Dornier 328 - 100

Airplane Flight Manual

Normal Procedures

T E M P 0 R A RY REV I S ION No. 05-064

GeT DeS.gn Organisalioo GmbH

EASA approved Design Qrgallisation

, EASA. 21J.033

11

Released by:

Date ,df. Uf 200:;

Approved by EASA under Approval No. !:ASA. A.{. .1061;2 on

Subject: POWER LEVER AURAL ALERT TEST

Reason for Issue: introduction of new system test titled POWER LEVER AURAL ALERT TEST.

This system ground test shall be performed right after the Np Overs peed

Governor test has been completed provided the airplane is equipped with the

power lever aural alert function introduced by S8-328-76-486.

(Change Notice No. CN-Ol01S Issue 01 Rev. 00)

Action: Amend the above mentioned manual as shown below:

1. Insert the pages at this Temporary Revision in the applicable manual as instructed below.

2. Page(s) affected by this Temporary Revision is (are):

Page 1 of 211tle

Page 2 of 2 facing page 2, Subsection 05-12-00

3. Enter the insertion of this Temporary Revision on the, Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instructed to do so.

TR 05-064

EFFECTIVITY: ALL

58-328-76-486 included

Page 1 of 2

EASA - Approved

Feb 13/09
10. POWER levers (both) ....

9. POWER lever latch handle (one after another)

8. POWER lever latch handles (both) .

Domier 328 - 100

Airplane Flight Manual

Normal Procedures

SUPPLEMENTARY NORMAL SYSTEM PROCEDURES

ENGINE I PROPELLER conl'd

ENRICHMENT SOLENOID TEST

(Ground test only - after maintenance)

BOTH ENGINES RUNNING

1. POWER lever . GI

2. CONDITION lever. . . . . . . . . . . FEA

3. ENRICH SOLENOID TEST SWitch LH

- NH increase. . . . . . . . . . . . . . . . Check

4. ENRICH SOLENOID TEST switch . . . . . Release

- NH decrease to previous value . . . .. • . Check

5. ENRICH SOLENOID TEST switch RH

- NH increase...................... . Check

6. ENRICH SOLENOID TEST switch. . . . . . . . Release

- NH decrease to previous value .. Check

Np OVERSPEED GOVERNOR and POWER LEVER AURAL ALERT TEST

(Ground tests only - daily)

BOTH ENGINES RUNNING

1. CONDITION levers (both) . . .. . .. .. . . .... . . . .. .. MIN

2. POWER levers (both) . . . . . . . . . . . . . . . . . . . . • .. .. Advance to 80% NP minimum

3. PROP OVSPD TEST switch . LH/RH

4. PROP RPM drop monitor to 72% - 77%, check stabilized

5. PROP OVSPD TEST switch. . . . . . . . . . . . . . . . .. Release

6. PROP RPM rise monitor to . Previous Np

NOTE: If PROP RPM is not within limits, repeat this test with CONDITION levers in position

MAX and ECUs in MAN. The test is acceptable if PROP RPM drop is now within limits.

Continue daily ground test to perform POWER Lever Aural Alert Test:

7. POWER levers (both) . . . , . . . . . . . . . Retard with both lever latch

handles lifted untill POWER levers

lock with aural alert sounding

.. Release - check sound of alert

silenced

Lift - check individual aural alert

sounds slightly different from that

generated with both latch handles

lifted

Release - check each individual

sound of alert silenced

.................... Retard to Fl, than GI - check no

aural alert sounds

TR 05-064

I

EFFECTIVITY: ALL

58-328-76-486 inCluded

Page 2 of 2

EASA - Approved

05-12-00

Page 2

Feb 13/09
Dornier 328 • 100

Airplane Flight Manual

Normal Procedures

T E M P 0 R A R Y REV I S ION No. 05-065

GCT Design Organisation GmbH

EA5A app:tNed Desi!J1 D!'gaIlisaliol1

EASA. 21J.033

Released by:

Date ./It. 01. i' OO!)

Approved by EASA under Approval No. FAg. 4.( 106"4'2. on

Subject: NEW DAILY SYSTEM TEST - (POWER LEVER AURAL ALERT TEST)

Reason for Issue: Introduction of new system test titled POWER LEVER AURAL ALERT TEST

This system ground test must be performed daily provided the airplane is

equipped with the power lever aural alert function introduced by

S8-328-76-486.

Additional editorial change on Page 2: the TRU function test, still mentioned as

system test to be performed before first flight of the day, has been corrected

for being a daily check to be in line with approved TR 05-041.

(Change Notice No. CN-01 018 Issue 01 Rev. DO)

Action: Amend the above mentioned manual as shown below:

1. Insert the pages of this Temporary Revision in the applicable manual as instructed below.

2. Page(s) affected by this Temporary Revision is (are):

Page 1 of 2 Title

Page 2 of 2 facing page 2, Subsection 05-03-00

3. Enter the insertion of this Temporary Revision on the Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instructed to do so.

TR 05-065

EFFECTIVITY: Mod 10 f Mod 20

S6-325-75-486 included

Page 1 of 2

EASA - Approved

Feb 13109
Dornier 328· 100

Airplane Flight Manual

Normal Procedures

ENGINE START

AFTER ENGINE START

r----- EXT POWER DISCONNECT (If applicable)

EXT power button. . . . . . . . . . . . . . . . . . . . ..... Off

GEN LH/RH FAIL lights . . . . . .. . . . . . . . . . . Extinguished

Check 26V DC minimum each MAIN BUS

External power Disconnect

PROBES 1, 2 and STBY buttons . On

HYD PWR STBY selector . . . . . . . .. . . . .. .. . . . . . .. AUTO

Ground crew. . . . . . . . . . . . . . . . . Disconnect (if applicable)

GND CALL button ............................•...... PUSH (if applicable)

CALL light . Extinguished

STBY attitude indicator. . . . . . . . . . . . . . . . . . . . . . . . . . . . Uncage

CONDITION levers (both) . MIN

Hydraulic pressure . . . . . .. . ~ Check 3 000 - 3 100 PSI

Brake temperature indicators .. . .. "' . . . Check

NWS button . •........... " On

ANTI SKID button . .......•................ On

FLAPS.... . SetforT/O

PACK LH/RH buttons . . . . . . . . . On

ECS BLEED LH/RH buttons......... . On

NOTE: For the ECS bleed air switch on wait either a minimum of 2 minutes with

the propellers in feather or a minimum of 1 minute after the propellers

have unfeathered.

System tests. . . . . . . . . . AS REQUIRED

(refer to the SUPPLEMENTARY NORMAL SYSTEM PROCEDURES)

Test to be performed before the first flight of the day:

- FLAP SYSTEM TEST

Tests to be performed daily:

- NP OVERSPEED GOVERNOR TEST

- POWER LEVER AURAL ALERT TEST

- PROP AUTO FEATHER TEST

- TRU FUNCTION TEST

TR 05-065

I

EFFECTIVITY: Mod 10 J Mod 20

S6-328-76-486 included

Page 2 of 2

EASA - Approved

05-03-00

Page 2

Feb 13/09
Dornier 328 - 100

Airplane Flight Manual

Normal Procedures

T E M P 0 R A R Y REV I S ION No. 05-066

GCT Qes;gn ~ GmbH

EASA appn:M:l(l Design O!;aoisation

CASA. 21J.033

')

Released by:

ignature Date ~{07 ?OOJ

Approved by EASA under Approval No. £I1SA./!.{ 106V2 on

Subject: NEW DAILY SYSTEM TEST - (POWER LEVER AURAL ALERT TESn

Reason for Issue: Introduction of new system test titled POWER LEVER AURAL ALERT TEST.

This system ground test must be performed daily provided the airplane is

equipped with the power lever aural alert function introduced by

58-326-76-466.

Additional editorial change on Page 2: the TRU function test, still mentioned as

system test to be performed before first flight of the day, has been corrected

for being a daily check to be in line with approved TR 05-042.

(Change Notice No. CN-01016 Issue 01 Rev. 00)

Action: Amend the above mentioned manual as shown below:

1. Insert the pages of this Temporary Revision in the applicable manual as instructed below.

2. Page(s) affected by this Temporary Revision is (are):

Page 1 of 2 Title

Page 2 of 2 facing page 2, Subsection 05-03-00

3. Enter the insertion of this Temporary Revision on the Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instructed to do so.

TR 05-066

EFFECTIVITY: JAA, Mod 30, Option 040-011

59-328-76-486 included

Page 1 of 2

EASA - Approved

Feb 13/09
Dornier 328 - 100

Airplane Flight Manual

Normal Procedures

ENGINE START

AFTER ENGINE START

,----- EXT POWER DISCONNECT (If applicable)

EXT power button . .

GEN LH/RH FAIL lights ....

Check 26V DC minimum each MAIN BUS

External power .

Off

Extinguished

Disconnect

PROBES 1, 2 and STBY buttons .. , . . . . . . On

HYD PWR STBY selector AUTO

Ground crew. . . . . . . . . . ........•.•.•.....•......... Disconnect (if applicable)

GND CALL button ..............•........................ PUSH (if applicable)

CALLlighl Extinguished

STBY attitude indicator ..................•................ Uncage

CONDITION levers (both) MIN

Hydraulic pressure ..............•..............•........ Check 3 000 - 3 100 PSI

Brake temperature indicators .. __..••.•••.•.•.••........ Check

NWSbutton ...................•....................... On

ANTI SKID button On

FLAPS. . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . . .. . . . . . . Set for T/O

PACK LH/RH buttons . . . . . . . . . . . . . On

ECS BLEED LH/RH buttons On

NOTE: For the ECS bleed air switch on wait either a minimum of 2 minutes with

the propellers in feather or a minimum of 1 minute after the propellers

have unfeathered.

System tests . . . . .. . . AS REQUIRED

(refer to the SUPPLEMENTARY NORMAL SYSTEM PROCEDURES)

Test to be performed before the first flight of the day:

- FLAP SYSTEM TEST

- GROUND SPOILER SYSTEM TEST

Tests to be performed daily:

- NP OVERSPEED GOVERNOR TEST

- POWER LEVER AURAL ALERT TEST

- PROP AUTO FEATHER TEST

- TRU FUNCTION TEST

TR 05-066

I

EFFECTIVITY: JAA, Mod 30, Option 040-011

58-328-76-486 included

Page 2 of 2

EASA - Approved

05-03-00

Page 2

Feb 13/09
Dornier 328 - 100

Airplane Flight Manual

Abnormal Procedures

T E M P 0 R A R Y REV I S ION No. 04-078

Date 121:).07 2010 'l~

Signatur

NOTE: This Temporary Revision deletes and replaces TR 04-075

GCT Design Organisallon GmoH

EASA approved Dasign Organisa!lon

EASA. 21J.033

Released by:

Approved by EASA under Approval No. -100.]-1 .JJf on ~o.o~. 2040

Subject: NUtSANCE POWER LEVER AURAL ALERT

Reason for Issue: Introduction of new procedure titled NUISANCE POWER LEVER AURAL

ALERT, valid for airplanes equipped with the power lever aural alert function

introduced by S8-328-76-486.

(Change Notice No. CN-01029 Issue 01 Rev.00)

Action: Amend the above mentioned manual as shown below:

1. Remove and destroy the pages of TR 04-075 and insert the pages of this Temporary Revision in

the applicable manual as instructed below.

2. Page(s) affected by this Temporary Revision is (are):

Page 1 of 2 Title

Page 2 of 2 facing page 12, Section 04-09-00

3. Enter the removal of the deleted Temporary Revision and the insertion of this Temporary

Revision on the Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instructed to do so.

TR 04-078

EFFECTIVITY: ALL

S8-328-76-486 included

Page 1 of 2

EASA - Approved Mar 15/10
Domier 328 - 100

Airplane Flight Manual

Abnormal Procedures

ENGINE

CONDITION NUISANCE POWER LEVER ---

AURAL ALERT

POWER LEVER AURAL ALERT SOUNDS WITH

BOTH LATCH HANDLES RELEASED

NOTE: A nuisance aural alert tone with both Power lever latch

handles released may be caused by a left or right latch

handle sensor failure or by a failure in the electrical wiring

of the sensor circuit. The nuisance alert may only be

silenced by pulling associated system circuit breakers.

If aural alert persists with both latch handles released:

1. PWR LVR AUDIO LH c/b (I 4) and

PWR LVR AUDIO RH c/b (M5) Pull to silence aural alert

~ If in flight:

CAUTION: BE AWARE OF DEACTIVATED POWER LEVER ALERT

FUNCTION. ASSURE THAT THE POWER LEVER LATCH

HANDLES ARE NOT LIFTED BEFORE TOUCH DOWN.

END

•••.If on ground:

2. Maintenance action required before takeoff

END

TR 04-078

EFFECTIVITY: ALL

88-328- 76-486 included

Page 2 of 2

EASA - Approved

04-09-00

Page 12A

Mar 15/10
Domler 328 - 100

Airplane Flight Manual

Abnormal Procedures

TEMPORARY REVISION No. 04-079

NOTE: This Temporary Revision deletes and replaces TR 04-076

Released by:

GeT Design Organisation GmbH

EASA approved Design Organisation

EASA.21J.033

1} //.L

Signatur ~ Date 2 'ij. 07· 2010

Approved by EASA under Approval No. /f 00 ;]/1 JJ 1-

Subject: EICAS CAUTION "PROXI SYSTEM"

on/10.0'j, ?040

Reason for Issue: Revised PROXI SYSTEM Procedure to inform Flight crew of failure of the

POWER lever aural alert function in case of "PROXI SYS FAIL" is displayed on

HYDR page. Revision is valid for airplanes equipped with the power lever aural

alert function introduced by 8B-328-76-486.

(Change Notice No. CN-01029 Issue 01 Rev.00)

Action: Amend the above mentioned manual as shown below:

1. Remove and c)estroy the pages ofTR 04-076 and insert the pages of this Temporary Revision in

the applicable manual as instructed below.

2, Page{s) affected by this Temporary Revision is (are):

Page 1 of 2 Title

Page 2 of 2 facing page 1, Secfion 04-04-00

3. Enter the removal of the deleted Temporary Revision and the insertion 01 this Temporary

Revision on the Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instrqcted to do so.

TR 04-079

EFFECTIVITY: Mod 10/ Mod 20

58-328-76-486 included

Page 1 of 2

EASA - Approved Mar 15/10
Dornier 328 - 100

Airplane Flight Manual

Abnormal Procedures

HYDRAULICS

EICAS~C~A~UT~IO~N~~:.s-----{EP~R~o~xITI]S~¥rS[!T]E~M[]

CONDITION" PROXI SYSTEM BITE HAS DETECTED FAILURE in:

"NWS or GEAR LOCK or WOW or HYD QTY LEVEL SENSING

I

I

On ground:

1. Maintenance action required before takeoff

In flight:

NOTE: If no HYDR page is available and no other CAUTIONs are available

on EICAS the PROXY SYS FAIL procedure should be applied.

~ PROXI SYS FAIL displayed on HYDR page (if available)

Be prepared for unreliable system indications. The following functions may

be affected:

All LOG GEAR CAUTION's and indications

Normal LOG GEAR

(use LANDING GEAR EXTENSION

MALFUNCTION procedure - if necessary)

Hydraulic system CAUTION's and indications

Door CAUTION's and indications

WOW-status

POWER lever aural alert function

Before the normal BEFORE LANDING procedure:

1. NWS button. . . . . . . . . . . . . . . . . . .. OFF

2. ANTI SKID button . . . . . . . . . OFF

3. WX RADAR. . . . . . . . . . . .. OFF

4. CAB DUMP button.. . . . . . . . . . . DUMP

5. PWR LVR AUDIO LH elb (I 4) and

PWR LVR AUDIO RH elb (MS) Pull

CAUTION: BE AWARE OF DEACTIVATED POWER LEVER ALERT

FUNCTION. ASSURE THAT THE POWER LEVER LATCH

HANDLES ARE NOT LIFTED BEFORE TOUCH DOWN.

6. Actual landing distance ..... Increase by factor given below:

CONDITION FACTOR

FLAPS 20" : • NWS OFF

• ANTI SKID SYSTEM OFF 1.15 (15%)

• Both engines full reverse

FLAPS 32° : • NWS OFF

• ANTI SKID SYSTEM OFF 1.35 (35%)

• Both engines full reverse

EFFECTIVITY: Mod 10 I Mod 20

58-328-76-486 included

TR 04-079

Page 2 of 2

EASA - Approved

cont'd next page

04-04-00

Page 1

Mar 15/10
Dornier 328 - 100

Airplane Flight Manual

Abnormal Procedures

T E M P 0 R A R Y REV I S ION No. 04-080

Signature Date 20.07. '20'10

NOTE: This Temporary Revision deletes and replaces TR 04-077

GCT Design Organisation GmbH

EASA approved Design Organisa!ioil

EASA. 21J.033

Released 11~. by:

Approved by EASA under Approval No. /100PI3J1 on dlJ ag. 20·10

Subject: EICAS CAUTION "PROXI SYSTEM"

Reason for Issue: Revised PROXI SYSTEM Procedure to inform Flight crew of failure of the

POWER lever aural alert function in case of "PROXI SYS FAll" is displayed on

HYDR page. Revision is valid for airplanes equipped with the power lever aural

alert function introduced by 8B-328-76-486.

(Change Notice No. CN-01029 Issue 01 Rev. 00)

Action: Amend the above mentioned manual as shown below:

1. Remove and destroy the pages of TR 04-077 and insert the pages of this Temporary Revision in

the applicable manual as instructed below.

2. Page{s) affected by this Temporary Revision is (are):

Page 1 at 3 Title

Page 2 of 3 facing page 1, Section 04-04-00

Page 3 at 3 facing page 1, Section 04-04-00, (behind at TR Page 2 of 3)

3. Enter the removal of the deleted Temporary Revision and the insertion of this Temporary

Revision on the Record of Approved Temporary Revisions.

4. Retain this page for record purposes and insert it behind the Record of Approved Temporary

Revisions.

5. Do not remove this Temporary Revision until instructed to do so.

TR 04-080

EFFECTIVITY: EASA, Mod 30. Option 040-011

58-328-76-486 included

Page 1 of 3

EASA - Approved Mar 15;10
I

I

Dornier 328 - 100

Airplane Flight Manual

Abnormal Procedures

HYDRAULICS

EICAS~C::A~U~TIO~NIi.-.!~:.s------[fP~R~o~xITI}S~yrSmT1E~M[}-----l

CONDITION: PROXI SYSTEM BITE HAS DETECTED MULTIPLE FAILURES in:

NWS SENSING, GEAR LOCK SENSING, WOW SENSING, HYD QTY LEVEL

SENSING, PSEU or ARINC DATA TRANSMISSION

On ground:

1. Maintenance action required before takeoff

In flight

NOTE: If no HYDR page is available and no other CAUTIONs are available

on EICAS the PROXY SYS FAIL procedure should be applied.

~ PROXI SYS FAIL displayed on HYDR page (if available)

Be prepared for unreliable system indications, The following functions may

be affected:

- All LDG GEAR CAUTION's and indications

Normal LDG GEAR

(use LANDING GEAR EXTENSION

MALFUNCTION procedure - if necessary)

Ground spoiler CAUTION's and indications

Hydraulic system CAUTION's and indications

Door CAUTION's and indications

WOW-status

POWER lever aura! alert function

Before the normal BEFORE LANDING procedure:

1. NWS button OFF

2. ANT] SKID button .. ... .. OFF

3. GND SPOILER button OFF

4. WX RADAR OFF

5. CAB DUMP button. . DUMP

6. PWR LVR AUDIO LH c/b (I 4) and

PWR LVR AUDIO RH c/b (M5) Pull

CAUTION: BE AWARE OF DEACTIVATED POWER LEVER ALERT

FUNCTION. ASSURE THAT THE POWER LEVER LATCH

HANDLES ARE NOT LIFTED, BEFORE TOUCH DOWN.

TR 04-080

EFFECTIVITY: EASA.Mod30, Option040-011 Page 2 of 3

S8-328-76-486 included

EASA - Approved

cont'd next page

04-04-00

Page 1

Mar 15/10
cont'd

Domier 328 - 100

Airplane Flight Manual

Abnormal Procedures

HYDRAULICS

EICAS CAUTION ~ ~I----I PROXI SYSTEM I

I

CONDITION: PROXI SYSTEM BITE HAS DETECTED MULTIPLE FAILURES in:

NWS SENSING, GEAR LOCK SENSING, WOW SENSING, HYD QTY LEVEL

SENSING, PSEU or ARINC DATA TRANSMISSION

Inflight (cont'd):

7. Actual landing distance . Increase by factor given below:

CONDITION FACTOR

FLAPS 20° . • NWS OFF

• ANTI SKID SYSTEM OFF 1.15 (15%)

o Ground spoilers retracted

• Both engines full reverse

FLAPS 320: • NWS OFF

• ANTI SKID SYSTEM OFF 1.35 (35%)

• Ground spoilers retracted

• Both engines full reverse

cont'd next page

TR 04-080

EFFECTIVITY: EASA, Mod 30. Op:iOfl040-011 Page 3 of 3

88-328- 76-485 included

EA8A - Approved

04-04-00

Page 1A

Mar 15/10