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158. True/False: Mechanical linkage will allow normal retraction of the nose gear even with the
launch bar extended.
159. After emergency extension of the air refueling probe, how is the probe retracted? (With loss of
2A system)
160. How many low fuel indications does the pilot receive? . . . . What are they?
161. Switching to RDR position on the HUD altitude switch will:
a. Cause radar altimeter information to be displayed at all times, until BARO is reselected.
b. Cause radar altimeter information to be displayed when at or below 5,000 feet AGL and valid.
c. Cause radar altimeter information to be displayed on the HUD while barometric altitude
continues to be displayed on the DDI.
d. Cause radar altimeter information to be displayed just below the boxed barometric altitude
display.
162. When data link information has been lost during an ACL mode 1 or 2 approach, the HUD
indication will be:
a. TILT cue
b. Break X
c. Flashing velocity vector
d. Both a and b
163. While using the A/A master mode the velocity vector on the HUD will be:
a. Caged
b. Uncaged
164. True/False: With an air-to-ground store or tank on a wing station, maximum roll rate is
automatically reduced about 33%.
A1-F18EA-NFM-000
X-30-18 ORIGINAL
PART XI
PERFORMANCE DATA
Refer to Supplemental Flight Manual A1-F18EA-NFM-200.
A1-F18EA-NFM-000
73 (Reverse Blank) ORIGINAL

APPENDIX A
SYSTEM ORGANIZATIONAL MAINTENANCE MANUALS.
System Organizational Maintenance Manuals (except for System Schematic and Classified Supplement
Manuals) are in the Interactive Electronic Technical Manuals (IETM).
The IETM also references System Schematic and Classified Supplement Manuals. The following list
contains the publication numbers and titles of the System Schematic and Classified Supplement
Manuals.
Classified Supplements
(DM)A1-F18EA
System Schematics
(DM)A1-F18EA System Title
-120-500 Seat, Canopy, Survival Equipment,
and Boarding Ladder
-130-500 Landing Gear and Related Systems
-240-500 Secondary Power System
-270-500 Power Plant and Related Systems
-410-500 Environmental Control Systems
-420-500 Electrical System
-440-500 Lighting System
-450-500 Hydraulic System
-460-500 Fuel System
-510-500 Instrument Systems
-570-500 Integrated Flight Controls
-580-500 Flight Incident Recorder and
Monitoring System
-600-500 Communication, TACAN, ADF,
Electronic Altimeter, and IFF Systems
A1-F18EA-NFM-000
A-1 ORIGINAL
Classified Supplements
(DM)A1-F18EA
System Schematics
(DM)A1-F18EA System Title
-630-110 -630-500 Data Link, Instrument Landing,
and Radar Beacon Systems
-710-500 Global Positioning System
-730-500 Inertial Navigation, Backup Altitude,
and Navigation Systems
-731-500 Digital Map Set
-740-500 Weapon Control System
-741-500 Mission Computer System
-742-150 -742-500 Radar System
-744-500 Forward Looking Infrared System
-745-500 Multipurpose Display Group
-746-500 Navigation Infrared Receiving
System
-750-500 Gun System
-760-500 Tactical Electronic Warfare Systems
-770-500 Video Recording and Reconnaissance
System
A1-F18EA-NFM-000
A-2 ORIGINAL
APPENDIX B
Aircraft Differences
(Aircraft 165533 thru 165679)
AIRCRAFT DIFFERENCES (Aircraft 165533 thru 165679)
The baseline aircraft for the NATOPS manual is aircraft 165779 and up. As a result, this chapter
documents the differences from the baseline aircraft for aircraft 165533 thru 165679.
The numbering scheme for this chapter differs from that used throughout the NATOPS manual.
The ²B² indicates the text is from this chapter, however the remaining numbers indicate the specific
paragraph in this manual affected by the difference.
B.2.4.3.6 Automatic Battery Cutoff (Aircraft 165533 thru 165544). Automatic battery cutoff occurs
after 1 minute.
B.2.4.3.7 Battery Gauge (Aircraft 165533 thru 165544). There is no cockpit indication of battery
voltage. Refer to figure 31-1.
B.2.4.3.8 BATT SW Caution and Caution Light (Aircraft 165533 thru 165544). The BATT SW
caution and caution light are set to alert the aircrew of an improperly placed BATT switch, or a battery
related malfunction. After a dual GEN failure, the BATT SW caution light must be referenced to
determine whether an EBB PMG or the battery is powering the essential bus. These cautions are set
in only four circumstances.
1. The BATT switch is ON on the ground in the absence of ac power (i.e., first engine start). The
battery is depleting and the switch should be placed to OFF unless APU start is about to be made.
　
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