## Dornier 328 - 100



## Airplane Flight Manual Normal Procedures



## T E M P0 RA RY REV ISION No. 05-064

GeTDeS.gnOrganisalioo 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 Overspeed 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 atthis Temporary Revision inthe applicable manual as instructed below. 2. Page(s) affected bythis Temporary Revision is (are): Page 1 of211tle Page 2 of2facing page 2, Subsection 05-12-00 3. Enter the insertion ofthis Temporary Revision on the, Record of Approved Temporary Revisions. 4. Retain this page for record purposes and insert it behind the Record ofApproved 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 13/0910. 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 

## IPROPELLER 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 isacceptable 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 ofalert 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 P0 RA RY REV IS 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 ofthe day, has been corrected for being adaily 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 ofthis Temporary Revision inthe applicable manual as instructed below. 2. Page(s) affected bythis Temporary Revision is (are): Page 1 of2Title Page 2 of 2facing page 2, Subsection 05-03-00 3. Enter the insertion ofthis Temporary Revision on the Record ofApproved 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 10fMod20

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 (Ifapplicable) 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 (ifapplicable) 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: Forthe ECS bleed airswitch on wait either a minimum of2 minutes with the propellers infeather or a minimum of 1 minute after the propellers have unfeathered. System tests. .. .. .. .. . AS REQUIRED (refer tothe SUPPLEMENTARY NORMAL SYSTEM PROCEDURES) Testto be performed before the first flight ofthe day:

- FLAP SYSTEM TEST Tests to be performed daily:

- NP OVERSPEED GOVERNOR TEST

- POWER LEVER AURAL ALERT TEST

- PROP AUTOFEATHER TEST

- TRU FUNCTION TEST 

# TR 05-065 I

EFFECTIVITY: Mod 10J 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 MP0 RA RY REV IS ION No. 

# 05-066

GCTQes;gn ~ GmbH EASAappn: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 ofthe day, has been corrected for being adaily 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 ofthis Temporary Revision inthe applicable manual as instructed below. 2. Page(s) affected bythis Temporary Revision is (are): Page 1 of2Title Page 2 of 2facing page 2, Subsection 05-03-00 3. Enter the insertion ofthis Temporary Revision on the Record ofApproved Temporary Revisions. 4. Retain this page for record purposes and insert it behind the Record ofApproved 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 (Ifapplicable) 

### 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 (ifapplicable) 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: Forthe ECS bleed air switch on wait either a minimum of 2 minutes with the propellers infeather ora minimum of 1 minute after the propellers have unfeathered. System tests ... ... . . AS REQUIRED (referto the SUPPLEMENTARY NORMAL SYSTEM PROCEDURES) Test to be performed before the first flight ofthe day:

- FLAP SYSTEM TEST

- GROUND SPOILER SYSTEM TEST Tests to be performed daily:

- NP OVERSPEED GOVERNOR TEST

- POWER LEVER AURAL ALERT TEST

- PROP AUTOFEATHER 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 MP0 RA RY REV I S ION No. 04-078

Date 

# 121

# :).072010 'l~ Signatur 

### NOTE: This Temporary Revision deletes and replaces TR 04-075 GCTDesignOrganisallon GmoH EASA approved Dasign Organisa!lon

EASA.21J.033 Released by:


### ApprovedbyEASAunderApproval No. 

## -100.]-1 

## .JJ

# f on 

# ~o.o~. 2040 Subject: NUtSANCE POWERLEVERAURAL 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 

### introducedbyS8-328-76-486. (ChangeNoticeNo.CN-01029 Issue01 Rev.00)

Action: Amend the above mentioned manual as shown below: 1. Remove and destroy the pages ofTR 04-075 and insert the pages ofthis Temporary Revision in the applicable manual as instructed below. 2. Page(s) affected bythis Temporary Revision is (are): 

### Page 1of2 Title Page2of2 facing page 12,Section04-09-00 3. Enter the removal ofthe deleted Temporary Revision and the insertion ofthis Temporary Revision onthe Record ofApproved Temporary Revisions. 4. Retain this page for record purposes and insert it behind the Record ofApproved 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 of2 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 afailure inthe electrical wiring ofthe sensor circuit. The nuisance alert may only be silenced by pulling associated system circuit breakers. Ifaural alert persists with both latch handles released: 1. PWR LVRAUDIO LH c/b (I4) and PWR LVRAUDIO RH c/b (M5) Pull to silence aural alert

~ Ifinflight: CAUTION: BE AWARE OF DEACTIVATED POWER LEVER ALERT

FUNCTION. ASSURE THAT THE POWER LEVER LATCH HANDLES ARE NOT LIFTED BEFORE TOUCH DOWN.

END •••.Ifon 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 DesignOrganisation GmbH EASA approved Design Organisation

EASA.21J.033 1} //.L 

### Signatur ~ Date 

## 2

# 'ij.07· 2010 ApprovedbyEASAunderApproval No. 

## /f00 ;]/1 

## JJ

# 1- Subject: EICASCAUTION "PROXI SYSTEM" 

## on/10.0'j, 

## ?040

Reason for Issue: Revised PROXI SYSTEM Procedure to inform Flight crew offailure ofthe

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

### page. Revision isvalid for airplanes equipped with the power lever aural alertfunction introduced 

### by 8B-328-76-486. 

### (ChangeNoticeNo.CN-01029 Issue01 Rev.00) Action: Amend the above mentioned manual as shown below: 1. Remove and c)estroythe pages ofTR 04-076 and insert the pages ofthis Temporary Revision in the applicable manual as instructed below. 2, Page{s) affected bythis Temporary Revision is (are): 

### Page 1of2 Title Page2of2 facing page 1,Secfion04-04-00 3. Enter the removal ofthe deleted Temporary Revision and the insertion 

### 01this Temporary Revision on the Record ofApproved 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 of2 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:

"NWSor GEAR LOCK or WOW or HYD QTY LEVEL SENSING 

# I

I On ground: 1. Maintenance action required before takeoff Inflight: NOTE: Ifno HYDR page isavailable 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 LVRAUDIO LH 

### elb (I4) and PWR LVRAUDIO 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 byfactor 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 10I 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 EM P0 RA RY REV IS ION No. 04-080

Date 

# 20.07. '20'10 Signature NOTE: This Temporary Revision deletes and replaces TR 04-077 GCTDesign Organisation GmbH EASA approved Design Organisa!ioil

EASA.21J.033 11~. Released by:

Approved by EASA under Approval No.

# /100PI

# 3J

# 1 on 

## dlJ 

## ag. 20·10 Subject: EICAS CAUTION "PROXI SYSTEM" Reason for Issue: Revised PROXI SYSTEM Procedure to inform Flight crew offailure of the

POWER lever aural alert function in case of "PROXI SYS 

### FAll" is displayed on HYDR 

### page. Revision isvalid 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 ofTR 04-077 and insert the pages ofthis Temporary Revision in the applicable manual as instructed below. 2. Page{s) affected bythis Temporary Revision is (are): Page 1 at3 Title Page 2 of3 facing page 1, Section 04-04-00 Page 3 at3 facing page 1, Section 04-04-00, (behind atTR Page 2 of3) 3. Enter the removal ofthe deleted Temporary Revision and the insertion ofthis Temporary Revision on the Record ofApproved Temporary Revisions. 4. Retain this page for record purposes and insert it behind the Record ofApproved 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 of3 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 Inflight NOTE: Ifno HYDR page isavailable and no other CAUTIONs are available on EICAS the PROXY SYS FAIL procedure should be applied.

~ PROXI SYS FAIL displayed on HYDR page (ifavailable) 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] SKIDbutton .. ... .. OFF 3. GND SPOILER button OFF 4. WX RADAR OFF 5. CAB DUMP button. . DUMP 6. PWR LVRAUDIO LH 

### c/b (I4) and PWR LVRAUDIO 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 EICASCAUTION ~ ~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 byfactor 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,Mod30. Op:iOfl040-011 Page 3 of 3

88-328- 76-485 included EA8A - Approved 04-04-00 Page 1A Mar 15/10