Limitations Flashcards
Maximum Operating Pressure Altitude is:
• 43,100 ft.
• 45,100 ft.
• 41,500 ft.
• 41,300 ft.
• 43,100 ft.
The maximum landing gross weight is:
• 503,500 pounds.
• 355,000 pounds.
• 380,000 pounds.
• 430,000 pounds.
• 380,000 pounds.
Engine oil temperature prior to engine start must be __ degrees or greater.
• There is no minimum
• -22c
• 0c
• -40c
• -40c
For 90 degree crosswinds between 40 and 55 kts, limit engine thrust to a setting normally used for taxi (45% N1).
A. True
B. False
A. True
Do not extend flaps above:
• 15,000 ft.
• 43,100 ft.
• 20,000 ft.
• 18,000 ft.
• 20,000 ft.
Maximum wind component speeds when T/O minima are predicated on HUD takeoff operations are __ .
• 15 kts headwind / 15 kts tailwind / 10 kts crosswind.
• 25 kts headwind / 10 kts tailwind / 5 kts crosswind.
• 25 kts headwind / 15 kts tailwind / 25 kts crosswind.
• 25 kts headwind / 15 kts tailwind / 20 kts crosswind.
• 25 kts headwind / 15 kts tailwind / 20 kts crosswind.
Maximum takeoff gross weight is:
• 502,500 lbs.
• 355,000 lbs.
• 380,000 lbs.
• 503,500 lbs.
• 502,500 lbs.
Maximum allowable wind speeds for autoland operations are:
• 25 kts headwind, 15 kts tailwind, 25 kts crosswind.
• 20 kts headwind, 10 kts tailwind, 20 kts crosswind.
• 38 kts headwind, 15 kts tailwind, 25 kts crosswind.
• None
• 25 kts headwind, 15 kts tailwind, 25 kts crosswind.
The maximum and minimum glidepath angle for ILS/GLS automatic landing (or approaches using IAN) is __ degrees.
• 2.25 max / 3.25 min
• 2.0 max / 3.0 min
• 3.25 max / 2.5 min
• 4.0 max / 2.5 min
3.25 max / 2.5 min
The B787 is certified as Category __ for instrument approaches and Category __ for circling approaches.
• D/D
• B/D
• A/C
• D/C
• D/D
What is the maximum takeoff and landing pressure altitude?
• 14,000 ft.
• 8,500 ft.
• 10,000 ft.
• 12,500 ft.
• 14,000 ft.
What is the maximum unrestricted T/O and Landing tailwind component?
• 5 kts.
• 25 kts.
• 15 kts.
• 20 kts.
• 15 kts.
The Ground Proximity Warning System (GPWS) terrain display can be used for navigation.
A. True
B. False
B. False
Do not use speed brakes inflight:
A. With flaps extended.
B. When altitude is less than 2000 ft AGL.
C. When altitude is less than 1000 ft AGL.
D. All the above.
C. When altitude is less than 1000 ft AGL.
When using Autoland:
A. Either 20, 25, or 30 flaps may be used.
B. Maximum ILS glide slope angle is 2.5 degrees.
C. May land over max landing weight if caution is used.
D. All the above
A. Either 20, 25, or 30 flaps may be used.
The flap placard speed for flaps 1 is:
• 265 kts.
• 235 kts.
• 215 kts.
• 250 kts.
• 250 kts.
Category Ill / Autoland is approved for all landing flaps settings only if both engines are operating.
A. True
B. False
B. False
Which of the following statements are true regarding autoland operations on the B787?
• Autolandings are certified even if all three hydraulic systems are lost.
• The B787 is not certified for autolandings with the loss of any one of the 3 hydraulic systems.
• Autolandings are not certified with the loss of the right hydraulic system.
• The B787 is not authorized for autolandings when using GLS approach procedures.
• The B787 is not authorized for autolandings when using GLS approach procedures.
Maximum Cabin Differential Pressure is:
• 0.11 psi.
• 1.0 psi.
• 8.5 psi
• 9.9 psi.
• 9.9 psi.
The autopilot must not be engaged:
• below 200 ft after takeoff.
• If NO AUTOLAND is displayed.
• On non-precision approaches below 1000ft.
• If the EICAS Message FLAP PRIMARY is displayed.
• below 200 ft after takeoff.
The Turbulent Air Penetration Speed is:
A. 290 KIAS below 25,000 feet.
B. 310 KIAS / .84 Mach at and above 25,000 feet.
C. 250 KIAS.
D. Both A and B.
D. Both A and B.
The maximum flap placard speed for flaps 30 is:
• 185 kts.
• 190 kts.
• 170 kts.
• 160 kts
• 170 kts.
The use of VNAV and/or LNAV with QFE selected is prohibited.
A. True
B. False
A. True
What is the maximum ramp weight?
• 380,000 lbs.
• 460,000 lbs.
• 503,500 lbs.
• 502,500 lbs.
• 503,500 lbs.
What is the maximum zero fuel weight?
• 355,000 lbs.
• 502,500 lbs.
• 380,000 lbs.
• 460,000 lbs.
• 355,000 lbs.
What considerations must be made when using QFE instead of QNH as an altitude reference?
A. The altitude reference for the PFD/HUD (QFE vs. QNH) must be selected in the FMC.
B. Vertical (VNAV) navigation is not allowed.
C. The use of IAN procedures is prohibited.
D. All the above.
D. All the above.
The flap placard speed for flaps 5 is:
• 230 kts.
• 215 kts.
• 190 kts.
• 210 kts.
• 230 kts.
The flap placard speed for flaps 15 is:
• 235 kts.
• 195 kts.
• 215 kts.
• 185 kts.
• 215 kts.
The flap placard speed for flaps 20 is:
• 230 kts.
• 210 kts.
• 190 kts.
• 170 kts.
• 210 kts.
The flap placard speed for flaps 25 is: • 170 kts. • 180 kts. • 190 kts. • 215 kts.
• 180 kts.
Use of reverse thrust is prohibited:
A. Below 80 kts.
B. For backing the aircraft.
C. lnflight.
D. Both B and C
D. Both B and C
Use of JP4 and Jet B is prohibited?
A. True
B. False
A. True
The maximum fuel temperature at takeoff is:
• + 37 degrees C.
• + 47 degrees C.
• + 49 degrees C.
• There is no maximum.
• + 49 degrees C.
lnflight fuel temperature is limited to __ (Jet A, A1, JP-5 or JP-8).
• + 65 degrees C
• + 49 degrees C
• + 15 degrees C
• + 37 degrees C
• + 65 degrees C
The fuel tank temperature for T/O is between -23 degrees C and -29 degrees C, each main and center tank fuel load must be less than 22,000 lbs.
A. True
B. False
A. True
The center fuel tank may contain up to 22,000 lbs of fuel with less than full main tanks provided:
A. Center tank fuel weight is added to the actual ZFW and the combined total does not exceed the maximum ZFW.
B. Maximum imbalance between left and right main tanks does not exceed 4500 lbs.
C. Center of gravity remains within limits.
D. Both A and C.
D. Both A and C.
