Piper Archer G1000 — Instrument Checkride Guide (Systems, Avionics, DPE Questions)

What IFR-relevant systems does the Piper Archer PA-28-181 have?

The Archer is a four-seat, low-wing, fixed-gear aircraft with a normally aspirated Lycoming O-360 engine. Its low-wing design produces several IFR-relevant system differences from the high-wing Cessna 172 that DPEs routinely probe as applied systems-knowledge questions, not number-recall exercises.

Fuel system — the most-tested Archer distinction. The Archer carries fuel in two independent wing tanks with a three-position selector: LEFT, RIGHT, and BOTH. Because the Archer is a low-wing aircraft, fuel cannot gravity-feed to the engine — the engine-driven fuel pump is the primary source, with an electric auxiliary boost pump used for start, takeoff, landing, and engine-driven pump failure. The DPE will ask you to explain this architecture in your preflight briefing. Misidentifying the pump as vacuum-driven, or failing to note when the boost pump must be ON, signals incomplete systems knowledge.

Electrical system. The Archer uses a standard 28-volt, single-alternator, single-battery electrical system. The avionics bus is controlled by a separate avionics master switch. Alternator failure during IFR flight begins draining the battery immediately; know your load-shedding priority order and approximate battery-only endurance for your specific aircraft from the POH.

No vacuum system in the G1000 configuration. The G1000-equipped Archer eliminates the vacuum pump entirely. Attitude and heading reference functions that vacuum-driven gyros perform in an analog-panel Archer are handled by the solid-state AHRS (see below). This changes the failure architecture significantly — the DPE expects you to articulate this difference explicitly when flying the G1000 variant.

What does the Garmin G1000 avionics suite include?

The G1000 is a fully integrated glass-panel avionics system. The Garmin G1000 Pilot's Guide for Piper PA-28 Series describes the hardware architecture in the aircraft-specific supplement. The key components and their IFR relevance are:

The dual GIA 63 units each contain an independent WAAS GPS receiver. Both support LPV minimums on RNAV (GPS) approaches when the WAAS signal is available and the navigation database is current, per AIM Section 1-1-17 . Each GIA also contains a VHF nav receiver for VOR and ILS/localizer/glideslope — giving the aircraft two fully independent nav chains from GPS through ILS.

How does the AHRS replace the vacuum system and what fails instead?

The GRS 77 AHRS uses microelectromechanical (MEMS) accelerometers and ring laser gyroscopes — solid-state sensors with no spinning mechanical parts. This architecture eliminates the single-point vacuum pump failure mode that grounded many IFR flights in analog-panel aircraft. Per the Instrument Flying Handbook (FAA-H-8083-15B) , understanding the power source and failure mode of every attitude and heading reference instrument is a core ACS requirement under

.

In the G1000 Archer, the AHRS runs on the aircraft's electrical bus. The practical implication: the failure mode that replaces "vacuum pump fails" is "electrical bus degrades or the GRS 77 itself fails." The DPE will ask how you would detect an AHRS degradation and what the G1000 annunciates.

• AHRS failure annunciation — the G1000 displays a red X through the attitude tape and heading display; the PFD will also show an AHRS alert message
• ADC failure — a failed GDC 74A causes red Xs through airspeed, altitude, and VSI tapes; pitot heat failure precedes this in icing conditions
• Magnetometer failure (GMU 44) — AHRS loses magnetic heading reference; heading tape may show dashes or an HDG FAULT flag
• Single GIA failure — one nav/comm/GPS chain becomes unavailable; the surviving GIA continues to support all approach types; the G1000 automatically reconfigures
• Unlike a vacuum gyro, AHRS does not drift — when it works, it is accurate; when it fails, the annunciation is immediate and unambiguous

What is reversionary mode and when do you use it?

Reversionary mode is the G1000's single-display fallback configuration, activated when one of the two GDU 1040 displays fails. In reversionary mode, the surviving display — either the PFD or MFD — shows a combined layout with the essential PFD data (attitude, airspeed, altitude, HSI) alongside a compressed engine and navigation display.

The DPE's reversionary-mode question is a systems-thinking check, not a procedure quiz. They want to hear that you understand the G1000 is a redundant system — one display failure does not leave you blind, and you know how to reconfigure.

What are the most common DPE oral questions for the Archer G1000?

DPEs testing applicants in the G1000 Archer consistently probe the following areas. These questions are drawn from the Instrument Rating ACS (FAA-S-ACS-8C) knowledge elements under Areas II (Preflight) and III (Air Traffic Control Clearances):

1. 1
   Walk me through your Archer's fuel system. Why do you use the boost pump on takeoff and landing? (Tests low-wing fuel architecture and pump sequencing — not just a checklist recitation)
2. 2
   Your vacuum-system gyros failed on your last flight in an analog Archer. What is the equivalent failure in this G1000 airplane, and what would you see on the PFD? (Tests AHRS vs. vacuum understanding)
3. 3
   The MFD goes black just after you enter the clouds. What do you do? (Tests reversionary mode knowledge and circuit-breaker discipline)
4. 4
   Your GPS navigation database expired yesterday. Can you fly the ILS approach at your destination? What about the RNAV (GPS) LPV approach? (Tests 14 CFR 91.205 and AIRAC currency rules)
5. 5
   This aircraft has two GIA 63 units, each with a GPS receiver. How does that redundancy change your RAIM planning compared to a single-GPS airplane? (Tests applied GPS architecture knowledge)
6. 6
   You receive a RAIM alert at the final approach fix. Walk me through your decision. (Tests AIM 1-1-17 and approach go/no-go decision-making)
7. 7
   When must both your VOR receivers be checked, and what are the acceptable methods? (Tests 14 CFR 91.171 — both GIA 63 units contain VOR receivers)
8. 8
   Your GFC 700 autopilot disconnects on final approach in IMC. Is this an emergency? What do you do? (Tests autopilot dependency awareness and hand-flying discipline)
9. 9
   What does the GMU 44 magnetometer do, and where is it located on the Archer? Why does its location matter? (Tests G1000 architecture depth — wingtip location avoids cockpit magnetic interference)

How do you set up an ILS or RNAV approach in the G1000?

The G1000 FMS approach workflow is a high-frequency checkride task. The DPE will expect you to brief and load an approach without fumbling. This is the conceptual workflow — always refer to your aircraft's Garmin G1000 Pilot's Guide for the authoritative procedure:

1. 1
   Press PROC on the MFD or PFD bezel to open the Procedures page
2. 2
   Select 'Select Approach' — the G1000 presents available approaches for the active destination
3. 3
   Choose the approach type (ILS, RNAV, VOR), runway, and transition (vectors-to-final or a fix-based transition)
4. 4
   Review the loaded approach on the Active Flight Plan page — verify the correct IAF, intermediate fixes, FAF, MAP, and missed approach procedure
5. 5
   Activate the approach or select 'Activate Vectors-to-Final' if ATC is providing radar vectors
6. 6
   Verify the correct nav source is selected on the PFD HSI — GPS for RNAV, VLOC for ILS/VOR; the G1000 may auto-sequence to VLOC when the localizer is captured
7. 7
   Cross-check the approach briefing: minimums, inbound course, FAF altitude, missed approach instructions — the DPE is watching whether you brief or just punch buttons

The GPS-to-VLOC auto-sequencing behavior is a known DPE probe point. When flying a coupled ILS approach, the G1000 automatically switches the nav source from GPS to VLOC when the localizer signal is captured. Verify this transition occurs — if you stay in GPS mode, you are not flying the ILS.

How do you verify database currency on the G1000?

Under 14 CFR 91.205 and the aircraft's flight manual supplement, the navigation database must be current for IFR approach operations. An expired database may not be used for GPS approaches regardless of whether the procedure appears unchanged.

• Database expiry is displayed on the G1000 startup splash screen and on the AUX — System Status page
• AIRAC cycles update every 28 days; the G1000 accepts a standard Jeppesen database card loaded via the SD slot on each GDU
• Both GIA 63 units share the same database card loaded into the MFD SD slot — verify the version on both units via the AUX page
• If the database is expired: you may continue enroute and terminal navigation only after verifying each procedure is unchanged against current chart publications; you may not fly GPS approaches
• A current database does not guarantee RAIM — confirm RAIM availability at your estimated time of arrival at the destination IAF before departure
• VOR receiver currency under 14 CFR 91.171 is separate from database currency — both apply simultaneously

The DPE will ask you to show them the database expiry date before departure. Know where to find it and be prepared to explain the legal consequence of an expired database for approach vs. enroute operations. This is a direct test of ACS knowledge element IR.II.A regarding navigation equipment currency.