TM  1-1520-240-10            2-9-3 through   the   HYDRAULICS   MAINT   PNL   LTS   circuit breaker on the No. 2 PDP. a. PRESSURE  Indicators.  The  FLT  CONT  NO.  1 and NO. 2 PRESSURE indicators are electrically connected to a corresponding pressure transmitter on the respective power control module. The UTILITY PRESSURE indicator is  electrically  connected  to  a  pressure  transmitter  on  the pressure control module. Indicator operation is independent of caution capsule operation. Power to operate the indica- tors  is  supplied  by  the  No.  2  DC  bus  through  the  HY- DRAULICS PRESS IND circuit breaker on the No. 2 PDP. b. TEMPERATURE  Indicators.  The  indicators  are below the PRESSURE indicators. They indicate the temper- ature of the hydraulic fluid at the outlet of the corresponding reservoir-cooler. Power to operate the indicators is supplied by  the  No.  2  DC  bus  through  the  HYDRAULICS  FLUID TEMP circuit breaker on the No. 2 PDP. c. RESERVOIR LEVEL Indicators.  The left indicator is dedicated to the No. 1 and No. 2 flight control hydraulics system.  In  addition,  a  two–position  FLT  CONT  switch  la- beled NO. 1 and NO. 2 is used to select the system of which the fluid level is to be indicated. The reservoir should be serviced to the FULL mark before flight. The right indicator is dedicated to the utility hydraulic system. When the push- button LEVEL CHECK switch is pressed, the fluid level in each  reservoir-cooler  will  be  indicated  by  the  appropriate indicator. d. FILTER CHANGE Indicating Lights.   The indicat- ing lights are arranged in three sets of two for each hydraulic system. Each set of indicating lights are labeled PRESS and RTN. The PRESS indicating light in each set monitors the pressure line filter in each system. The RTN indicating light monitors  the  return  line  filter  in  each  system.  When  the pressure  drop  across  a  filter  exceeds  75  psi,  indicating impending filter bypass, the corresponding filter change indi- cating light will illuminate. Power to operate the filter change indicating lights is supplied by the No. 2 DC bus through the HYDRAULICS MAINT PNL LTS circuit breaker on the No. 2 PDP. e. PUMP  FAULT  Indicating  Lights.  The  indicating lights are labeled NO. 1, NO. 2, APU, and UT. They are connected to sensors in the case drain line of each pump. If the flow rate from the case drain of a pump increases to the point which causes an increased pressure drop across the sensor, the sensor turns on the corresponding PUMP FAULT light ( a high flow rate from the case drain of a pump may indicate impending pump failure). Power to operate the lights  is  supplied  by  the  No.  1  DC  bus  through  the  HY- DRAULICS MAINT PNL circuit breaker on the No. 1 PDP. 2-9-6.  ENGINE CHIP DETECTOR Section. This section consists of two magnetic indicators labeled NO. 1 and NO. 2. When the corresponding ENGINE CHIP DETECTOR is bridged by ferrous particles, the associated chip detector indicator changes from all-black to black-and- white. In addition, the ENG CHIP DET caution will illumi- nate on the master caution panel. 2-9-7.  GROUND CONTACT Section. CAUTION Should either or both GROUND CONTACT indicating lights remain illuminated after lift-off  to  hover,  the  indicated  system(s) DASH will not function properly in forward flight. If both GROUND CONTACT indicat- ing lights remain illuminated after lift-off, the  AUTO  function  of  both  cyclic  trims system will be inoperative. This section consists of two indicating lights labeled L and R. When the landing gear proximity switch is activated, the appropriate GROUND CONTACT indicating light will illumi- nate. 2-9-8.  GND Switch. NOTE While in flight, the flight engineer shall alert the pilot when placing the GND switch on the MAINTENANCE PANEL to TEST. Placing the switch to TEST will cause the NO. 1 and NO. 2  ENG  CHIP  DET,  XMSN  OIL  HOT  and XMSN CHIP DET cautions to illuminate. The GND switch allows the flight engineer to perform a BITE (Built In Test Equipment) test on the circuitry of the MAINTE- NANCE PANEL. The switch is springloaded and locked at center-off position. At TEST, a black and white display ap- pears on all magnetic BITE indicators. At RESET, all mag- netic BITE revert to an all-black indication. Power is supplied to  the  switch  by  the  No.  1  DC  bus  through  the  HY- DRAULICS MAINT PNL circuit breaker No. 1 PDP. 2-9-9.  Windshield Wipers. CAUTION To prevent windshield damage, do not op- erate windshield wipers when windshield are dry. Two electrically driven windshield wipers (3, fig. 2-1-3) are installed, one on each pilot windshield. One motor operates both wipers through two flexible shafts and two windshield wiper converters. The windshield wiper motor is controlled by the W/S (windshield) WIPER switch located on the over- head switch panel. Power is supplied by the No. 2 DC bus through the WSHLD WIPER circuit breaker on the No. 2 PDP. The  W/S  WIPER  switch  has  five  positions  labeled  OFF, SLOW, MED, FAST, and PARK. Wiper speed can be ad- justed as desired, by rotating the switch from OFF. At OFF, the wipers will stop immediately at any position on the arc