Standard for Construction and Protection of Aircraft Engine Test Facilities

5.1 General Safeguards.
5.1.1* Where objects, such as supports, nuts, and bolts, are located such that they might be ingested into an aircraft turbine engine, one of the following criteria shall be met: (1) The objects shall be secured by safety wires, tack welding, adhesive, or approved aircraft-type locking devices. (2) An inlet screen of a design that protects an engine from foreign object damage shall be used.
5.1.2 All materials likely to become exposed to fuels, oils, or hydraulic fuids shall be resistant to deterioration from the fuels being used.
5.2 Drainage Systems.
5.2.1* Drainage systems shall be provided for engine test cells and support rooms containing fammable liquidor combustible liquid–handling systems to reduce fre and explosion hazards.
5.2.2 Floors subject to possible spillage of fammable or combustible liquids shall be pitched a minimum of 1 percent toward the drain(s), which shall be located to minimize fuel spread and exposure to equipment.
5.2.3 Curbs, ramps, or drain trenches shall be installed to prevent the fow of fammable or combustible liquids into adjacent rooms or buildings.
5.2.4* Drainage systems shall be designed and installed to provide a capacity that prevents a buildup of fammable or combustible liquids and water over the drain inlet under the maximum possible water discharge rate.
5.2.5* Drain traps shall have a trap seal water head. 5.2.5.1 In test cells, the seal water head shall be greater than the expected difference between the test cell operating pres‐ sure and atmospheric pressure.
5.2.6 Drain piping and joints shall be resistant to deterioration from fuels, engine oil, and aircraft hydraulic system fuids.
5.2.7 A common or separate oil separator(s) shall be provided in drains from the engine area, the exhaust plenum area, and support rooms.
5.2.7.1 Separator systems shall discharge fammable or combustible liquid products to an approved, safely located tank, cistern, sump, or pond that is away from or cut off from the engine test facility.
5.2.7.2 In aircraft engine test facilities protected by a fre protection system utilizing water, a bypass shall be provided around the separator to allow for emergency direct disposal of water and fammable liquids to an approved location.