CFR > Title 14 - Aeronautics and Space > CHAPTER I—FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION > SUBCHAPTER C—AIRCRAFT (parts 21 to 50) > PART 23—AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES > SUBPART E—Powerplant (§23.901 to §23.1203) > 23.1111—Turbine engine bleed air system.

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.

Code of Federal Regulations

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