Limits Chapter 4 Flashcards

1
Q

Exceeding Operating Limitations

A

Anytime an operational limit is exceeded, an appropriate entry shall be made on a MAF. The entry shall state what limits were exceeded and include range, duration and any additional data that would aid maintenance personnel

The flight displays digital readout will display “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 Limits

A

The engines are limited by Ng, Np, TGT, oil px, and oil temp. Specified temp limits ensure that the engines are operated at internal temps that will not shorten the service life expectancy of engine components

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3
Q

Engine Starter Limits

A

Engine starter limits are Figure 4-2. 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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4
Q

Engine Start Limits

A

The single and dual engine start envelopes are figure 4-2.

For crossbreed starts, the receiving engine shall be at or above 24% Ng prior to advancing PCL to idle

Engine starts are prohibited with the main rotors blades or tail pylon folded

The start TGT limit is 851 C until engine idle speed is attained

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5
Q

Engine Idle limits with Gust lock engaged

A

Engine operation with gust lock engaged is prohibited

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6
Q

TGT limits

A
0-810 continuous green
810-851 30 mins yellow
851-878 2.5 mins (10 mins max power and limiter checks only) red
878-903 2.5 mins red
903-949 12 seconds red
949 max red
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7
Q

Np Limits

A
<96% avoid red
96%-105% cont green (yellow above 101%)
105%-117% 20 seconds yellow
117%-120% 12 seconds yellow
120% max red

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

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8
Q

Nr Limits

A
<96% avoid red
96%-101% cont green
101%-120% precautionary yellow
120% max red
>120% 123% max for fcf red
127% overspeed latch red
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9
Q

Dual engine torque <80 KIAS

A

0-120% cont green
120-144% 10 seconds yellow
144% max red

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10
Q

Dual engine torque >80 KIAS

A

0-106% cont green
106-127% 10 seconds yellow
127% max red

Dual engine torque limits apply when both engines are above 65% torque

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11
Q

Single engine Torque

A

0-135% cont green
135-144% 10 seconds yellow
144% max red

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12
Q

Ng Limits

A

0-102.2% cont green
102.2-106% 2.5 mins yellow
106-107% 12 second red
107% max red

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13
Q

Transmission Px

A
20 psi min red
20-30 psi precautionary yellow
30-65 cont green.   45-60 psi in level flight
65-130 precautionary yellow
130 max red
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14
Q

Transmission Temp

A

-50-105 cont green
105-120 precautionary yellow
120 max red

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15
Q

Engine oil Temp

A

-50-135 cont green
135-150 30 mins yellow
150 max red

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16
Q

Engine oil Px

A
22 min red
22-26 precautionary yellow
26-100 cont green
100-120 precautionary yellow
120 max red

22-55 normal idle range

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17
Q

Engine Start limits

Starter engaged/starter disengaged

A
<16 C
First cycle 60 seconds
Second cycle 60 seconds
Third cycle 60 seconds
Fourth cycle 30 mins

16-52 C
First cycle 60 seconds
Second cycle 30 mins

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18
Q
Engine Motor (Ignition Off)
Starter Engaged/Starter Disengaged
A

2 mins 5 mins
2 mins 30 mins

  1. A start cycle is defined as starter initiation, acceleration, dropout
  2. Times for motoring are cumulative within a 5 min period
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19
Q

Min planned fuel on landing

A

Min planned fuel on landing shall be no less than 600 lbs

20
Q

APU limits

A

APU is not meant for routine in flight use. Operation of the APU in flight shall be limited to essential operations only. Acceptable in flight use includes emergency procedures, single engine training, practice auto rations, powering the ECS during extreme temperature operations

21
Q

Transmission Limits

A

The Transmission is limited by Nr, Torque, oil temp, oil px. Operation is governed by whichever limit is reached first.

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

22
Q

Transmission Oil temp limits

A

During an operating condition, no maintenance action is required if main transmission oil temp is in the precautionary range continuously for 5 mins or less

Prolonged Hovering in hot weather, 86 F/30 C may cause main transmission oil temp to rise into the precautionary range. Operation in the precautionary range for less than 30 mins during any one flight under this condition is acceptable and no maintenance action is required

23
Q

Transmission Oil Px Limits

A

During Steady State level pitch attitudes (level flight) transmission px 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 MAF

  1. Steady pressure outside of 45-60 psi but within the normal limits of 30-65
  2. Fluctuations not to exceed 10 psi range, but within the normal limits of 30-65

During transient pitch or steady state nose up attitudes (autos, rearward flight, downwind hovering, slope up landings) transmission oil px fluctuations (momentary fluctuations below 30 psi and transient drops below 20 psi for less than 1 second) are acceptable. Operating with px fluctuations below 30 psi shall be limited to 30 mins

24
Q

No Oil Flow condition

A

During Rotor engagement, a zero oil px 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 min and shall be documented on a MAF

25
Q

Rotor engagement and disengagement limits

A

Max wind velocity for rotor engagement or disengagement is 45 KTS in any direction

26
Q

Airspeed Limits

A
Max Vne - 180KIAS
Max limited by blade stall figure 22-3
Sideward/rearward flight 35 knots
Autorotation 100 KIAS
Boost off 140 KIAS
Either PRI SERVO caution in IMC 125 KIAS
SAS 1 and SAS 2 failed in IMC 125 KIAS
Searchlight in fixed position other than stowed 160 KIAS
Searchlight in transition 100 KIAS
Dome at or above trail 70 KIAS 45 AOB
Dome below trail 70 KIAS 15 AOB
Cabin door opening/closing 60 KIAS

With cabin door open, uncoordinated flight should be avoided
With MTS installed, failure to maintain balanced flight below 90 KIAS and ROD over 1000 fpm will result in inaccurate and erroneous airspeed indications

27
Q

Min Heigh for Safe landing after engine failure

A

Height Velocity diagram 27-7 gives show the combination of speed and wheel height that should be avoided during normal operations to provide for a safe landing if single or dual engine failure should occur. Delay in recognition of single engine failure or excessive maneuvering to reach a suitable landing site reduce the probability of a safe touchdown

28
Q

Hovering Limits

A
  1. Prolonged rearward flight or downwind hovering should be avoided to prevent accumulation of exhaust fumes in the Helo and heat damage to the window of an open cabin door
  2. Hovering turns greater than 30/second
  3. Dipping Sonar operations at altitudes other than 70 ft
    Caution: Deviation of aircraft hover altitudes from 70 ft while TA 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 folded and 4 KGS unfolded
    Caution: Exceeding these KGS may cause TA cable separation
    Note: Towing is defined as cable in contact with the funnel. If not towing, no need to follow these limits
29
Q

AOB limits

A

Bank angles shall be limited to the following

  1. Normal Operations - 45
  2. Operations above 10000ft DA - 30
  3. Boost off - 30
  4. Either PRI SERVO PRESS caution - 30
30
Q

Altitude Limits

A

Max operation DA is 13000 ft

31
Q

Prohibited Maneuvers

A

The following maneuvers are prohibited:

  1. Aerobatic Flight
  2. Practice full autorotation landings
  3. Intentional approaches or inducement of retreating blade stall
32
Q

Rotor Brake Operations

A

Max rotor speed application is 76% Nr
Routine stops shall be made between 30-50% Nr
Routine stops should be limited to 180 psi to extend service life

33
Q

Blade, pylon, and stab fold and spread limits

A

Max wind velocity for blade fold and spread is 45 knots from any direction. Following a complete blade fold and spread cycle, allow a 10 min cool down 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.

Max wind velocity for tail pylon or stab fold/spread evolution is 45 knots from and direction

34
Q

Landing Limits

A

The following land limits apply:
1. Max ROD for level terrain shall not exceed 720 fpm for gross weight below 19500 lbs and 480 fpm for gross weights above 19500 lbs
2. Max ROD for sloped terrain shall not exceed 360 fpm
3. Max touchdown speed shall not exceed 75 KGS with tail wheel locked and 20 KGS with tail wheel unlocked
4. Max ground tax speed is 40 KGS. If the shimmy dampener is not installed or inop, max ground tax speed is 20 KGS
5. Slope landing limts up slope 9, side slope 12, downslope 6
Note: a low frequency oscillation may occur when landing nose down on a slope with cyclic near the aft stop
6. Downwind landings should be avoided

35
Q

Windows

A

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

36
Q

JMPS limits

A

JPMS performance and Weight and balance calculations shall not be used as a substitute for performance calcs found in Part XI of NATOPS, and weight and balance calcs in accordance with NAVAIR 01-1B-50

37
Q

Aircraft operating Gross weight limits

A

max operating gross weight is 23500 lbs
Max launch/recovery gross weight for aviation ships 23500 lbs
Max launch/recovery gross weight for air capable amphibious assault aviation is 22500 lbs

38
Q

Inter load weight limits

A

Max cargo floor loading is 300 lbs/ft^2

39
Q

External load weight limits

A

Cargo hook - 6000lbs

Rescue hook 600 lbs

40
Q

Center of Gravity Limits

A

Longitudinal CG figure 4-5. At max gross weight limits, lateral cg limits are 7.5 inches left and 8 inches right.

41
Q

Min aircraft equipment for night flight over water

A

The following operable equipment is required for night flight over water:

  1. Altitude hold (BAR or RAD)
  2. Low altitude warning system (LAWS)
42
Q

Min aircraft equipment for flights into forecasted or known icing conditions

A

Helos equipped with operable anti ice and blade deice equipment are permitted flight into forecast or known trace or light icing conditions. All installed anti ice and blade deice equipment shall be operational prior to flight. Helos not equipped with operable blade deice equipment are prohibited from flight into forecast or known icing conditions (ambient temps of 5 C or below in visible moisture)

The following icing limits apply:

  1. Flight into known icing conditions without deice equipment is prohibited
  2. Flight into forecast or known moderate or severe icing conditions is prohibited
43
Q

Min Equipment for Pax

A

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

For pax and aircrew seating requirements refer to CNAF 3710 chapter 7

Warning: Gunner belts do not provide impact protection; therefore, use of those belts shall be restricted to only those occurrences when mission accomplishment requires persons to be out of their seats. Such belts shall not be worn when strapped into a seat

44
Q

Temperature Limits

A

Operation at temps below -40 C/F or above 60 C 140 F are prohibited

45
Q

Back up pump limits

A

During prolonged ground operations of the backup pump with the rotor system static, the back up pump is limited to the operating times to prevent hyd fluid overheating

33-38 C 24 mins on 72 mins off
39-60 C 16 mins on 48 mins off

46
Q

APU operating limits

A

To prevent APU overheating:
APU operations at ambient temps of 43 C and above with engine and rotor operating is limited to 30 mins
With engine and rotor static and ambient temps of 51 C or below, continuous operations