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a. Engine bleed air
b. Motive flow fuel
68. The fuel thermistors in the outboard section of the wing tanks perform what function?
69. The foe1 thermistors in fuel cell Nos. 2 and 5 perform these functions when either is uncovered~
a. d.
b. e.
39-9 ORIGINAL
NAVAIR 01-MUAD-1
70. All fuel enteringth e ventt anki s ventedo verboartdh roughth e ventm asti n the tailhooka ttachmenfat king.
a. True
b. False
71. Fuelt ransferf rom the externadl ropt anksi s accomplishebdy
72. ExternaAl betlr ansferc anb e checkeodn the deckb y OI
73. Fueld umpi sp rohibitedw ith speedbmkeosp ena nd/ora flerbumeor peration.
a. ‘he
b. False
74. Whent he fueld umpc ircuiti s activatedw, ing ande xternadl ropt ankt ransferi s automaticalliyn itiated.
a. True
b. False
75. Is it possibleto refuel in flight anda ccomplistho tal fuel transferw ithout electricapl ower or a combined
hydraulics ystem?If not, why?
76. On engines tartw ith the generatosrw itchi n normal,t he generatoisr automaticalleyx citeda ndt he generator
controlu nit bringsi t on the linew hene nginerp m is approximately percent.
77. stageb leeda ir is usedf or lDG oil groundc coling.
78. If thet hermacl utoutd ecoupletsh ed rivec lutcht o eitherm aing eneratoirn flight, theI DG mayb e recoupled
(reset)a maximumo f threet imes.
a. True
b. False
79. Failureo f eithera cg eneratoaru tomaticalclyo nnecttsh el eg andr ightm aina cb usesto theo perativgee nerator.
Thec ockpiti ndicatowr ill be a cautionli ght.
80. Thee mergencgye neratoirs poweredb y
81 . If thee mergencgye neratosrw itchi s in NORM, it will comeo nt hel inea utomaticallwy hen
82. Wheno peratingo n thee mergencgye neratotrh, ec ockpitli ghtinga vailableco nsistso f and
83. A singlee nginedrivenp umpo n the left powerst he combinehdy draulics ystema nda singlee ngine-driven
pumpo n ther ight powersth e flight hydraulics ystem
a. True
b. False
ORIGINAL 39-10
84.
85.
86.
If the pilot extinguishes the MASTER CAUTION light after a failure of one main hydraulic system, fsil~re
of the other system (will or will not) illuminate the MASTER CALJTION light. Why?
List the requirements for operation of DLC.
With the left engine shut down in flight and 0 percent windmill rpm, the combmed hydraulic system can be
powered by
88. With total loss of fluid fmrn either main hydraulic system, the hydraulic transfer pump will
89. The cockpit handpump will charge the brake accumulator in Sight if
90. Loss of all hydraulic fluid f?orn the flight hydraulic system will mean loss of power to the right inlet ramps.
a. Txue
b. False
91. With loss of the combined hydraulic system (combined system pressure zero), the main flaps are powered by
and the auxiliary flaps am
92. With the landing gear emergency blown down the nosewheel steering and normal brakes will operate after
touchdown.
a. True
b. False
93. The outboard spoiler module uses combined system fluid.
a. ‘he
b. False
94. Outboard spoilers are inoperative with wing-sweep angles atI of
95. The outboard spoiler module thermal cutout is inhibited when
96. The ON-OFF flag in the spoiler window of the hydraulic indicator indicates:
a. The outboard spoiler module is energized.
b. The outboard spoiler system is pressmined.
97. With loss of the combined hydraulic system (combined system pressure zero) the inboard spoilers wilh
98.
99.
The backup flight control module powers the and the
With the backup Sight control module switch in AUTO, the module is automatically energized when
NAVAIR Ql-l=l4AAD-1
100. The backup flight control module switch has three positions: AUTO, and
39-11 ORIGINAL
NAVAIR Ql-Fl4AAD-l
101. The backup Sight control module operates in the high-speed mode when
102. Operational status of the backup flight control module is indicated in the cockpit by
103. DLC requims an operable outboard spoiler module.
a. True
b. False
104. Failure of either the combined or flight hydraulic system will have what effect on wing sweep?
105. On the wing-sweep indicator, there are three position indicators. These show >
and wing-sweep position.
106. The aircraft is being operated with the wings afl of the forward limit. The wing-sweep control mode indicator
reads MAN. If speed is now increased beyond where the wing-sweep angle and forward lit coincide, the
control mode indicator will mad andthewingswill
107. The most forward wing-sweep angle allowed in bomb mode is
108. The emergency wing-sweep mode is a manual method of positioning the wings. This method incorporates
locks every from ZOOto 68Ot o prevent random wing movement in this mode.
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F-14D 飞行手册 Flight Manual 3(91)
