Limitations Flashcards by Rodney Cummings

Maximum Operating Pressure Altitude for 787 -8, -9 is: 

A. 43,100 ft
B.  45,100 ft.
C.  41,500 ft.
D.  41,300 ft.

A. 43,100 FT

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Maximum Operating Pressure Altitude for 787 -10 is: 

A. 43,100 ft
 B. 45,100 ft.
 C. 41,100 ft.
 D. 41,300 ft.

C. 41,100 FT

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The maximum landing gross weight for the 787-8 is:

A. 503,500 pounds.
B.  355,000 pounds. 
C. 380,000 pounds.
 D. 430,000 pounds.

C. 380,000 pounds

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The maximum landing gross weight for the 787-9 is:

A. 503,500 pounds.
B.  355,000 pounds. 
C. 380,000 pounds.
D.  425,000 pounds.

D. 425,000 pounds

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The maximum landing gross weight for the 787-10 is:

A. 503,500 pounds.
 B. 445,000 pounds. 
C. 380,000 pounds.
D.  425,000 pounds.

B. 445,000 pounds

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Engine oil temperature prior to engine start must be __ degrees or greater.

 A. There is no minimum
 B. -22c
 C. 0c
 D. -40c

D. -40 C

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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

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Do not extend flaps above:

A. 15,000 ft.
B. 43,100 ft.
 C. 20,000 ft. 
D. 18,000 ft.

C. 20,000 FT

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Maximum wind component speeds when T/O minima are predicated on HUD takeoff operations are __ . 

A. 15 kts headwind / 15 kts tailwind / 10 kts crosswind.
 B. 25 kts headwind / 10 kts tailwind / 5 kts crosswind.  
C. 25 kts headwind / 15 kts tailwind / 25 kts crosswind.
 D. 25 kts headwind / 15 kts tailwind / 15 kts crosswind.

D. 25 kts headwind / 15 kts tailwind / 15 kts crosswind.

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Maximum takeoff gross weight for 787-8 is:

 A. 502,500 lbs.
 B. 355,000 lbs.
 C. 380,000 lbs.
D.  503,500 lbs.

A. 502,500 lbs.

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Maximum takeoff gross weight for 787-9 is:

 A. 502,500 lbs.
 B. 563,500 lbs.
 C. 561,500 lbs.
 D. 503,500 lbs.

C. 561,500 lbs

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Maximum takeoff gross weight for 787-10 is:

 A. 560,000 lbs.
 B. 563,500 lbs.
C.  561,500 lbs.
 D. 503,500 lbs.

A. 560,000 lbs.

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Maximum allowable wind speeds for autoland operations are:

 A. 25 kts headwind, 10 kts tailwind, 15 kts crosswind.
B.  20 kts headwind, 10 kts tailwind, 15 kts crosswind.
 C. 38 kts headwind, 15 kts tailwind, 25 kts crosswind.
D.  None

A. 25 kts headwind, 10 kts tailwind, 15 kts crosswind.

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The maximum and minimum glidepath angle for ILS/GLS automatic landing (or approaches using IAN) is __ degrees. 

A. 2.25 max / 3.25 min
 B. 2.0 max / 3.0 min 
C. 3.25 max / 2.5 min
 D. 4.0 max / 2.5 min

C. 3.25 max / 2.5 min

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The B787 is certified as Category __ for instrument approaches and Category __ for circling approaches. 

A. D/D
B.  B/D  
C. A/C  
D. D/C

A. D/D

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What is the maximum takeoff and landing pressure altitude?

A. 14,000 ft.
 B. 8,500 ft.
 C. 10,000 ft.  
D. 12,500 ft.

A. 14,000 ft.

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What is the maximum unrestricted T/O and Landing tailwind component?  

A. 5 kts.
 B. 25 kts. 
C. 15 kts. 
D. 20 kts.

C. 15 kts. 

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The Ground Proximity Warning System (GPWS) terrain display can be used for navigation.

 A. True
 B. False

B. False

A GPWS terrain data base contains detailed terrain and man-made obstacle data. Obstacle and terrain data is not designed to be used as an independent navigation aid. Obstacles or terrain ahead of the airplane may exceed available climb performance. A GPWS caution or warning does not guarantee obstacle or terrain clearance.

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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. 

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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.

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The flap placard speed for flaps 1 for a 787-8 is:

A. 265 kts.
B. 235 kts.
C. 215 kts.
 D. 250 kts.

D. 250 kts.

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The flap placard speed for flaps 1 for a 787-9, -10 is:

 A. 260 kts.
 B. 235 kts.
C. 215 kts.
 D. 250 kts.

A. 260 kts.

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Category Ill / Autoland is approved for all landing flaps settings only if both engines are operating.

 A. True 
B. False

B. False

The autoland capability may be used with flaps 20, 25, or 30, with both engines operative or with one engine inoperative. The AFDS autoland annunciation must have LAND 2 or LAND 3 displayed.

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Which of the following statements are true regarding autoland operations on the B787? 

A. Autolandings are certified even if all three hydraulic systems are lost.
 B. The B787 is not certified for autolandings with the loss of any one of the 3 hydraulic systems. 
C. Autolandings are not certified with the loss of the right hydraulic system. 
D. The B787 is not authorized for autolandings when using GLS approach procedures.

D. The B787 is not authorized for autolandings when using GLS approach procedures.

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Maximum Cabin Differential Pressure is:  A. 0.11 psi.  B. 1.0 psi.  C. 8.5 psi  D. 9.9 psi.

D. 9.9 psi.

The autopilot must not be engaged:  A. Below 200 ft after takeoff.  B. If NO AUTOLAND is displayed.  C. On non-precision approaches below 1000ft.  D. If the EICAS Message FLAP PRIMARY is displayed.

A. 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 787-8 maximum flap placard speed for flaps 30 is:  A. 185 kts.  B. 190 kts.  C. 170 kts.  D. 160 kts

C. 170 kts. 

The 787-9, -10 maximum flap placard speed for flaps 30 is:  A. 180 kts.  B. 190 kts.  C. 170 kts.  D. 160 kts

A. 180 kts. 

The use of VNAV and/or LNAV with QFE selected is prohibited.  A. True  B. False

A. True

What is the 787-8 maximum taxi weight? A. 380,000 lbs.  B. 460,000 lbs. C. 503,500 lbs.  D. 502,500 lbs.

C. 503,500 lbs. 

What is the 787-9 maximum taxi weight? A. 560,000 lbs.  B. 561,500 lbs.  C. 563,000 lbs.  D. 562,500 lbs.

C. 563,000 lbs. 

What is the 787-10 maximum taxi weight? A. 560,000 lbs.  B. 561,500 lbs.  C. 563,000 lbs.  D. 562,500 lbs.

B. 561,500 lbs.

What is the 787-8 maximum zero fuel weight?  A. 355,000 lbs.  B. 502,500 lbs.  C. 380,000 lbs.   D. 460,000 lbs.

A. 355,000 lbs. 

What is the 787-9 maximum zero fuel weight?  A. 445,000 lbs.  B. 400,500 lbs.  C. 400,000 lbs.   D. 425,000 lbs.

C. 400,000 lbs.  

What is the 787-10 maximum zero fuel weight?  A. 445,000 lbs.  B. 400,500 lbs.  C. 400,000 lbs.   D. 425,000 lbs.

D. 425,000 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 787-8 flap placard speed for flaps 5 is:  A. 230 kts.  B. 215 kts.  C. 190 kts.  D. 210 kts.

A. 230 kts.

The 787-9, -10 flap placard speed for flaps 5 is:  A. 230 kts.  B. 250 kts.  C. 190 kts.  D. 240 kts.

D. 240 kts.

The 787-8 flap placard speed for flaps 15 is: A. 235 kts.  B. 195 kts.  C. 215 kts.  D. 185 kts.

C. 215 kts.

The 787-9, -10 flap placard speed for flaps 15 is: A. 230 kts.  B. 195 kts. C. 215 kts.  D. 220 kts.

D. 220 kts.

The 787-8 flap placard speed for flaps 20 is:  A. 230 kts.  B. 210 kts.  C. 190 kts.  D. 170 kts

B. 210 kts. 

The 787-9, -10 flap placard speed for flaps 20 is:  A. 230 kts.  B. 210 kts.  C. 190 kts.  D. 170 kts

B. 210 kts.

The 787-8 flap placard speed for flaps 25 is: A. 170 kts. B. 180 kts. C. 190 kts. D. 215 kts.

B. 180 kts.

The 787-9, -10 flap placard speed for flaps 25 is: A. 170 kts. B. 180 kts. C. 190 kts. D. 215 kts.

C. 190 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:  A. + 37 degrees C.  B. + 47 degrees C.  C. + 49 degrees C.  D. There is no maximum.

C. + 49 degrees C. 

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.

Approved Operations

Icing Extended overwater ops, Extended ops (up to 240-min ETOPS) Day/Night VFR and IFR Cat I,II,III Wingspan-Limited Ops Group V (FAA), Code E ICAO CAT D for approaches

Runway Slope

+ / - 2%

787-8 Flap Limit Speeds (Flaps 1-30)

1 250 5 230 10 N/A 15 215 17 N/A 18 N/A 20 210 25 180 30 170

787-9, -10 Flap Limit Speeds (Flaps 1-30)

1. 260 5. 240 10. 230 15. 220 17. 215 18. 215 20. 210 25. 190 30. 180

Maximum Landing Gear Speeds

270 kts. / .82

Turbulent Air Penetration Speed 1. Severe turbulence > / = 25,000 Ft. 2. Severe turbulence < 25,000 Ft.

1. > / = 25,000 ft. - 310 KIAS / .84 whichever is lower 2. < 25,000 ft. - 290 KIAS

787-8 Maximum Gross Weights: Taxi Takeoff Landing ZFW

Taxi 503.5 Takeoff 502.5 Landing 380.0 ZFW 355.0

787-9 Maximum Gross Weights: Taxi Takeoff Landing ZFW

Taxi 563.0 Takeoff 561.5 Landing 425.0 ZFW 400.0

787-10 Maximum Weights: Taxi Takeoff Landing ZFW

Taxi 561.5 Takeoff 560.00 Landing 445.0 ZFW 425.0

Flight Deck Door

Verify an operational check of the flight deck access system has been accomplished according to approved Normal Procedures prior to EACH flight.

Door Mounted Power Assists and Escape Slides

Armed with the door mode select levers in the automatic position and the electronically dimmable door windows in the clear state prior to taxi, takeoff, and landing whenever passengers are onboard.

Weather Radar

Do not operate in a hangar or within 50 ft. of any fuel spill.

Maximum Differential Pressure for takeoff and landing

.11 PSI

Icing Conditions

Icing conditions exist when OAT (ground) or TAT (flight) is 10° C or below and visible moisture. Note: Use TAT to determine EAI selection during ground operations to avoid nuisance ANTI-ICE ON EICAS messages. AND Visible moisture (fog with visibility of 1 SM or less, rain, sleet, snow, ice pellets, or other forms of moisture) is present, or Standing water, ice, slush, or snow is present on the ramps, taxiways, or runway surfaces.

Engine Anti-ice

Engine anti-ice must be selected ON during all ground operations, and selected to either ON or AUTO during flight, when icing conditions exist or are anticipated, except when the temperature is below -40°C (-40°F) OAT. Do not use engine anti-ice if OAT or TAT (on the ground) exceeds 10°C (50°F) or displayed TAT (inflight) exceeds 15°C (59°F).

Wing Anti-Ice System

Wing anti-ice must be selected to either ON or AUTO during flight when icing conditions exist or are anticipated, except when the temperature is below -40°C (-40°F) OAT. Do not operate wing anti-ice system in manual mode when TAT is above 15°C (59°F). Note: Primary Ice Detection System Operative: When the primary ice detection system is being used, icing conditions exist in flight when indicated by the primary ice detection system. Primary Ice Detection System Inoperative: When the primary ice detection system is inoperative, icing conditions may exist in flight when displayed TAT is less than or equal to 15°C (59°F). In flight, when displayed TAT is greater than 10°C (50°F) but less than or equal to 15°C (59°F) and visible moisture is present, engine and wing anti-ice must be selected ON except activation may be delayed until 2500 feet AGL for takeoff.

Maximum Altitude for Autoland

★Autoland capability may only be used for operations to runways at or below 8400 feet airport field elevation.

Autopilot ops without LAND 2 or LAND 3:

★Without LAND 2 or LAND 3 annunciated, the autopilot must be disengaged below 135 feet AGL.

Autopilot ops with LAND 2 or LAND 3 annunciated and glideslope angles greater that 3.25°:

★With LAND 2 or LAND 3 annunciated and glideslope angles greater than 3.25°, the autopilot must be disengaged below 100 feet AGL.

If the glidepath angle for approach is greater than 3.77°, the autopilot must be disengaged no later than _____

50 ft. below DH / MDA

★Do not use FLCH on final approach below _____ feet AFE.

1000 feet AFE

LOW VISIBILITY (HUD) TAKEOFF (RVR <500)

Low weather minima takeoff may only be performed using ILS localizer guidance on Type II or Type III ILS facilities (CAT II or CAT III). The Autopilot Flight Director System (AFDS) mode annunciation must have HUD TO/GA displayed.

Maximum wind component speeds when takeoff weather minima are predicated on HUD takeoff operations:

Headwind 25kts Tailwind 15kts Crosswind 15kts

SA CAT I APPROACHES Maximum wind component speed: (CROSSWIND)

15 kts

ILS AUTOMATIC LANDING : Maximum wind component speeds:

Headwind 25 knots Tailwind 15 knots (◘ 10 knots for CAT II/III) 25 knots Crosswind 25 knots (◘ 15 knots for CAT II/III)

★The maximum glideslope angle is _______. ★The minimum glideslope angle is _______. ◘ Do not autoland from a GLS approach, even if LAND 2 or LAND 3 is annunciated.

MAX 3.25° MIN 2.5° ◘ Do not autoland from a GLS approach, even if LAND 2 or LAND 3 is annunciated.

The autoland capability may be used with flaps ___, ____, or ____, with both engines operative or with one engine inoperative.

Flaps 20, 25, or 30

The AFDS autoland annunciation must have_____ or_____ displayed. Autoland operations are not certified above the maximum structural landing weight.

LAND 2 or LAND 3

Autoland operations are not certified above the _______.

Maximum Structural Landing Weight

If the APU fails to start after the second attempt, a _____ cooling period must be observed before a third attempt is made.

5 Minute

Do not operate _____ radio during fueling operations

HF radio

SAT PHONE (787-9 0971 and above) (787-10) Do not use _______ service for ATC communications.

SwiftBroadband (SBB)

AUDIO CONTROL PANEL (ACP) Use of the Captain’s or First Officer’s ACP to establish a SATCOM/cabin conference is_______.

Prohibited

ENGINE EGT Temperature Limits Ground starting Flight starting Maximum continuous Takeoff and go-around Maximum transient

Ground starting 750° Flight starting 875° Maximum continuous 1030° Takeoff and go-around 1065° 5 Minutes - ** Maximum transient 1070° 30 Seconds **10 minutes allowed in the event of loss of thrust of one engine.

1. Maximum oil temperature, continuous operation, is _____. 2. Maximum oil temperature, 15 minute limit, is _____. 3. The oil temperature must have an indicated _____ before acceleration to high thrust levels.

1. 160° C 2. 177° C 3. increase

Oil Quantity ◘ Minimum prior to start ★_____ quarts. ★Oil temperature must be greater than _____for engine start.

Oil Quantity ◘ Minimum prior to start ★18 quarts. ★Oil temperature must be greater than -40°C for engine start.

REVERSE THRUST ★Intentional selection of reverse thrust in flight is _______. ★_______ the airplane with use of reverse thrust is prohibited. Do not attempt a _______ after thrust reverser deployment.

REVERSE THRUST ★Intentional selection of reverse thrust in flight is prohibited. ★Backing the airplane with use of reverse thrust is prohibited. Do not attempt a go-around after thrust reverser deployment.

RPM N1 Maximum N2 Maximum

N1 Maximum - 108.5 % N2 Maximum - 117.5 %

For crosswinds greater than ______, limit thrust to a setting normally used for taxi (45% N1).

40 Knots

With a tailwind component greater than _______ and winds greater than _______, limit thrust to a setting normally used for taxi (45% N1).

1. 5 knots 2. 35 knots

For winds greater than _______, limit engine thrust to idle.

55 knots

ENGINE THRUST – ALTERNATE EEC MODE Maximum takeoff and landing tailwind component:

10 Knots

AFTER LANDING DURING SPECIFIC COLD WEATHER CONDITIONS Alternative Method of Compliance to AD 2019-20-07 In order to detect an unannunciated failure of the slat drive system, pilots must notify Maintenance via an approved means that a check of the slat drive system is required if either of the following:

The outside air temperature on the ground at the destination airport is 50°F (10°C) or below, and operating on the ground with ice, snow, slush, or standing water. An accumulation of airframe ice is observed or suspected.

Takeoff is permitted only in the _______ flight control mode.

Normal

★ Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g., large side slip angles) as they may result in structural failure at any speed, including below VA. A. True B. False

A. True

FLIGHT MANEUVERING LOAD ACCELERATION Flaps up _______ to _______ Flaps down _______ to _______

FLIGHT MANEUVERING LOAD ACCELERATION Flaps up +2.5 g to -1.0 g Flaps down +2.0 g to 0.0 g

The maximum altitude with flaps extended is _______ feet pressure altitude.

20,000 feet pressure altitude.

◘ Do not use speed brakes in flight below _______ feet AGL.

1000 feet AGL

In the event of loss of primary air data, standby system corrections must be applied. See Performance>Non-Normal Approach & Land>ISFD Airspeed and Altitude Correction tables.) Do not fly in _______ on the ISFD alone. The standby altimeter does not meet RVSM altimetry accuracy requirements.

RVSM airspace

GROUND PROXIMITY WARNING SYSTEM (GPWS) Do not use the_______ for navigation. The use of look-ahead terrain alerting and terrain display functions are prohibited within _______ of takeoff, approach, or landing at an airport not contained in the GPWS terrain database.

terrain display 15 nm

Select QFE altitude reference for the Primary Flight Displays (PFD) in the _______ whenever QFE is used instead of QNH. Note: United procedures do not require pilots to select QFE.

Flight Management System (FMS)

With QFE selected do not use_______ and/or_______.

VNAV and/or LNAV.

Prior to takeoff, the maximum allowable difference between Captain’s or First Officer’s altitude display and the field elevation is:

75 feet

Inflight, the maximum allowable difference between Captain’s and First Officer’s altitude displays is:

200 feet

Do not align IRS at North/South latitudes greater than:

78°14.75’

DEMONSTRATED 787 REQUIRED NAVIGATION PERFORMANCE (RNP) FLIGHT OPERATIONS VALUES (NM) FOR MODE OF FLIGHT INR - GPS NAV ON _______ INR - GPS NAV OFF _______

INR - GPS NAV ON - 0.10 NM INR - GPS NAV OFF - 0.30 NM

Tank fuel temperature prior to takeoff must not be less than _______.

-29°C (-20°F).

Fuel density must be between:

6.3 and 7.1 lb/gallon (0.7549 and 0.8507 kg/liter).

Do not jettison fuel at flaps:

flaps 30

Main tanks must be scheduled _______ if center tank fuel is loaded.

Full

The center tank may contain up to_______ of fuel with less than full main tanks provided center tank fuel weight plus actual zero fuel weight does not exceed the maximum zero fuel weight and center of gravity limits are observed.

22,000 pounds

FUEL CAPACITY 787-8 Left main Right main Center

FUEL CAPACITY 787-8 Left main 5570 (37,319) gals/lbs Right main 5570 (37,319) gals/lbs Center 22,200 (148,740) gals/lbs

FUEL CAPACITY 787-9,-10 Left main Right main Center

Left main 5520 (36,984) gals/lbs Right main 5520 (36,984) gals/lbs Center 22,340 (149,678) gals/lbs

Hydraulic quantity minimum for dispatch:

Above the RF

TIRE – MAXIMUM SPEED Takeoff Landing

Takeoff - 204 knots groundspeed Landing - 226 knots groundspeed

Oxygen Pressure Minimum at 50°C - 122°F 2 pilots 3 pilots 4 pilots Pilot Oxygen – Required pressure (PSI) for two cylinders (115 cu.ft.)

2 pilots - 325 psi 3 pilots - 437 psi 4 pilots - 532 psi Pilot Oxygen – Required pressure (PSI) for two cylinders (115 cu.ft.)

GPWS LOOK-AHEAD TERRAIN ALERTING Do not use the _______ display for navigation.

Terrain

GPWS LOOK-AHEAD TERRAIN ALERTING The use of look-ahead terrain alerting and terrain display functions are prohibited within _______ of takeoff, approach, or landing at an airport not contained in the GPWS terrain database. Airports/runways not in the current GPWS database are identified by NOTAM.

15 NM

Use of _____ and _____ fuels is prohibited.

JP-4 and jet B

In flight, tank fuel temperature must be maintained at least _____ above the freezing point of the fuel being used. The use of fuel system icing inhibitor additives does not change the minimum fuel tank temperature limit.

3°C

If the specific freeze point of the boarded fuel is provided by the departure station, add _____ to the supplied freeze value to determine the minimum inflight temperature (e.g., Jet A supplied freeze value -44°C, operational limit is -41°C).

3°