-weight: 46600 kg (102735.3852 lb)

 -CG: 24%.

 NOTE : In these conditions, the aircraft will be safe in winds up to
____
 55 kts (102 km/h).

 (2)
 Check the aircraft stability after removal of two engines.

 (a)
 From point A, make a horizontal line: this cuts across the weight axis at point B.

 (b)
 From this point B, subtract the weight of the two removed engines 7000 kg (15432.3540 lb) approx. to get point B'.

 (c)
 From point A, make a vertical line: this cuts across one division of the "removed engine" scale at point C.

 (d)
 Make a line across two divisions on this scale (1 division for each 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%
 -permitted wind: 35 kts (65 km/h).

 (3)
 Check the aircraft stability during engine installation with a hydraulic lift. For this example, we calculate 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'.

 (c)
 From this point E', make a vertical line until it cuts across the horizontal line DB' to get point F. The diagram shows that in these conditions, engine installation is possible in the open air in winds of less than 35 kts (65 km/h).

 (4) Calculate the quantity of ballast necessary for engine installation. The engines are installed in the open air with a maximum windspeed of 45 kts (83 km/h). If necessary, you will install the ballast in the forward cargo-compartment at position 11.
 (a)
 Continue line B'F until it cuts across the 45 kts (83 km/h) average windspeed line at point H.

 (b)
 Continue vertical line FE' until it cuts across the "ballast on section 11" scale at point G.

 (c)
 From point G, make a horizontal line which cuts across the vertical line from H at point J.

 (d)
 Count the number of divisions on the scale between point G and J (in the example, 2.3 divisions). The weight of ballast necessary is thus:

 2.3 x 500 kg (1102.3110 lb) = 1150 kg (2535.3153 lb) In the example given, use the same procedure to calculate the quantity of ballast necessary at cabin door No 1:
 1.6 x 500 kg (1102.3110 lb) = 800 kg (1763.6976 lb)
 NOTE : As the ballast only increases the aircraft weight by a
____
 small quantity, this is ignored.

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R  **ON A/C 301-399, 
R  TASK 05-57-00-200-001-B 
R  Aircraft Stability 
R  1. Reason for the Job__________________ 
R  The method given below is used to do graphical checks of the aircraft 
R  stability. 
R 
R  NOTE : The stability graphs for aircraft on wheels (on dry or wet ground)____ 
R  given in this procedure are applicable to a parked or towed aircraft. 
R  NOTE : With the stabilility graphs (A/C on wheels) given in this____ 
R  procedure,you can do a check of shifting or tipping stability limits, 
R  if you need to know only one shuch limit (when towing for example). 
R  It is also used to calculate the ballast necessary for aircraft stability 
R  under unfavorable conditions in the following configurations: 
R  - aircraft with 2 engines 
R  - 1 or the 2 engines removed 
R  - engine re-installation 
R  2. Job Set-up Information______________________ 
R  A. Referenced Information 
R  -------------------------------------------------------------------------------
R  REFERENCE  DESIGNATION 
R  -------------------------------------------------------------------------------
R  WBM  1-10-00 
R  05-57-00-991-004  Fig. 207 
R  05-57-00-991-005  Fig. 208 
R  05-57-00-991-006  Fig. 209 
R  05-57-00-991-013  Fig. 210 
R  05-57-00-991-014  Fig. 211 
　
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