Mid-Continent Instrument MD215 Series Technisches Dokument

Installation Manual and Operating Instructions

Model MD215 Series

Hybrid Counterdrum Altimeter

Mid-Continent Instrument Co., Inc.

dba Mid-Continent Instruments and Avionics

9400 E. 34th Street N.

Wichita, KS 67226 Manual Number 9018501

ph (800) 821-1212 fx (316) 630-0723 Revision C, October 11, 2017

Manual Number 9018501 2 Revision C, October 11, 2017

FOREWORD

This manual provides information intended for use by persons who, in accordance with current regulatory

requirements, are qualified to install this equipment. If further information is required, please contact:

Mid-Continent Instruments and Avionics

Attn: Customer Service Dept.

9400 E. 34th Street N.

Wichita, KS 67226 USA

PH (316) 630-0101

FX (316) 630-0723

www.mcico.com

We welcome your comments concerning this manual. Although every effort has been made to keep it free

of errors, some may occur. When reporting a specific problem, please describe it briefly and include the

manual part number, the paragraph/figure/table reference and the page number. Send your comments to:

Mid-Continent Instruments and Avionics

Attn: Technical Publications

9400 E. 34th Street N.

Wichita, KS 67226 USA

PH (316) 630-0101

FX (316) 630-0723

ks.customerservice@mcico.com

All products produced by Mid-Continent Instrument Co., Inc., including those identified as Mid-Continent

Instruments and Avionics or True Blue Power, are designed and manufactured in Wichita, KS, USA.

Mid-Continent Instrument Co., Inc.

Manual Number 9018501 3 Revision C, October 11, 2017

REVISION HISTORY

Revision Date Approved Detail

A 10/30/2015 BAW Initial Release.

B 01/19/2016 BAW Updates for TSO application.

C 10/11/2017 MKN Updated Figure 3.1 with notch.

Manual Number 9018501

4 Revision C, October 11, 2017

TABLE OF CONTENTS

SECTION 1GENERAL DESCRIPTION ..................................................................................6

1.1



Introduction ...................................................................................................................................... 6



1.2



Technical specifications ................................................................................................................... 7



Electrical Attributes ............................................................................................................... 7



Physical Attributes................................................................................................................. 7



Qualifications......................................................................................................................... 7



ARINC data labels................................................................................................................. 8



Gillham Code (Encoding Altimeter output)............................................................................ 9



SECTION 2PRE-INSTALLATION.........................................................................................10

2.1



General Information ....................................................................................................................... 10



2.2



Unpacking and inspecting equipment ............................................................................................ 10



2.3



Equipment Location ....................................................................................................................... 10



2.4



Cable Harness ............................................................................................................................... 10



Wire Gauge Selection ......................................................................................................... 11



Cable Harness Assembly.................................................................................................... 11



2.5



Limitations ...................................................................................................................................... 13



SECTION 3INSTALLATION .................................................................................................14

3.1



General .......................................................................................................................................... 14



3.2



mounting ........................................................................................................................................ 14



Rear Mount Installation ....................................................................................................... 15



Front Mount Installation....................................................................................................... 16



3.3



installation completion.................................................................................................................... 16



SECTION 4OPERATION......................................................................................................17

4.1



Description ..................................................................................................................................... 17



4.2



User Interface................................................................................................................................. 17



Altitude Display and Units ................................................................................................... 18



Pointer ................................................................................................................................. 18



Baro Setting and Units ........................................................................................................18



Push-button Rotary Knob (Flight Mode) ............................................................................. 18



Push-button Rotary Knob (Configuration Mode) ................................................................. 19



INOP Flag............................................................................................................................ 19



Annunciations (Flight Mode) ............................................................................................... 19



4.3



Modes of Operation........................................................................................................................ 19



Flight Mode.......................................................................................................................... 19



Manual Number 9018501

5 Revision C, October 11, 2017



Emergency Mode (for battery-installed units only).............................................................. 20



Configuration Mode............................................................................................................. 22



SECTION 5CONFORMANCE ..............................................................................................24

5.1



Instructions for Continued Air-Worthiness ..................................................................................... 24



Pressure System and Altimeter Verification........................................................................ 24



Maintenance........................................................................................................................ 24



Firmware Updates............................................................................................................... 24



Storage Information (for battery-installed units only) .......................................................... 24



Battery Maintenance and End of Life (for battery-installed units only) ............................... 24



Battery Disposal (for battery-installed units only)................................................................ 25



Shipping (for battery-installed units only) ............................................................................ 25



5.2



ENVIRONMENTAL QUALIFICATION STATEMENT .................................................................... 26



Manual Number 9018501 6 Revision C, October 11, 2017

SECTION 1 GENERAL DESCRIPTION

1.1 INTRODUCTION

The model MD215-( ) series two-inch Electric Hybrid Counterdrum Altimeter is a pressure actuated,

encoding, sensitive altimeter built to meet or exceed standards set forth in FAA TSO-C10b, C88b, C106,

C179a. The unit provides critical altitude data to the pilot and crew and offers features that enhance

usability, reliability and convenience.

The MD215 provides a needle pointer and two rotating counter drums to indicate altitude up to 55,000

feet and includes an adjustable barometric pressure correction. The user interface features a simple

push-and-turn knob to change the barometric pressure adjustment and address other features. The

flexibility of the MD215 also allows user-configurability to meet a variety of altitude requirements,

including altitude units in both feet and meters and barometric pressure units in both inches of mercury (in

Hg) and millibars (mBar).

The MD215 is designed to be installed in an aircraft cockpit instrument panel and has available options

for either a standard 2-inch ARINC-style front mount or round, bezel-mounted rear mount. Anti-reflective

glass maximizes contrast ratio and provides a clear, efficient display.

The primary input is a pneumatic connection to the aircraft’s static pressure system. Additionally, power is

provided by any input between 10 and 32 volts DC, allowing operation with 14 or 28V aircraft electrical

buses. The configurable lighting input powers an LED backlit display and can accept 5, 14 or 28V lighting

systems.

The MD215 offers excellent reliability based on its solid-state pressure sensor and servo-driven display,

far exceeding the expected life of traditional mechanical altimeters. Versions of the unit are also available

that include an integral and rechargeable Nanophosphate® lithium-ion battery that can power the unit for

one hour if main aircraft power is lost.

The unit has enhanced outputs and communication that provide information to and from the aircraft via a

single ARINC 429 receive bus and an ARINC 429 transmit bus. The input function can receive ARINC

data from the primary flight display system to automatically synchronize the baro adjustment with that

system without redundant pilot intervention. The data outputs provide altitude, baro and other data that

make the unit useful as an independent source of this information as needed on the aircraft. Traditional

encoding outputs (Gillham code) may also be connected to a mode-C transponder or similar legacy

equipment.

The operation and certification of the MD215 make it a great fit for Part 23 and 25 fixed-wing applications

as well as Part 27 and 29 rotorcraft.

Manual Number 9018501

7 Revision C, October 11, 2017

1.2 TECHNICAL SPECIFICATIONS

Electrical Attributes

Characteristics:

Input Voltage: 10-32 VDC

Input Power: (nominal) 3 watts (0.11A @ 28VDC)

(maximum) 9 watts max (when charging)

Battery Capacity (if installed): 3.3 watt-hours

Lighting Input: 5, 14, or 28VDC or automatic photocell control

Input Data: ARINC 429 (see Section 1.2.4)

Output Data: ARINC 429 (see Section 1.2.4);

Gillham encoded data (see Section 1.2.5)

Valid discrete signal to ground; invalid signal is open (pin 2)

Physical Attributes

Characteristics:

Range (altitude): -1,500 feet to 55,000 feet (-450 to 16,900 meters)

Range (baro): 28.00 to 31.00 IN HG (948 to 1050 MBAR)

Weight: 2.0 pounds (0.91 kg)

Dimensions:

(without connectors, mates & knob)

Bezel: 2.27” x 2.27” x 0.23” (HxWxD)

Chassis: 2.18” x 2.18” x 4.63” (HxWxD)

Cover Glass: HEA (anti-reflective) coated per MIL-C-14806

Mating Connectors: 9/16-18 UNJF-3B per MS33649-06 pneumatic fitting (MCI P/N

NY-400-1-6ST)

26-pin D-Sub, MCIA p/n 9018118 (Installation Kit)

Mounting: Front or rear mount, see panel cutout; Figure 3.1 and Figure 3.2

Lighting: Internally lit with white LEDs

Qualifications

Specifications:

Qualification: FAA TSO-C10b, C88b, C106, C179a

Environmental Qualification: RTCA DO-160G

(details listed in Section 5.2)

Complex Hardware Qualification: RTCA DO-254, Design Assurance Level A

Manual Number 9018501

8 Revision C, October 11, 2017

ARINC data labels

All labels are defined as Equipment ID 006 in BNR format.

ARINC 429 Output (Transmit) Speed

Label

Description

High

Low

203

Pressure Altitude

204

Baro Corrected Altitude

212 Altitude Rate X

217 Static Pressure, Corrected X

234 Baro Correction (mbar) X

235 Baro Correction (in Hg) X

350 Hardware Version (custom) X

377 Equipment ID (006) X

ARINC 429 Input (Receive) Speed

Label

Description

High

Low

203

Pressure Altitude

204

Baro Corrected Altitude

234 Baro Correction (mbar) X X

235 Baro correction (in Hg) X X

Table 1.1

ARINC Data Labels

Manual Number 9018501

9 Revision C, October 11, 2017

Gillham Code (Encoding Altimeter output)

Gillham output data (10 bits plus enable) is provided to be consistent with a legacy encoding

altimeter. These outputs are traditionally connected to an ATC Transponder, although they could

be used for other purposes.

The data format is described in the International (ICAO) Standard Code for S.S.R. Pressure

Altitude Transmission contained in ICAO International Standards and Recommended Practices;

Aeronautical Telecommunications, Annex 10, Volume I, Part I, Equipment and Systems. This

document is referenced by SAE AS8003, as required by FAA TSO C88b.

The enable bit (TRANSMIT_ENABLE_N pin 25 listed in the pinout Table 2.1) must be connected

to GND (pin 2 or equivalent) in order to actively update the outputs for normal operation.

Specifications:

Output voltage tolerance 0 – 40V

Current per output 0 – 150mA

Output impedance Modeled as FET in series with 15 ohms to GND

Output voltage Dependent on supply, self-limiting to 150mA

Leakage current 250uA

Maximum rate of change for coded altitude 20,000 ft/min

Maximum switching rate for transmit enable 100 KHz

Table 1.2

Gillham Output Data Specifications

Manual Number 9018501 10 Revision C, October 11, 2017

SECTION 2 PRE-INSTALLATION

2.1 GENERAL INFORMATION

This section contains information and considerations required to prepare for the MD215 installation,

including provided equipment, panel location, wiring and other information.

2.2 UNPACKING AND INSPECTING EQUIPMENT

When unpacking this equipment, make a visual inspection for evidence of any damage that may have

incurred during shipment. The following parts should be included:

a. Hybrid Counterdrum Altimeter MCI P/N 6420215-( )

b. Installation Kit MCI P/N 9018105

i. Electrical Connector Kit MCI P/N 9018118

ii. Pneumatic Fitting MCI P/N NY-400-1-6ST

iii. Screw, #6-32x3/8” MCI P/N 90-612-10011

c. Installation Manual MCI P/N 9018501

Equipment Not Provided

a. Wire, 22AWG (see 2.4.1)

b. Mounting Hardware (Front Mount Installation)

i. ATI2 Instrument Clamp MSP 9962B or similar

ii. Washer, Lock, #6 (optional) Qty (3)

2.3 EQUIPMENT LOCATION

The MD215 Hybrid Counterdrum Altimeter is designed primarily to be installed in the instrument

panel of the aircraft. However, within the limitations of the environmental qualifications, other

locations may be acceptable when considered within the context of the specific application and

with the appropriate installation certification.

Additionally, consider what equipment is behind the panel which may impede the installation of

the MD215. Clearance for the unit as well as its electrical and pneumatic connections and routing

must be allowed. Be aware of routing cables near other electronics or with other wire bundles that

may be susceptible to high energy flow. Avoid sharp bends in cabling or hoses and routing near

aircraft control cables. Also, avoid proximity and contact with aircraft structures, avionics

equipment, heat sources or other obstructions that could chafe or damage wires or hoses during

flight and cause undesirable effects.

2.4 CABLE HARNESS

Construct the cable harness in accordance with the instructions below (see Figure 2.1). Installers

should follow industry-accepted practices regarding aircraft wiring and applicable regulatory

requirements and guidance. The instructions for constructing the cable harness as listed within

this manual were also used to construct the harness during environmental and electrical testing.

Alterations may invalidate environmental qualification and/or performance results. Refer to

Section 2.3: Equipment Location for routing precautions.

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