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1. GND PWR switches 1, 2, 3, and 4 - B ON (hold 3 seconds)
2. INS known - CV/GND
3. INS - STD HDG (if available)
4. BATT switch - ON
5. APU switch - ON (READY light within 30 seconds)
6. R engine - START
7. L engine - START
8. FCS RESET button - PUSH (verify RSET advisory displayed)
9. OBOGS control switch and OXY FLOW knob -ON
10. External electrical power -DISCONNECT (if applicable)
11. SINS cable - DISCONNECT (if applicable)
12. INS knob - NAV, GYRO or IFA
13. T.O. checklist - COMPLETE
A1-F18EA-NFM-000
III-9-20 ORIGINAL
CHAPTER 10
Functional Checkflight Procedures
10.1 GENERAL
The intent of functional checks is to determine whether the airframe, power plant, accessories, and
equipment are functioning per predetermined standards. The unique electronic built-in test (BIT),
fault detection, and fault isolation capabilities of the F/A-18E/F allow functional checks that have
historically been performed inflight to be performed on the ground. In general, engine control and
flight control system faults are reliably detected, annunciated, and, in most cases, functionally
bypassed by the aircraft control systems.
In most cases, functional checks for the F/A-18E/F will be performed on the ground by maintenance
personnel based on the requirements set forth in the maintenance work package for the component
being removed, replaced, and/or installed and not by a pilot on a dedicated FCF. Required
maintenance ground checks take advantage of the aircraft's BIT and fault detection capability and
ensure the health of the component and the integrity of the installation.
10.1.1 Engine Functional Checks. Based on the engine component replaced, ground functional test
requirements for the engine may include any or all of the following: idle speed test (low power turn);
air, oil, fuel leak test (leak check); anti-ice test; MIL power test; MIN AB test; MAX power test (high
power turn); transient test; and/or shutdown test. For instance, a single engine removal/reinstallation,
a single engine replacement, or a dual engine removal/reinstallation requires a low power turn and a
leak check. A dual engine replacement requires a low power turn, leak check, and high power turn. A
FADEC replacement requires ALL functional checks. Additionally, a crossbleed start is required on all
engine reinstallations and replacements. Given the FADEC's fault detection capability, successfully
completing these functional checks ensures that the engine is properly installed and is functioning
normally. All engine functionality that would be checked inflight is checked during the required
ground checks. Dedicated FCFs are, therefore, not required following engine related maintenance
actions.
10.1.2 Flight Control System Functional Checks. Functional test requirements for the aircraft FCS
include electronic rigging, an FCS maintenance BIT, and a test group (TG) for the specific actuator or
surface which was reinstalled or replaced. The FCS maintenance BIT requires operator intervention
and is the most comprehensive test of the FCS. The FCS maintenance BIT also performs unique tests
to verify the proper installation of a system component. Successfully completing these functional
checks ensures that all surfaces and actuators are properly installed and the FCS is functioning
normally.
Generally, dedicated FCFs are not required following actuator/surface related maintenance actions.
An exception involves the replacement of a LEF hydraulic drive unit (HDU). It is possible for a weak
LEF HDU to pass ground checks yet fail to drive the LEF to the proper position when the surface is
subjected to air loads. A weak HDU may manifest itself by a LEF split, a FLAP SCHED caution,
and/or a possible roll off. Therefore, following the replacement of a LEF HDU, a series of inflight
functional checks are required to test the new component at flight conditions that safely detect weak
HDUs.
A1-F18EA-NFM-000
III-10-1 ORIGINAL
10.1.3 Landing Gear Functional Checks. Ground functional test requirements for the landing gear
system include the following: aircraft jack, LDG GEAR handle mechanical stop and DOWNLOCK
ORIDE button test, landing gear warning light and warning tone test, normal landing gear extension
and retraction, planing link failure test, and emergency landing gear extension (front and rear cockpits
in the F/A-18F). Successfully completing these functional checks ensures that the normal and
emergency landing gear systems are functioning normally. While a dedicated FCF is not required
following landing gear related maintenance, an airborne functional check of the emergency landing
gear system may nonetheless be desired. An airborne functional check, coded E, has been included to
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NATOPS Flight Manual 飞行手册 1(158)
