G-IV General and Limitations Flashcards
(212 cards)
1
Q
Steering Limits:
1) Steering Wheel Limits
2) Rudder Pedal Limits
3) Maximum Steering Angle
4) Minimum Taxi Strip Width For A 180 Degree Turn
A
1) 80 +/- 2 Degrees
2) 7 +/- 1 Degrees
3) 82 Degrees
4) 54.2 Feet (Based on a maximum nose wheel deflection of 80 degrees +2)
2
Q
Steering Wheel Limits
A
80 +/- 2 Degrees
3
Q
Rudder Pedal Limits
A
7 +/- 1 Degrees
4
Q
Maximum Steering Angle
A
82 Degrees
5
Q
Minimum Taxi Strip Width For A 180 Degree Turn
A
54.2 Feet
Based on a minimum nose wheel deflection of 80 degrees + 2
6
Q
General Dimensions:
1) Length
2) Width (wingspan)
3) Height
4) HSTAB Width
5) Fuselage Outside Cross Section
6) Fuselage Inside Cross Section
7) Wing Dihedral
8) Wing Sweep Angle
A
1) 88 Feet 4 Inches
2) 77 Feet 10 Inches
3) 24 Feet 5 1/8 Inches (height will be higher with a SATCOM antenna installed on the top of the vertical fin)
4) 32 Feet
5) 94 Inches
6) 88 Inches
7) 3 Degrees
8) Approximately 27 Degrees
7
Q
Aircraft Length
A
88 Feet 4 Inches
8
Q
Aircraft Width (Wingspan)
A
77 Feet 10 Inches
9
Q
Aircraft Height
A
24 Feet 5 1/8 Inches
height will be higher with a SATCOM antenna installed on top of the vertical fin
10
Q
HSTAB Width
A
32 Feet
11
Q
Fuselage Outside Cross Section Width
A
94 Inches
12
Q
Fuselage Inside Cross Section Width
A
88 Inches
13
Q
Wing Dihedral
A
3 Degrees
14
Q
Wing Sweep Angle
A
Approximately 27 Degrees
15
Q
How does the construction of the radome minimize lightening strike damage?
What is it constructed of?
A
It contains conductors.
It is constructed of fiberglass honeycomb.
16
Q
Will there be any warning to the crew if there is improper main door and baggage door seal pressures?
A
On aircraft having ASC 439 incorporated, a door seal warning system is installed.
17
Q
What keeps the main door closed?
A
6 sliding bayonets mechanically linked to the internal and external primary locking handles.
One bayonet activates the pressurization, and others control circuits within the hydraulic system and the “cabin doors” warning light in the cockpit.
18
Q
Regarding the air stair door, how is proper bayonet seating ascertained?
A
By a triangular pattern of orange dot.
If orange dots are not visible, it is possible that the dot has worn off or that it is obscured by lubricant, etc. The orange dot pattern is painted over a notch on the bayonet. If the notch is visible, the bayonet is extended properly into its receptacle.
19
Q
How many main entrance door lock switches are on the air stair door?
What are they for?
A
3
They are utilized to deactivate the auxiliary pump after the door is closed. The circuit is broken as the door is locked by the sliding bayonets physically actuating the doorlock switches.
20
Q
Where does power for the control system of the airstair door come from?
A
By the essential DC bus through the DOOR CONT WARN circuit breaker located in the copilot’s overhead circuit breaker panel.
21
Q
How do you close the door from outside the aircraft?
A
The external (guarded) battery switch is used to power the essential DC bus which will allow the OUTSIDE DOOR SWITCH to close the main door. CAUTION: After door is closed and locked, the external battery switch must be placed OFF to prevent a continuous drain on the battery.
On SNs 1156 and subsequent the essential DC bus is powered at the same time the outside door switch is activated so there is no need to use the outside battery switch.
22
Q
What indications will there be if the external battery switch is left on?
A
Internal:
Blue EXT BATT SWITCH ON CAS message.
EXT BATT SW capsule on the overhead annunciator panel illuminated.
External:
Bottom beacon light will be on.
23
Q
What keeps the baggage door closed?
A
4 Bayonets.
One controls the door sealing mechanism, and another controls the micro switch for the CABIN DOORS message.
24
Q
How is the space between the panels on the fixed windows kept defogged?
A
By a desiccator system.
25
Regarding the wing tank design, how is corrosion prevented?
The tanks are over coated with polyurethane.
26
What is the output of each of the engine driven alternators?
115 VAC, 3 Phase, 30 KVA.
It is variable frequency (varies with engine power).
Therefore, it is sent to Variable Speed Constant Frequency (VSCF) converters (2) located in the aft compartment so the power can be stabilized and regulated.
The power to the converters is then rectified to DC (270 VDC POR).
Then it is converted back to controlled AC (115 VAC, 400 Hz, 3 Phase, 23 KVA).
There is also DC output from the converters (28 VDC, 250 Amps).
27
What engines are installed on the G IV?
2 Rolls Royce Tay 611-8 engines.
| They are twin spool, axial flow bypass turbofans.
28
Regarding the aircraft engines, what does "Tay" mean, and why was it chosen for the name of the powerplant?
The River Tay is the longest river in Scotland and the seventh longest in the United Kingdom.
The use of river names (Trent, Nene, Avon, Tay, Conway, Spey, etc.) was introduced with the earliest Rolls jet engines to reflect their nature: a steady flow of power rather than the pulses of a piston engine.
Roll-Royce named their piston engines after birds if prey (e.g. Merlin, Peregrine, Kestrel, Vulture, and Buzzard).
29
What is the guaranteed minimum thrust rating of the main engines?
The Rolls-Royce Tay 611-8 engines have a guaranteed minimum thrust rating of:
13,850 lbs.
(ISA, Sea Level, Static)
30
What APU is installed on the G IV?
1) The Honeywell GTCP36-100[G]
- OR -
2) The Honeywell GTCP36-150[G] on some later air craft (ASC 465)
(The "G" simply stands for "Gulfstream")
31
What are the hydraulic systems on the G IV?
1) Combined - powered by the left engine hydraulic pump.
2) Flight - powered by the right engine hydraulic pump (remember "flight is right").
3) Utility - (PTU).
4) Auxiliary.
32
What conditions must be met for the utility pump to operate automatically when it is armed?
1) Combined system pressure less than 800 psi.
2) Flight system pressure more than 2000 psi.
3) Flight system fluid temp less than 220 degrees Fahrenheit.
4) Combined fluid is available.
Also, if flight system pressure falls below 1730 psi, the priority valve will close, causing utility pressure to go to zero. Placing the utility pump switch to ON will not restore the utility system.
33
How can the brake system be controlled from the cockpit?
Electrically or Hydraulically
- -The Brake by Wire (BBW) system uses an electrical signal to meter brake pressure.
- -The Hydromechanical Analog Brake (HMAB) system uses a hydraulic signal to meter brake pressure.
34
How is hydraulic power supplied to the brake system?
By the combined, utility or auxiliary system for both BBW and HMAB systems.
35
What controls the hydraulic stall barrier operation?
Angle of Attack inputs
36
What systems use bleed air?
```
Remember "TEA-PADS & Water"
T = TAT Probe Aspirator.
E = Engine Starter System.
A = Air Conditioning (ECS Packs).
P = Pressurization (ECS Packs).
A = Anti-Ice (Cowl & Wing).
D = Door Seal Systems.
S = Servo Control Air.
Water = Cabin Water System Pressure.
```
37
What engine stages provide bleed air?
7th or when needed 12th stage.
38
How are the cabin windows defogged?
By desiccant filters.
39
Where do the engine fire detection sensors monitor the engine temperatures?
They monitor the engine exterior temps in engine fire zone one, which comprises:
- Compressor,
- Combustion, and
- Turbine sections
40
How is engine fire extinguishing accomplished?
Through a two-shot, electrically fired chlorotrifluorobromomethane (CF3Br) system, consisting of two single-shot containers installed in the tail compartment.
41
How many pitot systems are on the aircraft?
| Where are their sources or pitot tubes located?
3 Independent Systems
- 2 Primary: Pilot & Copilot.
- 1 Standby.
Pitot Locations:
- Pilot and Copilot: On top of the nose, forward of the windshield.
- Standby: Left side of nose below AOA probe.
42
How many static systems are on the aircraft?
| Where are the static sources located?
4 Independent Systems
- 2 Primary: Pilot & Copilot.
- 1 Standby: Standby Altimeter and Airspeed Indicators.
- 4th System: Used by the cabin differential indicator on the overhead panel.
Static Sources:
- Each system has 2 sources (one on each side).
- Primary systems use upper ports, others use lower.
43
What type of capability does the autopilot provide?
The A/P uses 2 flight guidance computers to provide fail-operational capability.
44
What S/N aircraft changed from a G IV to either a G300 or a G400?
S/N 1500 & After
45
What is a G300 & G400?
G300: A production G IV-SP with ASC 436.
G400: A production G IV-SP with ASC 440.
46
Is the External BATT Switch required to be selected ON for door retraction?
On S/N 1000-1155: Yes.
On S/N 1156 and subsequent: No.
47
What bus is required to have electrical power for the NAV lights to work?
L Main AC
48
Which S/N G IV aircraft have the logo lights installed?
S/N 1280 and Later
49
Landing Light Limitation
Steady ON limited to 5 minutes duration on the ground.
50
Vmo / Mmo
| S/N 1000 and subs. without ASC 61
- - 340 KCAS to 28,000 feet.
- - Mach .85 at 28,000 feet linear change to Mach .88 at 34,000 feet.
- - Mach .88 from 34,000 feet to 43,500 feet.
- - Mach .88 at 43,500 feet linear change to Mach .874 at 45,000 feet.
51
Vmo / Mmo
| S/N 1000-1214 with ASC 61
- - 320 KCAS to 30,000 feet.
- - Mach .84 at 30,000 feet linear change to Mach .86 at 34,000 feet.
- - Mach .86 from 34,000 feet to 43,500 feet.
- - Mach .86 at 43,500 feet linear change to Mach .854 at 45,000 feet.
52
Flaps Extended Speeds
10 Degrees = 250 Kts. / .60 MT
20 Degrees = 220 Kts. / .60 MT
39 Degrees = 170 Kts. / .60 MT
(180 Kts. / .60 MT for S/N 1214 & subs. Or S/N 1000-1213 with ASC 190) (G IV-SP)
53
Gear Extended Speed
250 Kts. / .70 MT
| Gear Doors Opened or Closed
54
Gear Extension / Retraction Speed
225 Kts. / .70 MT
55
Alternate Gear Extension Speed
175 KCAS
56
Maneuvering Speed (Va)
170 KCAS
| 206 KCAS
S/N 1214 and subs. Or ASC 190
57
Turbulence Penetration Speed
270 KCAS / .75 MT
58
Engine Airstart Envelope
| Speed & Altitude
200-324 KCAS
25,000 Feet or Below
59
Manual Reversion Airspeed Limit
250 KCAS max
60
APU Inflight Start Envelope
Guaranteed Starting:
- - Altitude: 15,000 Feet and Below
- - Airspeed: 250 KCAS max
Guaranteed Running:
- - Altitude: 30,000 Feet and Below
- - Airspeed: Vmo / Mmo
61
Windshield Wipers Speed Limitation
200 KCAS
62
Tire Speed Limits
| S/N 1000-1213 Without ASC 190/266
Nose Tires = 182
Main Tires = 182
Overall Limit = 182
63
Tire Speed Limits
| S/N 1000-1213 With ASC 266
Nose Tires = 182
Main Tires = 195
Overall Limit = 182
64
Tire Speed Limits
| S/N 1000-1213 With ASC 190
Nose Tires = 195
Main Tires = 195
Overall Limit = 195
65
Tire Speed Limits
| S/N 1214 and Subsequent
Nose Tires = 195
Main Tires = 195
Overall Limit = 195
66
Wing Vortex Generator Not Installed
| Speed Limitation
0.80 MT
67
Mach Trim / Electric Elevator Trim Inoperative
| Speed Limitation
0.75 MT
68
Yaw Damper Inoperative Above 18,000 Feet
| Maintain At Least What Airspeed?
220 KCAS
69
Reverse Thrust Cancellation
| Initiate At What Airspeed?
70 KCAS
- - For landing on contaminated runways:
- Both engines in max reverse above 70 KCAS.
- Both engines in reverse idle (reversers deployed) below 50 KCAS.
70
Thrust Reverser Deployed In-Flight Airspeed
200 KCAS
71
Vmca (Minimum control speed air)
104 KCAS
72
Vmcg (Minimum control speed ground)
111 KCAS
73
Maximum Ceiling
45,000 Feet
74
Max Altitude Yaw Damper Inop
41,000 Feet
75
Max Altitude with an Engine Bleed Air Switch Off
41,000 Feet
76
Max Altitude for an Inflight Engine Airstart
25,000 Feet
77
Max Gear Extended Altitude
20,000 Feet
78
Max Altitude for Flaps 39 Degrees
20,000 Feet
79
Max Takeoff and Landing Airport Elevation
15,000 Feet
80
Max Altitude for APU Start
| Max Airspeed for APU Start
15,000 Feet
| 250 KCAS
81
APU Temp Limits During Start
| 36-100 APU
0% to 60% = 988 Degrees Celsius
60% to 100% = 821-732 Degrees Celsius (linear decrease)
Maximum Running = 732 Degrees Celsius
82
APU Temp Limits During Start
| 36-150 APU
0% to 50% = 973 Degrees Celsius
51% to 87% = 973-732 Degrees Celsius (linear decrease)
87% to 100% = 732 Degrees Celsius
Maximum Running = 732 Degrees Celsius
83
APU Max EGT Running
732 Degrees Celsius
84
APU Max EGT with APU Air On
680 Degrees Celsius
85
APU Operating RPM
100% +/- 3%
86
APU Overspeed RPM
110%
When the OVSP TEST-STOP switch is pushed an overspeed signal of 114% RPM is sent to the ECU, prompting the ECU to shut down the APU.
87
APU
| Record Time Operating Above
FL300
| For the 36-150 [G] APU
88
Continuous operation of the APU starter when powered by the airplane batteries
```
3 Consecutive Starts
30 Seconds Per Start
20 Minutes For Starter Cool Down
3 Additional Start Attempts May Be Made
1 Hour Cool Down Before Next Full Starter Cycle
```
89
Continuous operation of the APU starter when powered by an external DC source
```
2 Consecutive Starts
15 Seconds Per Start
20 Minutes For Starter Cool Down
2 Additional Start Attempts May Be Made
1 Hour Cool Down Before Next Full Starter Cycle
```
90
Successful consecutive APU starts limited to:
6 at 10 minute intervals per start
91
APU Fire Bottle Capacity
2.5 pounds of CF3Br (Halon 1301).
| Charged with nitrogen to 600 +50/-25 at 70 degrees Fahrenheit.
92
Engine Continuous Ignition (Airstart) Limitations
S/N 1000-1249 without ASC 304:
- -5 minutes on - 30 minutes off.
- -No limitation if used in a 30 second on-30 second off cycle.
S/N 1250 & subs. or S/N 1000-1249 with ASC 304:
--No duty cycle time limitation with ASC 304.
93
Maximum Engine Fuel Temp
90 Degrees Celsius
| 120 Degrees Celsius up to 15 minutes is permissable
94
Minimum Engine Fuel Temp
-40 Degrees Celsius for starting
95
Maximum Oil Inlet Temp
105 Degrees Celsius
| Up to 120 Degrees Celsius for a max of 15 minutes is permissable
96
Minimum Oil Temp For Starting
-40 Degrees Celsius
97
Minimum Oil Temp For Operating The Power Levers
-30 Degrees Celsius
98
Minimum Oil Pressure At Idle
16 PSI
99
Minimum Acceptable Oil Pressure For Takeoff
| At Takeoff Power
30 PSI
100
Minimum Oil Pressure Required To Complete Flight
At Max Continuous
(97.5% HP) -- 25 PSI
(92% HP) -- 22 PSI
(84% HP) -- 19 PSI
(76% HP) -- 16 PSI
101
Minimum Oil Pressure Required To Complete Flight
| At Max Continuous (97.5% HP)
25 PSI
102
Minimum Oil Pressure Required To Complete Flight
| 92% HP
22 PSI
103
Minimum Oil Pressure Required To Complete Flight
| 84% HP
19 PSI
104
Minimum Oil Pressure Required To Complete Flight
| 76% HP
16 PSI
105
Takeoff Power Limitation
-- Full power for takeoff is shown in "RATED EPR SETTINGS FOR TAKEOFF THRUST" charts.
-- Takeoff EPR must not exceed rated value by more than 0.01.
106
Engine Starter Duty Limits
```
30 Seconds ON
3 Minutes OFF
30 Seconds ON
3 Minutes OFF
30 Seconds ON
15 Minutes OFF
```
107
Engine Fuel Flow Limitation
No Limitations
108
Engine Pressure Ratio (EPR) Limits
None
109
EPR Pilot Selectable Command Marker Limits
0.85 to 2.0
110
Fuel Capacity
G IV / G400 :
29,500 Pounds (4370 gal.)
G300 :
26,900 Pounds
(Fuel in excess of these limits is permitted if max ramp weight and/or takeoff weight are not exceeded and CG is within limits)
111
Fuel Capacity
| G IV / G400
29,500 Pounds (4370 gal.)
(Fuel in excess of this limit is permitted if max ramp weight and/or takeoff weight are not exceeded and CG is within limits)
112
Fuel Capacity
| G300
26,900 Pounds
(Fuel in excess of this limit is permitted if max ramp weight and/or takeoff weight are not exceeded and CG is within limits)
113
Fuel Tank Temp Limits
| Min and Max
Minimum = -40 Degrees Celsius
Maximum = 54 Degrees Celsius
114
Maximum Fuel Imbalance
55,000 Pounds Gross Weight or Less:
2,000 Pounds
60,500 Pounds Gross Weight or More:
400 Pounds
(Sliding scale from 55,000 to 60,500)
115
Maximum Load Accelerations
Flaps Up = -1 to 2.5 Gs
Flaps Down = 0 to 2 Gs
116
Minimum Flight Crew
Maximum Passengers
Maximum Occupants
2
19
22
117
Maximum Tailwind for Takeoff or Landing
10 Knots
118
When is there no tailwind allowed for takeoff?
-- On contaminated runways,
Or
-- For FLEX takeoffs
119
Maximum Demonstrated Crosswind Component
24 Knots
-- Per the G IV OIS-9:
"For the G IV, the maximum demonstrated crosswind was 24 knots. The G IV has been tested in up to 30 knots of crosswind but the FAA did not observe those results." (Page 1)
120
Maximum Runway Slope
| Takeoff and Landing
+/- 2%
For Contaminated Runways:
- - Takeoff: Not greater than +1% (-2/+1)
- - Landing: Level or uphill only (-0/+2)
121
Maximum Cabin Pressure Differential
9.8 PSI
122
Maximum Cabin Pressure Differential for Taxiing, Takeoff or Landing
0.3 PSI
123
Altitude Limitation for Bleed Air
Do not operate above 41,000 feet without both engine bleeds ON, and each engine being bled by either the ACM Pack or Engine Cowl Anti-Ice.
124
Boost Pump Limitation
All operable fuel pumps shall be selected ON for all phases of flight unless fuel balancing is in progress.
125
Fuel Balancing Limitation
Fuel balancing may be accomplished by using the crossflow or intertank valve.
When balancing fuel through use of the crossflow valve, ensure that boosted fuel pressure is always available to the engines.
CAUTION: The engine will only run on suction fuel feed at or below 20,000 feet. Above 20,000 feet, the engine will run erratically and flame out if the crossflow is not open with at least one boost pump selected ON.
126
AOA Limitation
Angle-of-Attack (AOA) system may be used as reference.
Must be within the white band once forward airspeed is attained.
Shall not be used as a speed reference for takeoff rotation.
127
Stall Warning / Stall Barrier System Limitation
Dispatch with one Stall Warning / Stall Barrier system inoperative is allowed with reference to the MEL.
128
Yaw Damper Inoperative Prior To Takeoff Limitation
Max fuel quantity for takeoff = 9,000 pounds.
Below 18,000 feet: Maintain airspeed, as a function of fuel quantity.
If yaw damper fails with Mach trim compensation, observe speed limitations for both failures and limit altitude to 41,000 feet.
129
Engine Anti-Ice Pressure Limit
60 PSI
130
Operation of cowl anti-icing is required for taxi and takeoff when:
Static Air Temperature (SAT) is below +10 degrees Celsius (+50 degrees Fahrenheit) and visible moisture, precipitation, or wet runway are present.
Engine operation at 85% LP for 1 minute is recommended just prior to takeoff and at intervals of not more than 60 minutes under these temperature and moisture conditions.
131
Engine Ice Clearing Procedure
When taxiing or holding on the ground at low power in temperatures less than 1 degrees Celsius, engine operation at 85% LP for 1 minute is recommended just prior to takeoff and at intervals of not more than sixty (60) minutes under these temperature and moisture conditions.
132
The Amber "L-R COWL PRESS LOW" Warning CAS Message Will Occur When?
S/N 1000-1059 with ASC 51A and S/N 1060 and subsequent:
-- Pressure drops below 10+1 PSI.
S/N 1000-1189 with ASC 243 and S/N 1190 and subsequent:
-- Pressure drops below 4+1 PSI and after a 15 second delay.
133
Speed brakes are not approved with:
Flaps at 39 degrees or when landing gear is extended.
134
Takeoff is permitted with ground spoilers inoperative provided:
-- Anti-skid is operative,
and
-- 20 degrees flaps are used for takeoff.
135
Do not operate radar...
1) During refueling,
2) Within 300 feet (92 meters) of other refueling operations,
3) Within 49 feet (15 meters) of ground personnel with 24 inch antenna installed,
4) Within 33 feet (10 meters) of ground personnel with 18 inch antenna installed.
136
Landing Lights Limits
Ground operating time limit = 5 minutes.
Pulse lights = no limit.
137
Auto Throttle Limitations
Takeoff And Go-Around:
-- Prohibited when wing anti-ice is used.
Landing:
-- Disengage by 50 feet AGL.
138
Autopilot Limitations
Takeoff:
-- Do not engage below 200 feet AGL on takeoff.
Landing:
-- Disengage by 50 feet AGL.
Minimum altitude for autopilot coupled IMC VNAV operations is 300 feet AGL or 50 feet below the MDA, whichever is higher.
139
Static Ground Run Limitation
With crosswinds greater than 15 knots, stabilized engine operation in the band between 60% and 80% LP RPM fan speed is not permitted.
140
Airspeed and altitude limitations with flight power shutoff handle pulled or dual hydraulic system failure
Airspeed = 250 KCAS Maximum
Altitude = 25,000 Feet Maximum
141
Main Batteries
```
Two:
-- 24 Volt
-- 40 Amp/Hour
-- 20 Cell
-- NiCad
Batteries
```
142
Emergency Batteries
- - 2-8 Installed
- - 6 Amp/Hours
- - Approximately 40 Minutes
143
TRU
Transformer Rectifier Unit
- - 1 Installed
- - 300 Amp
- - 25-28 Volt
144
SEPS
```
SEPS = Standby Electric Power System
A.K.A. - ABEX or HMG
ABEX = American Brake Exchange
HMG = Hydraulic Motor Generator
-- 115 Volts AC - 5 KVA.
-- 28 VDC - 50 Amps.
-- Not capable of charging the batteries.
-- Located in the main wheel well.
-- Powered from the combined hydraulic system (with essential DC bus power available, the shutoff valve is energized closed; loss of essential DC bus power allows combined pressure to rotate the motor/generator).
```
145
E-Inverter
-- 1 Installed
-- 0.8 KVA (800 VA)
-- 115 VAC
-- 400 Hz
-- Phase A Only
-- Solid State Unit, Located Below The Floor
-- Powers The Essential AC Bus
-- Input power is from the essential DC bus (via automatic selection) or from the standby generator (via manual selection)
NOTE: The ESS AC BUS E INV switchlight, when illuminated, indicates a requested service only. The ESS voltmeter switchlight is the only verification of E Inverter operation.
146
Remote Power Supply
- - Power for the EPMP
- - 4 Sources of Power
- 1 From Each Aircraft Battery
- 2 From The Essential DC Bus
147
Maximum Ground Starting TGT
700 Degrees Celsius
| For 2 Seconds
148
Maximum Relighting (Airstart) TGT
780 Degrees Celsius
| For 2 Seconds
149
Maximum Takeoff And Maximum Go-Around
| LP%, HP% And TGT Degrees Celsius
```
Same for both (T/O & G/A):
-- LP% RPM = 95.5%
-- HP% RPM = 99.7%
-- TGT = 716-800 Degrees Celsius
(5 min. or 10 min. single engine)
```
150
Maximum Continuous:
| LP%, HP% and TGT Degrees Celsius
- - LP% = 95.5%
- - HP% = 97.5%
- - TGT = 715 Degrees Celsius
151
Minimum Idle HP% (Approach)
67% HP
152
Minimum Ground Idle HP%
46.6% HP
153
Maximum Reverse Engine Limits
-- HP - 88%
-- TGT - 695 Degrees Celsius
-- 1 Minute Every 30 Minutes
(S/N 1250 & subs. or S/N 1000-1249 with ASC 166 no limitation)
154
Maximum Overspeed Engine Operating Limitations
- - LP% = 98.3%
- - HP% = 102.6%
- - TGT = 801-820 Degrees Celsius
- - Time Limit = 20 Seconds
155
Maximum Zero Fuel Weight
S/N 1000-1213:
46,500 Pounds
S/N 1000-1213 With ASC 61 Or ASC 190:
49,000 Pounds
S/N 1214 And Subsequent:
49,000 Pounds
156
Maximum Zero Fuel Weight
| S/N 1000-1213
46,500 Pounds
| Unless ASC 61 or ASC 190 is installed, then the Max Zero Fuel Weight is 49,000 pounds
157
Maximum Zero Fuel Weight
| S/N 1214 And Subsequent
49,000 Pounds
158
Maximum Ramp Weight
S/N 1000-1213:
- 73,600 Pounds
S/N 1000-1213 with ASC 190 and S/N 1214 & subsequent:
- 75,000 Pounds
S/N 1500 & subsequent with ASC 436 (G300):
- 72,400 Pounds
S/N 1500 & subsequent with ASC 440 (G400):
- 75,000 Pounds
159
Maximum Ramp Weight
| S/N 1000-1213
73,600 Pounds
| Without ASC 190
160
Maximum Ramp Weight
| S/N 1000-1213 with ASC 190 and S/N 1214 & subsequent
75,000 Pounds
161
Maximum Ramp Weight
G300
(S/N 1500 and subsequent with ASC 436)
72,400 Pounds
162
Maximum Ramp Weight
G400
(S/N 1500 and subsequent with ASC 440)
75,000 Pounds
163
Maximum Structural Takeoff Weight
S/N 1000-1213:
- 73,200 Pounds
S/N 1000-1213 with ASC 190 and S/N 1214 & subsequent:
- 74,600 Pounds
S/N 1500 and subsequent with ASC 436 (G300):
- 72,000 Pounds
164
Maximum Structural Takeoff Weight
| S/N 1000-1213
73,200 Pounds
| Without ASC 190
165
Maximum Structural Takeoff Weight
| S/N 1000-1213 with ASC 190 and S/N 1214 & subsequent
74,600 Pounds
166
Maximum Structural Takeoff Weight
G300
(S/N 1500 and subsequent with ASC 436)
72,000 Pounds
167
Maximum Structural Landing Weight
S/N 1000-1213:
- 58,500 Pounds
S/N 1000-1213 with ASC 190 and S/N 1214 and subsequent:
- 66,000 Pounds
168
Maximum Structural Landing Weight
| S/N 1000-1213
58,500 Pounds
| Without ASC 190
169
Maximum Structural Landing Weight
| S/N 1000-1213 with ASC 190 and S/N 1214 & subsequent
66,000 Pounds
170
Variations of the G I V
- G IV
- G IV-SP
- G300
- G400
- C-20 G/H
171
Display Unit Cooling Fans
2 Cooling Fans
Fan #1: DU #1, #3 and #5
Fan #2: DU #2, #4 and #6
```
Remember #1 = Odd # DUs
#2 = Even # DUs
```
172
What do the pilots use to control the IRUs (or IRSs)?
The Mode Select Unit
173
What is the "primary job" of the IRSs?
Heading and Attitude
174
On the Audio Control Panel there is a button labeled "FILT".
| What does that stand for?
Filter
| Takes morse code out
175
FMS Inputs
Priority #1 = GPS
Priority #2 = DME/DME
Priority #3 = VOR/DME
Priority #4 = IRS
176
FMS Winds
PPOS to 200 NM = 100% Sensed
200 NM to 400 NM = 50% Sensed / 50% Entered
400 NM & Beyond = 20% Sensed / 80% Entered
177
Vref Rule of Thumb
First, find aircraft weight.
(PROGRAM page 2 or PERF INITIAL page 5)
```
Example: 55,000 Pounds
Put a 1 on the left and divide by 1000:
- 155 (Vref for flaps 0)
Subtract 10:
- 145 (Vref for flaps 10)
Subtract 5:
- 140 (Vref for flaps 20)
Subtract 5:
- 135 (Vref for flaps 39)
```
Target Approach Speed = Vref + 10.
The closer to sea level, the more accurate this rule of thumb will be.
178
What happens when you press TO/GA?
5 Things:
1) A/P - Disconnect
2) A/T - G/A Power
3) F/D - 12 Degrees Pitch Up
4) LAT Mode - Cancels (holds "wings level")
5) Flight Plan - Advances to Missed Aprroach
179
What will cause the A/T to be inhibited?
5 Things:
1) A/T ARM not "ON" on Flight Guidance Panel.
2) Both engines not running.
3) EPR below 1.17.
4) Isolation valve open.
5) Any A/T Disengage activated.
180
Pop-Up Checklists
1) APU Fire
2) Engine Fire
3) Engine Hot
4) T/R Unlock
5) Cabin Press Low
```
Remember: HOT-FIRE2 - RC
HOT = Engine Hot
FIRE2 = Engine Fire; APU Fire
R = Thrust Reverser Unlocked In Flight
C = Cabin Pressure Low
```
181
Systems With Their Own Test Light Circuits
1) EPMP
2) Cabin Press Manual Lamp
3) STBY Fuel Quantity
4) DBDIs (2)
5) Fire Handles (2)
6) HP Fuel Cocks (2)
Remember 3 + 3 squared:
3 = items 1-3
3 squared = items 4-6
OR:
Remember:
- - 2 on overhead panel (1 & 2)
- - 3 on instrument panel (3 & 4)
- - 4 on pedestal (5 & 6)
182
Approach Idle
```
Low Range (48%):
When any of the following occurs:
1) Nutcracker in a ground mode,
2) Wheel spin-up greater than 65 mph (57 Kts), or
3) Flaps less than 22 degrees
```
High Range (67% HP):
When:
1) In flight, and
2) Flaps greater than 22 degrees
183
Autospeeds On Takeoff
- V2 until V2+10.
- V2+10 until flap change.
- 200 until vertical mode change.
- Then via PERF INIT climb schedule.
184
Autospeeds On Descent
- Above 10,000 = PERF INIT climb schedule.
| - Below 10,000 = 240 (240 will be displayed if 250/10,000 is programmed).
185
During the arrival phase of flight, when will the autospeeds change from cruise speed to 200?
15 Nautical Miles (Track Miles) From The MAP (or runway).
186
Should you program "Direct To" anything in the FMS while still on the ground (i.e. on T/O tower clears you direct to a VOR in your flight plan)?
Why, or why not?
No.
| You will lose all of your PERF data including all of your T/O numbers.
187
What is a dead-spot in the rheostats known as?
A Non-Engineered Dead Spot (NEDS).
188
Where can you find a list of items powered by the E-Batts?
QRH Page EA-26
Remember:
- Unlucky number = 13.
- Remember, if you are down to E-Batts, you are really, really unlucky (unlucky X 2: 13 X 2).
189
What items are powered by the E-Batts?
?
190
What temperatures will trigger the battery cooling fan?
On at 90 degrees Fahrenheit.
| Off at 75 degrees Fahrenheit.
191
What is the AUX power priority?
1) APU
2) AC
3) DC
192
What power sources can start the APU?
- External DC (not external AC).
| - Main batteries.
193
How many fans do the converters have?
5 Each
194
What type of power does the SEPS produce?
SEPS, HMG, or ABEX
- - AC: 115 Volt 3 Phase AC at 5 KVA.
- - DC: 28V, 50 Amps.
HMG - AC - TRU - DC
HMG - DC - E-Inv - AC
(This was done this way in order to produce predictable, stable electric power)
Powers only the ESS AC & ESS DC busses.
195
What exactly is powered by the SEPS?
See page EA-4 in the QRH
| - "All essential AC and DC bus powered equipment..."
196
EDS Power Sources
```
DU #1: ESS DC
DU #2: R Main DC
DU #3: ESS DC
DU #4: R Main DC
DU #5: L Main DC
DU #6: R Main DC
```
"Eat Ravioli, Eat Ravioli, Love Ravioli"
197
Symbol Generator Control
| Power Sources
```
#1 (left knob): ESS DC
#3 (middle knob): L Main DC
#2 (right knob): R Main DC
```
"Everybody Loves Ravioli"
198
Dual Alternator / Converter Fail
| "Memory Items"
```
Remember "NAACP"
NAA = Normal-ALT-ALT
(Symbol Generators)
C = Crossflow (OPEN)
P = Pumps (Fuel Boost Pumps)
(One MAIN ON only, all others OFF)
```
199
If you have both batteries fully charged, how much electrical power (time) do you have after a dual alternator/converter failure?
20 Minutes
| If the SEPS cannot be used
200
Where can you find a list of items powered (electrically) by each different circuit or bus?
QRH page S-13 and following
| Remember, if you have to go back to the Blue Supplemental QRH section, you are having bad luck - hence, page # is 13
201
What does it mean if the ESS DC Bus AUTO, LEFT MAIN and BATT switch capsules are illuminated without the BATT 1 and BATT 2 switches illuminated or the BATT ON BUS message illuminated?
See QRH page EA-21
| - The K20/K22 relay experienced a failure of one of the two relay-poles. Report for maintenance action.
202
What values on the EPMP for AC Volts, Freq, and DC Volts will not trigger the out-of-limit range markings (red bar)?
AC Voltmeter: 100-125 Volts = No Red Bar.
Frequency: 380-420 Hz = No Red Bar.
DC Voltmeter: 26.0-30.9 VDC = No Red Bar.
Percent Power Meter: Below 101% = No Red Bar.
203
How many CAS messages can be displayed at one time?
23
204
What battery connects to the ground service bus?
Whenever the Ground Service Switch is selected ON the Ground Service Bus receives it's power from BATT #2.
205
When would you expect to see a Battery On Bus indication?
Remember "EAA"
E = ESS DC Bus powered by main batteries (manually or automatically).
A = APU Start.
A = AUX Pump ON (operating).
206
When the Emergency Power System is armed, when will the E-BATTS activate?
```
3 Conditions Will Turn On The E-BATTS:
(Remember "GEM")
G = G load of 2.5 or more,
E = ESS DC Bus loss of power (less than 20 volts),
M = Manually turning them on.
```
207
Where is the Remote Power Supply (RPS) located, and what does it power?
Location = Right Avionics Bay.
| It powers the EPMP switchlight, digit, and out-of-limit indicators.
208
External AC is capable of powering what busses?
With an external AC Power supply connected and operating, selecting the AUX Power switch and selecting at least one BATT Switch ON the AC Buses will be energized. The TRU will then be activated to power the DC Buses.
Also, battery charging is possible with External AC only (not with External DC).
209
What capabilities are lost if you lose the Flight Hydraulic System pressure?
```
Remember "PRAY":
P = PTU (Utility Pump)
R = Reverser (Right T/R)
A = Auto Pilot
Y = Yaw Damper
```
210
When armed, what will cause the Utility Pump to turn ON automatically?
Combined System failure (Amber CMB HYD FAIL CAS message) or combined system pressure falling to less than 800 psi.
Also, the Flight Hydraulic system will have to have:
1) At least 2000 psi, and
2) 220 degrees F or less fluid temp.
And, the Combined reservoir will have to have at least 1 gallon of hydraulic fluid in it.
211
What Flight Hydraulic system fluid temperature will activate the amber "FLT HYD HOT" CAS message?
More than 220 degrees Fahrenheit.
212
During engine start when will the "CMB HYD FAIL" CAS message extinguish?
As the Combined Hydraulic system pressure exceeds 1500 psi.
