- replace the defective angle of attack sensor (Ref. AMM TASK 34-11-19-000-001)> and (Ref. AMM TASK 34-11-19-400-001).

 (b) If the values are corrects:

 - do the AIDS Programmable Report.
 C. AIDS Programmable Report
R NOTE : For AIDS access password, refer to the paragraph Users Access
____ R Levels (Ref. AMM 31-36-00 P.Block 001)
 (1) Description
 The basic principles of the proposed method are:

 (a) Creation of an absolute AOA Reference (AOAref), independent of the external airflow, to which the 3 AOA sensors can be compared.

 (b) Estimation of acceptable tolerances between the AOAref and the output values of the 3 AOA sensors (AOA1, AOA2, AOA3).

 (c) Identification and rejection of the AOA sensor(s) evidenced to be out of tolerances.

 The AOA ref is obtained by differentiating the Pitch angle (PITCH) and the Flight Path Angle (FPA):
 AOA ref = PITCH - FPA
 (Ref. Fig. 203/TASK 34-11-00-991-003)
 To carry out this monitoring, the 3 AOA sensors, the Pitch Angle and the Flight Path Angle will be recorded on an AIDS programmable report.
 NOTE : You must have the conditions below to start the recording:
____
 - slats/flaps retracted

 - autopilot engaged in ALT (Altitude) mode

 - autothrust engaged in SPD/MACH mode

 - 2 deg. LH < Roll Angle < 2 deg. RH

 - airspeed (CAS) above 200Kts

 NOTE : In case an operator wishes to monitor the AOA accuracy in
____ the flight enveloppe where the FACs compute the aircraft weight (FL<150 and CAS<250Kts), a level-off should be performed below the FL150 (ALT hold), with a stabilized airspeed between 200 and 250Kts (SPD/MACH mode).
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞34-11-00∞∞∞∞∞∞∞∞∞∞Page A206
 May 01/05 CES

 Aircraft in Climb Phase
 Figure 203/TASK 34-11-00-991-003

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞34-11-00∞∞∞∞∞∞∞∞∞∞Page A207
 May 01/05R CES

 The analysis of the End-of-Flight AIDS printed report will allow the maintenance crews to clearly determine whether a given AOA sensor is healthy or not. The AIDS report represents a 30 seconds dynamic recording of the programmed parameters: This equals 60 snapshots or 120 lines of data.
 (2) On the GSE:
 (a) for report 16, enter the parameters below:
 --------------------------------------------------------------------------| Computer Parameter Name EQ/SYS/LAB/SDI | |------------------------------------------------------------------------| | ADIRUA ALTITUDE (1013.25mb) 06. 1 .203.01 | | ADIRUA CORRECTED ANGLE OF ATTACK 06. 1 .241.01 | | ADIRUA CORRECTED ANGLE OF ATTACK 06. 2 .241.10 | | FWC CORRECTED ANGLE OF ATTACK 26. 1 .241.11 | | ADIRUA COMPUTED AIRSPEED 06. 1 .206.01 | | ADIRU1 PITCH ANGLE 04. 1 .324.01 | | ADIRU1 ROLL ANGLE 04. 1 .325.01 | | ADIRU1 FLIGHT PATH ANGLE 04. 1 .322.01 | | THS STAB 6C. 1 .315.01 | | FAC WEIGHT (Kgs) 0A. 1 .074.00 | | FAC WEIGHT (Kgs) 0A. 2 .074.00 | | FMGC GROSS WEIGHT (Kgs) 02. 1 .075.00 | --------------------------------------------------------------------------
(b) enter the parameters and TRIGGERS conditions below:
 --------------------------------------------------------------------------| Computer Parameter Name EQ/SUS/LAB/SDI CONDITIONS | |------------------------------------------------------------------------| | ADIRU1 ROLL ANGLE 04. 1 .325.01 -2 < R.A.< 2 | | FMGCG DISCRETE STATUS 1 FMGC 01. 1 .274.00 = 11 | | FMGCG DISCRETE WORD ATS MODES 01. 1 .270.00 = 1 | | ADIRU1 COMPUTED AIRSPEED 06. 1 .206.01 > 200 | | SFCC1 SLAT AND FLAP SYSTEM STATUS 1B. 1 .046.01 = 1 | --------------------------------------------------------------------------
(3) Report analysis
 (a) Relation between the Pitch Angle, the FPA (Flight Path Angle) and the AOA ref (Reference Angle of Attack). (Ref. Fig. 203/TASK 34-11-00-991-003) The following page depicts an instance of AIDS report, and provides instructions on how to analyse the recorded parameters.
 1 On the printout of report No16, select an area of 24 lines in
_ a row (12 snapshots) where the conditions below are met: . Total Altitude variation not above 20 feet versus initial value
 May 01/05R CES

 . Total Roll Angle variation not above 1 deg. versus initial
 value
 . No abrupt AOA change between 2 snapshots (0.2 deg. max.)
 2_ In stabilized flight conditions the relation is:
　
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