General; Indication; Testing - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

BLEED-AIR LEAK
DETECTION

GENERAL

The bleed-air system can operate at extremely
high temperatures and pressures. Therefore,
structural damage and fatigue could result in
catastrophic consequences if leakage occurs.
The insulation surrounding the bleed-air ducts
has regularly spaced holes and is clasped at
both ends. If a crack or other duct failure oc-
curs, the hot air escaping from the holes in the
duct insulation impinges on two parallel sens-
ing loops that are routed along the ducts.
There are two detection units, each monitor-
ing inputs from two detector loops. The left
and right segments of the bleed-air manifold
are the most critical, and parallel loops are in-
stalled in each segment. These loops are iden-
tified as LOOP A and LOOP B, and both must
be grounded to trigger a DUCT FAIL warning.
The system thus provides protection against
a false signal triggering a warning indication
(includes 14-stage single wire).

INDICATION

A red DUCT FAIL light (Annunciator Panel
section) is located on the center instrument
panel. This light will flash as a master warn-
ing to alert the crew to a bleed-air leak.
At the same time, a steady red DUCT FAIL
light in one of the engine bleed-air switchlights
(Figure 9-1) or a single red DUCT FAIL light
in the wing anti-ice system will illuminate to
indicate the affected area.
Additional indication of a bleed-air leak lo-
cation is provided by the BLEED-AIR LEAK
annunciator panel located behind the copilot
(Figure 9-11). Each magnetic indicator iden-
tifies a specific section of the duct to pinpoint
a leak. Normally, the indicators show black
and, when tripped, they will show black and
white triangles. An indicator RESET switch
is provided to reset any tripped indicator.
CL-600-2B16 PILOT TRAINING MANUAL

TESTING

A SYSTEM TEST button located on the
BLEED-AIR LEAK annunciator panel, when
pushed, will (1) simultaneously trip all indi-
cators, (2) illuminate the flashing DUCT FAIL
light, (3) illuminate the DUCT FAIL lights in
the engine bleed-air switchlights (4 lights), and
(4) illuminate the DUCT FAIL light on the
ANTI-ICE control panel.
Releasing the SYSTEM TEST button will ex-
tinguish all DUCT FAIL lights. The magnetic
indicators must be reset by pushing the IND
RESET button which is also located on the
BLEED-AIR LEAK annunciator panel.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
14 STAGE
RIGHT LEFT
FUS
RIGHT LEFT
WING
RIGHT LEFT
10 STAGE
RIGHT LEFT
IND RESET SYSTEM TEST
BLEED AIR LEAK
Figure 9-11. Bleed-Air Leak Annunciator
L t é e
L t d .
NORMAL
TRIPPED
CL 601-3A 9-11