived from the AC system through transformer-rectifier (T-R) units.

Interior and exterior lighting are provided for all normal operations, ground servicing and emergency operations.

All fuel is carried in the interspar area of the wing structure. Two outboard reserve tanks and four main tanks are integral with the wing structure. The wing centre section tank is composed of integral sections at the wing root, plus nylon and rubber bladder cells enclosed by wing structure bays. Fuel is supplied directly to each engine from the respective main tank or from the fuel manifold. The fuel manifold can be supplied from any main tank or from the wing centre tank. Main tanks fuel boost pumps supply fuel directly to the corresponding engines and to the fuel manifold through the manifold valves. The centre wing tank boost pumps, when on, will override the main tanks boost pumps and will supply fuel to the fuel manifold.

Fuel flow from one tank to another, except for the reserve tanks, is prevented by check valves. Fuel from the reserve tanks feeds by gravity to the adjacent main tanks. A four point underwing pressure fuelling system is used. Provisions are also made for overwing fuelling through standard filler necks.

Engine mounted turbocomps and engine airbleeds provide high pressure air for pressurising, heating, cooling and ventilating the cabin interior. Fresh outside air is compressed to provide the air supply.

Cabin airconditioning is provided by an air cycle system. Pressurisation is accomplished by controlling the outflow of cabin air through the outflow valves, located along the bottom centreline of the aircraft.

Thermal anti-icing is provided for the wing leading edges, engine nose cowl and engine inlet guide vanes. Electrical anti-icing is used for the windshields.

The hydraulic system consists of a utility system and an auxiliary system designed for a working pressure of 3000 psi. Two engine-driven pumps supply pressure to the utility system and two electrically driven pumps supply pressure to the auxiliary system. An electrically driven pump supplies pressure to the brake system for ground operation.

The landing gear is a retractable tricycle type, hydraulically operated. Each main landing gear is a four wheel truck. The nose gear is a dual wheel hydraulically steerable unit. Main landing gear wheels incorporate hydraulically actuated brakes. The brake hydraulic system incorporates anti-skid. An emergency pneumatic brake system is provided for use in the event of failure of the brake hydraulic system.

The primary control surfaces consist of ailerons, elevator and rudder. The ailerons and elevator are aerodynamically balanced and are actuated by means of cable controlled tabs. The rudder, flaps and spoilers are hydraulically operated. In addition to aiding in lateral control, the spoilers can also be used as speed brakes. The horizontal stabiliser angle of incidence may be varied electrically, manually, by the autopilot, or Mach trim. The primary flight controls incorporate control systems for both manual and automatic (autopilot) operation of inboard ailerons, rudder and elevator.

The automatic flight control system consists of an autopilot which includes an automatic VOR and ILS coupling. The autopilot provides sensitive, automatic, co-ordinated control of the aircraft at any desired altitude, attitude and heading.

The aircraft flight instruments include an integrated flight instrument system and a Polar Path Compass System; a conventional magnetic compass; turn-and-bank indicator; rate-of-climb indicator and clock are also provided. The integrated flight instrument system provides heading, radio and attitude information. The Polar Path Compass system provides heading information from the D.G. transmitter. This information may be slaved to a magnetic heading as obtained from a Fluxgate Transmitter.

Radio and radar in the aircraft include communications equipment in the HF and VHF ranges. Navigation equipment including ADF, VOR-LOC, a Marker Beacon System, Loran, Glideslope, DME(T), Weather Radar and Doppler. An ATC radar beacon (transponder), a selcal system, a passenger address system and an interphone system are included in the aircraft communications equipment.

The control cabin accommodations provide for a pilot, copilot, flight engineer and a navigator. An observer or check pilot is accommodated behind the pilot. Main cabin interior arrangements provide accommodations for approximately 70 to 152 passengers and four cabin attendants. Seat tracks and removable partitions allow adjustment of passenger accommodations to provide any combination of tourist and luxury class seating. Cargo is accommodated in two cargo compartments, one located in the lower forward and the other located in the lower aft sections of the body.

Separate, independent oxygen systems provide oxygen for the crew and passengers. Supplemental and protective breathing oxygen are supplied to the crew. Supplemental and therapeutic oxygen are included for the passengers. The passenger supplemental oxygen system is actuated automatically or by the pilot when needed.

The aircraft is designed to facilitate servicing. Numerous access doors and panels are provided for inspection and maintenance. Most major servicing is accomplished on the right side of the fuselage. Passenger entry doors are located on the left side of the fuselage. Fuel is loaded from stations on the lower surface of each wing.

Emergency equipment, consisting of lights, oxygen, fire extinguishers and first aid kits, is used in the event of inflight or landing emergencies. Escape ropes, escape slides and crash axes are installed to assist in ditching or in abandoning the aircraft. Liferafts, UHF/VHF survival beacons and life vests are provided for use after ditching. Crash, fire and rescue information is provided in Chapter 3.

DIMENSIONS AND AREAS

The following dimensions and areas are approximate:

1. WING

2. FLAP AREA

3. CONTROL SURFACES

4. BODY

5. LANDING GEAR

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