Textron Bell 412, Руководство по обслуживанию

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BHT-412-MM-2
5-00-00
Page 18
Rev. 16 26 FEB 2013 Export Classification C, ECCN EAR99
4. Tail rotor pitch change links, crosshead, pitch horns,
counterweight arms, and links for security, corrosion, and
condition.
5. Pitch link bearing and counterweight link bearing
looseness shall not exceed 0.015 inch (0.381 mm) axial. Check
freedom of movement through full range of travel with antitorque
pedals positioned full right and then full left.
6. Pitch change links for binding with tail rotor blade moved to
both full flapping positions. Binding is not acceptable.
Chapter 65 TAIL ROTOR DRIVESHAFT
NOTE
Step 1 through step 5 pertain to helicopters S/N
33001 through 33213 and 36001 through 36019 not
modified by 412-570-001-003 or Pre BHT-412-SI-74
(412SP to 412HP Upgrade).
WARNING
CAUSE OF ANY DISCOLORATION SHALL BE
DETERMINED AND CORRECTED PRIOR TO
NEXT FLIGHT.
1. Hanger assemblies — bearings and surrounding areas for
evidence of grease leakage, condition, damage, security,
corrosion, and overheating. Discoloration of bearing (color
change to blue to blue/black in color) or multi-color appearance
of hanger that darkens adjacent to bearing is evidence of
overheating. Brown color of bearing shield is normal and is not
evidence of overheating.
2. Driveshaft sections for cracks, rivet failure, distortion,
dents, corrosion, and for damage to anodized finish.
3. Clamp sets for condition, security, and proper installation.
SCHEDULED INSPECTIONS
5-5. DAILY INSPECTION — PART A (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
INITIAL
MECH OTHER