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MH60S > LIMITS > Flashcards

LIMITS Flashcards

1
Q

Minimum Planned Fuel on Landing

A

Minimum planned fuel on landing shall be no less than 225 pounds (approximately 20 minutes) of fuel per main
tank. With fuel less than 300 pounds per main tank, maintain balanced flight at Angles Of Bank (AOBs) greater
than 30°.

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2
Q

Turbine Gas
Temperature (TGT)

A

0 to 810 °C Continuous Green
810 to 851 °C 30 minutes Yellow
851 to 878 °C 10 minutes Red
878 to 903 °C 2.5 Minutes Red
903 to 949 °C 12 seconds Red
949 °C Maximum Red

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3
Q

Power Turbine Speed
(Np)

A

<96% Avoid Red
96 to 105% Continuous Green (Yellow above
101%)
105 to 117% 20 seconds Yellow
117 to 120% 12 seconds Yellow
120% Maximum Red
(C)
During engagement, extended operations in the 20 to 40% and 60 to 75% ranges may cause engine damage.

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4
Q

Main Rotor Speed (Nr)

A

<96% Avoid Red
96 to 101% Continuous Green
101 to 120% Precautionary Yellow
120% Maximum Red
123% Maximum for FCF only Red
127% Overspeed Latch Red

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5
Q

Dual-Engine Torque
(TRQ) <80 KIAS

A

0 to 120% Continuous Green
120 to 144% 10 seconds Yellow
144% Maximum Red

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6
Q

Dual-Engine Torque
(TRQ) >80 KIAS

A

0 to 106% Continuous Green
106 to 127% 10 seconds Yellow
127% Maximum Red
(N)
Dual Engine Torque Limits apply when both engines are above 65% torque.

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7
Q

Single-Engine Torque
(TRQ)

A

0 to 135% Continuous Green
135 to 144% 10 seconds Red
144% Maximum Red

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8
Q

Gas Generator Speed
(Ng)

A

0 to 102.2% Continuous Green
>102.2 to 106% 2.5 minutes Yellow
>106 to 107% 12 seconds Red
107% Maximum Red

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9
Q

Transmission
Temperature (XMSN T)

A

-50 to 105 °C Continuous Green
105 to 120 °C Precautionary Yellow
120 °C Maximum Red

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10
Q

Transmission Pressure
(XMSN P)

A

20 psi Minimum Red
20 to 30 psi Idle and transient Yellow
30 to 65 psi (45 to 60 psi
in level flight) Continuous Green
65 to 130 psi Precautionary Yellow
130 psi Maximum Red

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11
Q

Engine Oil Temperature
(ENG OIL T)

A

-50 to 135 °C Continuous Green
135 to 150 °C 30 minutes Yellow
150 °C Maximum Red

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12
Q

Engine Oil Pressure
(ENG OIL P)

A

22 psi Minimum Red
22 to 26 psi Precautionary Yellow
26 to 100 psi Continuous Green
100 to 120 psi Precautionary Yellow
120 psi Maximum Red

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13
Q

Engine Start

A

<16 °C
First Cycle 60 Seconds
Second Cycle 60 Seconds
Third Cycle 60 Seconds
Fourth Cycle 30 Minutes

16 to 52 °C
First Cycle 60 Seconds
Second Cycle 30 Minutes

NOTES:
1. A start cycle is defined as starter initiation, acceleration in Ng, and starter dropout/disengagement.
2. Times for motoring are cumulative within a 5-minute period.

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14
Q

Transmission Oil Temperature Limitations

A

During any operating condition, no maintenance action is required if main transmission oil temperature is in the precautionary range continuously for 5 minutes or less. Prolonged hovering in hot weather, 86 ⁰F (30 ⁰C), may cause main transmission oil temperature to rise into the precautionary range. Operation in the precautionary range for less than 30 minutes during any one flight under this condition is acceptable and no maintenance action is required.

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15
Q

Transmission Oil Pressure Limitations

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 of 45 to 60 psi, but within the normal limits of 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 (autorotations, downwind hovering, rearward flight, slope-up landings, etc.) transmission oil pressure fluctuations (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).

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16
Q

Rotor Engagement and Disengagement Limitations

A

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

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17
Q

Maximum Forward Airspeed (Vne)

A

180 KIAS

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18
Q

Autorotation Airspeed

A

100 KIAS

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19
Q

Sideward/rearward flight Airspeeds

A

45 knots (35 knots with external load)

20
Q

SAS 1 and SAS 2 inoperative in IMC Airspeed

A

125 KIAS

21
Q

SAS/ BOOST OFF Airspeed

A

140 KIAS

22
Q

Either PRI SERVO PRESS caution Airspeed

A

125 KIAS

23
Q

Cabin Doors Opening/ Closing Airspeed

A

100 KIAS

24
Q

Cabin Doors Open Airspeed

A

120 KIAS

25
Q

Gunner Windows Opening/ Closing

A

170 KIAS

26
Q

Landing Light in Transition Airspeed

A

130 KIAS

26
Q

Searchlight in Transition Airspeed

A

100 KIAS

27
Q

Aircraft gross weight >22,000 lbs with external load airspeed

A

120 KIAS

28
Q

Cockpit doors removed and cabin doors closed or removed Airspeed

A

150 KIAS. Sideslip limit for flight in this
configuration is ±1/2 ball width.

29
Q

Hovering Limitations

A
  1. Prolonged rearward flight and downwind hovering should be avoided to prevent accumulation of exhaust
    fumes in the helicopter and heat damage to windows on open cabin doors.
  2. Hovering turns at a rate in excess of 30° per second.
30
Q

Bank angles shall be limited to the following:

A
  1. Normal operations — 45°.
  2. Operations above 10,000 feet DA — 30°.
  3. Either PRI SERVO PRESS caution — 30°.
  4. SAS/BOOST OFF flight — 30°.
31
Q

Maximum operating density altitude

A

13,000 feet.

32
Q

Prohibited Maneuvers

A
  1. Aerobatic flight.
  2. Practice full-autorotation landings.
  3. Intentional approaches into or inducement of retreating blade stall.
33
Q

Rotor Brake Operating Limitations

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.

34
Q

Blade, Pylon, and Stabilator Fold and Spread Limitations

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.

35
Q

Landing Limitations

A
  1. Maximum rate of descent for level terrain shall not exceed 540 fpm.
  2. Maximum rate of descent for sloped terrain shall not exceed 360 fpm.
  3. Maximum touchdown and takeoff speed shall not exceed 60 KGS with tailwheel locked and 20 KGS with tailwheel unlocked.
  4. Maximum braking speed is 35 KGS.
  5. Slope landing limitations:
    a. 9° nose-up slope.
    b. 12° cross-slope.
    c. 6° nose-down slope.
    (N)
    A low-frequency oscillation may occur when landing nose-down on a slope
    with the cyclic near the aft stop.
  6. Downwind landings should be avoided.
36
Q

Aircraft Operating Gross Weight Limitations

A

The maximum operating gross weight is 23,500 pounds. The maximum launch and recovery gross weight for aviation ships and amphibious assault aviation ships is 23,500 pounds. The maximum launch and recovery gross weight for air-capable ships is 22,500 pounds.

37
Q

Internal Load Weight Limitations

A

The maximum total internal weight in the cabin area aft of the cockpit (to include aircrew, passengers, and/or cargo) is 5,500 pounds. The maximum total weight for palletized cargo is 4,733 pounds. The maximum weight for a single pallet of cargo is 3,000 pounds. Refer to Weight and Balance Data Handbook, NAVAIR 01-1B-50, to determine cargo floor loading limitations in the cabin area.

38
Q

External Load Weight Limitations

A

The maximum external load when employing the cargo hook is 6,000 pounds. The maximum external load when employing the rescue hoist is 600 pounds.

39
Q

Minimum Aircraft Equipment for IMC Flight

A
  1. Both FDs.
  2. Both MDs.
  3. Both EGIs. Valid attitude data shall be provided by both and valid heading data by at least one.
  4. One ADC, providing pitot-static information on both FDs.
  5. Slip/skid indicators on both FDs.
  6. Standby magnetic compass with current calibration card.
  7. Radar altimeter, providing information on both FDs.
  8. Primary (MC) and backup (BC) mission computers.
  9. Digital clock on instrument panel or timer on FD.
  10. Pitot heat.
  11. All backup flight instruments (airspeed indicator, barometric altimeter, and attitude gyro).
  12. Instrument, navigation, and cockpit lighting.
  13. Communication equipment.
    a. One V/UHF radio.
    b. ICS, all crewmembers.
    c. Transponder, as required by Air traffic control (ATC).
  14. TACAN or VOR.
  15. SAS 2, trim, and autopilot.
  16. LAWS (over water).
  17. Altitude hold (over water).
40
Q

Minimum Aircraft Equipment for Night Flight Over Water

A
  1. LAWS.
  2. Altitude hold.
41
Q

Minimum Aircraft Equipment for Flights Into Forecast or Known Icing Conditions

A

Helicopters equipped with operable anti-ice and blade de-ice equipment are permitted flight into forecast or known trace or light icing conditions. All installed anti-ice/de-ice equipment (windshield, engine, rotor) shall be operational prior to flight.

Helicopters not equipped with operable blade de-ice equipment are prohibited from flight into forecast or known icing conditions (ambient temperatures of 5 °C or below in visible moisture). Refer to Chapter 14 for specific information on flight in icing conditions.

The following icing limitations apply:
1. Flight into known icing conditions without de-ice equipment is prohibited.
2. Flight into forecasted or known moderate or severe icing conditions is prohibited.

42
Q

Temperature Limitations

A

Operations at temperatures below -40 °C (-40 °F) or above 60 °C (140 °F) are prohibited.

43
Q

APU Operating Limitations

A

Rotors not engaged: APU may be operated continuously up to an ambient temperature limit of 51 °C.
Rotors engaged: APU may be operated continuously up to an ambient temperature limit of 43 °C. If operating the APU between 43° and 60 °C, operation is limited to 30 minutes.
(C)
Exceeding time or ambient temperature limits may cause APU overheating,
performance degradation, and a reduction in APU reliability.

44
Q

Hydraulic Pump Limitations

A

33 to 38 °C 24min operating 72min cooldown
39 to 60 °C 16min operating 48min cooldown

MH60S (11 decks)

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