Tesla TI4676 - Manual (Page 18)

CHAPTER 4
OPERATING AND INSTALLATION PROCEDURES
SECTION I. UNIT INSTALLATION
4-1. INSTALLATION
1. Remove original aircraft battery and dispose of properly (follow
your aircraft’s manual for proper removal and disposal of aircraft
battery).
2. Ensure that the TI4676 MPU is fully charged. Remove AC cord and
place the TI4676 MPU in the same position of the original battery (en-
sure that the DC receptacle is oriented in the same position as the
original battery).
3. Position the TI4676 MPU so that the aircraft battery tie-down bolts
are aligned with the bracket on the MPU. Secure the aircraft tie-down
bolts so that the MPU is securely fastened.
4. Attach the aircraft DC plug so that it is fully seated into the MPU
receptacle.
5. Because the TI4676 MPU uses monolithic dry-cell batteries, there is
no need to attach the ventilation tubes to the MPU.
6. Because there is no hazardous materials or liquids in the cells,
there is no risk of thermal runaway, and therefore no need to hook up
temperature sensors.
SECTION II. OPERATING PROCEDURES
4-2. GENERAL
Correct operation of the TI4676 includes both pre-use and operational
checks of the unit. Knowledge of the operating limits, restrictions,
performance, unit capabilities and functions is fundamental to correct
and safe operation. The operator shall ensure compliance with the in-
structions in this manual that affect operational safety and the war-
ranty of the unit.
4-3. OPERATING LIMITS AND RESTRICTIONS
The minimum, maximum and normal operating ranges result from careful
engineering and evaluation of test data. These limitations must be
adhered to during all phases of operation. Refer to Chapter 3, Section
II, OPERATING LIMITS AND RESTRICTIONS, for detailed information.
4-4. PERFORMANCE
Refer to Chapter 5, PERFORMANCE DATA to determine the capability of the
TI4676. Consideration must be given to changes in performance result-
ing from variations in ambient temperature, mode of operation, state of
charge (with or without 120 or 240 VAC power), and aircraft DC bus sys-
tem inefficiency (voltage drops).
4-1