(s)
Push the captain's BELOW G/S indicator.
(t)
Make sure that the G/S warning goes off.
(u)
Decrease the glideslope deviation signal to less than 1.3 dots.
(v)
Increase the radio altitude to 1500 feet, then decrease to 500 feet.
(w)
Increase the glide slope deviation signal to 2.5-dot.
(x)
Make sure that the G/S warning comes on with a soft voice.
(y)
Push the captain's BELOW G/S indicator.
(z)
Make sure that the G/S warning goes off.
(aa) Very slowly decrease the radio altitude to 0 feet.
(ab) Make sure that the G/S warning stays off.
(ac) Increase the radio altitude to 1500 feet, and then decrease to
900 feet. (ad) Make sure the G/S warning comes on with a soft voice. (ae) Push the first officers BELOW G/S indicator. (af) Make sure that the warning goes off. (ag) Decrease the glideslope to less than 1.3 dots. (ah) Increase the glide slope deviation signal to 2.5-dot fly-up and
slowly reduce radio altitude to 200 feet.
(ai) Make sure that no warning occurs.
(aj) Slowly decrease the altitude to 0 feet.
(ak) Make sure that no warning occurs.
E. Put the Airplane Back To Its Usual Condition
S 865-047
(1)
Slowly relieve pitot static system and remove test adapters.
(2)
Return flap system to normal.
(3)
Reset radio altitude to normal and disconnect test simulator.
(4)
Remove electrical power if it is not necessary (AMM 24-22-00/201).
S 865-048
S 865-049
S 865-050
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH SUNDSTRAND MK II GPWC ú
34-42-00
ú ú 02 Page 509 ú Mar 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
GROUND PROXIMITY WARNING SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________________
1. General_______
A. The ground proximity warning system (GPWS) provides the pilots with aural and visual warning of potentially dangerous flight paths relative to the ground. The GPWS processes signals from digital analog adaptor No. 1, VHF NAV receiver No. 1, radio altimeter No. 1, digital air data computer No. 1, inertial reference unit No. 1, digitial stall warning computers 1 and 2, flight management computer, flap warning switches, landing gear logic shelf and the landing gear lever.
(1)
Excessive rate of descent (Mode 1).
(2)
Level flight or too shallow climb towards rising terrain (Mode 2).
(3)
Takeoff altitude loss (Mode 3).
(4)
Unsafe terrain clearance (Mode 4).
(5)
Excessive deviation below the glide slope (Mode 5).
(6)
Descent below decision height (DH) (Mode 6).
(7)
Windshear (Mode 7).
B. In support of the above warning modes, the GPW computer provides a number of additional features. These features are outlined below:
(1)
Envelope Modulation
(a) The envelope modulation feature consists of storing information about peculiarities of particular approaches and departures where modes 1, 2, 4, 5, and 6 are not entirely appropriate as they are generally implemented. This stored information is used to first of all, verify the airplane location and configuration, and then to alter the basic mode parameters as necessary to optimize GPWS performance.
(2)
Programmable Data Tables
(a) There are three types of data that have been incorporated into programmable non-volitile memory; envelope modulation parameters, mode 6 altitude call-out menus, and mode 7 windshear constants and thresholds. This data is accompanied by version/data information. These data tables are in addition to the power immune latches and flight history information that is also stored in this non-volitile memory. The main difference between these two types of information is that the data tables can not be written to except on the bench
(i.e. read only via a hardware strap).
(3)
BITE and Flight History
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