Metro Audio Systems EC-135 Series Manuel utilisateur

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

SECTION I SYSTEM DESCRIPTION

The information contained herein supplements the information of the basic Flight Manual.

Forlimitations,procedures, andperformancedata notcontainedinthis supplement, referto

the basic Flight Manual.

1. General

This avionics system is designed to provide the pilot with redundant communication,

navigation, display, and automatic flight control systems (AFCS) for use in single-pilot IFR

operations.

1.1 Basic description

1.1.1 SYSTEM COMPONENTS

Component: Reference Manufacturer

Flight Control Display Sys FMS 9.2-53 (single) ECD

Flight Control Display Sys FMS 9.2-49 (dual) ECD

Standby Attitude Indicator FMS 9.2-56 or equivalent ECD

Standby VOR/ILS Indicator FMS 135M-150 MAI

AFCS:

Three-axis Autopilot System FMS 9.2-48 ECD

Pitch, Roll and YAW SAS FMS 9.2-5 ECD

Pitch Damper FMS 9.2-5 ECD

Navigation and communication system:

Two Nav / Com radios including: FMS 135M-150 MAI

VHF Communication

VOR / Localizer Receiver

Glide Slope Receiver

GPS Receiver

Standby Navigation Receiver (optional) FMS 135M-150 MAI

Marker Beacon Receiver FMS 135M-150 MAI

DME FMS 135M-150 MAI

Radio Altimeter FMS 135M-150 MAI

Transponder with Mode S FMS 135M-150 MAI

Two Audio Systems FMS 135M-150 MAI

Altitude Alerting System (optional) FMS 135M-150 MAI

Miscellaneous Systems:

Two Inverters FMS 9.2-4 ECD

Two AHRS including magnetometers FMS 9.2-48 ECD

Two Air Data Computers (ADC) FMS 9.2-48 ECD

Second heated pitot system FMS 9.2-44 ECD

Search Light FMS 9.2-8 or equivalent ECD

Annunciators, controls, and switches FMS 135M-150 MAI

Spare headset and ICS Cord FMS 135M-150 MAI

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

1.2 Displays and controls

1.2.1 Reconfiguration Control Unit (RCU) and Instrument Control Panel (ICP)

INACTIVE

1.2.2 Autopilot Mode Select (APMS) panel

1.2.3 Cyclic functions

SAS, P damper reset

SAS & AP cut-off

pitch & roll attitude and

upper mode function beep

force trim release

/P upper mode decouple

Spare

Transponder IDENT

Com #1 freq. transfer

TYPICAL CYCLIC CONTROL GRIP

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

1.2.4 Instrument panel

APMS

ICP #2

ICP #1

AUDIO #1 AUDIO #2

RCU

ENG CONTROL

ELEC CONTROL

CAD VEMD

XPNDR

NAV / COM #1

NAV / COM #2 ND

PFD

STBY

VOR / ILS

CLOCK STBY STBY STBY

A/S HORIZ ALT TRIPLE

TACH

WARNING PANEL

ALT ALERT

STBY NAV

PGS 1

PGS 2

RAD DIM

GPS DIM

DME HOLD

OBS

SINGLE-PILOT IFR INSTRUMENT PANEL TYPICAL CONFIGURATION

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

1.2.5 Instrument panel (Alternate Configuration)

SINGLE-PILOT IFR INSTRUMENT PANEL GNS-530 OPTION

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

1.3 Communication and Navigation

1.3.1 Combined navigation and communications system

The Garmin GNS-430/530 system consists of two fully integrated, panel mounted

nav/com radios. The system consists of a GPS antenna, GPS Receiver, GPS

navigation computer, VHF VOR/LOC/GS antenna, VOR/ILS/GS receiver, VHF

COMM antenna and a VHF communications transceiver.

Com#1 frequenciesmay betransferredbetween standbyandactive viaadedicated

switch on the pilot’s cyclic control grip (reference paragraph 1.2.3). Holding this

switch down for 2 seconds or more will place the emergency frequency 121.5 in the

active com 1 window.

NOTE: To go back to normal operation, after a “Com not Responding” message

occurs, the radio must be cycled off then on.

Provided the GPS receiver is receiving adequate usable signals, it has been

demonstrated capable of and has been shown to meet the accuracy specifications

for VFR/IFR enroute,terminal,and non-precisioninstrumentapproaches. Number 1

GNS-430/530VOR/ILS also drivestheGI-106 AstandbyVOR/ILS Indicatordirectly.

If the optional NR3320 VOR/ILS system is installed see 1.3.2 for GI-106A

description.

1.3.2 Standby VOR / ILS System (Optional)

StandbyVOR /ILS System consistsof a dedicatedNavigation Receiver(NR-3320)

which Navigation Indicator (GA-106A) powered on the Emergency Battery Bus for

VOR and LOC/ILS Navigation only.

1.4 Bus structure

1.4.1 Emergency Battery Bus

Thefollowing componentsare availablefollowingelectrical system failure andpower

is ensured for a minimum of 30 minutes:

•Standby Horizon

•Cockpit Floodlight

•Standby VOR / ILS System (Optional)

1.4.2 Essential buses

The following systems are available following dual generator system failure:

•Both Nav / Com radios

•Pitch and Roll SAS

•Yaw SAS

•Mode S transponder

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

1.4.3 Shed bus

The following systems are shed only following dual generator system failure:

•PFD & ND

•Autopilot (Note: Pitch and Roll SAS and Yaw SAS is available.)

1.4.4 IFR avionics bus

The following shows the general architecture of the avionics bus:

STBY HOR

STBY VOR / ILS

CKPT LTS

AHRS 1 AHRS 2

PITCH SAS

ROLL SAS BUS 1 BUS 2

PFD ND

ND PFD

BLW PEL

AHRS 2

ADC 2

AP 2

FCDM 2

DME

RAD ALT

FANNAV 2

COM 2

TXP

NAV 1

COM 1

AHRS 1

MKR

ALT ALERT

FDCM 1

DTS

AP 1

ADC 1

BLW PEL

ND PFD

AVIONICS

MASTER 1

INV SEL SW

AVIONICS ESS 1

EMER BUS 26 VAC BUS 1 26 VAC BUS 2 DISPLAY TST SW

SHED BUS 2

AVIONICS

MASTER 2

AVIONICS SHED 2AVIONICS ESS 2

ESS BUS 2

YAW SAS

MAST MM

PITCH DAMP

INST LT

A-COL LT

INV 2

INV 1

MSTR 2MSTR 1ESS B1 ESS B2

ESS BUS 1

WIPER

P / R SAS

TRIM REL

ROLL SEMA

YAW SEMA

AUD 1 AUD 2

XFR PUMP

HOR BAT

PIT HTR / ST HTR

LDG LT PWR

LDG LT CONT

POS LT

TRIM ACT (MTR)

SHED BUS 1

AVIONICS SHED 1

SHED BUS 2

ANN LT

PAX LT

XFR PUMP

HI LOAD BUS 1

EMB 1

GEN 1

HL 1

SHED 1 BUS TIE 1 BUS

TIE 2

GEN 2 EPU

HL 2

SHED 2

EMB 2

BAT MSTR BOX

BAT

GEN 2

BATTERY

26 AH EPU

HI LOAD BUS 2

GEN 1

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

SECTION II

LIMITATIONS

2. LIMITATIONS

2.1 Approved operation

This helicopter is approved for single-pilot day and night VFR and IFR operation

when the Metro Aviation, Inc. SPIFR kit (135M-150) is installed.

2.2 Operational limitations

Dispatch for single pilot IFR operation is permissible only with AFCS engaged and

fully operational.

2.3 Compatibility with other optional equipment

The following kit is not compatible:

•External mirror (FMS 9.2-19)

2.4 Flight crew

The minimum flight crew consists of one pilot in the right crew seat.

2.5 Flight limitations

2.5.1 Forward speed

Min. Airspeed (V min IFR) 60kt

Never exceed speed (VNE IFR) V

Best rate-of-climb speed (VyIFR)=Vy 65kt

2.5.2 Vertical speed

Maximum rate of descent 1500ft/min

2.5.3 Approach angle limitations

Maximum glide slope angle for approach 4.6o

2.5.4 Bank angle limitation

Maximum bank angle above 12,000 feet pressure altitude 20°

2.5.5 Altitude limitations

Maximum operating pressure altitude 15,000 Feet

METRO AVIATION, INC. FMS 135M-150

P.O. Box 7008

Shreveport, LA 71137

FAA Approved: 3/15/07 Revision E

2.5.6 Temperature limitations

Max OAT for aircraft operation is 45oC.

Ventilation must be set to maximum if OAT is greater than 30oC.

Max OAT for AFCS continuous operation with loss of ventilation is 30oC.

Max AFCS operating time with loss of ventilation is 30 min when OAT is between

30oC and 35oC.

Max operating time on ground is 20 minutes when OAT is greater than 42oC.

Max operating time on ground is 30 minutes when OAT is less than 42oC.

2.6 GPS limitations

APilot's Guide mustbeimmediately availabletothe flight crewwhenevernavigation

is predicated on the use of the system as follows:

GPS Model Manual P/N Rev. Level Date Effective

GARMIN GNS-430 190-00140-00 Rev. A Oct 1998 or later revision

GARMIN GNS-530 190-00181-00 Rev. B May 2001 or later revision

2.6.1 Software versions

The GNS-430/530 must utilize the following or later FAA approved software

versions:

Sub-System Software Version (GNS-430) Software Version (GNS-530)

Main 2.22 2.08

GPS 2.10 2.10

COMM 4.01 4.01

VOR/LOC 3.01 3.01

G/S 2.03 2.03

NOTE: The Main software version is displayed on the GNS-430/530 self test page

immediately after turn-on for 5 seconds. The remaining system software versions

can be verified on the AUX group sub-page 2, “SOFTWARE/DATABASE VER”.

2.6.2 GPS navigation limitations

2.6.2.1 Enroute

IFRenroute andterminal navigationpredicated uponthe GPS receiver isprohibited

unless the pilot verifies the currency of the data base or verifies each selected

waypoint for accuracy by reference to current approved data.

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