STUDENT GUIDE T-39N/G NATOPS
UNIT TWO: FUEL SYSTEM
REFERENCE: T-39 NATOPS MANUAL
Locate and operate T-39 N/G aircraft systems, given a mission in a T-39 in accordance with
Recall the basic description, related systems, and operating limitations of the T-39 fuel
NATOPS TWO: FUEL SYSTEM
1. Military: JP-4. JP-5. JP-8
2. JET B+, JET A, JET A+ (PRIST not necessary)
B. Fuel tank capacities/limitations
1. Fuselage tank (161 gals, 1100#) plus two wing tanks (451 gals each, 6130# total).
2. Total usable fuel of 1063 gals, or 7200# based on JP-5 (6.8#/gal. - standard day).
6 9 0 0 # based on JP-4 (6.5#/gal. - standard day).
Max imbalance is 200# during T/O and LDG, 400# en route.
Zero fuel weight: T-39N 13,300# (crew & baggage) 11,700# (empty).
Max gross weight: T-39N 20,422#, T-39G 20,372#.
Max takeoff weight: T-39N 20,037#, T-39G 20,172#.
Max landing weight: T-39N 17,500#, T-39G 17,500#.
7. Second segment fuel consideration - minimum climb gradient of 2.4% (24ft /1000ft
of downrange travel) at V2 (safe single eng climb speed) to a minimum of 400 feet AGL or
obstacle clearance altitude, whichever is higher. (Gear up/flaps up/take-off thrust). Since
A/C weight, air temp, and field elevation are the factors for maintaining this minimum climb
gradient, fuel weight may have to be reduced to maintain second segment climb.