Document ID: chunk:federal_register_of_legislation:F2021C01280:reg:5:p24
Version: federal_register_of_legislation:F2021C01280
Segment Type: reg
Provision Reference: reg 5 (pt 24/26)
Character Range: 66489–69370

remain concealed during each of the tests mentioned in paragraphs (a) and (b), however, when the signal input level is reduced so as to cause the deviation indicator deflection to fall by 2 dots, the flag must be at least partly visible.
Note 1   A simulator may be used for the checking mentioned in paragraphs 21.2 (a) to (c).
Note 2   The sensitivities referred to in this subclause are related to a "standard" 5 dot-0-5 dot, 150 microamperes-0-150 microamperes indicator. Proportional deflections apply to other than "standard" indicators.

Intervals
       21.3The checks mentioned in this clause must be carried out each time a periodic inspection is carried out in accordance with paragraphs 2.4 and 2.5 in Part 2 of Schedule 5 of CAR.

Attachment 1 to Appendix 1
                                      Note   See subclauses 3.3, 4.2 and 4.6 in Appendix 1.

Testing procedures for:

 Pitot-static systems
 Pressure altimeter systems
 Air data computers
 Automatic pressure altitude encoders
 Other transponder devices

Clause 1 Pitot-static system test

       (1)Static pressure systems

        Performance of the test procedures set out below, with all static instruments connected, must ensure that any leakage present is within the tolerance specified for the procedure.
(a) Visually inspect the ports, plumbing, accessories and instruments connected to the static system. Repair or replace those parts which are defective, for example, broken "B" nuts, cracked flare sleeves, deteriorated flexible tubing and quick disconnects, bad valves etc. If purging is necessary, use compressed air or nitrogen to remove foreign matter which may have accumulated in the tubing. Ensure that all static instruments are disconnected before commencing to purge.
(b) Ensure that no alterations or deformations of the airframe surface are present that would affect static air sensing. This is of particular importance for RVSM aircraft.
(c) Check any static port heaters to assure proper operation.
(d) If an aircraft has more than 1 static system, test each system separately to assure its independence and that the leak rate for each system is within tolerance.
(e) Connect the test equipment directly to the static ports, if practicable. If not practicable, connect to a static system drain or tee connection and seal off the static ports. If the test equipment is connected to the static system at any point other than the static port, it must be made at a point where the connection may be readily inspected for system integrity after the system is returned to its normal configuration.
(f) Determine that any leakage is within the tolerances mentioned in paragraph (g) or (h) (as the case requires).
(g) For unpressurised airplanes — evacuate the static pressure system to a pressure differential of approximately 33 hPa or to a reading on the altimeter that is 1 000 feet above