The test was completed using a level flight attitude. Both tanks were tested.
The average of the three tests was approximately 42.5 GPH. According to the fuel flow test guide, we needed to have a minimum flow based on the formula:
GPH =[ (.55 x HP) / 6] x 1.25
Using 290 HP, the minimum flow required was approximately 33.25 GPH; we were well above that.
Next, the aircraft was put in a 13.5 degree nose up attitude. The identical test was run on both wings tanks. The results were similar. All data is documented on the fuel flow test sheet.