1. Week 8 Day 1

2. Chapter 16 GPS Global Positioning System Answer questions 3 – 8, 12, 13, 15, 16 Chapter 17 EFIS Electronic Flight Instrument System Answer questions 2-5, 8-10

3. Test Review

4. Test Review

5. Test Review

6. Test Review

7. Test Review

8. Test Review

9. Test Review

10. Test Review

11. 2 weeks.

12. Electronic Flight Instrument System EFIS “Eee Fis”
Chapter 17
Electronic Flight Instrument System
EFIS
“Eee Fis”

14. EADI “Eee ADI”

15. EHSI “Eee HSI”

19. Multifunction Display: MFD-1 page 125

22. APU (Auxiliary Power Unit)

27. EFIS Architecture
Textbook page 124

30. Assignments Week 8
WEEK 8 Chapter 18 CVR FDR Answer questions Chapter 19 WX Radar Answer questions 2 – 13

31. Cockpit Voice and Flight Data Recorders
Chapter 18
Cockpit Voice and Flight Data Recorders

32. 2 Distinct recorders.
The Cockpit Voice Recorder (CVR) records all sounds in the cockpit.
The Flight Data Recorder (FDR) records “parameters” such as airspeed, altitude, airplane configuration, etc.
These are the “black boxes” that the media refer to when talking about crashes.

33. Cockpit Voice Recorder
Textbook page 131

34. CVR LRU
The recorder itself is always located in the fuselage for survivability in a crash.
Here is a CVR in a Learjet.

35. CVR Block Diagram
The recorder receives the 4 audio inputs: Area Mike, Captains Mike, First Officer’s Mike and PA audio.

38. Flight Data Recorder (FDR)
Textbook page 129

43. Vigorous Testing

44. FDR Cutaway

45. FDR Parameters
Textbook page 135

46. FAR Part 25.1457 Cockpit voice recorders.
(a) Each cockpit voice recorder required by the operating rules of this chapter must be approved and must be installed so that it will record the following:
(1) Voice communications transmitted from or received in the airplane by radio.
(2) Voice communications of flight crewmembers on the flight deck.
(3) Voice communications of flight crewmembers on the flight deck, using the airplane's interphone system.
(4) Voice or audio signals identifying navigation or approach aids introduced into a headset or speaker.
(5) Voice communications of flight crewmembers using the passenger loudspeaker system…
(6) If datalink communication equipment is installed, all datalink communications, using an approved data message set. Datalink messages must be recorded as the output signal from the communications unit that translates the signal into usable data.

47. FAR Part 25.1459 Flight data recorders.
(a) Each flight recorder required by the operating rules of this chapter must be installed so that— (1) It is supplied with airspeed, altitude, and directional data obtained from sources that meet the accuracy requirements of §§ , , and , as appropriate; (2) The vertical acceleration sensor is rigidly attached, and located longitudinally either within the approved center of gravity limits of the airplane, or at a distance forward or aft of these limits that does not exceed 25 percent of the airplane's mean aerodynamic chord; (3)(i) It receives its electrical power from the bus that provides the maximum reliability for operation of the flight data recorder without jeopardizing service to essential or emergency loads. (ii) It remains powered for as long as possible without jeopardizing emergency operation of the airplane. (4) There is an aural or visual means for preflight checking of the recorder for proper recording of data in the storage medium; (5) Except for recorders powered solely by the engine-driven electrical generator system, there is an automatic means to simultaneously stop a recorder that has a data erasure feature and prevent each erasure feature from functioning, within 10 minutes after crash impact; (6) There is a means to record data from which the time of each radio transmission either to or from ATC can be determined; (7) Any single electrical failure external to the recorder does not disable both the cockpit voice recorder and the flight data recorder; and (8) It is in a separate container from the cockpit voice recorder when both are required. If used to comply with only the flight data recorder requirements, a combination unit may be installed. If a combination unit is installed as a cockpit voice recorder to comply with § (e)(2), a combination unit must be used to comply with this flight data recorder requirement. (b) Each nonejectable record container must be located and mounted so as to minimize the probability of container rupture resulting from crash impact and subsequent damage to the record from fire. In meeting this requirement the record container must be located as far aft as practicable, but need

48. (1) Time;
(2) Altitude;
(3) Airspeed;
(4) Vertical acceleration;
(5) Heading; and
(6) Time of each radio transmission either to or from air traffic control.

49. no person may operate an airplane specified in paragraph (b) of this section unless it is equipped, before May 26, 1995
(1) Time;
(2) Altitude;
(3) Airspeed;
(4) Vertical acceleration;
(5) Heading;
(6) Time of each radio transmission either to or from air traffic control;
(7) Pitch attitude;
(8) Roll attitude;
(9) Longitudinal acceleration;
(10) Control column or pitch control surface position; and
(11) Thrust of each engine.

50. (1) Time;
(2) Altitude;
(3) Airspeed;
(4) Vertical acceleration;
(5) Heading;
(6) Time of each radio transmission either to or from air traffic control;
(7) Pitch attitude;
(8) Roll attitude;
(9) Longitudinal acceleration;
(10) Pitch trim position;
(11) Control column or pitch control surface position;
(12) Control wheel or lateral control surface position;
(13) Rudder pedal or yaw control surface position;
(14) Thrust of each engine;
(15) Position of each thrust reverser;
(16) Trailing edge flap or cockpit flap control position; and
(17) Leading edge flap or cockpit flap control position.

51. FAR Part 121.344 Digital flight data recorders for transport category airplanes.
(1) Time;
(2) Pressure altitude;
(3) Indicated airspeed;
(4) Heading—primary flight crew reference (if selectable, record discrete, true or magnetic);
(5) Normal acceleration (Vertical);
(6) Pitch attitude;
(7) Roll attitude;
(8) Manual radio transmitter keying, or CVR/DFDR synchronization reference;
(9) Thrust/power of each engine—primary flight crew reference;
(10) Autopilot engagement status;
(11) Longitudinal acceleration;
(12) Pitch control input;
(13) Lateral control input;
(14) Rudder pedal input;
(15) Primary pitch control surface position;
(16) Primary lateral control surface position;
(17) Primary yaw control surface position;
(18) Lateral acceleration;
(19) Pitch trim surface position or parameters of paragraph (a)(82) of this section if currently recorded;
(20) Trailing edge flap or cockpit flap control selection (except when parameters of paragraph (a)(85) of this section apply);

52. (21) Leading edge flap or cockpit flap control selection (except when parameters of paragraph (a)(86) of this section apply);
(22) Each Thrust reverser position (or equivalent for propeller airplane);
(23) Ground spoiler position or speed brake selection (except when parameters of paragraph (a)(87) of this section apply);
(24) Outside or total air temperature;
(25) Automatic Flight Control System (AFCS) modes and engagement status, including autothrottle;
(26) Radio altitude (when an information source is installed);
(27) Localizer deviation, MLS Azimuth;
(28) Glideslope deviation, MLS Elevation;
(29) Marker beacon passage;
(30) Master warning;

53. (31) Air/ground sensor (primary airplane system reference nose or main gear);
(32) Angle of attack (when information source is installed);
(33) Hydraulic pressure low (each system);
(34) Ground speed (when an information source is installed);
(35) Ground proximity warning system;
(36) Landing gear position or landing gear cockpit control selection;
(37) Drift angle (when an information source is installed);
(38) Wind speed and direction (when an information source is installed);
(39) Latitude and longitude (when an information source is installed);
(40) Stick shaker/pusher (when an information source is installed);

54. (42) Throttle/power lever position;
(41) Windshear (when an information source is installed);
(42) Throttle/power lever position;
(43) Additional engine parameters (as designated in Appendix M of this part);
(44) Traffic alert and collision avoidance system;
(45) DME 1 and 2 distances;
(46) Nav 1 and 2 selected frequency;
(47) Selected barometric setting (when an information source is installed);
(48) Selected altitude (when an information source is installed);
(49) Selected speed (when an information source is installed);
(50) Selected mach (when an information source is installed);
(51) Selected vertical speed (when an information source is installed);
(52) Selected heading (when an information source is installed);
(53) Selected flight path (when an information source is installed);
(54) Selected decision height (when an information source is installed);
(55) EFIS display format;
(56) Multi-function/engine/alerts display format;
(57) Thrust command (when an information source is installed);
(58) Thrust target (when an information source is installed);
(59) Fuel quantity in CG trim tank (when an information source is installed);
(60) Primary Navigation System Reference;

55. (61) Icing (when an information source is installed); (62) Engine warning each engine vibration (when an information source is installed); (63) Engine warning each engine over temp. (when an information source is installed); (64) Engine warning each engine oil pressure low (when an information source is installed); (65) Engine warning each engine over speed (when an information source is installed); (66) Yaw trim surface position; (67) Roll trim surface position; (68) Brake pressure (selected system); (69) Brake pedal application (left and right); (70) Yaw or sideslip angle (when an information source is installed); (71) Engine bleed valve position (when an information source is installed); (72) De-icing or anti-icing system selection (when an information source is installed); (73) Computed center of gravity (when an information source is installed); (74) AC electrical bus status; (75) DC electrical bus status;
(76) APU bleed valve position (when an information source is installed);
(77) Hydraulic pressure (each system);
(78) Loss of cabin pressure;
(79) Computer failure;
(80) Heads-up display (when an information source is installed);
(81) Para-visual display (when an information source is installed);
(82) Cockpit trim control input position—pitch;
(83) Cockpit trim control input position—roll;
(84) Cockpit trim control input position—yaw;
(85) Trailing edge flap and cockpit flap control position;
(86) Leading edge flap and cockpit flap control position;
(87) Ground spoiler position and speed brake selection;
(88) All cockpit flight control input forces (control wheel, control column, rudder pedal);
(89) Yaw damper status;
(90) Yaw damper command; and
(91) Standby rudder valve status.

56. Colgan Flight 3407

57. The National Transportation Safety Board determines the probable cause(s) of this accident to be:
The captain’s inappropriate response to the activation of the stick shaker, which led to an aerodynamic stall from which the airplane did not recover. Contributing to the accident were (1) the flight crew’s failure to monitor airspeed in relation to the rising position of the low- speed cue, (2) the flight crew failure to adhere to sterile cockpit procedures, (3) the captain’s failure to effectively manage the flight, and (4) Colgan Air’s inadequate procedures for airspeed selection and management during approaches in icing conditions.

59. EDR Event Data Recorder

60. Chapter 19
Weather Detection

61. Weather Radar
Weather radar helps pilots avoid dangerous weather by creating a picture on the radar screen. (screen?)
Weather radar works by transmitting a pulse and that pulse hits rain droplets and reflects back.
New weather radar displays are color which can also express intensity of the storm and which indicates turbulence.
In the new “glass cockpits” weather radar is displayed on a multifunction display along with other aircraft system information.

64. Weather Radar Block Diagram
The antenna sends and receives the pulse generated by the unit.
The Elevation Motor raises and lowers the antenna, the Azimuth Motor makes the antenna sweep side to side.
Inertial Reference keeps the antenna stabilized
The duplexer allows for both transmission and reception through one antenna.
The symbol generator converts weather data into the display.

65. Weather Radar Antenna

66. Weather Radar Antenna

68. WX Radar Radome

69. WX Radar Radome

70. Radar Display Here is a weather radar display.
The colors indicate the intensity of the storm.
Black less than .4” of rain per hour.
Green ” of rain per hour
Yellow ” of rain per hour
Red .5-2” of rain per hour
Magenta over 2” of rain per hour
Textbook page 137

71. Weather Radar on Multifunction Display
Textbook page 137
Here is an example of a weather radar display on a Multifunction Display.
This is showing the weather overlay and the compass card, TCAS for traffic threats, lightening strikes and terrain hazards.

72. Multifunction Display Block Diagram
The multifunction display
takes many inputs:
GPS
FMC
TCAS GPWS
Weather Radar
The system has standard industry interfaces.
ARINC 429
RS 232
Textbook page 138

75. Question: Where is the rain?
Answer: No where.

79. Ground Mapping with WX Radar

80. DATALINK
Nextrad, is a system of high-power ground radar stations that sweeps the sky for five minutes, mapping precipitation horizontally and sampling 14 different elevations up to 140 miles away.
Datalink sends images and text via satellite from the National Weather Service.

82. Lightening Detection/Storm Scopes
Here is a display of lightening strikes.
The lightening detector is tuned to 50KHz, the frequency where lightening energy is concentrated.

83. Windshear

84. Windshear System Block Diagram

85. AWOS Automated Weather Observing System ASOS Automated Surface Observing System

88. GPWS Audio 1 min 11 sec