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MH-60R RDAF > MH-60R Number limits > Flashcards

MH-60R Number limits Flashcards

1
Q

TURBINE GAS TEMPERATUR (TGT) LIMITS

A

0 - 810 Continuous Green

810 - 851 30 minutes Yellow

851 - 878 2.5 minutes (10 minutes for Max Power or limiter checks only) Red

878 - 903 2.5 minutes Red

903 - 949 12 seconds Red

949 Maximum Red

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2
Q

Power Turbine Speed (Np)

A

<96% Avoid Red

96-105% Continuous Green (Yellow above 101%)

105-117% 20 seconds Yellow

117-120% 12 seconds Yellow

120% Maximum Red

CAUTION
During engagement, extended operation in the 20 to 40% and 60 to 75% ranges may cause engine damage.

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3
Q

Main Rotor Speed (Nr)

A

<96 % Avoid Red

96 - 101% Continuous Green

101 - 120% Precautionary Yellow

120% Maximum Red

>120% 123% Maximum for FCF only Red

127% Overspeed latch Red

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4
Q

Dual-Engine Torque (TRQ) <80 KIAS

A

0 - 120 % Continuous Green

120 - 144 % 10 seconds Yellow

144% Maximum Red

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5
Q

Dual-Engine Torque (TRQ) >80 KIAS

A

0 - 106% Continuous Green

106 - 127 % 10 seconds Yellow

127% Maximum Red

NOTE
Dual Engine Torque limits apply when both engines are above 65% torque

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6
Q

Single-Engine Torque (TRQ)

A

0 - 135% Continuous Green

135 - 144% 10 seconds Red

144% Maximum Red

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7
Q

Gas generator Speed (Ng)

A

0 - 102.2% Continuous Green

102.2 - 106% 2.5 minutes Yellow

106 - 107 % 12 seconds Red

107% Maximum Red

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8
Q

Transmission Temperature (XMSN T)

A

-50 - 105 Continuous Green

105 - 120 Precautionary Yellow

120 Maximum Red

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9
Q

Transmission Pressure (XMSN P)

A

20 psi Minimum Red

20-30 psi Idle and transient Yellow

30 - 65 (45 to 60 psi in level flight) Continuous Green

65 - 130 Precautionary Yellow

130 Maximum Red

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10
Q

Engine Oil Temperature (Eng Oil T)

A

-50 - 135 Continuous Green

135 - 150 30 minutes Yellow

150 Maximum Red

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11
Q

Engine oil pressure (Eng Oil P)

A

22 psi Minimum Red

22 - 26 psi Precautionary Yellow

26 - 100 psi Continuous Green

100 - 120 psi Precautionary Yellow

120 Maximum Red

NOTE
Normal idle range is 22 to 55 psi

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12
Q

Engine Start with ignition on

A

<16 º
First Cycle 60 seconds
Second Cycle 60 seconds
Third Cycle 60 seconds
Fourth Cycle 30 minutes

16º - 52º
First Cycle 60 seconds
Second Cycle 30 minutes

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13
Q

Engine Start Ignition Off

A

Any temperature

Starter engaged 2 Minutes

Starter disengaged 5 Minutes

Starter Engaged 2 Minutes

Stater Disengaged 30 minutes

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14
Q

Rotor engagement and disengagement limitations

Maximum wind velocity for rotor engagement or disengagement is _______ from any direction.

A

Maximum wind velocity for rotor engagement or disengagement is 45 knots from any direction.

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15
Q

Airspeed limitations

  1. Maximum (Vne) - ________
  2. Maximum as limited by blade stall - refer to figure 22-3
  3. Sideward/rearward flight - ______
  4. Autorotation - ______
  5. Boost Off - ______
  6. SAS 1 and SAS 2 inoperative in IMC - ______
  7. Either PRI SERVO PRESS caution - _____
  8. Searchlight in fixed position other than stowed - ______
  9. Searchlight in transition - ______
  10. Dome at or above trail (Cable extended 10 feet, dome approximately 6 feet below aircraft) - ______, _______. Dome below trail - ______, _______
  11. Cabin door opening/closing - ______.

NOTE
With cabin door open, uncoordinated flight should be avoided.

With MTS installed, failure to maintain balanced flight below 90 KIAS in descents over ______ fpm will result in inaccurate and erratic airspeed indications.

A
  1. Maximum (Vne) - 180 KIAS
  2. Maximum as limited by blade stall - refer to figure 22-3
  3. Sideward/rearward flight - 35 knots
  4. Autorotation - 100 KIAS
  5. Boost Off - 140 KIAS
  6. SAS 1 and SAS 2 inoperative in IMC - 125 KIAS
  7. Either PRI SERVO PRESS caution - 125 KIAS
  8. Searchlight in fixed position other than stowed - 160 KIAS
  9. Searchlight in transition - 100 KIAS
  10. Dome at or above trail (Cable extended 10 feet, dome approximately 6 feet below aircraft) - 70 KIAS, 45 AOB. Dome below trail - 70 KIAS 15 AOB
  11. Cabin door opening/closing - 60 KIAS.

NOTE
With cabin door open, uncoordinated flight should be avoided.

With MTS installed, failure to maintain balanced flight below 90 KIAS in descents over 1,000 fpm will result in inaccurate and erratic airspeed indications.

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16
Q

External Load and Rescue Hoist Load Maneuvering

Limitations for maneuvering with external loads and rescue hoist loads are presented in Figure 4-4. Rate of descent is limited to _______ for rescue hoist loads.

A

Limitations for maneuvering with external loads and rescue hoist loads are presented in Figure 4-4. Rate of descent is limited to 1,000 fpm for rescue hoist loads.

17
Q

Hovering Limitations

  1. Prolonged rearward flight and downwind hovering should be avoided to prevent accumulation of exhaust fumes in the helicopter and heat damage to the window on an open cabin door.
  2. Hovering turns at a rate in excess of ___ per second.
  3. Dipping sonar operations at altitudes other than __ feet.

CAUTION

Deviation of aircraft hover altitude from __ feet while transducer assembly is entering or exiting the water may result in damage to the dipping sonar equipment due to electrostatic discharge.

  1. Do not tow the transducer in the water above __ KGS with array folded and __ KGS with array unfolded.

CAUTION

Exceeding __ KGS with array folded or __ KGS with array unfolded may cause TA cable separation.

Note

Towing is defined as the cable contacting the funnel. Aircraft ground speed may be greater than __ KGS (folded) or __ KGS (unfolded) provided the cable

is not in contact with the funnel.

A
  1. Prolonged rearward flight and downwind hovering should be avoided to prevent accumulation of exhaust fumes in the helicopter and heat damage to the window on an open cabin door.
  2. Hovering turns at a rate in excess of 30° per second.
  3. Dipping sonar operations at altitudes other than 70 feet.

CAUTION

Deviation of aircraft hover altitude from 70 feet while transducer assembly is entering or exiting the water may result in damage to the dipping sonar equipment due to electrostatic discharge.

  1. Do not tow the transducer in the water above 8 KGS with array folded and 4 KGS with array unfolded.

CAUTION

Exceeding 8 KGS with array folded or 4 KGS with array unfolded may cause TA cable separation.

Note

Towing is defined as the cable contacting the funnel. Aircraft ground speed may be greater than 8 KGS (folded) or 4 KGS (unfolded) provided the cable

is not in contact with the funnel.

18
Q

Angle of Bank (AOB) Limitations

Bank angles shall be limited to the following:

  1. Normal operations — ___.
  2. Operations above 10,000 feet DA — ___.
  3. Either PRI SERVO PRESS caution — ___.
  4. Boost off flight — ___.
A

Bank angles shall be limited to the following:

  1. Normal operations — 45°.
  2. Operations above 10,000 feet DA — 30°.
  3. Either PRI SERVO PRESS caution — 30°.
  4. Boost off flight — 30°.
19
Q

Rotor engagement and disengagement limitations

Maximum wind velocity for rotor engagement or disengagement is _______ from any direction.

A

Maximum wind velocity for rotor engagement or disengagement is 45 knots from any direction.

20
Q

Rotor brake operating limitations

Maximum rotor speed for rotor brake application is __ percent Nr. Routine rotor stops shall be made between __ and __ percent Nr. Routine rotor brake stops should be limited to ___ psi to extend service life.

A

Maximum rotor speed for rotor brake application is 76 percent Nr. Routine rotor stops shall be made between 30 and 50 percent Nr. Routine rotor brake stops should be limited to 180 psi to extend service life.

21
Q

Landing Limitations

The following landing limitations apply:

  1. Maximum rate of descent for level terrain shall not exceed ___ fpm for gross weight less than ______ pounds and ___ fpm for gross weight above ______ pounds.
  2. Maximum rate of descent for sloped terrain shall not exceed ___ fpm.
  3. Maximum touchdown speed shall not exceed __ KGS with tailwheel locked and __ KGS with tailwheel unlocked.
  4. Maximum ground taxi speed is __ KGS. If the shimmy damper is not installed or inoperative, maximum ground taxi speed is __ KGS.

Slope Landing limitations:

a. __ nose-up slope.
b. __ cross-slope.
c. __ nose-down slope.

NOTE

A low-frequency oscillation may occur when landing nose-down on a slope with the cyclic near the aft stop.

  1. Downwind landings should be _______.
A

The following landing limitations apply:

  1. Maximum rate of descent for level terrain shall not exceed 720 fpm for gross weight less than 19,500 pounds and 480 fpm for gross weight above 19,500 pounds.
  2. Maximum rate of descent for sloped terrain shall not exceed 360 fpm.
  3. Maximum touchdown speed shall not exceed 75 KGS with tailwheel locked and 20 KGS with tailwheel unlocked.
  4. Maximum ground taxi speed is 40 KGS. If the shimmy damper is not installed or inoperative, maximum ground taxi speed is 20 KGS.

Slope Landing limitations:

a. 9o nose-up slope.
b. 12o cross-slope.
c. 6o nose-down slope.

NOTE

A low-frequency oscillation may occur when landing nose-down on a slope with the cyclic near the aft stop.

  1. Downwind landings should be avoided
22
Q

During prolonged ground operation of the backup pump with the rotor system static, the backup pump is limited to the operating times shown in Figure 4-6 to prevent hydraulic fluid overheating.

A

OAT - Operating time (Minutes) - Cool down time (Minutes)

33 to 38oC - 24 - 72

39 to 60oC - 16 - 48

23
Q
  1. With engine and rotor operating
  2. With engine and rotor not operating
A
  1. With ambient temperature of 43oC and above - 30 minutes
  2. May be operated continuously up to an ambient temperature of 51oC.

MH-60R RDAF (5 decks)

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