-in the forward compartment
-at the pax/crew door No 1.
(2)
Refueling wing tanks can also be a method to put the aircraft back into balance. In this case, the weight of the fuel must be added to the aircraft weight.
NOTE : Before ballasts are put on the aircraft,make sure that the
____ limits below are not exceeded (Ref. WBM 1-10-00):
-
maximum weight of section 11
-
maximum loads on cabin floor
-
maximum load on jacking points.
(3) This method is applicable to these aircraft configurations for each of wich a diagram is given:
-
diagram for aircraft on wheels,on dry ground, (Ref. Fig. 213/TASK 05-57-00-991-007)
-
diagram for aircraft on wheels,on wet ground, (Ref. Fig. 214/TASK 05-57-00-991-008)
-
diagram for aircraft on jacks,
(Ref. Fig. 215/TASK 05-57-00-991-009)
-
diagram for aircraft on forward jack or on nose wheel jack, (Ref. Fig. 216/TASK 05-57-00-991-016)
-
diagram for aircraft on one main gear wheel jack, (Ref. Fig. 217/TASK 05-57-00-991-017)
-
diagram for aircraft jacked at main and nose gears for wheel change, (Ref. Fig. 218/TASK 05-57-00-991-018)
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Aircraft on its wheels (on dry ground) (applicable to a parked or towed aircraft) Figure 213/TASK 05-57-00-991-007
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aircraft on its wheels (on wet ground) (applicable to a parked or towed aircraft) Figure 214/TASK 05-57-00-991-008
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Aircraft on jacks
Figure 215/TASK 05-57-00-991-009
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Aircraft on Forward Jack or on Nose Wheel Jack
Figure 216/TASK 05-57-00-991-016
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Aircraft on one Main Gear Wheel Jack
Figure 217/TASK 05-57-00-991-017
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Aircraft Jacked at Main and Nose Gears for Wheel Change
Figure 218/TASK 05-57-00-991-018
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Subtask 05-57-00-210-055
B. Check of the Aircraft Stability.
NOTE : As the same procedure is applicable in any of the above
____ configurations, the diagram related to aircraft on wheels on dry ground is taken as an example (Ref. Fig. 213/TASK 05-57-00-991-007)
(1) Check of aircraft stability: aircraft with two engines installed.
-
without crew
-
without galleys
-
without pallets and containers. For instance, plot point A on the chart from these coordinates:
-weight: 46600 kg (102735.3852 lb)
-CG: 24%.
NOTE : Under these conditions, the aircraft will be safe in winds up
____
to 60 kts (111 km/h).
(2)
Check of aircraft stability after removal of the two engines.
(a)
From point A, make a horizontal line : it cuts across the weight axis at point B.
(b)
From this point B, substract the weight of two removed engines 7000 kg (15432.3540 lb) approx., to get point B'.
(c)
From point A, make a vertical line: it cuts across one division of the "removed engine" scale at point C.
(d)
Make a line across two divisions on this scale (1 division per engine) to get point C'.
(e)
From point C', make a vertical line and from point B', make a horizontal line: these two lines cut at point D. For this point, the diagram gives these values:
-aircraft weight: 39600 kg (87303.0312 lb)
-CG: 35.5%
-permissible wind: 40 kts (74 km/h).
(3)
Check of aircraft stability during engine installation with a hydraulic lift. For the purpose of this example, it is considered that the hydraulic lift puts a 800 kg (1763.6976 lb) contact force on the pylon.
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(a)
Continue vertical line DC' until it cuts across the "contact force" scale to get point E.
(b)
From this point, make a line across one division (0.8
ton/division) to get point E'.
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