47D CH 5

Two Pilots and one Flight Engineer

Should 108 percent power off be inadvertently exceeded, no entry need be made in DA Form 2408-13-1 unless the rotor system exceeds 111 percent. Even though no action is required when RPM exceeds 108 percent power off but remains less than 111 percent, willful operation should not be conducted in this range. Operation between 97 and 92 percent is permitted when water taxiing.

Flight at or below 98% RRPM (NR) with an inoperative cruise guide indicator is prohibited.

• APU - shall not be started with a tailwind in excess of 25 knots.
• Main ENG - shall not be started with a tailwind in excess of 10 knots.
• If it becomes necessary to shut down in conditions outside the limits shown in figure 5-7, the following precautions are recommended:
• a. landed in an area which is clear, as level as possible, and at least 300 feet away from any vertical obstructions, abrupt changes in ground terrain, trees, bushers, fences, ect.
• b. Oriented such that the wind would be coming in at the left side. If unable to determine wind, dispatch a crew member beyond the rotor wash to make a true wind direction determination before engines are secured.

• 91% minimum transient
• 96% (not applicable)
• 97-101% normal operation
• 102-105% transient
• 106% max transient Power ON
• 108% max during AUTOROTATION
• 111% max transient
• 115% (not applicable)

170 Knots maximum (refer to section 5 for addtional airspeed limitations)

• 400^o C to 815^oC Continuous Operation
• 855^oC maximum for not more than 30 minutes
• 900^oC maximum for not more than 10 minutes
• 930^oC maximum for not more than 2.5 minutes
• 816^oC to 940^oC Time-Limited operations
• 940^oC maximum for not more than 12 seconds NEVER EXCEED

• 50 % minimum ground idle
• 110 % maximum

• 5 PSI min at ground idle
• 35 PSI min at 80 to 95% N1 (NG)
• 50 PSI min at 95% N1 or Above
• 35 to 90 PSI for normal operation
• 110 PSI max at Emergency Power
• 150 PSI max for cold weather starts

149^oC Maximum

• 100 % max Dual Engine
• 123 % max Single Engine

• 2000 PPH 100% Torque
• (for "fuel flow limit with torque indicator system failure" only. Dual Engine)

• 7 PSI min at ground idle
• 20 PSI min at 100% RRPM
• 20 to 90 PSI normal operation

140^oC Max

• 2500 PSI min
• 2500 to 3200 PSI normal operation
• 3200 PSI max

• 2500 PSI min
• 2500 to 3500 PSI normal operation
• 3500 PSI max

• 120^oC Max
• 95^oC to 120^oC Caution

For pre-mission performance planning, 30 minute power available is the maximum power authorized for departure and arrival at or below 40 KIAS. Maximum Continuous Power is the maximum power authorized for cruise flight. Additional gross weight limits are contained in CH 7 cruise charts.

Contingency power is A Single Engine Operating condition only to be used during actual emergency conditions. Usage of contingency power 900^o to 930^oC PTIT is permissible for an unlimited number of occurrences as long as each occurrence is 2 minutes 30 seconds or less. Maximum transient 940^oC PTIT is not to exceed 12 seconds.

A gas producer (N1 (NG)) overspeed exists when N1 (NG) of 110 is exceeded. An N1(NG) overspeed can cause over temperature and/or over torque. A power turbine (N2(IP)) overspeed may exist, depending on power being used when 106% RRPM (NR) is exceeded.

Emergency Fuel shall not be used for more than six hours cumulative time. NOTE: JP8+100 is not considered "Emergency Fuel".

50,000 pounds max allowable operating gross weight

Structural limitations only

• FWD & AFT hook 17,000 lbs each
• Tandem FWD & AFT hook 25,000 lbs
• Center Cargo hook 26,000 lbs

Combination Internal and external loads and the external exceeds 12,000 lbs, position the internal load forward of the utility hatch. This porcedure will preclude encountering an excessively aft CG.

Shall not exceed:

• 3,000 lbs straight line pull
• 6,000 lbs one pulley
• 9,000 lbs two pulleys
• 12,000 lbs three pulleys

Rescue Hook is limited to a max load of 600 lbs

Maximum airspeed in sideward flight is 45 knots

Maximum airspeed in rearward flight is 45 knots

CAUTION: a Dual FADEC primary channel failure may occur when rearward flight or a tailwind exceeds 40 knots. These conditions should be avoided.

NOTE: Aircrew should be alert to the potential for large engine torque oscillations during rearward flight operations

Maximum crosswind or tailwind for hover is 45 knots

Maximum airspeed with the lower section of the cabin entrance door open and locked is 60 KIAS

The rescue hatch door shall not be opened or closed above 90 KIAS

The windshield wipers shall be off at airspeeds above 130 knots

Upper section of the cabin entrance - assure that airspeed is less than 100 KIAS before closing door in flight

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

Refer to the Chart 5-3 (max allowable airspeeds and gross weights with either LCT fully retracted)

DO NOT Manually extend the LCT beyond the GND position on the cyclic trim inidcators at indicated airspeeds below 60 knots. Use of extended cyclic trim at low airspeeds will result in high aft rotor blade stresses.

The airspeed limit when operating on single AFCS is 100 KIAS or Vne, whichever is slower. The helicopter may be operated with both AFCS off up to 160 KIAS or Vne, whichever is slower.

Aerobatics are prohibited with this helicopter. Aerobastics are defined as intentional maneuvers beyond +/- 30^opitch and/or 60^o roll.

With an operative cruise guide indicator, bank angles are limited by the cruise guide indicator, but no greater than 60^o. When operating with altitude hold, limit bank angle limits to 45^o maximum.

Inoperative Cruise Guide indicator - Figure 5-5

Max ground speed for running landing is 60 Knots.

Max nose-up attitude during landings is 20^o.

To prevent droop stop pounding, when all the landing gear are in contact with the ground, and the thrust is at ground detent, flight control movements shall not exceed the follwing from the neutral position:

• Right or Left directional pedal 0.75 inch
• Aft Cyclic 2.00 inch
• Lateral Cyclic 1.00 inch
• Thrust No lower than ground detent

When ground taxiing less than 75 feet from an obstruction, on an unimproved/unfamiliar airfield not designated for CH-47D helicopters, a blade watcher and taxi director shall be positioned as show in figure 8-2. If approved designation - does not apply

ATG Towing operations are prohibited

APU operation in flight is prohibited except during emergencies

the PITOT switch shall not be on for more than 5 minutes on the ground.

Windshield heat shall not be used above 24^oC

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

Max capacity 825.5 US Gallons - usable fuel is 800 US Gallons per tank when single point pressure refueling

Trying to pressure refuel the tanks without connecting the vent lines could over pressurize the tanks

Max pressure in the ERFS II Tank should not exceed 5 PSI

Max allowable suction defueling pressure is -11 PSI (greater could damage the internal components of the ERFS II tank assembly)