Figure 3-1 Initial Running Rendezvous Picture Wing Covering Exhaust Stack

T-34C PRIMARY FORMATION FLIGHT TRAINING

CHAPTER THREE

amount to allow Wing a closing advantage during the climbout. Maintain 120 KIAS with this

reduced power setting. If a turn is required prior to the Wingman rejoining, then Lead will use

no more than 20 of bank. As Wing approaches the parade position on the starboard side, Lead

will smoothly set power as required (850 ft-lbs maximum) and continue the departure. Lead

should make all power adjustments at a slow constant rate.

The Wingman. Once safely airborne, adjust the angle of bank as necessary to establish the

aircraft inside Lead's turn, maintaining Lead slightly above the horizon throughout the

rendezvous. When Lead rolls out wings level, there will no longer be the closing advantage

provided by radius of turn so now the joinup will be a function of airspeed differential. Once

Lead is rolled out, maneuver to the starboard side of Lead and put him at the 11 o'clock position

with at least 20 feet of stepdown. The Lead's wing should initially cover the exhaust stack

(Figure 3-1).

Figure 3-1 Initial Running Rendezvous Picture Wing Covering Exhaust Stack

Use power to control the closure rate approaching lead. Closure can be difficult to judge with a

tail aspect, so reference your airspeed indicator to help determine your closure rate. As a rule of

thumb, use about 10 knots per T-34C length as a guide for airspeed closure. In other words, if

Lead is flying 120 KIAS, be no more than 140 knots at two T-34C lengths. Be no more than 130

knots at one T-34C length. Do not exceed 170 knots during the Running Rendezvous.

At approximately three plane lengths out or when you can read the "Navy/Marines" on Lead's

aircraft, utilize coordinated power and control inputs to first move to and then stabilize beneath

the starboard parade position with 20 feet of stepdown (Figures 3-2 and 3-3). In the 20 feet of

stepdown position, the "ventral point" will be over the opposite "cutout," with the "prop

arc" under the "midpoint" of the starboard wing, and the trailing edge of the starboard

exhaust stack tangent to the leading edge of the starboard wing. After stabilizing in this

SECTION PARADE 3-5