The information is permanently updated. The bleed pressure, upstream of the precooler, is displayed normally in green. The index and the numerical value pulse red above 950°C. Active and Standby selection is based upon the health of the channels and each channel determines its own health status. The indication pulses below 3 quarts decreasing, or 5 quarts increasing. Organizations also consider this a critical document because it ensures smooth work flow and when employees leave their jobs and new employees take over it enables them to understand their jobs thoroughly through the manual.
When the pressure loss in the filter drops below 8. This sensor is also used for trim balance operations. Otherwise, a non-motoring test is performed. There are two types of Built-In-Test : Initialization test and Periodic test. The previous flight legs increment from 01 to 63.
The aircraft can be dispatched with these faults, but they should be cleared at an interval that is not greater than the time limitation specified in the Aircraft Maintenance Manual. You may also see Why Do You Need Sample Training Manual Templates? Most systems are type 1 and these can memorize failures which have occurred in the last 64 flights. The oil filter clog message appears in amber in case of excessive pressure loss 25. It can store up to 200 failures recorded over the last 63 flights. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. The time, in seconds, logged at these maximum values is also displayed. The test will complete automatically in less than one minute.
The healthiest is selected as the Active channel. A maximum of 3 faults per page are displayed with a maximum of 12 faults recorded. The normal indication pulses if : - the oil pressure exceeds 90 psi and will continue to pulse until the pressure drops below 85 psi. Propulsion system survey parameters are directly displayed on dedicated Engine Warning and System Displays. The maximum value that can be displayed is 10 units. In addition, the technical data therein and the direct product of those data, may not be diverted, transferred, re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U.
The fuel filter clog message appears in amber in case of excessive pressure loss 11. A training manual lets your new employees have an idea about their responsibility and the process in details. The indication pulses above 140°C increasing and continues to pulse until the temperature drops below 135°C. Therefore, None of the information may be disclosed to other than the recipient. When the pressure loss in the oil filter drops below 22 psid, the caution disappears. Specific tests are available to verify certain engine functions. However, there may be possible maintenance, or operational procedures that allow dispatch with the fault s and the maintenance manual refers to these particular cases.
The two last digits are dashed if the fuel used indication is inaccurate due to a loss of fuel flow information for more than 1 minute. In order to avoid two different types of unit indication being provided to the crew, the two values are transformed and displayed in cockpit units. During this test, hydraulic pressure must be available for supply to the thrust reverser system. This condition does not satisfy dispatch criteria and should be corrected prior to aircraft dispatch. Flight leg numbers are displayed in reverse chronological order with the most recent flight leg first and the faults within each leg are displayed in chronological order with the oldest fault first.
This zone contains the fault number, flight leg 0-63 and number of fault occurrences up to 4. The start valve position is green and displayed only during the start sequence. The purpose is to prompt the operator to return cockpit switches to safe positions. Troubleshooting data is displayed in reverse chronological order, i. If an indication is not available, the corresponding indication is replaced by 2 amber crosses. Limit exceedance of engine parameters. These conditions are system faults that have no immediate direct impact on the loss of thrust control and satisfy the engine and aircraft safety objectives during the time limitation.
It can store up to 40 warnings, which occurred during the last flight. When the reset option is selected by the operator, a confirmation screen is displayed. The oldest data is overwritten by incoming data. Troubleshooting data is not available for scheduled maintenance faults. This is the case on the ground, five minutes after the last engine shut down.
Only the last 3 detected failures are displayed. . The resolver is mechanically linked to the throttle levers in the cockpit. The needle pulses amber when the actual N1 is above the N1 Max. After the values have been calculated and processed in the control law logic, they pass through to the output stage for transmission to engine, or aircraft systems. The current flight leg or, last leg if on ground is identified by 00 on the menu mode display.
The operator must confirm the start of the test by pressing the appropriate line select key. If the number was wrongly entered incorrect number of digits, or a letter accidentally keyed , a different screen will be displayed informing the operator that a mistake was made and allowing the correct number to be re-entered. The non-motoring test will complete automatically in about two minutes. An Advisory may, or may not, lead to a failure. It is disclosed in confidence, and the technical data therein is exported under a U. The page is displayed until the operator does so and then, when the return key is pressed, the screen displays the main menu. This mode is available on ground only.