Limitations - All Flashcards
Runway slope
+/- 2%
Maximum Takeoff and Landing Tailwind Component
15 knots
Maximum Operating Altitude
43,100 ft pressure altitude
Maximum Takeoff and Landing Altitude
14,000 ft pressure altitude
Turbulent Air Penetration Speed
Turbulent air penetration speed (in severe turbulence) is defined as:
290 KIAS below 25,000 feet
310 KIAS/.84 Mach (whichever is lower) at and above 25,000 feet.
The maximum demonstrated crosswind for takeoff is
35 knots
The maximum demonstrated crosswind for landing is
33 knots.
Do not operate HF radios when
refueling
Operational Limitations
Non-AFM Operational Information
Do not operate the weather radar in a hangar or when personnel are within the area normally enclosed by the aircraft nose radome. Do not operate the weather radar within 50 feet of fueling operations or fuel spills.
RVSM Operations
Do not fly in RVSM airspace on ISFD alone. The standby altimeter does not meet RVSM altimeter accuracy requirements.
Maximum Taxi Weight
787-8
787-9
503,500 Pounds
547,000 Pounds
Maximum Takeoff Weight
787-8
787-9
502,500 Pounds
545,000 Pounds
Maximum Landing Weight
787-8
787-9
380,000 Pounds
425,000 Pounds
Maximum Zero Fuel Weight
787-8
787-9
355,000 Pounds
400,000 Pounds
Autopilot/Flight Director System
The autopilot must not be engaged below a minimum engage altitude of
200 feet AGL after takeoff.
Autopilot/Flight Director System
Autoland capability may only be used for operations into runways at or below _____.
8400 feet airport field elevation.
Autopilot/Flight Director System
Without LAND 2 or LAND 3 annunciated, the autopilot must be disengaged below
100 feet AGL.
Autopilot/Flight Director System
With LAND 2 or LAND 3 annunciated and glidepath angles greater than ____ degrees, the autopilot must be disengaged ____________AGL.
3.25
below 100 feet
Autopilot/Flight Director System
If the glidepath angle for approach is greater than ________, the autopilot must be disengaged no later than _____________DH/MDA.
3.77 degrees
50 feet below
Low Visibility (HUD) Takeoff
Low weather minima takeoff may only be performed using ILS guidance on
U.S. CAT II or CAT III ILS facilities.
Low Visibility (HUD) Takeoff
Maximum wind component speeds when takeoff weather minima are predicated on HUD takeoff operations:
Headwind
25 knots
Low Visibility (HUD) Takeoff
Maximum wind component speeds when takeoff weather minima are predicated on HUD takeoff operations:
Tailwind
15 knots
Low Visibility (HUD) Takeoff
Maximum wind component speeds when takeoff weather minima are predicated on HUD takeoff operations:
Crosswind
15 knots
Automatic Landing
Maximum wind component speeds when performing autoland operations (may be limited by visibility or runway condition):
Headwind
25 knots
Automatic Landing
Maximum wind component speeds when performing autoland operations (may be limited by visibility or runway condition):
Tailwind
15 knots
Automatic Landing
Maximum wind component speeds when performing autoland operations (may be limited by visibility or runway condition):
Crosswind
25 knots
Automatic Landing
The maximum glide slope angle is________. The minimum glide slope angle is 2.5 degrees
3.25 degrees
Automatic Landing
The minimum glide slope angle is __________.
2.5 degrees
Automatic Landing
Autoland capability may be used with flaps ____, ____, _____, with both engines ________ or with one engine________.
20, 25, or 30
operative
inoperative
Automatic Landing
The autopilot flight director system (AFDS) autoland status annunciation must have _______ or _________ displayed.
LAND 2 or LAND 3
Communications
Flight Deck Communications Systems (Datalink)
Datalink messages sent from the COMPANY format or received with a .COMM or .PRINTER on EICAS are limited to messages which will not create an unsafe condition if:
- the message or parts of the message are delayed or not received, or
- the message is delivered to the wrong recipient, or
- the message content may be frequently corrupted However, datalink messages can be transmitted and received via the COMPANY format if they are verified per approved operational procedures.
Datalink messages sent from the COMPANY format or received with a .COMM or .PRINTER on EICAS are limited to messages which will not create an unsafe condition if:
- the message or parts of the message are delayed or not received, or
- the message is delivered to the wrong recipient, or
- the message content may be frequently corrupted However, datalink messages can be transmitted and received via the COMPANY format if they are verified per approved operational procedures.
Communications
Audio Control Panel (ACP)
Use of the Captains or First Officers ACP to establish a SATCOM/cabin conference is prohibited. Use the center ____.
ACP
Communications
Boom Mics Non-AFM:
Boom Mics must be used when below
18,000 feet
Engines
Engine Oil System
Oil temperature must be greater than ______ for engine start.
-40° C
Engines
Reverse Thrust
Intentional selection of reverse thrust in flight is _________.
Backing the airplane with use of reverse thrust is _________.
prohibited
prohibited
Engines
Tailwind and Crosswind
Ground wind operating envelope:
- for crosswinds greater than _____knots, limit thrust to a setting normally used for taxi (____ N1).
- with a tailwind component greater than ___ knots and winds greater than ___ knots, limit thrust to a setting normally used for taxi (____% N1).
- for winds greater than ___ knots, limit engine thrust to ______.
Crosswind: 35 kts / 45% N1
Tailwind: 5 kts / 45% N1
greater than 55 kts / idle
Flight Controls
Avoid rapid and large ________ _________ inputs, especially in combination with large changes in ______, ______ or ______ (e.g. large side slip angles) as they may result in structural failure at any speed, including below VA.
alternating control
pitch, roll, or yaw
Flight Controls
Do not extend flaps above ________ feet.
20,000 feet
Fuel
Fuel Temperature Maximum tank fuel temperature at takeoff is 49° C (120° F) for Jet A, Jet A-1, JP-5, JP-8 or TS-1.
Inflight fuel temperature is limited to 65° C (150° F) for Jet A, Jet A-1, JP-5 or JP-8.
Inflight fuel temperature for TS-1 is limited to 57° C (135° F) at or above 35,000 feet and 65° C (150° F) below 35,000 feet.
Tank fuel temperature prior to takeoff must not be less than -29° C (-20° F).
In-flight tank fuel temperature must be maintained at least 3° C above the freezing pointofthefuelbeingused. TheuseofFuelSystemIcingInhibitoradditivesdoes not change the minimum fuel tank temperature limit. (Refer to Performance Initialization Page in Chapter 11, Section 40, for additional information.)
Fuel
Fuel Loading
Main tanks must be scheduled to be ____ if center tank fuel is loaded.
Note: Thecenter tank may contain up to 22000 pounds 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.
full
Warning Systems
GPWS - Look-Ahead Terrain Alerting
Do not use the terrain display for navigation.
The use of look-ahead terrain alerting and terrain display functions are prohibited within 15 NM of takeoff, approach or landing at an airport or runway not contained in the GPWS terrain database.
Warning Systems
TCAS
Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with a TCAS resolution advisory. Evasive maneuvers must not be based solely on information from the traffic display or traffic advisory (TA) without visually sighting the traffic.
