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539 Cards in this Set
- Front
- Back
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Shall has been used only when application of a procedure is _______.
|
MANDATORY
|
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_______ has been used only when application of a procedure is recommended.
|
SHOULD
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WARNING: A popped NO.1 ENG OVSP or NO.2 ENG OVSP circuit breaker should / shall not be reset in flight.
|
SHALL
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CAUTION: Illumination of the ENG INLET ANTI-ICE ON light when OAT is above _____ degrees C is an indication of a faulty engine inlet anti-ice modulating valve. The resultant loss of power could be a maximum of ____% when the engine anti-ice system is activated.
|
13. 49.
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CAUTION: During single-point pressure refueling, if the right cell fills faster than the left cell, monitor the fuel quantity gauges closely. If the difference in cell quantities persists stop refueling before the _____ cell is full (approximately _____ pounds.
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RIGHT. 1700.
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WARNING: When AFCS computer power is interrupted, ______ is disengaged and an unguarded cyclic will allow the rotor arc to dip to as low as ______ feet above the deck.
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TRIM. 4.
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WARNING: It is possible for the stabilator to fail without illumination of the STABILATOR caution light and associated aural warning tone. In this case, the first indication of failure will be _______________________.
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UNCOMMANDED PITCH CHANGE
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|
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WARNING: If JP-4 is used, the following operational restrictions apply: All takeoffs shall stabilize in a hover with no fuel pressure caution lights for a minimum of 5 / 10 / 20 seconds before commencing transition to forward flight. Sinigle-engine training operations shall / should / may not be conducted while using JP-4/JET B.
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10. SHALL.
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Operation of the T700-GE-401C engine within the ______ light region of the VIDS may be limited to _____ minutes and operation below the high temperature level displayed on the VIDS may result in engine overtemperature.
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YELLOW. 2.5.
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|
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TGT Limits with Normal and CPWR
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"0-810 CONTINUOUS
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|
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Nr Limits (Power On/Power Off/MR Overspeed)
|
"POWER ON
|
|
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Np Limits (max, continuous, and avoid ranges)
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MAX:120%. CONT: 96-101. AVOID OTHER THAN TRANSIENT 20-40 AND 60-75.
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Single-Engine Torque Limits (max continuous and 10 second transient)
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0-135% CONT. 135-144% 10 SEC TRANSIENT
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Dual-Engine Torque Limits (max continuous and 10 second transient)
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"0-4000DA: 106%
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Ng Limits
|
"CONTINUOUS: 0-98%
|
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Engine Oil Temperatures
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"CONTINUOUS: -50-135
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|
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Engine Oil Pressure (with idle range)
|
"MIN: 22 PSI
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Main Transmission Oil Temperature
|
"MAX CONTINUOUS: 105
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Main Transmission Oil Pressure (with steady state flight)
|
"MIN: 20PSI
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|
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Situations which can result in engine overtemperature
|
"ADVANCING PCL TO IDLE WITH TGT OVER 80
|
|
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Engine Start cycles (any temp motoring)
|
AMBIENT TEMPERATURE (°C) STARTER ON STARTER OFF
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|
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When crossbleed starts are attempted, the operating engine must be operating at or above ___ percent Ng and rotor speed must be ____ to ____ percent Nr.
|
"LESS THAN 16C First Cycle 60 Seconds
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|
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T/F. Engine start with main rotor blades or tail pylon spread is prohibited.
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TRUE
|
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The main transmission may be operated up to _____ minutes at a time with pressure fluctuations when the aircraft is known to be in a nose-up attitude (slope landings or hover with extreme aft cg). In forward flight steady-state conditions, the transmission pressure shall be in the ___ to ___ psi range; fluctuations or pressure below ____ psi under these conditions requires maintenance action.
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30. 45. 60. 45.
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|
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Maximum wind velocity for rotor start or stop is ____ knots from any direction.
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45
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|
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Maximum (redline) airspeed limit is _____.
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180
|
|
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Maximum airspeed for autorotations is _____.
|
100
|
|
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Maximum airspeed with one engine inoperative is _____.
|
150
|
|
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Sideward/rearward flight limit is _____.
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35
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Airspeed limit with SAS 1 and 2 inop in IMC is ______.
|
125
|
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Airspeed limit when two hydraulic systems are inoperative in IMC is ____.
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125
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|
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Airspeed limit when Boost Servo is off _____ and off when in IMC is ____.
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140. 125.
|
|
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Airspeed limit when opening or closing cabin door limit is ____.
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60
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Airspeed limit when operating windshield wipers is _____.
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130
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Airspeed limit when searchlight is in any position other than stowed is ___.
|
160
|
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The maximum forward airspeed to move the searchlight is ____.
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100
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Maneuvering with rescue hoist loads are limited to ____ degrees AOB and rate of descent is limited to ______ feet per minute.
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20. 1000.
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Bank angles during normal operations is limited to 45 degrees and ____ degrees when one __________ or ________ caution light is on, or above _________ feet density altitude.
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45. 30. PRI SERVO PRESS. 10,000.
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|
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Prolonged hovering in ____ knot, ____-side wind should be avoided.
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20. RIGHT.
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Maximum operating density altitude is _________ feet.
|
13,000
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Prohibited manuevers
|
"1. Aerobatic flight (e.g., rolls, loops, inverted flight).
|
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MAD minimum altitude
|
200 FT AGL
|
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MAD Deployment (Climb, Descent, AOB, Airspeed)
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"CLIMB: 1000FPM. DESCENT-0FPM.
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|
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MAD Retrieval/docking airspeeds (up to last 12 feet/last 12 feet)
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UP TO LAST 12: 40 TO 90 KIAS LEVEL FLIGHT. LAST 12: 50 TO 55 KIAS LEVEL FLIGHT.
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MAD airspeeds at full trail (straight and level, level turns, descents, climbs)
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"STRAIGHT AND LEVEL: 40 TO 150 KIAS
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MAD jettisoning profile airspeed
|
STRAIGHT AND LEVEL, 0 TO 60 KIAS
|
|
|
Airspeed limit for Mk 46 release from starboard pylon when MAD is deployed is _____.
|
80 KIAS
|
|
|
Minimum altitude for employment of sonobuoys is ____ feet AGL below 100 knots and _____ AGL above 100 knots.
|
100. 150.
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|
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Maximum rotor speed for rotor brake application is ___ % Nr. Routine rotor stops shall be done between ___ and ___ percent Nr. Routine rotor brake stops should be limited to ____ psi for extended rotor brake life.
|
76. 30. 50. 180.
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|
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Blades ______ not be folded or spread in winds over ____ knots from any direction.
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SHOULD. 45.
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Allow a ___-minute cooling period between a blade fold and spread evolution before recycling the blade-fold motors.
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10
|
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|
Tail pylon/stabilator fold and spread operations are limited to a maximum windspeed of ____ knots.
|
45
|
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Maximum rate of descent for level terrain shall not exceed ____ fpm, and for sloped terrain shall not exceed ____ fpm.
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720. 360.
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Maximum forward touchdown speed shall not exceed ____ knots groundspeed, with tail wheel locked and ____ knots groundspeed with tail wheel unlocked.
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75. 20.
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Maximum ground taxi speed is limited to ____ knots with tail gear shimmy damper, and ____ knots without shimmy damper.
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40. 20.
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Slope landing limitations are ____ degrees noseup slope, ____ degrees nosedown slope, ____ degrees cross slope.
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9. 6.12.
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|
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Maximum gross weight of the helicopter is ________ lbs. Maximum gross weight internal load limit is ______ lbs. Maximum cargo floor loading is ____ pounds/square foot.
|
21,700. 20,800. 225 POUNDS/SQ FT.
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|
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Maximum weight that may be suspended from the cargo hook is limited to _____ pounds.
|
6000
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Maximum weight that may be suspended from the rescue hoist is ____ lbs.
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600
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|
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Helicopters without blade de-ice equipment are prohibited from flight into icing conditions (ambient temperatures of ____ degrees or below in _________.
|
5 DEG C OR BELOW IN VIS MOISTURE.
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|
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Environmental restrictions of the aircraft prohibit operation in temperatures below -____ or above +____.
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-40C(-40F) OR ABOVE +60C(+140F)
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Backup hydraulic pump operation limits when rotor is not engaged.
|
"+33 to +38: 24MIN ON, 72 MIN OFF
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|
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APU operation at ambient temperature of ___ degrees C and above with engine and rotor operating is limited to ____ minutes. With engine and rotor not operating, the APU may be operated continuously up to an ambient temperature of ___ degrees C.
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43. 30 MINUTES. 51.
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|
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CAUTION: Engines should be cooled for ___ minutes at an Ng of ___ percent or less before moving PCLs to OFF. If an engine is shut down without being cooled, it should not be restarted for ___ hours unless restart is performed within 5 minutes.
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2. 90. 4.
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|
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CAUTION: If TGT rises above ____ degrees C, perform Post Shutdown Engine Fire emergency procedure.
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540
|
|
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Methods of eliminating roughness caused by blade stall (6)
|
"1. Decrease collective pitch.
|
|
|
To recover from Vortex Ring State: (3)
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"1. Decrease collective pitch.
|
|
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WARNING: While operating in a salt spray environment for any period of time, a TGT rise of ____ degrees C or more for a constant torque is an indication of engine performance and possible ____________. A TGT rise of greater than ____ degrees C for a constant torque is an indication of engine performance degradation which may result in ____________.
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20. SALT ENCRUSTATION. 40. COMPRESSOR STALLS.
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|
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Note: The urgency of certain emergencies requires immediate and instinctive action by the ______. The most important single consideration is ____________. All procedures are subordinate to this requirement.
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PAC. HELICOPTER CONTROL.
|
|
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Define Land As Soon As Possible.
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EXECUTE A LANDING AT THE FIRST SITE AT WHICH A SAFE LANDING CAN BE MADE.
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|
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Define Land as soon as practical.
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EXTENDED FLIGHT IS NOT RECOMMENDED. THE LANDING SITE AND DURATION OF THE FLIGHT ARE AT THE DISCRETION OF THE PIC.
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|
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Define LAND IMMEDIATELY (IAW chapter 12).
|
EXECUTE A LANDING WITHOUT DELAY. THE PRIMARY CONSIDERATION IS TO ENSURE THE SURVIVAL OF THE OCCUPANTS.
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Note: Master caution light illumination with no corresponding caution light may be an indication of a malfunctioning ______________ and/or ______________.
|
INTERMEDIATE TRANSMISSION. TAIL GEARBOX CHIP DETECTOR.
|
|
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When do the Fuel Low Caution Lights illuminate? _____
|
200-225 POUNDS.
|
|
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Engine OUT master warning illuminates at less than _____ percent Ng
|
55
|
|
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Low Rotor RPM master warning illuminates at less than ____ percent Nr.
|
96
|
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Establishing single-engine conditions involves placing the aircraft in the optimum configuration and flight regime to operate with one engine inoperative (OEI). This includes, but is not limited to, _____________ and ______________.
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ESTABLISHING SINGLE-ENGINE AIRSPEED AND REDUCING AOB.
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|
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Engine Malfunction in Flight EP
|
"*1. Control Nr.
|
|
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EMIF WARNING: Flying at an airspeed greater than _____ KIAS with one engine inoperative may result in ______________ in the event of a dual-engine failure.
|
105. UNRECOVERABLE DECAY OF NR.
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|
|
EMIF WARNING: With engine anti-ice on, up to ___ percent torque available is lost. Torque may be reduced as much as ___ percent with improperly operating engine inlet anti-ice valves.
|
18. 49.
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Engine High-Side Failure in Flight EP
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"*1. Engine Malfunction in Flight emergency
|
|
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Engine High-Side Failure on Deck EP
|
*1. PCLs — IDLE.
|
|
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Engine Low-Side Failure in Flight EP
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"*1. Engine Malfunction in Flight emergency procedure — PERFORM.
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|
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Engine Torque or TGT Spiking/Fluctuations
|
"If an engine instrument is spiking/fluctuating and inducing secondary indications in Ng, Np, and/or Nr:
|
|
|
ENG TQ/TGT Spiking WARNING: PCL movement during engine fluctuations may precipitate an engine failure. Consider performing _____________ procedure prior to manipulating the PCL. Maintaining a _______________when moving the PCL will minimize the Nr decay rate if the malfunctioning engine fails.
|
APU EMERGENCY START PROCEDURE. LOW POWER SETTING
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|
|
Compressor Stall EP
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"*1. Engine Malfunction in Flight emergency procedure — PERFORM.
|
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Engine High Speed Shaft Failure EP
|
"*1. Engine Malfunction in Flight emergency
|
|
|
HIGH SPEED SHAFT CAUTION: Following a high-speed shaft failure, the engine will overspeed, the Np over-speed system will flameout the engine, and the auto-ignition system will activate the relight feature. The engine Np governor will eventually bring Np down towards 100 percent. A _______ may be experienced each time the engine relights. The engine must be manually shut down to prevent further damage.
|
YAW KICK
|
|
|
An LDS malfunction is indicated (with PCLs in Idle) by Ng of the malfunctioning engine ___% to ___% higher than the other engine.
|
3 TO 4
|
|
|
Abort Start EP
|
"To abort start:
|
|
|
Conditions to Abort Start (5)
|
"1. Ng does not reach 14 percent within 6 seconds after starter initiation.
|
|
|
Engine Malfunction During Hover/Takeoff EP
|
"*1. Control Nr.
|
|
|
Autorotation NOTE: With both engines secured, the cushioning collective pull at the bottom of the autorotation will result in ____ yaw vice the ____ yaw associated with practice autorotations.
|
LEFT YAW VICE THE RIGHT YAW.
|
|
|
Single-Engine Failure EP
|
*1. Engine Malfunction in Flight emergency procedure — Perform.
|
|
|
Engine Air Restart EP
|
"*1. APU Emergency Start procedure — As required.
|
|
|
Approximately _____ feet will be required to accomplish a dual engine restart based on APU and engine start cycles and typical autorotative rates of descent
|
5000
|
|
|
Engine Restart WARNING: Engine failure accompanied by ______________ indicates damage to the engine. There is a possibility that any attempt to restart the engine may result in a ________.
|
EXPLOSION OR UNUSUAL NOISE. FIRE.
|
|
|
CAUTION: Nose attitudes in excess of ____ nose-up at altitudes of ____ ft or less will caust the tail bumper/stabilator to impact the ground.
|
13 DEGREES. 15.
|
|
|
WARNING: Appearance of the ENG INLET ANTI-ICE ON advisory when OAT is greater than 13 degrees C is an indication of a malfunctioning engine inlet anti-ice valve. The resultant loss of torque could be a maximum of ____ percent when anti-ice valves are open.
|
49
|
|
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APU Emergency Start EP
|
"*1. ECS — OFF.
|
|
|
CAUTION: To prevent an APU exhaust fire, wait at least ___ minutes after APU shutdown before attempting a restart.
|
2
|
|
|
CAUTION: During ground operation at high ambient temperatures, the APU OIL HOT caution may appear. The APU should be shut down immediately to prevent damage. After allowing APU to cool for ___ minutes, check oil level. If within limits, APU may be restarted.
|
60
|
|
|
WARNING: With unusual vibrations in flight, a running landing is RECOMMENDED / NOT RECOMMENDED due to rotor instability and possible loss of helicopter control
|
NOT RECOMMENDED
|
|
|
Unusual Vibrations on Deck EP
|
"*1. Collective — Lower.
|
|
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Hung Droop Stop EP
|
*1. Re-engage rotor to greater than 75 percent Nr.
|
|
|
Low Rotor RPM EP
|
*1. Control Nr.
|
|
|
Rotor Overspeed EP
|
*1. Land as soon as practical.
|
|
|
Main Transmission Malfunction
|
"If failure is imminent:
|
|
|
Main Transmission Malfunction WARNING: Catastrophic transmission failure will result in ______________. Consideration should be given to transiting at minimum power airspeed and a low altitude flight profile (approximately ___ ft and ___ KIAS) to permit a quick flare followed by an immediate landing/ditching. Applicable steps of the Immediate Landing/Ditching emergency procedure should be completed.
|
LOSS OF HELICOPTER CONTROL. 80. 80.
|
|
|
Input Module Chip EP
|
*1. Main Transmission Malfunction emergency procedure — Perform.
|
|
|
Tail/Intermediate Transmission Malfunction EP
|
"If failure is imminent:
|
|
|
Tail transmission Malfunction WARNING: High power settings require maximum performance of the tail rotor drive system and may precipitate __________.
|
ULTIMATE DRIVE FAILURE
|
|
|
Tail transmission Malfunction WARNING: Consideration should be given to transiting at an altitude sufficient to _____________ and performing the applicable steps of the Immediate Landing/Ditching emergency procedure.
|
ENTER AN AUTOROTATION
|
|
|
Loss of TR Drive ALT/AS sufficient to establish Autorotation EP
|
"*1. PAC call — AUTO, AUTO, AUTO.
|
|
|
Loss off TR Drive WARNING: Altitude hold will remain engaged unless deselected. If the __________ release button is not depressed, the DAFCS will attempt to maintain aircraft altitude through the _________ servo. AFCS commanded collective movement can result in an accelerated ________.
|
COLLECTIVE TRIM. COLLECTIVE TRIM.
|
|
|
Loss of TR Drive ALT/AS not sufficient to establish Autorotation EP
|
"*1. PAC call — HOVER, HOVER, HOVER.
|
|
|
WARNING: an uncommanded _____ yaw of at least ____ to ____ degrees will occur when the tail rotor servo switches from normal to backup in a hover.
|
RIGHT. 20. 30.
|
|
|
Loss of Tail Rotor Control EP
|
"*1. Collective/airspeed — Adjust as required to control yaw.
|
|
|
#1 Primary Servo or #1 Transfer Module Leak EP
|
"*1. SERVO Switch — 1st OFF.
|
|
|
#2 Primary Servo or #2 Transfer Module Leak EP
|
"*1. SERVO Switch — 2nd OFF.
|
|
|
CAUTION: Up to ___ pounds of left pedal force will be required when hovering with boost servos off with starboard crosswinds. This value is significantly reduced with port crosswinds.
|
75
|
|
|
Boost Servo Hardover EP
|
*1. SAS/BOOST pushbutton — OFF.
|
|
|
Flashing AFCS Degraded Caution Light at Night/IMC EP
|
"During automatic approach (Night/IMC):
|
|
|
Flashing AFCS Degraded Caution Light with ALT Fail at Night/IMC EP
|
"In a coupled hover (night/IMC):
|
|
|
Stabilator Auto Mode Failure EP
|
"*1. PAC Call — STAB, STAB, STAB.
|
|
|
Stabilator Failure EP WARNING: Re-engagement of the automatic mode after a shutdown results in automatic mode operating for ______...subsequent re-engagement (circle one) SHOULD / SHALL not be attempted since it may result in additionall stabilator movement.
|
1 SEC. SHALL
|
|
|
Stabilator Fixed airspeed Limits
|
"0 DEG: 150KIAS
|
|
|
Unusual Attitude Recovery EP
|
"*1. Level wings.
|
|
|
Total AC Power Failure EP
|
"*1. Safe Altitude and Airspeed — Establish.
|
|
|
#1 or #2 Fuel Filter Bypass/ #1 or #2 Fuel Press CL EP
|
"*1. Fuel selector lever (affected engine) — XFD (DIR if currently in XFD).
|
|
|
#1 and #2 Fuel Filter Bypass/ #1 and #2 Fuel Press CL EP
|
"*1. Land As Soon As Possible.
|
|
|
Fuel Filter Bypass WARNING: Be prepared for a _____________. Recommended aispeed profile is 80 KIAS to minimize Nr droop should dual-engine failure occur.
|
DUAL-ENGINE FAILURE
|
|
|
Fuel Press Caution Light WARNING: Intermittent appearance of a FUEL PRESS caution may be an indication of __________________ which could cause momentary fluctation in engine power or _______.
|
AIR LEAKING INTO THE FUEL SUPPLY LINES
|
|
|
Fuel Low Caution Light WARNING: With less than ____ pounds of fuel, fuel starvation may occur when balanced flight is not maintained and/or pitch attitudes exceed ___ degrees noseup or nosedown.
|
600. 15.
|
|
|
External Engine Fire EP
|
"*1. Confirm Fire.
|
|
|
Internal Engine Fire EP
|
*1. Starter — Engage. Motor Engine.
|
|
|
APU Fire EP
|
"*1. APU T--Handle — PULL.
|
|
|
Cockpit Fire/Cabin Fire EP
|
"*1. Affected power switches and CBs — Secure.
|
|
|
Sonobuoy Lithium Battery Venting EP
|
"If the pungent odor and rusty metallic taste characteristic of SO2 fumes are detected, execute the following procedure:
|
|
|
Smoke and Fumes Elimination EP
|
"*1. Airspeed — Adjust, as required.
|
|
|
Immediate Landing/Ditching EP
|
"*1. Crew and passengers — Alert.
|
|
|
Immediate Landing/Ditching WARNING: Failure to remain strapped in aircraft until all violent motion or inrushing water stops may result in ______ or ______.
|
INJURY/INCAPACITATION
|
|
|
Underwater Egress EP
|
"*1. HABD — As required.
|
|
|
Underwater Egress WARNING: Do not _________ until outside of helicopter.
|
INFLATE LPU
|
|
|
FLIR Uncommanded Lasing EP
|
"*1. WEAPON SELECT (AN/ASQ-198) — OFF.
|
|
|
Shall
|
has
|
|
|
_______
|
has
|
|
|
WARNING:
|
|
|
|
CAUTION:
|
|
|
|
CAUTION:
|
|
|
|
WARNING:
|
|
|
|
WARNING:
|
|
|
|
WARNING:
|
If
|
|
|
Operation
|
of
|
|
|
TGT
|
Limits
|
|
|
810-851
|
30
|
|
|
851-903
|
2.5
|
|
|
903-949
|
12
|
|
|
NORMAL
|
CONDITIONS:
|
|
|
C-POWER
|
891+-10"
|
|
|
Nr
|
Limits
|
|
|
NORMAL
|
96-101%.
|
|
|
POWER
|
OFF
|
|
|
NORMAL
|
90-105.
|
|
|
OVERSPEED:
|
127.
|
|
|
Np
|
Limits
|
|
|
Single-Engine
|
Torque
|
|
|
Dual-Engine
|
Torque
|
|
|
4000-5000DA:
|
103%
|
|
|
5000-6000DA:
|
100%
|
|
|
6000-8000DA:
|
94%
|
|
|
8000-1000DA:
|
88%
|
|
|
1000-13000DA:
|
78%
|
|
|
10
|
SEC
|
|
|
Ng
|
Limits "CONTINUOUS:
|
|
|
INTERMEDIATE
|
30
|
|
|
12-SECOND
|
TRANSIENT:
|
|
|
Engine
|
Oil
|
|
|
30
|
MIN
|
|
|
MAX:
|
150"
|
|
|
Engine
|
Oil
|
|
|
PRECAUTIONARY:
|
22-26
|
|
|
NORMAL
|
OPERATION:
|
|
|
PRECAUTIONARY:
|
100-120
|
|
|
MAXIMUM
|
120
|
|
|
NOTE:
|
NORMAL
|
|
|
Main
|
Transmission
|
|
|
PRECAUTIONARY:
|
105-120
|
|
|
MAX:
|
120"
|
|
|
Main
|
Transmission
|
|
|
IDLE
|
AND
|
|
|
CONTINUOUS:
|
30-65PSI
|
|
|
PRECAUTIONARY:
|
65-130PSI
|
|
|
MAX:
|
130PSI
|
|
|
WARNING:
|
FORWARD
|
|
|
Situations
|
which
|
|
|
STARTER
|
DROPOUT
|
|
|
OPERATION
|
IN
|
|
|
CROSSBLEED
|
STARTS
|
|
|
COMPRESSOR
|
STALLS
|
|
|
Engine
|
Start
|
|
|
When
|
crossbleed
|
|
|
Second
|
Cycle
|
|
|
Third
|
Cycle
|
|
|
Fourth
|
Cycle
|
|
|
16C
|
TO
|
|
|
Second
|
Cycle
|
|
|
ANY
|
TEMPERATURE
|
|
|
NoteTimes
|
for
|
|
|
T/F.
|
Engine
|
|
|
The
|
main
|
|
|
Maximum
|
wind
|
|
|
Maximum
|
(redline)
|
|
|
Maximum
|
airspeed
|
|
|
Maximum
|
airspeed
|
|
|
Sideward/rearward
|
flight
|
|
|
Airspeed
|
limit
|
|
|
Airspeed
|
limit
|
|
|
Airspeed
|
limit
|
|
|
Airspeed
|
limit
|
|
|
Airspeed
|
limit
|
|
|
Airspeed
|
limit
|
|
|
The
|
maximum
|
|
|
Maneuvering
|
with
|
|
|
Bank
|
angles
|
|
|
Prolonged
|
hovering
|
|
|
Maximum
|
operating
|
|
|
Prohibited
|
manuevers "1.
|
|
|
2.
|
Abrupt
|
|
|
3.
|
Bank
|
|
|
4.
|
Hovering
|
|
|
5.
|
Practice
|
|
|
6.
|
Practice
|
|
|
7.
|
Intentional
|
|
|
MAD
|
minimum
|
|
|
MAD
|
Deployment
|
|
|
AOB:
|
0.
|
|
|
AIRSPEED
|
40
|
|
|
MAD
|
Retrieval/docking
|
|
|
MAD
|
airspeeds
|
|
|
LEVEL
|
TURNS:
|
|
|
DESCENTS:
|
80
|
|
|
CLIMBS:
|
80
|
|
|
MAD
|
jettisoning
|
|
|
Airspeed
|
limit
|
|
|
Minimum
|
altitude
|
|
|
Maximum
|
rotor
|
|
|
Blades
|
______
|
|
|
Allow
|
a
|
|
|
Tail
|
pylon/stabilator
|
|
|
Maximum
|
rate
|
|
|
Maximum
|
forward
|
|
|
Maximum
|
ground
|
|
|
Slope
|
landing
|
|
|
Maximum
|
gross
|
|
|
Maximum
|
weight
|
|
|
Maximum
|
weight
|
|
|
Helicopters
|
without
|
|
|
Environmental
|
restrictions
|
|
|
Backup
|
hydraulic
|
|
|
+39
|
and
|
|
|
APU
|
operation
|
|
|
CAUTION:
|
Engines
|
|
|
CAUTION:
|
If
|
|
|
Methods
|
of
|
|
|
2.
|
Decrease
|
|
|
3.
|
Gradually
|
|
|
4.
|
Increase
|
|
|
5.
|
Decrease
|
|
|
6.
|
Decrease
|
|
|
To
|
recover
|
|
|
2.
|
Move
|
|
|
3.
|
Enter
|
|
|
WARNING:
|
While
|
|
|
Note:
|
The
|
|
|
Define
|
Land
|
|
|
Define
|
Land
|
|
|
Define
|
LAND
|
|
|
Note:
|
Master
|
|
|
When
|
do
|
|
|
Engine
|
OUT
|
|
|
Low
|
Rotor
|
|
|
Establishing
|
single-engine
|
|
|
Engine
|
Malfunction
|
|
|
W:Flying
|
at
|
|
|
*2.
|
CONTGCY
|
|
|
*3.
|
Single--engine
|
|
|
*4.
|
ENG
|
|
|
W:
|
With
|
|
|
*5.
|
External
|
|
|
as
|
required.
|
|
|
*6.
|
Identify
|
|
|
EMIF
|
WARNING:
|
|
|
EMIF
|
WARNING:
|
|
|
Engine
|
High-Side
|
|
|
procedure
|
—
|
|
|
*2.
|
PCL
|
|
|
a.
|
Torque
|
|
|
b.
|
Matched
|
|
|
c.
|
Matched
|
|
|
3.
|
Land
|
|
|
C:
|
If
|
|
|
system
|
will
|
|
|
N:
|
With
|
|
|
Engine
|
High-Side
|
|
|
Engine
|
Low-Side
|
|
|
2.
|
PCL
|
|
|
a.
|
Torque
|
|
|
b.
|
Matched
|
|
|
c.
|
Matched
|
|
|
3.
|
Land
|
|
|
C:
|
When
|
|
|
Engine
|
Torque
|
|
|
*1.
|
Engine
|
|
|
If
|
fuel
|
|
|
*2.
|
Land
|
|
|
W:
|
PCL
|
|
|
ENG
|
TQ/TGT
|
|
|
Compressor
|
Stall
|
|
|
*2.
|
PCL
|
|
|
C:
|
If
|
|
|
Engine
|
High
|
|
|
procedure
|
—
|
|
|
*2.
|
PCL
|
|
|
3.
|
Land
|
|
|
C:
|
Following
|
|
|
HIGH
|
SPEED
|
|
|
An
|
LDS
|
|
|
Abort
|
Start
|
|
|
*1.
|
PCL
|
|
|
*2.
|
ENGINE
|
|
|
*3.
|
Starter
|
|
|
4.
|
Starter
|
|
|
C:
|
For
|
|
|
Conditions
|
to
|
|
|
2.
|
No
|
|
|
3.
|
No
|
|
|
4.
|
ENG
|
|
|
5.
|
TGT
|
|
|
Engine
|
Malfunction
|
|
|
*2.
|
CONTGCY
|
|
|
If
|
a
|
|
|
*3.
|
Set
|
|
|
If
|
able
|
|
|
*4.
|
Engine
|
|
|
Autorotation
|
NOTE:
|
|
|
Single-Engine
|
Failure
|
|
|
Engine
|
Air
|
|
|
*2.
|
ENGINE
|
|
|
*3.
|
Fuel
|
|
|
*4.
|
PCL(s)
|
|
|
*5.
|
Starter(s)
|
|
|
*6.
|
PCL(s)
|
|
|
*7.
|
PCL(s)
|
|
|
W;
|
EXPLOSION
|
|
|
W:
|
CROSSBLEED
|
|
|
C:
|
94%
|
|
|
|
Approximately
|
|
|
Engine
|
Restart
|
|
|
CAUTION:
|
Nose
|
|
|
WARNING:
|
Appearance
|
|
|
APU
|
Emergency
|
|
|
*2.
|
AIR
|
|
|
*3.
|
FUEL
|
|
|
*4.
|
APU
|
|
|
*5.
|
APU
|
|
|
CAUTION:
|
To
|
|
|
CAUTION:
|
During
|
|
|
WARNING:
|
With
|
|
|
Unusual
|
Vibrations
|
|
|
*2.
|
PCLs
|
|
|
*3.
|
Rotor
|
|
|
Hung
|
Droop
|
|
|
Low
|
Rotor
|
|
|
Rotor
|
Overspeed
|
|
|
Main
|
Transmission
|
|
|
*1.
|
LAND
|
|
|
If
|
secondary
|
|
|
*2.
|
Land
|
|
|
3.
|
APU
|
|
|
4.
|
NO.
|
|
|
If
|
no
|
|
|
5.
|
Land
|
|
|
W:
|
Catastrophic
|
|
|
Main
|
Transmission
|
|
|
Input
|
Module
|
|
|
Tail/Intermediate
|
Transmission
|
|
|
*1.
|
LAND
|
|
|
If
|
failure
|
|
|
2.
|
Land
|
|
|
W:
|
High
|
|
|
W:
|
Consideration
|
|
|
Tail
|
transmission
|
|
|
Tail
|
transmission
|
|
|
Loss
|
of
|
|
|
*2.
|
Autorotation
|
|
|
*3.
|
Drive
|
|
|
*4.
|
Immediate
|
|
|
*5.
|
PCLs
|
|
|
W:
|
Altitude
|
|
|
Loss
|
off
|
|
|
Loss
|
of
|
|
|
*2.
|
Collective
|
|
|
*3.
|
PNAC
|
|
|
*4.
|
PCLs
|
|
|
C:
|
Altitude
|
|
|
WARNING:
|
an
|
|
|
Loss
|
of
|
|
|
W:
|
If
|
|
|
C:
|
If
|
|
|
#1
|
Primary
|
|
|
*2.
|
Land
|
|
|
If
|
the
|
|
|
*3.
|
Land
|
|
|
If
|
the
|
|
|
*4.
|
LAND
|
|
|
C:
|
Switching
|
|
|
#2
|
Primary
|
|
|
*2.
|
Land
|
|
|
If
|
the
|
|
|
*3.
|
Land
|
|
|
If
|
the
|
|
|
*4.
|
LAND
|
|
|
CAUTION:
|
Up
|
|
|
Boost
|
Servo
|
|
|
Flashing
|
AFCS
|
|
|
*1.
|
Initiate
|
|
|
Flashing
|
AFCS
|
|
|
*1.
|
Initiate
|
|
|
Stabilator
|
Auto
|
|
|
*2.
|
Cyclic
|
|
|
*3.
|
Collective
|
|
|
*4.
|
MAN
|
|
|
W:
|
It
|
|
|
W:
|
Re--engagement
|
|
|
and
|
re--engagement
|
|
|
Stabilator
|
Failure
|
|
|
Stabilator
|
Fixed
|
|
|
10DEG:
|
100
|
|
|
20DEG:
|
80KIAS
|
|
|
30DEG:
|
60KIAS
|
|
|
40DEG:
|
45KIAS"
|
|
|
Unusual
|
Attitude
|
|
|
*2.
|
Nose
|
|
|
*3.
|
Center
|
|
|
*4.
|
Stop
|
|
|
*5.
|
Control
|
|
|
Total
|
AC
|
|
|
*2.
|
Stabilator
|
|
|
W:
|
Ensure
|
|
|
N:
|
The
|
|
|
*3.
|
APU
|
|
|
#1
|
or
|
|
|
2.
|
Land
|
|
|
W:
|
Low
|
|
|
#1
|
and
|
|
|
*2.
|
APU
|
|
|
W:
|
Be
|
|
|
W:
|
Fuel
|
|
|
N:Consideration
|
should
|
|
|
Fuel
|
Filter
|
|
|
Fuel
|
Press
|
|
|
Fuel
|
Low
|
|
|
External
|
Engine
|
|
|
*2.
|
Engine
|
|
|
*3.
|
PCL
|
|
|
*4.
|
Engine
|
|
|
*5.
|
FIRE
|
|
|
If
|
airborne
|
|
|
*6.
|
LAND
|
|
|
If
|
fire
|
|
|
*7.
|
Land
|
|
|
N:
|
HF
|
|
|
Internal
|
Engine
|
|
|
APU
|
Fire
|
|
|
*2.
|
Confirm
|
|
|
*3.
|
FIRE
|
|
|
If
|
airborne
|
|
|
*4.
|
LAND
|
|
|
If
|
fire
|
|
|
*5.
|
Land
|
|
|
If
|
on
|
|
|
*6.
|
Fire
|
|
|
W:
|
Severity
|
|
|
N:
|
HF
|
|
|
Cockpit
|
Fire/Cabin
|
|
|
*2.
|
Portable
|
|
|
If
|
fire
|
|
|
*3.
|
Cabin/doors/vents/ECS
|
|
|
*4.
|
Unnecessary
|
|
|
CBs
|
—
|
|
|
If
|
fire
|
|
|
*5.
|
Land
|
|
|
W:
|
Without
|
|
|
W:
|
Severity
|
|
|
W:
|
Vapors
|
|
|
W:
|
It
|
|
|
C:
|
If
|
|
|
Sonobuoy
|
Lithium
|
|
|
W:
|
Portable
|
|
|
*1.
|
Alert
|
|
|
N:
|
If
|
|
|
*2.
|
Smoke
|
|
|
W:
|
Sulfur
|
|
|
Smoke
|
and
|
|
|
*2.
|
Doors/windows/vents
|
|
|
*3.
|
Aircraft
|
|
|
Immediate
|
Landing/Ditching
|
|
|
*2.
|
Shoulder
|
|
|
*3.
|
External
|
|
|
DUMP
|
as
|
|
|
*4.
|
Searchlight
|
|
|
*5.
|
MAYDAY/IFF
|
|
|
In
|
the
|
|
|
*6.
|
Windows
|
|
|
After
|
landing:
|
|
|
*7.
|
PCLs
|
|
|
*8.
|
Rotor
|
|
|
*9.
|
ATO
|
|
|
After
|
all
|
|
|
*10.
|
EGRESS."
|
|
|
Immediate
|
Landing/Ditching
|
|
|
Underwater
|
Egress
|
|
|
*2.
|
ICS
|
|
|
*3.
|
Door/Window
|
|
|
*4.
|
Place
|
|
|
*5.
|
Harness
|
|
|
*6.
|
Exit
|
|
|
After
|
egress:
|
|
|
*7.
|
Swim
|
|
|
Underwater
|
Egress
|
|
|
FLIR
|
Uncommanded
|
|
|
*2.
|
MASTER
|
|
|
*3.
|
LASER
|
|
|
If
|
lasing
|
|
|
*4.
|
FLIR
|
|
|
*5.
|
FLIR
|
|
|
panel,
|
SO
|
|
|
FLIR/HFS
|
AC)
|
