Integrated Engine Instrument Systems; Meggitt Engine Instrument Display System (Eids) - Piper Malibu Meridian PA-46-500TP Airplane Maintenance Manual

1.

Meggitt Engine Instrument Display System (EIDS) -

Meggitt Avionics' next Generation Integrated Cockpit (MAGIC) Engine Instrument Display System (EIDS)
is the primary engine instrumentation. The MAGIC EIDS consists of two primary components:
Engine Display Unit (EDU) and
Data Acquisition Unit (DAU).
NOTE: Whenever a DAU is replaced, perform Engine Torque Indication Calibration, 77-10-00; Fuel
Quantity Indication Calibration, 28-40-00; and, Fuel System Functional Test, 28-00-00.
WARNING: FAILURE TO CONSULT APPLICABLE VENDOR PUBLICATION(S), WHEN SERVICING
OR INSPECTING VENDOR EQUIPMENT INSTALLED IN PIPER AIRCRAFT, MAY
RENDER THE AIRCRAFT UNAIRWORTHY. (SEE INTRODUCTION - SUPPLEMENTARY
PUBLICATIONS.)
As installed in the Meridian, a single Data Acquisition Unit (DAU) and its associated sensors feed two
Engine Display Units (EDU) (a primary and a secondary). Torque (TQ), fuel flow (FF), inter-turbine
temperature (ITT), propeller speed (Np), and gas generator speed (Ng) are acquired by the DAU through
dual redundant channels. In addition, vacuum pressure (VAC), oil temperature (OT), outside air
temperature (OAT), and oil pressure (OP) are acquired by the DAU on a single channel and then cross-
fed to dual redundant channels. The left, right, and total fuel level is also determined by the DAU.
Engine instrumentation display is provided by the primary and secondary EDU. The primary EDU is
located on the pilot's side to the left of the standby airspeed indicator and the secondary EDU is located
on the co-pilot's side to the right of the standby altimeter. The information displayed is primarily derived
from signal conditioned, digital data provided by the DAU, which is located behind the instrument panel,
mounted to a bracket on the right side of the forward pressure bulkhead. The only data not provided by
the DAU is the estimated time enroute (ETE) and fuel at destination (FAD) displays which both require
Garmin GPS data and an active flight plan.
The primary EDU indicates torque, ITT, Np, and Ng in both analog and digital format. During engine
start, fuel flow is also digitally indicated on the primary EDU. The secondary EDU indicates vacuum
pressure, fuel flow, remaining useable fuel, oil temperature, and oil pressure in both analog and digital
format. Additional secondary EDU digital indications are OAT, ETE, and FAD, accompanied by the
appropriate GPS 1 or 2 data source label.
The system also includes exceedance, engine condition trend monitoring (ECTM), and instrumentation
fault detection features. Parameter exceedance data is recorded by the DAU for display on the EDU and
subsequent download to a laptop. A parameter exceedance is alerted by an aural alarm and visual
warning consisting of digital indications highlighted with a red background and analog indications with a
red pointer. The aural alarm is cancelable by pressing the mute switch, located below the glare shield on
the pilot side. Engine condition trend monitoring data is automatically recorded by the DAU for
subsequent download to a laptop. Recording of ECTM data is signified by a CRUISE1 or CRUISE2
indication on the primary EDU. In addition, the EDU is constantly searching for instrumentation faults
caused by a failure in the EDU, DAU, or its associated sensors. Should a system fault occur, a MAINT
indication is displayed on the primary and secondary EDU. Upon completion of the flight, all MAINT
indications should be investigated by a qualified technician and the necessary repairs made prior to
further flight.
Line maintenance of this system is limited to basic troubleshooting.
A. Troubleshooting
See Chart 1.
7J1
PIPER AIRCRAFT, INC.
PA-46-500TP, MALIBU MERIDIAN
MAINTENANCE MANUAL

INTEGRATED ENGINE INSTRUMENT SYSTEMS

77-40-00
Apr 15/07
PAGE 1