Century 2000 Manuale utente

CENTURY 2000

AUTOPILOT FLIGHT SYSTEM

PILOT’S OPERATING MANUAL

REVISED APRIL 9, 1999

68S1035

FACTORY SERVICE CENTERS

Century Flight Systems, Inc. has established Factory

owned and operated Customer Service Center. The

personnel operating this Center are dedicated to providing

Customer Satisfaction with our products.

Besides providing technical consultation, Service Center

personnel also provide competent repairs and spares

support to our dealers as well as direct customer in or out

of warranty repair service. The location of our Factory

Service Center is:

Municipal Airport, Mineral Wells, Texas

Product Support

Telephone: (940) 325-2517

If any time you need service at the Center please call for

and arrange for an appointment. This way, we can

minimize shop repair time.

LOG OF REVISIONS

06-01-87 Altitude Preselect Addition

Pages i, ii, Replaced

Pages 75, 76, 77, 78 Added

06-01-87 Page 9, 10 Replaced

07-19-94 Preflight Test Sequence

Page 7a, 7b, 7c, and 7d added.

02-07-97 Directional Gyro Section added.

Book reformatted and pages renumbered.

12-19-97 Add to NOTE on pages 7, 9, and 11.

04-09-99 Changes to Yaw Damper write-up on

page 22.

i ii

FORWARD . . . . . 1

FEATURES . . . . . 3

. .

Autopilot ON-OFF . . . . .

Master Disconnect/Trim Interrupt . . 6

. . 7

Preflight Test Sequence (“A” Mod. . .

Preflight Test Sequence (“A” Mod. Trim Prompt 11

Lateral Operating Modes . . . 13

. . . . . .

Heading Systems . . . . .

Selected Intercept Angle . . . 16

Approach . . . . . 17

. . . . 18

Review of Interlocks and Failure Warnings 21

Yaw Damper Systems . . . .

DIRECTIONAL GYRO . . . . 23

. . . . . . 25

C2000 FLIGHT DIRECTOR/STEERING HORIZON 27

CENTURY 2000 OPERATING TECHNIQUES 29

HSI VOR NAVIGATION . . . .

HSI VOR APPROACH . . . . 32

. . . .

HSI GS ARMING & CAPTURE . . .

HSI LOCALIZER BACK COURSE . . .

DG VOR NAVIGATION . . . . 55

. . . . 57

DG LOCALIZER APPROACH - - - 63

- - - 70

. . . . . 73

. . . .

WARRANTY . . . . . 75

iii

FORWARD

The Century Flight Systems, Inc. Century 2000 Autopilot is an advanced

General Aviation Flight Control System utilizing “State of the Art”

electronic techniques.

In this handbook we have detailed the features, functions and general

operating instructions of the Century 2000 System.

May we suggest that you do two things:

1. Read this handbook and your Airplane Flight Manual

Supplement. The handbook presents general operating

procedures. Each aircraft installation has an Airplane Flight

Manual Supplement or Autopilot Handbook that contains FAA

approved flight procedures and operating limitations in that

particular model aircraft. The appropriate AFM Supplement is a

document which must be aboard U.S. Registered Aircraft with the

autopilot installed.

2. Spend some VFR time with the equipment to become familiar

with its operation so that you may have the full benefit of its

capabilities.

NOTE

The Century 2000 Autopilot is a modular design. It may be installed and

operated as a roll axis only autopilot, roll and pitch axis, or a roll, pitch,

and yaw axis. The asterisk symbol (*) appearing before certain sections

of this manual indicates instructions for those systems having the pitch

expansion installed. Operators of the roll only Century 2000 should

disregard the sections, paragraphs and sentences marked by asterisk.

THE CENTURY 2000 3-AXIS IFCS

FEATURES

The Century 2000 Autopilot

This autopilot only version uses a standard artificial horizon in

combination with a directional gyro (DG) or an NSD-360A, NSD-1000

Horizontal Situation Indicator (HSI). A Century Flight Systems, Inc. Yaw

Damper (Y/D) may be incorporated with the Century 2000 when a Y/D is

certified for your plane.

An outstanding feature of the Century 2000 is that it has a rate based

inner loop for short term dynamics. This means that rate information is

derived from the horizon so that motion about the roll and pitch axis is

programmed to occur at a rate appropriate to the activity. Examples of

controlled rate motion are as follows:

ROLL AXIS:

Heading Command - Roll at 5°° per second diminishing near bank

limit.

Navigation Soft Mode - Roll at 2.5 degrees per second to reduced

bank limit (8°°).

Gust Disturbances - Resisted by certificated servo velocity.

*PITCH AXIS:

Command Attitude - 0.7°° per second attitude change.

Gust Recovery - Maximum rate consistent with passenger comfort.

Maximum System Capability - 2.4°° per second .

CENTURY OPERATING CONTROLS

The MODE PROGRAMMER push-button switches are backlighted and

dimming is provided by the control panel light dimmer switch.

The MODE ANNUNCIATOR light intensity is controlled automatically by a

self-contained ambient light level sensor; this feature provides optimum

Mode Annunciator light level for all cockpit conditions. The Century 2000

Autopilot is activated with the Aircraft Master switch and operates in a

low power state until the autopilot operation is desired. Mode selection is

made by pushing the desired mode switch on the Mode Programmer. The

selected mode will be illuminated on the Mode Annunciator.

*A separate Trim Master switch is located on the Control Panel. Autotrim

function is activated by the Autopilot Engage switch.

AUTOPILOT ON-OFF -

Autopilot engage is accomplished by pressing

the momentary ON switch on the left side of the

Programmer. The Autopilot will engage in the

HDG mode. If the system is pitch expanded, the

ATT mode will also be present when engaged

and the autopilot will synchronize to the

existing aircraft pitch attitude.

In HDG mode the aircraft will track the heading selected on the DG or HSI.

In NAV, APR, or REV modes the aircraft will intercept and track any

properly programmed radio-defined course. Instructions for proper radio

setup in these modes are included in this manual.

* In ATT mode the autopilot will synchronize to the aircraft pitch attitude

upon engagement.

* In ALT mode the aircraft will synchronize to the indicated altitude

present at the time of engagement.

The autopilot may be disengaged by pressing

the momentary OFF switch on the programmer,

* by pressing the AP OFF switch on the control

wheel trim switch; * by pressing the Master

Disconnect/Trim Interrupt switch, if present on

the control wheel; or by interrupting power at

the Aircraft Master switch. Disengagement

causes the AP annunciator to flash for 5

seconds.

*MANUAL ELECTRIC TRIM - With the Aircraft and Trim Master switches

on, a manually operated electric trim function is activated by the control

wheel trim switch. This switch serves a dual function:

*1. Disengage the Autopilot.

2. Activate manual electric trim.

*Moving the red portion of the trim switch forward or aft will cause

autopilot disengagement. Moving both parts of the trim switch forward or

aft simultaneously will disengage the autopilot and cause the trim to run

up or down.

*MASTER DISCONNECT/TRIM INTERRUPT

Many Century 2000 autopilots incorporate an additional switch on the

control wheel (usually a red button). Pressing this button will disconnect

the Century 2000, the Yaw Damper (if installed), and will interrupt the

operation of the Trim System. Release of the button will restore power to

the Trim System. However, the Autopilot will return to the HDG and ATT

mode and will require re-engagement in order to resume automatic flight.

*AUTOTRIM - The Century 2000 autopilot is equipped with automatic pitch

trim. When the Trim Master switch is on, Autotrim is activated by

engaging the autopilot.

*The Autotrim system is fail safe in design. The integrity of the trim

system is verified by the preflight test.

OFF

WHEEL SWITCH CONFIGURATIONS

VARY WITH AIRCRAFT MODEL.

PREFLIGHT TEST SEQUENCE

CENTURY 2000 PREFLIGHT PROCEDURES

FOR NO MOD. CENTURY 2000

NOTE

During system functional check the system must be provided adequate

D.C. voltage (12.0 VDC or 24 VDC min.) and instrument air (4.2 in. Hg.

Min.). It is recommended that the engine be operated to provide the

necessary power and that the aircraft be positioned in a level attitude,

during the functional check. Due to the weight of the elevator in certain

models of aircraft, steps 4 and 5 may not move the control wheel. To

verify correct direction of commands, support elevators to remove weight

and continue steps.

AUTOPILOT/AUTOTRIM - To be performed before the first flight of each

day.

*1. Trim Master switch - ON.

2. Engage autopilot.

3. Move the heading bug left and right of the lubber line. Observe that

the control wheel moves in the direction of the heading bug

displacement.

*4. Press the DN switch - verify that the control wheel moves in the down

direction. Verify that after approximately a 3 second delay, the trim

moves in the down direction.

*5. Press the UP switch - verify that the control wheel moves in the up

direction. Verify that after approximately a 3 second delay, the trim

moves in the up direction.

6. Grasp control wheel and override roll and *pitch servo actuators to

assure override capability.

7. Hold control yoke and disengage autopilot by activating the AP OFF

switch on the control wheel or by the programmer off switch.

8. Check controls through full travel in roll and pitch to assure complete

autopilot disengagement.

9. With autopilot OFF, press TST switch. All annunciators shall

illuminate.

*10.After “GS” and “ALT” annunciators extinguish release TST SWITCH;

only “HDG”, “ATT”, and “TST” remain illuminated.

*11.Press DN switch, HDG, and ATT annunciators remain illuminated, TST

may momentarily flicker and then remains illuminated.

*12.Press UP switch, HDG, and ATT annunciators remain illuminated, TST

may momentarily flicker and then remains illuminated.

*13. Momentarily press TST switch. HDG and ATT annunciators remain

illuminated, TST annunciator flashes.

*14. Press and hold DN switch. TST annunciator extinguishes

*15.Press and hold the UP switch. TST annunciator extinguishes.

*16.Momentarily press and release TST switch. HDG and ATT

annunciators remain illuminated, TST annunciator extinguishes.

*COMMAND TRIM SYSTEM - To be performed before the first

flight of each day.

1. Using the control wheel trim switch, verify normal trim up and down

operation.

2. Move red portion of trim switch forward and aft. Observe that the trim

system does not operate.

3. Release the red bar on the control wheel trim switch. Move the black

portion fore and aft. Observe that the trim system does not operate.

This completes the test sequences.

CAUTION

Any failure of the above procedures indicates that a failure exists in the

system and the system shall not be operated until the failure has been

located and corrected.

CAUTION

Check the elevator trim setting before takeoff.

7 8

PREFLIGHT TEST SEQUENCE

CENTURY 2000 PREFLIGHT PROCEDURES

FOR “A” MOD. CENTURY 2000

NOTE

During system functional check the system must be provided adequate

D.C. voltage (12.0 VDC or 24 VDC min.) and instrument air (4.2 in. Hg.

Min.). It is recommended that the engine be operated to provide the

necessary power and that the aircraft be positioned in a level attitude,

during the functional check. Due to the weight of the elevator in certain

models of aircraft, steps 4 and 5 may not move the control wheel. To

verify correct direction of commands, support elevators to remove weight

and continue steps.

AUTOPILOT/AUTOTRIM - To be performed before the first flight of each

day.

*1. Trim Master Switch - ON.

2. Engage Autopilot.

3. Move the heading bug left and right of the lubber line. Observe that

the control wheel moves in the direction of the heading bug

displacement.

*4. Press the DN Switch - verify that the control wheel moves in the down

direction. Verify that after approximately a 3 second delay, the trim

moves in the down direction.

*5. Press the UP Switch - verify that the control wheel moves in the up

direction. Verify that after approximately a 3 second delay, the trim

moves in the up direction.

6. Grasp control wheel and override roll and pitch servo actuators to

assure override capability.

7. Hold control yoke and disengage autopilot by activating the AP OFF

Switch on the control wheel or by the programmer off switch.

8. Check controls through full travel in roll and pitch to assure complete

autopilot disengagement.

9. With autopilot OFF, press and hold TST switch. All available mode

annunciators shall illuminate for 3 seconds then extinguish and the

AP shall flash as long as the TST switch is held.

*10. Release the TST switch. Only HDG, ATT and TST shall be illuminated.

*11.Press and hold the DN switch. The TST annunciator may momentarily

flicker but should remain illuminated. HDG and ATT shall

remain on. Release the DN switch.

*12.Press and hold the UP switch. The TST annunciator may momentarily

flicker but should remain illuminated. HDG and ATT shall remain on.

Release the UP switch.

*13.Momentarily press and hold the TST switch. The AP and TST

annunciators shall flash and the HDG and ATT shall stay illuminated.

Release the TST switch. The HDG and ATT shall remain on the TST

annunciator shall remain flashing.

*14.Press and hold the DN switch. The TST annunciator shall extinguish.

HDG and ATT shall remain on. Release the DN switch.

*COMMAND TRIM SYSTEM - To be performed before the first flight of

each day.

1. Using the control wheel trim switch, verify normal trim up and down

operation.

2. Move red portion of trim switch forward and aft. Observe that the trim

system does not operate.

3. Release the red bar on the control wheel trim switch. Move the black

portion fore and aft. Observe that the trim system does not operate.

CAUTION

Any failure of the above procedures indicates that a failure exists in the

system and the system shall not be operated until the failure has been

located and corrected.

CAUTION

Check the elevator trim setting before takeoff.

9 10

PREFLIGHT TEST SEQUENCE

CENTURY 2000 PREFLIGHT PROCEDURES

FOR “A” MOD. CENTURY 2000

TWO AXIS TRIM PROMPTER

NOTE

During system functional check the system must be provided adequate

D.C. voltage (12.0 VDC or 24 VDC min.) and instrument air (4.2 in. Hg.

Min.). It is recommended that the engine be operated to provide the

necessary power and that the aircraft be positioned in a level attitude,

during the functional check. Due to the weight of the elevator in certain

models of aircraft, steps 4 and 5 may not move the control wheel. To

verify correct direction of commands, support elevators to remove weight

and continue steps.

1. Engage autopilot.

2. Move the heading bug left and right of the lubber line. Observe that

the control wheel moves in the direction of the heading bug

displacement.

3. Press the DN Switch - Verify the control wheel moves in the

DOWN direction.

** Verify that after approximately a 3 second delay, the Trim DN

Prompt flashes.

4. Press the UP Switch - Verify the control wheel moves in the

UP direction.

** Verify that after approximately a 3 second delay the Trim UP Prompt

flashes.

5. Grasp the control wheel and override roll and pitch servo’s to assure

override capability.

6. Hold control wheel and disengage autopilot. Check controls through

full travel in all axis to assure complete autopilot disengagement.

7. With autopilot OFF, press and hold TST switch. All available mode

annunciators shall illuminate for 3 seconds then extinguish and the

AP shall flash as long as the TST switch is held.

8. Release the TST switch. Only HDG, ATT and TST shall be illuminated.

9. Press and hold the DN switch. The TST annunciator may momentarily

flicker but should remain illuminated. HDG and ATT shall remain on.

Release the DN switch.

10. Press and hold the UP switch. The TST annunciator may momentarily

flicker but should remain illuminated. HDG and ATT

shall remain on. Release the UP switch.

11. Momentarily press and hold the TST switch. The AP and TST

annunciators shall flash and the HDG and ATT shall stay illuminated.

Release the TST switch. The HDG and ATT shall remain on the TST

annunciator shall remain flashing.

12. Press and hold the DN switch. The TST annunciator shall extinguish.

HDG and ATT shall remain on. Release the DN switch.

13. Press and hold the UP switch. The TST annunciator shall extinguish.

HDG and ATT shall remain on. Release the UP switch.

14. Momentarily press the TST switch. HDG and ATT shall remain

illuminated, TST annunciator shall extinguish.

**The control wheel may have to be assisted to move up and/or down.

CAUTION

Any failure of the above procedures indicates that a failure exists in the

system and the system shall not be operated until the failure has been

located and corrected.

CAUTION

Check the elevator trim setting before takeoff.

11 12

PREFLIGHT TEST SEQUENCE

CENTURY 2000 PREFLIGHT PROCEDURES FOR

“A” MOD. CENTURY 2000 SINGLE AXIS

NOTE

During system functional check the system must be provided adequate D.C.

voltage (12.0 VDC or 24 VDC min.) and instrument air (4.2 in. Hg. Min.). It is

recommended that the engine be operated to provide the necessary power and

that the aircraft be positioned in a level attitude, during the functional check.

1. Engage autopilot.

2. Move the heading bug left and right of the lubberline. Observe that the

control wheel moves in the direction of the heading bug displacement.

3. Grasp the control wheel and override roll servo to assure override

capability.

4. Hold control wheel and disengage autopilot. Check control through full

travel to assure complete autopilot disengagement.

5. With autopilot OFF, press and hold TST switch. All available mode

annunciators shall illuminate.

CAUTION

Any failure of the above procedures indicates that a failure exists in the

system and the system shall not be operated until the failure has been

located and corrected.

CAUTION

Check the elevator trim setting before takeoff.

LATERAL OPERATING MODES

HEADING - In HDG mode the autopilot will

capture and hold the heading selected on the

DG or HSI. HDG annunciator will illuminate.

NAVIGATION - In NAV mode the autopilot has an

automatic 45 degree VOR-LOC intercept angle.

Selected angle intercepts are available when the

system is equipped with NSD-360A, NSD-1000 or

other HSI.

When executing an intercept, the rate at which the aircraft is closing upon

the selected radio-defined course is determined by the computer and at

the proper time an on-course turn is initiated. thirty-five seconds after the

on-course turn the computer will reduce its bank limits to 13 degrees.

After 70 seconds the bank limits will be reduced to 8 degrees to produce a

‘soft’ navigation mode when tracking a VOR signal. The system will

remain in ‘soft’ mode during station passage. However, if a new course

which requires re-intercept is selected, the ‘soft’ mode will unlock and the

intercept sequence will reoccur.

NOTES

The NAV mode should be used when executing a holding pattern on the

localizer to prevent automatic glideslope coupling.

When radio receiver is tuned to a localizer frequency, the coupler will

operate with localizer (APR) dynamics in the NAV mode.

HDG

NAV

ON HDG NAV APR REV DN

OFF TST FD YD ALT UP

NAV

ON HDG NAV APR REV DN

OFF TST FD YD ALT UP

HDGAP

13 14

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