CSP−HMI−2
MD Helicopters, Inc
.
MAINTENANCE MANUAL
Page 206
Revision 39
53−40−30
1.25 IN. (3.175 CM) CRACK
LENGTH PERMISSIBLE
6G53−102A
1.25 IN. (3.175 CM) CRACK
LENGTH PERMISSIBLE
Figure 202. Tailboom Flap Inspection
NOTE:
The flap may be raised slightly, using
finger pressure only, to aid in checking this
area.
(f). Inspect flaps for cracking and
1). A crack of any length, in line with
aft edge of flap, is permissible at
interface between flap and tail-
boom.
2). A crack of 1.25 inch (3.175 cm)
maximum length, in line with the
forward edge of flap, is permissible
at interface between flap and
tailboom.
NOTE:
If crack in forward edge of flap is longer
than 1.25 inch (3.175 cm), contact your local
MDHI Field Service Representative for dis-
position.
(g). Inspect horizontal stabilizer mount-
ing brackets (pay particular attention
to the forward inboard legs) and
attachment fittings for cracks, voids,
separation and delamination.
(h). Inspect stabilizers (Ref. Sec.
53−50−30).
(i). Inspect (tail−skid) for cracks, dents,
holes and delamination.
(j). Inspect rotating thruster cone for
freedom of operation, cracks, holes,
separation and delamination.
(k). Inspect tailboom grommets (2) places
for cracks and proper fit.
(2). Inspect tailboom interior as follows:
(a). Check stator vanes and stator
diffuser cone for cracks, delamina-
tions and separation.
1). Maximum allowable cracks found
emanating from stator vane inserts
should not exceed 0.10 inch (2.54
mm) span−wise.
