APART Flash Cards

• 5 psi minimum @ ground idle
• 35 psi minimum between 80% & 95%
• 50 psi minimum Equal to or greater than 95%
• 35-90 psi Normal Operation
• 110 psi maximum for Contingency
• 150 psi maximum for Cold Weather Starts

149 C Maximum

140 C

• 7 psi Minimum @ Ground Idle
• 20 psi Minimum @ 100% NR
• 20 to 90 psi Normal Operation

• 91% Minimum Transient power-on (red range)
• 91-97% Transient (yellow range)
• 97-101% Normal (green range)
• 101-106% Transient (yellow range)
• 106% Maximum Transient power-on (red)
• 108% Maximum during Autorotation (red)
• 111% Maximum Transient (red)

• Low Limit 2500 psi
• Normal 2500-3200 psi
• High Limit 3200 psi

• Low Limit 2500 psi
• Normal 2500-3500 psi
• High Limit 3500 psi

• red/white 120C maximum
• yellow/white 95-120C Caution

• 816C Maximum Continous (Green)
• up to 854C Intermediate (Yellow, 30 min range)
• up to 899C Maximum (Yellow, 10 min range)
• up to 932C Contingency Power (Yellow, 2.5 min)
• up to 943C Maximum Transient (Red, 12 sec)

• 100% Dual engine
• 123% single engine

• 50% Ground idle
• 50-111% Normal (Green)
• >111% Maximum (Red)

111.5% Maximum Transient

• NOTE:
• JP8+100 is not considered "Emergency Fuel". A DA Form 2408-13-1 entry will be made as described in Appendix C.

50,000 lbs

Structural Limit of Forward and AFT hook: 17,000 lbs

Structural Limit of Center Cargo hook: 26,000 lbs

• The maximum single load that can be suspended as a tandem load from the forward and aft hooks is 25,000 lbs
• When a combination of external and internal loads are carried during the same flight and the external load exceeds 12,000 lbs, position the internal load forward of the utility hatch. This procedure preclude encountering an excessively aft CG.

• The winch shall not exceed:
• (1) 3,000 lbs, straight pull
• (2) 6,000 lbs, one pulley
• (3) 9,000 lbs, two pulleys
• (4) 12,000 lbs, three pulleys

The rescue hoist is limited to a maximum load of 600 lbs

• A. Lowering the thrust
• B. Reducing the severity of the maneuver
• C. Reducing Airspeed

45 KCAS

45 KCAS

45 KCAS

60 KCAS

above 90 KCAS

above 130 KCAS

less than 100 KCAS

If a sling or hook should fail while carrying a tandem load, limit airspeed to a maximum of 60 KCAS

• Single DAFCS 100 KCAS
• DAFCS OFF 160 KCAS or Vne whichever is slower

• Chart in Ch. 5 (Fig. 5-9)
• Do not manually the LCT beyond the GND position on the cyclic trim indicators at calibrated airspeeds below 60 knots

• Maximum allowable airspeed is limited to 130 KCAS or Vne, whichever is slower
• Maximum allowable GWT for ground operation is 50,000 lbs
• The maximum allowable rate of descent at touchdown in snow is 480 ft/min. at GWTs up to 33k lbs, decreasing linearly to 240 ft/min at 46k lbs. For GWTs 46k lbs to 50k lbs, the rate of descent is 240 ft/min

• Normal operations: 36k lbs
• Emergency operations: 46K lbs

Taxiing will not be conducted in water conditions above Sea State 1 or in wind above 6 KCAS. Fast taxiing will be conducted in a straight line only and to a maximum speed of 10 KCAS when the lower nose enclosure is left in the water.

Rotor starting and shutdown will not be conducted when water conditions exceed Sea State 1 or wind exceeds 6 KCAS. Maximum GWT for starting and shutdown is 28,550 lbs.

Operation on water is restricted to 30 mins total flotation time without draining the helicopter

PROHIBITED

Operation in flight is prohibited except during emergencies.

The PITOT HEAT switch shall not be on for more than 5 mins. on the ground

Windshield heat shall not be used above 24C

The maximum rate for pressure refueling is 300 gal/min at 55 psi

• 820 US gallons
• useable fuel is 800 US gallons

should not exceed 5 psi

-11 psi

• Combat equipped Soldiers: 240
• Combat equipped paratroopers: 260
• Litter patient: 200 lbs per
• Medical attendants: 200 lbs per

33 fully equipped ground troops is provided by ten 3-man seats and three 1-man seats.

2k lbs capacity

24 litters, stacked 4 high, 3 tiers on each side of cargo compartment

On the treadways between STA 200.00 and 400.00

Uniformly distributed loads are those loads wherein the total weight of the item is equally spread over the item's entire contact area.

Compartments C, D and E are limited to 300 psf. The cargo ramp (Compartment F) is limited to 300 psf with a maximum total load of 3k lbs. when the ramp is level with the cargo floor.

Concentrated loads are those loads wherein the total weight of the item is supported by a contact area that is small compared to the size and weight of the load.

Concentrated loads can be loaded on the treadways and on the walkways. The treadways AFT of STA 160.00 and the ramp extensions are stressed for a total wheel load of 2500 lbs. The treadways forward of STA 160.00 and the walkway can be loaded to a total wheel load of 1,000 lbs. 75 psi for pneumatic tires and 50 psi for block and roller type wheels.

5k: 83 in fuselage floor and 4 on the ramp for a total of 87

10k: 8

Ramp MUST be level with the cargo floor if used for cargo. Weight should not exceed 3k lbs or 300 psf.

• Forward and down 4.0 g's
• Aft and Up 2.0 g's
• Lateral 1.5 g's

• Made up of extruded panels. Raised Extruded ridges provide surfaces on which cargo is moved.
• The flooring between STA 200.00 and 400.00 adn from buttline 44L and 44R, rests on rubber
• isolators which reduce overall internal load vibrations.

• Defined as executing a landing at the nearest suitable landing (e.g. open field) WITHOUT DELAY.
• The primary consideration is survival of the occupants.

is defined as executing a landing to the nearest suitable airfield/heliport.

is defined as adjusting the flight controls as necessary to establish an autorotational descent and landing.

• A. Thrust Control: Adjust as required to maintain NR.
• B. Pedals: Adjust as required.
• C. Cyclic: Adjust as required.

is defined as engine shutdown without delay. Engine shutdown in flight is usually not an immediate action item unless a fire exists. Before executing an engine shutdown, identify the affected engine by checking indications of torque, NR, NG, PTIT, engine oil pressure, ENG 1(2) FAIL warning.

• a. ENG COND lever-STOP
• b. FIRE PULL HANDLE-Pull as required
• c. ENG START switch-MTR if high PTIT is indicated

• is defined as engine shutdown to prevent PTIT from exceeding limits or whenever abnormal operation is indicated.
• If high PTIT is indicated, the engine must be motored to decrease PTIT below 260C.

• a. ENG COND lever-STOP
• b. ENG START switch-MTR if high PTIT is indicated

• If a second engine start is to be attempted, wait at least 15 seconds after the NG indicates zero before attempting start.
• This will allow sufficient time for fuel to drain from the combustion chamber.

• 1. AUTOROTATE
• 2. External Cargo-Jettison
• 3. FLT DIR CPLR-Uncouple

• a. Power turbine shaft failure, NP is greater than NR by more than 3%
• b. NG underspeed. NG speed is below 48%
• c. Engine flameout
• d. Over temperature start abort (primary mode only)
• e. FADEC primary and reversionary failure

• 1. Thrust control lever-Adjust as necessary to maintain NR
• 2. External Cargo-Jettison (if required)
• 3. FLT DIR CPLR-Uncouple
• Continued flight is not possible;
• 4. Land as soon as possible
• 5. EMER ENG SHUTDOWN (when conditions permit)
• Continued flight is possible;
• 1. Land as soon as practicable
• 2. EMER ENG SHUTDOWN (when conditions permit)

• 1. FADEC INC/DEC beep switch (affected engine)-As required
• 2. Reduce rate of thrust control changes

• 1. FADEC INC/DEC beep switches-Beep to 100%, match TQs
• 2. Reduce rate of thrust control lever changes
• 3. Land as soon as practicable

CAUTION: Do not manually select reversionary on the affected engine as ucommanded power changes may occur

• If engine power IS required for flight:
• 1. Land as soon as possible
• After landing:
• 2. EMER ENG SHUTDOWN-(Affected Engine)
• If engine power IS NOT required for flight:
• 1. EMER ENG SHUTDOWN-(Affected Engine)
• 2. FIRE PULL HANDLE (affected engine)
• 3. Refer to single-engine failure emergency procedures

• 1.Land as soon as possible
• 2.EMER ENG SHUTDOWN-As required

EMER ENG SHUTDOWN-(Affected engine)

When NG reaches zero (0):

EMER ENG SHUTDOWN-(Engaged engine)

If engine power IS required for flight:

Land as soon as possible

If engine power IS NOT required:

• 1. EMER ENG SHUTDOWN-(Affected Engine)
• 2. Refer to single engine failure procedures

If engine power IS required for flight:

Land as soon as possible

If engine power IS NOT required for flight:

• if engine/engine transmission oil presure IS below minimum limits or if engine/engine transmission oil temperature IS above the maximum limit:
• 1.EMER ENG SHUTDOWN-(Affected engine)
• 2.Refer to single engine failure procedures

• if engine/engine transmission oil presure IS NOT below minimum limits or if engine/engine transmission oil temperature IS NOT above the maximum limit:
• 3. ENG COND lever-Retard to reduce torque (10% minimum) on the affected engine
• 4. Land as soon as practicable

• 1. EMER ENG SHUTDOWN
• F2. Affected engine transmission-Check
• 3. Land as soon as possible

• F1. GND RESET-TEST switch-RESET
• If indicator does not reset:
• 2. Land as soon as possible

• F1. GND RESET-TEST switch-RESET
• If indicator DOES NOT reset and engine power IS required for flight:
• 2. Land as soon as possible
• If indicator DOES NOT reset and engine power IS NOT required for flight:
• 3. EMER ENG (affected engine)
• 4. Refer to single engine failure procedures

Land as soon as possible

• 1. Altitude-Descend to minimum safe altitude
• 2. Airspeed-100 Knots or Vne whichever is slower
• 3. Land as soon as practicable

• Engine power IS required:
• Land as soon as possible
• Engine power IS NOT required:
• 1. EMER ENG SHUTDOWN
• 2. Refer to single engine failure procedures

Land as soon as possible

• MAIN XMSN (FWD, COMB or AFT:
• Main transmission oil pressure and temperature ARE ABNORMAL
• Land as soon as possible
• Main transmission oil pressure and temperature are NORMAL
• Land a soon as practicable

Land as soon as possible

• 1. Land as soon as possible
• 2. Electrical Load-Reduce as much as possible

• Engine power IS required for flight:
• Land as soon as possible
• Engine power IS NOT required:
• 3. EMER ENG SHUTDOWN
• 4. Refer to single engine failure procedures

Land as soon as possible, Mandatory that the cockpit windows, air control handles and cockpit air knobs be closed

A hot start or residual fire will be detected by a rapid and abnomral rise in PTIT from the engine tail cone.

1. Abort Start

• 1. ABORT START
• 2. FIRE PULL HANDLE (affected engine)-PULL

• 1. Land as soon as possible
• F2. Confirm Fire
• 3. EMER ENG SHUTDOWN (affected engine)
• 4. Refer to single engine failure procedures
• After landing:
• EMER ENG SHUTDOWN

• 1. APU switch-OFF
• 2. ABORT START

• 1. EMER ENG SHUTDOWN
• 2. APU Switch-OFF (If operating)
• 3. BATT Switch-OFF

• 1. Land as soon as possible
• 2. GEN1 and 2 switches-OFF
• After landing:
• 3. EMER ENG SHUTDOWN
• 4. BATT Switch-OFF

• 1. Airspeed-Above 60 knots
• 2. Pilot sliding window-Open
• 3. Helicopter attitude-Yaw left, one half to one ball width on the inclinometer
• 4. Upper half main cabin door-open
• 5. RAMP EMER Switch-As required
• 6. Cargo loading ramp-As required
• 7. Copilot Sliding window-Closed
• 8. NVG Curtain-Open (if applicable)

• 1. AUX FUEL PUMP Switches (affected side) or ERFS II Pump switches if installed-OFF
• 2. Main Tank (affected side)-Monitor
• When 1k lbs of fuel remain:
• 3. AUX FUEL PUMP switches (affected side) or ERFS II Pump switches if installed-ON (monitor fuel page)
• When tank quantity reaches 1,600 lbs:
• 4. AUX FUEL PUMP Switches (affected side) or ERFS II Pump switches if installed-OFF
• 5. Steps 2 through 4-Repeat until auxillary tanks are empty

• 1. XFEED switch-OPEN (above 6,000 ft PA)
• 2. FUEL PUMP(S) circuit breakers-Check in
• Pump(s) are operational-Proceed to step 3
• Pump(s) are not operational-Proceed to step 4
• 3. XFEED Switch-CLOSED
• 4. FUEL PUMP Switches-OFF (inoperative pump(s))

• 1. XFEED Switch-CLOSED
• 2. Land as soon as possible

No.1 RECT and No. 2 RECT FAIL, ENG1 and ENG2 FUEL PRESS LO, and AFCS1 and AFCS2 FAIL (all on the failed GEN side)

• if bus tie DOES NOT exist
• 1. GEN switch-OFF/RESET, then ON
• If power is not restored:
• 2. Land as soon as possible
• If a bus tie DOES exist:
• 3. GEN switch-OFF/RESET, then ON
• if the caution remains on:
• 4. GEN switch-OFF
• 5. Electrical Load Meters-Check, if > than 100%, reduce electrical load as required
• SUGGEST SHEDDING THE FOLLOWING
• -LH/RH AC Cabin Utility Receptacles (if in use)
• -ENG1 and ENG2 EAPS FANs (if in use)
• 6. Monitor load meters as required (especially if additional equipment is added to the electrical load)
• 7. Land as soon as practicable

• If both generators fail:
• Land as soon as possible
• If unable to land:
• 1. Airspeed-below 100 knots
• 2. Altitude-Below 6,000 FT PA
• 3. AFCS SYSTEM SEL switch-OFF
• 4. PDPs-Check circuit breakers and AC cross-tie gang bars down
• 5. GEN1 and GEN2 Switch-OFF/RESET, then ON
• If electrical power IS restored (from either generator)
• Land as soon as possible
• If electrical power IS NOT restored:
• 6. APU-Start
• 7. APU GEN-ON
• 8. Reduce electrical load-As required
• 9. Land as soon as possible

• DC bus tie HAS NOT occurred:
• PDPs-check
• If power IS NOT restored:
• Land as soon as possible
• DC bus tie HAS occurred (only the No. 1 RECT or No. 2 RECT FAIL caution will be on):
• 1. PDPs-check
• 2. Electrical load meters-Check, if > than 100%, reduce electrical load as required

• SUGGEST SHEDDING THE FOLLOWING:
• -LH/RH DC Utility Receptacles (if in use)
• -PLT and CPLT Searchlights (if in use)
• -Air warrior system (if in use)

• 3. Monitor Load meters as required, (especially if additional equipment is added to the electrical load)
• 4. Land as soon as practicable

• Land as soon as possible
• if unable to land:
• 1. Airspeed-Below 100 knots
• 2. Altitude-Below 6k FT PA
• 3. AFCS-OFF
• 4. PDPs-Check circuit breakers in
• 5. DC CROSSTIE circuit breakers on both No. 1 and No. 2 PDPs-Pull out
• 6. DC equipment not required-OFF or pull out circuit breakers
• 7. Land as soon as possible

• Fluid loss IS evident:
• Land as soon as possible
• Fluid loss IS NOT evident:
• 1. PWR XFER switch (affected system)-ON
• F2. MAINTENANCE PANEL-Monitor
• 3. Land as soon as possible
• High fluid temperature IS evident:
• 4. Land as soon as possible

• 1. PWR XFER 1 and 2 switches-ON
• 2. Land as soon as possible Avoid large control inputs

• Fluid loss IS evident:
• 1. Land soon as possible
• 2. Isolation switch (affected subsystem)-OFF
• If pressure IS restored
• 1. Land as soon as practicable
• F2. Maintenance panel-monitor
• If fluid loss IS NOT evident:
• 1. APU-START
• 2. Land as soon as practicable
• F3. Maintenance panel-monitor
• If temperatures or pressures are abnormal or abnormal vibrations occur:
• Land as soon as possible
• High fluid temperature IS evident:
• Land as soon as possible

• 1. Land away from personnel in the water
• 2. EMER ENG SHUTDOWN

• Power Off:
• AUTOROTATE
• Power on:
• 1. Approach to a hover-5 to 10 feet
• 2. EMER ENG SHUTDOWN
• 3. AUTOROTATE

• If in AUTO MODE:
• 1. Airspeed-Adjust
• 2. CYCLIC TRIM circuit breakers-IN
• If LCT operation IS NOT indicated:
• 3. CYCLIC TRIM switch-MANUAL
• 4. FWD and AFT CYCLIC TRIM switches-Adjust for airspeed
• If LCT operation IS NOT indicated:
• FWD and AFT CYCLIC TRIM switches- RET for 30 seconds, before landing
• If in manual mode:
• 1. Airspeed-Adjust
• 2. CYCLIC TRIM circuit breakers-IN
• If LCT operation IS NOT indicated:
• CYCLIC TRIM switch-AUTO
• If LCT operation IS NOT indicated:
• 1. CYCLIC TRIM switch-MANUAL
• 2. FWD and AFT CYCLIC TRIM switches-RET both LCTs for 30 seconds, before landing

• 1. AIRSPEED-REDUCE to 100 knots or Vne, whichever is slower
• 2. Altitude-Adjust as required
• 3. AFCS SYSTEM SEL switch-Isolate defective system. Turn NO. 1, if not isolated, turn NO. 2 ON
• If system IS NOT isolated:
• AFCS SYSTEM SEL SWITCH-OFF

• AFCS SYSTEM SEL switch-OFF
• If IMC:
• Land as soon as practicable