Limitations Flashcards
1
Q
Maximum design takeoff weight
A
Maximum design takeoff weight
17,110 Pounds
2
Q
Maximum design takeoff weight
A
Maximum design takeoff weight
17,110 Pounds
3
Q
Maximum design takeoff weight
A
Maximum design takeoff weight
17,110 Pounds
4
Q
Maximum design landing weight
A
Maximum design landing weight
15,660 Pounds
5
Q
Maximum design zero fuel weight
A
Maximum design zero fuel weight
12,500 Pounds
6
Q
Maximum baggage weight in nose compartment
A
Maximum baggage weight in nose compartment
400 Pounds
7
Q
Maximum baggage weight in tailcone compartment
A
Maximum baggage weight in tailcone compartment
600 Pounds
8
Q
Maximum load distribution
(nose baggage compartment)
A
Maximum load distribution
(nose baggage compartment)
35 Pounds per Square Foot
9
Q
Maximum load distribution
(tailcone baggage compartment)
A
Maximum load distribution
(tailcone baggage compartment)
150 Pounds per Square Foot
10
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Dispatch is not allowed with any _____ annunciator or ____ message
displayed. Refer to applicable Minimum Equipment List (MEL) for
dispatch with amber annunciator or amber message.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Dispatch is not allowed with any red annunciator or red message
displayed. Refer to applicable Minimum Equipment List (MEL) for
dispatch with amber annunciator or amber message.
11
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is __________ with an amber ENGINE CTRL SYS FAULT L and/or
R message displayed.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is prohibited with an amber ENGINE CTRL SYS FAULT L and/or
R message displayed.
12
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
The autopilot and yaw damper must be _________\_ for takeoff and
landing.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
The autopilot and yaw damper must be disengaged for takeoff and
landing.
13
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Dispatch with the yaw damper inoperative is _________.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Dispatch with the yaw damper inoperative is prohibited.
14
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is _________ if the antiskid system is inoperative.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is prohibited if the antiskid system is inoperative.
15
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is prohibited until the battery charging amps is ___ amps or less.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoff is prohibited until the battery charging amps is 20 amps or less.
16
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Cabin must be depressurized prior to ______.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Cabin must be depressurized prior to landing.
17
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoffs and landings are limited to ______ runway surfaces.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Takeoffs and landings are limited to paved runway surfaces.
18
Q
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Except where required by AFM procedures, speed brakes must be
retracted prior to ____ feet AGL for landing.
A
TAKEOFF AND LANDING
OPERATIONAL LIMITS
Except where required by AFM procedures, speed brakes must be
retracted prior to 500 feet AGL for landing.
19
Q
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude
A
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude
FL450
20
Q
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with WING XFLOW on
A
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with WING XFLOW on
FL410
21
Q
ENROUTE OPERATIONAL LIMITS
Maximum altitude for extension of flaps and/or landing gear
A
ENROUTE OPERATIONAL LIMITS
Maximum altitude for extension of flaps and/or landing gear
FL180
22
Q
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with inoperative yaw damper
A
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with inoperative yaw damper
FL240
23
Q
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with amber
DC GENERATOR OFF L-R displayed
A
ENROUTE OPERATIONAL LIMITS
Maximum operating altitude with amber
DC GENERATOR OFF L-R displayed
FL350
24
Q
FUEL LIMITS
Maximum demonstrated fuel imbalance for emergency return following a
fuel system malfunction is ____ lbs.
A
ENROUTE OPERATIONAL LIMITS
Maximum demonstrated fuel imbalance for emergency return following a
fuel system malfunction is 600 lbs.
25
**FUEL LIMITS**
**Maximum approved fuel imbalance for normal operation**
**FUEL LIMITS**
**Maximum approved fuel imbalance for normal operation**
200 lbs
26
**FUEL LIMITS**
Single point refueling operations must be conducted per the procedures
contained on the placard installed on the single point refueling access
door. Refueling pressure range is ____ psi; maximum defuel pressure is
\_\_\_\_ psi.
**FUEL LIMITS**
Single point refueling operations must be conducted per the procedures
contained on the placard installed on the single point refueling access
door. Refueling pressure range is **_10-55_** psi; maximum defuel pressure is
**_-10_** psi.
27
**FADEC (FULL AUTHORITY DIGITAL
ENGINE CONTROLLER)**
Engine start and/or dispatch with an amber ENGINE CTRL SYS FAULT
L-R message displayed is \_\_\_\_\_\_\_\_.
**FADEC (FULL AUTHORITY DIGITAL
ENGINE CONTROLLER)**
Engine start and/or dispatch with an amber ENGINE CTRL SYS FAULT
L-R message displayed is **_prohibited_**.
28
**ENGINE OPERATING LIMITS**
Takeoff thrust settings, which are normally limited to ___ minutes duration
for all engine operating conditions, may be used for up to ___ minutes for
one engine inoperative operations. Timing begins when throttle lever is
advanced to the TO detent.
**ENGINE OPERATING LIMITS**
Takeoff thrust settings, which are normally limited to **_5_** minutes duration
for all engine operating conditions, may be used for up to **_10_** minutes for
one engine inoperative operations. Timing begins when throttle lever is
advanced to the TO detent.
29
**APPROVED OILS**
\_\_\_\_\_\_\_\_\_\_\_\_ is the preferred oil.
**APPROVED OILS**
**_Mobil Jet II_** is the preferred oil.
30
**APPROVED OILS**
Mixing of approved oils is \_\_\_\_\_\_\_\_\_.
**APPROVED OILS**
Mixing of approved oils is **_permissible_**.
31
**APPROVED OILS**
Approved oils include _________ & \_\_\_\_\_\_\_\_.
**APPROVED OILS**
Approved oils include **Mobil Jet II** & **Mobil 254**.
32
**APPROVED OILS**
Maximum oil consumption is _____ gallons per 1 hour period (\_\_ qt or
\_\_ L per 8 hours). Refer to the aircraft maintenance manual when oil
consumption exceeds this value.
**APPROVED OILS**
Maximum oil consumption is **_0.032_** gallons per 1 hour period (**_1_** qt or
**_1_** L per 8 hours). Refer to the aircraft maintenance manual when oil
consumption exceeds this value.
33
**ENGINE START LIMITS (GENERAL)**
Amber ENGINE CTRL SYS FAULT message
displayed
**ENGINE START LIMITS (GENERAL)**
Amber ENGINE CTRL SYS FAULT message
displayed
**Engine start prohibited**
34
**ENGINE START LIMITS (GENERAL)**
Generator switches
**ENGINE START LIMITS (GENERAL)**
Generator switches
**ON for engine starts**
35
**ENGINE START LIMITS (GENERAL)**
Time to light-off is defined as the time from first indication of fuel flow
until an ____ increase is observed.
**ENGINE START LIMITS (GENERAL)**
Time to light-off is defined as the time from first indication of fuel flow
until an **_ITT_** increase is observed.
36
**ENGINE START LIMITS (GENERAL)**
Maximum time to light-off
**ENGINE START LIMITS (GENERAL)**
Maximum time to light-off
**10 seconds (ground starts only)**
37
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum elevation for battery or cross generator starts
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum elevation for battery or cross generator starts
**14,000 Feet**
38
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum tailwind component
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum tailwind component
**10 Knots**
39
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum crosswind component
**ENGINE START LIMITS
(GROUND STARTS)**
Maximum crosswind component
**10 Knots**
40
**ENGINE START LIMITS
(GROUND STARTS)**
Minimum battery voltage for battery start
**ENGINE START LIMITS
(GROUND STARTS)**
Minimum battery voltage for battery start
**24 Volts**
41
**ENGINE START LIMITS
(GROUND STARTS)**
Engine oil must be preheated to at least _____ prior to conducting a start.
**ENGINE START LIMITS
(GROUND STARTS)**
Engine oil must be preheated to at least **_-40°C_** prior to conducting a start.
42
**ENGINE START LIMITS
(GROUND STARTS)**
Lithium batteries must be preheated to at least \_\_\_°C prior to start
(SYSTEMS 1 format/overlay on MFD).
**ENGINE START LIMITS
(GROUND STARTS)**
Lithium batteries must be preheated to at least **_-10°C_** prior to start
(SYSTEMS 1 format/overlay on MFD).
43
**ENGINE START LIMITS
(GROUND STARTS)**
Nickel-cadmium and lead-acid batteries must be preheated to at least
\_\_\_°C prior to start (SYSTEMS 1 format/overlay on MFD).
**ENGINE START LIMITS
(GROUND STARTS)**
Nickel-cadmium and lead-acid batteries must be preheated to at least
-**_20°C_** prior to start (SYSTEMS 1 format/overlay on MFD).
44
**ENGINE START LIMITS
(GROUND STARTS)**
If the airplane has been cold soaked in ambient temperatures below -40°C,
the FADECs must be warmed with electrical power for at least ___ minutes
followed by a power cycle with the battery switch.
**ENGINE START LIMITS
(GROUND STARTS)**
If the airplane has been cold soaked in ambient temperatures below -40°C,
the FADECs must be warmed with electrical power for at least **_3_** minutes
followed by a power cycle with the battery switch.
45
**ENGINE START LIMITS
(GROUND STARTS)**
Minimum engine oil temperature (indicated on EIS)
**ENGINE START LIMITS
(GROUND STARTS)**
Minimum engine oil temperature (indicated on EIS)
**-40°C**
46
**START CYCLE LIMITS**
This limit is independent of starter power source (i.e., battery, generator
assisted cross start, or external power unit) and applies to both starting and
dry motoring of the engine.
Engine starter limits:
**START CYCLE LIMITS**
This limit is independent of starter power source (i.e., battery, generator
assisted cross start, or external power unit) and applies to both starting and
dry motoring of the engine.
Engine starter limits:
**Three** engine starts per **30** minutes.
**Three** cycles of operation with a
**60**-second rest period between
cycles is permitted.
47
**SPEED LIMITS**
MMO (above 27,884 feet)
**SPEED LIMITS**
MMO (above 27,884 feet)
**Mach 0.77 (indicated)**
48
**SPEED LIMITS**
VMO (between 8000 and 27,884 feet)
**SPEED LIMITS**
VMO (between 8000 and 27,884 feet)
**305 KIAS**
49
**SPEED LIMITS**
VMO (below 8000 feet)
**SPEED LIMITS**
VMO (below 8000 feet)
**260 KIAS**
50
**SPEED LIMITS**
Full application of rudder and aileron controls as well as maneuvers that
involve angle-of-attack near the stall should be confined to speeds below
\_\_\_\_\_\_ __________ \_\_\_\_\_\_\_ speed. Refer to LOAD FACTOR limits
for pitch maneuvering limits.
**SPEED LIMITS**
Full application of rudder and aileron controls as well as maneuvers that
involve angle-of-attack near the stall should be confined to speeds below
**_maximum operating maneuvering_** speed. Refer to LOAD FACTOR limits
for pitch maneuvering limits.
51
**SPEED LIMITS**
Maximum flap extended speed - VFE
Takeoff and approach position (15°)
**SPEED LIMITS**
Maximum flap extended speed - VFE
Takeoff and approach position (15°)
**200 KIAS**
52
**SPEED LIMITS**
Maximum flap extended speed - VFE
Landing position (35°)
**SPEED LIMITS**
Maximum flap extended speed - VFE
Landing position (35°)
**160 KIAS**
53
**SPEED LIMITS**
Maximum landing gear extended speed - VLE
**SPEED LIMITS**
Maximum landing gear extended speed - VLE
**200 KIAS**
54
**SPEED LIMITS**
Maximum landing gear operating speed - VLO
(Extending or Retracting)
**SPEED LIMITS**
Maximum landing gear operating speed - VLO
(Extending or Retracting)
**200 KIAS**
55
**SPEED LIMITS**
Maximum speed brake operation speed VSB
**SPEED LIMITS**
Maximum speed brake operation speed VSB
**No Limit**
56
**SPEED LIMITS**
Maximum autopilot operation speed
**SPEED LIMITS**
Maximum autopilot operation speed
**305 KIAS or Mach 0.77**
57
**SPEED LIMITS**
Maximum autopilot operation speed
**SPEED LIMITS**
Maximum autopilot operation speed
**305 KIAS or Mach 0.77**
58
**SPEED LIMITS**
Minimum speed for sustained flight In icing conditions (Flaps 0°)
**SPEED LIMITS**
Minimum speed for sustained flight In icing conditions (Flaps 0°)
**160 KIAS**
59
**SPEED LIMITS**
Maximum tire ground speed
**SPEED LIMITS**
Maximum tire ground speed
**165 KIAS**
60
**MANEUVER LIMITS**
Acrobatic maneuvers, including spins, are \_\_\_\_\_\_\_\_\_\_\_.
**MANEUVER LIMITS**
Acrobatic maneuvers, including spins, are **_prohibited_**.
61
**MANEUVER LIMITS**
Intentional stalls are prohibited above _______ feet.
**MANEUVER LIMITS**
Intentional stalls are prohibited above **_18,000_** feet.
62
**BATTERY LIMITS**
Lead-acid and nickel-cadmium batteries are approved for use in the CJ4.
Lithium batteries may ____ be used for ground or flight operations unless
approved by later AFM revision.
**BATTERY LIMITS**
Lead-acid and nickel-cadmium batteries are approved for use in the CJ4.
Lithium batteries may **_not_** be used for ground or flight operations unless
approved by later AFM revision.
63
**BATTERY LIMITS**
The battery temperature indicating system must be operational for all
\_\_\_\_\_\_\_ and _____ operations.
**BATTERY LIMITS**
The battery temperature indicating system must be operational for all
**_ground_** and **_flight_** operations.
64
**BATTERY LIMITS**
If the red BATTERY OVERTEMP message displays during ground operations, do not take off until the proper maintenance procedures have
been accomplished. Even if the message subsequently clears, dispatch
is ________ until after the proper maintenance procedures have been
accomplished.
**BATTERY LIMITS**
If the red BATTERY OVERTEMP message displays during ground operations, do not take off until the proper maintenance procedures have
been accomplished. Even if the message subsequently clears, dispatch
is **_prohibited_** until after the proper maintenance procedures have been
accomplished.
65
**BATTERY LIMITS**
Battery start limit
**BATTERY LIMITS**
Battery start limit
**Three engine starts per hour**
66
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
Ground
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
Ground
**240 Amps**
67
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
Air ≤ FL250
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
Air ≤ FL250
**300 Amps**
68
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
\> FL250 and ≤ FL450
**ELECTRICAL POWER SYSTEMS**
Steady state generator limits are:
\> FL250 and ≤ FL450
**Linear decrease from 300 Amps to 170 Amps**
69
**CABIN PRESSURIZATION LIMITS**
Structural cabin pressurization
limits
**CABIN PRESSURIZATION LIMITS**
Structural cabin pressurization
limits
**(-0.5 to 9.0 PSI) ± 0.1 PSI Differential**
70
**SUPPLEMENTAL OXYGEN SYSTEM**
The use of medical oxygen is \_\_\_\_\_\_\_\_\_.
**CABIN PRESSURIZATION LIMITS**
The use of medical oxygen is **_prohibited_**.
71
**SUPPLEMENTAL OXYGEN SYSTEM**
Crew and passenger oxygen masks are not approved for use above \_\_\_\_\_\_
feet cabin altitude. Prolonged use of passenger masks above 25,000 feet
cabin altitude is not recommended.
**CABIN PRESSURIZATION LIMITS**
Crew and passenger oxygen masks are not approved for use above **_40,000_**
feet cabin altitude. Prolonged use of passenger masks above 25,000 feet
cabin altitude is not recommended.
72
**SUPPLEMENTAL OXYGEN SYSTEM**
Prior to flight, the crew oxygen mask must be checked and stowed properly
in its receptacle to qualify as a ______ \_\_\_\_\_\_\_\_ oxygen mask.
**CABIN PRESSURIZATION LIMITS**
Prior to flight, the crew oxygen mask must be checked and stowed properly
in its receptacle to qualify as a **_quick donning_** oxygen mask.
73
**SUPPLEMENTAL OXYGEN SYSTEM**
For single pilot operations, a crew oxygen mask _____ be available for
a passenger occupying the right crew seat. The mask must be checked
during preflight and passenger briefed on its use.
**CABIN PRESSURIZATION LIMITS**
For single pilot operations, a crew oxygen mask **_must_** be available for
a passenger occupying the right crew seat. The mask must be checked
during preflight and passenger briefed on its use.
74
**PASSENGER COMPARTMENT**
For taxi, takeoff, and landing, all adjustable seats must be fully \_\_\_\_\_\_
and \_\_\_\_\_\_\_\_; all occupied seats must have the head rest extended, seat
controls inboard, seat tracked away from the table and then outboard, and
passenger seat belts and shoulder harnesses must be fastened.
**PASSENGER COMPARTMENT**
For taxi, takeoff, and landing, all adjustable seats must be fully **_upright_**
and **_outboard_**; all occupied seats must have the head rest extended, seat
controls inboard, seat tracked away from the table and then outboard, and
passenger seat belts and shoulder harnesses must be fastened.
75
**PASSENGER COMPARTMENT**
The maximum number of occupants in the passenger compartment is \_\_\_\_\_
(\_\_\_\_\_ with the optional two-place side-facing couch installed).
**PASSENGER COMPARTMENT**
The maximum number of occupants in the passenger compartment is **_eight_**
(**_nine_** with the optional two-place side-facing couch installed).
76
**PASSENGER COMPARTMENT**
The lavatory door must be latched _____ for taxi, takeoff, and landing.
**PASSENGER COMPARTMENT**
The lavatory door must be latched **_open_** for taxi, takeoff, and landing.
77
**PASSENGER COMPARTMENT**
The lavatory is limited to one occupant.
**PASSENGER COMPARTMENT**
The lavatory is limited to **_one_** occupant.
78
**GROUND OPERATIONAL LIMITS**
Limit ground operation of pitot/static heat to ____ minutes to prevent
damage to the pitot tubes and angle of attack vane.
**GROUND OPERATIONAL LIMITS**
Limit ground operation of pitot/static heat to **_two_** minutes to prevent
damage to the pitot tubes and angle of attack vane.
79
**GROUND OPERATIONAL LIMITS**
Ground operation at greater than 75% N2 engine RPM with wing anti-ice on
is limited to ____ minutes. Do not operate with wing anti-ice on more than
\_\_\_\_ minute after the cyan or amber WING ANTI-ICE COLD message(s) have
extinguished during preflight checks.
**GROUND OPERATIONAL LIMITS**
Ground operation at greater than 75% N2 engine RPM with wing anti-ice on
is limited to **_two_** minutes. Do not operate with wing anti-ice on more than
**_one_** minute after the cyan or amber WING ANTI-ICE COLD message(s) have
extinguished during preflight checks.
80
**GROUND OPERATIONAL LIMITS**
Ambient surface temperature must be obtained from the ____ \_\_\_\_\_ on
the cockpit displays, with either or both engines operating, or from an
appropriate ground station.
**GROUND OPERATIONAL LIMITS**
Ambient surface temperature must be obtained from the **_SAT field_** on
the cockpit displays, with either or both engines operating, or from an
appropriate ground station.
81
**GROUND OPERATIONAL LIMITS**
The control lock must not be set if the airplane will be exposed to
temperatures below \_\_\_\_°C.
**GROUND OPERATIONAL LIMITS**
The control lock must not be set if the airplane will be exposed to
temperatures below **_-10_**°C.
82
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
Category II approaches are ____ approved.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
Category II approaches are **_not_** approved.
83
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
Operating in the _________ mode is limited to training and display
failure conditions.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
Operating in the **_composite_** mode is limited to training and display
failure conditions.
84
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
\_\_\_\_\_\_\_\_ the airplane is prohibited until all AHRS ground alignment is
completed.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
**_Taxiing_** the airplane is prohibited until all AHRS ground alignment is
completed.
85
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
Autopilot:
a. Use of the autopilot or yaw damper is prohibited during takeoff or landing.
b. One pilot must remain seated with seat belt fastened during all autopilot operations.
c. The autopilot minimum engage height, during climb following takeoff or go-around,
is ____ feet AGL.
d. The autopilot minimum use height is:
(1) ILS approach (CAT I) & LPV/WAAS - ____ feet AGL (flaps 0°-35°)
(2) Other non-precision approach - ____ feet AGL
(3) Cruise - _____ feet AGL
e. Do not override the autopilot in pitch during normal operation.
f. Use of the autopilot is prohibited if primary elevator trim is inoperative.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
Autopilot:
a. Use of the autopilot or yaw damper is prohibited during takeoff or landing.
b. One pilot must remain seated with seat belt fastened during all autopilot operations.
c. The autopilot minimum engage height, during climb following takeoff or go-around,
is **_300_** feet AGL.
d. The autopilot minimum use height is:
(1) ILS approach (CAT I) & LPV/WAAS - **_200_** feet AGL (flaps 0°-35°)
(2) Other non-precision approach - **_200_** feet AGL
(3) Cruise - **_1000_** feet AGL
e. Do not override the autopilot in pitch during normal operation.
f. Use of the autopilot is prohibited if primary elevator trim is inoperative.
86
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
VOR approaches must not be conducted in the ____ mode of the flight director.
Use the ____ mode, or manually track the approach course using the HDG mode.
This limit applies to both flight director only and autopilot coupled operation.
Autopilot coupled operation is prohibited during any portion of a VOR approach
in which the VOR is located behind the airplane by more than ___ miles, unless
the HDG mode of the flight director is being used to manually track the approach
course.
VOR approaches conducted without DME must be intercepted greater than \_\_\_
nautical miles from the VOR.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
VOR approaches must not be conducted in the **_NAV_** mode of the flight director.
Use the **_APPR_** mode, or manually track the approach course using the HDG mode.
This limit applies to both flight director only and autopilot coupled operation.
Autopilot coupled operation is prohibited during any portion of a VOR approach
in which the VOR is located behind the airplane by more than **_15_** miles, unless
the HDG mode of the flight director is being used to manually track the approach
course.
VOR approaches conducted without DME must be intercepted greater than **_6_**
nautical miles from the VOR.
87
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
It is prohibited to display the non-coupled side Flight Director unless the
coupled side Flight Director is being displayed. Failure to adhere to this limit
will result in _________ Flight Director guidance. Use of the coupled side Flight
Director by itself will operate correctly.
When conducting an approach that utilizes a localizer (ILS, LOC, LOC-BC,
LDA, SDF), the approach mode (\_\_\_\_\_) must not be selected until the course
deviation indicator (CDI) has clearly moved away from a full scale deflection
and the aircraft is within the published service volume for the approach. Failure
to observe this limit may result in capture of a false localizer lobe, resulting in
incorrect lateral guidance.
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
It is prohibited to display the non-coupled side Flight Director unless the
coupled side Flight Director is being displayed. Failure to adhere to this limit
will result in **_incorrect_** Flight Director guidance. Use of the coupled side Flight
Director by itself will operate correctly.
When conducting an approach that utilizes a localizer (ILS, LOC, LOC-BC,
LDA, SDF), the approach mode (**_APPR_**) must not be selected until the course
deviation indicator (CDI) has clearly moved away from a full scale deflection
and the aircraft is within the published service volume for the approach. Failure
to observe this limit may result in capture of a false localizer lobe, resulting in
incorrect lateral guidance.
88
**ROCKWELL COLLINS FCS-3000
INTEGRATED FLIGHT CONTROL SYSTEM**
## Footnote
The angle-of-attack system may be used as a \_\_\_\_\_\_\_\_\_, but does not
replace the airspeed display in the PFD as a primary instrument.
The angle-of-attack system can be used as a reference for approach
speed (VREF) at all airplane weights, CG locations, and flap positions.
VREF is indicated by approximately ___ on the AOA gauge, green circle
on AOA indexer (if installed), and by the green circle on the pilot and
copilot’s airspeed indicators.
**ANGLE-OF-ATTACK AND
STICK SHAKER SYSTEM**
## Footnote
The angle-of-attack system may be used as a **_reference_**, but does not
replace the airspeed display in the PFD as a primary instrument.
The angle-of-attack system can be used as a reference for approach
speed (VREF) at all airplane weights, CG locations, and flap positions.
VREF is indicated by approximately **_0.6_** on the AOA gauge, green circle
on AOA indexer (if installed), and by the green circle on the pilot and
copilot’s airspeed indicators.
89
**COCKPIT SPEAKER MUTE**
## Footnote
```
The pilot(s) must use a headset(s) when the overhead cockpit speaker
audio is \_\_\_\_\_\_\_.
```
**COCKPIT SPEAKER MUTE**
## Footnote
```
The pilot(s) must use a headset(s) when the overhead cockpit speaker
audio is **_muted_**.
```
90
**PULSELITE SYSTEM**
## Footnote
The pulse light system must be OFF and remain OFF during the
following night ground and night flight operations: taxi, takeoff, and
landing approach at ____ feet AGL and below.
**PULSELITE SYSTEM**
## Footnote
The pulse light system must be OFF and remain OFF during the
following night ground and night flight operations: taxi, takeoff, and
landing approach at **_300_** feet AGL and below.
91
**ICE AND RAIN PROTECTION**
## Footnote
Icing conditions in flight exist when SAT is \_\_\_\_°C or colder and visible
moisture in any form is present (such as clouds, fog with visibility of one mile
or less, rain, snow, sleet, or ice crystals).
Icing conditions on the ground exist with an OAT or SAT below \_\_\_°C or colder
and where surface snow, slush, ice or standing water may be ingested by the
engines or freeze on engine nacelles, or engine sensor probes.
The wing icing inspection light must be operative ____ to flight into known or
forecast icing conditions at night.
All anti-ice and de-ice systems must be ___ in flight when operating in icing
conditions, except tail deice must be off when SAT is below -30°C.
**ICE AND RAIN PROTECTION**
## Footnote
Icing conditions in flight exist when SAT is **_+10_**°C or colder and visible
moisture in any form is present (such as clouds, fog with visibility of one mile
or less, rain, snow, sleet, or ice crystals).
Icing conditions on the ground exist with an OAT or SAT below **_+5_**°C or colder
and where surface snow, slush, ice or standing water may be ingested by the
engines or freeze on engine nacelles, or engine sensor probes.
The wing icing inspection light must be operative **_prior_** to flight into known or
forecast icing conditions at night.
All anti-ice and de-ice systems must be **_ON_** in flight when operating in icing
conditions, except tail deice must be off when SAT is below -30°C.
92
**ICE AND RAIN PROTECTION**
## Footnote
Engine anti-ice must be ON during ground operations in icing
conditions, except selection of anti-ice on is prohibited for __ \_\_\_\_\_\_\_
after ground engine start (to ensure accurate RAT for takeoff). If engine
anti-ice was inadvertently turned ON prior to 1 minute of engine
operation, the anti-ice must be turned off for __ \_\_\_\_\_\_\_\_ before turning
it back on. If minor engine vibrations are felt or heard during ground
operations, the crew must momentarily increase engine speed (typically
20-30% N1) to assist with shedding the accumulated ice from the
spinner, fan, and stators.
**ICE AND RAIN PROTECTION**
## Footnote
Engine anti-ice must be ON during ground operations in icing
conditions, except selection of anti-ice on is prohibited for **_1 minute_**
after ground engine start (to ensure accurate RAT for takeoff). If engine
anti-ice was inadvertently turned ON prior to 1 minute of engine
operation, the anti-ice must be turned off for **_2 minutes_** before turning
it back on. If minor engine vibrations are felt or heard during ground
operations, the crew must momentarily increase engine speed (typically
20-30% N1) to assist with shedding the accumulated ice from the
spinner, fan, and stators.
93
**ICE AND RAIN PROTECTION**
## Footnote
When SAT is below \_\_°C, the wing and engine anti-ice systems may be
operated in the ENG ONLY position if it can be visually verified that no
ice is accumulating.
**ICE AND RAIN PROTECTION**
## Footnote
When SAT is below **_-40_**°C, the wing and engine anti-ice systems may be
operated in the ENG ONLY position if it can be visually verified that no
ice is accumulating.
94
**ICE AND RAIN PROTECTION**
## Footnote
Failure to operate engine anti-ice may result in amber ENG CTRL SYS
FAULT messages due to ice accumulation on the engine \_\_\_\_\_\_\_\_
probe.
**ICE AND RAIN PROTECTION**
## Footnote
Failure to operate engine anti-ice may result in amber ENG CTRL SYS
FAULT messages due to ice accumulation on the engine **_PT2/TT2_**
probe.
95
**ICE AND RAIN PROTECTION**
Minimum temperature for operation of tail deicing boots (SAT)
**ICE AND RAIN PROTECTION**
Minimum temperature for operation of tail deicing boots (SAT)
**-30°C**
96
**ICE AND RAIN PROTECTION**
Minimum airspeed for sustained flight in icing conditions (except takeoff,
approach, and landing) is ____ KIAS. If wing anti-ice protection has failed
and/or ice has accumulated on the wing leading edge, maintain ____ KIAS
minimum until approaching to land and disengage the autopilot prior to
extending flaps or reducing airspeed below ____ KIAS.
**ICE AND RAIN PROTECTION**
Minimum airspeed for sustained flight in icing conditions (except takeoff,
approach, and landing) is **_160_** KIAS. If wing anti-ice protection has failed
and/or ice has accumulated on the wing leading edge, maintain **_160_** KIAS
minimum until approaching to land and disengage the autopilot prior to
extending flaps or reducing airspeed below **_160_** KIAS.
97
**ICE AND RAIN PROTECTION**
In icing conditions, operating the airplane at other than flaps 0° and
landing gear up for an extended period of time (except approach and
landing) is \_\_\_\_\_\_\_.
**ICE AND RAIN PROTECTION**
In icing conditions, operating the airplane at other than flaps 0° and
landing gear up for an extended period of time (except approach and
landing) is **_prohibited_**.
98
**ICE AND RAIN PROTECTION**
Minimum engine N2 speed for effective wing anti-icing
**ICE AND RAIN PROTECTION**
Minimum engine N2 speed for effective wing anti-icing
**75% N2**
99
**ICE AND RAIN PROTECTION**
Operation in severe icing is \_\_\_\_\_\_\_\_\_. The airplane has not been
designed or certified to provide protection against severe icing
conditions, including freezing drizzle, freezing rain, or severe conditions
of mixed or clear ice.
**ICE AND RAIN PROTECTION**
Operation in severe icing is **_prohibited_**. The airplane has not been
designed or certified to provide protection against severe icing
conditions, including freezing drizzle, freezing rain, or severe conditions
of mixed or clear ice.
100
**ICE AND RAIN PROTECTION**
## Footnote
Severe icing conditions that exceed those for which the airplane is
certificated shall be determined by the following visual cues:
1. Unusually extensive ice accumulation on the airframe and \_\_\_\_\_\_\_\_\_
in areas not normally observed to collect ice (such as the outboard
1/3 of forward \_\_\_\_\_\_\_\_).
2. Unusual accumulation of ice on the upper surface of the \_\_\_\_\_
(significant accumulations on the heated surfaces, ridge formations
running inboard to outboard on the upper surface, runback ice
extending more than 18 inches aft of the heated leading edge).
**ICE AND RAIN PROTECTION**
## Footnote
Severe icing conditions that exceed those for which the airplane is
certificated shall be determined by the following visual cues:
1. Unusually extensive ice accumulation on the airframe and **_windshield_**
in areas not normally observed to collect ice (such as the outboard
1/3 of forward **_windshield_**).
2. Unusual accumulation of ice on the upper surface of the **_wing_**
(significant accumulations on the heated surfaces, ridge formations
running inboard to outboard on the upper surface, runback ice
extending more than 18 inches aft of the heated leading edge).
101
**ICE AND RAIN PROTECTION**
## Footnote
If one or more of these visual cues exist:
1. Use of the autopilot is \_\_\_\_\_\_\_\_\_\_.
2. Immediately request priority handling from Air Traffic Control to
facilitate a route or altitude change to exit the icing conditions.
3. Leave flaps in ______ position, do not extend or retract.
4. Avoid abrupt and excessive maneuvering that may aggravate control
problems.
5. If unusual or uncommanded roll control movement is observed,
reduce \_\_\_\_\_\_\_\_\_\_.
**ICE AND RAIN PROTECTION**
## Footnote
If one or more of these visual cues exist:
1. Use of the autopilot is **_prohibited_**.
2. Immediately request priority handling from Air Traffic Control to
facilitate a route or altitude change to exit the icing conditions.
3. Leave flaps in **_current_** position, do not extend or retract.
4. Avoid abrupt and excessive maneuvering that may aggravate control
problems.
5. If unusual or uncommanded roll control movement is observed,
reduce **_angle-of-attack_**.
102
**ICE AND RAIN PROTECTION**
## Footnote
Since the autopilot, when installed and operating, may mask tactile cues
that indicate adverse changes in handling characteristics, use of the
autopilot is prohibited when:
1. Unusual ________ trim is required while the airplane is in icing
conditions.
2. ________ \_\_\_\_\_\_ warnings are encountered while the airplane is in icing
conditions.
**ICE AND RAIN PROTECTION**
## Footnote
Since the autopilot, when installed and operating, may mask tactile cues
that indicate adverse changes in handling characteristics, use of the
autopilot is prohibited when:
1. Unusual **_lateral_** trim is required while the airplane is in icing
conditions.
2. **_Autopilot trim_** warnings are encountered while the airplane is in icing
conditions.
103
**ADS-B OUT OPERATION**
## Footnote
When ADS-B Out is required by operating rule, the following limitations
apply:
1. ______ must be selected as the operating transponder, unless an
applicable emergency/abnormal procedure requires the selection of
ATC1.
2. One FMS CDU must display the primary TUNE (1/2) page and the
pilot must periodically check it for an amber _____ \_\_\_\_ message,
indicating an ADS-B Out failure condition.
**ADS-B OUT OPERATION**
## Footnote
When ADS-B Out is required by operating rule, the following limitations
apply:
1. **_ATC2_** must be selected as the operating transponder, unless an
applicable emergency/abnormal procedure requires the selection of
ATC1.
2. One FMS CDU must display the primary TUNE (1/2) page and the
pilot must periodically check it for an amber **_XPDR FAIL_** message,
indicating an ADS-B Out failure condition.
104
**EMERGENCY BUS**
## Footnote
Items on the emergency bus are:
**EMERGENCY BUS**
## Footnote
Items on the emergency bus are:
105
**CONVERTED BUS**
## Footnote
Items not on the converted bus are:
**CONVERTED BUS**
## Footnote
Items not on the converted bus are:
