R 1EFF : 001-049, 051-099, 101-149, 151-199, 1 05-56-00Page 649 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1
R **ON A/C 301-399,
R Subtask 05-56-00-220-054-A
R E. Position of the Points of the Vertical Stabilizer
R (1) Verticality check
R (Ref. Fig. 610A/TASK 05-56-00-991-012-A)
R (a) Install the SIGHTING RODS SET (98D08103500000) on the points 30,
R 31, 32 and 33 L.
R (b) Align a theodolite at the dimension of 642.5 mm (25.2952 in.) to
R the left of the aircraft centerline.
R (c) Write down the variations in relation to the optical axis.
R (2) X position of the point 32 L
R (Ref. Fig. 611B/TASK 05-56-00-991-013-B)
R (a) Install the tool.
R (b) Align the 0 mark of the tool with the two theodolites on each
R side of the vertical stabilizer.
R (c) Make a mark the two sight lines on the floor and the intersection
R point.
R (d) Write down the X dimension in relation to the point 11A.
R Subtask 05-56-00-220-055-A
R F. Position of the Engine Pylon
R (1) X position of the points 40 and 41 of the pylon
R (Ref. Fig. 612A/TASK 05-56-00-991-014-A)
R (a) Make a projection to the floor of the points of the tool with the
R PLUMB LINE PYLON (98D08103501000). Measure the X dimension of
R these points in relation to the point 11A.
R (2) Y position of the points 40 and 41 of the pylon
R (Ref. Fig. 612A/TASK 05-56-00-991-014-A)
R (a) Make a projection to the floor of the points of the tool with the
R PLUMB LINE PYLON (98D08103501000). Measure the Y dimension of
R these points in relation to the aircraft centerline.
R (b) Calculate the Y dimensions of the points 40 and 41 : -1100 mm
R (43.3071 in.)
R (3) Calculate the angle of the pylons
R (Ref. Fig. 612A/TASK 05-56-00-991-014-A)
R (a) Enter the Ya and Yb values for the pylon measurements on the
R measurement table.
R YA : in relation to the pylon centerline for the forward external
R point
R YB : aft external point
R YA = Y 40 - Ya
R YB = Y 41 - Yb
R YB - YA
R tg Alpha = -----------
R (X41 - X40)
R (b) Calculate Alpha (Refer to the applicable table).
R (4) Z value of the points 40 and 41
R (Ref. Fig. 605A/TASK 05-56-00-991-007-A)
R (a) Measure the height of the points 40 and 41. Use a sight tube set
R at -3500 mm (137.7953 in.) from the horizontal datum of the
R fuselage.
R Subtask 05-56-00-220-056-A
R G. Position of the Landing Gear
R (1) Nose landing gear (NLG)
R (a) X position
R (Ref. Fig. 613A/TASK 05-56-00-991-015-A)
R 1 Make a projection to the floor of the centerline of the NLG_
R jacking point with SET-PLUMB BOBS MLG NLG WHEELS
R (98D08003000000).
R 2_ Align a cord with HOLDING SET - MEASURING CORD
R (98A08001005000) along the centerline of the aircraft through
R the points 11A and 12.
R 3_ Write down the X position of the jacking point in relation to
R the point 11A (dimension XC).
R 4_ Calculate the position of the axis of the shock strut of the
R landing gear.
R (b) Y position
R (Ref. Fig. 613A/TASK 05-56-00-991-015-A)
R 1_ Measure the variation between the axis of the NLG shock strut
R and the aircraft centerline.
R 2_ The sign of the deviation is + if the offset of the axis of
R the shock strut is to the right. It is - if the offset is to
R the left.
R (c) Verticality of the axis of the shock strut
R (Ref. Fig. 613A/TASK 05-56-00-991-015-A)
R 1_ Write down the angle Alpha (left side) (in a plane
R perpendicular to the aircraft centerline). Write down the
R angle Beta (in a plane parallel to the aircraft centerline).
R Do these measurements with a clinometer.
R (2) Main landing gear (MLG)
R (a) X position
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