FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Table of Contents Introduction ....................................................................................................................... 11-1 Electronic Flight Instrument System (EFIS) ................................................................ 11-1 Components and Operations ...................................................................................... 11-2 Primary Flight Display ........................................................................................... 11-2 Multifunction Display ............................................................................................. 11-4 EFIS Comparator Monitor ........................................................................................... 11-6 Full-Time Comparator ........................................................................................... 11-6 Pitch ...................................................................................................................... 11-6 Roll ........................................................................................................................ 11-6 Heading................................................................................................................. 11-6 Altitude .................................................................................................................. 11-7 Indicated Airspeed ................................................................................................ 11-7 Category II Comparator......................................................................................... 11-8 LOC Deviation....................................................................................................... 11-8 G/S Deviation ........................................................................................................ 11-8 RA Deviation ......................................................................................................... 11-9 Comparator Indications and EFIS Failure Displays ............................................ 11-10 Air Data System .............................................................................................................. 11-12 Pitot-Static System.................................................................................................... 11-12 Temperature-Sensing System .................................................................................. 11-14 Air Data Computers (ADCs)...................................................................................... 11-14 Air Data Calculations........................................................................................... 11-14 Air Data Computations ........................................................................................ 11-14 Air Data Transmission ......................................................................................... 11-15 Controls and Indicators ................................................................................................... 11-16 Display Control Panel................................................................................................ 11-16 Format/Range Knob............................................................................................ 11-16 Navigation Source Knob ..................................................................................... 11-16 Bearing Pointers.................................................................................................. 11-16 Information Overlay Buttons................................................................................ 11-16 Air Data Reference Panel ......................................................................................... 11-18 Speed Reference Section ................................................................................... 11-18 Altitude Reference Section.................................................................................. 11-18 Barometric Pressure Section .............................................................................. 11-19 PFD Displays ............................................................................................................ 11-20 Attitude Display ................................................................................................... 11-20 Slip/Skid indicator................................................................................................ 11-20 Unusual Attitude Display ..................................................................................... 11-20 Airspeed Displays ............................................................................................... 11-22 Altitude Displays.................................................................................................. 11-26 Vertical Speed Display ........................................................................................ 11-30 Navigation Displays............................................................................................. 11-32 For Training Purposes Only
May 03
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FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Multifunction Display Formats ................................................................................... 11-34 HSI Format.......................................................................................................... 11-35 NAV Sector Format ............................................................................................. 11-38 FMS Map Format ................................................................................................ 11-40 Plan Map Format................................................................................................. 11-42 TCAS Format ...................................................................................................... 11-43 Radio Altimeter ............................................................................................................... 11-44 Description ................................................................................................................ 11-44 Components and Operation...................................................................................... 11-44 Receiver/Transmitter........................................................................................... 11-44 Antennae............................................................................................................. 11-44 Radio Altitude Display ............................................................................................... 11-45 Analog Radio Altitude Scale................................................................................ 11-45 Ground Bar (Rising Runway) .............................................................................. 11-45 Standby Instruments ....................................................................................................... 11-47 Standby Airspeed Indicator....................................................................................... 11-47 Standby Altimeter...................................................................................................... 11-48 Standby Attitude Indicator......................................................................................... 11-48 Standby Compass..................................................................................................... 11-49 Aircraft Clocks................................................................................................................. 11-50 Display Reversionary Panel ...................................................................................... 11-52 Abnormal Conditions........................................................................................... 11-52 EICAS Messages...................................................................................................... 11-54
11-ii
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
List of Figures Graphic Title
Figure
Electronic Flight Displays .................................................................................................. 11-1 Primary Flight Display (PFD) ............................................................................................ 11-2 Multifunction Display (MFD) .............................................................................................. 11-3 Altitude Comparator Graph ............................................................................................... 11-4 Radar Altimeter Deviation Limits Graph............................................................................ 11-5 PFD Comparator Annunciations ....................................................................................... 11-6 PFD Failure Displays ........................................................................................................ 11-7 Pitot-Static Systems.......................................................................................................... 11-8 Display Control Panel ....................................................................................................... 11-9 Air Data Reference Panel ............................................................................................... 11-10 PFD Attitude Displays ..................................................................................................... 11-11 PFD Airspeed Display and Underspeed / Overspeed Cues ........................................... 11-12 Speed Reference (Bug) Field ......................................................................................... 11-13 PFD Altitude Displays ..................................................................................................... 11-14 MDA and DH Displays .................................................................................................... 11-15 PFD Vertical Speed Display............................................................................................ 11-16 Marker Beacon Annunciations ........................................................................................ 11-17 PFD HSI Display ............................................................................................................. 11-18 MFD Radar Mode and Status Lines................................................................................ 11-19 MFD HSI Format............................................................................................................. 11-20 MFD Sector Format ........................................................................................................ 11-21 MFD Data Window.......................................................................................................... 11-22 MFD FMS Plan Map Format ........................................................................................... 11-23 MFD TCAS Format ......................................................................................................... 11-24 Radar Altimeter Display .................................................................................................. 11-25 Standby Instruments Locator .......................................................................................... 11-26 Standby Airspeed Indicator............................................................................................. 11-27 Standby Altimeter............................................................................................................ 11-28 Standby Attitude Indicator............................................................................................... 11-29 Standby Compass........................................................................................................... 11-30 Clock Prior to A/C 5331 .................................................................................................. 11-31 Clock A/C 5331 and Later............................................................................................... 11-32 Display Reversionary Panel ............................................................................................ 11-33
For Training Purposes Only
May 03
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PILOT TRAINING GUIDE
Page Intentionally Left Blank
11-iv
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
CHAPTER 11: FLIGHT INSTRUMENTS
Introduction The flight instruments chapter includes the Electronic Flight Instruments System (EFIS), Air Data System (ADS), standby instruments, clock and radio altimeter.
Electronic Flight Instrument System (EFIS) The Electronic Flight Instrument System (EFIS) takes input data from airplane radios, sensors and control panels and displays the information on four Electronic Flight Displays (EFDs). Two of the EFDs function as primary flight displays (PFD), and two EFDs function as multifunction displays (MFDs). The color conventions used for the PFD and MFD symbology are: White
For all scales and on-side FMS sensor data
Green
For on-side sensor data (non-FMS)
Yellow
For cross-side sensor data and caution information
Magenta
For pilot-selectable data
Cyan
For secondary information
Red
For warnings and failure flags
MFD 1
MFD 2
3000
10
UTC 11:01
4
VOR1 YUL TTG--:--
300
2 4
2
200
1
TAS 0
GS 0
FMS2 LONNA
0
40
N1
N
000 1
100
2
RA
N
E
323
UTC 11:01
CYUL LONNA ALEXS CYUL
TAS 0
1NM 12NM 20NM 111NM
GS 0
SAT 15 C
11:02 11:05 11:07 11:25
0:03 0:04 0:23
EGT
7137LB
35.6GM
23
BLEED PRESS
0
OIL TEMP FAN VIB
- FUEL (LBS) - TOTAL
24
4050 ADF 2
ADF2
0 0
0 0 33 0.0
- FLAPS -
20
36
DN DN DN STAB NU
8100
5.0
LWD
4050 ND
15
- TRIM -
V1 113 00
25
35
BULK OXY
DME 1
1820
C ALT
100
RATE
0
10
CYUL
DTK 056 12.2NM LONNA
YUL 12.7
DME 2 ––––
1
100
000 1
RA2 IRS2 ADC2 DCP2
20
100
0FT TRU
FMS2 12.5
AIL
6
3
GS RA
29.92 IN 2400M
2 4
TCAS OFF
E
TERM
RWD
RUDDER NL
ENGINE
LONNA
2
200
1
0
V2 133 20 VR 121
4
300
2 4
SPOILERS
NR
P
VOR 1
0.0
FMS MAP
ADF 2
VOR1
15
VOR 1
FF (PPH) OIL PRESS
10
40
VT 150
E
3
TOC
3000 2500M
8000
20
60
059
CABIN TEMP
TO ALTS
200 80
TAT 15 C
12
15
33
TO DR LOC 1
WX+TRB
100
RPM
47
- GEAR -
0 0 33 0.0
0.78 318 0.85 197 197 250
APU R FUEL PUMP ON L FUEL PUMP ON DOOR CLOSED PARKING BRAKE ON PROX SYS FAULT FDR FAIL
0.0 N2
S
12
NO FLIGHT PLAN
29.92 IN 2400M
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
30
45
0
ALEXS
TCAS OFF
E
FEET X 1000
FUEL TEMP 4
30
6
8
CABIN 10 ALTITUDE
20
4
2
W
TRU
3
GS
33
20
0FT
0.0 15
RA2 IRS2 ADC2 DCP2
TERM
VOR1
6 2 3
E
21
10
FMS1 DTK 333 12.7NM YUL
ALT
12
00
180
6
3
12
V1 113
1 9 2 2 3 000 4
1014 6 5 2992 4
ITT
V2 133 20 VR 121
7
LL TO C AG
R ENG OIL PRESS L ENG OIL PRESS L WSHLD HEAT L WINDOW HEAT INBD BRAKE PRESS R WSHLD HEAT R WINDOW HEAT OUTBD BRAKE PRESS R PROBE HEAT OFF L PROBE HEAT OFF HYD 3 LO PRESS
0.0
TTG --:--
100
VE
P
0.0
DTK056 12.2 NM
059
180 VT 150
MB
DI
U
TAT 15 C
SAT 15 C
CRS 012 12.7NM
1
CLI
KTS 200 300 250
WX + TRB
2500M
8000
20
OFF
350
33
TO ALTS
60
0
60 100 400 IAS 150
0.78 318 0.85 197 197 250
N
TO DR LOC 1 200 80
AIRSPEED LIMITS - (INDICATED SPEEDS)
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
ADF2 BR
BR
BR
BR
BR
BR
T
T
T
T
T
T
P604_11_047
AIRSPEED LIMITS - (INDICATED SPEEDS)
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
PFD 2
N
PFD 1
EICAS EFD
Electronic Flight Displays Figure 11-1
For Training Purposes Only
May 03
11-1
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Components and Operations Primary Flight Display The Primary Flight Display (PFD) presents the flight instruments in a typical “T” formation, which includes both the Attitude Director Indicator (ADI) and the Horizontal Situation Indicator (HSI). The two PFDs are the outboard EFDs of the instrument panel. The PFDs come on automatically upon receiving DC power. The following data is displayed on the PFD: • • • • • • • •
11-2
Attitude Heading Airspeed Altitude Vertical Speed Flight Mode Annunciators Nav source and navigation information HSI
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Attitude Indicator
Flight Mode Annunciators
TO DR LOC 1
TO
3000
ALTS
2500M
200
80 60
Nav Source FMS1
Navigation Information
1
200
2 1
Vertical Speed
100
000 1
RA2 IRS2 ADC2 DCP2
20
100
0FT TRU
GS RA
HDG 340 6
3
Heading
4
Horizontal Situation Indicator
TCAS OFF
E
NO FLIGHT PLAN
29.85 IN 2400M
2
12
DTK 333 12.7NM YUL
300
0 10
Altitude
4 2
15
33
TERM
VOR1
P604_11_046
40 VT 150 V2 133 VR 121 V1 113
10
N
Airspeed Tape
8000
20
Primary Flight Display (PFD) Figure 11-2
For Training Purposes Only
May 03
11-3
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Multifunction Display The MFDs present navigation information in pilot-selectable formats. The MFDs are the displays located inboard of the PFDs. Like the PFDs, they come on automatically upon receiving DC power. The MFDs also provide reversionary backup displays for the PFD or the EICAS. The following page formats may be displayed on the MFDs: • • • • •
HSI Nav Sector Map FMS Map Plan Map TCAS
Additional MFD information includes: • • • • •
11-4
Weather Radar Terrain data (if EGPWS installed) Checklist (operated from the EICAS Control Panel) Reversion to PFD or EICAS Remote Text (Maintenance Diagnostic Computer and FMS Text)
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
MFD FORMATS RADAR OFF UTC22 : 40
RADAR OFF
TGT
TAS 250
GS 247
SAT
15C
TAT–15C
UTC01 : 50
TGT
TAS 146
GS 145
SAT
10C
TAT–13C
FMS1
DTK 333
FMS2
DTK 030
LOC1
CRS 059
FMS2
DTK 030
YUL
12.7NM
YUL
12.7NM
IUL
8.5NM
YUL
12.7NM
TTG
TTG11 : 42
TTG
: 42
: 04
059
059
TTG11 : 04
G+1
LX/MAP UTC22:15
BDF JDT PMM CYUL
TAS 467
22NM 40NM 153NM 737NM
USTB
GS 537
T+10.7 T-4.5 SAT-49C
TAT -20C
: DES 1:11/ 616NM 0:05 : ADVISORY 0:07 : 1:33 :
071 6
E
12
N
3
15
33
10 100
5
JOT 25
S
30
ABOVE BELOW ABOVE BELOW
21
––––
VOR1
W
24
RW06L YUL HOKKE CYOW
USTB
G+3 TAS 0
0NM 13NM 37NM 97NM
GS 0
VOR2
NAV SECTOR
HSI FORMAT
UTC 22:39
DME2
-12 BDF
VOR2
FMS1
LX/RADAR OFF
-20
NAV SECTOR
T+10.7
TAS 0
UTC 22:39
USTB
G+3
LX/RADAR OFF TAT 15C
SAT 15C
GS 0
ADF2
VOR1
FMS MAP TRAFFIC OVERLAY T+10.7 TAT 15C
SAT 15C
: 0:03 : 0:07 : 0:21 :
10 YOW /2900
X (2900) /2960A
12.5
RW32 WATTO 4000
YRRNB /2600 DME1
DME2
––––
––––
TO WPT UNLOCKED
V=000° L=360T
PLAN MAP FORMAT
TCAS TRAFFIC DISPLAY
ADDITIONAL INFORMATION DISPLAYS TAS 0
1NM 14NM 38NM 119NM
GS 0
T+10.7 T+5.0 SAT 15C
FMS2
: 0:03 : 0:07 : 0:25 :
YUL
TTG :04
239 W
21
USTB
T+10.7 1/2
TAKEOFF REFERENCE
RWY ID RWY WIND RWY LENGTH RWY SLOPE RWY COND
V1: 113
RW06R ––– 9600 FT – –.– DRY
G+1
LX/MAP UTC22:15
CYUL
BDF JDT PMM CYUL
TAS 467
22NM 40NM 153NM 737NM
VR: 121
USTB
GS 537
T+10.7 T-4.5 SAT-49C
TAT -20C
: DES 1:11/ 616NM 0:05 : ADVISORY 0:07 : 1:33 :
071
V2: 132 VFTO/VT: 152
S
30
50
HOKKE 25
CYUL
DME1 ––––
G+3
LX/RADAR OFF TAT 15C
DTK 333 12.7NM
YUL
-20
DME2 ––––
-12 ADF2
ADF1
FMS MAP WX OVERLAY TRAFFIC OVERLAY
WIND OAT ONH P ALT
– – –°/– – – KT +15°C 29.75 IN 272 FT
TOW GWT MTOW
35.0 LB 34.7 LB 48.3 LB
ENG BLEED APR THRUST REV CG
TOFL: 3568 FT OCR CLB GRAD: 10.1%
100
JOT 25
10TH ARMED BOTH –– %
ABOVE BELOW
TRIM: 90.3 TO: 90.3 MCT: 93.7
DME2 ––––
BDF ADF2
VOR1
REMOTE TEXT
P604_11_030
UTC04:23
RW24L YUL HOKKE CYOW
USTB
G+3
LX/WX
FMS MAP TERRAIN OVERLAY
Multifunction Display (MFD) Figure 11-3
For Training Purposes Only
Sept 04
11-5
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
EFIS Comparator Monitor Data displayed on the two PFDs is continuously compared for deviations. When defined trip levels are exceeded, the EFIS COMP MON caution EICAS message is displayed, and the flashing MASTER CAUTION lights are triggered. The comparator monitor has two sections; the full-time comparators and the Category II comparators. Full-Time Comparator Full-time comparator warning is performed for pitch, roll, heading, altitude and airspeed data. Comparator warnings appear in yellow and flash temporarily on the PFD. They then remain displayed while the condition exists.
NOTE A subsequent EFIS comparator monitor indication will not cause another Master Caution to flash. Only the comparator indication on the PFD will flash. Pitch Pitch comparator monitoring is enabled if both sides are using different Inertial Reference System (IRS) sources and both sources have not failed (any ATT flag). When enabled, if the pilot’s and copilot’s displayed pitch difference is greater than 4° when en route, or greater than 3° during approach, the pitch comparator warning “PIT” shows on the attitude indicator. Roll Roll comparator monitoring is enabled if both sides are using different IRS sources, and both sources have not failed (any ATT flag). When enabled, if the pilot’s and copilot’s roll difference is greater than 4° when en route, or greater than 3° during approach, the comparator warning “ROL” shows on the attitude indicator. Heading The heading comparator is enabled when: • • •
both sides are using the same heading reference (MAG or TRU) both sides are using different IRS sources, and both sources have not failed (no HDG flag)
If the heading comparator is enabled and the heading difference is greater than 6°, the heading comparator warning “HDG” shows on the compass arc.
11-6
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Altitude The altitude comparator is enabled if both sides are using different air data sources and both sides have not failed (no ALT flag). If the altitude comparator is enabled and the altitude difference is not within limits, the altitude comparator warning “ALT” shows vertically on the lower portion of the altitude scale. As the altitude increases, so do the altitude difference limits, as indicated by the following formula: if the ALT difference exceeds [60 + (pilot’s altitude + copilot’s altitude)/460] feet, the altitude comparator warning shows. 300
250
200
150
100
P604_11_045
Altimeter difference
Altitude difference = [60 + (pilot’s altitude + copilot’s altitude)/460]
50
0 0
5,000
10,000
15,000
20,000 25,000 Aircraft Altitude
30,000
35,000
40,000
45,000
Altitude Comparator Graph Figure 11-4
Indicated Airspeed The airspeed comparator is enabled if both sides are using different air data sources, both sides have not failed (no IAS flag), and the indicated airspeed is greater than 90 knots. If the airspeed comparator is enabled and the airspeed difference is greater than 10 knots, the airspeed comparator warning “IAS” shows on the upper portion of the airspeed scale. The following table summarizes the trip values for the full-time comparator monitoring functions:
For Training Purposes Only
May 03
11-7
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
SYSTEM
FLAG
VALUE
HEADING
HDG
> 6°
ROLL
ROL
> 3° Approach, > 4° En route
PITCH
PIT
> 3° Approach, > 4° En route
ALTITUDE
ALT
60 ft with BARO set within 0.02 inches. The amount of difference required to trigger the flag increases as altitude increases.
AIRSPEED
IAS
> 10 kts above 90 kts
Category II Comparator Category II comparators are enabled if approach mode is selected and the DH is set below 200 feet. Comparator monitoring is performed for LOC, G/S and Radio Altimeter deviations. The following conditions must be valid to enable the CAT II comparisons: • • • •
the on-side RA is valid and RA is less than 1000 feet the cross-side data is valid the LOC on both sides are tuned identically and are valid approach mode is selected
LOC Deviation When the LOC comparator is enabled and the pilot’s and copilot’s lateral deviations differ by more than a predetermined amount, a yellow “LOC” comparator flag shows in the compass arc. The amount of difference allowed varies with the location of the pilot’s localizer. As the pilot’s localizer moves toward the center of the display, the comparison tolerance decreases. For example, when the pilot’s side deviation pointer is at the center of the scale, the comparator allows up to approximately +½ dots of deviation error on the copilot’s side before showing the comparator warning flag. G/S Deviation When the G/S comparator is enabled and the pilot’s and copilot’s lateral deviations differ by more than a predetermined amount, a yellow “GS” comparator flag shows below the glideslope scale. The limits vary with the position of the pilot’s deviation pointer. As it moves closer to the centerline of the scale, the comparison tolerance decreases.
11-8
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
For example, when the pilot’s side deviation pointer is at the center of the scale, the comparator allows up to approximately +¾ dots of deviation error on the copilot’s side before showing the comparator warning flag. RA Deviation When the RA comparator is enabled and the pilot’s and copilot’s RA difference is not within limits, a yellow “RA” comparator flag shows below the attitude indicator. To enable the RA comparator, the on-side RA altitude is less than 1000 feet and the crossside RA is valid. As the altitude increases, so do the RA difference limits increase as per the following formula: [30 feet + 0.028 X (pilot’s RA height + copilot’s RA height)]. RAD ALT Diff
100 ALT Diff
90 80
Radio Altimeter difference
70 60 50 40 30 Altitude difference = [30 + 0.028 X (pilot’s RA height + copilot’s RA height)] P604_11_031
20 10 0 0
250
500 Aircraft Altitude
750
1000
Radar Altimeter Deviation Limits Graph Figure 11-5
For Training Purposes Only
May 03
11-9
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Comparator Indications and EFIS Failure Displays The Comparator warning icon on the PFD will remain displayed while the condition exists. If the comparator monitor fails, the Amber EFIS COMP MON INOP caution EICAS message is displayed, and the flashing MASTER CAUTION lights will be triggered. DR
LOC1
GS
2500
ALTS PATH GS
20
AP
143 I A S
180
4
900
10
1
800
160
1
T
140 120
2
R
FD
10PIT
ROL
700
2
GS
M.452
30
RA
600
A L T
20
1 2
500 29.85 IN
4
0.8
LOC1 CRS 071
6
E
N
NO FLIGHT PLAN
33
LOC
MDA
580
15
ADF1
12
3
P604_11_032
4.3H
HDG S
PFD Comparator Annunciations Figure 11-6
The failure of a selected source removes the respective scale or display and presents a red flag. Vertical Deviation Flag
Airspeed Flag G S
IAS
ATT DISPLAY TEMP
Attitude Flag DCP2 FMS1
GS
TRU
LOC1
CRS 310 - - - NM
33
N
30
W
ADF1
NO FLIGHT PLAN
6
MSG1 MSG2
24
3
Navigation Source Flag
V S
Vertical Speed Flag Overtemperature Warning Expanded Lateral Deviation Flag Radio Altitude Flag
LOC RA
Display Control Panel Source Flag
ALT
FD
1
ADF2
Heading Flag
E
P604_11_018
Flight Director Flag
Barometric Altitude Flag
PFD Failure Displays Figure 11-7
11-10
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
The following Failure Flags are available:
Failure flag label
Meaning
Items removed from display
ALT
Air Data Computer failure
Barometric altitude tapes, digital altitude readout, preselected altitude reference, digital preselect altitude, metric altitude readout and metric preselected altitude
ATT
Inertial Reference System failure
Sky/ground raster, pitch tape, roll pointer, roll scale, slip/skid indicator
DCP
Display Control Panel failure
Flight director bars
MAG, TRK, TRU
Heading Sensor input failure Inertial Reference System failure
The heading display is not removed, but the heading is not updated
FD
Flight Director failure
Flight director bars
FMS/GS/LOC/VOR
Respective Navigation System failure
Flight director bars Lateral deviation scale Red boxed Nav Source
GS
Glideslope failure
Vertical deviation scale and pointer
IAS
Air Data Computer failure
Airspeed tape and information
VS
Air Data Computer failure
Vertical speed scale pointer, digital readout
RA
Radio Altimeter failure
Analog radio altitude symbology, analog decision height marker and digital radio altitude
For Training Purposes Only
May 03
11-11
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Air Data System The Air Data System (ADS) uses air pressure and temperature information to calculate all of the parameters related to flight. It supplies the following information to EFIS for display: • • • • • •
Altitude (ALT) Indicated Airspeed (IAS) Vertical speed (VS) True airspeed (TAS) Static Air Temperature (SAT), and Total Air Temperature (TAT)
The ADS also provides computed data to: • • • • • • •
Inertial Reference System (IRS) Flight Data Recorder (FDR) Stall Protection and Flap systems Air Traffic Control (ATC) transponders Traffic Collision Avoidance System Automatic Flight Control System (AFCS), and Engine Indication and Crew Alerting System (EICAS)
The Air Data System contains the following subsystems: • • • •
Pitot-Static System Temperature Sensing System Air Data Computer System (ADC) Air Data Reference Panels (ADRPs)
Pitot-Static System The pitot-static system includes: • •
two main pitot-static systems one standby pitot-static system
The two main pitot-static systems designated P1/S1 and P2/S2 supply variable pressure inputs to the ADCs. The pitot pressure is sensed through an opening in the forward end of the pitot heads. The static pressure is ported through eight holes on the contoured midsection of the pitot head. Each static port consists of four holes; two on the upper side and two on the lower side of the pitot head. The S1 static port holes are forward and the S2 holes are aft along the pitot head. The contoured surface provides aerodynamic compensation to correct static pressure position error.
11-12
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
The P3 standby pitot system supplies pitot air pressure to the standby airspeed indicator. Two S3 standby static ports supply static pressure to the Cabin Pressure Acquisition Module (CPAM) Cabin Pressure Controller, standby airspeed indicator and standby altimeter. Ice Protection is provided by electric heating elements for all pitot-static probes. LEGEND Pilot's Pitot Pressure Copilot's Pitot Pressure Pilot's Static Pressure Copilot's Static Pressure Pitot Pressure Static Pressure TAT Probe Line
COPILOT’S PITOT-STATIC (P2S2)
PILOT’S PITOT-STATIC (P1S1)
P1
S1
S2
NO. 1 ADC
P2
NO. 2 ADC CENTER INSTRUMENT PANEL P3
Standby ASI
Standby ALT
S3
S3
STANDBY PITOT (P3) CABIN PRESS CTRL S3
CPAM S3
LEFT STATIC PORT (S3)
P604_11_027
TAT PROBE
RIGHT STATIC PORT (S3)
Pitot-Static Systems Figure 11-8
For Training Purposes Only
May 03
11-13
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Temperature-Sensing System The temperature-sensing system receives data from a Total Air Temperature (TAT) Probe. The ADCs use the outputs from the probe to calculate the Static Air Temperature (SAT) and the True Airspeed (TAS)/Mach number. This information is displayed on the Primary Flight Displays (PFDs) and Multifunction Displays (MFDs). Ice Protection is provided by electric heating elements.
Air Data Computers (ADCs) The ADCs are digital, microprocessor-controlled units. The two ADCs receive on-side pitot and static air pressure information from the pitot-static system and air temperature information from the TAT probe. The ADCs also receive operator/display selected input from the ADRPs and the Automatic Flight Control System (AFCS). From these inputs, the ADC calculates all necessary air data parameters and transmits the information to the applicable systems. Air Data Calculations The ADC calculates air data parameters for the following: • • • • • • • • •
Pressure altitude (corrected for static-port pressure errors) Barometric corrected altitude (inches of mercury or hectopascals) Vertical Speed Indicated airspeed (IAS)/Calibrated airspeed (CAS) Mach number Maximum airspeed (VMO/MMO) True airspeed (TAS) Static air temperature (SAT) Total air temperature (TAT)
Air Data Computations The ADC computes data for the following: • • • • • • •
11-14
Preselect altitude Vertical speed reference Airspeed reference Mach reference IAS trend vector Secondary speed reference (V1, VR, V2 and VT) Flap overspeed limits (231, 197 and 189 Kts)
For Training Purposes Only
May 03
PILOT TRAINING GUIDE
FLIGHT INSTRUMENTS
Air Data Transmission The ADC sends the computed air data to the following systems and components: • • • • • • • • • • • •
Flight Data Recorder (FDR) Radio Tuning Unit (RTU) Mode S Transponder Traffic Alert and Collision Avoidance System (TCAS) Primary Flight Display (PFD)/Multifunction Display (MFD) AFCS IRSs DCUs Ground Proximity Warning System (GPWS) Horizontal Stabilizer Trim Control Unit (HSTCU) Stall protection computer Flap Electronic Control Unit (FECU)
For Training Purposes Only
May 03
11-15
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Controls and Indicators Display Control Panel The DCP provides the pilot and copilot with the controls needed to select the desired navigational features of the EFIS system. For the PFDs, this includes lateral and vertical navigation source information and bearing pointers. For the MFDs, this includes the format, range and display overlays. Each MFD/PFD pair has a dedicated DCP. If one of the DCPs should fail, the other DCP may be used to control both EFIS displays. Format/Range Knob Turning the (outer) FORMAT knob selects a desired on-side MFD display format for the associated MFD. There are five selectable display formats: HSI, NAV Sector, FMS Map, Plan Map and TCAS. The (inner) RANGE knob varies the display range scale on the MFD. Navigation Source Knob The NAV SOURCE knob selects the active navigation source. This action controls the selection of displayed information on each pilot’s PFD/MFD. Possible selections are FMS 1, VOR 1, (or LOC 1), VOR 2 (or LOC 2) FMS 2 and FMS 3. Pushing the center of the knob alternately adds or removes cross-side NAV data on the MFD HSI and NAV sector displays only. Bearing Pointers The single-bar BRG pointer selects the No. 1 Bearing pointer for each pilot’s PFD/ MFD. Possible selections are VOR 1, ADF 1, FMS 1, and FMS 3 (if installed). The double-bar BRG pointer selects the No. 2 Bearing pointer for each pilot’s PFD/MFD. Possible selections are VOR 2, ADF 2, FMS 2, and FMS 3 (if installed). Information Overlay Buttons The WX button selects weather radar and lightning detection system depictions on the MFD. This button sequentially selects weather radar information, or adds radar/ lightning overlays. The Weather Radar is available on all dynamic map MFD formats, but is not available for HSI and Plan Map. The TFC button alternately selects or deselects the TCAS Traffic Map Overlay display on the associated MFD. The TERR button selects the terrain information and replaces the Weather Radar information. For more details about terrain overlay information, see the EGPWS section in Chapter 17 Navigation Systems.
11-16
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
No. 1 Bearing Pointer Source Switch Push to select No. 1 source
BRG
Terrain Information Display Select Switch Used to select or deselect Terrain Information Display
TERR
WX
Weather Radar Display Select Switch Used to select or deselect Weather Radar Display
TFC Switch Used to directly select TCAS traffic display on MFD
TFC
RANGE
P US H X-
No. 2 Bearing Pointer Source Switch Push to select No. 2 source
MFD Format Selector Switch Used to select basic format/mode displayed on MFD
SID
E
FORMAT
P604_11_003
NAV SOURCE
Range Selector Switch Used to select range displayed on MFD
Cross-Side Course Selection PushButton Switch Used only on MFD; in HSI and NAV Sector formats
Navigation Source Knob Rotate to select navigation source
Display Control Panel Figure 11-9
For Training Purposes Only
May 03
11-17
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Air Data Reference Panel The Air Data Reference Panel (ADRP) is used to set speed, altitude and barometric pressure values, which are then sent to the EFIS for display. The two ADRPs are installed on the center pedestal. Each panel has three rotary knobs with inset pushbutton switches. The panel is divided into three sections: the speed reference section, the altitude reference section and the barometric pressure section. •
the Speed Reference section is used to make changes to airspeed references (V1, VR, V2 and VT)
•
the Altitude Reference section is used to control the Minimum Descent Altitude (MDA) and Decision Height (DH) display on the EFIS. It also incorporates a test switch for the Radio Altimeter (RA) the Barometric Pressure section is used to make changes to the ADC barometric correction function
•
Speed Reference Section To manually change the speeds posted on the V-Speed table, turn the TGT/VSPDS outer knob to either TGT (VT), or VSPDS (V1, VR and V2). Rotate the SET (inner) knob to change the speed values. In the VSPDS position the reference speeds can be alternately edited by pushing the SEL button and rotating the SET knob. The SET switch (inner knob) enables/disables the PFD display of the selected target or reference airspeed. These speeds are displayed below the IAS scale on the PFD and are located on the speed tape in their respective positions (V1, VR, V2 and VT). Manually entered V-speeds will be displayed in cyan. For Precision-Plus-equipped aircraft, V-speeds can be computed and entered via the FMS where they will be displayed in cyan. Manually entered V-speeds in Precision-Plus-equipped aircraft are displayed in magenta. Altitude Reference Section To change the altitude value displayed for either the Minimum Descent Altitude (MDA) or the Decision Height (DH), rotate the DH/MDA (outer) knob to select the altitude to be amended. The SET (inner knob) switch is rotated to change the values. These altitudes are displayed on the PFD below the altitude scale. The SET switch is pushed to enable or disable the display of either the DH or the MDA. The Radio Altimeter (RA) test switch is depressed to conduct an internal test on the Radio Altimeter. The RA value on the bottom of the Attitude Direction Indicator will change to 50 feet and the rising runway symbology, located on the Radio Altimeter analog scale, moves down 50 feet.
11-18
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Barometric Pressure Section The Barometric (BARO) knob changes the barometric pressure. Pushing the SET switch selects standard barometric pressure (29.92 inches of mercury, or 1013 hectopascals). The value is displayed below the PFD altitude scale. The HPA/IN switch alternately selects barometric pressure correction in hectopascals (hPa), or inches of mercury (inHg).
DH
MDA
P
BARO RA TEST
H
US SET OFF
H
SPEED REFS TGT VSPDS
HPA/IN
US SET OFF
P
SEL
HPA/IN Toggles between hPa/mb or inches of mercury
DH/MDA Knob Outer knob - Select DH/MDA. Inner set knob - Rotate to set. PUSH OFF - removes display from PFD.
SPEED REFS Knob Outer knob - Selects target speed VT or V speeds V1, VR, V2. Inner set knob - Adjusts value of selected V-speed. PUSH OFF - Removes display of selected speed.
PUSH
S T D
RA TEST Initiates radio altimeter test
P604_11_044
SEL Button Toggles between V1, VR or V2
BARO Knob Knob - rotate to set barometric pressure.
Air Data Reference Panel Figure 11-10
For Training Purposes Only
May 03
11-19
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
PFD Displays Attitude Display The attitude symbology provides pitch, roll and slip/skid information. IRS information is used to drive the attitude symbology. An inverted black V-bar airplane symbol denotes the aircraft’s relative attitude on the Attitude Director Indicator (ADI). Large-scale markings are placed at 10, 20, 30, 40, 50, and 65 degrees of pitch. Medium markings are placed at 5-degree intervals up to ± 30 degrees. Small tick marks are placed at 2.5-degree intervals up to ± 20 degrees. Roll scale markings are used to indicate airplane roll angles between ± 60 degrees. The roll pointer is used with the roll scale to indicate the airplane roll angle. The pointer is oriented perpendicular to the horizon line and next to the roll scale to represent degrees of roll (bank) angle. The roll pointer rotates about the center of the airplane symbol in response to changes in airplane roll angle. Slip/Skid indicator The slip/skid indicator is located just below the roll pointer and approximates the displacement of an inclinometer. The indicator is a small rectangular symbol. The slip/ skid indicator is driven by lateral accelerations. Unusual Attitude Display If the airplane is flown into an unusual attitude, all non-necessary indications are removed. Unusual attitudes occur when pitch exceeds +30 degrees (up), or –20 degrees (down), or when roll exceeds 65 degrees. During excessive attitude, only pitch, roll airspeed and altitude are displayed. Red chevrons point toward zero in extreme pitch attitudes. A portion of blue or brown coloring representing sky or ground remains displayed, regardless of pitch attitude, to assist with orientation.
11-20
For Training Purposes Only
Jan 04
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Roll Scale LNV1 DR LOC 1
FLC
12000
ALTS
1.0
Roll Pointer
2500M
250
4
8000
30
2
280
Pitch Scale
Slip/Skid Indicator
Roll Pointer
600 1
20
260
500
3
7
10
400
240
Slip/Skid Indicator
1
220
300
RA2 IRS2 ADC2 DCP2
TRU
FMS1
GS RA
33
30
29.85 IN 2400M 25
4
3.6 TCAS OFF
N
W
DTK 279 25.3NM HOKKE
2
10
24
3
NO FLIGHT PLAN TERM MSG
6 VOR2
FMS1
NORMAL ATTITUDE DISPLAY
4
2500M
280
4
8000
300
2
65
300
180
1
000
140
TRU
2400M 14 TRAFFIC
N
33 3
RA
3
W
6
E
E
UNUSUAL PITCH ATTITUDE
4
2400M 2.8 TRAFFIC
N
NO FLIGHT PLAN
6
W
900 GS
4
NO FLIGHT PLAN
24
1 2
30
33 30
000
200
GS RA
220
100
2
30 TRU
4
20
40
1
240
100
2
200
10
160
200
260 10
5
1
24
200
P604_11_033
2500M
8000
UNUSUAL BANK ANGLE ATTITUDE
PFD Attitude Displays Figure 11-11
For Training Purposes Only
May 03
11-21
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Airspeed Displays IAS Scale The indicated airspeed scale is a vertical “moving tape” display. The IAS scale contains a line marking every 5 and 10 knots and a numeric label every 20 knots. If airspeed data becomes invalid, the scale is replaced with a red IAS annunciation. IAS Pointer This stationary triangle is displayed at the center of the IAS window. The current indicated airspeed is the IAS scale indication at the pointer. IAS Trend Vector The IAS Trend Vector is a magenta line that extends from the IAS pointer to predicted future airspeed. The head of the trend vector aligns with the IAS scale to predict what the airspeed will be in 10 seconds (if present acceleration is maintained). The vector extends up as airspeed increases and down as airspeed decreases. The trend vector is not displayed when the airplane is on the ground. Mach Display The current indicated Mach speed automatically displays below the airspeed scale with an M label as Mach increases above 0.450. This display is removed when Mach decreases below 0.400. Mach display changes in 0.002 increments. Overspeed Cue The overspeed reference is shown de-emphasized (red triple-width vertical bar) on the airspeed scale ascending from VMO/MMO to the top of the airspeed tape. The deemphasized overspeed reference changes to an emphasized overspeed reference (red and gray checkerboard symbol) when the airspeed is two knots or greater into the VMO/MMO region. The de-emphasized overspeed reference also changes to an emphasized overspeed reference when the airspeed trend has been two knots or greater into the VMO/MMO region for five seconds or more. Low Speed Cue The Low Speed Cue indicates the aircraft’s impending stall speed and is generated by Angle-of-Attack information from the Auxiliary Angle-of-Attack vane. The Low Speed Cue indication is shown de-emphasized (red triple-width vertical bar) on the airspeed scale descending from impending stall speed to the bottom of the airspeed tape. The deemphasized cue changes to an emphasized cue (red and gray checkerboard symbol) when airspeed is two knots or greater into the impending stall speed region. The deemphasized cue also changes to an emphasized cue when the airspeed trend has been two knots or greater into the impending stall speed region for five seconds or more.
11-22
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
TO DR LOC 1
IAS Scale
TO
3000
ALTS
T
20
2
10
8000
4 2
300
1
200
2
140
IAS Pointer Mach Display
1.0
2500M
200
120 R
0
1
100
1
100
000
10
1
240 320
240
320
100
20
80
0FT
M.452
TRU
GS RA
300
280
DTK 333 12.7NM YUL
280
6
NO FLIGHT PLAN
260
TERM
15
DE-EMPHASIZED OVERSPEED CUE
M.476
33
260 M.466
TCAS OFF
10
E
3 N
FMS1
4
12
300
29.85 IN 2400M
2
VOR1
EMPHASIZED OVERSPEED CUE
TAKEOFF ROLL DISPLAY IAS Trend Vector
200 200
180
200
180
TO DR LOC 1
TO
3000
ALTS
1.0
2500M
200 180
8000
4 2
300
30
160
2 1
140 M.466
DE-EMPHASIZED LOW SPEED CUE
1
160 140
T
140
0
10
2
120 M.466
200
20
100
000
120
1 2
EMPHASIZED LOW SPEED CUE
0FT 10 TRU
FMS1
6
E
N
3
NO FLIGHT PLAN
100 29.85 IN 4 2400M 1.2 TCAS 10 OFF
12
DTK 333 12.6NM YUL
GS RA
15
33
TERM
VOR2
VOR1
P604_11_034
160
ROTATION DISPLAY
PFD Airspeed Display and Underspeed / Overspeed Cues Figure 11-12
Speed Reference (Bug) Field This line display shows a selected speed reference (bug) value that can be controlled using either Air Data Reference Panel (ADRP). The SPEED REFS knob and SEL button are used to sequentially select one of four available bugs, 1, R, 2, or T, corresponding to (V1, VR, V2, or VT) for display in this field.
For Training Purposes Only
May 03
11-23
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
The SET knob on the ADRP is used to change this value. The PUSH OFF switch on the ADRP enables/disables display of the selected bug. The bug position on the IAS scale automatically updates as the numeric values change. After five seconds of inactivity, the speed reference field display blanks. Speed Reference (Bug) Table The table displays on the lower portion of the IAS scale when airspeed is less than 40 knots. When the table displays, use the ADRP to select and change one of four airspeed bugs (V1, VR, V2 or VT).
NOTE For Precision-Plus-equipped aircraft, V-speeds can be computed and entered via the FMS. V1 Bug The reference marker is a cyan line followed by a 1. The V1 bug is the takeoff decision speed reference. The V1 bug is automatically removed at lift-off. VR Bug The reference marker is a cyan line followed by an R. The VR bug is the rotation speed reference. The bug display is automatically removed after the V2 speed is exceeded. V2 Bug The reference marker is a cyan line followed by a 2. The V2 bug is the takeoff safety speed reference. The bug display is automatically removed after the V2 speed is exceeded (V2 + 40 knots + weight off wheels for 7 seconds). VT Bug The reference marker is a cyan line followed by a T. The VT bug is the target speed reference. IAS Reference Field The magenta display shows the selected IAS reference value. The value is marked by the notched-box (bucket) symbol on the IAS scale. Turn the SPEED knob on the FCP to set this value. While in Mach mode, turning the SPEED knob then sets a magenta selected Mach number at the top of the IAS scale and correspondingly moves the notched-box symbol on the IAS scale.
11-24
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
IAS Reference Marker The magenta notched-box symbol is the IAS reference marker. The IAS reference marker is always selected for display and is set by the SPEED knob on the FCP. While in Mach mode, the IAS reference marker corresponds to the selected Mach number set in the reference field at the top of the IAS scale.
TO LOC 1
DR
IAS Reference Field
TO
3000
ALTS
2500M
200
80
80
60
60
40 VT 150 V2 133 VR 121 V1 113
10
40 VT 150 V2 133 VR 121 V1 113
300
1
200
200 240
2
10
1
220
100
200
000
180
1
20
FMS1
GS RA
6
DTK 333 12.7NM YUL
2
100
0FT TRU
FMS Computed V Speeds
4 2
0
V2 133
160
M.466
4
29.85 IN 2400M
IAS Reference Marker (Bucket)
TCAS OFF
E
3
12
N
Manually Entered V Speeds
8000
20
NO FLIGHT PLAN
15
33
TERM
VOR1
DISPLAY BEFORE TAKEOFF
TO LOC 1
DR
TO
3000
ALTS
TO LOC 1
1.0
2500M
200
T
20
2
10
8000
200
1
120 R
0
1
4
8000 300
30 2
1
160
2 1
200
20 1
T
100
1.0
140
0
10
100
2 000
20
100
1
80
0FT TRU
FMS1
6
50FT 10 TRU
TCAS OFF
FMS1
6
3
E
100 4 29.85 IN 2400M 1.2 TCAS 17 OFF
12
DTK 333 12.6NM YUL
GS RA
NO FLIGHT PLAN
VOR2
VOR1
15
15
33
TERM
33
TERM
1 2
4
12
NO FLIGHT PLAN
29.85 IN 2400M 9
E
N
3
GS RA
000
120
2
VOR2
VOR1
DISPLAY BEFORE ROTATION
P604_11_035
10
N
100
DTK 333 12.7NM YUL
3000 2500M
180
2
140
TO ALTS
200
4
300
2
DR
DISPLAY WHEN AIRBORNE
Speed Reference (Bug) Field Figure 11-13
For Training Purposes Only
May 03
11-25
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Altitude Displays Barometric Altitude Display The display simulates a rolling drum mechanism and is outlined by a white window. The present barometric corrected altitude displayed is the sum of the numeric “thousands” readout and the “hundreds” moving tape indication at the window. If barometric altitude data becomes invalid, the altitude displays are replaced with a red ALT annunciation.
NOTE A metric barometric altitude readout may also be displayed below the pressure display. This boxed readout with an “M” label displays the barometric altitude in meters. Fine Barometric Altitude Scale The fine barometric altitude scale is a vertical “moving tape” display. The display window range is 450 feet. The scale contains a line marking every 20 feet and a numeric label every 100 feet. The scale moves down for increasing altitude. Coarse Barometric Altitude Scale The coarse barometric altitude scale is a non-numbered vertical “moving tape” display that helps visualize (preselected) altitude captures. Large rectangles on the scale represent 1000-feet altitude increments and small rectangles represent 500-foot increments. The display window range is 2250 feet. The scale moves down for increasing altitude. Barometric Pressure Display Barometric pressure correction is numerically displayed in either inches of mercury or in hectopascals (hPa). The correction value and format are set by the on-side ADRP. Preselect Altitude Display The preselected altitude is numerically displayed in magenta above the barometric altitude scales. The ALT knob on the FCP sets the value.
NOTE A metric preselected altitude readout with an “M” label may also be displayed below the normal display. The boxed readout displays the preselected altitude in meters.
11-26
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
LNV1 DR LOC 1
VGP
1500
128
AP
180 160
4
500 81000
20
400
FMS VNAV Altitude
2
Coarse Altitude Scale
Fine Altitude Scale
400
1
10
300
T
140 120
Preselect Altitude
0.7
2500M
2 R
1
200
300
2 10
100
Preselect Altitude Bug (Coarse Scale)
1 2
20
100 M.576
1800FT TRU
FMS1
6
DTK 071 1.7NM ONB
3
200
Barometric Pressure Display
840
N
NO FLIGHT PLAN
33
S
HDG DR LOC 1
ALTS
22000
Selected Altitude Metric Readout
6710M AP
4
8000
200
20
280
2 1
100
10
260
22
240 220
800
20
M.584
TRU
FMS1
E
DTK 279 21.6NM HOKKE
000
100
10
GS RA
Preselect Altitude Bug (Fine Scale)
29.92 IN 6700M
1 2 4
Altitude Metric Readout
12
6
3
15 NO FLIGHT PLAN
N
S
TERM
2
VOR1
VOR2
P604_11_028
250
MDA
2
15
ADF1
000 29.96 IN 4 2400M 0.8
E 12
GPS APPR
GS RA
PFD Altitude Displays Figure 11-14
Preselect Altitude Bug The ALT set knob on the FCP is used to set the preselected altitude value. The preset altitude is displayed on the top of the altitude scale in magenta, and as a window on the coarse and fine altitude scales. This four-line marker displays on the coarse and fine barometric altitude scales to mark the preselected altitude value. The marker is always in view on the coarse barometric altitude scale and then shows on the fine barometric altitude scale when in range.
For Training Purposes Only
May 03
11-27
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
The preselected altitude display and bug both change colors and/or flash as the airplane acquires a preselected altitude. These displays are normally magenta. Both displays flash magenta when the airplane approaches the preselected altitude and then become steady again at altitude capture. Preselect Altitude Warnings Preselect altitude warnings provide aural and visual signals. The aural warning signal is a one-second C-chord tone. After capture, the digital display flashes amber for minor altitude deviations. The bug and numeric display both flash amber for major altitude deviations. The Air Data Computers use the preselected altitude data to initiate two different types of cues and warnings. These cues and warnings are initiated when the difference between the preselected and barometric altitude is greater than the programmed limits. The programmed limits are: • •
minor deviation is ± 200 feet major deviation is ± 1000 feet
(See Chapter 4 Automatic Flight Control System for additional altitude preselect tracking information) Preselect Altitude Cross-Side Tracking Each ADC receives the preselected altitude via its on-side ADRP and the cross data bus. The ADCs compare the preselected altitude values of the two computers. If the values are not equal due to a bus failure, the digital preselect altitude indication changes from magenta to cyan when the adjustment knob is turned. If full bus operation is recovered, the two sides will synchronize to the value held by the coupled side ADC. The indication returns to magenta after synchronization has been achieved. MDA Display The Minimum Descent Altitude (MDA) is numerically displayed below the altitude scale. The on-side ADRP is used to select this display and set the appropriate value. An MDA alert displays near the left center of the ADI when the airplane is at the Minimum Descent Altitude. During the MDA alert the icon flashes yellow. MDA Pointer A cyan pointer marks the selected Minimum Descent Altitude on the fine barometric altitude scale. This pointer appears when the MDA display is selected and the value is in the display range. This pointer flashes during an MDA alert.
11-28
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Decision Height Display The Decision Height value is selected for display and set by the on-side ADRP. If this display is selected, it is automatically displayed once the aircraft has descended through 2500 feet above ground. If Decision Height data becomes invalid, the numeric values are replaced with red dashes. A DH alert displays when the airplane is at or below Decision Height. On the right center of the attitude indicator, DH flashes in yellow, accompanied by the voice alert “MINIMUMS”. There is also a DH Pointer which marks the selected Decision Height on the analog radio altitude scale. This pointer appears when the DH display is selected and the value is in the display range.
VGP
LOC1
129
MDA Alert
AP
RWY
140
2 120
2
10
6
000
5
900
MDA 4
10
20 430FT
6
0
500
LOC1
6
CRS 071 1.0NM IOW
DH Display
TA ONLY MDA DH
NO FLIGHT PLAN
S
S
ADF1
E
3 N
840 100
1
300 29.85 IN 4 2400M 0.6
15
N
20 80FT
M.452
15
33
1
2
12
12
MDA DH
1
400
0.6 TA ONLY
NO FLIGHT PLAN
DH
R
10
4
2
600
100
2
E
3
700
10
1
29.85 IN 2400M
DTK 072 1.3NM RW07
ADF1
120
2
FMS1
GPS APPR
800
DH Alert “MINIMUMS” Voice Alert
4 3
2
T 140
700
M.452
RWY 20
2
3
900
AP
160
0
R
100
MDA Display
128
1
T
GS ALTS
4
20
160
DR
900
ALTS
840 102
P604_11_036
DR
33
LNV1
0 MDA POINTER
DH POINTER
MDA and DH Displays Figure 11-15
For Training Purposes Only
Jan 04
11-29
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Vertical Speed Display The current vertical speed is shown by a green pointer on a vertical white scale; the green pointer drags a green vertical line from the center of the scale. Vertical speed (when 200 feet/minute or greater) is numerically repeated at the bottom of the scale followed by an arrow pointing “up” for climb, or “down” for descent. The vertical speed is selected by using the VS/Pitch Wheel on the FCP and the magenta numerical value is displayed at the top of the Vertical Speed scale with a corresponding up or down arrow as selected. The FMS Vertical Navigation computer continuously calculates vertical speed required to reach the next point on the flight plan at the altitude required. The required vertical speed when greater than 500 fpm for FMS VNAV is displayed on the vertical speed scale in the form of a cyan circle.
NOTE For Precision-Plus-equipped aircraft, the cyan circle will be displayed if VNAV is selected or VNAV advisory enabled. TCAS advisories display on the VS scale as green or red lines. A green line shows a recommended “fly-to” range of vertical speeds. A red line shows “avoidance” or “exit” vertical speeds. TCAS modes and messages are also displayed below the VS scale as appropriate (see Chapter 17 Navigation Systems for further details).
11-30
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
4
30
VS Pointer
2
280
600 1
20 260
500
10 400
240
300
220
1 2
10
4
VS Digital Readout
Selected VS 4
20
800
10
700
280
2 1
320
600 300
10 280
500 1
400
20
VS Pointer
2
Selected VS Bug VS Digital Readout
4
4
160
20
800
T
2 1
140
10
700
2 R
600
120
500 100
10 400
VS Advisory
2 4
20
6
1
E
4
200
160
20 T
100
140
2 1
10 2
000
R
TCAS Resolution Advisory
120
900
10
1
800
4
20
S
2
21
P604_11_037
100
PFD Vertical Speed Display Figure 11-16
For Training Purposes Only
Sept 04
11-31
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Navigation Displays Vertical Deviation Display (GS, FMS and VNAV) The ILS glideslope vertical deviation display appears when all conditions are met. Use the on-side DCP to select FMS or LOC as the active NAV source. If deviation data becomes invalid, this display is replaced with a red GS (flag) annunciation. When conducting a back course approach, the scale displays without a pointer or flag annunciation. With LOC selected as the active NAV source, glideslope deviation is shown by the position of a diamond-shaped pointer relative to the deviation scale. The scale consists of two dots above and two dots below center. When the pointer moves to the top or bottom of the scale, it changes to a half diamond (triangle) pointing in the direction of the glideslope. A star against the same scale displays FMS glideslope vertical deviation. Marker Beacon Annunciation Marker beacon status is annunciated by a cyan boxed “OM” (Outer Marker), yellow boxed “MM” (Middle Marker), or by an empty white box (Inner Marker).
20
20 OM
MM
10
10 P604_11_050
10
20
Marker Beacon Annunciations Figure 11-17
Horizontal Situation Indicator (HSI) Function The PFD has a Horizontal Situation Indicator located at the bottom center. It consists of an airplane symbol and a compass rose. The compass rose is graduated in fivedegree marks, with numeric labels at every 10 degrees and letters at N, E, S and W. Airplane heading is read against the fore lubber line. Selected heading is set by the HDG knob on the Flight Control Panel, which moves a heading bug on both PFDs together. The digital value is displayed at the top left of the HSI while turning the HDG knob and remains displayed for a period of three seconds once HDG knob rotation is stopped. Selected course VOR, LOC or desired FMS track is digitally presented, and also displayed by an arrow. Course or track deviation is displayed against a scale centered on the airplane. Two bearing pointers are available to display bearing to navigation stations or a flight plan TO waypoint. 11-32
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Full Scale Deflection of Glideslope 1/2BNK
DR VS
HDG LOC1
GS
ALTS
2500
GS
AP
190
Glideslope Captured
4
500
4
20 10
300
160
200
140 M.452
2000FT20
VSPD
2
160
10
1
10
T
29.96 IN
600
180
400
2
700
2
200 1
10 180
2500
AP
173
2
200
GS ALTS PATH GS
600
20
FD2
DR
LOC1
0.9
500 400
T
2
140 M.452
4
2100FT
1
1
300
2
29.96 IN
4
20
0.6
VT 170 LOC1
LOC1
CRS 071
E
25
12
CRS 071
MDA
6
7.0H IOW
25
E
3
MDA
580
15
ADF1
33
S
N
N
580
12
3
6
15
8.9H IOW
ADF1
S
1/2BNK
LNV1
DR VGP
LOC1
128
900
ALTS PATH GS
RWY
AP
800
20 T
700
10 2
Heading Bug
2 1
140
120
FMS VNAV Glide Path Captured
4
160
1
R
600 500
10
100
M.452
400 29.96 IN
1200FT20
1 2 4
0.7
HDG 072
DTK 072 3.8NM RW07 N
MDA 15
ADF2
33
ADF1
25
E
12
GPS APPR MSG
6 3
840
P604_11_038
FMS1
S
PFD HSI Display Figure 11-18
For Training Purposes Only
Jan 04
11-33
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Multifunction Display Formats Various information can be displayed on the five different display formats available on the Multifunction Display (MFD). Weather Radar or EGPWS Terrain information can be overlaid only on the active (dynamic) maps: Nav Sector, FMS Map, and TCAS formats. The top two lines of all the different display formats present the following data (except for the remote text pages).
•
Radar mode line (top line): Weather Radar mode of operation, gain, antenna stabilization and tilt; this is replaced with TERRAIN when in Terrain mode of EGPWS Status line (bottom line): UTC time, True Airspeed, Ground Speed, Static Air Temp and Total Air Temp Radar Mode Line
LX/WX+TRB+GCS UTC 11:42
TAS 250
G+3 GS 254
USTB
T+10.7 SAT 12 C
TAT -15 C
Status Line
P604_11_048
•
MFD Radar Mode and Status Lines Figure 11-19
11-34
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
HSI Format This display shows navigation information in a traditional 360-degree full compass rose format.
NOTE Weather Radar, Terrain and TCAS information cannot be displayed in HSI format. The following sections are part of the HSI format: • •
Status Line: This line displays the current UTC time, True Airspeed (from ADC), Ground Speed (from FMS) and temperatures (from ADC) On-side Course Display: The (left) display window shows on-side course information in green, yellow or white (VOR / LOC on-side green, VOR / LOC cross-side yellow, FMS on-side white or FMS cross-side yellow). This information is the active NAV course data displayed on the on-side PFD
The top line annunciates the NAV source and shows a numeric course readout. The NAV source is selected on the DCP. The CRS readout shows the course to the selected navaid station or next waypoint (also indicated by a single-line course pointer). The next line is a station identifier and numeric distance readout. The station identification of the tuned navaid or next waypoint displays with the distance to that position (in nautical miles). The NAV source is boxed and red if the NAV data is invalid. •
Cross-side Course Display: The (right) display window shows cross-side course information in cyan. This information is the active NAV course data displayed on the cross-side PFD. A dual dashed-line course cyan pointer also indicates crossside course
NOTE Cross-side course information is selected or deselected for display by the PUSH X-SIDE switch on the DCP. Compass Rose The compass rose contains index markings every five degrees and alphabetic or numeric markings displayed at 30-degree intervals. Additional fixed index marks display outside the compass rose perimeter at 45-degree intervals with respect to the lubber line.
For Training Purposes Only
May 03
11-35
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Airplane Symbol A stationary airplane symbol displays in the center of the compass rose. This symbol points directly toward the lubber line. Lubber Line The lubber line is a fixed symbol at the top of the compass rose. The current airplane heading is the compass reading directly under the lubber line. Selected Heading Bug A heading bug symbol marks a selected heading reference. Turn the HDG knob on the FCP to move the heading bug around the compass rose. Momentarily pushing the center switch (PUSH SYNC) of the knob resets the heading bug to the current airplane heading. Selected Heading Display This display numerically shows the position of the selected heading bug. This display appears when the HDG knob is turned and disappears three seconds after rotation stops. Drift Angle Pointer This pointer is a small green circle that shows the airplane drift angle. Bearing Pointers There are two bearing pointers that may be selected for display (BRG buttons on DCP). One pointer is a single bar and the other pointer is a dual bar. Each pointer shows the bearing to a selected navaid station or the next FMS waypoint. The appropriate source for the bearing pointer is displayed below it. Course Pointers The on-side course pointer is a solid-line pointer. This pointer shows the on-side NAV course. This value is numerically repeated in the on-side course display. Push the DCP X-SIDE button to display the cross-side cyan course pointer. The cross-side course pointer is a dual dashed-line cyan pointer. This pointer shows the cross-side NAV course. This value is numerically repeated in the cross-side course display. To/From Symbol A triangle symbol shows “to” or “from” direction. This symbol turns as a part of the on-side course pointer and points toward the tuned station or next waypoint.
11-36
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Lateral Deviation Bars The lateral deviation bars are the center portions of the course pointers. Each bar moves left or right from the pointer to show lateral deviation from the NAV course. Lateral Deviation Scale The lateral deviation scale consists of four dots that display perpendicular to the onside course lateral deviation bar. Two dots display on either side of the airplane symbol. Vertical Deviation Display The ILS glideslope or the FMS VNAV vertical deviation display appears when all appropriate conditions are met. The on-side DCP selects LOC/FMS as the active NAV source. If, or as deviation data becomes invalid, this display is replaced with a red GS icon. When FMS VNAV deviation data is invalid, the deviation scale and pointer are removed. When making a back course approach, the scale displays without a pointer or flag annunciation. ILS/GS vertical deviation is shown by the position of a green diamond-shaped pointer relative to the deviation scale; whereas a white star pointer shows the FMS VNAV vertical deviation. The scale consists of two dots above and two dots below center. If GS deviation becomes excessive, the pointer and scale flash yellow.
RADAR OFF UTC22 : 40
TGT
TAS 0
GS 0
SAT
15C
TAT–15C
FMS1
DTK 333
FMS2
DTK 333
YUL
12.7NM
YUL
12.7NM
TTG
TTG
: 04
: 04
059 6
E
21
24
W VOR1
P604_11_039
S
30
15
33
12
N
3
MFD HSI Format Figure 11-20
For Training Purposes Only
May 03
11-37
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
NAV Sector Format This display shows navigation information on an enlarged section of the compass rose. The following sections are part of the NAV sector format. On-side Course Display The (left) display window shows on-side course information in green, yellow or white (VOR/LOC on-side green, VOR/LOC cross-side yellow, FMS on-side white or FMS cross-side yellow). This information is the active NAV course data displayed on the on-side PFD. Cross-side Course Display The (right) display window shows cross-side course information in cyan. This information is the active NAV course data displayed on the cross-side PFD.
NOTE Cross-side course information is selected or deselected for display by the PUSH X-SIDE switch on the DCP. Range Rings There are two range rings, which provide a distance scale to help visualize the airplane position relative to navaid symbols and weather radar targets. A distance annunciator displays by each ring. The RANGE knob (on the DCP) selects a desired display range. The possible full-scale ranges are 5, 10, 25, 50, 100, 200, 300 and 600 nm (maximum is 300 nm with WX selected on). The outer range ring is a 120-degree sector of the compass rose. This arc contains index markings every five degrees and alphabetic or numeric markings every 30 degrees. The inner range ring is a circle that is centered on the airplane. NAVAID Display The NAVAID display shows airplane heading, selected heading, on-side course, crossside course, bearing, vertical deviation and wind information. The sector format may display (only) two or three navaid symbols. These symbols are generated using bearing/distance information (not FMS map data). VORTAC symbols with station identifiers display if the two actively tuned VOR stations are within range and data is valid. The TO waypoint of the FMS flight plan will also display. No other navaid symbols display on the sector format.
11-38
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
LX/RADAR OFF
TGT
TAS 0
FMS1
DTK 333
YUL
12.7NM
GS 0
SAT
15C
UTC01 : 50
TAS 146
DTK 333
LOC1
CRS 059
YUL
12.7NM
IUL
8.5NM
TTG11 : 04
TTG11 : 04
059
TTG11 : 04
RADAR OFF
TAT–15C
FMS2
25
059
SAT
10C
TAT–13C
FMS2
DTK 030
YUL
12.7NM TTG11 : 04
10
HOKKE
12.5
5 CYUL
VOR1
TGT GS 145
NAV SECTOR
ABOVE BELOW
YUL
VOR2
ADF
SECTOR FORMAT WITH CROSS-SIDE DATA SELECTED AND WEATHER RADAR OVERLAY
NAV SECTOR
P604_11_040
UTC22 : 40
SECTOR FORMAT APPROACH
MFD Sector Format Figure 11-21
For Training Purposes Only
May 03
11-39
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
FMS Map Format This format shows a dynamic geographic depiction of the flight as it occurs. The map display is always centered on the airplane present position with current heading toward the top of the screen. The screen shows a moving map display of flight plan symbols and background navaid symbols relative to airplane present position.
NOTE An FMS data window may be displayed on the FMS map. Airplane Symbol This symbol is a reference used to visualize airplane position relative to the geographic map and radar targets. The airplane symbol is stationary and always displayed in the center of the screen. The navaid symbol, radar targets and flight plan line move down the screen as the flight progresses. Range Rings There are two range rings displayed, which provide a distance measuring scale. These rings show distance from the airplane. A distance annunciator displays by each ring. The RANGE knob (on the DCP) selects a desired display range. The possible fullscale ranges are the same as for NAV Sector format. NAV Display The NAV display shows the FMS flight plan line and a background navigation map. The map consists of navaid symbols generated from the FMS database. The FMS flight plan displays on the map as a solid white line. This track line consists of straightline segments connecting consecutive flight plan waypoints. The TO waypoint displays in magenta. FMS-generated navaid and map symbols are cyan. Data Window The data window displays FMS progress parameters for the FROM, TO, NEXT and Destination waypoints in the flight plan. The CDU is used to select the various options of the data window. The data window can be selected to ON, COMP, VNAV, or OFF.
11-40
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
TAS 342
UTC01: 07
USTB
G+3
LX/RADAR OFF
T+10.7 T+5.0
GS 342
TAT-13C
SAT-29C
LEFT DISPLAY MENU MAP DISPLAY HI NAVAIDS
YOW /2900 [ 2900 ] /2900A RW32 YRENS /2600 TEXEN
LO NAVAIDS
1/2 NDBS ETA
/2600A
INTERS 50
ARPTS
THURO
ABOVE BELOW
25 HOKKE
DME1
DME2
YUL 21.1
YUL 21.2
TERM WPTS WINDOW OFF OFF/ON/VNAV/COMP [
SPEED ALTITUDE MISS APPR SIDE L/R> ]
OFF
TAS 341
YUL HOKKE THURO CYOW
23NM 1NM 18NM 58NM
T+10.7 T+5.0
GS 0
0:00 0:03 0:14
TAT-13C
SAT-29C
00:55 01:08 01:11 01:21
LEFT DISPLAY MENU 9670 LB
37.0GW
280 RW32 YRANS 2600 TEXEN 2600A
MAP DISPLAY HI NAVAIDS LO NAVAIDS INTERS ARPTS
50
THURO
ABOVE BELOW
25
DME1
DME2
HOKKE
YUL 23.4
YUL 23.4
YUL
VOR1
TAS 345
UTC01: 06
YUL HOKKE THURO CYOW
15NM 9NM 26NM 66NM
GS 0
3.3° 2600A 0:11/
ON
56NM
LEFT DISPLAY MENU MAP DISPLAY HI NAVAIDS LO NAVAIDS INTERS
THURO
ARPTS
50 HOKKE
DME1
DME2
YUL 15.6
YUL 15.6
YUL
VOR1
CRS
IUL
8.5NM
TTG11 : 42
GS 343
SAT –29C
DTK 030
YUL
12.7NM
279
TTG11 : 04
LEFT DISPLAY MENU MAP DISPLAY HI NAVAIDS
INTERS
THURO
ARPTS
25 HOKKE ABOVE BELOW
DME1
VOR1
SIDE L/R> ]
VNAV
LO NAVAIDS
YUL 18.8
ETA
SPEED ALTITUDE MISS APPR
TAT–13C
FMS2
TEXEN 26000A
50
NDBS
TGT
TAS 343
LOC1
TERM WPTS WINDOW OFF/ON/VNAV VNAV /COMP [
1/2
ADF2
RADAR OFF UTC01 : 07
SIDE L/R> ]
TAT-13C
2000
280
25
ETA
SPEED ALTITUDE MISS APPR
T+10.7 T+5.0 SAT-29C
: 0:02 : DIRECT 0:05 : TEXEN 0:15 :
26000A
ABOVE BELOW
NDBS
ADF2
USTB
G+3
LX/RADAR OFF
TERM WPTS WINDOW OFF/ON ON /VNAV/COMP [
1/2
DME2
YUL NAV SECTOR
YUL 18.8
TERM WPTS WINDOW OFF/ON/VNAV/COMP COMP [
1/2 NDBS ETA
SPEED ALTITUDE MISS APPR SIDE L/R> ]
P604_11_041
UTC01: 06
USTB
G+3
LX/RADAR OFF
COMP
VOR2
MFD Data Window Figure 11-22
For Training Purposes Only
May 03
11-41
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Plan Map Format This format shows a static geographic depiction of a section of the flight plan (or a selected route). Use this map as a visual aid to enter a new flight plan/route or to plan a deviation from the flight plan/route. The plan map is always presented with true North at the top of the screen. This screen shows flight plan/route symbols and background navaid symbols within range. The (dynamic) weather radar, terrain and TCAS cannot be overlaid onto the (static) plan map. Optional “Precision Plus” FMS upgrades incorporate a 3D-map capability on the plan map page. Range Ring A range ring provides a distance measuring scale. This ring shows distance from the center waypoint. The range rings also display a range distance. The RANGE knob on the DCP selects the desired range. The possible full-scale ranges are 5, 10, 25, 50, 100, 200, 300, and 600 nm. NAV Display The NAV display shows the FMS flight plan or route line and a background navigation map. The map consists of navaid symbols generated from the FMS database. The FMS-generated navaids and map symbols are cyan. The active FMS flight plan/route displays on the map as a solid white line. This track line consists of straight line segments connecting consecutive waypoints. The TO waypoint displays in magenta.
TAS 378
UTC 22:48
THURO AGLIN FANOL CYOW
USTB
G+3
LX/RADAR OFF
4NM 9NM 16NM 29NM
GS 378
20:48 0:02 0:04 0:09
20:48 20:50 20:52 20:57
T+10.7 SAT-9C
TAT 10C
20:48 20:50 20:52 6930 LB 343GW
25
DME1 ––––
TO WPT UNLOCKED
THURO
DME2 ––––
V=000° L=360T
P604_11_042
AGLIN FANOL TEFLY /2500A FF25 /2500A RW25 /2600A TOC ONE 774A /2600
MFD FMS Plan Map Format Figure 11-23
11-42
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
TCAS Format The TCAS format provides a dynamic map with a complete 360-degree circular representation which is dedicated to TCAS information. Weather radar information can be overlaid on this page. For further details on TCAS see Chapter 17 Navigation Systems. USTB
LX/WX UTC04:30
TAS 0
GS 0
T+10.7 T+5.0 SAT 15C
TAT 15C
FMS2 YUL
-10
-04
P604_11_043
10
MFD TCAS Format Figure 11-24
For Training Purposes Only
May 03
11-43
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Radio Altimeter Description The radio altimeter measures direct radio height (distance above terrain) for use by the Flight Control Computers (FCCs) and for display on the PFDs.
Components and Operation The radio altimeter (RA) system consists of the following components: • • • • •
one Receiver/Transmitter one Radio Altitude Converter one Transmit Antenna one Receive Antenna Associated Components: • two Air Data Reference Panels (ADRPs) • two PFD Indicators
NOTE In order to conform to JAA CAT II certification requirements, service bulletin 604-34-005 indicates that the installation of a second RA is required. Receiver/Transmitter The receiver/transmitter transmits, receives and processes RF signals to provide a display of radio altitude and decision height information on the pilot’s and copilot’s PFDs. The receiver/transmitter performs this function by measuring the difference in frequency between the transmitted and received signals. Internal monitoring and selftest capabilities are also provided. Antennae The system uses two identical, linearly polarized antennae, flush-mounted on the underside of the airplane along the centerline. The forward antenna is used to transmit and the aft antenna to receive.
11-44
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Radio Altitude Display The radio altitude of the aircraft is displayed both in digital and analog format on the PFD. This numeric display appears at the bottom of the attitude indicator as the airplane descends through 2500 feet above ground level (AGL) and disappears as the airplane climbs through 2500 feet AGL. Analog Radio Altitude Scale A small window appears at the center of the scale as the airplane descends through 1250 feet AGL. This window marks the current radio altitude. This value is numerically repeated in the bottom portion of the attitude indicator. An analog radio altitude scale appears as the airplane descends through 1100 feet AGL. This analog scale is used in conjunction with the ground bar (rising runway) to assist in visualization of the aircraft’s height above terrain. The scale contains line marks and single-digit numeric labels. Each digit indicates 100 feet of radio altitude.
NOTE At Decision Height (DH), the numeric label and scale change from green to yellow. Ground Bar (Rising Runway) A ground bar displays on the analog radio altitude scale to represent the terrain. As the airplane descends through 200 feet AGL, the ground bar rises on the analog scale. At 0 feet radio altitude, the top of the ground bar aligns with the center of the scale.
For Training Purposes Only
May 03
11-45
11-46 30
29
20
1100FT
20
1200FT
20
2500FT
20 30
1
10
10
10
1
20
20
10
10
1
10
20
10
10
P604_11_025
0’
200’
1100’
1200’
2500’
3000’
Note: Not to Scale
30
1
200FT
20
10
10
20
0
30
1
2
3
4
20
0FT
10
10
20
0
30
1
2
FLIGHT INSTRUMENTS PILOT TRAINING GUIDE
Radar Altimeter Display
Figure 11-25
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Standby Instruments The standby instruments include an airspeed indicator, altimeter, attitude indicator and compass.
Standby Instruments Locator Figure 11-26
Standby Airspeed Indicator The airspeed indicator supplies non-corrected (indicated) airspeed. It uses the standby pitot source P3 and the standby static ports S3.
Speed Pointer Indicates speed readout in knots indicated
60 100 400 IAS 150 KTS 200 300 250
P604_11_019
350
Standby Airspeed Indicator Figure 11-27
For Training Purposes Only
May 03
11-47
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Standby Altimeter The standby altimeter incorporates an altitude pointer and an altitude counter. The altitude pointer and altitude counter operate through a mechanical linkage connected to a pressure capsule. The pressure capsule moves with changes in static pressure. Barometric correction is selected by a knob at the bottom right of the instrument and displayed in inches of mercury and hectopascals. The instrument receives its static pressure from the standby static ports S3. Altitude Counter Indicates barometric altitude from - 1,000 to 50 000 feet, in 1,000 foot increments.
Altitude Pointer and Scale Pointer indicates altitude in 100-foot increments as read from scale. Full circle for each 1,000 feet of altitude.
0
1 2 2 3000 4 9
7
mb/hPa
ALT
in Hg
2
Barometric Pressure Indicators Indicates selected barometric pressure as expressed in hectopascals or inches of mercury.
3
1014 6 5 2992 4
P604_11_020
Barometric Set Knob Used to change barometric pressure values as read at hPa/in Hg readouts. Range for this standby Instrument is as follows: ! from 952 to 1049 mb/hPa and ! from 28.02 to 30.99 in Hg.
Standby Altimeter Figure 11-28
Standby Attitude Indicator The standby attitude indicator has an electrically-operated vertical gyroscope. The gyroscope is mechanically connected to the sphere to show attitude information. To cage or uncage the instrument, the PULL TO CAGE knob is pulled and turned. When the instrument is uncaged, the cage knob is turned to adjust the pitch reference.
Power Off Flag Appears when power to indicator is lost or during gyro failure. Gyro will continue to run for approximately 9 minutes after power is lost.
OFF
CLI
MB
DI
VE
Fixed Airplane Symbol Indicates roll and pitch attitude relative to the horizon.
Horizon Line
LL TO C AG
E
P
U
Caging/Pitch Adjust Knob
P604_11_021
Roll/Sky Pointer Indicates bank angles referenced against roll index.
Sphere Indicates airplane movement in pitch. Marked at 5-degree increments
Roll Scale and Index Markings at 10, 20, 30, 45 and 90 degrees.
Standby Attitude Indicator Figure 11-29
11-48
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Standby Compass The standby magnetic compass is a self-contained dry unit, which uses eddy current damping to prevent overshooting. The standby compass is installed below the overhead panel.
STANDBY COMPASS WITH ALL RADIOS ON SWUNG
TO FLY
N
30
60
E
120
150
S
BY
210
240
W
300
330
STEER
Magnetic Compass Indicates heading of airplane in relation to magnetic north.
6 E 12
P604_11_022
33 N 3
24 W 30
Fixed Airplane Symbol
Rotating Compass Dial
15 S 21
Compensating Screws
Standby Compass Figure 11-30
For Training Purposes Only
May 03
11-49
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Aircraft Clocks The digital clocks are located on the side panels of the pilot and copilot. The clocks can display local time, flight time and elapsed time. Starting with A/C 5331, the clocks have been changed to add a GMT time display. Set Switch ! Sprung to center position. ! Hold to left (UP) position advances clock 1 second for every second held. ! Hold to right (D) position retards clock 1 second for every second held.
Bright/Dim Switch ! Select B for bright display. ! Select D for dim display. ! Select 1 hr up momentary position and release to advance clock 1 hour.
Minutes
D
UP SET
B
1hr up DIM
Hours Time Switch ! Select TIME to display local or standard time. ! Select F.T. to display flight time. ! Select E.T. to display elapsed time.
DAVTRON
TIME F. T. E.T.
ZERO s t o p RUN
Elapsed Time Switch ! ZERO momentary position sets elapsed time to zero. Also zeros flight time if aircraft power is removed. ! STOP position stops elapsed time meter. ! RUN position starts elapsed time meter.
Press To Reset
Press to Reset Allow the clock's flight time recorder to be reset to zero without turning off aircraft electrical power
P604_11_026
Seconds
Clock Prior to A/C 5331 Figure 11-31
11-50
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
M877 Greenwich Mean Time Local Time 12-hour format with 24-hour option
CHRONOMETER
12 00 GMT LT
FT
Elapsed Time
ET
Flight Time
SELECT SEL
CONTROL CTL
Audio Alarm Speaker Select Button ! To select GMT, LT, FT, ET and back when momentarily pressed. ! To turn off alarm.
Control Button ! Starts and resets elapsed time when momentarily pressed. ! Press and hold for 3 seconds for test mode. ! With FT selected, press and hold for 3 secs to reset flight time. ! To turn off alarm.
Note: Press SEL and CTL buttons simultaneously to enter set mode for GMT, LT, FT and ET Countdown
P604_11_049
DAVTRON
Clock A/C 5331 and Later Figure 11-32
For Training Purposes Only
May 03
11-51
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
Display Reversionary Panel The display reversionary switches on the Display Reversionary Control Panel are used to select the desired reversion mode of the L(R) MFD. Both the L MFD and the R MFD can be set to one of three positions: • • •
Norm: The MFD operates in the NORM position and displays navigation, weather radar, terrain or TCAS information as selected on the Display Control Panel PFD: By turning either the L MFD or the R MFD rotary selector to PFD, the associated PFD is now transferred to the selected MFD EICAS: By turning either the L MFD or the R MFD rotary selector to EICAS, the STATUS page will be displayed on the selected MFD. The EICAS Control Panel then controls EICAS page selections
Abnormal Conditions In the event of a DCP failure, a red boxed DCP shows on the affected PFD. To allow selection of the operating DCP, a reversionary selector switch is provided on the reversionary panel. This switch has three positions, NORM, 1, or 2. In the NORM position, each DCP controls its own MFD. In either the 1 or the 2 position, the remaining DCP controls the display on both MFDs.
11-52
For Training Purposes Only
May 03
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
AIRSPEED LIMITS - (INDICATED SPEEDS)
10
VOR1 YUL TTG--:--
2
200
1
TAS 0
SAT 15 C
GS 0
CRS 012 12.7NM
VT 150
TTG --:--
N1
N
000 1
LL
GS RA
29.92 IN 2400M
FEET X 1000
2
E
TO C AG
0.0
WX+TRB
100
323
UTC 11:01
CYUL LONNA ALEXS CYUL
TAS 0
GS 0
1NM 12NM 20NM 111NM
SAT 15 C
11:02 11:05 11:07 11:25
0:03 0:04 0:23
EGT
RPM
47
CABIN TEMP
23
BLEED PRESS
0
35.6GM
- GEAR -
OIL TEMP FAN VIB
- FUEL (LBS) - TOTAL
W 24
ADF 2
- TRIM -
STAB NU
20
8100
5.0
ENGINE
15
BULK
00
LONNA
25
NL
C ALT
100
RATE
0
YUL 12.7
000
20
100
0FT TRU
29.92 IN 2400M
2 4
TCAS OFF
E
3
LONNA
GS RA
6
DTK 056
12.2NM
DME 2 ––––
CYUL
1
100
10
1
RA2 IRS2 ADC2 DCP2
FMS2 DME 1
1820
OXY
TERM
RWD
RUDDER
ND
ADF2
TOC
V1 113
2
200
1
0
V2 133 20
35
4
300
2 4
VT 150
E
3
12.5
LWD
4050
36
AIL
10
40
SPOILERS
NR
VOR 1
0.0
P
FMS MAP
ADF 2
T
T
T
T
T
T
ED 1
EICAS EIC
BR
BR
BR
BR
BR
BR
EICAS
NORM
R MFD NORM
NORM ED 2
EICAS AS
PFD PF
ADC
DCP
NORM 1
ADF2
VOR1
L MFD PFD D
15
0 0
4050
VOR 1
- FLAPS -
DN DN DN
0 0 33 0.0
3000 2500M
8000
20
60
VR 121
N2 FF (PPH) OIL PRESS
TO ALTS
200 80
TAT 15 C
7137LB
059
12
15
33
TO DR LOC 1
APU R FUEL PUMP ON L FUEL PUMP ON DOOR CLOSED PARKING BRAKE ON PROX SYS FAULT FDR FAIL
0.0
0 0 33 0.0
S
N
4
12
NO FLIGHT PLAN
0.78 318 0.85 197 197 250
ALEXS
TERM
VOR1
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
30
45
0
FUEL TEMP
TCAS OFF
E
3
8
CABIN 10 ALTITUDE
20
4
2
30
TRU
6
DTK 333
12.7NM
100
33
20
0FT
15
RA2 IRS2 ADC2 DCP2
21
10
FMS1 YUL
6 2 3
12
00
ALT
E
3
12
V1 113
180
1 9 2 2 3 000 4
1014 6 5 2992 4
ITT
V2 133 20 VR 121
7
R ENG OIL PRESS L ENG OIL PRESS L WSHLD HEAT L WINDOW HEAT INBD BRAKE PRESS R WSHLD HEAT R WINDOW HEAT OUTBD BRAKE PRESS R PROBE HEAT OFF L PROBE HEAT OFF HYD 3 LO PRESS
0.0
DTK056 12.2 NM
6
100
VE
P
0.0
TAT 15 C
FMS2 LONNA 059
1
180
0
MB
DI
U
WX + TRB UTC 11:01
4
300
2 4
CLI
KTS 200 300 250
N
3000 2500M
8000
20
40
OFF
350
33
TO ALTS
60
0
60 100 400 IAS 150
0.78 318 0.85 197 197 250
N
TO DR LOC 1 200 80
AIRSPEED LIMITS - (INDICATED SPEEDS)
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
NORM 2
1
2
REVERSIONARY SELECTORS DISPLAY REVERSIONARY CONTROL PANEL AIRSPEED LIMITS - (INDICATED SPEEDS)
AIRSPEED LIMITS - (INDICATED SPEEDS)
4 2
N1 1
200
1
180
0
40
VT 150
V1 113 00
1 9 2 2 3 000 4
ALT
6 2
180
100
10
FEET X 1000
2
20 TRU
FMS1
6
OIL TEMP FAN VIB
- FUEL (LBS) - TOTAL
- FLAPS -
20
36
DN DN DN
0 0 33 0.0
23
BLEED PRESS
0
8100
5.0
V1 113
NL
SPOILERS
NR
1820
C ALT
100
RATE
0
DTK 056 12.2NM LONNA
0.0
P
1
RA2 IRS2 ADC2 DCP2
20 TRU
6
3
2
100
0FT
GS
4
29.92 IN 2400M
RA
TCAS OFF
E
ADF2 BR
BR
BR
T
T
T
R MFD NORM
NORM ED 2
ED 1
EICAS EIC
000
VOR1
T
T
T
EICAS
NORM
10
FMS2
OXY
BR
BR
BR
L MFD PFD D
1
100
TERM
RWD
RUDDER
ND
00
BULK
AIL
LWD
4050
ADF2
0
V2 133 20
35
ENGINE
15
- TRIM -
STAB NU
2
200
1
15
0 0
4050
15
33
FF (PPH) OIL PRESS
4
300
2 4
10
VT 150
12
NO FLIGHT PLAN TERM
VOR1
CABIN TEMP
VR 121
- GEAR -
0 0 33 0.0
TCAS OFF
E
3000 2500M
8000
20
60
47
N2
TO ALTS
200 80
FUEL TEMP
29.92 IN 2400M
RA
N
3
323
0.78 318 0.85 197 197 250
EGT 40
0.0
4
12
DTK 333 12.7NM YUL
GS
TO DR LOC 1
APU 100
RPM
2
100
0FT
0.0
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
30
45
0
R FUEL PUMP ON L FUEL PUMP ON DOOR CLOSED PARKING BRAKE ON PROX SYS FAULT FDR FAIL
000 1
RA2 IRS2 ADC2 DCP2
8
CABIN 10 ALTITUDE
20
4
3
1014 6 5 2992 4
ITT
V2 133 20 VR 121
7
LL TO C AG
R ENG OIL PRESS L ENG OIL PRESS L WSHLD HEAT L WINDOW HEAT INBD BRAKE PRESS R WSHLD HEAT R WINDOW HEAT OUTBD BRAKE PRESS R PROBE HEAT OFF L PROBE HEAT OFF HYD 3 LO PRESS
0.0
300
2 4
10
VE
P
0.0
2500M
8000
20
MB
DI
U
3000
ALTS
60
CLI
KTS 200 300 250
N
TO
OFF
350
33
TO DR LOC 1 200 80
0
60 100 400 IAS 150
0.78 318 0.85 197 197 250
E
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
EICAS AS
PFD PF
Display Reversionary Selector must be selected to display PFD on MFD
10
R FUEL PUMP ON L FUEL PUMP ON DOOR CLOSED PARKING BRAKE ON PROX SYS FAULT FDR FAIL
4
300
2 4
2
200
1
1
100
VT 150 VR 121 V1 113 00
FMS1
000
20 0FT TRU RA
100
6
GS
29.92 IN 2400M
6 2 3
LL
8
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
CABIN 10 ALTITUDE
20
4 2
FEET X 1000
30
45
0
TO C AG
180
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
0
TO DR LOC 1
100
323
ENGINE
47
SPOILERS
ADF2
RATE
0
P
FF (PPH) OIL PRESS OIL TEMP FAN VIB
- FUEL (LBS) - TOTAL
4050
0.0
0 0
0 0 33 0.0
- FLAPS -
20
36
DN DN DN
8100
15
- TRIM -
STAB NU
5.0
LWD
4050 ND
AIL
BLEED PRESS
0
V1 113
SPOILERS
NR
1820 100
RATE
0
20 0FT TRU RA
100
1
RA2 IRS2 ADC2 DCP2
FMS2 DTK 056 12.2NM LONNA
000
6
3
GS
29.92 IN 2400M
2 4
TCAS OFF
E
0.0
VOR1
ADF2
T
NORM ED 2
P
BR
ED 1
00
35
BULK
T
EICAS EIC
T
T
T
T
EICAS
NORM
ENGINE
OXY C ALT
BR
BR
BR
BR
BR
L MFD PFD D
1
100
10
TERM
RWD
RUDDER NL
0
V2 133 20
FUEL TEMP
0 0 33 0.0
2
200
1
15
100
4
300
2 4
12
1820
10
VT 150
23
VR 121
- GEAR -
35
BULK OXY C ALT
3000 2500M
8000
20
60
40
0.0 N2
15
TO ALTS
200 80
EGT
RPM
CABIN TEMP
0.0
0.78 318 0.85 197 197 250
APU R FUEL PUMP ON L FUEL PUMP ON DOOR CLOSED PARKING BRAKE ON PROX SYS FAULT FDR FAIL
FUEL TEMP 36
15
33
ALT
ITT
23
TERM
VOR1
1 9 2 2 3 000 4
1014 6 5 2992 4 E
P
180
4
TCAS OFF
E
N
3
NO FLIGHT PLAN
BLEED PRESS
7
R ENG OIL PRESS L ENG OIL PRESS L WSHLD HEAT L WINDOW HEAT INBD BRAKE PRESS R WSHLD HEAT R WINDOW HEAT OUTBD BRAKE PRESS R PROBE HEAT OFF L PROBE HEAT OFF HYD 3 LO PRESS
0.0 N1
47
VE
2
12
DTK 333 12.7NM YUL
10
1
RA2 IRS2 ADC2 DCP2
0.0
323
100
CABIN TEMP
V2 133 20
MB
DI
U
EGT
RPM
0
CLI
KTS 200 300 250
APU
3000 2500M
8000
20
40
OFF
350
N
TO ALTS
60
0
60 100 400 IAS 150
0.78 318 0.85 197 197 250
33
TO DR LOC 1 200 80
AIRSPEED LIMITS - (INDICATED SPEEDS)
189 MMO (22,150FT TO 26,570FT) 197 VMO (26,570FT TO 30,990FT) 231 MMO (30,990FT TO 41,000FT) VLO (EXT) (L/G EXTENSION) 248 VLO (RET) (L/G RETRACTION) 187 VLE (L/G EXTENDED) 300 348
P604_11_004
AIRSPEED LIMITS - (INDICATED SPEEDS)
VFE (45 FLAPS) VFE (30 FLAPS) VFE (20 FLAPS) VA (MANEUVERING) (AT SEA LEVEL 48,200LB) (AT 20,000FT 26,000LB) VNO (BELOW 8,000FT) VNO (8,000 TO 22,150 FT)
R MFD NORM EICAS AS
PFD PF
Display Reversionary Selector must be selected to display EICAS on MFD
Display Reversionary Panel Figure 11-33
For Training Purposes Only
May 03
11-53
FLIGHT INSTRUMENTS
PILOT TRAINING GUIDE
EICAS Messages MESSAGE
AURAL WARNING (IF ANY)
MEANING
EFIS COMP MON
Indicates mismatch detected between on-side and cross-side data.
EFIS COMP INOP
EFIS comparator has failed.
EICAS Messages Table 11-1
11-54
For Training Purposes Only
May 03
