Honeywell International Inc. DMA-37B2 Manuale Utente

Page 2002

10 Oct 2007

DMA-37B DME System

© Honeywell International Inc. Do not copy without express permission of Honeywell.

(1) The DMA-37B DME System must be installed in the aircraft in a manner consistent with 

acceptable workmanship and engineering practices, and in accordance with the 

instructions set forth in this publication. To make sure that the system has been properly 

and safely installed in the aircraft, the installer must make a thorough visual inspection 

and conduct an overall operational and functional check of the system on the ground 

prior to flight.

(1) Location of the DMA-37B DME System in the aircraft is not critical, as long as the 

environment is compatible with the equipment design. Refer to the Leading Particulars, 

Table 5, in the DESCRIPTION AND OPERATION section of this manual. Forced air 

cooling is required for cooling the DMA-37B DME Interrogator in accordance with 

ARINC Characteristic 600. The associated cooling equipment must be mounted in 

accordance with the manufacturer’s instructions. 

(2) Antenna mounting must be in accordance with the manufacturer’s instructions for the 

antenna being used. The coaxial cable connecting the antenna to the mount must be as 

short and direct as possible and any required bends must be gradual. When two or more 

DMA-37B DME Systems are installed in an aircraft, it is necessary to provide adequate 

space isolation between antennas of each system to make sure that the use of one unit 

does not interfere with reception from another system. A minimum of 35 dB of space 

isolation must be provided, and any steps which can be taken to provide further isolation 

must be considered.

(3) Control unit location and mounting can be determined by mutual agreement between the 

user and airframe manufacturer.

(1) General

(a) Figure 2006 is a complete interwiring diagram for a single DMA-37B DME System 

and associated components. This diagram requires thorough study before the 

installer begins installation of the aircraft wiring.

(b) When two systems are being installed in the aircraft, the interconnecting wiring 

shown in Figure 2006, as well as all other installation instructions must be 

duplicated.

(c) Cabling must be fabricated by the installer in accordance with Figure 2006. Wires 

connected to parallel pins must be approximately the same length, so that the best 

distribution of current can be effected. Honeywell recommends that all wires, 

including spares, shown in Figure 2006, be included in the fabricated harness. 

However, if full ARINC wiring is not desired, the installer must make sure that the 

minimum wiring requirements for the features and functions to be used are 

incorporated.