Pilot Front Support Disassembly and Assembly

TM 9-1270-212-14&P

position the plunger so that the threaded portion extends

conforming to

compound

sealing

e. Apply

l/20-inch beyond the surface of the aft support.

MIL-S-22473, grade T (primer) and grade H, to

quick-release plunger (10) and position the plunger so that

f. Apply the same fluids as in e above to locking screw

the threaded portion extends 1/20-inch beyond the Surface

(11) and tighten the screw. Socket-drive setscrew (13) and

of the aft support.

its locking screw are not secured with sealing compound.

f. Apply the same fluids as in e above to the locking

5-18. Gunner Front Support Disassembly and Assembly

screw (9) and tighten the screw. Socket-drive setscrew (11)

(fig. B-8).

and its locking screw are not secured with sealing

compound.

a. Remove items (1) through (14) and assemble in

5-15. Pilot Front Support Disassembly and Assembly (fig.

reverse disassembly sequence.

B-5).

b. Perform final adjustment of bracket (5) during test

(paragraph 4-24, table 4-2, step 8). At that time, sealing

a. Remove items (1) through (14) and assemble in

reverse disassembly sequence.

compound conforming to MIL-S-22473, grade T (primer)

and grade H, is applied to machine bolt (1).

b. Perform final adjustment of angle bracket (7) during

c. Apply

sealing

compound

conforming to

test (paragraph 4-14, table 4-2, step 12). At that time,

MIL-S-22473, grade T (primer) and grade H, to

sealing compound conforming to MIL-S-22473, grade T

quick-release plunger (11) and position the plunger so that

(primer) and grade H, is applied to machine bolt (5).

the threaded portion extends 1/20-inch beyond the surface

c. Apply MIL-S-22473, grade T (primer) and grade H,

of the front support.

sealing compound to quick-release plunger (12) and

d. Apply the same fluids as in c above to locking screw

position the plunger so that. the threaded portion extends

(8) and tighten the screw. Socket-drive setscrew (12) and its

l/20-inch beyond the surface of the front support.

locking screw (8) are not secured with sealing compound.

d. Apply the same fluids as in c above to locking screw

5-19. Installation of Linkage Assemblies (fig. 5-3).

(8) and tighten the screw. Socket-drive setscrew (13) and its

locking screw (8) are not secured with sealing compound.

a. Remove the two self-locking nuts, four concave

washers, four convex washers, loop clamp (gunner linkage

5-16. Arm Assembly Repair (figs. B-6 and B-9).

only), and two key washers from the two mounting

brackets.

Repair or replace screwlock assembly (1).

b. Secure the front and aft mounting brackets to the

5-17. Gunner Linkage Disassembly and Assembly (fig.

helicopter airframe, using the four screws that were

B-7).

retained in 5-13f.

a. Remove items (2) through (13).

c. Place the concave washer (flat side up) and convex

washer (flat side down) on each mounting bracket.

b. Remove two spring pins (14) by placing aft support

(15) on a block and driving the spring pins out with a 5/32

d. Place the linkage assembly on the mounting brackets.

drift pin.

c. Remove rails (16) and arm assembly (17).

d. Assemble in reverse disassembly sequence. Place rails

The front end of the linkage assembly must be

(16) in aft support (15) so that the grooves in the rails line

supported while the mounting hardware for the

up with the spring-pin holes. Drive in new pins (14) so that

aft end is installed.

the dots on the spring pins are opposite the grooves in the

rails.

e. Place the key washer on the aft mounting bracket. .

e. Apply MIL-S-22473, grade T (primer) and grade H,

Mesh and align the washer with the mating surface of the

sealing compound to quick-release plunger (12) and

aft support.

5-8