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so that, when it is closed, the switches inside are
in the proper position for flight. In addition, when the
landing gear handle is in UP, all switches are deactivated.
The panel serves a maintenance and preflight
purpose and is not intended for use by the flightcrew.
2.41.4 External Baggage Container (CNU-1 WA).
The external baggage container (Figure 2-136) is a
modified Aero ID 300-gallon fuel tank that incorporates
forward and alI baggage compartments. Each compartment
has an access door (forward, letI side; aft, right
side), a shelf, and a baggage tiedowo harness. The tiedown
harness consists of two sets of seatbelt straps that
form a crossover pattern to secme baggage to the shelf.
The external baggage container may be loaded with any
equipment that tits within the confines ofthe shelf, does
not exceed the shelf weight, and maintains the cg limits.
Locate baggage as near the center of the shelf as possible.
Care should be taken to ensure that straps are tight
to preclude any significant shift of cargo. Figure 2-135. Systems Test and System Power
Ground Panel
WEIOHT:
LENOTH:
DIAMETER:
CAPACITY:
S”SPENSION:
Figure 2-136. CNU-188/A External Baggage Container
2-269 (Reverse Blank) ORIGINAL

NAVAIR 01.Fl4AAD-1
CHAPTER 3
Servicing and Handling
3.1 SERVICING DATA
The following servicing data is for use by the
flightcrew and maintenance crews who are unfamiliar
with servicing the a&aft (Figure 3-1). When operating
in and out of military airfields, consult the current DOD
IFR Supplement for compatible servicing units, fuel,
etc. Figure 3-2 contains a tabulation of servicing data
and power units required to support the aircraft.
3.1.1 Ground Refueling. Single-point refueling is
provided for pressure tilling of all aircraft fuel tanks
through a standard refueling receptacle on the lower
right side of the forward fuselage. Ground refueling is
controlled by two procheck selector valves and the vent
pressure gauge adjacent to the refuel receptacle on the
ground refuel and defuel panel. Positioning of these
valves can be used for selective ground refueling of
either the fuselage or wing and drop tanks. The diit
reading vent pressure gauge indicates pressure in the
system vent lines. When aircraft fuel tanks are full, tireling
stops automatically. For hot refueling procedures,
refer to paragraph7 .6. For defueling procedures,r efer
toNAVAIROl-F14AAD-2-1.
The maximum refueling rate is approximately 500
gpm at a pressure of 50 psi. Nominal and minimum
pressure is approximately 15 psi; maximum pressure is
50 psi.
Figure 3-1. Aircraft Servicing Locations
3-1 ORIGINAL
NAVAIR WF14AAD4
DESlGNAllON
engine control) shall be
set for type fuel in use.
Chevron Flo-Cool
wipes. Afler l-minute
drying, wipe clean with
Figure3 -2. Aircraft ServicingD ata( Sheet1 of 2)
ORIGINAL 3-2
NAVAlR OI-FI4AAD-1
Acceptable USN
Units
Ground Support
Equipment
Requirements
PNEUMATIC/
GAS TURBINE
STARTING
POWER
ELECTRICAL AIR
POWER CONDITIONING
NC8A NR 5C (Electrical)
MD-3 NR 8 (diesel)
MD-3A MA-l
MD-3M MA-1A
MA-3MPSU AIM32C-5
A/M32A-60 AIM32C-6
A/M32A-60A
HYDRAULIC
ASHORE:
NCPP-105
RCPT- 105
AiM47A-4
AHT-63164
TTU-226/E
(AHT-73)
MJ-3
AFLOAT:
AlS47A- 1
200 Ib/min at 75i3 psi
(STD. DAY)
115*20Vac,
400 f 25 Hz,
60 kVA, 3 phase
rotation
70 Ib/min at 3 psi 50 gallmin maximum
and 60°F at 3,000 psi
PNEUMATIC PRESSURE
SYSTEM PRESSURE
Emergency Landing Gear 3,000 psi at
70°F
Combined Hydraulic 1,600 psi at
70°F
Flight Hydraulic 1,600 psi at
70°F
Canopy Normal (1,200 psi
Minimum)
Canopy Auxiliary (600 psi
Minimum)
Wheel brake accumulators (2)
3,000 psi at
70°F
3,000 psi at
70°F
1,900 psi at
70°F
Arresting Hook Dashpot
Main Gear Shock Struts (2)
Nose Gear Shock Strut
6OO*lOpsi
980 psi
1,300 psi
TYPE
Nose (2)
22X6.6-10
20 Ply
Main (2)
37X11.50-16
26 Ply
TIRES
Ashore
Afloat
Ashore
Afloat
PRESSURE
105 psi
350 psi
245 psi
350 psi
Dry nitrogen, specification BB-N-41 B.
Type 1, Grade A; is preferred for tire inflation
and charging pneumatic systems since it is
Inert, and therefore will not support
combustion.
　
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