CSP
−
902RFM207E
−
1
ROTORCRAFT FLIGHT MANUAL
MD900 (902 Configuration with PW 207E)
Systems Description
Original
7
−
24
Reissue 2
7
−
8.
PROPULSION SYSTEM
The propulsion system is designed to meet the engine isolation requirements for
multi-engine rotorcraft that are defined by the Category A requirements of FAR
Part 29, paragraph 29.903(b).
Powerplant:
This system consists of two Pratt and Whitney Canada (P&WC) PW207E turbo
shaft engines mounted above the baggage compartment and pointing inboard
to drive into the main transmission gearbox (Ref. Figure 7-13 and Figure 7-14).
Each engine is mounted to the fuselage upper deck by a three point, adjustable
titanium mount. The air inlet which is in the middle of the engine is located
inside a titanium-walled inlet plenum that leads from a flush-mounted inlet
in the side of the cowling. The combuster end of the engine is surrounded by
titanium firewalls forward, aft, inboard side, and below. It is covered by a fairing
door, and is ventilated by an exhaust-driven ejector at the aft end of the compart
ment.
PRIMARY EXHAUST
NOZZLE ASSEMBLY
SECONDARY
EJECTOR
INSULATION
BLANKET
F92
−
067
TRIPOD
MOUNT
TRIPOD
MOUNT
FWD INLET
PANEL
AFT INLET
PANEL
ENGINE
AIR INLET
REAR STAY
ASSEMBLY
FORWARD
FIRE SEAL
AFT
FIRE SEAL
FMU
SHROUD
Figure 7
−
13. PW207E Engine Installation
Summary of Contents for MD900 Explorer
Page 4: ......
