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NATOPS > Limits > Flashcards

Limits Flashcards

1
Q

Measured Gas Temperature (MGT) Limits

A

Starting:
>807-835° C Transient (1 sec)
779-807° C Transient (3 sec)

Operating:
>852-874° C   Transient (3 sec)
>803-852° C   Max (10 min)
>766-803° C   Intermediate (30 min)
0-766° C         Max Continuous
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2
Q

Gas Generator (Ng) Limits

A

101% Max Transient (3 sec)

100% Max Steady State

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3
Q

Power Turbine Speed (Np) Limits

A 
120%           Max Transient (3 sec)
114-120%      FADEC Fuel Shutoff
105%           Max Steady State /      
                       FADEC Fuel Cutback
104%           Interim Power
100%           VTOL / CONV Normal
84%             APLN Normal
20-33%,
53-67%        Avoid Range
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4
Q

Engine Torque (TRQ) Limits

A

> 139% Invalid
111-139% High Warning
101-111% High Caution
0-101% Normal

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5
Q

Engine Oil Pressure Limits

A 
>90 psi          High Warning
>60-90 psi     High Caution
35-60 psi       Normal
30-<35 psi     Low Caution
Below 30 psi   Low Warning
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6
Q

Engine Oil Temperature Limits

A 
>140° C         High Warning
>135-140° C   High Caution
40-135° C      Normal
20-<40° C     Low Caution
Below 20° C   Low Warning
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7
Q

APU Limits

A

-Not qualified for continuous in-flight operation
-15 sec before each attempted APU restart
-If APU fails to start after 3 attempts, cool starter motor for
55 minutes before attempting restart

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8
Q

PRGB/TAGB Oil Pressure Limits (Dual Engine)

A 
>150 psi        High Warning
>95-150 psi   High Caution
60-95 psi      Normal
30-<60 psi     Low Caution
Below 30 psi   Low Warning
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9
Q

PRGB/TAGB Oil Pressure Limits (Single Engine)

A 
>150 psi        High Warning
>95-150 psi   High Caution
60-95 psi      Normal
50-<60 psi    Low Caution
Below 50 psi   Low Warning
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10
Q

MWGB Oil Pressure Limits

A 
>100 psi        High Warning
>65-100 psi   High Caution
40-65 psi      Normal
25-<40 psi    Low Caution
Below 25 psi   Low Warning
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11
Q

PRGB/TAGB (Both Engines) and MWGB Oil Temperature Limits

A

> 132° C High Warning
110-132° C High Caution
20-110° C Normal
<20° C Low Caution

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12
Q

PRGB/TAGB Oil Temperature Limits (Single Engine)

A

> 121° C High Warning
110-121° C High Caution
20-110° C Normal
<20° C Low Caution

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13
Q

General Rotor Speed (Nr) Limits

A
  • Max airspeed for 100% Nr is 220 KCAS
  • Max altitude for 100% Nr is 17,000 ft DA
  • Nr shall be above 75% before starting 2nd Engine
  • SFD may indicate RPM HIGH condition when one does not actually exist. Refer to CDU and DEU for correct Nr.
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14
Q

VTOL/CONV Rotor Speed (Nr) Limits

A 
>113%         High Warning
>104-113%   High Caution
104%          Takeoff
100%          Normal
96%           Min - Power On
<94%          Low Warning
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15
Q

APLN Rotor Speed (Nr) Limits

A

> 113% High Warning
104-113% High Caution
82-104% Normal
Below 82% Low Warning

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16
Q

84% Proprotor Mast Torque (Qm) Limits

A 
>111%         High Warning
>100-111%   High Caution
>10-100%   Normal
3-10%        Low Caution
<3%           Low Warning
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17
Q

100% Proprotor Mast Torque (Qm) Limits

A 
>132%         High Warning
>100-132%   High Caution
>12-100%     Normal
3-12%          Low Caution
<3%             Low Warning
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18
Q

104% Proprotor Mast Torque (Qm) Limits

A 
>132%        High Warning
>117-132%   High Caution
>12-117%     Normal
3-12%         Low Caution
<3%            Low Warning
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19
Q

CAUTION: During high power settings, possible proprotor overtorque may occur with excessive ________ ________ _______.

A

lateral cyclic inputs

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20
Q

CAUTION: Delay takeoff until gearbox oil temperatures reach ___

A

20° C

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21
Q

CAUTION: Do not operate engines above ground idle with engine oil temperature below

A

20° C

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22
Q

NOTE: For 100% or 104% Nr, PRTR OVERTORQUE (L/R) will post when either Qm is >___ for ___ seconds or >___ Qm instantaneous. For 84% Nr, PRTR OVERTORQUE (L/R) will post when either Qm is > ___ for ___ seconds or > ___ Qm instantaneous.

A

> 132% for 5 seconds; >150% Qm instantaneous

>111% for 5 seconds; >126% Qm instantaneous

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23
Q

NOTE: During Rotor Speed Transitions from 84% to 100% or 100% to 84%, the mast torque will ________, resulting in an _______ change in the display which does not represent the actual torque change.

A

re-reference

instantaneous

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24
Q

Flight is prohibited with hydraulic fluid temperature below ____.

A

-18° C

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25
Q

Hydraulic Pressure Limits

A

5500 psi High Warning
5250 to <4600 psi Low Caution
Below 4200 psi Low Warning

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26
Q

Generator Operation Range

A
  • Generators 1* and 2 Trip on at 72% Nr and off at 67%** Nr.
  • Generators 3 and 4 Trip on at 82% Nr and off at 80-82% Nr.
  • If APU engaged, GEN 1 unaffected by Nr.
  • *May remain on for values below 67% Nr, the trip value will be determined by load and frequency.
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27
Q

Regulated converters shall be started above ____. Once started above ___, regulated converters are limited to a continuous operational OAT of ____ to ____. The converters are limited to ___ minutes of operation from ___ to ___.

A

-40°C; -40°C; -54°C to 50°C

30 minutes; 55°C to 71°C

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28
Q

For operations without domed searchlight cover, ensure searchlights are turned off and allowed to cool for ___ ______ prior to performing refueling operations (air or ground).

A

2 minutes

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29
Q

The search/landing lights shall not be operated in ______ ______ ______ without proprotors turning.

A

Unprepared grassy areas

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30
Q

The searchlights shall not be motorized to/from the extended position above ___ kts.

A

200 kts

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31
Q

Flight outside of the ______ ______ ______ is prohibited. Commanding maximum rate ______ ______ at the Vcon limits is prohibited.

A

Conversion protection limits

Aft nacelle

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32
Q

WARNING: Flight outside of the ______ ______ ______ limits may result in in-flight structural damage.

A

Upper conversion protection

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33
Q

Flight with nacelles between ___ and ___ is limited to relative crosswinds less than ___ kts and relative rearward airspeed less than ___ kts.

A

85° and 75°; 20 kts; 10 kts

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34
Q

NOTE: Relative airspeed and direction are sum of ______ ______ and ______ ______ components.

A

Ground speed; wind speed

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35
Q

While airborne with nacelles at or below ___, forward nacelle modulation is prohibited until airspeed exceeds ___ ____.

A

75°; 40 KCAS

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36
Q

WARNING: Flight with nacelles below the ______ ______ ______ ______ at any gross weight may result in severe pitch down and significant _____ ______.

A

Low speed transition limit

Altitude loss

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37
Q

WARNING: Forward nacelle modulation combined with _______ ______ ______ ______ ______ could lead to nose down pitching moments that may not be recoverable.

A

Reduced aft longitudinal stick authority

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38
Q

NOTE: The severity of the nose down pitch is aggravated with ______, ______ ______, and ______ ______.

A

tailwinds, forward CG, and pedal inputs

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39
Q

NOTE: Raising nacelles and centering pedals and lateral stick may restore ______ ______ ______.

A

longitudinal control authority

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40
Q

Flight at 84% Nr is limited to ___ KCAS or ___ Mach; whichever is less.

A

280 KCAS, 0.48 Mach

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41
Q

Flight at 100% Nr is limited to ___ KCAS or ___ Mach; whichever is less.

A

220 KCAS, 0.46 Mach

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42
Q

With a disabled FFR, transition out of avoid region as soon as possible. WARNING: With a disabled FFR, ______ ______ ______ i the avoid regions may result in in-flight structural damage

A

sustained flight operations

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43
Q

Flight as 84% Nr is limited to ___ ft DA.

A

25,000 ft DA

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44
Q

Flight at 100% Nr is limited to ___ ft DA with >30° Nacelle. Below 30° Nacelle, the altitude gradually increases to ___ ft DA.

A

14,000 ft DA

17,000 ft DA

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45
Q

Landing (STO/ROL and VTO/VL) is prohibited above ___ ft DA.

A

12,000 ft DA

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46
Q

NOTE: The ROTOR LOAD HIGH CAUTION will post more frequently when operating at ______ ______ ______ in VTOL/CONV mode. Use the ______ to assess severity of present flight conditions.

A

high density altitudes

FFR

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47
Q

Blowdown limiting exists within the flight control software such that the flaps will retract as a function of ______.

A

airspeed

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48
Q

0° Flaps

A

APLN mode only

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49
Q

10° Flaps

A

APLN mode only; 220 KCAS or less

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50
Q

20° Flaps

A

APLN mode only; 180 KCAS or less

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51
Q

40° Flaps

A

All modes authorized; 180 KCAS or less

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52
Q

Full Flaps

A

VTOL/CONV mode only; 45 KCAS or less

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53
Q

Ground taxi operations on unpaved surfaces have five additional restrictions:

A
  1. Taxi director required
  2. Minimize braking to prevent porpoising
  3. Use only light braking while turning
  4. Minimize nosewheel steering
  5. Soft or muddy unpaved surface ground taxi is prohibited
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54
Q

Maximum up/down/cross slope takeoff/landing is ___.

A

9°

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55
Q

Traversing or taxi over obstacles greater than ___ inches in height is prohibited.

A

1.5 inches

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56
Q

______, ______ ______ on unprepared surfaces is prohibited.

A

STO, run-on landing

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57
Q

Pivoting about a ______ ______ is prohibited

A

single MLG

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58
Q

The ______ ______ and ______ ______ must be off for STO.

A

power steering and nosewheel lock

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59
Q

______ braking is prohibited

A

Abrupt

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60
Q

WARNING: Hard braking above ___ KGS may cause structural damage to the carbon brake disks resulting in loss of braking in the affected wheel braking or binding in the brake causing skidding in the affected wheel brake. hard braking above ___ KGS may cause flat spotting and tire failure.

A

20 KGS

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61
Q

Maximum brake application

A

60 KGS

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62
Q

Maximum taxi speed for turning

A

20 KGS

63
Q

Maximum taxi on paved surfaces to include AM-2 matting

A

100 KGS

64
Q

Maximum taxi speed on unpaved surfaces

A

5 KGS

65
Q

Maximum takeoff on paved surfaces to include AM-2 matting (Nacelles <85°)

A

100 KGS

66
Q

Maximum landing on paved surfaces to include AM-2 matting (Nacelles <85°)

A

88 KGS

67
Q

Minimum STO Nacelle (Nacelles <85°)

A

60°

68
Q

Minimum Landing Nacelle (Nacelles <85°)

A

75°

69
Q

Maximum crosswind (Nacelles <85°)

A

20 Kts

70
Q

Maximum tailwind (Nacelles <85°)

A

10 Kts

71
Q

Maximum airspeed for extension/retraction of landing gear

A

140 KCAS

72
Q

Maximum airspeed for operation with landing gear extended

A

150 KCAS

73
Q

Maximum speed with ramp open

A

260 KCAS

74
Q

______ ______ prohibited with ramp open

A

Negative-g maneuvers

75
Q

Maximum ramp loading is ___ lbs. Movement of loaded ramp ______ is prohibited

A

1,750 lbs

in-flight

76
Q

Maximum palletized load on ramp for ground operations movement

A

5,000 lbs

77
Q

Cargo Compartment Floor limit is ___ pounds per square foot.

A

300

78
Q

WARNING: Use of AUTO mode with the Utility Isolation Valve closed is prohibited. If ramp/door movement is inadvertently commanded through the cockpit ramp control rocker switch while in AUTO mode with the utility isolation valve closed, the command will not be executed until the utility isolation valve opens. This delayed action may appear to be ______ and can result in personnel injury/death and/or equipment damage if not anticipated.

A

uncommanded

79
Q

Single cargo hook limited to ___ lbs.

A

10,000 lbs

80
Q

Dual hook is limited to loads between ___ and ___ lbs.

A

2,000 and 12,500 lbs

81
Q

Dual point maximum distribution between hooks is ___ or ___.

A

70/30 or 30/70

82
Q

The external cargo hook doors are limited to: [A] ___ KCAS (latched open), [B] ___ KCAS (latched open, when being opened or closed). [A] shall not be opened or closed above ___ KCAS.

A

200 KCAS
250 KCAS
80 KCAS

83
Q

______ ______ mode is prohibited while conducting external operations.

A

FD coupled

84
Q

Single/Dual point load is limited to ___ KCAS.

A

200 KCAS

85
Q

With external cargo hook door(s) removed limited to ___ KCAS.

A

280 KCAS

86
Q

External operations at ___ Nr are prohibited.

A

84% Nr

87
Q

Maximum angle of bank during external cargo operations is ___.

A

30°

88
Q

All ______ ______ require a functioning radar altimeter without load interference.

A

night operations

89
Q

______ ______ are prohibited; including entry or glide.

A

Practice autorotations

90
Q

______ are prohibited.

A

Aerobatics

91
Q

______ ______ ______ control inputs are prohibited.

A

Abrupt large amplitude

92
Q

Maximum out of trim condition for maneuvering in APLN and CONV mode is ______ ______ ______.

A

one ball out

93
Q

Flight into known ______ ______ ______ conditions is prohibited. Immediate recovery shall be initiated at the first activation of the ______ ______ ______ warning system.

A

Vortex Ring State

High Sink Rate

94
Q

Operations with gross weight above 57,000 lbs only authorized under the following conditions:

A
  1. Max gross weight does not exceed 60,500 lbs.
  2. Load factors not to exceed 0.5-1.5g.
  3. Max angle of bank is 30°. Transient to 35° authorized in flight director coupled mode.
  4. Max airspeed in APLN mode is 250 KCAS.
95
Q

NOTE: During flight director coupled mode operations at gross weights above 57,000 lbs, the flight director may command up to ___ exceedences of the angle of bank limitations.

A

5°

96
Q

Max Touch Down Rate

A

GW ≤ 46,000 lbs = 720 fpm

GW > 46,000 lbs = 600 fpm

97
Q

Max Turn Rate (Hover)

A

30° /SEC

98
Q

Normal Load Factor (VTOL/CONV)

A 
VTOL = 0.5g to 2.0g
CONV = 0.5g to 3.0g
99
Q

Max Angle of Bank (VTOL/CONV)

A

VTOL = 30°
CONV < 60 KCAS = 30°
CONV > 60 KCAS = 60°

100
Q

Max Pitch Attitude (VTOL/CONV)

A

20° Nose Up

101
Q

APLN Load Factor Limits

A

Symmetric: -0.5g to 4.0g
Asymmetric: -0.5g to 3.2g
Negative g: Max 10 seconds per event

102
Q

NOTE: Positive g is limited by structural load limiting. Actual load factors attainable at a given flight condition may be less than 4.0. Negative g limits are controlled by ______ ______.

A

the pilot

103
Q

Max Angle of Bank (APLN)

A

60°

104
Q

Max Pitch Attitude (APLN)

A

35°

105
Q

Practice 1g Stall Limits

A

Max deceleration rate: 5 KCAS per second.

Max allowable torque throughout the maneuver to include recovery (until stall warning <100%): 60% torque

106
Q

Wheeled Vehicle Transport Mission Limits

A

Max angle of bank: 30°

Normal load factor: 0.5g to 1.5g

107
Q

Aircraft Configuration for defensive/tactical maneuvering

A
  1. AUTO flaps only
  2. Max gross weight: 48,000 lbs
  3. STA CG: 395-403 inches
  4. LAT CG: -3 to +3 inches
108
Q

Flight Conditions for defensive/tactical maneuvering (APLN)

A
  1. Min airspeed: 160 KCAS

2. Max pressure altitude: 10,000 ft

109
Q

Flight Conditions for defensive/tactical maneuvering (CONV)

A

Balanced flight while turning away from the threat with continuous transition to APLN authorized. Sustained CONV operations not authorized.

110
Q

Flight Conditions for defensive/tactical maneuvering (VTOL)

A

Hover pedal turns to change heading are authorized. Sustained VTOL operations not authorized.

111
Q

Control Inputs for defensive/tactical maneuvering

A
  1. Pedals centered, CONV and APLN (no more than 1/4 ball out with constant trim)
  2. Abrupt, large amplitude inputs and abrupt reversals prohibited.
  3. Maximum cyclic inputs (from center to stop):
    A. Single axis: 1/2 deflection
    B. Multiple axis: 1/4 deflection
112
Q

WARNING: Control inputs beyond those authorized may lead to departure of the aircraft from controlled flight that may be unrecoverable. The potential for departure at elevated angle of attack is increased with concurrent pedal inputs and/or ______ ______ application.

A

full TCL

113
Q

Stall Warning limits for defensive/tactical maneuvering

A
  1. Maximum 80%

2. Tactical maneuvering prohibited with STALL WARN FAIL advisory posted

114
Q

Flight or filing through forecasted or actual ______ ______ is prohibited

A

severe icing

115
Q

Icing APLN: Flaps shall be set to ______ or ___, maximum stall warning ___, and a minimum of ___ Qm margin. FLAPS - AUTO, 200 KCAS recommended.

A

AUTO or 0, 60%, 10%

116
Q

Icing CONV: FLAPS - ______, ___ nacelle, ___ KCAS recommended. Avoid extended operations in VTOL or CONV mode.

A

AUTO, 60°, 110 KCAS

117
Q

Flight Operations in visible moisture from 4° to -4° C

A 
Fully functional IPS, or:
Pitot Heat
AOA Heat
EAPS
Engine Anti-Ice
If ice is visually detected, exit icing conditions
118
Q

Flight Operations in visible moisture from <-4° to -20° C

A 
Fully functional IPS, or:
Pitot Heat
AOA Heat
EAPS
Engine Anti-Ice
Functional Ice detector
An official forecast of "none" or "trace" icing within ±4,000ft of the route of flight
119
Q

Flight Operations in visible moisture from <-20° to -40° C

A

Fully functional IPS, and:
An official forecast of “none” or “trace” icing within ±4,000 ft of the route of flight.
WARNING: Any ice accumulation in this temperature range shall be considered severe icing as it will exceed the capabilities of the icing system.

120
Q

Ground Operations in visible moisture

A 
All ice or snow on the aircraft shall be removed prior to flight.  Aircraft air inlets shall be inspected for ice accumulation prior to all flights that are preceded by ground operations in icing conditions.  AND:
Pitot Heat
AOA Heat
EAPS
Engine Anti-ice
121
Q

NOTE: It is possible to get ice in the engine due to induced spray/moisture on the ground without the system detecting ice. ______ ______ will not automatically be turned on. Consideration should be given to selecting ______ ______ - ______ and just prior to takeoff return to ______.

A

Engine anti-ice
ENGINE ANTI-ICE - ON
AUTO

122
Q

Turn IPS MODES - ______ prior to cloud immersion at ___ C or less.

A

ON

-15° C

123
Q

IPS capability is dependent on specific PRTR IPS failure:
Heater Zones 1, 2 = ___
Heater Zone 3 = ___
All other PRTR IPS fails = ___

A

Operate no lower than:

  • 15° C
  • 10° C
  • 4° C
124
Q

Washing engines below ___ C not authorized.

A

-15° C

125
Q

If winds in excess of ___ kts are expected, the aircraft shall be flown away, placed in a hangar or proprotor blades and rudders removed.

A

90 kts

126
Q

With winds above ___ kts, without hydraulic power, all gust locks shall be installed.

A

45 kts

127
Q

With winds above ___ kts, the aircraft shall be placed nose into the wind to prevent possible rotor head damage.

A

60 kts

128
Q

Wind Limit - Ground engine start up/shutdown

A

45 kts

129
Q

Wind Limit - Any BFWS operations

A

45 kts

130
Q

Wind Limit - Static FLT RDY, Fold Horizontal or Fold Vertical

A

60 kts

131
Q

Wind limit - FULL STOW

A

90 kts

132
Q

Without ______ ___ and the ___ ______ Receiver, the ______ shall not be used as a primary navigation source or for filing IFR.

A

AFC 86, -020 VOR, VOR

133
Q

The use of type equipment code ___ prohibited.

A

/G

134
Q

Flying under conditions of ______ turbulence should be avoided.

A

severe

135
Q

Maximum turbulence penetration airspeed

A

220 KCAS

136
Q

Turbulence penetration torque limit

A

At 100% Nr, ≤ 75% Qm

At 84% Nr, ≤ 65% Qm

137
Q

CAUTION: Operation of the aircraft in conditions of severe turbulence may result in ______ ______ annunciation and damage to the rotor and drive system as a result of asymmetrical gust loading. The aircraft is more susceptible to these ______ in APLN mode at high airspeeds and high torque settings in areas of severe turbulence, especially below ___ ft AGL due to orographic effects.

A

PRTR OVERTORQUE
overtorques
1000 ft AGL

138
Q

Fuel dump is ______ ______ ______ ______.

A

prohibited except in emergencies

139
Q

Fuel dump required configuration (time permitting)

A
  1. Cargo ramp and door closed
  2. Landing gear up
  3. Main cabin door closed
140
Q

WARNING: Fuel will impinge on and seep into the ramp and empennage during fuel dump operations increasing the ______ ______ ______. Aircraft commander should weigh the risk of ______ ______ ______ with fuel prior to emergency landing.

A

risk of fire

saturating the aircraft

141
Q

Minimum feed tank quantity

A

300 lbs

142
Q

Maximum forward sponson allowable fuel split

A

2,500 lbs

143
Q

During MATS refueling, the fuel level within each MATS must be monitored and ______ ______ (No auto shutoff).

A

manually isolated

144
Q

Forward MATS limit

A

2,350 lbs

145
Q

Mid and Aft MATS limit

A

2,200 lbs

146
Q

MATS RGR Configuration (three tanks)

A

FWD: 2,350 lbs
MID: 2,200 lbs
AFT: 1,750 lbs

147
Q

MATS RGR Configuration (two tanks)

A

FWD: 2,350 lbs
MID: 1,900 lbs

148
Q

MATS RGR Configuration (one tank)

A

FWD: 1,900 lbs

149
Q

WARNING: Filling MATS greater than the fuel tank fill volumes will exceed the structural requirements of the tiedown restraints in the event of a crash. Exceeding these limits can cause MATS ______ ______ in a crash, resulting in personal injury or death.

A

restraint failure

150
Q

WARNING: The troop seats directly ______ of the first and second MAT are not authorized for use due to loss of ______ ______ and possible head strike.

A

aft

crash attenuation

151
Q

Maximum gross weight (VTOL)

A

52,600 lbs

152
Q

Maximum gross weight (Shore-based STO)

A

57,000 lbs

153
Q

Maximum alternate gross weight

A

60,500 lbs

NATOPS (3 decks)

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