• Caution Panel - The panel is located on the instrument panel and illumination of any light alerts pilot to a system fault.
• BRIGHT-DIM Switch - Located on instrument panel, permits selection of bright or dim for all amber colored caution lights, AFCS controller panel, GPS panel, and CLEAR CHIP indicator. Up is bright, down is dim, spring-load to neutral.
• Test Switch - Press-to-test switch will cause illumination of all worded segments on caution panel.
• Chip Detector Warning Lights - Chip detectors are installed on the drain plugs of the transmission sump, engine sump, and tail rotor gearbox to detect metal particles in the oil. The freewheeling unit also has a similar pug, but it is not electrically connected to the cockpit. Filings in the oil bridge the gap across the detector and complete a circuit. Three caution chip lights are ENG CHIP (+CLEAR CHIP), TRANS CHIP,  and T/R CHIP. A continuity check occurs for 5 sec, whenever electrical power is interrupted or test switch is pressed in excess of 2 sec.
• Fire Detection System -Consists of ENG FIRE warning light, FIRE DET TEST switch, detection control box, and a heat-sensitive fire detection element in the upper portion of the engine cowling. Excessive heat causes increased pressure in the element, triggering a pressure switch in the control box and illuminating caution light.
• TOT Overtemperature Light - Attached to TOT gauge and illuminates when 810-927C for 10 sec, or 927C is exceeded.
• Engine Failure Warning System - An engine-out switch is splined to the Ng tach-gen and activates a beeping signal and ENG OUT light when Ng drop below 55 +/- 3%. On start it goes out at 52 +/-3%.
• Rotor RPM Warning System - A low-rotor rpm switch is splined to the Nr tach-gen and activates an audible tone and ROTOR LOW RPM when Nr drops below 90 +/- 3%.
• Audio-Mute Switch - Located left of the caution panel, the switch controls the volume of the engine out and low rotor horns to the pilot and co-pilots headsets. Normal mode is audio, while mute deactivates the headset audio.
• Note - The ENG OUT and ROTOR LOW RPM warning circuits are deactivated by pulling the CAUTION LT C/B.
• Warning - During daylight operations with the BRIGHT-DIM switch in DIM and the instrument lights
  set on low setting, the amber colored caution lights will be extremely difficult to distinguish.
• Caution - The CLEAR CHIP button will illuminate during the chip detector continuity test along with all
  the caution panel chip lights. Depression of the CLEAR CHIP button while illuminated may cause
  damage to the continuity sensor.
• Note - A collective cutoff switch disables the low rotor rpm audio unit when the collective is within
  approximately 1 inch of the full down position.
• Caution - The audio-mute switch should be left in the audio position during flight.

• HYDRAULIC PRESSURE
  Hydraulic Pressure <= 300 psi Refer to HYDRAULIC SYSTEM MALFUNCTION proc.
• DUCT HIGH TEMP
  Excessive heat in ducting Turn cabin heat off . Turn AIR COND/FAN switch to FAN. Turn HI/LO switch to HI. If the DUCT HIGH TEMP caution light does not extinguish, LAND AS SOON AS PRACTICAL
• ENG FIRE
  Excessive heat in engine compartment Refer to ENGINE FIRE procedures
• MAIN GEN/GEN FAIL
  Main generator has failed Refer to GENERATOR FAILURE procedures
• FUEL LOW
  Less than 20 gallons of fuel remaining Monitor fuel quantity, land with minimum of 10 GALLONS INDICATED. If fuel pump light is on, LAND AS SOON AS POSSIBLE
• TOT
  TOT light flashes once per second within Adjust collective as req. to remain within limits transient range TOT light flashes twice per second when LAND AS SOON AS POSSIBLE limit is exceeded
• A/F FUEL FILTER
  Impending Bypass of the A/F Fuel Filter LAND AS SOON AS POSSIBLE
• FUEL PUMP
  One or both fuel boost pumps inoperative Refer to FUEL BOOST PUMP procedures. WARNING - With one or both fuel boost pumps inoperative, fuel quantity below 20 gallons shall be considered unusable
• TRQ
  TRQ light flashes once per second within Adjust collective as req. to remain within limits transient range. TRQ flashes twice per second when limit LAND AS SOON AS POSSIBLE. NOTE- TOT light will extinguish once out of transient and exceedence ranges. Digital readout will continue to flash twice per second if limit is exceeded.
• T/R CHIP
  Metal part. on tail rotor gearbox chip det. LAND AS SOON AS POSSIBLE
• ENG CHIP/CLEAR CHIP
  Metal part. on engine chip detector ENGINE INSTRUMENTS - Check eng. instruments for secondary indications of impending failure. If these exist LAND AS SOON AS POSSIBLE. If no secondary indications exist:
  • First Chip - Press CLEAR CHIP; if eng chip light goes out, note the time and continue flight. If eng chip light remains illuminated, LAND AS SOON AS POSSIBLE
  • Second Chip - If sustained within 30 min of the first, LAND AS SOON AS POSSIBLE. If more than 30 min have elapsed since the first light, press the clear chip and proceed as
    with the first flight. {out-note & continue/on-land ASAP}
  • Any subsequent Chip - If within 50 flight hours of the first, LAND AS SOON AS POSSIBLE and make no attempt to clear chip. All chip lights shall be documented on VID/MAF. Chip lights signed off as PASTE do not count toward the total number of lights in a 50 hour period
• TRANS OIL CHIP
  Metal part. on Xmissn chip detector LAND AS SOON AS POSSIBLE
• BATTERY HOT
  Battery case temp 60 +/- 3C or higher Bat - OFF. LAND AS SOON AS POSSIBLE  
• BATTERY TEMP
  Battery case temp 54 +/- 3C or higher Bat - OFF. Flight may be continued.
• TRANS OIL PRESS
  Xmissn oil press at or below 30 +/- 2 psi LAND AS SOON AS POSSIBLE.
  Note - Check the transmission oil press w/ twist grip full open. Illumination of the TRANS OIL PRESS caution light is common, while the twist grip is at flight idle, after power off maneuvers. However the gauge should indicate positive transmission oil pressure.
• TRANS OIL TEMP
  Xmsn oil temp at or above 110 C LAND AS SOON AS POSSIBLE
• ENG OUT
  Engine power failure Ng at 55 +/- 3% Engine power failure accompanied by an aural signal. Monitor Nr and engine instruments and enter AUTOROTATION if the
  power failure is confirmed. If the actuation of the warning system is the result of Ng tach/gen or speed sensor switch failure, LAND AS SOON AS PRACTICAL  
• ROTOR LOW RPM
  Nr less than 90% Collective - LOWER to preserve Nr. Check twist grip full open. If power is not regained, follow ENG FAILURE proc. If the activation of the
  warning system is the result of an Nr tach/gen failure, monitor eng instruments and LAND AS SOON AS PRACTICAL
• SPARE
  Light incorrectly wired Check for other indications and LAND AS SOON AS POSSIBLE
   
  ©BATTERY RELAY Illumination during starting is normal If BAT HOT light is not illuminated, continue flight in VMC and At other times with BAT switch ON, LAND AS SOON AS PRACTICAL. If BAT HOT light is continued illumination indicates fault in illuminated, BAT-OFF, LAND AS SOON AS POSSIBLE battery relay or protection circuits Note - Under certain conditions, total or partial electrical failure may follow illumination of the BATTERY RELAY light. With BUS TIE RELAY CB popped, the main battery is being discharged.
   
  ©FCS Fail. of the AFCS fault protective circuits If lights continues to illuminate push STAB button off, pull FCS CB
   
  ©STBY BATT ON Stdby attitude indicator switch left ON Turn off stdby attitude indicator prior to leaving helicopter to after other power turned off avoid depleting standby battery.
   
  ©STBY GEN FAIL Stdby generator failure Refer to GENERATOR FAILURE procedures

» Back to the Advanced Gouge list
» Contact the webmaster, Bryan Weatherup

DISCLAIMER: The information provided on this page is to be used only to assist Student Naval, Marine, Coast Guard Aviators and U.S. Air Force Student Pilots. It is by no means meant to replace or supercede the knowledge presented in NATOPS, OPNAV 3710.7T, Flight Training Instructions, FLIPS, or any other official Navy, Marine, Coast Guard or U.S. Air Force publication. Knowledge of these documents is considered paramount to flight safety. Any unauthorized use of the information on this page in an actual flight (without reference to the official publication) is strictly prohibited. Viewing web pages listed above constitutes acceptance of all responsibility for flight safety by you, the user. The author of this page assumes no responsibility for the completeness of these documents or their use in Aviation training.

If you find discrepencies in the information here, please contact me. This is NOT an official Navy web site. All opinions and statements are exclusively those of the authors and do not reflect the views of the Department of Defense, The United States Navy, The United States Marine Corps, The United States Coast Guard or the The United States Air Force.