Contact|RisingUp Home

Federal Aviation Regulations

Sec. 23.1111 — Turbine engine bleed air system.

For turbine engine bleed air systems, the following apply:

(a) No hazard may result if duct rupture or failure occurs anywhere between the engine port and the airplane unit served by the bleed air.

(b) The effect on airplane and engine performance of using maximum bleed air must be established.

(c) Hazardous contamination of cabin air systems may not result from failures of the engine lubricating system.

[Amdt. 23–7, 34 FR 13095, Aug. 13, 1969, as amended by Amdt. 23–17, 41 FR 55465, Dec. 20, 1976]

NEXT: Sec. 23.1121 - General.
PREVIOUS: Sec. 23.1109 - Turbocharger bleed air system.

Search the FARS for