Textron Bell 206L3, Руководство по обслуживанию

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BHT-206L3-MM-1 TC APPROVED
4-00-00
Page 10
Rev. 24 25 JUN 2019
Export Classification C, ECCN EAR99
Each component with a retirement life sensitive to torque events will be assigned a maximum Retirement
Index Number (RIN). This RIN corresponds to maximum allowed fatigue damage resulting from lifts and
takeoffs. A torque event is defined as a takeoff (one takeoff plus subsequent landing = one RIN) or a lift
(internal or external). For example, if an operator performs six takeoffs and 10 slingloads, this would total
16 torque events; (6 takeoffs = 6 events, 10 slingloads = 10 events, 6 + 10 = 16 torque events total).
Pilots are to record total number of torque events for each flight. This allows maintenance personnel to
convert torque events to RIN by applying the appropriate RIN adjustment factor. Refer to ASB 206L-94-99
Rev. B, dated 10 August 2001. A new component will begin with an accumulated RIN of zero, that will be
increased as lifts and takeoffs are performed. Operator will record number of lifts and takeoffs (torque
events), and increase accumulated RIN accordingly. When maximum RIN is reached or retirement flight
hours, whichever occurs first, component will be removed from service.
The retirement life of trunnion 206-011-120-103/-105 is based solely on RIN. Retire trunnion when
RIN = 24,000. For each takeoff/lift, add one RIN if the trunnion is installed on 206L, 206L1, or 206L3
(includes 206L3 with Increased Power Operation kit installed per BHT-206-SI-2039) and two RIN if the
trunnion is installed on a 206L4 (also applicable to 206L3+ helicopters (Increased Gross Weight Upgrade
Kit 206-706-530 installed per BHT-206-SI-2052)). Refer to ASB 206L-94-99 Rev. B, dated
10 August 2001.
Retire main rotor mast 206-040-535-001/-005/-101/-105/-109 when RIN = 44,000. For each takeoff/lift,
add one RIN if the mast is installed on 206L, 206L1, or 206L3 (includes 206L3 with Increased Power
Operation kit installed per BHT-206-SI-2039) and two RIN if the mast is installed on a 206L4 (also
applicable to 206L3+ helicopters (Increased Gross Weight Upgrade Kit 206-706-530 installed per
BHT-206-SI-2052)). Refer to ASB 206L-94-99 Rev. B, dated 10 August 2001.
Collective idler link 206-010-446-105, serial numbers A-1 through A-27, inclusively, and serial numbers
RE-238 through and including RE-270 will be retired from service at 1200 hours service time. Refer to
ASB 206L-98-110, dated 6 May 1998.
Collective lever 206-010-447-105, serial numbers A-1 through A-22, inclusively, will be retired from
service at 1200 hours service time. Refer to ASB 206L-98-110, dated 6 May 1998.
Swashplate support assemblies 206-010-452-109 must be inspected every 50 hours after the swashplate
support has accumulated 1500 hours in service. Refer to ASB 206L-93-89 Rev. B, dated 4 April 1994.
Landing gear aft crosstube 206-053-211-103 has an airworthiness life of 33,000 landings. Refer to
ASB 206L-94-97, dated 17 August 1994.
Reservoir per DOT-3HT specification and Exemption Letter DOT-E-7218. Life starts from date of
manufacture.
Reservoir per DOT-3HT specification and Exemption Letter DOT-E-8162. This reservoir is a detail part of
reservoir assembly 206-073-848-121. Life starts from date of manufacture.
Tail rotor blade 206-016-201-127 and subsequent, retirement life increased to 2500 hours. Refer to
TB 206L-89-147, dated 2 June 1989.
Main rotor blades 206-015-001-ALL (all dash numbers). It is permissible to use any main rotor blade (mix
and match) on 206L, 206L1, 206L3, and 206L4 provided that all conditions are met. Refer to
TB 206L-87-142, dated 1 October 1987, and IL 206L-00-68 Rev. A or subsequent.
Table 4-1. Airworthiness Limitations Schedule (Cont)
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