曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

upper and lower. Clockwise rotation increases headset volume for the controlled sub-system from the
LO to the HI position. The six knobs control the indicated sub-system and are labeled as follows:
1. TACAN morse code identification (TCN knob (upper)).
2. Intercockpit and aircrew/ground crew voice (ICS knob (lower)).
3. ALR-67 tones (RWR knob (upper)).
4. ECM equipment (when installed) (ECM knob (lower)).
5. AIM-9 seeker audio (WPN knob (upper)).
6. Unused (AUX knob (lower)).
The ground crew headset plug in jack and ICS volume control knob are located in door 8R on the
right side of the forward fuselage.
B.23.6 DCS - DIGITAL COMMUNICATION SYSTEM
Aircraft 165533 thru 165544 do not incorporate DCS.
Foldouts. Refer to figures B-1 and B-2 for specific cockpit component locations.
A1-F18EA-NFM-000
B-4 ORIGINAL
NOTE
FCS status display is shown for pitch
rate gyro channels 1 and 2 failure
example.
EFFECTS:
No change in flying qualities.
Autopilot inoperative.
EFFECTS:
Autopilot inoperative
ATC inoperative
Sensitive dynamic pitch characteristics.
Aggressive pitch inputs may result in PIO.
Figure B.15-37. FCS Failure Indications and
Effects
Figure B.15-38. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
B-5 ORIGINAL
EFFECTS:
Degraded roll CAS.
Reduced roll damping.
Autopilot inoperative.
Flaps - HALF or FULL:
Sluggish roll response.
Lateral PIO tendency.
EFFECTS:
Autopilot inoperative.
ASRM inoperative.
Flaps - AUTO:
Poor dutch roll damping.
Large sideslip with lateral stick.
Flaps - HALF or FULL:
Poor dutch roll damping.
Large sideslip with full rudder pedal.
Lateral PIO tendency.
Directional PIO may occur during aggressive
ground tracking.
Figure B.15-39. FCS Failure Indications and
Effects
Figure B.15-40. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
B-6 ORIGINAL
EFFECTS:
Degraded yaw CAS.
Autopilot inoperative.
Flaps - HALF or FULL:
Large sideslips with full rudder pedal.
EFFECTS:
Autopilot inoperative.
ATC inoperative.
Spin recovery arrow not provided, but ASRM
still available.
Flaps - AUTO:
Degraded pitch CAS.
Flaps - HALF or FULL:
No change in flying qualities.
Figure B.15-43. FCS Failure Indications and
Effects
Figure B.15-44. FCS Failure Indications and
Effects
A1-F18EA-NFM-000
B-7 ORIGINAL
Figure B-1. Cockpit F/A-18E/F (Sheet 1 of 2)
A1-F18EA-NFM-000
B-8 ORIGINAL
Figure B-1. Cockpit F/A-18E/F (Sheet 2 of 2)
A1-F18EA-NFM-000
B-9 ORIGINAL
Figure B-2. Rear Cockpit F/A-18E/F
A1-F18EA-NFM-000
B-10 ORIGINAL
ALPHABETICAL INDEX
Page
No.
A
ABORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . V-14-2
ACL MODE 1 AND 1A APPROACHES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . III-8-14
ACL MODE 2 APPROACH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . III-8-17
ADF (AUTOMATIC DIRECTION FINDER). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VII-24-46
AFCS - AUTOMATIC FLIGHT CONTROL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I-2-80
AFCS Mode Deselection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .I-2-80
AFCS Mode Selection.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .I-2-80
AFCS Related Caution and Advisories. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I-2-83
Basic Autopilot. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .I-2-80
Coupled Data Link Modes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .I-2-83
CPL - Coupled Steering Modes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I-2-83
Pitch-Axis Pilot Relief Modes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I-2-82
BALT - Barometric Altitude Hold. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . I-2-82
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：NATOPS Flight Manual 飛行手冊 2(131)