2.47 TAIL ROTOR QUADRANT/WARNING. WARN. If the helicopter is shut down and/or hydraulic
power is removed with one tail rotor cable failure, discon-
The tail rotor quadrant contains microswitches to turn on nection of the other tail rotor cable will occur when force
a caution legend marked TAIL RTR QUADRANT if a tail from the boost servo cannot react against control cable
rotor cable becomes severed. Spring tension allows the quadrant spring tension. The quadrant spring will displace
quadrant to operate in a normal manner. Electrical power to the cable and boost servo piston enough to unlatch the
operate the warning system is provided from No. 1 dc pri- quadrant cable.
mary bus through a circuit breaker marked T RTR SERVO
Section IX UTILITY SYSTEMS
2.48 WINDSHIELD WIPERS.
Two electrically-operated windshield wipers are installed, one on the pilot’s windshield and one on the copi-lot’s windshield (Figure 2-1). Both wiper arms are driven by a common motor through .exible drives and converters. Power to operate the windshield wiper system is from No. 1 ac primary bus through a circuit breaker, marked WSHLD WIPER.
NOTE
The use of rain repellent on the windshields will improve visibility above speeds of 50 KIAS.
2.48.1 Windshield Wiper Control.
To prevent possible damage to windshield surface, do not operate windshield wipers on a dry windshield.
Control of the windshield wipers is through a spring-loaded rotary switch on the upper console (Figure 2-6). The switch is labeled WINDSHIELD WIPER, with marked positions PARK-OFF-LOW-HI. When the switch is turned from OFF to LOW or HI, the wipers will operate at the corresponding speed. The wipers will stop at any posi-tion when the switch is turned OFF. When the switch is turned to PARK, the wipers will return to the inboard windshield frame and stop. When the switch is released, it will return to OFF.
2.48.2 Windshield Anti-Ice/Defogging System.
Continued use of a faulty windshield anti-ice system may result in structural dam-age (delamination and/or cracking) to the windshield.
Do not allow ice to accumulate on the windshield, as ice shedding can cause engine FOD.
Pilot’s, copilot’s and center windshield are electrically anti-iced and defogged. Transparent conductors imbedded between the laminations provide heat when electrical power is applied. The temperature of each panel is controlled to a heat level of about 43°C (109°F). The windshield anti-ice system fault monitoring circuit prevents windshield burnout when the windshield surface heat is above 43°C (109°F). If heat increases, the monitor circuit will turn off the system. Three switches, one for the pilot, one for the copilot and one for the center windshield are on the upper console (Fig-
ure 2-6) with markings of WINDSHIELD ANTI-ICE-PILOT-OFF-ON, and COPILOT-OFF-ON and CTR-OFF-ON. Power to operate the anti-icing system is provided by the No. 1 and No. 2 ac primary buses through circuit breakers marked PILOT WSHLD ANTI-ICE, CPLT WSHLD ANTI-ICEand CTR WSHLD ANTI-ICE. Power to control the anti-ice system is provided by the No. 1 and No. 2 dc primary buses through circuit break-ers marked CPLT WSHLD ANTI-ICE and WIND-SHIELD ANTI-ICE PILOT and CTR. If the APU gen-erator is the sole source of ac-generated power, the backup pump and the windshield anti-ice cannot be used simulta-neously.
2.49 PITOT HEATER.
Pitot tube heat is provided by heating elements within each pitot tube head. Power to operate both heating ele-ments is controlled by a single switch on the upper console, marked PITOT HEAT OFF and ON. When the switch is placed ON, current .ows to the heating elements. Current sensors in the circuits sense the current .ow and keep the caution legends, marked LFT PITOT HEAT and RT PITOT HEAT, turned off. If a heating element fails, the current sensor will detect no current .ow, and turn on the caution legend for that pitot tube. Power to operate the pitot tube heaters is provided from the No. 2 ac primary bus for the right pitot tube, through a circuit breaker marked RT PITOT HEAT, and from the No. 1 ac primary bus for the left pitot tube, through a circuit breaker marked LEFT PITOT HEAT. Power to operate the caution lights is pro-vided from the No. 1 dc primary bus through a circuit breaker, marked NO. 1 ENG ANTI-ICE.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：UH-60Q 直升機技術手冊 直升機操作手冊 1(40)
