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a. Check oil level by observing sight gage on the checked by observing the hydraulic reservoir sight
transmission. When checking oil level, ensure glass (54, fig. 2-1) through a window located on the left
helicopter is parked on a relatively level area with side of the forward cowling.
engine shut down.
a. Servicing. Check hydraulic fluid level by
NOTE observing sight gage. Proper fluid level is when
hydraulic fluid level is indicated by the sight glass being
When oil is visible in the yellow area of the completely filled with fluid.
sight gage, it is not required to service the
transmission; however, if oil is not visible in CAUTION
the yellow area, add oil to center level of the
sight gage.
b. Service with approved lubricating oil (table 2-1) DO NOT mix MIL-H-5606 and MIL-H-
and record on helicopter servicing records. 83282.
b. Service hydraulic reservoir as required with
2-97. TAIL ROTOR GEARBOX SERVICING. approved hydraulic fluid (table 2-1). Record on
helicopter servicing records.
The tail rotor gearbox may be serviced through the oil
filler port, located on top of the gearbox. Oil level may
be checked by observing the sight gage, located on the 2-99. GROUND HANDLING.
aft, bottom part of the gearbox.
Two tow rings are provided on the forward portion of
CAUTION each landing gear skid for attachment of a standard
helicopter tow bar. Helicopter is towed on ground
handling wheel assemblies mounted on the landing
DO NOT mix MIL-L-7808 and DOD-L- gear skids.
85734 oil except in an emergency. If oils
are mixed, oil shall be drained and
system serviced with approved oil within NOTE
5 hours of operation.
For installation requirements of access
a. Check oil level by observing sight gage on doors, panels, fairings, and covers for
gearbox with helicopter parked on level ground with towing, refer to TM 1-1520-248-23.
2-72
TM 1-1520-248-10
2 - 1 0 0 . P R O T E C T I V E C O V E R S A N D (1) Position blades at 45 degree angle to
TIEDOWNS. fuselage to secure tiedown lines to forward and aft
crosstubes. Blades may be rotated forward or rearward.
Protective covers and tiedowns are furnished as loose
equipment and are used for parking or mooring of (2) Install sock on main rotor blade as follows:
helicopter. Additional equipment such as ropes, cable,
clevises, ramp tiedowns, or dead-man tiedowns will be
required during mooring. NOTE
a. Protective Covers. Securing rings are preadjusted to give
forward and aft blades moderate tension
(1) Engine Inlet and Pitot Tube Cover. when secured to the helicopter tiedown
Engine inlet protective covers and a pitot tube points. Tie down forward blades with
protective cover are provided to prevent entrance of tiedown assemblies that have flags labeled
dust, etc., into engine inlet and pitot system when FWD BLADES, and a f t b l a d e s w i t h
helicopter is parked. assemblies that have flags labeled AFT
(2) Engine Exhaust Ejector Protective Cover. BLADES.
A single engine exhaust ejector protective cover is
provided for the exhaust ejector to prevent foreign (a) With sock secured to wand, install sock on
objects entering the exhaust ejector when the end of main rotor blade.
helicopter is parked. This cover slides into the end of
the exhaust ejector. (b) After sock is installed, extend tiedown line
to crosstube, pass snap hook around forward crosstube
b. Tiedowns. The main rotor tiedown kit for for forward blades and aft crosstubes for aft blades.
nonfolded blades consists of four sock assemblies and Secure snap hook to rings.
a wand. The nylon mesh sock assemblies include a
removal loop tiedown line. Each tiedown line includes (c) Install the remaining three socks in the
two tiedown rings and a snap hook. The wand is used same manner. All blades must be tied down when
to install sock assemblies on the main rotor blade tips. blades are being secured.
Install tiedowns as follows:
NOTE
CAUTION
The above procedure is for unfolded blades.
Procedures for main rotor blade folding and • To prevent damage to main rotor securing folded blades is described in
blades or hub assembly, use only Chapter 1 of TM 1-1520-248-23.
tiedown assemblies 406-070-300-101
and 406-070-301-101 and procedures
described in this chapter. 2-101. MOORING HELICOPTER.
• Maximum tiedown load applied
vertically at the blade tip shall not Mooring of helicopter shall be accomplished in
exceed 60 pounds. accordance with TM 1-1520-248-23.
SECTION XVI. HELICOPTER SECURITY SYSTEM
2-102. HELICOPTER SECURITY SYSTEM. b. Right Crew Door Locking Device. The right
crew door is locked from the outside with a hasp and
　
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