Refer to figure.
The dynamic pressure is the basic measure of airspeed in the aircraft. The Airspeed Indicators are calibrated to read corrrectly at Sea Level ISA conditions.

At a height the air density reduces and therefore the same dynamic pressure reflects a higher TAS. The same thing would happen, if the air was warmer than standard.

Conversely, at a lower height or in colder air than standard, the same dynamic presssure reflects a lower TAS.

This means that at height we have two airspeeds, the CAS based on dynamic pressure and the higher TAS than CAS through the air.

As an aircraft descends from one altitude to one other lower with constant CAS, but higher to Sea Level, the TAS will be in both cases higher than the CAS, but the difference between them increases as altitude increases and decreases as altitude decreases, until they become equal at Sea Level in ISA conditions.

For this question, the TAS will be always higher than CAS during the descent (thus, 119 kt is excluded), but a few minutes later, after FL080, the TAS will be lower than 135 kt, 131 kt.