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A380 - Memory Items / Limitations > LIM > Flashcards

LIM Flashcards

1
Q

FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
Clean configuration?
Other configurations?

A

Clean configuration
-1 g to +2.5 g
Other configurations
0 g to +2 g

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2
Q

ENVIRONMENTAL ENVELOPE
Minimum TAT

A

-53 °C

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3
Q

AIRPORT OPERATIONS AND WIND LIMITATIONS

Runway slope (mean)
Minimum runway width

A

Runway slope (mean)
± 2 %
Minimum runway width
45 m

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4
Q

Maximum certified crosswind at takeoff (gust included)

A

35 kt

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5
Q

Maximum certified crosswind at landing (gust included)

A

40 kt
Note:
The maximum certified crosswind value is an AFM limitation. It is an engine limitation.

For information, maximum demonstrated crosswind at landing: 42 kt gusting 56 kt.

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6
Q

MAXIMUM RECOMMENDED CROSSWIND FOR TAKEOFF AND LANDING
6 - DRY
5 - GOOD
4 - GOOD TO MEDIUM
3 - MEDIUM
2 - MEDIUM TO POOR
1 - POOR

A

TO / LDG

35 / 40
35 / 40
27 / 27
20 / 20
20 / 20
15 / 15

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7
Q

Maximum tailwind at takeoff

A

15KT

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8
Q

Maximum tailwind at landing

A

BELOW 8000FT - 15 kt
ABOVE 8000FT - 10

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9
Q

Maximum wind for cabin door operation

A

40 kt
Maximum wind is 50 kt, if the aircraft nose is oriented into the wind.
The cabin and cargo door must be closed before the wind reaches 60 kt.

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10
Q

Maximum wind for cargo door operation

A

40 kt
Maximum wind is 50 kt, if the aircraft nose is oriented into the wind, or if the door is on the leeward side.
The cabin and cargo door must be closed before the wind reaches 60 kt.

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11
Q

COCKPIT WINDOW MAXIMUM OPENING/CLOSING SPEED

A

250KT / 160KT

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12
Q

MAXIMUM OPERATING SPEED VMO/MMO

A

VMO 340 kt
MMO 0.89

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13
Q

MAXIMUM SPEEDS FOR LANDING GEAR:
VLE
VLO
GRAVITY EXTENSION

A

Maximum speed with the landing gear extended (VLE) - 250 kt / M 0.55
Maximum speed with the landing gear operating (VLO) - 250 kt / M 0.55
Maximum speed for landing gear gravity extension (VLE/VLO) - 220 kt/M 0.48

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14
Q

MAXIMUM TIRE SPEED

A

204KT

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15
Q

MINIMUM CONTROL SPEEDS

RR / EA

A

RR
VMCL - 123 kt
VMCL-2 - 147 kt
EA
VMCL - 120 kt
VMCL-2 - 145 kt

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16
Q

WINDSHIELD WIPERS MAXIMUM SPEED

A

250 kt

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17
Q

TAKEOFF PACKS OFF?

A

PROHIBITED

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18
Q

CABIN PRESSURE
Maximum positive differential pressure
Maximum negative differential pressure
Maximum normal cabin alt
Minimum cabin alt selecion

A

9.65 psi
0.725 psi
7500ft
-2000ft

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19
Q

AUTOPILOT

Minimum height for use of autopilot:

At takeoff

Non-precision approach

Circling approach

ILS approach with APPR1 displayed on FMA

After manual go-around

All other phases

A

100 ft AGL, and at least 5 s after liftoff (An internal PRIM logic prevents the autopilot from engaging during 5 s after liftoff.)

200 ft AGL

200 ft AGL

160 ft AGL

100 ft AGL

500 ft AGL

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20
Q

MAXIMUM WIND CONDITIONS FOR AUTOMATIC APPROACH, LANDING, AND ROLL-OUT

Maximum headwind

Maximum crosswind

Maximum tailwind at landing

A

38kt

30kt

below 8000ft - 15kt
above 8000ft - 10kt

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21
Q

GLS CATEGORY I

Minimum decision height

A

200ft

At least one autopilot must be engaged in approach mode, and APPR1 must be displayed on the FMA.

If the flight crew performs an automatic approach without autoland, the autopilot must be disengaged no later than 160 ft AGL.

22
Q

ILS CATEGORY II

Minimum decision height

A

100ft

At least one autopilot must be engaged in approach mode, and LAND2, LAND3 SINGLE or LAND3 DUAL must be displayed on the FMA.

If the flight crew performs an automatic approach without autoland, the autopilot must be disengaged no later than 80 ft AGL.

23
Q

ILS CATEGORY III FAIL-PASSIVE

Minimum decision height

A

50ft

At least one autopilot must be engaged in approach mode, and LAND3 SINGLE or LAND3 DUAL must be displayed on FMA.

24
Q

ILS CATEGORY III FAIL-OPERATIONAL

Alert Height
Min RVR
With DA
Without DA

A

200ft
75m
<50ft
0ft

Both APs must be engaged in approach mode and LAND3 DUAL must be displayed on FMA.

25
Q

AUTOMATIC LANDING
RUNWAY CONDITIONS

CAT IIIB operation on contaminated runways?

A

is not authorized

The performance of the ROLL OUT mode is demonstrated on dry and wet runways (up to 3 mm of water). The roll out performance on contaminated runways was not demonstrated and cannot be assured.

Therefore, if the flight crew aims to keep AP engaged during rollout on a contaminated runway, they must apply all of the following:
Consider the maximum crosswind value that is the most restrictive (associated either with the runway condition, or with autoland)

Be prepared to disengage the AP and take over manually if the ROLL OUT directional control is no longer sufficient.

26
Q

APPROACH CAPABILITY

FAIL-OPERATIONAL AUTOMATIC LANDING SYSTEM

A

An automatic landing system is fail-operational if, in the event of a failure below alert height, the remaining part of the automatic system allows the aircraft to complete the approach, flare, and landing. A LAND3 DUAL system is a fail-operational automatic landing system.

Note:
In the event of a failure, the automatic landing system operates as a fail-passive system.

27
Q

FAIL-PASSIVE AUTOMATIC LANDING SYSTEM

A

An automatic landing system is fail-passive if, in the event of a failure, there is no significant out-of-trim condition, or deviation of flight path or attitude, but the landing is not completed automatically. A LAND3 SINGLE system is a fail-passive automatic landing system.

Note:
With a fail-passive automatic landing system, the flight crew controls of the aircraft after a failure.

28
Q

ALERT HEIGHT

A

The alert height is the height above the runway, above which a LAND3 autoland would be discontinued, and a missed approach executed, if a failure occurred in either the airplane systems, or the relevant ground equipments. Below the alert height, if such a failure occurs, the flare, touchdown and roll-out may be accomplished using the remaining automatic system.

Note:
Below 200 ft RA, the FG freezes the LAND3 capability. Therefore, a failure occurring below 200 ft RA does not change the capability of the system.

29
Q

APU START

A

5s before APU Master ON

aborted APU start or APU shutdown, wait 60 s before a new start attempt.

This 60 s period is due to the ECB inhibition logic after an aborted APU start or APU shutdown.

After three consecutive APU start attempts, the flight crew must wait 60 min before a new start attempt.

This 60 min period is to allow the APU starter to cool down.

30
Q

APU OPERATIONAL ENVELOPE:

-APU START?

APU GENERATORS:

-On ground, each APU generator can supply up to X KVA?

-In flight, up to ?

APU BLEED AIR SUPPLY:

-APU bleed air can be supplied up to?
-Use of APU bleed air for wing anti-ice?

A

20 000FT

120 KVA.

22 500 ft, only one APU generator can operate.

22 500 ft, provided the aircraft airspeed is below M 0.56.

Use of APU bleed air for wing anti-ice is not permitted.

31
Q

EA OIL LImitations:

max temp?
min start temp?
min temp for TO?
min press?

A

177 for 5 sec or 163 for 20min
-40
50
25psi

32
Q

EA OIL QUANTITY

A

FT below 10 h - 10 qts

FT at or above 10 h - 6 qts + 0.4 qt/h

33
Q

RR OIL

MAX CONT TEMP:
MIN START TEMP:
MIN TEMP FOR TO:

A

Maximum continuous temperature - 196°C

Minimum starting temperature - −40°C

Minimum temperature prior to takeoff - 40°C

34
Q

RR OIL QUANTITY

A

OAT < 0 °C

FT below 14h - 13 qts
FT at or above 14h - 6 qts + 0.5 qt/h

OAT ≥ 0 °C

FT below 8 h - 10 qts
FT at or above 8 h - 6 qts + 0.5 qt/h

35
Q

RR MINIMUM OIL PRESSURE

A

25PSI

36
Q

EA STARTER

A

Three periods of 5 min continuous starter use are possible.

2 min cool down for each minute of starter time.

When the starter accumulates 15 min of use, the starter must cool down for 30 min before a new engine start is attempted.

37
Q

RR STARTER

A

Maximum continuous starter operation is 5 min:

-Two consecutive cycles of 2 min duration maximum, plus one additional cycle of 1 min, with a run down to zero N3 between each cycle, or

-One 5 min cycle.

Wait 30 min after the last cycle to allow the starter to cool.

38
Q

SOFT GO-AROUND

A

prohibited on airport with missed approach gradient greater than 8%.

39
Q

Maximum operating altitude with slats and/or flaps extended

A

20 000FT

40
Q

MAXIMUM FLAPS/SLATS SPEEDS
0
1
1+F
2
3
FULL

A

0 - VMO/MMO
1 - 263KT
1+F - 222KT
2 - 220KT
3 - 196KT
FULL - 182KT

41
Q

MINIMUM FUEL TEMPERATURE

JET A
JETA1

MAXIMUM FUEL TEMPERATURE

A

JETA - 40C
JETA1 - 47C

53C

42
Q

MAXIMUM ALLOWED WING FUEL IMBALANCE

FEED 1/4
FEED 2/3
INNERS
MIDS
OUTERS

A

3000KG
3000KG
3000KG
2500KG
1200KG

43
Q

MINIMUM FUEL QUANTITY BEFORE PUSHBACK

A

each feed tank is more than 4 000 kg

44
Q

BRAKE TEMPERATURE

A

300C

45
Q

In the case of BWS Fault

A

-180 ° turn on a 60 m (200 ft) wide runway is forbidden,

-180 ° turn on a turn pad is not recommended if the runway is wet.

46
Q

Maximum altitude at which the landing gear can be extended

A

21 000 ft
The speed limitation for landing gear extension is 250 kt/M 0.55. The Landing Gear Control and Indication System (LGCIS) uses only speed limitation to inhibit the landing gear extension. To avoid any inadvertent landing gear extension out of speed limit when the aircraft flies in Mach, the cross-over altitude corresponding to the speed of 250 kt/M 0.55 is introduced as the highest altitude target to extend the landing gear. This altitude is 21 000 ft. Nevertheless in the case of emergency, respecting the M 0.55 speed limitation, the flight crew can extend the landing gear if necessary.

47
Q

The following limitations apply in order to be able to taxi or to tow the aircraft with deflated tires

In the case of towbarless towing?

Maximum taxi speed?

Maximum nosewheel steering (NWS) angle?

Up to (?) tires can be deflated with the following maximum of deflated tires per landing gear:

A

No deflated nose landing gear tire

3 kt

30 °

9

-One deflated tire on the nose landing gear, or/and

-Two deflated tires per body landing gear provided they are not on the same axle, or/and

-Two deflated tires per wing landing gear provided they are not on the same axle.

***For runway vacating only, the two deflated tires on the body or wing landing gear can be on the same axle.

For taxi, the two deflated tires can be located on the center axle of the body landing gear.

48
Q

After a landing with one abnormal wing or body landing gear, the following limitations apply in order to taxi or to tow the aircraft:

Maximum taxi speed?

Maximum NWS angle?

A

5 kt

50 °

49
Q

TAXI WITH ONE ABNORMAL WING OR BODY LANDING GEAR:

-For taxi with one abnormal WLG, the maximum recommended wind?
-For taxi on Dry and Wet runway/taxiway with one abnormal BLG, max wind?

A
  • 40kt (maximum recommended crosswind for landing is applicable)
  • The maximum crosswind component is limited to 35 kt (gust included)
50
Q

During refueling, do not use the external lights, except for?

A

NAV/LOGO/WING

51
Q

Ground alignment of the IRS is possible in latitudes between

A

82 ° North and 78.25 ° South.

52
Q

In NAV mode, the IR will not provide valid magnetic heading and magnetic track angle?

A

North of 82 ° North

North of 73 ° North between 90 ° and 120 ° West (magnetic polar region)

South of 60 ° South.

When flying at latitudes beyond these limits, TRUE reference must be selected.

A380 - Memory Items / Limitations (2 decks)

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