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Limits Flashcards

1
Q

Engine Start Limits

A
  1. Crossbleed: the rx engine shall be at or above 24% Ng prior to advancing the PCL to IDLE.
  2. Start with blades or pylon folded is prohibited.
  3. Start TGT limi is 851 C until idle speed is attained.

Engine operation with gust lock engaged is prohibited.

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2
Q

TGT

A 
0-810 (G) Continuous
810-851 (Y) 30 min
851-878 (R) 10 min (as reqd for max power/limiter checks only)
878-903 (R) 2.5 min
903-949 (R) 12 secs
949 MAX
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3
Q

Np

A 
< 96 (R) AVOID
96-105 (G [Y>101]) Continuous
105-117 (Y) 20 seconds
117-120 (Y) 12 seconds
120 (R) MAX

During engagement, prolonged operation in 20-40 and 60-75 can cause engine damage.

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4
Q

Nr

A 
< 96 (R) AVOID
96-101 (G) Continuous
101-120 (Y) Precautionary
120 (R) MAX
>120 (R) 123 MAX FCF
127 Overspeed Latch
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5
Q

DET <80 KIAS

A

0-120 (G) Continuous
120-144 (Y) 10 seconds
144 (R) MAX

Dual engine torque limits apply anytime both engines are above 65% torque.

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6
Q

DET >80 KIAS

A

0-106 (G) Continuous
106-127 (Y) 10 seconds
127 (R) MAX

Dual engine torque limits apply anytime both engines are above 65% torque.

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7
Q

SET

A

0-135 (G) Continuous
135-144 (Y) 10 seconds
144 (R) MAX

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8
Q

Ng

A

0-102.2 Continuous
>102.2-106 2.5 min
>106-107 12 seconds
107 MAX

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9
Q

XMSN TEMP

A

-50-105 Continuous
105-120 Precautionary
120 MAX

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10
Q

XMSN PX (just numbers for now young one)

A 
20 minimum
20-30 idle/transient
30-65 continuous (45-60 level flight)
65-130 precautionary
130 MAX
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11
Q

Transmission Oil Temperature Limitations

A
  1. 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.
  2. Prolonged hovering in hot weather (30 degrees C) and high gross weight may cause temps to rise in the yellow precautionary range. Operation in the precautionary range for less than 30 minutes during any one flight under these conditions is acceptable.
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12
Q

Transmission Oil Pressure Limitations

A

During steady state level pitch attitudes, the transmission oil PX should be 45-60 psi. The following do not constitute an immediate emergency but may be indicative of a degraded lubrication system. Shall be documented in a MAF.

  1. Steady PX outside of 45-60 but within 30-65.
  2. Fluctuations not to exceed a range of 10, but within 30-65.

During transient pitch or steady state nose high pitch, transmission oil PX fluctuations (momentary below 30 and transient below 20 for less than 1 second) are acceptable. Operating with PX fluctuations below 30 psi shall be limited to 30 minutes.

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13
Q

Main Transmission Lubrication System Cautions and Advisories

A 
OIL HOT (Y): oil temp sensor (>117) at manifold input
OIL HOT (W): oil temp >105 AND caution NOT active

PRESS LOW (Y): oil px sensor (<14) in No. 1 ACC module furthest from pumps
PRESS LOW (W): oil px < 30, Nr < 25, AND oil caution NOT active.

PRESS HI (Y): oil px > 130 (red tape)
PRESS HI (W): oil px between 65 and 130 psi (yellow tape)
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14
Q

Transmission Secondary Indication

A

The first indication of a loss of lubrication may be a decrease in oil px. Low oil pressure can be confirmed by the appearance of the MAIN XMSN PRESS LOW caution since it is triggered by a discrete pressure sensor, and should be considered a secondary indication.

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15
Q

Engine Oil TEMP

A

-50-135 Continuous
135-150 30 minutes
150 MAX

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16
Q

Engine Oil PX

A 
22 minimum
22-26 precautionary
26-100 continuous
100-120 precautionary
120 MAX

22-55 is normal IDLE range

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17
Q

Starter Limits

A

Engaged(seconds)/Disengaged
STARTING < 16 C: 1/60 2/60 3/60 4/30 minutes
STARTING 16-52C: 1/60 2/30 minutes

MOTOR: 2 min / 5 min :: 2 min 30 min

  1. A start cycle is defined as starter initiation, acceleration, and dropout.
  2. Times for motoring are cumulative within a 5 minute window.
  3. A 60 second delay between start attempts when a start is aborted.
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18
Q

APU Limits

A
  1. Not intended for routine in-flight use; shall be limited to essential operations only (EPs, single-engine training, practice autos, and powering ECS during extreme temps).
  2. To prevent overheating:
    With engine and rotor operating and GREATER THAN OR EQUAL to 43 C limited to 30 minutes; With engine and rotor NOT operating and LESS THAN OR EQUAL to 51, there is not limit (continuous)
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19
Q

Minimum Planned Fuel On Landing

A

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

20
Q

Max Airspeed (Vne)

21
Q

Sideward/Rearward Airspeed

22
Q

Auto Airspeed

23
Q

Boost Off Airspeed

24
Q

Two SAS INOP in IMC Airspeed

25
Either PRI SERVO PRESS Caution
125 KIAS
26
Searchlight in fixed position other than stowed
160 KIAS
27
Searchlight in transition
100 KIAS
28
Cabin Door Opening/Closing
60 KIAS
29
Airspeed Dome Limits
At or above trail (10 feet of POCL, Dome 6 feet below the aircraft): 70 KIAS and 45 degrees AOB. Below trail: 70 KIAS and 15 degrees AOB.
30
AOB Limits
Normal Operations: 45 Operations above 10,000 DA: 30 Boost Off: 30 Either PRI SERVO PRESS caution: 30
31
Prohibited Manuevers
Aerobatics Practice full autos to a landing Intentional approaches into or inducement of retreating blade stall
32
Maximum Airspeed
As limited by blade stall
33
Hovering Limits
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 degrees per second. 3. Dipping sonar operatins 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. 4. Do not tow the TA in the water above 8 KGS with array folded or 4 KGS with array unfolded. CAUTION: exceeding may cause TA cable separation. NOTE: towing is defined as the cable contacting the funnel. Aircraft ground speed may be greater than 8/4 provided the cable is not in contact with the funnel.
34
Rotor Brake Limits
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.
35
Spread Limitations
Maximum wind velocity for blade fold and spread AND tail pylon/stab fold and spread is 45 knots from any direction. Following blade fold and spread, allow 10 minutes before commencing another evolution. A complete blade fold and spread is defined by a full spread followed by a full fold and vice versa.
36
Altitude Limitation
Maximum operating density altitude is 13,000 feet.
37
Landing Limitations
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 limited to 40 KGS with aircraft equipped with a tail gear shimmy damper, 20 KGS for aircraft without shimmy damper. 5. Slope landing limits: 6 down, 9 up, 12 cross NOTE: 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.
38
Windows
Windows shall not be installed or removed inflight, except during actual aircraft emergencies.
39
Aircraft Operating Gross Weight Limitations
The maximum operating gross weight is 23,500 pounds. The maximum launch and recovery gross weight for aviation ships is 23,500 pounds. The maximum launch and recovery gross weight for air-capable ships and amphibious assault aviation ships is 22,500 pounds.
40
External Load Weight Limits
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.
41
Minimum Aircraft Equipment for Night Flight Over Water
1. LAWS | 2. Altitude Hold (RADALT or BARALT)
42
Minimum Aircraft Equipment for Flights into Forecast or Known Icing Conditions
Helos equipped with operable AA/blade deice equipment are permitted flight into forecast or known TRACE or LIGHT icing conditions. All installed AA/deice 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). WARNING: flight into forecast or known MODERATE or SEVERE icing conditions is prohibited.
43
Temperature Limitations
Operations at temperatures below -40 C or above 60 C are prohibited.
44
Backup Hydraulic Pump Limitations
During prolonged ground operation of the backup hydraulic pump with the rotor system static, the backup pump is limited to the operating times below to prevent hydraulic fluid overheating. 33 to 38 C: 24 on / 72 off 39 to 60 C: 16 on / 48 off
45
APU Operating Limitations
To prevent APU overheating, APU operations at ambient temperatures of 43 C and above with engine and rotor operating is limited to 30 minutes. With engine and rotor systems static, the APU may be operated continuously up to an ambient temperature of 51 C.
46
Static Rollover Critical Rollover Dynamic Rollover
- 28 degrees; angle at which the helicopter will tip over - 12 degrees; max lateral angle that can be negotiated in a takeoff or landing - buildup of angular velocity of the cg about the wheel touching the ground

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