Fill the tank with new oil.

Range values should include an allowance for fuel to start, taxi, takeoff, climb and reserve. For start, taxi and takeoff, allow 5 minutes of fuel flow at takeoff power. Reserve shall be computed as 45 minutes at the cruise power to be used for the flight.

The effective wind components along the runway shall be taken as 50% of headwind components and 150% of tailwind components in all takeoff, landing, accelerate-stop, accelerate-go and other runway performance.

The procedure shall specify that intentionally rendering one engine inoperative for the purpose of demonstrating, or training in, the recognition of VMCA will be done by starting at or above VSSE, then gradually reducing the speed (at approximately one knot per second) until either VMCA or stall warning, whichever occurs first, is obtained.

The recommended fuel conservation procedures shall contain a caution, if applicable, that the power settings recommended by the manufacturer must be used during the break-in period of new and newly overhauled engines. The use of economy power settings during this period may be detrimental to the engine life.

All flow control devices within the system, such as check valves, fuel pumps, accumulators, and relays should be included and indicated. Solenoid valves shall be indicated as such and shall include a notation indicating whether the valve is spring-loaded to the open or closed position. Once a symbol or device is established for a valve or control, it shall be used for this type of unit throughout the manual. The symbols used should be shown and identified in a legend block on the schematic diagram.

The schematic diagrams should include generators, tanks, and reservoirs that are considered to be the starting points of the flow shown. The diagram shall be arranged so that the flow of the system can be traced with a minimum of effort. Cross-overs shall be avoided as much as possible.

Schematic diagrams shall be used when necessary to indicate "flow" and to illustrate the operation of air control, electrical, fluid-power, fuel and turbo systems in as straightforward a manner as possible.

In cases where an item has an exceptionally high degree of complexity requiring specialized techniques, test equipment, or expertise, it is not required that internal diagrams and construction details, or data in interconnect systems, maintenance, troubleshooting, inspection or repair, will be included in the basic airframe Maintenance Manual on major components such as avionics, specialty electronics, engines and propellers.

It is expected that the manufacturers of major components will provide maintenance, troubleshooting, inspection and repair data in the format of this specification. However, power sources, bus systems, relays, circuit breakers, switches and other items that are common to a particular make and model are to be shown and described as necessary in the basic airframe Maintenance Manual.

Troubleshooting information describing probable malfunctions, how to recognize those malfunctions, and the remedial action for those malfunctions shall be provided.