Limitations

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Author:
Saabass
ID:
292140
Filename:
Limitations
Updated:
2015-01-01 22:34:41
Tags:
limitations
Folders:
Saab
Description:
Limitations for Saab 340
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  1. Span ( without extended wing tips)
    21.44 m
  2. Span (with extended wingtips)
    22.75m
  3. Define icing conditions
    Icing conditions exist when visible moisture in any form is present (such as clouds, fog with visibilityof one mile (1,850 m) or less, rain, snow, sleet, ice crystals) or standing water, slush, or snow (hardpacked snow excluded) is present on the ramps, taxiways or runways and the OAT or SAT is +5°Cand below during ground and flight operation. In these conditions, or whenever the blue ICE SPDstatus light or EAI is on, the minimum speed for flight in icing conditions must be observed. IASmode must be selected on the FD if climbing when these conditions exist.

    CAUTIONThe defined or minimum speed for flight in icing conditionsmust be observed whenever the blue ICE SPD status light orEAI is ON regardless of the actual conditions the aircraft isoperating in.
  4. Maximum Flaps Extended Speeds
    Flaps may only be extended on ground, as required for take-off, low altitude holding, approach and landing, up to a maximum altitude of 14,000 ft.

    (M)Flap Position VFE7 or 15 175 KIAS (M)20 165 KIAS (M)35 140 KIAS (M)
  5. Maximum Landing Gear Speeds
    Retraction Speed VLOR = 150 KIAS (M)Extension Speed VLOE = 200 KIAS (M)Emergency Extension Speed VLOEE = 200 KIAS (M)Extended Speed VLE = 200 KIAS (M)
  6. Minimum Control Speeds
    • VMCL = 103 KIAS (Flaps 20 and 35) (SF340A) VMCL = 106 KIAS (Flaps 20 and 35) (SF340B)
    • VMCL = 103 KIAS (Flaps 20 and 35) (SF340B (WT))
  7. Maximum Operating Speed Vmo
    VMO = 250 KIAS up to approx. 16,000 ft. Above this altitude VMO decreases as indicated by theVMO pointer to approx. 210 KIAS at 25,000 ft.
  8. Maximum Manoeuvring Speed, VA
    VA = 180 KIAS
  9. Maximum Rough Air Penetration Speed, VRA
    VRA = 190 KIAS up to 21,000 ft ISA. Above this altitude, reduce the speed as indicated by the VMOpointer minus 30 kts.
  10. Maximum Take-off Tailwind Component
    10 kts
  11. Maximum Landing Tailwind Component
    10 kts
  12. Maximum Operating Altitude
    25,000 ft
  13. Maximum Crosswind Component
    >23 m rwy width - 35 kts

    23 m rwy width - 25 kts

    <23 m rwy width 17kts
  14. Airborne Collision Avoidance System (ACAS)
    Deviations from the ATC assigned altitude is authorised only to the extent necessary to complywith an ACAS Resolution Advisory (RA)
  15. Flight Director
    Use of flight director information in go-around mode during take-off is not authorised
  16. Autopilot
    • Autopilot operations not authorised:
    • • Below 200 ft AGL - during take-off or go-around.
    • • Below 500 ft AGL - during cruise.
    • • Below 50 ft AGL - during approach.
    • • Below 100 ft AGL - for a non-coupled approach.

    In icing conditions (as defined) FD/AP IAS MODE IS THE ONLY VERTICAL MODE TO BE USED DURING CLIMB WHEN ICE ACCUMULATION IS OBSERVED OR IF IT IS NOT CERTAIN THERE IS NO ICE ACCUMULATION ON THE AIRCRAFT.

    It is a requirement to disconnect the autopilot following an engine failure and re-trim the aircraft before re-engagement of the autopilot. This is to avoid the autopilot holding roll trim forces in case of an unexpected disconnect (e.g. stall warning)

    Maximum Roll trim tolerance for dispatch + ½ Unit from neutral.
  17. Yaw Damper
    Yaw Damper Operation is not authorised for:

    • Take-off, Go-around or Landing
  18. Flap
    Landing Flap is to be set by 300 ft radio height during normal landing.

    Company requires that the final flap setting is called for at no less than 500 ft AGL.

    • When holding in icing conditions (as defined) Flap 0 must be used.
  19. Cargo Fire
    The cargo compartment is classified as a Class C cargo compartment and has been demonstrated to provide the following minimum fire protection duration, based on cargo compartment configuration and fire protection system installation.

    • 60 min for 340B (WT) (Mod No. 1149 incorporated (2 bottles)).

    • 35 min for all other REX aircraft
  20. Attitude/Heading Reference System
    • During initialisation on ground the aircraft must not be moved.
    • Take-off is not permitted until two minutes after initialisation is completed and the attitude difference between the attitude displayed on both EADIs and the standby attitude indicator is 3 degrees or less (bank and pitch) and the heading on the compass card is not slewing away from the aircraft heading.
  21. WEIGHTS (SF340A)
    Max Taxi Weight (MTW) 12,840 kg

    Max T/O Weight (MTOW) 12,700 kg

    Max Landing Weight (MLW) 12,340 kg

    Max Zero Fuel Weight (MZFW) 11,660 kg
  22. WEIGHTS (SF340B & 340B (WT))
    Maxi Taxi Weight (MTW) 13,290 kg

    Maxi Take-Off Weight (MTOW) 13,155 kg

    Max Landing Weight (MLW) 12,930 kg

    Max Zero Fuel Weight (MZFW) 12,020
  23. Cabin differential pressure
    In flight 7.5

    Landing 0.3

    Cabin Pressure warning 7.5

    Cabin altitude CABIN PRESS warning 10000ft
  24. DC Generators
    Voltage ... V DC 27.5-29 norm 28

    Nominal load per generator ... A – 400 

    Max load for 5 min. A – 600

    Main batteries Voltage... V DC – 24
  25. External power
    VoltageGPU ... V DC 28 – 29.5

    • Battery Cart ...V DC Higher than aircraft
    • batteries for engine start 29.5

    Amp requirement– Normal operation...A 600

    Engine start ...A 1,400 – 1,600
  26. FUEL
    Min fuel takeoff, each tank ... kg 135

    Max imbalance between tanks... kg  90

    LOW LEVEL light... 135

    XFEED AND CONN VALVE switches shall be in the OFF and CLOSED position during take-off and landing in norm ops

    The total quant. of useable fuel is 2,542 kg
  27. Windshield heating
    Time in NORM b4 switching to HIGH...min 7
  28. Pitot Tubes
    Time from switching STBY PITOT ON until full ice-protection is obtained ... 5 min
  29. Windshield Wipers
    In LOW position... kts – 130

    In HIGH position... kts – 160
  30. Altimeters, Operational Tolerances
    • With an accurate QNH set, all the altimeters should read the nominated elevation to within 60 ft.
    • If an altimeter has an error in excess of + 75 ft it is to be considered
    • unserviceable.
    • The SAAB 340 requires all three altimeters for IFR operations; two of the altimeters must read the nominated elevation to within 60 ft. When the remaining altimeter has an error between 60 ft and75 ft, flight under the IFR to the first point of landing, where the accuracy of the altimeter can be rechecked, is approved.
    • In the event that the altimeter shows an error in excess of 60 ft on thesecond check the altimeter must be considered unserviceable
  31. LANDING GEAR
    • Gear extension speed...kts 200
    • Gear retraction speed ...kts 150
  32. Number of brake applications on fully charged brakeaccumulators
    11
  33. Max speed for use of brakes with the anti-skidsystem off or inoperative
    40
  34. POWER PLANT B Model
    • T/O PWR+APR...107% 940 ITT 1396 RPM 5 min
    • 950 ITT 2 min

    T/O PWR no APR... 100% 917 ITT 1396 RPM 5 min 927 ITT 2 min

    Max cont. 100 % 940 ITT 1396 RPM

    Transient (12 sec)... 112% 965 ITT 1572 RPM

    Engine start 965 ITT
  35. Power plant A model
    T/O PWR...108% 930 ITT 1396 RPM

    Max cont. 100 % 917 ITT 1396 RPM

    Transient (12sec)... 118% 960 ITT 1572 RPM

    Engine start 960 ITT
  36. Starter/Generator (S/G) Duty Cycle Limits
    Starter Duty Cycle:– Two start attempts with 3 minutes cooling between, then 25 minutes cooling before subsequent starts

    Motoring: Three 30-second ventilations with 3 minutes cooling between each, then a one-hour cooling period before subsequent starts or motoring.

    Time to light-off (from initial Ng rotation to ITT rise), 20 seconds maximum (direct startonly).

    Maximum time with starter engaged is 70 seconds of which max 30 seconds plain motoring.

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