CSP−900RMM−2MD Helicopters, Inc.
Rotorcraft Maintenance Manual
Page 603
Revision 1
28-10-00
2. Supplemental Fuel Tank Leak
Check/Pressure Test
A. Supplemental Fuel Tank Leak
Check/Pressure Test Method 1 (Requires
Floor Panel Removal)
(Ref. Figure 601)
Consumable Materials
(Ref. CSP−SPM)
Item Nomenclature
C702 Lockwire
C809 Leak Detector, Liquid
Special Tools
(Ref. CSP−SPM)
Item Nomenclature
T2014−4 Manometer
T2014−6 Regulator, Air Pressure
(1). Defuel supplemental fuel tank (Ref.
Section 12-00-00).
(2). Remove baggage compartment floor
(Ref. Section 53-20-00).
Aviation Turbine Fuel
(3). Remove lockwire (2) and slide hose (1)
to expose end of vent tube (3).
NOTE: Cap must be capable of retaining 2.0
psig (13.8 kPa).
(4). Cap end of vent tube (3).
(5). Install baggage compartment floor with
a minimum of every other fastener (Ref.
Section 53-20-00).
(6). Remove aft left main fuel tank vent/rol
lover valve access panel AL230 (Ref.
Section 53-20-00).
(7). Disconnect fuel transfer hose (2) from
elbow fitting (1).
(8). Connect the air supply and U-tube
manometer (T2014-4) hose to the fuel
transfer hose (2).
(9). Use clean, regulated, low pressure,
filtered, compressed air source, an
accurate pressure gage and a shut-off
valve.
Ensure baggage floor is
installed with a minimum of ev
ery other screw.
(10). Ensure supplemental fuel filler cap is
tightly secured.
(11). If new fuel cell is installed, slowly apply
2.0 psig (13.8 kPa) using air pressure
regulator (T2014-6), 56 inches of
water as measured on the manometer
(T2014-4) to the hose and hold for 10
minutes as a precautionary measure.
This will allow air trapped between the
cell and the helicopter structure to
escape and also allow the cell to adjust
to the contour of the cell cavity. Release
the air pressure slowly and repeat if
necessary.
(12). Slowly apply 2.0 psig (13.8 kPa) of
regulated air pressure to obtain 56
inches of water to the fuel cell as
measured on the manometer
(T2014-4).
(13). After the air supply pressure is shut off,
verify that the air pressure inside does
not drop more than 0.125 psig (0.86
kPa) or 3.5 inches of water after 15
minutes as measured on the manome
ter (T2014-4).
Do not attempt to remove
access panels with air pres
sure applied. This could result in seri
ous injury and damage to fuselage
structure.
(14). If leakage exceeds the amount allow
able, apply liquid leak detector (C809)
to areas suspected of leaking.
(15). Test fuel drain plug.
(16). Slowly release air pressure from fuel
cell.
(17). Remove baggage area floor panels and
check all connections.
CAUTION
WARNING
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