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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