Aviation Technical English for aircraft maintenance engineers (Авиационный технический английский язык для студентов-авитехников)

13 1. After engine start, air for the bleed air system is normally supplied by the engines. 2. Engine bleed air is obtained from the 5th and 9th stages of the compressor section. 3. Isolation valve position is not affected by the APU bleed air switch. 4. Both wiper systems are controlled by a common switch. 5. All pitot-static probes, the total air temperature probe, and angle airflow sensors are electrically heated to prevent the formation of ice. 6. Valve position is monitored by the blue VALVE OPEN lights. 7. The automatic flight system (AFS) consists of the autopilot flight director system (AFDS) and the autothrottle (A/T). 8. Two independent radio altimeters provide radio altitude to the related FCC. 9. The master FCC is indicated by illumination of the related master (MA) F/D indicator light. 10. The flight mode annunciations are displayed on the EADI. 11. An ASP is installed at the Captain, First Officer, and Observer stations. 12. Each panel controls an independent crew station audio system and allows the crewmember to select the desired radios, navigation aids, interphones, and PA systems for monitoring and transmission. 13. Engine instruments are: engine speed indicator, thermometers, oil and fuel pressure gages, fuel flow meters, fuel contents gages. 14. The aileron supply shut off valve is a component of the aileron system modular unit. 15. The aft flap assembly is a monospar structure and consists of the spar nose ribs and a machine-tapered honeycomb trailing edge. 16. The continuous loop sensing element consists of an inconel tube filled with a ceramic core. 17. The outlet of the main pump is connected with a valve: one way to the water delivery hose, the other – to the cleaning system of the waste tank. 18. Arinsing water hose is connected to the water pump via a control valve. The hose is stowed on a hose reel.