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ABAA
Validity : S / N 1 - 9999 05-50 04Page 601
(CA) JUN 01
 
- the propeller :
signs of strike (black fusion or micro-fusion pits of various dimensions) are normally located at blade tips, if such signs are detected, remove the propeller and :
. test blade hardness in the damaged area,
. inspect blade roots for signs of electric arcing and, if such signs are detected, carry out the same inspection as above,
• discard blades with incorrect hardness,
. always replace the blade root thrust bearings,
. inspect all sections of the propeller hub for defects,
. always demagnetize magnetizable components of the propeller,
inspect the propeller shaft for signs of electric arcing, if such signs are detected, remove the engine for inspection in a specialized workshop (internal effects, damage to heat treatments),
- the antennas and their supports,
2) Carry out a complete operational test of :
- the communication / radionavigation systems,
- all electrical equipment and ancillary electrical systems (internal lighting, external lighting, warning lights, pumps and switches).
3) Check the compensation curve of the :
- magnetic compass,
- the flux valve (if installed).
ABAA
Validity : S / N 1 - 9999 05-50-04Page 602
(CA) JUN 01
 
SPECIAL INSPECTIONS DUE TO FATIGUE
INSPECTION / CHECK
1. GENERAL
Repercussion of TB10 fatigue tests on TB20 aircraft.
Apply to in service fleet, information acquired during fatigue tests.
These tests have led to an increased wing service life. They have also shown the necessity of specific inspections on certain components and the obligation to change certain vital parts after a number of hours of utilization which varies according to the component.
2. DESCRIPTION
A. Wing service life
Wing service life unchanged : 10000 hrs.
B. Wing / fuselage passage duct
1) Validity
All
2) Applicability
Detailed visual inspection every 2000 hrs.
3) Description
Perform detailed visual inspection of wing / fuselage passage duct ends - see figure 601, Detail A. If a crack less than 1.18 in (30 mm) is found, drill crack stop hole and continue inspection cycle.
If a crack larger than 1.18 in (30 mm) is found, contact manufacturer for further instructions before continuing flights.
 
 
Zone de crique
Crack area
ADM
Validity : S / N 1 - 9999 Special inspections due to fatigue
Figure 601
05 Page 602
50-05 (EA) JUN 01
 
CHECK OF CAMBER AND PARALLELISM
INSPECTION / CHECK
1. GENERAL
Camber and parallelism should be checked after a forced landing in a field or a hard landing on runway.
2. CHECK OF CAMBER AND PARALLELISM
　
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