MD Helicopters 369 Series, Manual

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CSP−HMI−2
MD Helicopters, Inc
.
MAINTENANCE MANUAL
Page 14
Revision 39
04−00−00
FAA APPROVED
(25) The 600N3500 − 503 tailboom may be reworked to a 600N3500 − 505 tailboom, and the 600N3500 − 513
tailboom may be reworked to a 600N3500 − 515 tailboom by modifying the attachment fittings to all − steel
fittings.
(26) (Ref. Sec. 05 − 20 − 00) Using a flashlight and 10X magnifying glass, inspect horizontal stabilizer mounting
brackets for cracks (pay particular attention to the forward inboard legs) (Ref. Tailboom Inspection).
(27) Sockets must be inspected for cracks every eight hours after the initial 100 hour inspection.
(28) Log all landings: Brace life is limited to 35400 logged landings or 5900 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(29) Log all landings: Strut life is limited to 4170 logged landings or 696 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(30) Log all landings: Foot life is limited to 23780 logged landings or 3900 hours flight time if landing are not
logged (assumed six landings per one hour of flight time).
(31) The following main rotor blades have a finite life of 2,500 hours or 15,000 torque events*, whichever occurs
first;
P/N 369D21100 − 517 with S/N H664, H665, H667, H669, H671, H672, H674, H676, H679, H680, H683 thru
H724, H726 thru H999 and J000 thru J039, J041 thru J055 and
P/N 369D21102 − 517 with S/N 1976 thru 2100, 2106 thru 2115.
* TORQUE EVENT (TE) − A TE is recorded for every transition from forward flight to a hover (Reference
Service Bulletins SB369D − 195R3, SB369E − 088R3, SB369F − 075R3, SB500N − 015R3).
(32) RIN = (200 x Hrs.) + (52 x TE).
(33) RIN = (160 x Hrs.) + (24 x TE).
(34) RIN = (153 x Hrs.) + (3 x TE).
(35) RIN = (50 x Hrs.) + (3 x TE).
(36) RIN = (768 x Hrs.) + (11 x TE).
(37) After accumulation of 750 flight hours and 13,720 TE, perform Main Rotor Blade Torque Event Inspection
(Ref. Sec. 62 − 10 − 00) every 35 flight hours or 200 TE’s (whichever occurs first).
(38) The 369D21640 − 501, − 503, − 505, − 507 tail rotor blades are two − way interchangeable with the 369D21613
tail rotor blades in sets of two only.
The 369D21641 − 501, − 503, − 505, − 507 tail rotor blades are two − way interchangeable with the 369D21615
tail rotor blades in sets of two only (installed on the same inboard or outboard hub).
The 369D21642 − 501, − 503, − 505, − 507 tail rotor blades are two − way interchangeable with the 369D21606
tail rotor blades in sets of two only.
(39) The 369H1203 − BSC, − 11, − 21, − 31, − 51 and − 61 lead lag link assemblies can only be installed using the
369H1235 − BSC bearing.
(40) The 369H1203 − 53 lead lag link assembly can only be installed using the 369H1235 − 1 bearing.
(41) The 369N2608 − 11 Control Support Bracket must be removed from 600N helicopters equipped with YSAS
(Ref. SB600N − 040).
(42) RIN = (29 x Hrs.) + (1 x TE).