TM 1-1520-238-23
4-378.2
Change 8
4.119.
NO. 1 AND NO. 2 ENGINE PRIMARY EXHAUST NOZZLE REMOVAL/INSTALLATION – continued
NOTE
Step (1) only applies to primary exhaust nozzles without removable flange support assemblies.
Step (2) only applies to primary exhaust nozzles with removable flange support assemblies.
b. Check primary exhaust nozzle for holes in nozzle ducts.
(1) Holes may be patched by aircraft certified welder using 0.020 STL CRES SH 321 (AMS5510) or material
from unserviceable nozzle (TM 1-1500-204-23).
(2) Holes may be patched by aircraft certified welder using 0.020 NKL SH 625 (AMS5599) or material from
unserviceable nozzle (TM 1-1500-204-23).
(3) Patches not to exceed 20 SQUARE INCHES on any nozzle duct.
c. Check primary exhaust nozzle for cracks in nozzle ducts.
(1) No intersecting cracks allowed. Remove damaged material and inspect/repair hole in accordance with
step b.
(a) Nozzles containing cracks within allowable limits (less than 4.0 inches in length) shall be inspected
before and after flight to check for initiation of new cracks and to monitor growth of any existing cracks.
Growth of cracks will be monitored by measuring length of crack(s) before and after each flight and by
flight time.
(b) Aircraft logbook entries shall be made to document data on initiation of crack, crack growth and flight
time.
(c) Copies of DA Form 2408-13 of Aircraft Corrective Maintenance Record (ACRM) will be mailed to the
point of contact at U.S. Army Aviation and Missile Command, Directorate of Engineering.
(2) Cracks exceeding 4.0 INCHES in length may be repaired by aircraft certified welder (TM 1-1500-204-23).
Nozzle material is STL CRES SH 321 (AMS5510) or NKL SH 625 (AMS5599). All cracks in nozzles should
be repaired at next scheduled maintenance.
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