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 42) Visually inspect the fuel selector - refer to 28-20-02 201.   
28-20 43) Clean or replace the filtering element of the fuel selector, check the support - refer to 28-20-02 201. 200 300 hrs or
1 year 
28-20 S / N 1 - 9999 200  
 44) Perform an operational test of the fuel tank selector cock   
 - refer to 28-20-04 201.   
30-10 45) Remove cover plate 244L and inspection door 216C, slightly lift and hold the de-icing system tank (if installed). 200 5 years 
 Inspect the inner face of the fuselage skin under the tank for corrosion.   
 Install tank, cover plate and inspection door - refer to 30-09-90 301.   
30-10 46) Check the de-icing system (if installed) - refer
to 30-09-90 301. 200 NOTE 1 
32-30 47) Visually inspect the landing gear hydraulic generator and check for leaks. Check fluid level - refer to 12-13-03 301. 200 NOTE 1 
32-30 48) Check the brushes of the PRESTOLITE hydraulic generator for condition. 200 1000 hrs 

NOTE 1 : If a 100-hr. inspection has been carried out during the last 3 months, do not perform this operation unless this annual inspection replaces a 100-hr. inspection. For US registered aircraft, perform all operations.
ADM
Validity : S / N 1 - 9999 05-20 Page 207
06 (EA) JUN 01
 

ATA ANNUAL INSPECTION (AI)
COCKPIT AND FUSELAGE INSPECTION (AREA 200) AREA OTHER
INSPECTION PERFORMED
BY
32-30 49) Perform an overhaul and a bench test of the 200 2000 hrs 
 PRESTOLITE hydraulic generator.   
32-30 50) Replace the LHC hydraulic generator seals. 200 5 years 
32-30 51) Perform an overhaul of the LHC hydraulic generator. 200 7500 hrs or 
   15 years 
32-30 52) Visually inspect the landing gear hydraulic system
emergency valve. Check for leaks at the unions and check the control for condition. 200  
32-30 53) Visually inspect the landing gear hydraulic system tubes for evidence of leaks and wear ; check the routing ; check the attach fittings and the unions for condition and interference. 200 500 hrs 
32-40 54) Visually inspect the master cylinders. 200  
 Check the brake system for condition, attachment, union security and tightness.   
34-10 55) Drain the normal static pressure system and (if installed in rear fuselage) the emergency system - refer to 200  
　
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