Limitations Flashcards
0
Q
TOLD Runway slope Limits: +/-___%
A
+/-2%
1
Q
TOLD Altitude Limits: -_____ to _____ feet (pressure altitude)
A
-1000 ft to 10,000 ft (pressure altitude)
2
Q
TOLD Limiting tail wind component: ___ knots
A
10 knots
3
Q
TOLD Temperature limits: -___ C to +___ C
A
-54 C to 54 C
4
Q
Maximum zero fuel weight: _____ pounds
A
230,000 pounds
5
Q
Maximum taxi weight: _____ pounds
A
336,000 pounds
6
Q
Maximum takeoff weight (flaps down): _____ pounds
A
333,600 pounds
7
Q
Maximum in-flight weight (flaps up): _____ pounds
A
331,000 pounds
8
Q
Maximum inflight weight with the reserve tanks empty: _____ pounds
A
280,000 pounds
9
Q
Maximum normal landing weight (600 fpm sink rate): _____ pounds
A
247,000 pounds
10
Q
Maximum landing weight (360 fpm sink rate): _____ pounds
A
326,000 pounds
11
Q
N1 Continuous Operation
A
25% - 107%
12
Q
Maximum Allowable N1
A
110%
13
Q
N1 idle below ___% is a sign of possible engine malfunction
A
25%
14
Q
N2 Normal Idle Operation
A
58% - 62%
15
Q
N2 Continuous Operation
A
57% - 101%
16
Q
Maximum Allowable N2
A
106%
17
Q
Ground idle RPM is ___ - ___ N2, standard day, with no bleed air, generator or hydraulic pump loads
A
58% - 62%
18
Q
EGT Continuous Operation
A
340 C - 510 C
19
Q
EGT Caution
A
510 C - 575 C
20
Q
Maximum Allowable EGT
A
575 C
21
Q
During engine start, if EGT is rising rapidly or exceeds ___ C, shut down the engine
A
450 C
22
Q
On takeoff, an EGT between ___ - ___ C is not necessarily a malfunction to abort at high speed
A
575 - 600 C
23
Q
Oil Pressure Normal Operating Range
A
40 - 60 PSI
24
Undesirable Oil Pressure (Caution)
35 - 40 PSI
25
Minimum Oil Pressure (Idle)
It may decrease to ___ psi during rapid engine deceleration
35 PSI
30 psi
26
Maximum Oil Pressure
Following rapid advances of throttles to T/O or GA may indicate as high as ___ psi
60 PSI
65 psi
27
Oil Temperature Continuous Operation
40 - 132 C
28
Recommended Oil Temperature
80 - 100 C
29
10-Minute Max Operation Oil Temparature
132- 143 C
30
Maximum Allowable Oil Temperature
143 C
31
___ minute(s) on, ___ minute(s) off for 1st starting attempt
1; 1
32
___ minute(s) on, ___ minute(s) off for subsequent starting attempts
1; 5
33
Use of the engine ignition system should not exceed ___ minutes
10 minutes
34
Ignition should be set to _____ for takeoff, emergency descent, minimum fuel approach, any engine-out approach, and flight through volcanic ash
BOTH
35
Ignition should be set to _____ for turbulence, entry into icing, compressor stall recovery, and practice approach to stall recovery
1 or 2
36
Bleed Air System Normal Start Pressure Range
25- 60 PSIG
37
Cabin Air Duct Pressure Normal
4- 20 inches
38
Maximum Cabin Air Duct Pressure
20 inches
39
Maximum (inflight) Cabin Differential Pressure
8.6 PSI (+/- 0.15)
40
Cabin Differential Pressurization relief valve
9.42 PSI (+/- 0.15)
41
Utility Hydraulic System Precharge
2000 PSI
42
Utility Hydraulic System Maximum Pressure
3500 PSI
43
Utility Hydraulic System Pump output, no load
2850 - 3150 PSI
44
Utility Hydraulic System Minimum Pressure under load
2400 PSI
45
Brake Hydraulic System Precharge
750 PSI
46
Brake Hydraulic System Normal Range
750 - 3150 PSI
47
Brake Hydraulic System Maximum Pressure
3500 PSI
48
Auxiliary Hydraulic System Precharge
2000 PSI (not indicated on rudder gauge)
49
Maximum Auxiliary Hydraulic System Pressure (as read on rudder gauge)
3500 PSI
50
Auxiliary Hydraulic System Pump output, no load (as read on rudder gauge)
2750 - 3150 PSI
51
Auxiliary Hydraulic System Write-up required(as read on rudder gauge)
2200 - 1400 PSI
52
Auxiliary Hydraulic System Maintenance required (as read on rudder gauge)
1400 PSI or less
53
Auxiliary Hydraulic System Rudder deboost range (as read on rudder gauge)
2100 - 2400 PSI
54
Aircraft Generator Load, Continuous operation
261 amperes per generator
55
Aircraft Generator Load, 5-second operation
348 amperes
56
Aircraft Generator Frequency
400 (+/-20) hertz (as limited by using equipment)
57
Aircraft Generator Voltage
200 (+/-8) volts
58
External Power Frequency
400 (+/-20) hertz
59
External Power Voltage
200 (+/-8) volts
60
External Power Load
265 (+/-25) amperes for 5 to 7 secs, main receptacle only
61
Minimum Airplane Battery voltage for APU start
22 volts
62
Minimum Airplane Battery voltage for flight
24 volts
63
Emergency Airplane battery only operation
30 minutes
64
APU Normal operating speed
100% RPM
65
APU Overspeed
110% RPM
66
APU Underspeed
95% RPM
67
APU Normal Operating Temperature
330 C
68
APU Maximum Allowable Temperature
675 C
69
APU Caution Temperature (yellow)
605 C - 675 C
70
APU continuous load
348 amperes
71
APU 5-minute load
406 amperes
72
APU 5-second load
580 amperes
73
APU Generator Frequency
400 (+/-7) hertz
74
Minimum voltage for APU Start
22 volts
75
The APU battery is a ___ volt, 44 amp-hour nickel-cadmium unit located in the _____ main wheel well compartment
24
right
76
Maximum Operating Speed
350 KIAS from SL to 25,800 feet
| M .84 above 25,800 feet
77
Max airspeed with MACH trim inop (& emerg descent)
M .79; (M .825)
78
Do not exceed ___ KIAS with flaps extended to 14 degrees
223 KIAS
79
Do not exceed ___ KIAS with flaps extended to 25 degrees
215 KIAS
80
Do not exceed ___ KIAS with flaps extended to 40 degrees
200 KIAS
81
Do not exceed ___ KIAS with flaps extended to 50 degrees
195 KIAS
82
Landing Gear Normal Operating Speed
270 KIAS, M .83
83
Landing Gear Emergency Operating Speed
320 KIAS, M .83
84
Landing Gear Extended Speed
320 KIAS, M .83
85
Max Tire Speed
195 knots groundspeed
86
Retractable Landing Lights Extension Speed
250 KIAS
87
Retractable Landing Lights Retraction Speed
No limit
88
The operating life of the retractable landing lights increases if the lights are retracted below ___
250 KIAS
89
Fixed landing lights should be ___ (except for momentary checks) unless the aircraft is moving. When a/c is on ground and not in motion, limit operation to ___ minutes
Off
5 minutes
90
Fuel Dump Chutes Operating Limit
240 KIAS, M .83
91
Fuel Dump Chutes Extended Limit
275 KIAS, M .83
92
If aircraft requires more than ___ unit(s) of aileron trim or ___ unit(s) of rudder trim, enter condition on AFTO Forms 781A
1.5
1
93
At 80 knots, the maximum allowable difference between the pilot and copilot airspeed indicators is ___ knots
4 knots
94
If more than ___ unit(s) of aileron trim or ___ unit(s) of rudder trim are required, maintenance correction should be made at the next capable station
3
1.5
95
Maintain ___ clearance to equip being refueled. Maintain ___ to ungrounded electro-explosive devices with weather radar on
10; 40
96
Do not transmit on the HF radios (on the ground) unless personnel are at least ___ feet from all aircraft surfaces
15 feet
97
Do not transmit on HF radios within ___ feet of equipment being fueled/defueled or any underground electro-explosive devices
30 feet
98
Do not transmit on the AN/ARC-186 VHF radios (on the ground) unless personnel are at least ___ feet from the radiating antenna
4 feet
99
Do not transmit on the AN/ARC-186 VHF radios within ___ feet of equipment being fueled/defueled or any ungrounded electro-explosive devices
24 feet
100
Do not trasmit on the AN/ARC-210 (TCTO 762) VHF radios (on the ground) unless personnel are at least ___ feet from the radiating antenna
5 feet
101
Do not transmit on the AN/ARC-210 (TCTO 762) VHF radios within ___ feet of equipment being fueled/defueled or any ungrounded electro-explosive devices
7 feet
102
Do not trasmit on the UHF radios (on the ground) unless personnel are at least ___ feet from the radiating antenna
4 feet
103
Do not transmit on the UHF radios within ___ feet of equipment being fueled/defueled or any ungrounded electro-explosive devices
8 feet
104
In flight, do not transmit on mission radar within ___ feet horizontally or ___ feet vertically from another aircraft
1000; 1000
105
transmission of the mission radar on the ground is _____ except by radar maintenance personnel using radar maintenance technical orders
Prohibited
106
Mission radar ground speed envelope
450 +/-60 knots (rule of thumb)
107
Re-compute applicable takeoff data if change occurs greater than...
Runway Temp: +/- 2˚C
PA: +/- 500 ft
GW: +/- 5000 lbs
CG: +/- .5%
108
CFL is increased/decreased by approximately ___ by increases or decreases of...
100 ft
1˚C
100 ft PA
1,000 lbs GW
109
With ___ increase in temperature, obstacle clearance calculations will be re-accomplished if obstacle clearance is ___ or less.
any
| 100 ft
110
Increase rotation speed ___ knots for every ___ knots of tailwind.
4 knots
| 10 knots
111
When increasing rotation, takeoff, or climbout speeds for gusts on takeoff, the maximum allowable increase is ___ knots
10
112
When correcting approach speed for headwind and gusts, the total wind correction must not exceed ___ knots
20
113
A/R airspeed from level off until 2 NM
M .76 or 310 KIAS, whichever is lower
114
A/R airspeed at 1 NM
M .72 or 290 KIAS, whichever is lower
115
A/R airspeed at 1/2 NM
M .69 or 285 KIAS, whichever is lower
116
A/R airspeed in contact
M .66 or 275 KIAS, whichever is lower
117
KC-135
| inner extension limit
6 ft
118
KC-135
| center extension
12 ft
119
KC-135
| outer extension limit
18 ft
120
KC-135
| left/right azimuth limits
10˚
121
KC-135
| center azimuth position
0˚
122
KC-135
| upper vertical limit
20˚
123
KC-135
| center vertical position
Approximately 30˚
124
KC-135
| lower vertical limit
40˚
125
KC-10
| inner extension limit
6 ft
126
KC-10
| center extension
13 ft
127
KC-10
| outer extension limit
21 ft
128
KC-10
| left/right azimuth limits
19˚
129
KC-10
| center azimuth position
0˚
130
KC-10
| upper vertical limit
20˚
131
KC-10
| center vertical position
Approximately 30˚
132
KC-10
| lower vertical limit
40˚
133
A maximum of ___ KC-10 aerial refuel transfer pumps should be used during refueling to prevent over pressurization of refueling system
4
134
Flap indicators may read +/- ___ of actual flap position
3˚
135
Flaps will not be extended above ___
20,000 MSL
136
Leading edge flaps extend and retract as the _____ trailing edge flaps pass through the _____ position
inboard
6 (+/- 3)˚
137
If the mach bell rings before ___ or ___ is indicated, the point at which the bell begins to ring is limiting
Vmo
| Mmo
138
The airplane battery is a ___ volt, 31 amp-hour, lead acid unit located in the _____ section
24
right lower nose
139
Rudder pressure should be approximately ___ when rudder is set to the high range and ___ when rudder is in low range
3000 psi
2250 psi
140
Altimeter must read within ___ of known elevation (RESET/STBY modes)
75 ft
141
Allowable tolerance between both RMDIs is ___
2.5˚
142
Allowable difference between the RMDI and an HSI repeater (on the same compass system) is ___
1˚
143
During the ADI test, the indicator should display ___ right bank and ___ nose up pitch
20˚
10˚
144
Gaseous O2 pressure should be _____
290-430 psi
145
LOX convertor stores ___ of LOX at a nominal pressure of ___
75 L
300 psi
146
Oxygen level low light comes on at or below ___ or when the system pressure is below ___
7.5 L
42 psi
147
Utility hydraulic reservoir is located in the ___ main wheel well
All airplanes have an extended filler neck and an expansion tank which has a capacity of ___
left
6.9 gal
148
Hydraulic fluid above the ___ level replenished the auxiliary hydraulic system reservoirs
3.2 gal
149
Rudder boost low pressure light indicates pressure in supply line to the rudder power unit is below approximately ___
Armed with _____ flaps down ___ or greater and rudder hydraulic pressure in the high range
2500 PSI
inboard
2˚
150
Yaw damper disengaged light will come on when rudder pressure drops below ___ or yaw damper _____ power is lost or when certain circuit _____ occur within the yaw damper circuits
1200 psi
electric
faults
151
Auxiliary and utility hydraulic pump low pressure lights come on when pressure decreases to approximately ___
The lights go out when pressure increases to approximately ___
1100 psi
1200 psi
152
When fuel temperature is ___ or below, turn fuel heat on for ___ prior to T/O
0˚C
1 min
153
If engines have been operating at idle thrust for ___ or more, fuel heater may be operated with engines at idle
Otherwise, fuel should be increased to ___ before the heaters are turned on and maintained at ___ for ___ after the heaters are turned off
5 min
1500 pph
1500 pph
2 min
154
Fuel heat should be ___ for takeoff
off
155
Turn on engine anti-icing during ground operations whenever icing conditions exist for takeoff (OAT ___ or lower with visible moisture present)
10˚C
156
If the nose cowl anti-ice valve does not open in ___ at idle thrust, increase thrust to ___ N1
Do not exceed ___ N1 - if valve does not open within ___, valve has failed
1 sec
40%
40%
1 sec
157
Do not use wing anti-ice for takeoff or until reaching ___
1000 AGL
158
The oil pressure caution light will come on at ___ or ___.
| It will go out at ___ on increasing pressure.
32 +/- 2 PSI or 50 PSID
36 PSI
159
Oil pressure caution light should go off within ___ seconds after engine reaches stabilized idle
30
160
Fuel flow at light-off above ___ pph indicates impending hot start (normally less than ___ pph)
1400
| 1000
161
Fuel flow peaks at _____ pph during engine acceleration and stabilizes at ___ pph at idle
1600-1800
| 1100
162
A rise in EGT should occur within ___ seconds after start lever is adanced
20
