This SAE Aerospace Information Report (AIR) has been compiled to provide information on hydraulic systems fitted to commercial aircraft.

Data has been provided for following aircraft types:

a. Wide body jet airliners

b. Narrow body jet airliners

c. Turboprop/commuter aircraft

d. Business jet aircraft

The airliners that have been included in this document are generally in operational service with either airlines or cargo operators. Information on aircraft that have been retired from in-service use has been included for reference purposes. No information is presented for aircraft that are currently being developed.

The following information is provided for each aircraft

• Design requirements: Governing airworthiness regulations

• System pressure: Fluid power system operating pressure

• Hydraulic fluid: Type of fluid the hydraulic system uses

• Number of hydraulic systems: Number and identification of independent hydraulic systems

• System temperature: Minimum and maximum design operating temperatures

• Main hydraulic pump data: Flow, pressure, displacement

• Auxiliary pump data: System auxiliary pump or back-up data

• Hydraulic motor data: System hydraulic motor requirements

• Accumulator data: Usage, volume and precharge requirements

• Reservoir data: Type, volume and pressure

• Relief valve data: Usage, crack and reseat pressures, rated flow

• Filtration data: Usage, filtration rating

• Tubing data: Materials, sizes, wall thicknesses

• Fitting data: Type, size range, material

• Schematic diagram: System architecture, services supplied.

NOTES

1. For some aircraft, the data is incomplete. This is due to difficulties in obtaining the data (particularly for the older aircraft presented in this report).

2. For some aircraft, the pumps may not be those as stated in this document. This is because when they are supplied by more than one vendor for a specific aircraft application, the pumps' displacement and running speed may differ.

3. Electric motor pumps are fixed frequency type unless otherwise stated.

4. The schematic diagrams for each aircraft have been simplified for clarity and ease of understanding. For example:

- The return side of each system has not been shown

- Specific features such as internal leak measuring systems are not shown

- Single accumulators are shown at locations where multiple accumulators are used

However, the complete power generation system and elements of the supply system for each aircraft is shown using symbols in accordance with AS1290.

5. The filtration ratings that are presented in this report are the absolute rather than nominal ratings. However, it should be noted that there is no consistent definition of the absolute rating for the filters for the aircraft hydraulic systems that are described in this report