Text in force at 23-63: from 23-17, effective 1 Feb 1977.
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.] Notice of Invitation to Submit Proposals; Notice No. 74-5; Issued on 2/14/74. Notice of Compilation of Proposals; Notice No. 74-5A; Issued on 5/22/74. Notice of Availability of Agenda; Notice No. 74-5B; Issued on 10/3/74. Notice of Clarifying Revisions; Notice No. 74-33; Issued on 10/3/74. Notice of Conference; Notice No. 74-5C; Issued on 11/25/74. Notice of Availability of Conference Summary; Notice No. 74-5D; Issued on 2/4/75. Notice of Airworthiness Review Program No. 2; Notice No. 75-10; Issued on 2/27/75. Notice of Airworthiness Review Program No. 3; Notice No. 75-19; Issued on 5/13/75. Notice of Airworthiness Review Program No. 4; Notice No. 75-20; Issued on 5/13/75. Notice of Airworthiness Review Program No. 5; Notice No. 75-23; Issued on 5/19/75. Notice of Airworthiness Review Program No. 6; Notice No. 75-25; Issued on 5/29/75. Notice of Airworthiness Review Program No. 7; Notice No. 75-26; Issued on 6/9/75.
41 FR 55465 · Source