Page 235 - (KU)01-75GAJ-1.5 - Change 1

INTRO

EP'S (KU)01-75GAJ-1.5 FIGURES

1.6.3 WINDSHIELD AND WINDOW FAILURE
ACAWS
Flight Station

FAILURE LIMITATION GROUND

‡ Inner pane cracked ‡ Limit cabin differential to 10 inHg or less.
TAKEOFF
‡ Outer pane cracked ‡ Limit cabin differential to 10 inHg or less.
‡ Do not exceed 187 KIAS below 10,000
‡ Both panes cracked feet. FIRE/SMK
NORM ‡ Avoid icing conditions.

PRES/OXY
NOT FOR FLIGHT
Cargo Compartment

FAILURE LIMITATION ENG/PROP

‡ Single pane cracked ‡ Limit cabin differential to 10 inHg or less.
FUEL

‡ Both panes cracked ‡ Reduce differential pressure to zero.
AAR
(End of Procedure)
SPEC 1.6.4 Windshield Anti-Icing System Failures ELEC

Turn off the NESA HEAT switches if any of the following conditions are
noticed: HYD

‡ 3DQHOV DUH H[FHVVLYHO\ KRW WR WKH WRXFK FLT CTRL
‡ (OHFWULFDO DUFLQJ LV REVHUYHG LQ DQ\ RI WKH SDQHOV
‡ $Q\ RI WKH SDQHOV FRQWDLQLQJ WKHUPLVWRUV DUH QRW KHDWLQJ
This might cause the other panels in the same system to overheat. GEAR

Operations with inoperative windshield anti-icing is permissible
provided: DOR/RMP
PERF ‡ 7KH DLUFUDIW LV QRW ÀRZQ LQ NQRZQ LFLQJ

‡ 7KH PD[LPXP VSHHG OLPLW EHORZ IHHW LV .,$6 JETTISON

Descent from high altitude into warm moist air with an inoperative NESA
windshield anti-icing system will cause possible fogging and icing of LANDING
the windshield. To minimize this, increase cabin air temperature and
open the pilot and copilot windshield defogging valves. Position the
FURVV ÀRZ YDOYH VZLWFK WR 0$1 FORVHG WR GLUHFW PD[LPXP DLU WR WKH DITCHING
ÀLJKW VWDWLRQ ,W LV UHFRPPHQGHG WKDW D JUDGXDO GHVFHQW EH PDGH WR
allow the windshield, which has been cold-soaked at altitude, to warm
with ambient cabin air. BAILOUT

OPER FAULT LG

Use, copying and/or disclosure is 1 -203
governed by the statement on the
title page of this document. BACK CHARTS