TM 55-2840-241-23
CHAPTER 9
FINAL ENGINE ASSEMBLY
9-1. Scope
This chapter provides instruction for installing
major engine assemblies and components on the
engine while it is installed in the airframe or in the
6795579 engine assembly turnover stand. (See figure
2-8.)
Use only chrome plated steel or unplated
steel tools for the assembly procedures
described in this manual. The use of cad-
mium or zinc plated tools is not permitted
since these platings are prone to chipping
and flaking. Should these chips enter the
engine, they may contaminate the lubrica-
tion system, ultimately clogging the filters
or produce intergranular attack on nickel
or titanium base alloys at elevated tem-
peratures.
9-2. Combustion Section Installation.
Install the combustion section on the engine while
the engine is installed in the airframe or while it is
installed in turnover stand, tool No. 6795579. (See
figure 2-8.) If the turnover stand is used, rotate the
engine in the stand to a vertical position with the
compressor on the bottom.
a. Install the first stage nozzle shield (22, figure
3-8).
(1) Apply anti seize compound (item 15, table
2-2), and install two positioning plugs (21). Tighten to
100-150 in. lb. and secure with lockwire (item 10, table
2-2).
b. Place the combustion liner (3) over the first-stage
turbine nozzle shield with the igniter plug opening at
the nine o’clock position (as viewed from the rear of the
engine).
c. Slip the retaining rings (17) over the large ends of
the compressor discharge air tubes (18).
d. Apply lubricant (item 31, table 2-2) to the seal
ring assemblies (19 and 20) if they do not incorporate a
previously applied bonded lubricant. Install the indi-
vidual components of the seal assemblies (19 and 20) on
the compressor discharge air tubes (18). On the small
end of air tubes (18), position the ring gaps 180 degrees
apart with the gap of the seal rings to the outboard side
of tubes (18). On the large end of air tubes (18), position
the ring gaps 180 degrees apart with the gap of the seal
rings to the inboard side of tubes (18).
e. Insert the left-hand compressor discharge air
tube (18) through the firewall. Compress the seal ring
with the compressor discharge air tube-to-compressor
scroll installation clamp, tool No. 6799953. (See figure
2-3.) Mate the air tube (18) with the compressor scroll;
then, remove the installation clamp.
f. Install the right-hand compressor discharge air
tube (18) in the same manner used for installing the
left-hand tube.
g. Compress the seal rings at the large end of air
tubes (18) with the compressor discharge air tube-to-
outer combustion case installation clamps, tool No.
6799952. (See figure 2-3.) Then, place the outer com-
bustion case (6) over combustion liner (3) while mating
case (6) to compressor discharge air tubes (18). Case (6)
is properly indexed when the drain port is at the bot-
tom of the engine. Also, check to ensure that the igniter
plug hole in outer combustion case (6) aligns with the
igniter plug hole in combustion liner (3) before insert-
ing attaching bolts.
h. Coat the threads of the 24 outer combustion case
attaching bolts (1,2) lightly with antiseize compound
(item 15, table 2-2). Secure the outer combustion case
(6) to the gas producer turbine support with the 24
bolts (1,2) and nuts (5). The half-inch length bolt is used
to secure the thermocouple harness clamp (4) on the
rear side of the splitline flange at bolt position 6
(viewed from the rear of the engine with 1 at top cen-
ter). Tighten nuts (5) to 20-30 in. lb. Remove the
Change 14 9-1
