Aviation Electronics Technician 1 - Historic Naval Ships Association

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eadings are higher than actual. This error isnegligible during climbs and descent at a slow rate orafter maintaining a new altitude for a short period oftime.Absolute (Radar) AltimeterAccurate absolute altitude is important fornavigation, photography, and bombing, as well as forsafe piloting. Absolute altitude can be computed fromthe pressure altimeter readings, but the results areoften inaccurate. Under changing atmosphericconditions, corrections applied to pressure altimeterreadings to obtain true altitudes are only approximate.Also, any error made in determining the terrainelevations results in a corresponding error in theabsolute altitude.The radar altimeter, AN/APN-194(V), is a pulsed,range-tracking radar that measures the surface ofterrain clearance below the aircraft. It is reliable inthe altitude range of 20 to 5,000 feet. This altimeterdevelops its information by radiating a short durationradio frequency (RF) pulse from a transmit antennaand measuring the time interval it takes to receive thereflected signal. The altitude information is thencontinuously sent to the indicator in feet of altitude.The height indicator is disabled when the aircraft isabove 5,000 feet. When the aircraft is on the ground,the system is disabled by the weight-on-wheelsswitch.HEIGHT INDICATOR.— The AN/APN-194(V)uses the ID-1760A/APN-194(V) as its heightindicator (fig. 2-10, view A). The only operatingcontrol is in the lower left-hand corner. This controlknob is a combination power switch, self-test switch,and a positioning control for low altitude limit index(limit bug). The adjustable limit bug is set to adesired altitude for use as a reference for flying at afixed altitude. The indicator displays the altitude on asingle-turn dial that is calibrated from 0 to 5,000 feet.If the aircraft is above 5,000 feet, or the signalbecomes unreliable, the OFF flag appears and thepointer goes behind the dial mask.If you rotate the control knob clockwise, it willapply power to the system. If you continue to rotatethe knob, it will set the limit bug to the desiredreference altitude. While the aircraft is in the air, youcan close the self-test switch by pressing the controlknob. When this occurs, the indicator will read 100±10 feet. This self-test will not work on the groundFigure 2-10.-AN/APN-194(V) components. A. ID-1760A/APN-194(V). B. RT-1042/APN-194 (V), MX-9132A/APN-194(V). C. BZ-157A.2-10
ecause the system is disabled by the weighton-wheelsswitch.RECEIVER-TRANSMITTER.— This systemuses the RT-1042/APN-194(V) as its receivertransmitter(fig. 2-10, view B). It is an airtight unitthat contains all the electronic components for thegeneration, detection, and time differencecomputations of the radar pulses.There are two altitude modes of operation-onefor low level and one for high level. The low-levelmode is for altitudes less than 1,000 feet. In thismode, the RT transmits a very narrow, low-poweredpulse to get maximum range resolution. Thehigh-level mode is for altitudes above 1,000 feet. Inthis mode, the output pulse is a wider, high-poweredpulse, which ensures sufficient ground return energyfor tracking.There are two ranging modes of operation—onefor search and one for tracking. In the search mode,the system successively examines increments ofrange with each cycle of operation until the completealtitude range is searched for ground return. Whenthe range is found, the system switches to the trackmode. In the track mode, the system locks onto andtracks the leading edges of the ground return pulses.It then sends continuous altitude information to theindicator.In most aircraft with this system, there is anInterference Blanker, MX-9132A/APN-194(V),located next to the RT (fig. 2-10, view B). Thisblanker attenuates any RF from direct antennaleakage and provides isolation of the receiver fromthe transmit antenna.LOW ALTITUDE AUDIBLE ALARM.— Someof the aircraft with the APN-194(V) system have theBZ-157A low altitude audible alarm installed (fig.2-10, view C). In the EA-6A aircraft, this box is onthe ICS relay box behind the EWO’s seat. This alarmwill apply a tone to the intercommunication systemwhen the aircraft falls below the altitude that the limitbug is set. The tone is a 2-second tone alternatingbetween 700 and 1700 Hz at 2-Hz intervals. Thisalarm will also sound when there is an unreliablecondition in the system. This tone alternates between700 and 1700 Hz at 8-Hz intervals. The alarm willalso send a signal to the indicator to cause the OFFflag to appear. The unreliable condition warningsignal takes precedence over the low altitude warningsignal.The BZ-157A has three switches on it. The firstone is the volume control, which controls the volumeof the alarm. The other two are press-to-test switches.Depressing the LOW ALT switch will cause the alarmto be heard. Depressing the UNREL switch willcause the alarm to be heard and the OFF flag toappear.LOW ALTITUDE WARNING LIGHT.— Thelow altitude warning light is mounted on the pilot’sinstrument panel. This light will illuminate wheneverthe aircraft falls below the altitude that the limit bug isset.RADAR ALTIMETER WARNING SETThe radar altimeter warning set (RAWS) works inconjunction with the radar altimeter systems that donot have the BZ-157A alarm unit. The P3-C aircraftuses the AN/APQ-107 system. This system providesthe pilot and copilot with warning signals wheneverany of the following conditions exists:. Aircraft flies below preselected altitudes.. Input power to radar altimeter fails.. RAWS warning circuit indicates unreliability.When the aircraft descends to 380 (±20) feet(high-altitude index), the radar altimeter signal toRAWS is interrupted. This causes the AUTOPILOT/RADAR ALTM warning lights to flash and a 1-kHzinterrupted tone to be heard over the ICS. Bothsignals occur at a rate of two pulses-per-second for a3-second duration. This also happens as the aircraftdescends through 170 feet (low-altitude index). Thewarnings will continue as long as the aircraft remainsbelow the low index. When the nosegear is down orthe flaps are in the approach, takeoff, or landingposition, the warning signals are disabled.If the radar altimeter receiver signal is too weak toprovide reliable altitude information or the altimetermalfunctions, the RAWS will give both warnings.This occurs unless the signals are disabled by thenosegear or flap position.There are two RAWS press-to-test switcheslocated in the aircraft. One on the RAWS itself, andone on the forward load center. If you depress theswitch on the RAWS, it will actuate both signals,unless the nosewheel is down and locked-then onlythe aural warning occurs. Depressing the switch onthe forward load center results in both the visual andthe aural warnings.2-11
Page 7 and 8: PASS/FAIL ASSIGNMENT PROCEDURESIf y
Page 9: Student CommentsCourse Title:Aviati
Page 12 and 13: Table 1-1.-Radio-Frequency Spectrum
Page 14 and 15: Figure 1-3.-LS-602/AI control panel
Page 16 and 17: Figure 1-4.-Manchester encoding.thr
Page 18 and 19: they can complete a full cycle. The
Page 20 and 21: one-shot circuit output is directly
Page 22 and 23: Figure 1-7.-VHF-AM control box.Figu
Page 24: indicators in the following text. E
Page 27 and 28: Figure 1-11.-C-9245/ARC-161 control
Page 29 and 30: and the PWR/FILL switch is not in t
Page 31 and 32: panel is in OFF. If the DTS control
Page 33 and 34: the keyboard are sent directly. Rec
Page 35: the signal data converter, where it
Page 38 and 39: Navigation is both an art and a sci
Page 40 and 41: this axis at right angles to it (fi
Page 42 and 43: . Course is the intended horizontal
Page 44 and 45: The standard atmosphere is theoreti
Page 48 and 49: The barometric switch in the RAWS a
Page 50 and 51: Major ComponentsThe AN/ARN-84(V) TA
Page 52 and 53: the outputs is used for the automat
Page 54 and 55: DOPPLERIn the following text we wil
Page 57 and 58: CHAPTER 3RADARAs an avionics superv
Page 59 and 60: the antennas will stop at the posit
Page 61 and 62: AS-2146/APS-115 AntennaThe radar an
Page 63 and 64: completes the processing of radar a
Page 65 and 66: In the on-line mode, the sensor sta
Page 67 and 68: Mode SwitchThe mode switch is pract
Page 69 and 70: purpose of the horizon line is to i
Page 71 and 72: Maximum range for tracking is 40,00
Page 73 and 74: transmit a reply when RF interrogat
Page 75 and 76: airspeed-altitude computer. All fra
Page 77 and 78: SIF reply code is identical to the
Page 79: In mode 4, the reply video pulse is
Page 82 and 83: sound wave. The frequency (in hertz
Page 84 and 85: to affect the rate of travel of the
Page 86 and 87: DOPPLER EFFECTWhen there is relativ
Page 88 and 89: Figure 4-7.-Transducer installed on
Page 90 and 91: The Sonar Detecting-Range Set AN/AQ
Page 92 and 93: Figure 4-16.-RO-358/ASQ-13A.mechani
Page 94 and 95: applies 115 volts ac to the transmi
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are known as angles of dip (fig. 4-
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feet in length and represents the f
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compensation is needed for the long
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labeled ALT COMP. This switch is us
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select which signal goes to which p
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the passive directional sonobuoy (f
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REVIEW QUESTIONSQ1. How was the wor
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TACAN signals. When localizer signa
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1. The HEADING NO-GO indicator illu
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Figure 5-7.-New optical sight with
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computer’s program determines whi
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ias circuit, horizontal and vertica
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Figure 5-9.-Symbology—Continued.5
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Figure 5-14.-Sparrow mode.Figure 5-
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TACTICAL DISPLAY SYSTEM INTERFACEFi
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electrical signal, which varies in
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noise-free at that level. The impor
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Like the random interlace, this sys
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The polarity of the signal develope
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The SEC tube has applications in ex
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CHAPTER 6INFRAREDThe term infrared
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Table 6-1.-Characteristics of IR Ra
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potential difference across a PN ju
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system increases, and the reliabili
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used in the Navy, their principles
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signals from the control servomecha
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Figure 6-15.-FLIR positioning/stabi
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Figure 6-17.-Video converter video
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clamping signals from the sync gene
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shared by both azimuth and elevatio
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where they are converted into three
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go to the azimuth/elevation heat si
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TARGET TRACKING SIGHT CONTROLAs men
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control is injected in this module.
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CHAPTER 7WEAPONS SYSTEMSAs a result
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Figure 7-5.-Master light control pa
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Rocket firing systemWalleye systemA
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The wing-form display is displayed
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Figure 7-15.-Emergency jettison con
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The A/A weapon select switch select
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Part of the system consists of unpr
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Figure 7-22.-SH-3 (series) search a
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ottle and the ECU are mounted on to
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Figure 7-25.-Pylon/rack assembly.ci
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REVIEW QUESTIONSQ1. True or False.
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COMPUTER APPLICATIONSTYPES OF COMPU
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the most important. This data manip
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and other data that are to be used
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to represent the same data that was
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compatibility permits the computer
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most cases, the processing speed fa
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4. Stores the results of manipulati
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An overall check of a computer can
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CHAPTER 9AUTOMATIC CARRIER LANDING
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stabilized deck-coordinated system
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Figure 9-3.-Mode I landing sequence
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Figure 9-5.-Lateral automatic wave-
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Precipitation StaticPrecipitation s
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l Sliding-contact interference. Thi
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the signal applied to it. These spu
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the following methods: short circui
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Figure 10-4.-Internal construction
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Figure 10-9.-Methods for using RC f
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Band-Rejection FiltersA band-reject
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Causes of Static ElectricityGenerat
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composed of carbon particles, impre
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APPENDIX 1REFERENCES USED TODEVELOP
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Chapter 7Airborne Weapons/Stores Lo
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CHAPTER 3A1.A2.A3.A4.A5.A6.A7.A8.A9
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A7. Linking two or more computers t
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FORMULASAIII-2
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AIII-4
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Comparison of Units in Electric and
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Antisubmarine warfare weapons syste
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Electrostatic discharge, 10-15compo
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Heads-up display (HUD), 5-5air-to-a
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NNavigation basics, 2-1airborne nav
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Teletype system, 1-22block diagram,
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Assignment QuestionsInformation: Th
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1-11. What will the Sillumination o
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1-35.1-36.1-37.1-38.UHF-1 does NOT
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1-59. What arethat thetactical1. Fr
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ASSIGNMENT 2Textbook Assignment:
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IN ANSWERING QUESTIONS 2-22 THROUGH
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2-43. What method does the AN/APN-1
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2-64. What distance is the maximum
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3-12.3-13.The antenna position prog
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3-32. The 128 nautical mile range i
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IN ANSWERING QUESTION 3-53,FIGURE 3
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3-74. What is the nominal peak powe
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4-12. Sonar transmission losses can
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4-31.4-32.4-33.When positive gradie
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4-52. The function of the dual curs
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4-71. The angle between a magnetic
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IN ANSWERING QUESTIONS 5-9 THROUGH
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5-29. What component contains theop
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5-51. What type of RF output signal
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6-20. On the HSI, when a tactical m
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6-42. What control(s) the symbolbri
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6-65. Which, if any, of the followi
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7-11. If the temperature of a black
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7-34.A scan mirror is indexed three
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7-56. What is the primary differenc
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8-21. With the landing gear handle
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8-42. With the F/A-18 AIM-9 Sidewin
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8-66. The jettison of wing stores I
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9-13. What method is used to change
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9-36. In magnetic core memories, a
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9-57. What typeaccess toof instruct
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10-12. To maintain the angle-of-att
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10-35. A receiver tuned to 2.4 kHze
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10-55. When rubbed against any of t
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