14 CFR 23.1111 - Turbine engine bleed air system.

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§ 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]

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United States Code

Title 14 published on 03-May-2017 03:58

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 23 after this date.

  • 2017-04-24; vol. 82 # 77 - Monday, April 24, 2017
    1. 82 FR 18841 - Special Conditions: Viking Air, Ltd., Models DHC-6-100/-200/-300; Avmax Aviation Services, Inc., Installation of Rechargeable Lithium Batteries
      GPO FDSys XML | Text
      DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration
      Final special conditions; request for comments.
      The effective date of these special conditions is April 24, 2017. We must receive your comments by June 8, 2017.
      14 CFR Part 23