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LEFT for a minimum of 3 minutes, the engine must continue to run. Set
the fuel tank selector to RIGHT for a minimum of 3 minutes, the engine
must continue to run.
S Do a positive Fuel Cut-off check.
Set the engine mixture control to LEAN/CUT OFF.
When the propeller stops rotating:
S Set the ignition switch to OFF.
S Set the ALT/BAT switch to OFF.
AIRCRAFT
DA 40 Series
AMM
Time Limits and
Maintenance Checks
Doc # 6.02.01
Rev. 5 05-20-00 Page 53
20 Sep 2007
B. Engine Ground Test Record - TAE Version
Do the engine test in accordance with Section 71-01, Paragraph 3. Take photocopies of Sub-
Paragraphs C to E of that Paragraph into the cockpit and enter results and comments.
WARNING: DO NOT STAND WITHIN THE DANGER AREA OF THE PROPELLER.
THE PROPELLER CAN CAUSE DEATH OR INJURY TO PERSONS.
WARNING: YOU MUST MAKE SURE THAT THE ENGINE IS SAFE BEFORE YOU
TURN THE PROPELLER. MAKE SURE THAT:
- THE ELECTRIC MASTER KEY SWITCH IS SET TO "OFF".
- THE ENGINE MASTER SWITCH IS SET TO "OFF".
- THE POWER LEVER IS SET TO "IDLE".
WARNING: DO NOT GET OIL ON YOU. OIL CAN CAUSE SKIN DISEASE.
WARNING: DO NOT GET FUEL ON YOU. FUEL CAN CAUSE SKIN DISEASE. DO
NOT ALLOW FIRE NEAR FUEL. FUEL BURNS AND CAN CAUSE
INJURY TO PEOPLE AND DAMAGE TO EQUIPMENT.
WARNING: WHEN YOU COMPLETE AN INSPECTION, MAKE SURE THAT YOU
REMOVE ALL LOOSE ITEMS/TOOLS FROM THAT AREA. LOOSE
ITEMS/TOOLS CAN PREVENT FULL MOVEMENT OF THE AIRPLANE
CONTROLS. THIS CAN CAUSE DEATH OR INJURY TO PERSONS.
CAUTION: YOU MUST ATTACH BLANKS/CAPS TO HOLES/PIPES WHEN YOU
REMOVE COMPONENTS. IF YOU DO NOT DO THIS, UNWANTED
DEBRIS CAN ENTER THE HOLES/PIPES. THIS CAN CAUSE
BLOCKAGE TO THE AIRPLANE SYSTEMS.
AIRCRAFT
Time Limits and
Maintenance Checks
DA 40 Series
AMM
Page 54
20 Sep 2007 05-20-00 Doc # 6.02.01
Rev. 5
% (1) Drain Holes Inspection Checklist
% Do a check of the drain holes. The drain holes must not be blocked by dirt or other residues.
% Make sure to remove all foreign objects and clean the drain holes to their full diameter,
% otherwise the drain capacity may not be sufficient under certain conditions like heavy rain etc.
%
% (a) Fuselage
%
% Drain hole location Initials
% (1) Flange top hat section, RH
% (2) Flange top hat section, LH
% (3) Lower fuselage shell in the wing nose area, outboard of top hat section, LH
% (4) Lower fuselage shell in the wing nose area, outboard of top hat section, RH
% (5) Lower fuselage shell, in front of front spar flange, center position
% (6) Lower fuselage shell, next to front spar, LH
% (7) Lower fuselage shell, next to front spar, RH
% (8) Lower fuselage shell, aft of front spar flange, center position
% (9) Lower fuselage shell, next to rear spar, LH
% (!0) Lower fuselage shell, next to rear spar, RH
% (11) Lower fuselage shell, aft of rear spar flange, center position
% (12) Lower fuselage shell, fuselage rib reinforcement section, LH
% (13) Lower fuselage shell, fuselage rib reinforcement section, RH
% (14) Lower fuselage shell, inner corner of fuel duct flange, LH
% (15) Lower fuselage shell, inner corner of fuel duct flange, RH
% (16) Footwell Cockpit to the clearance, LH
% (17) Footwell Cockpit to the clearance, RH
% (18) Lower fuselage shell, aft of baggage compartment frame base
% (19) Through roll over bar duct and baggage compartment frame
% (20) Through lower end of ring frame1
% (21) Lower fuselage shell, aft of ring frame 2
% (22) Lower fuselage shell, aft of ring frame3
% (23) Lower fuselage shell, aft of front web vertical tail
% (24) Lower fuselage shell, aft of rear web vertical tail
AIRCRAFT
DA 40 Series
AMM
Time Limits and
Maintenance Checks
% Drain hole location Initials
Doc # 6.02.01
Rev. 5 05-20-00 Page 55
20 Sep 2007
% (25) In rib of vertical tail, in front of front stem of the vertical tail
% (26) In rib of vertical tail, in front of aft stem of the vertical tail
% (27) Fuselage strake on lowest point, LH
% (28) Fuselage strake on lowest point, RH
% (29) Rudder pedestal for rudder
% (30) On lowest point of the fin
% (b) Canopy and door
% Drain hole location Initials
% (1) Lower canopy frame, in front of Bowden cable guide, RH
% (2) Lower canopy frame, in front of Bowden cable guide, LH
% (3) Lower canopy frame, aft of the canopy locking mechanism
% (4) Inner door shell, below the front locking bolt
% (c) Horizontal stabilizer
% Drain hole location Initials
% (1) Elevator end rib, next to the rear spar, next to lower shell, LH
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钻石40系列AMM 1(43)
