Class Iv Aircraft; Part 121/135 Operations - Garmin GI 275 Installation Manual

2.1.12 Class IV Aircraft

For installations in Class IV aircraft (refer to Section 1 for definition), this STC only approves installation
of the following: GI 275 ADAHRS (P/N 011-04489-30) configured as a full-time, dedicated standby, a
GMU 44B, a GTP 59, or a GI 275 Base (P/N 011-04489-00) configured as an MFD with the following
pages: Traffic, SXM or FIS-B Weather, Terrain, Map, Stormscope and Rad Alt. Additionally, only the
following GI 275 interfaces are approved in Class IV aircraft. GI 275 pins not listed below must remain
unconnected. Aircraft identified in Table D-1 as "Limited to MFD or Standby ADI" are restricted to these
pins only.
• Aircraft Power (connector P2751 – pins 2, 3)
• Aircraft Ground (connector P2751 – pins 41, 61)
• Configuration Module (connector P2751 – pins 1, 21, 40, 60)
• USB pigtail (P/N 325-00238-02) (connector P2751 – pins 39, 58, 59, 78) OR
GSB 15 (connector P2751 – pins 39, 58, 59)
• Lighting Bus (connector P2751 – pins 22, 42)
• GMU 44B (connector P2751 – pins 19, 20, 49, 69, [18 or 38])
• GTP 59 (connector P2752 – pins 21, 60, 62)
• GPS source wiring shown in Figure B-4 (connector P2751 only)
• ARINC 429 and RS-232 wiring shown in Figure B-5 (connector P2751 only)
• Backup GPS Antenna (BNC connector)
• HSDB Traffic (connector P2751 – pins 8, 9, 27, 28, 46, 47, 65, 66) OR
ARINC 429 Traffic Input or Radar Altimeter Input (connector P2751 – pins 14, 15, 33, 34, 52, 53,
72, 73)

2.1.13 Part 121/135 Operations

Aircraft requiring a third attitude instrument for operations under 14 CFR Part 121 or 135 must still
comply with the GI 275 standby instrument requirements. Consequently, one additional attitude indicator
is required for the co-pilot's position. Aircraft that require the third attitude source are described in
14 CFR §121.2, 14 CFR §135.2, and 14 CFR §121.305(j). The third attitude indication may be a traditional
gyro, GI 275, or G500/G600 TXi system.
Single-engine aircraft operated under 14 CFR Part 135 must have two independent electrical sources or a
standby battery or generator/alternator capable of supplying 150% of the electrical loads of all required
instruments and equipment necessary for safe emergency operations of the aircraft for 60 minutes in
accordance with 135.163(f).
For multi-engine aircraft operated under 14 CFR Part 135, the electrical load of all required instruments
and equipment necessary for emergency operations must not be greater than one-half of the total generated
power in accordance with 14 CFR 135.163(g). List of required instruments and equipment necessary for
safe emergency operations must be expanded to include the pilot's PFD, AHRS, ADC, and standby attitude
indicator (if installed) when evaluating aircraft electrical loads.
190-02246-10
Rev. 11
GI 275 Part 23 AML STC Installation Manual
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