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Flashcards in MH-60R LIMITS Deck (41)
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1

EXCEEDING OPERATING LIMITATIONS

The flight display’s digital readout will desplay ”XXX” in red when a TGT or torque limit is exceeded. If a limit is exceeded to the extent that a red ”XXX” is indicated, the crew shall land as soon as practicable.

2

ENGINE LIMITATIONS

A start cycle is defined as:

 A start cycle is defined as starter initiation, acceleration of the output drive, and starter dropout. A __-second delay between start attempts is required any time a start is aborted, except during emergencies.

A start cycle is defined as starter initiation, acceleration of the output drive, and starter dropout. A 60-second delay between start attempts is required any time a start is aborted, except during emergencies.

3

ENGINE START LIMITATIONS

The Single– and dual-engine start envelopes are presented in figure 4-3. For crossbleed starts, the receiving engine shall be at or above __ percent Ng prior to advancing PCL to IDLE. Engine start with the main rotor blades or tail rotor pylon folded is prohibited. The start TGT limit is ___ C until idle speed is attained.

The Single– and dual-engine start envelopes are presented in figure 4-3. For crossbleed starts, the receiving engine shall be at or above 24 percent Ng prior to advancing PCL to IDLE. Engine start with the main rotor blades or tail rotor pylon folded is prohibited. The start TGT limit is 851 C until idle speed is attained.

4

ENGINE IDLE LIMITATIONS WITH GUST LOCK ENGAGED

Engine operation with gust lock engaged is prohibited.

5

TURBINE GAS TEMPERATUR (TGT) LIMITS

  1. 0 - 810 Continuous   Green
  2. 810 - 851 30 minutes  Yellow
  3. 851 - 878 2.5 minutes (10 minutes for Max Power or limiter checks only) Red
  4. 878 - 903 2.5 minutes   Red
  5. 903 - 949 12 seconds   Red
  6. 949 Maximum   Red

6

Power Turbine Speed (Np) 

  1. <96%   Avoid   Red
  2. 96-105%    Continuous   Green (Yellow above 101%)
  3. 105-117% 20 seconds  Yellow
  4. 117-120% 12 seconds   Yellow
  5. 120% Maximum   Red

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

7

Main Rotor Speed (Nr)

  1. <96 %   Avoid   Red
  2. 96 - 101% Continuous Green
  3. 101 - 120% Precautionary Yellow
  4. 120% Maximum Red
  5. >120%   123% Maximum for FCF only  Red
  6. 127%  Overspeed latch   Red

8

Dual-Engine Torque (TRQ) <80 KIAS

  1. 0 - 120 % Continuous Green
  2. 120 - 144 % 10 seconds Yellow
  3. 144% Maximum Red

9

Dual-Engine Torque (TRQ) >80 KIAS

  1. 0 - 106% Continuous Green
  2. 106 - 127 % 10 seconds Yellow
  3. 127% Maximum Red

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

10

Single-Engine Torque (TRQ) 

  1. 0 - 135% Continuous Green
  2. 135 - 144% 10 seconds Red
  3. 144% Maximum Red

11

Gas generator Speed (Ng)

 

  1. 0 - 102.2% Continuous Green
  2. 102.2 - 106% 2.5 minutes Yellow
  3. 106 - 107 % 12 seconds Red
  4. 107% Maximum Red

12

Transmission Temperature (XMSN T)

  1.  -50 - 105  Continuous Green
  2. 105 - 120 Precautionary Yellow
  3. 120 Maximum Red

13

Transmission Pressure (XMSN P)

  1. 20 psi  Minimum Red
  2. 20-30 psi Idle and transient Yellow
  3. 30 - 65 (45 to 60 psi in level flight) Continuous  Green
  4. 65 - 130 Precautionary Yellow
  5. 130 Maximum Red

14

Engine Oil Temperature (Eng Oil T)

  1. -50 - 135 Continuous Green
  2. 135 - 150 30 minutes Yellow
  3. 150 Maximum Red

15

Engine oil pressure (Eng Oil P)

  1. 22 psi Minimum Red
  2. 22 - 26 psi Precautionary Yellow
  3. 26 - 100 psi Continuous Green
  4. 100 - 120 psi Precautionary Yellow
  5. 120 Maximum Red

NOTE
Normal idle range is 22 to 55 psi

16

Engine Start with ignition on 

  • <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    
     

17

Engine Start Ignition Off

Any temperature 

  1. Starter engaged 2 Minutes
  2. Starter disengaged 5 Minutes
  3. Starter Engaged 2 Minutes
  4. Stater Disengaged 30 minutes

18

Minimum planned fuel on Landing

Minimum planned fuel on landing shall be no less than ___ pounds

Minimum planned fuel on landing shall be no less than 600 pounds

19

APU LIMITATIONS

The APU is not intented for routine in-flight use. Operation of the APU in flight shall be limited to the essential operations only. Acceptable in flight use includes ________________, ____________, ____________, and _____________________.

The APU is not intented for routine in-flight use. Operation of the APU in flight shall be limited to the essential operations only. Acceptable in flight use includes emergency procedures, single-engine training, practice autorotations, and powering the ECS during extreme temperatur operations.

20

Transmission Limitations (text)

The transmission is limited by Nr, torque, oil pressure and oil temperatur. Operation is governed by whichever limit is reached first.

NOTE

Engine torques over ____ are displayed as red ”XXX”

The transmission is limited by Nr, torque, oil pressure and oil temperatur. Operation is governed by whichever limit is reached first.

NOTE

Engine torques over 150% are displayed as red ”XXX”

 

21

Transmission Oil Temperature (text)

During any operating condition, no maintenance action is required if main transmission oil temperatur is in the precautionary range contionously for __ minutes or less.
Prolonged hovering in hot weather ___ (___), may cause main transmission oil temperatur to rise into the precautionary range. Operation in the precautionary range for less than __ minutes during any one flight under this condtion is acceptable an no maintenance action is required.

During any operating condition, no maintenance action is required if main transmission oil temperatur is in the precautionary range contionously for 5 minutes or less.
Prolonged hovering in hot weather 86 F (30 C), may cause main transmission oil temperatur to rise into the precautionary range. Operation in the precautionary range for less than 30 minutes during any one flight under this condtion is acceptable an no maintenance action is required.

22

Transmission Oil Pressure limitations (text)

During steady-state level pitch attitudes (i.e., level flight), the transmission oil pressure should be __ to __ psi. The following conditions do not constitute an immediate emergency situation, but may be indicative of a degraded lubrication system. Any discrepancy shall be documented on a maintenance action form (MAF).
1. Steady pressure outside __ to __ psi, but within normal __ to __ psi.
2. Fluctuations not to exceed a range of __ psi, within the normal limits of __ to __ psi.
During transient pitch or steady-state nose-high pitch attitudes (autorotation, downwind hovering, rearward flight, slope landing, etc.) transmission oil pressure fluctuation (including momentary fluctuations below __ psi and transient drops below __ psi for up to one second) are acceptable. Operating with pressure fluctuations below __ psi shall be limited to __ minutes.
During rotor engagement, a zero oil pressure indication may indicate a no-oil-flow condition through the oil lubrication system. Operating with a no oil pressure indication shall be limited to less than __ minute and shall be documented on a Maintenance Action Form (MAF)

During steady-state level pitch attitudes (i.e., level flight), the transmission oil pressure should be 45 to 60 psi. The following conditions do not constitute an immediate emergency situation, but may be indicative of a degraded lubrication system. Any discrepancy shall be documented on a maintenance action form (MAF).
1. Steady pressure outside 45 to 60 psi, but within normal 30 to 65 psi.
2. Fluctuations not to exceed a range of 10 psi, within the normal limits of 30 to 65 psi.
During transient pitch or steady-state nose-high pitch attitudes (autorotation, downwind hovering, rearward flight, slope landing, etc.) transmission oil pressure fluctuation (including momentary fluctuations below 30 psi and transient drops below 20 psi for up to one second) are acceptable. Operating with pressure fluctuations below 30 psi shall be limited to 30 minutes.
During rotor engagement, a zero oil pressure indication may indicate a no-oil-flow condition through the oil lubrication system. Operating with a no oil pressure indication shall be limited to less than 1 minute and shall be documented on a Maintenance Action Form (MAF)

 

23

Rotor engagement and disengagement limitations 

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

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

24

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. 

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. 

 

25

Minimum Height for Safe Landing After Engine Failure

The height-velocity diagrams (Figure 27-7) show the combinations of speed and wheel height that should be avoided during normal operations to provide for safe landing if single- or dual-engine failure should occur. Delay in recognition of the single-engine failure or excessive maneuvering to reach a suitable landing area reduce the probability of a safe touchdown.

26

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.

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.

27

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.

4. 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.

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.

4. 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.

28

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 — ___.

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°.

29

Prohibited Maneuvers

1. Aerobatic flight.

2. Practice full-autorotation landings.

3. Intentional approaches into or inducement of retreating blade stall.

30

Maximum operating density altitude

13.000 ft