AFM Procedure / FSI Flow
FlightSafety teaches this as a flow through Step 12, with Gulfstream's blessing. I tend to avoid flows but this is the only one for this airplane and it appears to work. Alternatively, you could bookmark the appropriate page from your AFM.
- CBs . . . Check
- EMERGENCY POWER . . . ARM
Verify the following are powered:
- Emergency Lighting
- Standby Flight Displays (2)
- TSC 2 and TSC 3
It takes a few seconds for the displays to come up, so use that time to look back for evidence the emergency lighting is up, then forward to see two displays on the glareshield and two more near the throttle quadrant.
- OHPTS 1 and OHPTS 2
- DU1 and DU4
- TSC 1 thru TSC 5
- LANDING GEAR Lights – 3 Green
"Two, two, three, and five." (Looking from the overhead panel to the DU panel to the panel below that and then to all the TSCs.)
Following the selection of the flight controls EBHA and UPS battery switches to ON, the FCS will perform a System Power-On Self Test (SPOST), which requires approximately 45 seconds. If electrical power to the FCC channels is interrupted while the SPOST is in progress, FCS No Dispatch (caution) CAS message, FCC Fail (caution) CAS message, or FCC Fail (advisory) CAS messages may display and not extinguish. If this occurs it will be necessary to power down the airplane, wait at least one minute, then reapply power and perform procedures in the normal sequence.
If the EBHA voltage is between 22-24 Vdc or UPS voltage is between 22-23 Vdc, it will be necessary to turn off the associated battery and charge the associated battery for 15 minutes while operating on external ac power, APU generator, or engine generator prior to selecting EBHA or UPS battery switch ON. Refer to the Maintenance Manual If the EBHA / UPS battery voltage is less than 22 Vdc.
Photo: OHPTS Fire test, PAS, p. 4-78
Click photo for a larger image
EBHA BATT: 24 Vdc minimum
UPS BATT: 23 Vdc minimum
This should be the OHPTS that comes up on the left by default. As for these voltages, one is 23 and one is 24, which? The one with three letters is 23, the one with four letters is 24.
If the airplane has been exposed to a prolonged or overnight cold soak of temperatures lower than -20°C (-4°F), and the ambient temperature is -20°C (-4°F) or colder at the time of APU start, the batteries should be warmed by external means to raise battery temperature prior to attempting APU start. Use an external AC cart, if available, to charge and warm batteries prior to APU start.
While you are pressing and holding, you are looking for 1 overhead light, 2 master warning lights, 4 CAS, and 4 lights below. Some people count 13 items, counting each L-R CAS line as two items.
- FIRE TEST . . . PRESS and HOLD
- Verify the followng indications are present:
- Overhead APU "Fire" light illuminated
- Master warning light (2)
- APU FIRE (U) (warning) CAS message
- >APU FAIL (caution) CAS message
- L-R Engine Core Fire (warning) CAS message
- L-R Engine Fire (warning) CAS message
- Fire handle lights illuminated (2)
- Fuel control fire light illuminated (2)
- APU Ready Light: Verify On
With the APU Master on, the "Fire Test" button goes away.
Photo: Electrical control panel, PAS, p. 4-25
Click photo for a larger image
- RAT GEN . . . ON
- GEN (Left and Right) . . . Selected In
- APU GEN . . . ON
- BUS TIE (Left and Right) . . . AUTO
- EXT PWR . . . As required
(1) IRS As required
The generators (RAT, L GEn, APU GEN, R GEN) should all be in, the RAT is dark, the rest (RESET, EXT PWR, L BUS TIE, and R BUS TIE) should all be out. The IRS normal come on with APU power, so if you are using EXT PWR and want an IRS, it is up to you to turn it on.
- ENG (Left and Right) . . . Selected In
- APU . . . ON
- Isolation Valve . . . Closed (Out)
When operating in high ambient temperatures (greater than 35°C / 95°F), cabin temperature can be reduced by selecting ECS Mode to Manual and Cockpit / Cabin Temps to Minimum. To expedite cooling the aircraft, lower the window shades, close the MED, and close the external baggage door.
If you were using a flow, this would be a good time to move to the checklist.
Photo: Master Test, PAS, p. 5-12
Click photo for a larger image
You can find this test explained in the AOM, §01-01-120, Functional Checks. You are looking for four red, five amber, and one blue CAS messages. Note that your probably have one or two "Fwd-Aft Lav Smoke as shown on the PAS but not the AOM. In the simulator there are no Lav line(s) so you end up with 13 items again, counting each L-R item as two. You are also looking for all the annunciator lights that didn't come one with the Fire test as well as the passenger oxygen on light to illuminate.
The setup tab on the TSC is under "Disp Ctrl" and the "HUD/EVS" tab. You will need to press both the "Display" and "EVS" buttons to green. It is probably a good idea to enter a -3.00 degree FPA too.
You can find this test explained in the AOM, §01-01-70, Functional Checks. Here is the quick way to do this:
- Move pitch trim switch on side stick both forward and aft and verify trim moves correctly, while doing so press AP DISC button to confirm trim movement stops. Do this on both control sticks.
- Verify trim moves with both BACKUP trim switches, but not with single BACKUP trim switches.
- Move stick roll trim full left for 3 seconds until it times out and a tone is heard, repeat in opposite direction which leaves you with neutral roll trim.
- Hold yaw trim left and verify movement. Then right until it stops and Yaw Trim Centered CAS message appears.
For aircraft without an installed TOLD database, takeoff data should be calculated using the data in 05-05-10, Takeoff Speeds Planning Tables.
The FCS pitch trim indicator will default to a flaps 20 takeoff trim setting, however, 02-02-20, Takeoff Pitch Trim Settings for Flaps 10 Degrees trim settings shall be used for Flaps 10 takeoffs.
Fuel quantity should be checked on OHPTS/Fuel Tab, Primary Engine Display, and TSC/Systems/Ground Service vs expected fuel quantity. If discrepancies ±500 lbs exist between the displayed fuel quantities or if specified CMC fuel indications are displayed, refer to 3C-06-230, FQMS Degrade, L-R.
- Maintenance Messages / Active / ATA 28 . . . Select
- FQM CH CHAIN OVERCURRENT LIMIT . . . Verify not displayed
- FQSC PROBE FAILED . . . Verify not displayed
You should see this on TSC 1 but can get to it from the MAIN MENU and then selecting CABIN POWER, then the "All On" button.
There should be a shortcut from the Cabin Power page, select it and ensure there are no popped SSPCs.
THE SPEED BRAKE HANDLE MUST BE FULLY SEATED IN THE RETRACT DETENT TO PREVENT INADVERTENT EXTENSION.
WHEN SETTING THE PARKING BRAKE, THE HANDLE MUST BE FULLY LATCHED IN THE UP POSITION. FAILURE TO DO SO MAY RESULT IN UNINTENDED BRAKE RELEASE.
Before initiating the FCS Test, ensure the sidesticks are clear of obstructions and the horizontal stab is clear for full movement. Do not touch either sidestick, the FCS test button, or any trim switch during the test, as any input will interrupt the FCS Test. In addition, avoid applying abrupt force to the cockpit structure (i.e., adjusting the rudder pedals or cockpit seats) as this may also interrupt the FCS Test. The test is complete when the FCS Test In Progress (advisory) CAS message extinguishes.
Ensure both sticks are clear, select from the SYSTEM menu, then the TEST tab, the FCS TEST, and wait for it to complete.
Green Oxygen supply switch is designed to remain in the ON position.
- Supply Pressure Check . . . Perform
- MIC . . . BOOM
- BKUP VOLUME . . . OFF
- 121.5 EMER . . . OFF
Gulfstream GVII-G500 Airplane Flight Manual, Revision 3, July 16, 2019
Gulfstream GVII-G500 Aicraft Operating Manual, Revision 2, February 20, 2019
Gulfstream GVII-G500 Production Aircraft Systems, Revision 1, Oct 1, 2018