曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

windshield defog.
If OAT is approaching or is above 103¡F -
1. Consider turning off non-essential avionics equipment before entering the landing pattern.
21.5 AFTER LANDING
During ground operations with fuel temperatures above 40°C, the LCS pump and ground cooling fan
are commanded on regardless of RADAR knob position to provide ram air cooling for the fuel system.
Placing the RADAR knob to OFF postflight removes the radar as a heat source, aids LCS/fuel cooling,
and should extend ground operating time.
Once clear of the runway -
1. Avionics equipment - OFF
2. RADAR knob - OFF
If line shutdown -
3. Canopy - LEAVE OPEN
If hotpits -
3. Monitor feed tank fuel temperatures.
NOTE
The ground L or R FUEL HOT caution thresholds are 79°C with less
than 5,000 lb fuel and 59°C with more than 5,000 lb fuel.
If feed tank fuel temperatures are approaching limits -
4. Consider shutting down the left engine (significantly reduces the heat load).
If a L or R FUEL HOT caution appears -
5. Perform the corrective action items.
A1-F18EA-NFM-000
VI-21-2 ORIGINAL
CHAPTER 22
Cold Weather Procedures
22.1 EXTERIOR INSPECTION
If the aircraft has not flown within 4 hr -
1. Pay particular attention to the nosewheel oleo, and APU and brake accumulator pressures.
22.2 BEFORE ENTERING COCKPIT
If a battery/APU start is anticipated -
1. Consider using external power to raise the canopy to conserve battery power.
22.3 INTERIOR CHECK
1. Canopy - Consider leaving open until the right engine has been started to (1) conserve battery
power and (2) permit rapid egress.
If the aircraft has been cold soaked below -18¡C (0¡F) -
1. Rudder pedal adjustment may be difficult or impossible and the inertia reel may not retract
automatically until the cockpit warms up (typically 5 to 10 minutes).
22.4 ENGINE START
1. Perform normal engine starts (windmilling is not required)
APU starts should be successful if the battery and the APU accumulator are fully charged. The
FADEC modulates fuel flow as required to prevent a hung start. Successful engine starts have been
demonstrated at ambient temperatures down to -40°F without start anomalies; however, expect engine
starts to be slower than at nominal temperatures.
2. Avoid activating any hydraulic actuated system for 2 minutes after both engines are online.
This allows hydraulic fluid to warm both systems and prevents hydraulic seal damage and potential
hydraulic leaks.
3. Oil pressure on the EFD may appear as invalid if 200 psi is exceeded. Maximum oil pressure 2½
minutes after engine start is 180 psi.
22.5 BEFORE TAXI
If ambient temperature between 0 and 7¡C -
1. Minimize engine operation above IDLE to reduce the potential for ice accumulation on the engine
inlet lips. Inlet lip icing can occur at these conditions without the INLET ICE caution.
A1-F18EA-NFM-000
VI-22-1 ORIGINAL
If visible moisture exists (rain, fog) and the temperature is 45¡F (7¡C) or less-
1. ENG ANTI ICE switch - ON (after engine start)
2. PITOT ANTI ICE switch - ON (after taxi but prior to takeoff)
If the aircraft has not flown within 4 hr with ambient temperature below -18¡C (0¡F) -
1. Up to three selections of the FCS exerciser mode may be required in order to obtain a successful
FCS RESET after the initial 2 minute warm-up.
For cold weather operations below -18¡C (0¡F) -
1. Three arresting hook cycles should be performed to bring extension time within specification (2
seconds is nominal).
2. Proper operation of the OBOGS monitor may not occur until 2 minutes of warm up.
22.6 TAKEOFF
If snow or slush has accumulated on the landing gear -
1. Leave the gear down for 1 minute after takeoff to clear snow or slush.
2. The landing gear may be slow to retract (up to 30 seconds) following cold soak below -18°C (0°F).
Gear retraction times in excess of 15 seconds annunciate the landing gear warning tone.
3. Carefully monitor gear uplock signals (all three landing gear position lights out, landing gear
warning light out).
A1-F18EA-NFM-000
VI-22-2 ORIGINAL
PART VII
COMM-NAV EQUIPMENT
AND PROCEDURES
Chapter 23 - Communications-Identification Equipment
Chapter 24 - Navigation Equipment
Chapter 25 - Backup/Degraded Operations
Chapter 26 - Visual Communications
Chapter 27 - Deck Ground Handling Signals
A1-F18EA-NFM-000
65 (Reverse Blank) ORIGINAL

CHAPTER 23
Communication-Identification
Equipment
23.1 ICS - INTERCOM SYSTEM
The ICS provides amplification and distribution of intercockpit voice communications, aircrew-toground
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：NATOPS Flight Manual 飛行手冊 2(72)