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                               PART 1 - DESCRIPTIVE
          

Actual
altitude
(ft.)
Cockpit
altitude
(ft.)
Cockpit altitude at which
warning light comes on
(ft.)
20,000 13,000 13,750
30,000 16,500 18,000
40,000 22,500 24,000
(d) (i) A "flood flow" valve is incorporated in the system which may be controlled in AUTO or MANUAL according to the setting of the FLOOD AIR FLOW control switch (11). (ii) When the switch is set to MANUAL, "flood flow" is brought into operation and is used primarily for clearing any transparency misting. (iii)When the switch is at AUTO, should loss of cockpit pressure cause the cockpit altitude to exceed 38,000 ft., an altitude switch operates to supply "flood" air to the cockpit. (e) A switch (10) for ground testing the visual warning and flood air supply is aft of the normal controls. It must not be used in flight. 39. Anti-G suit system (a) The purpose of the system is to provide air at low pressure for the pilot's anti-G suit, the connection for which is on the port side of the ejection seat. (b) Air under pressure is stored in two air bottles, the contents of which are indicated by a pressure gauge (81) on the starboard wall. When the cock (79) below the gauge is ON and G in excess of approximately 1½ is applied, a spring-loaded valve operates and allows air to pass to and inflate the anti-G suit. The amount of inflation depends on the amount of G applied. (c) The system may be tested, with the cock ON, by pressing the ANTIG-TEST button (80), adjacent to the on/off cock, as gently as possible to avoid severe discomfort due to too rapid inflation.

37

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