Attachment_2_-_APN-209_Performance_Specifications_-_17R0017.pdf

NOTE DATA MARKED WITH AN ASTERISK (*) IS PECULIAR TO A PRIOR

MANUFACTURER IT DOES NOT TAKE PRECEDENCE OVER ANY

OTHER DATA ON THIS DRAWING AND IS NOT CONTRACTUALLY

BINDING ON EITHER THE CONTRACTOR OR THE GOVERNMENT.

D E P A R T M E N T O F D E F E N S E U S A R M Y E L E C T R O N I C S C O M M A N D

F O R T M O N M O U T H N E W J E R S E Y 0 7 7 0 3

S C A L E

80063

A S H E E T

H O N E Y W E L L I N C .

R E V I E W E D

A P P R O V E D

D A T E

E L E C T R O N I C C O M M A N D

THIS DOCUMENT HAS

BEEN PURCHASED BY

THE GOVERMENT

AND MAY BE

REPRODUCED AND

USED IN

CONNECTION WITH

ANY GOVERNMENT

PROCUREMENT OR

MAINTENANCE

OPERATION

S I Z E C A G E C O D E

MSWORD

NONE

DRAWN

APVD

DATE

DATE

PREPARED IN ACCORDANCE WITH DOD-STD-100

APPLICATION

NEXT ASSY USED ON

HG7209AD

HG7210AC

REVISIONS

LTR DESCRIPTION DATE APPROVED

- CONTROL/EO 96-7877-0028 96-03-19 HG7209AD01

A REV PER EO 96-10423 96-06-04 BK/MA

B REV PER EO 96-10496 96-06-20 BK/MA

C REV PER EO 96-10667 96-08-15 BK/MA

D SEE ECO 133663 2011/10/18 EW/MAC

PERFORMANCE SPECIFICATION FOR

RT-1115J/APN-209(V) AND

RT-1411B/APN-209(V)

A3183960

REV D A A A B A A B A - - - A A - C - - - A B - C - B - C -

SHEET 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

REV - - A C A B B B B D C A C A A A B A A A B A A A A A A A

SHEET 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56

CONTROL CLASS C

D A A B 0 7 - 9 5 - C - B 7 5 8

P R

O D

U C

T

IO

N

R el ea se

O ct

:3

5:

M S

T

P rin te d on

Ju l 2

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1.0 SCOPE 8

1.1 General description. 8

1.1.1 IRT 8

1.1.2 RT 8

2.0 GENERAL 9

2.1 Applicable documents 9

2.2 Definitions 10

2.3 Test equipment 10

2.3.1 Standard (commercial) test equipment 10

2.3.2 Special test equipment 10

3.0 REQUIREMENTS 10

3.1 Power input 10

3.1.1 Power input summary 10

3.1.1.1 IRT 10

3.1.1.2 RT 11

3.1.2 Integral lighting power (IRT only) 11

3.1.3 Dimming control power (IRT only) 11

3.1.4 Power on control 11

3.1.5 Transient spike voltages 11

3.2 System constraints 11

3.2.1 Antenna isolation 11

3.2.2 RF cables 11

3.3 Performance requirements 11

3.3.1 Altitude range 11

3.3.2 Altitude accuracy 12

3.3.2.1 Short term drift 12

3.3.3 System sensitivity 12

3.3.4 Self test provisions 12

3.3.4.1 IRT 12

3.3.4.2 RT 12

3.3.5 Transmitter frequency 13

3.3.6 Track rate 13

3.3.7 Search rate 13

3.3.8 Transmitter power 13

3.3.9 Output protection 13

3.3.10 Multiple indicator protection 13

3.3.11 Installation delay adjustment 13

3.3.12 Altitude memory 13

3.3.13 Data lag 13

3.3.14 Display function (IRT only) 13

3.3.14.1 Lighting 13

3.3.14.1.1 Integral lighting 14

3.3.14.1.2 LED(s) 14

3.3.14.1.3 Hi/Lo warning lamps 14

3.3.14.1.4 Dimming 14

3.3.14.2 Display 14

3.3.14.3 Minus command 14

3.3.15 Power failure and power off display functions 14

3.3.16 Altitude voice warning system (AVWS) 14

3.3.16.1 AVWS operation 15

3.3.16.1.1 IRT 15

3.3.16.1.2 RT 15

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3.3.17 Interface 16

3.3.17.1 IRT 16

3.3.17.2 RT 16

3.3.18 Pitch/rol 16

3.3.19 Interchangeability 16

3.3.20 Compatibility 16

3.4 Mechanical requirements 16

3.4.1 Weight 16

3.4.1.1 IRT 16

3.4.1.2 RT 16

3.4.2 Dimension 16

3.4.2.1 IRT 16

3.4.2.2 RT 16

3.4.3 Indicator display (IRT only) 16

3.4.3.1 Display fogging (IRT only) 16

3.4.4 Controls (IRT only) 16

3.4.4.1 Lo trip knob 16

3.4.4.2 Hi trip knob 16

3.4.4.2.1 Hi altitude 16

3.4.4.2.2 PTT 16

3.4.4.2.3 Mute 17

3.4.5 Finish, protective 17

3.5 Electrical signal output characteristics. 17

3.5.1 Transmitter output (J4) 17

3.5.2 Remote analog altitude signal (J2-2) 17

3.5.3 Auxiliary altitude outputs (J2-3) 17

3.5.4 Reliability signal (J1-12, J2-6) 17

3.5.5 High altitude and low altitude trip (lamps) (IRT only) 18

3.5.5.1 Low altitude warning signal (J1-1) 18

3.5.5.2 High altitude warning signal (J1-2) 18

3.5.6 Digital altitude (J2-12, J2-10) 19

3.5.6.1 Minus command (IRT only) 19

3.5.7 Enable pulse (J2-4, J2-1) 19

3.5.8 Blanking pulse (J1-6) 19

3.5.9 Self test confidence signal (J2-13) 20

3.5.10 Altitude voice warning output (J2-7) 20

3.5.10.1 AVWS operation 20

3.5.10.1.1 IRT 20

3.5.10.1.2 RT 21

3.5.10.2 AVWS reaction time 21

3.5.10.3 Mute-PTT input 21

3.5.10.4 Volume adjust 21

3.5.10.5 Calibration message 21

3.6 Electrical signal input characteristics 22

3.6.1 RF received signal (J3) 22

3.6.2 PRF inhibit signal (J1-13) 22

3.6.3 Mute-PTT (J2-18) 22

3.6.4 Simulated T-zero signal (J1-8) 22

3.6.5 Simulated T-x pulse (J1-11) 22

3.6.6 Dim control (J1-7) (IRT only) 22

3.6.7 Power on control (J2-5) 23

3.6.8 Integral lighting (J1-10 and J1-5) (IRT only) 23

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3.6.9 High altitude and low altitude trip (RT only) 23

3.6.9.1 Low altitude warning signal (J1-1) 23

3.6.9.2 High altitude warning signal (J1-2) 23

3.7 Environmental requirements 23

3.7.1 Temperature-Altitude 23

3.7.2 Humidity 23

3.7.3 Dust 23

3.7.4 Vibration 23

3.7.5 Shock 23

3.7.5.1 Bench handling 23

3.7.5.2 Basic 24

3.7.5.3 Crash safety 24

3.7.6 Fungus 24

3.7.7 Salt fog 24

3.7.8 Explosive atmosphere 24

3.7.9 Acceleration 24

3.7.10 Rain 24

3.7.11 Reliability 24

3.7.11.1 IRT 24

3.7.11.2 RT 24

3.8 Electromagnetic interference 24

3.8.1 Power lead conducted emission (30 Hz to 50 KHz) method CE01 24

3.8.2 Signal lead conducted emission (30 Hz to 50 KHZ) method CE03 25

3.8.3 Conducted emission, power and signal leads (50 KHz to 50 MHz) methods CE04 and CE05 25

3.8.4 Power lead conducted susceptibility (30 Hz to 50 KHz) method CS01 25

3.8.5 Power lead conducted RF susceptibility (50 KHz to 400 MHz) method CS02 25

3.8.6 Conducted susceptibility intermodulation (430 MHz to 10 GHz) method CS03 25

3.8.7 Conducted susceptibility, rejection of undesired signals (3 KHz to 10 GHz) method CS04 25

3.8.8 Conducted susceptibility, power lead spike method CS06 25

3.8.9 Radiated emission, electric field (14 KHz to 10 GHz) method RE02 and RE02.1 26

3.8.10 Transmitter spurious and harmonic emission method RE03 26

3.8.11 Radiated susceptibility, magnetic induction field spike method RS02 26

3.8.12 Electric field radiated susceptibility (14 KHz to 12.4 GHz) method RS03.2 26

3.9 Manufacturing 26

3.9.1 Marking 26

3.9.2 Workmanship 27

3.10 Calibration 27

4.0 QUALITY CONFORMANCE INSPECTION OF EQUIPMENT BEFORE PACKAGING 27

4.1 Quality assurance provisions 27

4.1.1 Responsibility for inspection 27

4.1.2 Classification of inspection 27

4.1.3 First article 27

4.1.3.1 First article 27

4.1.3.2 First article inspection 27

4.1.3.3 First article data 27

4.1.4 Inspection covered by subsidiary documents 28

4.2 Group A, B, C, and D description 28

4.2.1 Group A inspection 28

4.2.1.1 Order of inspection within group A 31

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4.2.2 Group B inspection 32

4.2.2.1 Order of inspection within group B 32

4.2.2.2 Sampling for group B inspection 32

4.2.2.2.1 IRT 32

4.2.2.2.2 RT 32

4.2.2.2.3 IRT and RT 32

4.2.3 Group C inspection 34

4.2.3.1 Order of inspection within group C 34

4.2.3.2 Sampling for group C inspection 34

4.2.3.2.2 Subgroup I 36

4.2.3.2.2.1 IRT 36

4.2.3.2.2.2 RT 36

4.2.3.2.2.3 IRT and RT 36

4.2.3.2.3 Subgroup II 36

4.2.3.2.3.1 IRT 36

4.2.3.2.3.2 RT 36

4.2.3.2.3.3 IRT and RT 36

4.2.3.2.4 Subgroup III 36

4.2.3.2.4.1 IRT 36

4.2.3.2.4.2 RT 36

4.2.3.2.1.3 IRT and RT 36

4.2.3.3 Non-compliance 36

4.2.3.4 Re-inspection of conforming group C sample 36

4.2.4 Group D inspection 37

4.2.4.1 Sampling for group D inspection 37

4.2.4.2 Group D failures 37

4.2.4.3 Reliability testing 37

4.2.4.3.1 Conditions precedent to reliability testing 37

4.2.4.3.2 Reliability test conditions 37

4.2.4.3.3 Failure definition 38

4.3 Test requirements 38

4.3.a IRT 38 4.3.b RT 38

4.3.1 Production run-in 38

4.3.2 Burn-in/debugging 38

4.3.3 Acceptance Test 38

4.3.4 Test conditions 38

4.4 Burn-in/debugging 39

4.4.1 Test conditions 39

4.4.2 Calibration (burn-in) 39

4.4.2.1 IRT 39

4.4.2.2 RT 39

4.4.3 Parameters to be measured 40

4.4.3.a IRT 40 4.4.3.b RT 40

4.4.3.1 Altitude range and accuracy 40

4.4.3.1.1 IRT 40

4.4.3.1.2 RT 41

4.4.3.2 System sensitivity 41

4.4.3.3 Self test 41

4.4.3.3.1 IRT 41

4.4.3.3.2 RT 41

B

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4.5 Acceptance tests (IRT only) 42

4.5.1 Altitude accuracy 42

4.5.2 System sensitivity 43

4.5.3 Self test 43

4.5.4 Display function 43

4.5.5 AVWS output 44

4.5.6 High-low altitude trips 46

4.5.6.1 High altitude trip 46

4.5.6.2 Low altitude trip 46

4.5.7 Power failure - output signals 46

4.5.8 Unreliable conditions - output signals 47

4.5.9 Integral lighting 47

4.5.10 Visual and mechanical 47

4.6 Acceptance tests (RT only) 47

4.6.1 Altitude accuracy 47

4.6.2 System sensitivity 48

4.6.3 Self test 48

4.6.4 AVWS output 48

4.6.5 Power failure - output signals 50

4.6.6 Unreliable conditions - output signals 50

4.6.7 Visual and mechanical 50

4.7 Quality conformance inspection of packaging 50

5.0 RESERVED 50

6.0 NOTES 50

6.1 Acronyms 50

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TABLE OF TABLES

TABLE DESCRIPTION PAGE

Ia Interface summary for IRT 29 Ib Interface summary for RT 30 IIa Group A inspection for IRT 31 IIb Group A inspection for RT 32 IIIa Group B inspection for IRT 33 IIIb Group B inspection for RT 33 IVa Group C inspection for IRT 34 IVb Group C inspection for RT 35 V Group D inspection 37 VI Analog and digital readings requirements for IRT 42 VII Test conditions for IRT 43 VIII Test indications for test conditions for IRT 44 IX AVWS for IRT 45 X Analog and digital output requirements for RT 48 XI AVWS for RT 49

TABLE OF FIGURES

FIGURE DESCRIPTION PAGE

1a Outline dimensions for IRT 51 1b Outline dimensions for RT 52 2 Indicator display (for IRT only) 53 3 Timing diagram - in track 54 4 Timing diagram - out of track 55 5 Test setup 56

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1.0 SCOPE

This drawing establishes the performance specification for the RT-1115J/APN-209 Receiver-

Transmitter, Height Indicator (IRT) and RT-1411B/APN-209 Receiver-Transmitter (RT). Also included are detailed acceptance test procedures for group A, B and C testing. Group A comprises acceptance testing.

1.1 General description.

1.1.1 IRT. The Receiver-Transmitter, Height Indicator (IRT) transmits a radio frequency signal, receives the reflected signal, and derives the proper signals for altitude range of 0 to at least 1500 feet. In addition, the IRT displays analog altitude, digital altitude, and high and low altitude warnings. It provides these signals along with an auxiliary analog altitude signal, a digital altitude signal, a reliability signal and a self test confidence signal. Digital altitude is indicated on a four digit lighted readout. Above 200 feet, the digital altitude is rounded to the nearest 10 feet. Movable markers positioned against the same dial shall indicate the preselected height above or below which the high and low altitude warnings operate. Unreliable operation is indicated by an "off" flag coming into view and the digital readout blanked when:

a. The signal strength to the IRT becomes inadequate to provide reliable altitude information or

b. The IRT is turned off, or

c. Aircraft power to the system is lost or

d. Aircraft altitude is above the maximum track altitude. The maximum track altitude is between

1,500 and 2,000 feet. Unreliable indications shall remain in view at altitudes above 2,000 feet.

1.1.2 RT. The Receiver-Transmitter (RT) transmits a radio frequency signal, receives the reflected signal, and derives the proper signals for altitude range of 0 to at least 1500 feet. The RT provides an auxiliary analog altitude signal, a digital altitude signal, a reliability signal and a self test confidence signal. Unreliable operation is indicated when:

a. The signal strength to the RT becomes inadequate to provide reliable altitude information or

b. The RT is turned off, or

c. Aircraft power to the system is lost or

d. Aircraft altitude is above the maximum track altitude. The maximum track altitude is between

1,500 and 2,000 feet. Unreliable indications shall remain at altitudes above 2,000 feet.

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2.0 GENERAL

2.1 Applicable documents. The following documents of exact notice are applicable to the extent described herein:

SPECIFICATIONS

MILITARY

MIL-M-13231C June 7, 1986. Marking of Electrical Items

MIL-P-15024E January 29, 1993. Plates, Tags and Bands for

Identification of Equipment

MIL-L-85762A August 26, 1988. Lighting, Aircraft, Interior, NVIS

STANDARDS

MILITARY

DOD-STD-100C Notice 6, March 15, 1988. Engineering Drawing Practices

MIL-STD-105E May 10, 1989, Sampling Procedures and Tables for

Inspection

MIL-STD-252B January 19, 1970. Classification of Visual and Mechanical

Defects

MIL-STD-461A Notice 4, February 9, 1971. Control of EMI Emission and susceptibility

MIL-STD-704D September 30, 1980, Notice 2. Aircraft Electrical Power

Characteristics

MIL-STD-781B Notice 1, July 28, 1969. Reliability Testing for

Engineering Development, Qual, and Production

MIL-STD-810E July 14, 1989. Evnironmental Test Methods and

Engineering Guidelines

MIL-STD-2000A Standard Requirements for Soldered Electrical and

Electronic Assembly

INDUSTRY

ANSI/J-STD-001(R) Requirements for Soldered Electrical and Electronic

Assemblies

ANSI/ASQC Q9001-1994 Quality Systems - Model for Quality Assurance in Design, Development, Production, Installation and Servicing

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2.2 Definitions. In the following sections a TTL positive pulse is defined as a pulse which transistions from low to high for the pulse width then returns low. A TTL negative pulse is a pulse which transitions from high to low for the pulse width then returns high. A TTL high or “1” is defined as a voltage between +2.5 and +5.0 VDC. A TTL low or “0” is defined as a voltage between 0.0 and +0.8 VDC. Pulse widths are measured at the 50% points unless otherwise specified. Rise and fall times are from the 10% to 90% points unless otherwise specified.

2.3 Test equipment.

2.3.1 Standard (commercial) test equipment. All commercial instrumentation listed below shall have a tolerance of 20% or less of the tolerance of the reading to be observed.

Oscilloscope, Tektronix 2465 or equivalent Voltmeter DC, Fluke 8300A or equivalent Power supply Trygon HR40-2.5 or equivalent Ammeter DC HP428B or equivalent

2.3.2 Special test equipment. All special test equipment shall be fabricated by the testing activity to provide the required inputs and outputs.

3.0 REQUIREMENTS

3.1 Power input.

3.1.1 Power input summary.

3.1.1.1 IRT. Power input shall be have the following general characteristics:

Pin Range Current +28 VDC Pwr In J1-9 +22.0 to +30.0 1.1 A (max) Power Ground J1-3 Power On Control J2-5 +22.0 to +30.0 20 mA (max) Integral Lighting J1-10, 5 5V 0.5A (max)

Operating power shall be 1.1 amperes maximum at 27.5 VDC at J1-9. The IRT shall meet the performance as specified herein when energized from a power source having characteristics as defined in MIL-STD-704, Notice 2, for Category B utilization equipment. Steady-state DC voltage limits of operation shall be as specified in MIL-STD-704, Notice 2, table II for normal, abnormal and landing modes of electric system operation. Reduced system performance is acceptable for emergency electrical system operation. If conflicts arise between the requirements of MIL-STD- 704 and MIL-STD-461, Notice 4, the requirements of MIL-STD-461, Notice 4 shall apply.

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3.1.1.2 RT. Power input shall be have the following general characteristics:

Pin Range Current +28 VDC Pwr In J1-9 +22.0 to +30.0 0.8 A (max) Power Ground J1-3 Power On Control J2-5 +22.0 to +30.0 20 mA (max)

Operating power shall be 0.8 amperes maximum at 27.5 VDC at J1-9. The RT shall meet the performance as specified herein when energized from a power source having characteristics as defined in MIL-STD-704, Notice 2, for Category B utilization equipment. Steady-state DC voltage limits of operation shall be as specified in MIL-STD-704, Notice 2, table II for normal, abnormal and landing modes of electric system operation. Reduced system performance is acceptable for emergency electrical system operation. If conflicts arise between the requirements of MIL-STD- 704 and MIL-STD-461, Notice 4, the requirements of MIL-STD-461, Notice 4 shall apply.

3.1.2 Integral lighting power (IRT only). Input current for the IRT’s indicator integral lighting shall not exceed 0.5 ampere at 5 VAC or VDC per indicator.

3.1.3 Dimming control power (IRT only). Input current for controlling the dimming (J1-7) of the IRT digital display and warning lamps shall not exceed 6 mA at 27.5 VDC per indicator.

3.1.4 Power on control. Input current for the Power On Control (i.e. the device on/off switch) (J2-5) shall not exceed 20 mA.

3.1.5 Transient spike voltages. The IRT and RT shall show no degradation in performance after being subjected to a transient spike voltage of 600 volts in magnitude and 10 microseconds duration;

decreasing linearly from + 600V to +200V and -600V to -170V, in 40 microseconds; decreasing linearly from +200V to +70 and -170V to +7v in 400 microseconds; and remaining at these levels for 9.5 milliseconds. This spike shall occur at least 60 times within one hour.

3.2 System constraints.

3.2.1 Antenna isolation. Isolation between transmit and receive antennas shall be > 85 dB excluding cable loss. Antennas are typically mounted 24 to 36 inches apart, H plane coupled, and free from obstructions in the antenna beam width. If spacing between antennas exceeds 1.5 times the mean center height above ground there may be degradation of system performance on the ground and at low altitudes (below 10 feet).

3.2.2 RF cables. A double shielded RF cable is required for each antenna. The RF cables shall be type

RG-142B or equivalent. Cable length shall be kept to a minimum.

3.3 Performance requirements. Unless otherwise specified, the IRT and RT shall be capable of meeting the following requirements.

3.3.1 Altitude range. The IRT and RT shall accurately indicate absolute altitude from 0 to at least 1,500 feet over all types of terrain surfaces, such as trees, foliage, deep snow, ice, land and water. The altimeter shall provide a digital output from 0 to at least 1,500 feet, and an analog output from 0 to at least 1,500 feet. The maximum altitude range to track shall not exceed 2,000 feet and is typically 1,750 feet. The “off flag” of the IRT shall be visible above 2,000 feet.

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3.3.2 Altitude accuracy. The accuracy of the output altitude signals from 0 to 1,500 feet shall be as follows:

Output Accuracy Temperature range Altitude range

Digital (3 feet +3%) (6 feet +3%)

-40C to +55C -55C to -41C; +56C to +71C

0 - 1,500 feet

Analog display on indicator (IRT only) greater of 2 feet or 2% of Rmt* greater of 10 feet or 2% of Rmt*

-55C to +71C -55C to +71C

0 - 200 feet 201 - 1,500 feet

Aux and Rmt* (3 feet +3%) (6 feet +3%)

-40C to +55C -55C to -41C; +56C to +71C

* Aux = Auxilary Analog Altitude

* Rmt = Romote Analog Altitude

3.3.2.1 Short term drift. After initial warm up of at least 2 minutes, the short term drift of the digital altitude at any constant temperature within the stated environmental requirements shall not exceed 2 feet within 15 minutes for altitude range between 0 and 200 feet.

3.3.3 System sensitivity. Minimum far range system sensitivity shall be 119 dB between the temperatures of 0°C and 40°C or 117 dB at all other temperatures. System sensitivity at 0 feet shall be 78 5 dB over the temperature range of 0C and 40C, and 78

7 dB of all other temperatures.

3.3.4 Self test provisions.

3.3.4.1 IRT. A self test shall be incorporated. This shall be used for inflight and preflight testing of the IRT.

Self test shall be activated by depressing the control knob on the indicator for at least 1.5 second and shall be capable of being energized continuously with no performance degradation to the IRT.

Whenever self test is activated, the indicator display and altitude output shall indicate an altitude of 1000 ± 100 feet. The self test function shall also be capable of being performed remotely by grounding or applying a TTL low to J2-8 for at least 1.5 second. A self test confidence output on J2-13 shall be provided if the self test acceptance criteria has been met during the self test operation. Antenna leakage is used for self test. If antenna leakage exceeds 110 dB, the self test function may not be operational.

The self test input on J2-8, called Mute-PTT, also functions as volume control for AVWS.

Reference paragraph 3.3.16 and 3.5.10.

3.3.4.2 RT. A self test shall be incorporated. This shall be used for inflight and preflight testing of the RT.

Self test shall be activated by applying a TTL low to J2-8 for at least 1.5 second and shall be capable of being energized continuously with no performance degradation to the RT. Whenever self test is activated and altitude outputs shall indicate an altitude of 1000 ± 100 feet. A self test confidence output on J2-13 shall be provided if the self test acceptance criteria has been met during the self test operation. Antenna leakage is used for self test. If antenna leakage exceeds 110 dB, self test function may not be operational.

The self test input on J2-8, called Mute-PTT, also functions as volume control. Reference paragraph 3.3.16 and 3.5.10.

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3.3.5 Transmitter frequency. The IRT and RT shall operate within the allocated frequency range of 4200 to 4400 MHz.

3.3.6 Track rate. The analog altitude signal (excluding the indicator display of the IRT) shall follow changes in height at rates up to at least 1000 feet/second.

3.3.7 Search rate. While in the search mode the IRT and RT shall search from zero altitude to maximum altitude at a rate of 4 0.5 times per second.

3.3.8 Transmitter power. The transmitter peak power shall not exceed +35 dBm when measured at the

J4 transmitter port. At 0 feet, transmitter peak power shall not exceed +27 dBm.

3.3.9 Output protection. Protection circuitry shall be included in the system, both receivers and transmitters, to prevent damage due to accidental short-circuits or open-circuits of the electrical signal outputs (remote indicator outputs, auxiliary outputs, relay closures, etc.), and the RF signals.

3.3.10 Multiple indicator protection. When more than one indicator is used, the user shall provide isolation between indicators to prevent a short-circuit to ground or incorrect voltage on one indicator from affecting other indicators.

3.3.11 Installation delay adjustment. The analog and digital altitudes shall be adjustable externally to allow for an aircraft installation delay from 1 to 70 feet. (Installation delay includes antenna height above ground, antenna separation, and for RF coaxial cable lengths.)

3.3.12 Altitude memory. All "in track" outputs shall be maintained for 1.8 0.5 seconds after loss of return signal before reverting to the out of track mode.

3.3.13 Data lag. Electrical analog data from the IRT and RT shall not lag any simulated or actual altitude by more than 0.2 second when tracking at an altitude rate change up to 1000 feet per second.

This requirement does not pertain to the digital altitude signal in as much as the digital data is averaged over a period of 0.44 second.

3.3.14 Display function (IRT only).

3.3.14.1 Lighting. Indicator lighting shall meet MIL-L-85762 as modified below.

Lighting Source Integral LEDs Warning Lamps Color NVIS Green A NVIS Green B* NVIS Yellow NVIS Radiance (max) 1.7x10-10** 1.7x10-10 1.5x10-7 Sunlight Reliability N/A 10,000 FC 10,000 FC

* Chromaticity requirements are not critical provided NVIS radiance requirement is met.

** This value is a design goal; slightly higher radiance values may be accepted.

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3.3.14.1.1 Integral lighting. The IRT background shall be internally lighted as defined in 3.3.14.

3.3.14.1.2 LED(s). The indicator shall have four LED(s) to display digital altitude. The display shall have the following characteristics.

Color: Reference 3.3.14 Max altitude: 1999 feet Min altitude: 0 feet Minus comm: Indicater “-” in the 1,000 digit when below zero feet Size: Reference figure 2

3.3.14.1.3 Hi/Lo warning lamps. A separate lamp for Hi warning and Lo warning shall be as defined in 3.3.14.

3.3.14.1.4 Dimming. Dimming of the digital display and warning lamps shall be controlled separately from the dial lighting (integral lighting). The dimming voltage shall be 0 to 27.5 VDC. The digital display shall be dimmable from full brightness with 27.5 VDC input to full off with 5 VDC or less input. The warning lamps shall be dimmable from full brightness with 27.5 VDC input to a level visible only with night vision devices such as AN/PVS-5. An AN/PVS-5 will be furnished as government loaned property.

3.3.14.2 Display. Digital altitude shall be indicated on a four digit lighted readout. Above 200 feet, the digital altitude shall be rounded to the nearest 10 feet. Analog altittude shall be indicated from 0 to 1500 feet by means of a single pointer against a fixed dial. Movable markers positioned against the same dial shall indicate the pre-selected height above or below which the high and low altitude warnings operate. Unreliable operation shall be indicated by an “OFF” flag coming into view, the pointer shall go behind the masked portion of the indicator dial and the digital readout and the high and low warning lamps blanked when:

a. The signal strength to the IRT becomes inadequate to provide reliable altitude information or

b. Aircraft altitude is between 1500 and 2000 feet. (Unreliable indicators shall remain in view at altitudes above 2000 feet.)

3.3.14.3 Minus command. Refer to paragraph 3.5.6.

3.3.15 Power failure and power off display functions. An unreliable operation indication shall occur when

28 VDC power to the system is lost, except that the pointer need not go behind the masked portion of the indicator dial.

3.3.16 Altitude voice warning system (AVWS). The voice output signal on J2-7 and referenced to signal ground shall be either one of five different messages or no message. The five messages are:

a. ALTITUDE HIGH, CHECK ALTITUDE with compression for full volume.

b. ALTITUDE HIGH, CHECK ALTITUDE 50% volume no compression (i.e. “soft”).

c. ALTITUDE LOW, TOO LOW with compression for full volume.

d. ALTITUDE LOW, TOO LOW 50% volume no compression (i.e. “soft”).

e. 1 KHz tone used for calibration.

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3.3.16.1 AVWS operation.

3.3.16.1.1 IRT. When flying inside the altitude warning presets (i.e. HI and LO warning both off), no message shall be issued. Upon transition from inside to outside (one warning on) the altitude warning presets, the appropriate full volume message will be issued. After issuance, a 10 1 second pause shall occur before message repeat if the aircraft remains outside an altitude warning preset.

An excursion inside then outside during the 10 1 second pause is ignored. The status of the warning is read at the end of each 10 1 second pause. An excurion from one warning to the other warning during the 10 1 second pause pulse causes the other warning’s full volume message to be issued immediately.

A soft volume/no volume mode is controlled by a volume activation. A volume activation is the TTL low activation of the Mute-PTT input of duration of less than 500 50 msec and longer than 50 msec. When in high volume, activation of Mute-PTT reduces the volume of the next message. A second and subsequent volume activation of Mute-PTT reduces volume to zero. A 10 1 second pause is still active with zero volume.

AVWS is reinitialized 10 1 seconds after the end of last message (including volume zero) and the aircraft is brought inside altitude warning presets.

Upon IRT power up, altitude indication must be brought inside the preset to initialize AVWS.

NOTE: Volume control can only occur during the 10 1 second part of a message.

3.3.16.1.2 RT. A remote indicator is required to provide HI and LO warning inputs to the RT for AVWS operation. When flying inside the altitude warning presets (i.e. HI and LO warning both off), no message shall be issued. Upon transition from inside to outside (one warning on) the altitude warning presets, the appropriate full volume message will be issued. After issuance, a 10 1 second pause shall occur before message repeat if the aircraft remains outside an altitude warning preset. An excursion inside then outside during the 10 1 second pause is ignored. The status of the warning is read at the end of each 10 1 second pause. An excurion from one warning to the msec. When in high volume, activation of Mute-PTT reduces the volume of the next message. A

Upon RT power up, altitude indication must be brought inside the preset to initialize AVWS.

NOTE: Volume control can only occur during the 10 1 second part of a message.

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3.3.17 Interface.

3.3.17.1 IRT. The electrical interface is summarized in table 1. Mating connectors to J1 and J2 are defined in table 1a.

3.3.17.2 RT. The electrical interface is summarized in table 1. Mating connectors to J1 and J2 are defined in table 1b.

3.3.18 Pitch/roll. Pitch and roll capability system is dependent on the antennas and RF cables as well as the IRT. With AS-3586 or AS-3831 antennas and cable loss not exceeding 6 dB, the IRT and RT shall be capable of meeting performance at up to at least 45 pitch or 45 roll.

3.3.19 Interchangeability. Like devices shall be physically and functionally interchangeable.

3.3.20 Compatibility. An IRT or RT shall operate with the ID-1917X Remote Indicator.

3.4 Mechanical requirements.

3.4.1 Weight.

3.4.1.1 IRT. The weight of IRT shall not exceed 3.9 pounds.

3.4.1.2 RT. The weight of RT shall not exceed 2.9 pounds.

3.4.2 Dimension.

3.4.2.1 IRT. Reference figure 1A for outline dimensions of the IRT.

3.4.2.2 RT. Reference figure 1B for outline dimensions of the RT.

3.4.3 Indicator display (IRT only). The indicator display shall display altitude via 4 LED(s) (i.e. “digital altitude”) and via a pointer. The pointer scaling is two tiered. Figure 2 shows the layout of the IRT’s indicator.

3.4.3.1 Display fogging (IRT only). The indicator display shall not exhibit fogging which impacts readability) during normal use.

3.4.4 Controls (IRT only). All movable controls shall operate properly without binding or other undue restriction. Controls shall not be assembled in a misaligned condition.

3.4.4.1 Lo trip knob. The lo altitude trip knob shall control the low altitude position marker positioned on the perimeter of the dial. The marker shall be adjustable from 0 to at least 1,500 feet. The knob shall also control on/off to the IRT. When the marker is well below zero feet, the IRT shall be off.

3.4.4.2 Hi trip knob. The hi altitude trip knob shall have three functions: Hi altitude trip, PTT, and mute.

3.4.4.2.1 Hi altitude. The hi altitude trip knob shall control the hi altitude position marker positioned on the perimeter of the dial. The marker shall be adjustable from 0 to at least 1,500 feet.

3.4.4.2.2 PTT. Depressing the hi altitude knob for at least 1.5 seconds places the IRT in the self-test mode.

C

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3.4.4.2.3 Mute. Depressing the hi altitude knob once for greater than 50 msec and less than 500 50 msec is a single activation of volume control.The electrical interface is summarized in table 1. Mating connectors to J1 and J2 are defined in table 1a.

3.4.5 Finish, protective. The IRT and RT shall be given protective finish. This includes finish of hardware, such as screws, etc., and necessary touch-up after mounting. The bezel of the IRT shall be black.

3.5 Electrical signal output characteristics.

3.5.1 Transmitter output (J4). The RF output at the transmitter port (J4) shall have the following characteristics:

Spec Nominal Pulse width at 0 feet <100 nsec 25 nsec at 1000 feet <200 nsec 90 nsec Peak power, max at 0 feet 27 dBm 25 dBm at 1000 feet 38.5 dBm 31 dBm

Pulse repetition frequency 18

4 KHz 18 3 KHz

Center frequency 4.300 0.100 GHz 4.300 GHz Impedance 50 50

The J4 connector is type TNC female.

3.5.2 Remote analog altitude signal (J2-2). The IRT and RT shall provide an isolated analog DC voltage proportional to altitude to drive its internal indicator and also a remote indicator on J2-2. The signal at J2-2 shall be 0 to -10.5 VDC representing 0 to 1,500 feet respectively. During no-track or unreliable operation, J2-2 shall be -13 ± 2 VDC. Output impedance shall be less than 10 ohms.

J2-2 shall be capable of driving a load of 10,000 ohms or more.

3.5.3 Auxiliary altitude outputs (J2-3). The IRT and RT shall provide an analog DC voltage proportional to altitude on J2-2. J2-3 shall be 0 to -10.5 VDC representing 0 to 1500 feet respectively. During no-track or unreliable conditions J2-3 shall be +0.75 ± 0.5 VDC and shall be capable of driving a load of 2000 ohms or more.

3.5.4 Reliability signal (J1-12, J2-6). The IRT and RT shall provide a TTL logic compatible reliability signal at J1-12 and J2-6 of 4.5 ± 1.0 VDC during track or reliable operation and 0.5 ± 0.5 VDC during search or unreliable system operation. Load impedance, if other than TTL logic, shall be greater than 5000 ohms.

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3.5.5 High altitude and low altitude trip (lamps) (IRT only). The LO warning lamp shall be on when the indicated altitude is below the LO set bug and off when the indicated altitude is above the LO set bug. When descending, actuation of the warning shall occur when the indicated altitude is within

50 feet between 1500 feet and 200 feet or

5 feet less than 200 feet) or

5 percent whichever is greater of the selected warning altitude. Below 200 feet when ascending, deactivation of the warning shall occur when the indicated altitude is within 7 feet or 5 percent of the selected warning altitude, whichever is greater, above the point of activation of the warning. Above 200 feet when ascending deactivation of the warning shall occur when the indicated altitude is within 70 feet or 5 percent of the selected warning altitude, whichever is greater, above the point of activation of the warning.

The HI warning lamp shall be on when the indicated altitude is above the HI set bug and off when the indicated altitude is below the HI set bug. When ascending, actuation of the warning shall occur when the indicated altitude is within (

2 feet between 0 and 200 feet or

20 feet above 200 feet) or

2 percent whichever is greater of the selected warning altitude. Below 200 feet when descending, deactivation of the warning shall occur when the indicated altitude is within 7 feet or 5 percent of the selected warning altitude, whichever is greater, below the point of activation of the warning. Above 200 feet when descending, deactivation of the warning shall occur when the indicated altitude is within 70 feet or 5 percent of the selected warning altitude, whichever is greater, below the point of activation of the warning.

3.5.5.1 Low altitude warning signal (J1-1). The low altitude warning function shall be activated when the actual altitude displayed is at or below the pilot adjustable low altitude limit setting. The output at J1-1 shall be controlled by the collector of a common emitter NPN transistor switch. The transistor shall be on when the warning is activated and off when there is no warning. The transistor shall have a maximum voltage of 1.2 volts and be capable of sinking 80 milliamperes from a DC voltage source of up to 50 volts when on. When off, the output shall be an open collector and capable of withstanding 50 VDC. In series with J1-1 and the transistor is a diode.

3.5.5.2 High altitude warning signal (J1-2). The high altitude warning function shall be activated when the actual altitude displayed is at or above the pilot adjustable high altitude limit setting. The output at J1-2 shall be controlled by the collector of a common emitter NPN transistor switch. The transistor shall be on when the warning is activated and off when there is no warning. The transistor shall have a maximum voltage of 1.2 volts and be capable of sinking 80 milliamperes from a DC voltage source of up to 50 volts when on. When off, the output shall be an open collector capable of withstanding 50 VDC. In series with J1-2 and the transistor is a diode.

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3.5.6 Digital altitude (J2-12, J2-10). The IRT and RT shall provide a digital altitude signal for use in a remote indicator. This signal shall be a series of pulses with each pulse equal to 1 foot of altitude.

Pulses shall be transmitted from a differential line driver (J2-12 HI and J2-10 LO) and shall have the following characteristics:

Signal Description Pulse width: 100 nanoseconds minimum Rise time: 50 nanoseconds maximum Fall time: 50 nanoseconds maximum Amplitude: 1.6 volts minimum, differential Frequency: 150 kHz maximum

Reference figures 3 and 4 for digital altitude information and timing diagram during track and search conditions.

3.5.6.1 Minus command (IRT only). When digital altitude is less than zero feet, a minus sign shall be observed on the 1000’s digit of the IRT’s indicator display.

3.5.7 Enable pulse (J2-4, J2-1). The IRT and RT shall provide an enable pulse during the time that the digital altitude pulses are being transmitted. The pulse shall be transmitted from a differential line driver (J2-4 HI and J2-1 LO) and shall have the following characteristics:

Lead time: 15 microseconds minimum Lag time: 75 microseconds maximum Rise time: 50 nanoseconds maximum Fall time: 50 nanoseconds maximum Amplitude: 1.6 volts minimum, differential Width: 0.20 ± 0.06 seconds Frequency: 2.7 ± .8 Hz

Reference figures 3 and 4 for digital altitude information and timing diagram during track and search conditions.

3.5.8 Blanking pulse (J1-6). The IRT and RT shall provide a blanking pulse for external use to indicate when the IRT is transmitting an RF pulse. The blanking pulse on J1-6 shall when driving a 1000 ohm load have the following characteristics:

Pulse width (not during PTT): 0.9 ± 0.3 microseconds Pulse width (during PTT): 3.0 ± 0.6 microseconds Rise time: 0.5 microsecond maximum Fall time: 0.5 microsecond maximum Amplitude: 6.0 ± 0.75 volts Baseline: 0.0 0.5 VDC Frequency average: 18 ± 4, -6 KHz

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3.5.9 Self test confidence signal (J2-13). The self test confidence signal on J2-13 shall be 4.5 ± 1.0 VDC when the Mute-PTT signal on J2-8 is at ground or a TTL low and the auxiliary analog signal on J2- 3 and remote analog signal on J2-2 is between -6.50 0.20 and -7.50 0.20 VDC. If the Mute- PTT is not at a TTL low or if either analog signal is not between -6.50 0.20 and -7.50 0.20 VDC, the self test confidence signal shall be 0.0 ± 0.5 VDC.

Application of +28 VDC thru a 5.11K ohm series resistor to J2-13 during a valid PTT shall activate the calibration message.

3.5.10 Altitude voice warning output (J2-7). The voice output signal on J2-7 and referenced to signal ground shall be either one of five different messages or no message. The five messages are:

a. ALTITUDE HIGH, CHECK ALTITUDE with compression for full volume.

b. ALTITUDE HIGH, CHECK ALTITUDE 50% volume no compression (i.e. “soft”).

c. ALTITUDE LOW, TOO LOW with compression for full volume.

d. ALTITUDE LOW, TOO LOW 50% volume no compression (i.e. “soft”).

e. 1 KHz tone used for calibration.

3.5.10.1 AVWS operation.

3.5.10.1.1 IRT. When flying inside the altitude warning presets (i.e. HI and LO warning both off), no message shall be issued. Upon transition from inside to outside (one warning on) the altitude warning presets, the appropriate full volume message will be issued. After issuance, a 10 1 second pause shall occur before message repeat if the aircraft remains outside an altitude warning preset.

An excursion inside then outside during the 10 1 second pause is ignored. The status of the warning is read at the end of each 10 1 second pause. An excurion from one warning to the msec. When in high volume, activation of Mute-PTT reduces the volume of the next message. A

Upon IRT power up, altitude indication must be brought inside the preset to initialize AVWS.

NOTE: Volume control can only occur during the 10 1 second part of a message.

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3.5.10.1.2 RT. A remote indicator is required to provide HI and LO warning inputs to the RT for AVWS operation. When flying inside the altitude warning presets (i.e. HI and LO warning both off), no message shall be issued. Upon transition from inside to outside (one warning on) the altitude warning presets, the appropriate full volume message will be issued. After issuance, a 10 1 second pause shall occur before message repeat if the aircraft remains outside an altitude warning preset. An excursion inside then outside during the 10 1 second pause is ignored. The status of the warning is read at the end of each 10 1 second pause. An excurion from one warning to the msec. When in high volume, activation of Mute-PTT reduces the volume of the next message. A

Upon RT power up, altitude indication must be brought inside the preset to initialize AVWS.

NOTE: Volume control can only occur during the 10 1 second part of a message.

3.5.10.2 AVWS reaction time. AVWS reaction time (total elapsed time from receipt of input to initiation of full volume message) shall be less than 0.1 seconds.

3.5.10.3 Mute-PTT input. Activation of Mute-PTT input (J2-8) to a TTL low or signal ground for a duration of less than 500 50 msec and longer than 50 msec shall only change volume. Activation of Mute- PTT input for more than 500 50 msec shall only place the IRT or RT into PTT. A TTL high or open circuit (impedance to ground greater than 10 megohms) allows normal operation. The ground or TTL low shall be capable of sinking 10 milliamps.

3.5.10.4 Volume adjust. Volume adjust shall be performed by an external adjustment potentiometer through the volume adjust access hole in the IRT and RT case. As measured in the calibration message, the volume shall be factory adjusted to 0.90 0.25 VRMS into a 150 10 ohm load.

As measured during the calibration message, the maximum adjustable range of the volume shall be 3.00 0.50 VRMS into a 150 10 ohm load.

3.5.10.5 Calibration message. The calibration message shall be a 1 KHz tone of duration 10 1 second with 10 1 second pauses following. The calibration message is intended for bench use and is initiated by:

a. Placing the IRT or RT into a valid PTT (i.e. self test confidence active as a TTL high).

b. Applying +28 VDC thru a 5.11K ohm resistor to self test confidence output (J2-13).

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3.6 Electrical signal input characteristics.

3.6.1 RF received signal (J3). The RF received signal applied to the receiver input port J3 is the transmitted RF pulse which is delayed and attenuated as a function of altitude. The delay represents the time of travel of the RF pulse from the transmitter TNC port to the receiver TNC port. The maximum peak signal strength applied to J3 shall not exceed +10 dBm. The J3 connector is type TNC female.

3.6.2 PRF inhibit signal (J1-13). A TTL low or ground applied to J1-13 inhibits the transmitter. A TTL high or open circuit (impedance to ground greater than 10 megohms) allows normal transmitter operation. The ground or TTL low shall be capable of sinking 10 milliamps.

3.6.3 Mute-PTT (J2-18). A TTL low or ground applied to J2-8 for more than 500 50 msec places the

IRT in the self test mode after 500 50 msec. A TTL high or open circuit (impedance greater than 10 megohms) allows normal IRT operation. The TTL low or ground shall be capable of sinking 10 milliamps.

A TTL low or ground applied for a duration of less than 500 50 msec and more than 50 msec shall be a volume activation.

3.6.4 Simulated T-zero signal (J1-8). A test only signal. A negative going TTL pulse applied to J1-8 which is used to simulate altitude. J1-8 starts the IRT timing. J1-8 shall have the following characteristics:

Signal Description Polarity: negative going, TTL Pulse width: 100 50 nsec Rise time: 20 nsec (max) Fall time: 20 nsec (max) Frequency: 36.0 3.0 KHz

3.6.5 Simulated T-x pulse (J1-11). A test only signal. A negative going TTL pulse applied to J1-11 which is used to simulate altitude. J1-11 fires the transmitter and is synchronous with J1-8. J1-11 shall have the following characteristics:

Polarity: negative going, TTL Pulse width: -800 4500 nsec Rise time: 20 nsec (max) Fall time: 20 nsec (max) Frequency: 36.0 3.0 KHz

3.6.6 Dim control (J1-7) (IRT only). A voltage applied to J1-7 in accordance with paragraph 3.2.3 that can be varied from 0 to +28 VDC. This signal is a variable DC voltage of 0 to +27.5 VDC, present at J1-30, which controls the brightness of the indicator LED(s) and warning lamps by adjusting the duty cycle of pulse modulation. A lower voltage corresponds to a lower brightness. Below +5.0 VDC, the lamps and LED(s) should be completely off. Above +22.0 1.0 VDC, the lamps and LED(s) shall be at full brightness.

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3.6.7 Power on control (J2-5). +25 ± 5 VDC applied to J2-5 in according to paragraph 3.2.4 allows IRT and RT operation. An open circuit at J2-5 turns the IRT and RT off. The IRT shall also be turned on when the LO set knob on the indicator is rotated to position the LO warning index at or above zero feet or whenever the signal is +25 5 VDC even though the power control knob on the indicator is off.

3.6.8 Integral lighting (J1-10 and J1-5) (IRT only). 5.0 ± 0.1 VAC or VDC applied between J1-10 and J1-

5 in accordance with paragraph 3.2.2.

3.6.9 High altitude and low altitude trip (RT only).

3.6.9.1 Low altitude warning signal (J1-1). The low altitude warning function shall be activated (a low state) when the Remote Indicator’s actual altitude displayed is at or below the pilot adjustable low altitude limit setting. When off, the input shall be an open collector.

3.6.9.2 High altitude warning signal (J1-2). The high altitude warning function shall be activated (a low state) when the Remote Indicator’s actual altitude displayed is at or above the pilot adjustable high altitude limit setting. When off, the input shall be an open collector.

3.7 Environmental requirements. The IRT and RT shall meet the following MIL-STD-810E service conditions:

3.7.1 Temperature-Altitude. The IRT and RT shall be subjected to and meet the temperature-altitude requirements when non-operating from -54C through +100C at sea level to 30,000 feet. The IRT and RT shall be operable and conforming to limits specified from -40C through +75C at sea level to 30,000 feet with the exception that the accuracy may degrade to (6.5 feet + 3% of altitude) in the temperature range of +55C to +75C. Operation shall be intermittent over the temperature range of +55C to +75C. No damage shall result from exposure to temperatures in the range of

-54C to +100C and pressures from sea level to 30,000 feet. Test conditions shall be as specified in method 520.1, procedure 3.

3.7.2 Humidity. The IRT and RT shall withstand up to 100 percent relative humidity including conditions wherein condensation takes place in the form of water. When exposed to the above conditions the IRT and RT shall suffer no damage in the non-operating condition and shall meet specified performance when operated. Test conditions shall be as specified in method 507.3, procedure 3.

3.7.3 Dust. The IRT and RT shall withstand exposure to dust particles as encountered in desert areas with winds up to 17 knots. Test conditions shall be as specified in method 510.3.

3.7.4 Vibration. The IRT and RT normally mounted shall not suffer damage or fail to meet specified performance when subjected to method 514.4, category 6 at 3 hours per axis.

NOTE: This vibration is a broadband random vibration with source sine dwells.

3.7.5 Shock. The IRT and RT shall meet the conditions of method 516.4 with the specific procedure identified in the sub-paragraph.

3.7.5.1 Bench handling. The non-operating IRT and RT shall be capable of withstanding the normal bench handling of procedure 6.

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3.7.5.2 Basic. The IRT and RT shall withstand the normal shocks encountered in airplanes and helicopters as specified in procedure 1.

3.7.5.3 Crash safety. The normally mounted IRT and RT shall show no failures of the attaching points when the IRT are subjected to the level of shock encountered in a crash situation of procedure 5.

Bending and distortion is permitted.

3.7.6 Fungus. The IRT and RT shall show no evidence of viable fungus after being subjected to 28 days of fungus exposure. Test conditions shall be as specified in method 508.4.

3.7.7 Salt fog. The IRT and RT shall be capable of withstanding exposure, in normal operating configuration, to salt fog for 48 hours and shall show no evidence of corrosion as evidenced by any visible degradation that can be attributed to flaky, pitted, blistered, or otherwise loosened finish or clogging or binding of moving parts. Test conditions shall be as specified in method 509.3.

3.7.8 Explosive atmosphere. When operated in an ambient explosive mixture of gas and air the IRT and

RT shall cause no ignition. Test conditions shall be as specified in method 511.3.

3.7.9 Acceleration. The IRT and RT shall be operable without degradation in specified performance, and shall sustain no physical damage, when exposed to steady-state acceleration levels up to 6 g for one (1) minute. Test conditions shall be as specified in method 513.4.

3.7.10 Rain. The IRT and RT shall withstand a steady-state rainfall on all surfaces, meet specified performance, and sustain no physical damage. The IRT and RT with connectors covered shall be exposed to a “steady-state” rainfall of 4 1 inches per hour on all surfaces for a total time duration of not less than 2.0 hours. After completion of the rain test, the IRT and RT shall be turned on within 30 minutes and shall meet the tests required to determine compliance.