Limitations - All Flashcards by b737flygirl@yahoo.com Ponce

Q

Runway slope

A

+/- 2%

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Q

Maximum Takeoff and Landing Tailwind Component

A

15 knots

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Q

Maximum Operating Altitude

A

43,100 ft pressure altitude

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Q

Maximum Takeoff and Landing Altitude

A

14,000 ft pressure altitude

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Q

Turbulent Air Penetration Speed

A

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.

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Q

The maximum demonstrated crosswind for takeoff is

A

35 knots

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Q

The maximum demonstrated crosswind for landing is

A

33 knots.

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Q

Do not operate HF radios when

A

refueling

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Q

Operational Limitations

Non-AFM Operational Information

A

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.

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Q

RVSM Operations

A

Do not fly in RVSM airspace on ISFD alone. The standby altimeter does not meet RVSM altimeter accuracy requirements.

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Q

Maximum Taxi Weight

787-8

787-9

A

503,500 Pounds

547,000 Pounds

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Q

Maximum Takeoff Weight

787-8

787-9

A

502,500 Pounds

545,000 Pounds

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Q

Maximum Landing Weight

787-8

787-9

A

380,000 Pounds

425,000 Pounds

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Q

Maximum Zero Fuel Weight

787-8

787-9

A

355,000 Pounds

400,000 Pounds

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Q

Autopilot/Flight Director System

The autopilot must not be engaged below a minimum engage altitude of

A

200 feet AGL after takeoff.

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Q

Autopilot/Flight Director System

Autoland capability may only be used for operations into runways at or below _____.

A

8400 feet airport field elevation.

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Q

Autopilot/Flight Director System

Without LAND 2 or LAND 3 annunciated, the autopilot must be disengaged below

A

100 feet AGL.

Q

Autopilot/Flight Director System

With LAND 2 or LAND 3 annunciated and glidepath angles greater than ____ degrees, the autopilot must be disengaged ____________AGL.

A

3.25

below 100 feet

Q

Autopilot/Flight Director System

If the glidepath angle for approach is greater than ________, the autopilot must be disengaged no later than _____________DH/MDA.

A

3.77 degrees

50 feet below

Q

Low Visibility (HUD) Takeoff

Low weather minima takeoff may only be performed using ILS guidance on

A

U.S. CAT II or CAT III ILS facilities.

Q

Low Visibility (HUD) Takeoff

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

Headwind

A

25 knots

Q

Low Visibility (HUD) Takeoff

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

Tailwind

A

15 knots

Q

Low Visibility (HUD) Takeoff

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

Crosswind

A

15 knots

Q

Automatic Landing

Maximum wind component speeds when performing autoland operations (may be limited by visibility or runway condition):

Headwind

A

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.