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MH-60R HAC Study > Limits > Flashcards

Limits Flashcards

1
Q

Engine Start Limitations

A
  1. The single- and dual-engine start envelopes are presented in Figure 4.1-3. For crossbleed starts, the receiving engine shall be at or above 24 percent Ng prior to advancing PCL to IDLE.
  2. Engine start with the main rotor blades or tail rotor pylon folded is prohibited.
  3. The start TGT limit is 851 °C until idle speed is attained.
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2
Q

Turbine Gas
Temperature (TGT)

A

0-810 °C Continuous Green MCP
810-851 °C 30 minutes Yellow IRP
851-878 °C 10 minutes Red MRP
878-903 °C 2.5 minutes Red CRP
903-949 °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
CAUTION
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
NOTE
Dual engine torque limits apply when both engines are above 65% torque.

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7
Q

Single-Engine Torque

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 Continuous Green
(45 to 60 psi in level flight)
65 to 130 psi Precautionary Yellow
130 psi Maximum Red

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11
Q

Engine Oil Temperature

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

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14
Q

Engine Motor

A

(Any Temperature)
2 Minutes Engaged
5 Minutes Disengaged
2 Minutes Engaged
30 Minutes Disengaged

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15
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 °F (30 °C), 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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16
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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17
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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18
Q

Maximum (Vne)

A

180 KIAS

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19
Q

Sideward/rearward flight

A

35 KNOTS

20
Q

Autorotation

A

100 KIAS

21
Q

BOOST OFF

A

140 KIAS

22
Q

SAS 1 AND SAS 2 INOP IN IMC

A

125 KIAS

23
Q

EITHER PR SERVO PRESS CAUTION

A

125 KIAS

24
Q

SEARCHLIGHT IN POSTION OTHER THAN STOW

A

160 KIAS

25
Q

SEARCHLIGHT IN TRANSITION

A

100 KIAS

26
Q

DOME AT OR ABOVE TRAIL

A

70 KIAS, 45° AOB.

27
Q

DOME BELOW TRAIL

A

70 KIAS, 15° AOB.

28
Q

Cabin door opening/closing

A

60 KIAS

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 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.
  4. Do not tow the transducer in the water above 8 KGS with array folded and 4 KGS with array unfolded.
30
Q

Angle of Bank (AOB) Limitations

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

Altitude Limitation

A

Maximum operating density altitude is 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 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. Slope landing limitations:
    a. 9° nose-up slope.
    b. 12° cross-slope.
    c. 6° nose-down slope.
  4. 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 cargo floor loading is 300 pounds per square foot. 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 weight that may be suspended from the cargo hook is 6,000 pounds. The maximum weight that may
be suspended from the rescue hoist is 600 pounds.

39
Q

Minimum Aircraft Equipment for Night Flight Over Water

A

The following operable equipment is required for night flight over water:
1. LAWS.
2. Altitude hold (RAD ALT or BAR ALT).

40
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.

41
Q

Minimum Equipment for Passengers

A

Except in emergency situations, helicopter emergency egress lighting system (ADHEELS and IHEELS) shall be
operational for all overwater flights requiring passengers/non-aircrew in the cabin

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 Temperature

A

To prevent APU overheating, APU operation at ambient temperature of 43 °C and above with engine and rotor
operating is limited to 30 minutes. With engine and rotor not operating, the APU may be operated continuously up
to an ambient temperature of 51 °C.

44
Q

Backup Hydraulic Pump Limitations

A

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 4.3-1 to prevent hydraulic fluid overheating.
33 to 38 °C 24 ON 72 OFF
39 to 60 °C 16 ON 48 OFF

45
Q

Maximum Touchdown Speed

A

75 KGS locked
20 KGS unlocked

46
Q

Maximum Ground taxi speed

A

40 KGS
20 KGS shimmy damper inop

MH-60R HAC Study (8 decks)

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