Hi Diesel and Dust,
1) Given airfield elevation of 1500 ft, altimeter 1000 millibars, calculate pressure altitude:
The Altimeter indicates the Pressure Altitude when set to 1013
Since QNH = 1,000 mbs, you'd simply wind on another 13mbs on the sub scale.
The Altimeter would then indicate a Pressure Altitude of 1500 + (13*27ft = 351 ft), i.e. 1851 ft.
But why the 4/1000 ? is it something I am missing or what.
The temperature correction is proportional to the Absolute Temperature scale (measured in degrees Kelvin) where ISA at sea level = 288° K. (273+15)
If the temperature deviation is ISA -15 degs C, then apply a correction of 15/288 * Height of the column of air (7,500) = 390 ft.
So I get 10,000 - 390 = 9610 ft.
3) There are two runways, one is 8,000' and one is 10,000' long. With respect to second segment climb, which runway will allow for greater 2nd segment performance.
I'm not certain what the examiner is asking here, but assuming all Obstacles are measured from the far end of the runways, then starting 2,000 feet further back with the same aircraft performance will give you more clearance during the second segment climb.
4)On a 3° glide path, OAT -25°, OM crossing height of 1760', the aircraft altitude will indicate
The 3° glide slope will place you physically at the correct height at the OM. Assume airfield is at sea level.
Since surface temp = -25 (ISA-40), then apply 40/288 * 1760 correction = 244ft
Therefore the Altimeter would over read by 244 feet, and show 2004 ft at the OM.