MAINTENANCE MANUAL

PITOT / STATIC SYSTEM — ADJUSTMENT / TEST

1. Air Data System — Functional / Leak Test
NOTE: This procedure allows for recertification of an Air Data Module (ADM) while installed on aircraft.
This procedure meets requirements of Federal Aviation Regulations (FARs) 91.411 and 43
(Appendix E) for all Reduced Vertical Separation Minimums (RVSM) certified and non-RVSM
certified aircraft.
This procedure can be used for system recertification if performed by a certified repair station.
If ADM being installed has a valid certification sticker per FAR 91.411, only a reconnect check is
required. See Pitot / Static System - Reconnect Check, 34-13-00, Inspection / Check or Code
341030.
This procedure can be used to verify the following:
• Pilot pitot / static system
• Copilot pitot / static system
• Both pilot and copilot pitot / static system
A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT

Air data test set ...................................................................................... GSE3400217 or equivalent

Circuit breaker safety clips .................................................................... GSE2400984 or equivalent
Pitot / static pressure test kit ................................................................. GSE3400304 or equivalent
Power Supply ......................................................................................... GSE2400108 or equivalent
NOTE: It is recommended to use high temperature adapters when performing procedure.
(1) References
• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices
• External Electrical Power Application, 20-20-10, Maintenance Practices
• Pitot / Static System - Reconnect Check, 34-13-00, Inspection / Check or Code 341030
• Pitot / Static System Probes / Lines - Contamination Check, 34-13-00, Inspection /
Check or Code 341300
• Birdstrike Plate - Removal / Installation, 53-02-01, Removal / Installation or Code
530205
• Radome - Open / Close, 53-02-01, Maintenance Practices
(2) Aircraft Preparation
NOTE: It is not necessary to disconnect Cabin Pressure Acquisition Module (CPAM) during
test.
(a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance
Procedure, 20-00-00, Maintenance Practices.
(b) Open and secure radome. See Radome - Open / Close, 53-02-01, Maintenance
Practices.
(c) Remove birdstrike plate. See Birdstrike Plate - Removal / Installation, 53-02-01,
Removal / Installation or Code 530205.
(d) Comply with the following on pitot / static system:
1 Ensure pitot / static system is free from entrapped moisture, restrictions and
contamination.

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2 Ensure no alterations or deformations of pitot / static probes affect relationship

between static system and true ambient static air pressure for any flight
condition.
3 Ensure all pitot / static lines are properly connected.
CAUTION: OPERATING KOLLSMAN TEST SET IN AUTO-EXERCISE / CAL / SELF-
TEST MODE WHILE CONNECTED TO AIRCRAFT WILL CAUSE
COMPONENT FAILURE.
BOTH PITOT AND STATIC SYSTEMS SHOULD BE RUN UP AT SAME
TIME OR DAMAGE TO INTEGRATED STANDBY INSTRUMENT CAN
OCCUR.
OPERATING RATE OF CLIMB >3000 FEET PER MINUTE MAY
DAMAGE SYSTEM COMPONENTS.
OPERATING STATIC SYSTEM AT A RATE >100 KNOTS PER MINUTE
MAY DAMAGE SYSTEM COMPONENTS.
USING SNOOP / LEAKTEK AROUND PITOT / STATIC PROBES MAY
DAMAGE PROBES.
(e) Connect test set to applicable pitot / static systems. See Figure 501.
NOTE: Refer to manufacturer’s instructions on proper connection and checkout of
test set.
If using Kollsman test set, do not operate auto-exercise, calibrate or self-test
mode with test set connected to aircraft.
(f) Determine test altitude using the following:
1 Obtain local barometric field pressure in Inches of Mercury (inHg) from local
airport authority or certified barometer.
2 Find obtained field pressure on chart and determine test altitude. See Figure 502.
3 Record test altitude
(g) Apply electrical power to aircraft. See External Electrical Power Application, 20-20-10,
Maintenance Practices.
(h) On aircraft having pneumatic cabin differential 3 in 1 indicator, select STATIC
SELECTOR valve to OFF.
(i) Pull, tag and install safety clips on the following Circuit Breakers (CB):

CB NAME CB PANEL CB LOCATION

L LWR PITOT HTR Pilot ANTI-ICE
L UPR PITOT HTR Pilot ANTI-ICE
R LWR PITOT HTR Copilot ANTI-ICE
R UPR PITOT HTR Copilot ANTI-ICE

NOTE: On Plane Connect aircraft; before putting aircraft in flight mode pull, NAV /
COMM CB.

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(j) Ensure the following CBs are depressed.

CB NAME CB PANEL CB LOCATION

ADM #1 Pilot FLT INSTRUMENTS
ADM #3 Pilot FLT INSTRUMENTS
STBY EBDI Copilot FLT INSTRUMENTS
ADM #2 Copilot FLT INSTRUMENTS

(k) On Cockpit Overhead Panel (COP), select / verify switches as follows:

• DISPLAY UNIT CONTROL Section
– DU 1 switch NORM
– DU 2 switch NORM
– DU 3 switch NORM
– DU 4 switch NORM
• ANTI ICE HTR Section
– PROBE / PRI switch OFF (extended)
– PROBE / STBY switch OFF (extended)
NOTE: CAS shall be monitored for any overheat or miscompare warnings.
(l) On IRS MODE SELECT panel, select switches as follows:
• IRS NO. 1 switch on (depressed)
• IRS NO. 3 switch on (depressed)
• IRS NO. 2 switch on (depressed)
(m) On Flight Guidance Panel (FGP), press PFD-CMD push-button to select L.
(n) On both pilot / copilot Display Controllers (DCs), comply with the following:
1 Press NAV push-button ON.
2 At DC Cathode Ray Tube (CRT), press NAV line select key until 1 (pilot) / 2
(copilot) is boxed.
3 Press PFD push-button ON.
4 At DC CRT, comply with the following:
a Press ADI line select key.
b Press BARO line select key to select IN for barometric display.
c Press METRIC ALT line select key until METRIC ALT is not boxed
(selected).
5 Press SENSOR push-button ON.
6 At DC CRT, press ADS line select key until 1 (pilot) / 2 (copilot) is boxed.
7 Press BARO knob PUSH STD push-button.
(o) On both pilot / copilot Primary Flight Display (PFD) and integrated Standby Flight
Display (SFD), verify displayed barometric pressure indicates 29.92.

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(p) At both pilot / copilot DC CRT, press ADS line select key until 2 is boxed.
(q) On pilot and copilot PFD, verify ADS 2 message (amber) is displayed above altitude
tapes.
(r) On both pilot / copilot DC, press and release BARO knob PUSH STD push-button.
(s) On both pilot / copilot PFD, verify displayed barometric pressure indicates 29.92.
(t) At both pilot / copilot DC CRT, press ADS line select key to select 3.
(u) On pilot and copilot PFD, verify ADS3 message (amber) is displayed above altitude
tapes.
(v) On both pilot / copilot DC, press BARO knob PUSH STD push-button.
(w) On pilot and copilot PFD, verify displayed barometric pressure indicates 29.92.
(x) On pilot / copilot DC, comply with the following:
1 If verifying ADM No. 1 and No. 2, select as follows:
• Pilot: ADS 1
• Copilot: ADS 2
2 If verifying ADM No. 1 and No. 3, select as follows:
• Pilot: ADS 1
• Copilot: ADS 3
3 If verifying ADM No. 2 and No. 3, select as follows:
• Pilot: ADS 3
• Copilot: ADS 2
4 If verifying all ADMs, use pilot / copilot DC to select between ADS 1 / 2 / 3 to take
applicable readings.
B. Procedure
NOTE: The following procedures are provided to test pitot / static system:
• Pitot / Static System Lines - Leak Check: Step 1.B.(1)
• Air Data System - Altitude Hold / Alert Checks: Step 1.B.(2)
• Pitot / Static System - Accuracy Check: Step 1.B.(3)
(1) Pitot / Static System Lines - Leak Check
(a) On pitot / static test set, comply with the following:
1 Perform leak check on test set and plumbing breakout box. Record information.
NOTE: Ensure leak rates are within tolerance provided in operation manual.
Because Static Source Error Correction (SSEC) has not been engaged,
cockpit indications for altitude and airspeed will not be same as those at
test set. Accuracy of altitude and airspeed will be validated later in this
procedure. The purpose of this test is to determine leak rate and
nonexistence of cross-plumbing.
2 Adjust airspeed to 100 knots per minute.
3 Adjust airspeed to 300 knots and allow system to stabilize for 1 minute, then
monitor leak rate of pitot system for a minimum of 1 minute. Record information.

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4 Subtract test set leak rate recorded in Step 1.B.(1)(a)1 from leak rate in Step
1.B.(1)(a)3 to determine actual leak rate.
NOTE: If pitot system leak rate is more than 1 knot per minute, stop and correct
leak.
When leak corrected, comply with Step 1.B.(1)(a)1 thru Step 1.B.(1)(a)4
again.
5 Adjust airspeed to 100 knots.
6 Adjust altitude to test altitude determined in Step 1.A.(2)(f)3 at a rate of 5000 feet
per minute and allow system to stabilize for 1 minute, then monitor leak rate of
static system for a minimum of 1 minute. Record information.
7 Subtract test set leak rate recorded in Step 1.B.(1)(a)1 from leak rate in Step
1.B.(1)(a)6 to determine actual leak rate.
NOTE: If static system leak rate is more than 100 feet per minute, stop and
correct leak.
When leak corrected, comply with Step 1.B.(1)(a)5 thru Step 1.B.(1)(a)7
again.
8 Adjust altitude to 0 feet at 5000 feet per minute.
NOTE: Airspeed will increase if there is a pitot leak to ambient and will
decrease if there is a pitot leak to static.
9 Adjust airspeed to 0 knots (or minimum setting recommended for test unit) at 100
knots per minute.
(2) Air Data System - Altitude Hold / Alert Checks
NOTE: This procedure is to be run in conjunction with and immediately following Step
1.B.(1) (Pitot / Static System - Lines Leak Test).
(a) In radome, place SSEC switch to DISABLED position.
(b) On Display Unit (DU) No. 3, verify SSEC 1-2-3 Disabled messages (amber) are
displayed on CAS.
(c) On test set, increase altitude and airspeed to the following values at 3000 feet per
minute:
• Altitude: 5,000 feet
• Airspeed: 120 knots
(d) On both pilot / copilot PFD and Visual Guidance System (VGS), verify the following is
displayed:
• Altimeter: 5,000 feet (±35)
• Airspeed: 120 knots (±2)
• Mach: 0.20 (±0.01)
(e) On integrated SFD, verify the following is displayed:
• Altimeter: 5,000 feet (±40)
• Airspeed: 120 knots (±3)
(f) On test set, increase altitude and airspeed to the following values at 3000 feet per
minute:

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• Altitude: 10,000 feet

• Airspeed: 320 knots
NOTE: An overspeed warning tone will be heard if landing gear is down.
(g) Ensure an overspeed aural warning tone occurs when passing through 250 knots (+3).
(h) At pilot DC, comply with the following:
1 Select SENSOR push-button ON.
2 At DC CRT, press ADS line select key until 2 is boxed.
(i) Ensure overspeed aural warning tone is still audible.
(j) At DC CRT, press ADS line select key until 1 is boxed.
(k) Ensure overspeed aural warning tone is still audible.
(l) On both pilot / copilot PFD and VGS, verify the following is displayed:
• Altimeter: 10,000 feet (±40)
• Airspeed: 320 knots (±3)
(m) On integrated SFD, verify the following is displayed:
• Altimeter: 10,000 feet (±80)
• Airspeed: 320 knots (±5)
(n) On test set, increase altitude and airspeed to the following values at 3000 feet per
minute:
• Altitude: 25,000 feet
• Airspeed: 220 knots
(o) On both pilot / copilots PFD and SFD, verify the following:
• Altitude increasing
• Airspeed decreasing
(p) Ensure overspeed aural warning tone is no longer audible as airspeed descends below
250 knots.
(q) On both pilot / copilot PFD and VGS, verify vertical speed indication is 3000 feet-per-
minute (±150).
(r) On FGP, comply with the following:
1 Select AP push-button ON.
2 Using ALTITUDE selector knob, adjust ALTITUDE display to 25,000 feet.
(s) On both pilot / copilot PFD, verify ASEL is displayed (white).
NOTE: FMS source has to be selected, for ASEL to be displayed.
(t) On FGP, select VNAV push-button ON.
(u) On VGS, verify ALT is displayed.
(v) On both pilot / copilot PFD and VGS, verify the following:
• As altitude reaches 24,000 feet
– Altitude alert tone audible (approximately 2 seconds)
– On both PFDs, ASEL is boxed (green) indicating capture

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– On VGS, ASEL is displayed and boxed

• As altitude reaches 25,000 feet, ASEL capture mode canceled on PFDs and VGS
(w) On FGP, verify ALTITUDE hold push-button light is ON (green).
NOTE: This indicates altitude hold mode is engaged.
(x) On both pilot / copilot PFD, verify ALT is displayed (green).
(y) On VGS, verify ALT is displayed and boxed.
(z) On FGP, press ALTITUDE hold push-button off to deselect altitude hold.
(aa) On both pilot / copilot PFD, verify the following is displayed:
• Altimeter: 25,000 feet (±75)
• Airspeed: 220 knots (±3)
• Mach: 0.53 (±0.01)
(ab) On integrated SFD, verify the following is displayed:
• Altimeter: 25,000 feet (±155)
• Airspeed: 220 knots (±5)
(ac) At pilot control column, select AP DISC switch verifying autopilot disengages.
(ad) On test set, increase altitude and airspeed to the following values at 3000 feet per
minute:
• Altitude: 45,000 feet
• Airspeed: 200 knots
(ae) On both pilot / copilot PFD, verify the following is displayed:
• Altimeter: 45,000 feet (±125)
• Airspeed: 200 knots (±3)
(af) On integrated SFD, verify the following is displayed:
• Altimeter: 45,000 feet (±255)
• Airspeed: 200 knots (±5)
(ag) At DC CRT, press ADS line select key until 2 is boxed.
(ah) On SFD, verify display is within 340 feet of readings in Step 1.B.(2)(ae).
(ai) On test set, increase altitude and airspeed to the following values at 3000 feet per
minute:
• Altitude: 51,000 feet
• Airspeed: 200 knots
(aj) On FGP, comply with the following:
1 Using ALTITUDE selector knob, adjust ALTITUDE display to 51,000 feet.
2 Select AP push-button ON.
(ak) On both pilot / copilot PFD, verify ASEL is displayed (white).
(al) On FGP, select VNAV push-button ON.
(am) On both pilot / copilot PFD and SFD, verify the following:
• Altimeter increasing

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• Airspeed increasing
(an) On both pilot / copilot PFD, verify the following:
• As altitude reaches 50,000 feet
– Altitude alert tone audible (approximately 2 seconds)
– ASEL is boxed (green) indicating capture
• As altitude reaches 51,000 feet, ASEL capture mode canceled and ALT is
displayed green on PFDs
(ao) On FGP, verify ALTITUDE hold push-button light is ON (green).
(ap) At pilot control column, select AP DISC switch and verify the following:
• Autopilot disengages
• Autopilot disconnect tone audible
(aq) On both pilot / copilot PFD, verify the following is displayed:
• Altimeter: 51,000 feet (±140)
• Airspeed: 220 knots (±3)
• Mach: 0.92 (±0.01)
(ar) On integrated SFD, verify the following is displayed:
• Altimeter: 51,000 feet (±280)
• Airspeed: 220 knots (±5)
NOTE: Proceed to Step 1.B.(3).
(3) Pitot / Static System - Accuracy Check
NOTE: The following procedure is defined per FAR 91.411 altimeter system and altitude
reporting equipment tests and inspections.
This procedure is to be run in conjunction with and immediately following Step
1.B.(1) (Pitot / Static System - Lines Leak Test) and Step 1.B.(2) (Air Data System -
Altitude Hold / Alert Checks).
Disregard overspeed warning sound while performing this test.
(a) In radome, place SSEC switch to DISABLED position.
NOTE: The SSEC switch is located left of weather radar R/T.
(b) On DU, verify SSEC 1-2-3 Disabled message (amber) is displayed on CAS.
NOTE: If SSEC disable switch was not selected to disable prior to applying power,
SSEC 1-2-3 Disabled message will not be displayed on CAS; however, SSEC
disabled will be displayed on standby altitude tape.
(c) On Integrated Standby Instrument (ISI) verify SSEC message (amber) is displayed.
(d) On both pilot / copilot DC, comply with the following on side selections:
1 Select SENSOR push-button ON.
2 At DC CRT, select ADS line select key until 1 (pilot) / 2 (copilot) is boxed.
(e) On test set, comply with the following:

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NOTE: Aircraft having GH-3100 Integrated Standby Instruments (ISI) display, it is

normal for display to indicate changes when air data test set is changing
airspeed / altitude during routine air data tests. Allow display to complete
alignment prior to initiating any changes to airspeed, then disregard any
altitude changes after a significant change in airspeed until after display has a
chance to correct out.
1 Adjust altitude and airspeed to test points in Table 501 and record requested
information:
NOTE: Allow systems to stabilize for 1 minute before taking reading from pilot /
copilot / ISI display.
On DC, select applicable ADM as required for pilot / copilot readings.
After recording airspeed readings for pilot / copilot, readjust airspeed for
ISI (if required).
Values must fall within tolerances in applicable table.
2 Adjust altitude to 0 feet at 5000 feet per minute.
3 Adjust airspeed to 0 knots (or minimum setting recommended for test unit) at 100
knots per minute.
C. Follow On
(1) Remove electrical power from aircraft. See External Electrical Power Application, 20-20-10,
Maintenance Practices.
(2) On IRS MODE SELECT panel, select switches as follows:
• IRS NO. 1 switch OFF (extended)
• IRS NO. 3 switch OFF (extended)
• IRS NO. 2 switch OFF (extended)
(3) On Cockpit Overhead Panel (COP) in DISPLAY SYSTEM CONTROL section, select switches
as follows:
• DU 1 switch OFF
• DU 2 switch OFF
• DU 3 switch OFF
• DU 4 switch OFF
NOTE: CAS shall be monitored for any overheat or miscompare warnings.
(4) Remove all test equipment from aircraft.
(5) In radome, place SSEC switch to NORMAL position (down).
(6) Remove safety clips, tags and depress CBs pulled in Step 1.A.(2)(i).
(7) If pitot / static probe heaters activated with pitot / static tester hoses connected, comply with
Pitot / Static System Probes / Lines - Contamination Check, 34-13-00, Inspection / Check or
Code 341300.
(8) Inspect for presence of foreign objects.
(9) Install birdstrike plate. See Birdstrike Plate - Removal / Installation, 53-02-01, Removal /
Installation or Code 530205.
(10) Inspect for presence of foreign objects.

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(11) Close and secure radome. See Radome - Open / Close, 53-02-01, Maintenance Practices.
(12) Record all maintenance actions in accordance with current governing authority.

Table 501: Pilot / Copilot - Altitude / Airspeed Readings

TEST SET OVERSPEED WARNING

ALTITUDE AIRSPEED MACH NO
POINTS ACTUATION POINTS

Pilot Copilot ATC Pilot Copilot Pilot Copilot Pilot Copilot

ADM ADM ADM ADM ADM ADM Master ADM ADM

Altitude No. 1 (2) Airspeed Mach No.
Alt A/S No. 1 (1) No. 2 (1) No. 1 (1) No. 2 (1) No. 1 (1) No. 2 (1) Airspeed No. 1 (1) No. 2 (1)

Limits Limits Limits

ADM ADM ADM ADM ADM ADM Limits ADM ADM
No. 2 (2)

No. 3 (1) No. 3 (1) No. 3 (1) No. 3 (1) No. 3 (1) No. 3 (1) No. 3 (1) No. 3 (1)

MAX: 51,097 MAX: 192.0 MAX: 0.82 MAX: 207

51,000 190
MIN: 50,903 MIN: 188.0 MIN: 0.80 MIN: 203
MAX: 50,095 MAX: 199.0 MAX: 0.83 MAX: 213
50,000 197
MIN: 49,905 MIN: 195.0 MIN: 0.81 MIN: 209
MAX: 45,085 MAX: 236.0 MAX: 0.87 MAX: 244
45,000 234
MIN: 44,915 MIN: 232.0 MIN: 0.85 MIN: 240
MAX: 40,075 MAX: 258.0 MAX: 0.85 MAX: 275 N/A N/A
40,000 256
MIN: 39,925 MIN: 254.0 MIN: 0.83 MIN: 271 N/A N/A
MAX: 35,065 MAX: 293.0 MAX: 0.86 MAX: 308 N/A N/A
35,000 291
MIN: 34,935 MIN: 289.0 MIN: 0.84 MIN: 304 N/A N/A
MAX: 30,055 MAX: 323.0 MAX: 0.84 MAX: 335 N/A N/A
30,000 320
MIN: 29,945 MIN: 317.0 MIN: 0.83 MIN: 331 N/A N/A
MAX: 25,050 MAX: 303.5 MAX: 0.73 MAX: 344 N/A N/A
25,000 300
MIN: 24,950 MIN: 296.5 MIN: 0.71 MIN: 340 N/A N/A
MAX: 20,045 MAX: 293.5 MAX: 0.64 MAX: 344 N/A N/A
20,000 290
MIN: 19,955 MIN: 286.5 MIN: 0.62 MIN: 340 N/A N/A
MAX: 15,040 MAX: 307.5 MAX: 0.61 MAX: 344 N/A N/A
15,000 304
MIN: 14,960 MIN: 300.5 MIN: 0.59 MIN: 340 N/A N/A
MAX: 10,035 MAX: 280.5 MAX: 0.51 MAX: 344 N/A N/A
10,000 277
MIN: 9965 MIN: 273.5 MIN: 0.49 MIN: 340 N/A N/A
MAX: 5032.5 MAX: 216.0 MAX: 0.36 MAX: 304 N/A N/A
5,000 212
MIN: 4967.5 MIN: 208.0 MIN: 0.34 MIN: 300 N/A N/A
MAX: 1020 MAX: 216.0 MAX: 0.34 MAX: 304 N/A N/A
1000 212
MIN: 980 MIN: 208.0 MIN: 0.32 MIN: 300 N/A N/A
MAX: 20 MAX: 323.5 MAX: 0.48 MAX: 304 N/A N/A
0 (SL) 320
MIN: -20 MIN: 316.5 MIN: 0.47 MIN: 300 N/A N/A
MAX: -1020 MAX: 323.5 MAX: 0.48 MAX: 304 N/A N/A
-1000 320
MIN: -980 MIN: 316.5 MIN: 0.47 MIN: 300 N/A N/A

(1)
Record aircraft reading as directed from pilot / copilot PFD.
(2)
Record altitude reporting display and verify it agrees with displayed altitude on PFD within ±125 feet.

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Pitot / Static System - Layout

Figure 501

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Aircraft - Barometric Pressure / Test Altitudes

Figure 502 (Sheet 1 of 2)

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Aircraft - Barometric Pressure / Test Altitudes

Figure 502 (Sheet 2 of 2)

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2. Standby Pitot / Static System — Functional / Leak Test

NOTE: This procedure allows for recertification of integrated standby flight display while installed on
aircraft. This procedure meets requirements of Federal Aviation Regulation (FAR) 91.411, Part
43 (Appendix E).
This procedure can be used for system recertification if performed by a certified repair station.
A. Preparation
SPECIAL TOOLS AND TEST EQUIPMENT

Circuit breaker safety clip ...................................................................... GSE2400984 or equivalent

Air data test set ...................................................................................... GSE3400217 or equivalent
NOTE: It is recommended to use high temperature adapters when performing procedure.
Pitot / static system breakout box ......................................................... GSE3400846 or equivalent
Main landing gear WOW switch adjustment tool ........................................................ GSE3200907
(1) References
• Safe Ground Maintenance Procedure, 20-00-00, Maintenance Practices
• External Electrical Power Application, 20-20-10, Maintenance Practices
• Pitot / Static System Probes / Lines - Contamination Check, 34-13-00, Inspection /
Check or Code 341300
• Birdstrike Plate - Removal / Installation, 53-02-01, Removal / Installation or Code
530205
• Radome - Open / Close, 53-02-01, Maintenance Practices
(2) Aircraft Preparation
NOTE: It is not necessary to disconnect Cabin Pressure Acquisition Module (CPAM) during
test.
(a) Prepare aircraft for safe ground maintenance. See Safe Ground Maintenance
Procedure, 20-00-00, Maintenance Practices.
(b) Open and secure radome. See Radome - Open / Close, 53-02-01, Maintenance
Practices.
(c) If required, remove birdstrike plates. See Birdstrike Plate - Removal / Installation,
53-02-01, Removal / Installation or Code 530205.
(d) Comply with the following on pitot / static system:
1 Ensure pitot / static system is free from the following:
• Entrapped moisture
• Restrictions
• Contamination
2 Ensure no alterations or deformations of pitot / static probes that would affect
relationship between static system and true ambient static air pressure for any
flight condition.
3 Ensure that all pitot / static lines are properly connected.
(e) Ensure the following Circuit Breakers (CBs) are pulled:

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CB NAME CB PANEL CB LOCATION

L LWR PITOT HTR Pilot ANTI-ICE
L UPR PITOT HTR Pilot ANTI-ICE
R LWR PITOT HTR Copilot ANTI-ICE
R UPR PITOT HTR Copilot ANTI-ICE

(f) Ensure the following CBs are depressed:

CB NAME CB PANEL CB LOCATION

ADM #1 Pilot FLT INSTRUMENTS
ADM #3 Pilot FLT INSTRUMENTS
ADM #2 Copilot FLT INSTRUMENTS

(3) In radome, select Static Source Error Correction (SSEC) DISABLE switch to disabled position
(up).
CAUTION: USING SNOOP OR LEAKTEK AROUND PITOT / STATIC PROBES MAY
CAUSE DAMAGE.
(4) Connect test set to standby pitot / static systems. See Figure 501.
NOTE: See manufacturer instructions on proper connection and checkout of test set.
(5) Determine test altitude using the following steps:
(a) Obtain local barometric field pressure in inches of mercury (inHg) from local airport
authority or certified barometer.
(b) Find obtained field pressure on chart and determine test altitude. See Figure 502.
(c) Record test altitude.
(6) On Cockpit Overhead Panel (COP) in ANTI ICE HTR section, verify switches are selected as
follows:
• PROBE - PRI switch OFF (extended)
• PROBE - STBY switch OFF (extended)
(7) On Standby Altitude / Airspeed Indicator (SAAI), set BARO knob to 29.92 InHg.
B. Procedure
(1) On test set, comply with the following:
(a) Adjust altitude rate knob to minimum position, then turn power switch ON.
(b) Adjust airspeed control so that master airspeed indicator reads 318 knots.
(2) In cockpit, verify SAAI reads 318 knots (±5).
(3) On test set, comply with the following:
(a) Adjust altitude rate knob so that master altimeter reads test altitude determined in Step
2.A.(5)(c).

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NOTE: See Table 502 to obtain required airspeed for altitude being used.
(b) Adjust vertical speed control so that master altimeter climbs at a rate not exceeding
5000 feet per minute. Allow to stabilize.
(c) Perform pitot / static leak test per test set instructions and after 1 minute, verify the
following:
• Master altimeter has not decreased more than 112 feet
• Master airspeed indicator has not decreased more than 5 knots
(d) Using Table 502, adjust altitude and airspeed to test points as indicated and record
readings in appropriate column.
NOTE: Allow readings to stabilize for one minute before recording applicable
readings from SAAI.
Readings must fall within tolerances given in table.
(e) Adjust altitude control to 0 feet (ambient).
(f) Adjust vertical speed control so that master altimeter descends at a rate not exceeding
5000 feet per minute.
(g) Adjust airspeed control so that master airspeed indicator reads 0 knots.
(h) Select power switch OFF.
C. Follow On
(1) Remove electrical power from aircraft. See External Electrical Power Application, 20-20-10,
Maintenance Practices.
(2) Depress CBs pulled in Step 2.A.(2)(e).
(3) Disconnect all test equipment from aircraft.
(4) If any of the following conditions apply, comply with Pitot / Static System Probes / Lines -
Contamination Check, 34-13-00, Inspection / Check or Code 341300:
• Pitot / static probe heaters activated with pitot / static tester hoses connected
• In flight, standby altitude doesn’t agree within 220 feet of MADC No. 2 at 0.80 mach at
FL 450
(5) In radome, select SSEC switch to ENABLE position (down).
(6) Inspect for presence of foreign objects.
(7) Install birdstrike plates. See Birdstrike Plate - Removal / Installation, 53-02-01, Removal /
Installation or Code 530205.
(8) Inspect for presence of foreign objects.
(9) Close and secure radome. See Radome - Open / Close, 53-02-01, Maintenance Practices.
(10) Record all maintenance actions in accordance with current governing authority.

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Table 502: Standby Altitude / Airspeed Indicator - Readings

TEST SET POINTS ALTITUDE AIRSPEED

Altitude Aircraft Airspeed Aircraft

Alt A/S
Limits Reading (1) Limits Reading (1)

MAX: 20 MAX: 345

0 (SL) 340
MIN: -20 MIN: 335

MAX: 5,040 MAX: 217

5,000 212
MIN: 4,960 MIN: 207

MAX: 10,080 MAX: 282

10,000 277
MIN: 9,920 MIN: 272

MAX: 15,105 MAX: 309

15,000 304
MIN: 14,895 MIN: 299

MAX: 20,130 MAX:328

20,000 323
MIN: 19,870 MIN: 318

MAX: 25,155 MAX: 345

25,000 340
MIN: 24,845 MIN: 335

MAX: 30,180 MAX: 343

30,000 337.7
MIN: 29,820 MIN: 333

MAX: 35,205 MAX: 307.5

35,000 302.5
MIN: 34,795 MIN: 297.5

MAX: 40,230 MAX: 274.7

40,000 269.7
MIN: 39,770 MIN: 264.7

MAX: 45,255 MAX: 245.2

45,000 240.2
MIN: 44,745 MIN: 235.2

MAX: 50,280 MAX: 218.7

50,000 213.7
MIN: 49,720 MIN: 208.7

MAX: 51,300 MAX: 203

51,000 200
MIN: 50,700 MIN: 197

NOTE
Airspeed and altitude indicator tolerances are for production instruments. Refer to
indicator manufacturer data sheet for specific tolerances.
Airspeed indicator mach readings are usually invalid below 0.550 mach. Refer to
indicator manufacturer data sheet for specific tolerances.

(1)
Record aircraft reading as directed from SAAI.

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