System Maintenance Manual

G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 4-1
190-00682-01 Revision F
4 Instructions for Continued Airworthiness
4.1 Airworthiness Limitations
The G1000 Integrated Flight Deck including the GFC 700 AFCS is airworthy when installed, configured,
and maintained in accordance with this section.
The G1000 and GFC 700 systems possess the following maintenance airworthiness limitations: The
intervals for the airworthiness limitations are shown in maximum number of hours between checks, as
required for certification. Table 4-1 aligns these requirements with the King Air Phase Inspection
Program. These limitations were derived from the certification data.
GFC 700 Limitations:
• Every 220 hours, perform a check to verify that flaps-in-motion discrete inputs function
correctly. Refer to Table 4-1.
• Every 420 hours, perform a GSM 85A slip clutch check (if GSM 85A is applicable) to
verify proper operation. Refer to Table 4-1.
• Every 3000 hours, perform a GSM 86 clutch check (if GSM 86 is applicable) to verify
proper operation. Refer to Table 4-1.
• Every 1000 hours, perform a servo current display check of the pitch, roll, and yaw servo.
Refer to Table 4-1.
• Every 220 hours, perform a trim annunciator check to verify proper operation. Refer to
Table 4-1.
G1000 Limitations:
• Every 220 hours, perform a G1000 redundant connections check. Refer to Table 4-1.
• Every 220 hours, perform a G1000 cooling system electrical check. Refer to Table 4-1.
• Every 220 hours, perform a nose avionics compartment fans operational check. Refer to
Table 4-1.
• Every 220 hours, perform an instrument panel fans operational check. Refer to Table
4-1.
• Every 820 hours, perform an engine data check. Refer to Table 4-1.
• Every 820 hours, perform a G1000 miscompare check. Refer to Table 4-1.
Other Limitations:
• Every 220 hours, check for proper function of the internal lighting of the standby attitude
indicator (Mid-Continent P/N 4200-10), standby altimeter (Thommen P/N
3A43.22.35F.28.1.FU) and standby airspeed indicator (Thommen P/N
5A58.22.26K.28.1) as well as the proper power availability to the standby attitude
indicator and standby altimeter vibrator by performing the Standby Instrument Electrical
Power Checks. Refer to Table 4-1.
• Every 200 hours or 6 Calendar Months (whichever occurs first), perform an Emergency
Battery Check of the L-3 PS-835(C or D Model) Emergency Battery. Refer to Table 4-1.