BHT-212-MM-1
5-00-00
Page 216 Rev. 14 26 JUN 2013
Export Classification C, ECCN EAR99
(4) Remove inboard and outboard drag brace bolts.
Check bolts for deformation and perform magnetic particle
inspection. If satisfactory, return to service.
(5) Visually inspect stabilizer bar outer tubes for
bending. (Allowable deflection is 0.150 inch (3.81mm) in each
tube.)
(6) Remove main rotor pillow blocks from main rotor
yoke and check for deformation of bushings and bushing holes
in pillow blocks and yoke.
(7) Perform close visual inspection of all other main
rotor components.
BHT-212-CR&O (8) If any discrepancies are noted as a result of
inspection in step (4) through step (7), remove and replace
main rotor hub and blade assembly, stabilizer bar assembly, and
mast assembly. Removed assemblies shall have an overhaul
evaluation performed. Make an entry in component records to
show reason for removal was compressor stall.
3. Airframe.
a. Check tailboom fin for evidence of damaged skin panels
and/or structure and rivets for looseness and/or sheared heads.
If inspection shows no indication of damage, return helicopter to
flight status. If positive evidence of damage is found, comply
with step b through step e.
b. Remove skin from tailboom fin adjacent to tail rotor
gearbox mounting. Inspect all support structures in this area
and repair as required. Install new skin.
c. Make close visual inspection of complete tailboom
structure for distortion, buckles, skin cracks, and sheared or
loose rivets, paying particular attention to tailboom attachment
points at FS 241.43 to 243.9 and adjacent fuselage to tailboom
structure and intermediate gearbox support structure.
d. Make close visual inspection of main pylon support and
engine mount attachment structure for distortion, buckles,
cracks, sheared, or loose rivets, etc.
5-54. AFTER ENGINE COMPRESSOR STALL OR SURGE (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
INITIAL
MECH OTHER
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