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Jetstar > Limitations MAIN > Flashcards

Limitations MAIN Flashcards

1
Q

Turbulence penetration speed

A

Up to FL200 = 250k FL200 - FL310 = 275 Above FL 310 = 0.76M Signs ON A/P keep on A/THR disconnect if changes excessive. Consider descent for buffet margin. For approach use A/ THR in managed speed.

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2
Q

A320 Max Certified Pax

A

180

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3
Q

A320 Wingspan

A

34.1m

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4
Q

Largest Radius

A

Wingtip

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5
Q

Min pavement Width for turn

A

22.9m

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6
Q

MTOW

A

77,000KG

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7
Q

MLW

A

66,000kg

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8
Q

MZFW

A

62,500 kg

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9
Q

G limit

A

Clean -1 to +2.5 With Flap/Slat 0 to +2

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10
Q

Max Alt Certified

A

39,800ft

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11
Q

Max Alt for take off & landing

A

9,200ft

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12
Q

Nominal Rwy Width?

A

45M

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13
Q

Max Rwy Slope

A

+- 2%

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14
Q

Max Tailwind

A

Take off & Landing 10k except; VWY VWZ = 15 k Take off 10k Landing VWT 15k T/off and LDG

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15
Q

Max Crosswind for take off & Ldg

A

38 knots Gusts includedApplicable to: ALLTAKEOFF LIMITATIONS ON CONTAMINATED RUNWAYSTakeoff is not recommended on the following runway conditions:‐ Wet ice‐ Water on top of Compacted Snow‐ Dry Snow or Wet Snow over Ice

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16
Q

Max wind for pax door operation

A

65 k

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17
Q

Max operating speed Vmo Mmo

A

350 knots 0.82 Mach

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18
Q

Manoeuvring speed

A

.78 Mach into 300k @ 30,000 260k 10,000 & below

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19
Q

Max tyre speed

A

195 knots

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20
Q

Max Slat Speed

A

230 knots

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21
Q

Max Flap 1 speed

A

215 k

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22
Q

Max flap 2 speed

A

200 knots

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23
Q

Max flap 3 speed

A

185 knots

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24
Q

Max flap full speed

A

177 knots

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25
Q

Vle

A

280 knots Mach 0.67

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26
Q

Vlo ext

A

250 Knots

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27
Q

Vle retract

A

220 knots

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28
Q

Max alt gear extended

A

25,000 ft

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29
Q

Minimum height for A/P on take off

A

100 feet and/or 5 seconds

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30
Q

EGT for Starting

A

635 degrees

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31
Q

EGT for TOGA

A

635 for 5 Mins, or 10 OEI650 for A321

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32
Q

MCT

A

610

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33
Q

Minimum Oil quantity

A

11 quarts plus 0.3 for every hour of flight

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34
Q

Minimum Cockpit OXY px

A

1500 psi Orange Half box appears, see LIM-35 P 1/2 for exact Min Limits.

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35
Q

Minimum Oil Px

A

60 Psi

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36
Q

Max N1

A

100%

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37
Q

Max N2

A

100%

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38
Q

Starter limits

A

3 consecutive cycles: 2 cycles of 2 min, followed by 3rd cycle of 1 min. Pause between start attempts 15 secs Cooing period following 3 start attempts or 4 mins of continuous cranking: 30 Mins No running engagement of starter when N2 is above 10% on gnd or 18% in flight

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39
Q

Reverse thrust

A

Not permitted in flight. Not permitted to back aircraft Max not below 70k Idle permitted to A/C stops

40
Q

Max Wiper operation speed

A

230 kt

41
Q

Cockpit Window open

A

200k

42
Q

Narrow Runway crosswind limits

A

SOP’s Takeoff dry………………………38kt Takeoff Wet……………………..33kt Landing Dry………………………30kt Landing Wet………………………20kt Refer CASA INSTRUMENT OM1

43
Q

Max Taxi (Ramp) weight

A

77400Kg

44
Q

Max Wind for Cargo door operation

A

40k, 50k if on leeward side of A/C and must be closed by 65k

45
Q

TAKEOFF LIMITATIONS ON CONTAMINATED RUNWAYS

A

Takeoff is not recommended on the following runway conditions: ‐ Wet ice ‐ Water on top of Compacted ‐ Dry Snow or Wet Snow over Ice

46
Q

TAXI speed

A

From Limitations: When the taxi weight is higher than 76 000 kg (167 550 lb), do not exceed a taxi speed of 20 kt during a turn. From OM 1 Max speed 30knots, 10 knots prior to a sharp turn.

47
Q

STALL SPEED

A

EXAMPLE : DATA : 60 000 kg (132 276 lb), pressure altitude 15 000 ft, clean configuration. RESULT : VS1G CAS = 150 kt

48
Q

Ram Air Inlet

A

Only open if px diff is less than 1psi

49
Q

Maximum positive differential pressure

A

9.0 PSISafety Relief Valve Setting 8.6 PSI

50
Q

Maximum negative differential pressure

A

-1 PSI

51
Q

Avionics Ventilation

A

During ground operations, limit the aircraft electric power supply with avionics ventilation system in normal configuration as follows : OAT = 49 °C no limitation OAT = 55 °C time limit 2 h OAT = 60 °C time limit 1 h OAT = 64 °C time limit 1/2 h

52
Q

Minimum height for A/P

A

Minimum height for use of the autopilot in: ‐ Straight-in NPA……………….. applicable minimum ‐ ILS approach when CAT2 or CAT3 is not displayed on the FMA …………….160 ft AGL ‐ PAR approach (Precision Approach Radar) ……………………………. 250 ft AGL Use of the AP and/or FD is authorized in PAR approach, with HDG V/S or TRK FPA. ‐ Go-around (AP or FD engagement) 100 ft AGL ‐ All other phases…………. 500 ft AGL Use of the AP or FD in OPEN DES or DES mode is not permitted in approach

53
Q

USE OF NAV AND FINAL APP MODES FOR NON-PRECISION APPROACH

A

NAV, or NAV and FINAL APP mode may be used for VOR, VOR/DME, NDB, NDB/DME or RNAV (including GPS) approach, but not for ILS, LOC, LOC-BC, LDA, SDF, or MLS final approach. For instrument procedures not coded in the WGS 84 coordinate system, the GPS must be deselected, unless the shift between the local coordinate system and the WGS 84 is found acceptable for the intended operation. Note: 1. The assesment of this shift can be done: ‐ In flight, monitoring the NAVAID raw data in non RNAV procedures, ‐ On ground performing a GPS survey of the procedure waypoints. 2. RNAV (GPS) and RNP RNAV approach procedures require WGS 84 coordinates and GPS. FINAL APP mode guidance capability with GPS PRIMARY has been demonstrated down to MDH/DH (barometric) 250 ft. VOR, VOR/DME, NDB or NDB/DME approach procedures may be performed, in NAV, or NAV and FINAL APP mode, provided AP or FD is used, and: ‐ GPS PRIMARY is available. In this case, the reference NAVAID may be unserviceable, or the airborne radio equipment may be inoperative, or not installed, provided operational approval is obtained. ‐ Without GPS PRIMARY: • The reference NAVAID and the corresponding airborne equipment is serviceable, tuned, and monitored during the approach, or • The radio NAVAID coverage supports the RNP value, specified for the approach procedure, and an operational approval is obtained. For GPS approach, GPS PRIMARY must be available. RNAV approach without GPS PRIMARY may be performed only if the radio NAVAID coverage supports the RNP value and HIGH accuracy is displayed on the MCDU with the specified RNP, and operational approval is obtained. NAV mode may be used in the terminal area, provided: ‐ GPS PRIMARY is available, or ‐ HIGH accuracy is displayed, and the appropriate RNP is checked or entered on the MCDU, or ‐ NAVAID raw data is monitored.

54
Q

TAKEOFF IN GPS PRIMARY

A

For certain airports, where the difference between the local coordinate system and WGS 84 (geodesic standard used by GPS, FMS) is not negligible, an incorrect NAV guidance may occur after takeoff. GPS must be deselected for takeoff from these airports, until a safe altitude is reached.

55
Q

ILS CATEGORY II

A

Minimum decision height………..100 ft AGL At least one autopilot must be engaged in APPR mode, and CAT 2, CAT 3 SINGLE or CAT 3 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 at 80 ft AGL

56
Q

ILS CATEGORY III FAIL PASSIVE (SINGLE)

A

MDH……………………………………50 ftAt least one autopilot must be engaged in APPR mode, and CAT 3 SINGLE or CAT 3 DUAL must be displayed on the FMA. A/THR must be used in selected or managed speed.

57
Q

ILS CATEGORY III FAIL OPERATIONAL (DUAL)

A

A/THR must be used in selected or managed speed.Alert height……………….100 ft‐ CAT III with DH : Minimum decision height……………………….22 ft2 autopilots must be engaged in APPR mode and CAT 3 DUAL must be displayed on the FMA.‐ CAT III without DH :2 autopilots must be engaged in APPR mode and CAT 3 DUAL must be displayed on the FMA. Minimum RVR……………………. 75 m

58
Q

ENGINE OUT

A

CAT II and CAT III fail passive autoland are only approved in configuration FULL, and if engine-out procedures are completed before reaching 1 000 ft in approach.

59
Q

MAXIMUM WIND CONDITIONS FOR CAT II OR CAT III AUTOMATIC APPROACH LANDING AND ROLL OUT

A

Headwind: 30 ktTailwind : 10 ktCrosswind : 20 kt (except Sharklet 15K if Auto Roll Out)Note: Wind limitation is based on the surface wind reported by ATC. If the wind displayed on ND exceeds the above-noted autoland limitations, but the tower reports a surface wind within the limitations, then the autopilot can remain engaged. If the tower reports a surface wind beyond limitations, only CAT I automatic approach without autoland can be performed.

60
Q

AUTOMATIC LANDING

A

CAT II and CAT III autoland are approved in CONF 3 and CONF FULL. Automatic landing is demonstrated: ‐ With CAT II and CAT III ILS beam. ‐ With slope angle within (-2.5 °, -3.15 °) range. ‐ At or below the maximum landing weight. ‐ For airport elevation at or below 6 500 ft. ‐ At approach speed (VAPP) = VLS + wind correction. Minimum wind correction 5 kt, maximum wind correction 15 kt. Automatic rollout performance has been approved on dry and wet runways, but performance on snow-covered or icy runways has not been demonstrated.

61
Q

ILS AUTOMATIC LANDING IN CAT I OR BETTER WEATHER CONDITIONS

A

The automatic landing system’s performance has been demonstrated on runways equipped with CAT II or CAT III ILS approaches. However, automatic landing in CAT I or better weather conditions is possible on CAT I ground installations or when ILS sensitive areas are not protected, if the following precautions are taken: ‐ The airline has checked that the ILS beam quality and the effect of terrain profile before the runway have no adverse effect on AP/FD guidance. In particular, the effect of terrain discontinuities within 300 m before runway threshold must be evaluated. ‐ The crew is aware that LOC or GS beam fluctuations, independent of the aircraft systems, may occur and the PF is prepared to immediately disconnect the AP and take appropriate action, should unsatisfactory guidance occur. ‐ At least CAT2 capability is displayed on the FMA, and CAT II/III procedures are used. ‐ Visual references are obtained at an altitude appropriate to the performed CAT I approach, otherwise go–around is initiated.

62
Q

AUTOTHRUST FUNCTION

A

Use of the autothrust is approved with, or without, AP/FD in selected or managed mode.

63
Q

MAX continuous load per generator

A

100 % (90 KVA)

64
Q

MAX continuous load per TR (continuous)

A

200 A

65
Q

Max operating altitude with slats and/or flaps extended

A

20 000 ft.

66
Q

MAXIMUM ALLOWED WING FUEL IMBALANCE - INNER TANKS (OUTER TANKS BALANCED).

A

Tank Fuel Quantity (Heavier tank) / Max allowed imbalance Full / 1 500 kg (3 306 lb) 4 300 kg (9 479 lb) / 1 600 kg (3 527 lb) 2 250 kg (4 960 lb) / 2 250 kg (4 960 lb) The variation is linear between these values (No limitation below 2 250 kg /4 960 lb)

67
Q

OUTER TANKS Maximum allowed imbalance

A

690 kg

68
Q

FUEL TEMPERATURE

A

MAXI 54 °C MINI -43 °C

69
Q

MINIMUM FUEL QUANTITY FOR TAKEOFF

A

1 500 KG WING TK LO LVL warning must not be displayed on ECAM for takeoff.

70
Q

FUEL TANK MANAGEMENT

A

‐ Tanks must be emptied in the following order: • center tank then wing tanks. ‐ Take off on center tank is prohibited.

71
Q

HYDRAULIC Normal operating pressure

A

3 000 PSI ± 200

72
Q

Maximum brake temperature for take off (brake fans off)

A

300 °C

73
Q

TAXI WITH DEFLATED TIRES

A

If tire damage is suspected after landing or after a rejected takeoff, an inspection of the tires is required before taxi. If the tire is deflated but not damaged, the aircraft can be taxied at low speed with the following limitations : 1. If one tire is deflated on one or more gears (ie. a maximum of three tires), the speed should be limited to 7 kt when turning. 2. If two tires are deflated on the same main gear (the other main gear tires not being deflated), speed should be limited to 3 kt and the nose wheel steering angle limited to 30 °.

74
Q

NOSEWHEEL STEERING (NWS)

A

The nosewheel steering angle is limited to 75 ° when using the handwheels. For towing and pushback, the nosewheel steering angle is limited to 95 °. Towbarless towing and pushback on the nose landing gear is approved for the “accepted towbarless towing vehicles” that are listed in the Airbus SIL 09-002, but the nosewheel steering angle must be limited to 85 °

75
Q

INERTIAL REFERENCE SYSTEM

A

IRS ground alignment has been demonstrated to be satisfactory up to 73 ° latitude. In NAV mode, the IRS will not provide a valid magnetic heading: • For latitude greater than 73 ° North, • For latitude greater than 60 ° South. Flight outside the above-noted limits is prohibited.

76
Q

ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS)

A

• Aircraft navigation is not to be predicated on the use of the terrain display. The terrain display is only intended as a situational awareness tool, and may not provide the accuracy on which to solely base terrain avoidance maneuvers. • The EGPWS enhanced function should be inhibited (TERR pushbutton to OFF, on the GPWS panel) when the aircraft position is less than 15 nm from the airfield : ‐ For operations to/from runways not incorporated in the EGPWS database. ‐ For specific approach procedures, which have previously been identified as potentially producing false terrain alerts.

77
Q

ISIS

A

When both PFDs are lost, the ISIS bugs function must not be used.

78
Q

APU OIL QUANTITY

A

The APU may be started and operated even if the LOW OIL LEVEL ECAM advisory is displayed. Maintenance action is required within next 10 h of APU operation.

79
Q

APU STARTER

A

After 3 starter motor duty cycles, wait 60 min before attempting 3 more cycles.

80
Q

APU ROTOR SPEED Maximum N

A

107 %Note: The APU automatically shuts down at 107 % N speed, that appears on the ECAM. This corresponds to an actual N speed of 106 %.

81
Q

APU EGT

A

Maximum EGT…………………………..675 °C Maximum for start (blw 35 000 ft)..1090 °C Maximum for start (abv 35 000 ft)…1120 °C

82
Q

APU start envelope

A

In the APU start envelope, the APU start is guaranteed within 3 consecutive start attempts. Envleope = Throughout normal flight envelope.

83
Q

APU ELECTRICAL POWER

A

Electric power extraction: At or below 25 000 ft: ISA + 35 °C and below…………………. 90 KVA

84
Q

APU Air bleed and generator load in flight:

A

TWO PACKS UP TO 15 000 ft 100 % (90 KVA) ONE PACK UP TO 22 500 ft 78 % (70 KVA) ENG START UP TO 20 000 ft IF SPEED ABOVE 180 kt 92 % (83 KVA) ENG START UP TO 15 000 ft IF SPEED BELOW 150 kt 92 % (83 KVA) ‐ Air bleed extraction for wing anti-icing is not permitted.

85
Q

OIL TEMPERATURE

A

Minimum prior to exceeding idle -10 °C Minimum prior to takeoff……………50 °C Max continuous temperature……155 °C Max transient temperature (15 min)..165 °C Minimum starting temperature…………-40 °C

86
Q

RPM

A

N1 max……………………………. 100 % Note: The N1 limit depends upon ambient conditions and engine airbleed configuration. These may limit N1 to a value lower than the one noted above (For additional information, refer to Performance/Thrust Ratings). N2 max……………………………. 100 %

87
Q

STARTER

A

‐ 3 consecutive cycles : 2 cycles of 2 min each, followed by a 3rd cycle of 1 min . ‐ Pause between start attempts : 15 s. ‐ Cooling period, following 3 start attempts or 4 min of continuous cranking : 30 min . ‐ No running engagement of the starter, when N2 is above 10 % on ground, and 18 % in flight.

88
Q

REDUCED THRUST TAKEOFF

A

Takeoff at reduced thrust is only permitted, if the airplane meets all applicable performance requirements at the planned takeoff weight, with the operating engines at the thrust available for the assumed temperature. ‐ Thrust reduction must not exceed 25 % of the full rated takeoff thrust. To meet this requirement, the flexible temperature must not be higher than ISA + 55 °C(T MAX FLEX). ‐ The assumed temperature must not be lower than the flat rating temperature, or the current OAT. ‐ Takeoff at reduced thrust is not permitted on contaminated runways. ‐ Takeoff at reduced thrust is permitted with any inoperative item affecting the performance, only if the associated performance shortfall has been applied to meet all performance requirements at the takeoff weight, with the operating engines at the thrust available for the flex temperature.

89
Q

POWER PLANT CROSS WIND OPERATION ON GROUND

A

This engine is capable of starting in crosswinds up to 35 kt .

90
Q

Narrow RunwaysPRO-SPO-60 P 2/4

A

Minimum runway width…………30mThe dispatch from/to narrow runways is not allowed in case of :‐ Nose wheel steering inoperative‐ One brake or more inoperative Autoland is not allowed. Diversion to a 45 m wide runway is recommended in case of :‐ Rudder jam‐ Rudder pedal jam‐ Yaw damper system fault‐ All failures leading to the loss of the nose wheel steering (HYD Yellow system loss, double hydraulic failure, double BSCU fault, double LGCIU fault)Maximum demonstrated crosswind for takeoff and landing:Dry runway…………38 kt (gust included) for takeoff and landingWet runway…………33 kt (gust included) for takeoff and landingContaminated runway..10kt (gust included) for takeoff and landing.Note: These maximum demonstrated crosswind values are based on the assumption that the crew have been trained accordingly.Operations on icy runways have not been demonstrated.CAUTION: THERE ARE MORE RESTRICTIVE X-WIND LIMITATIONS IN THE CASA INSTRUMENT OM1

91
Q

F/O PF Limitations Reference:PRO-NOR-JSS-A P 22/36

A

Jetstar Low-Vis Takeoff Approval – FO…… 550 m visibility (VIS RV or RVR). Landing:PF………… Whilst remaining within the criteria for approach procedures, as described in Section 6.4 Approach Procedures – restrictions 200 ft DH/800 m VIS or 550 m RVR. Environmental Limits………… Crosswind max 30 kt however after initial promotion, FOs are limited to a maximum crosswind component of 20 kts until completing 12 months line operations, two recurrent training sessions, and until 30 kt crosswind training completed. Note: If the crosswind exceeds the limit specified for FOs, it is NOT acceptable for other than the duty runway at any airport to be used purely to allow the FO to complete the takeoff or landing.

92
Q

AutoPilot Approach

A

REGO Dependant;Straight in NPA………. Applicable minimumStraight in LNAV/VNAV………..Applicable DACircling App………. CCT ALTILS if CAT2 or CAT3 Not displayed 160ft AGLPAR approach(subject to approval)….250ft AGLGA (AP or FD engagement) 100ft AGLALL OTHER PHASES 500ft AGLUse of the AP or FD in OPEN DES or DES mode is not permitted in approach, unless the FCUaltitude is set to, or above, MDA (MDH) or 500 ft, whichever is the highest.

93
Q

Flight Management Function

A
94
Q

30M Runway LimitsJetstar Standard Operating procedures

A

Ident.: PRO-NOR-JSS-B-20808405.9001001 / 29 MAY 14*JJetstar A320 Narrow Runway Limits.. 30metresCross wind for takeoff and landing on narrow runways:Dry Runway…………..38 kt (gust included) for takeoffDry Runway…………….0 kt (gust included) for landingWet Runway…………… 33 kt (gust included) for takeoffWet Runway…………. 20 kt (gust included) for landingNote: These maximum demonstrated crosswind values are based on the assumption that thecrew have been trained accordingly

95
Q

Narrow RunwaysCASA INSTRUMENT CASA EX26/12

A

Jetstar (14 decks)

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