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MH-60R RDAF > MH-60R LIMITS > Flashcards

MH-60R LIMITS Flashcards

1
Q

EXCEEDING OPERATING LIMITATIONS

A

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.

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2
Q

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

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.

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3
Q

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.

A

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.

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4
Q

ENGINE IDLE LIMITATIONS WITH GUST LOCK ENGAGED

A

Engine operation with gust lock engaged is prohibited.

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5
Q

TURBINE GAS TEMPERATUR (TGT) LIMITS

A
  1. 0 - 810 Continuous Green
  2. 810 - 851 30 minutes Yellow
  3. 851 - 878 2.5 10 minutes Red
  4. 878 - 903 2.5 minutes Red
  5. 903 - 949 12 seconds Red
  6. 949 Maximum Red
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6
Q

Power Turbine Speed (Np)

A
  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.

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7
Q

Main Rotor Speed (Nr)

A
  1. <96 % | Avoid | Red
  2. 96 - 101% | Continuous | Green
  3. 101 - 120% | Precautionary | Yellow
  4. 120% | Maximum| Red
  5. 123% | Maximum for FCF only | Red
  6. 127% | Overspeed latch | Red
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8
Q

Dual-Engine Torque (TRQ) <80 KIAS

A
  1. 0 - 120 % | Continuous | Green
  2. 120 - 144 % | 10 seconds | Yellow
  3. 144% | Maximum | Red
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9
Q

Dual-Engine Torque (TRQ) >80 KIAS

A
  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

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10
Q

Single-Engine Torque (TRQ)

A
  1. 0 - 135% | Continuous | Green
  2. 135 - 144% | 10 seconds | Red
  3. 144% | Maximum| Red
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11
Q

Gas generator Speed (Ng)

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

Transmission Temperature (XMSN T)

A
  1. -50 - 105 | Continuous | Green
  2. 105 - 120 | Precautionary | Yellow
  3. 120 | Maximum | Red
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13
Q

Transmission Pressure (XMSN P)

A
  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
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14
Q

Engine Oil Temperature (Eng Oil T)

A
  1. -50 - 135 | Continuous | Green
  2. 135 - 150 | 30 minutes | Yellow
  3. 150 | Maximum | Red
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15
Q

Engine oil pressure (Eng Oil P)

A
  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
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16
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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17
Q

Engine Start Ignition OFF

A

Any temperature

  1. Starter engaged - 2 Minutes
  2. Starter disengaged - 5 Minutes
  3. Starter Engaged - 2 Minutes
  4. Starter Disengaged - 30 minutes
18
Q

Minimum planned fuel on Landing

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

A

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

19
Q

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 _____________________.

A

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
Q

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”

A

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
Q

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.

A

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
Q

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)

A

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
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.

24
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. TA 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. TA 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
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.

26
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 TA 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 TA 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.

27
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°.
28
Q

Prohibited Maneuvers

A
  1. Aerobatic flight.
  2. Practice full-autorotation landings.
  3. Intentional approaches into or inducement of retreating blade stall.
29
Q

Maximum operating density altitude

30
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.

31
Q

Blade, Pylon, and Stabilator Fold and Spread Limitations

Maximum wind velocity for blade fold and spread is __ knots from any direction. Following a complete blade fold and spread cycle, allow a __-______ cooling period before commencing another blade fold and spread evolution. A complete blade fold and spread cycle is defined as a full spread evolution followed immediately by a full fold evolution or vice versa.

Maximum wind velocity for tail pylon or stabilator fold/spread operations is __ knots from any direction.

A

Maximum wind velocity for blade fold and spread is 45 knots from any direction. Following a complete blade fold and spread cycle, allow a 10-minute cooling period before commencing another blade fold and spread evolution. A complete blade fold and spread cycle is defined as a full spread evolution followed immediately by a full fold evolution or vice versa.

Maximum wind velocity for tail pylon or stabilator fold/spread operations is 45 knots from any direction.

32
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
33
Q

Windows

Windows shall not be ________ or _________ in flight, except during actual aircraft emergencies.

A

Windows shall not be installed or removed in flight, except during actual aircraft emergencies.

34
Q

Joint Mission Planning System Limitations

Joint Mission Planning System (JMPS) performance and weight and balance calculations shall ___________________________ for preflight performance calculations found in part XI of NATOPS, and weight and balance calculations in accordance with NAVAIR 01-1B-50.

A

Joint Mission Planning System (JMPS) performance and weight and balance calculations shall not be used as a substitute for preflight performance calculations found in part XI of NATOPS, and weight and balance calculations in accordance with NAVAIR 01-1B-50.

35
Q

Aircraft operating gross weight limitations

  1. Maximum operating gross weight
  2. Maximum launch & recovery gross weight for aviation ships
  3. Maximum launch & recovery gross weight for air-capable and amphibious assault aviation ships
A
  1. 23.500 lbs
  2. 23.500 lbs
  3. 22.500 lbs
36
Q

Maximum cargo floor loading

A

300 lbs/sqft

Refer to Weight and Balance Data Handbook, NAVAIR 01-1B-50, to determine cargo floor loading limitations in the cabin area.

37
Q
  1. Maximum weight that may be suspended from the cargo hook
  2. Maximum weight that may be suspended from the rescue hoist
A
  1. 6.000 lbs
  2. 600 lbs
38
Q

Temperature limitations

Operational temperatures below _____ or above _____ are prohibited.

A

Operational temperatures below -40o C (-40oF) or above 60o C (140o F) are prohibited.

39
Q

Backup Hydraulic Pump Limitations

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

40
Q

APU OPERATING LIMITATIONS

  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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