TM 1-1520-238-23
5-232
Change 8
5.51.
TAIL ROTOR ASSEMBLY INSPECTION
5.51.5. Tail Rotor Blade Inspection
a. Perform the following inspection for the tail rotor blade transition area.
NOTE
This is a chordwise inspection of the doubler and spar edges located in the transition area of the tail
rotor blade. The transition area of the blade root fitting begins 1.5 inches from the centerline of the
blade retention bolt and ends 2.5 inches from the centerline of blade retention bolt.
(1) Remove any reflective tape used in tail rotor balancing from the transition area prior to performing
inspection.
(2) Solvent wipe both front and back sides of the transition area with isopropyl alcohol (item 25A, App F) or
acetone (item 1A, App F) and allow to dry for 15 minutes.
NOTE
Re-appearance of alcohol/acetone after the surface appears dry during the 15 minute drying period is
a strong indication that a debond may be present.
(3) Visually inspect the doublers and spars in the transition area, both front and back sides, for “crazing”
(appearance of paint cracks) utilizing a 10X magnifier and flashlight or other light source.
(4) If no crazing or cracks are found, inspection is complete.
(5) If a crack is found at any time during the inspection procedures, proceed to paragraph b.1.
(6) If crazing is found, perform the following additional inspection procedures –
NOTE
Blade may be removed from aircraft to facilitate inspection and repair procedures.
CAUTION
Do not used power sanders, chemical strippers or paint scrapers to remove topcoat, primer or filler
material. The only approved method is by hand sanding using the following procedures.
WARNING
No sanding of the root fitting is authorized. Sanding of the root fitting may cause damage,
which would lead to blade rejection.
(a) Install masking tape (item 205, App F) (or equivalent) in a chordwise direction along inboard edge of
filler to ensure sufficient coverage to prevent sanding of the root fitting.
