How to calculate TAS and fuel for Diamond DA20-C1? The PoH for the Diamond DA20-C1 is here: http://support.diamond-air.at/fileadmin/uploads/Canada/Tech_Pubs_DA20-C1/AFM/DA202-C1-Rev-28.pdf.
The plane has an MT prop, and the supplement for it is here: https://static1.squarespace.com/static/59b981e8b07869d96fe0c365/t/5e457224a5db6b6a6ce00bc2/1581609513640/DA20+MT+Propeller+Supplement+%283%29.pdf.
I need to calculate fuel consumption and TAS under the following conditions:

8000' pressure altitude (PA)
2600 RPM
-1C OAT

There's two charts in the supplement that I think I need to solve this:


It seems I need to use the first graph to find the density altitude (DA) from the temperature and PA. So for -1C and 8000, the DA appears to be 8000 as well. Looking at the table, this would give me 7.1 GPH and 132 TAS. Is this correct? I'm confused by the &quot;standard temperature&quot; heading in the table.
Your steps are all correct, as is your answer.

I'm confused by the &quot;standard temperature&quot; heading in the table.

Consider this table from your first link:



The column I put in a green box, if it was the only one, then the altitudes would all be density altitudes -- just like the table in the question, with the label &quot;Standard Temperature.&quot;