Dornier 328 - 100 Airplane Flight Manual

DORNIER 328-100 · Flight Manual Supplement

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Overview

The Dornier 328-100 Flight Manual Supplement provides essential information regarding normal and abnormal procedures for the aircraft, including specific tests and checks that must be performed. It includes temporary revisions related to the power lever aural alert system and other operational procedures.

The Power Lever Aural Alert Test must be performed daily if equipped.
Ground tests include the NP Overspeed Governor and Enrichment Solenoid tests.
The manual includes procedures for engine start and after engine start checks.
Nuisance alerts may occur due to sensor failures and require maintenance action.
Specific temporary revisions are noted for compliance and record-keeping.
The manual is EASA approved and includes multiple temporary revisions.
Daily system tests are required before the first flight of the day.
The manual outlines procedures for both normal and abnormal operations.

Document

Source

Originally published by regulations.gov. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Flight Manual Supplement
Year: 2009
File size: 2.0 MB
Publisher: regulations.gov
Language: en

About this document

What is the Dornier 328 - 100 Airplane Flight Manual?

The Dornier 328 - 100 Airplane Flight Manual is a flight manual supplement for the DORNIER 328-100, dated 2009.

Where does the Dornier 328 - 100 Airplane Flight Manual come from?

This copy of the Dornier 328 - 100 Airplane Flight Manual was originally published by regulations.gov and is hosted on Sprinkle as a free, searchable reference copy.

What year was the Dornier 328 - 100 Airplane Flight Manual published?

The Dornier 328 - 100 Airplane Flight Manual — the DORNIER 328-100 flight manual supplement on file — is dated 2009.

Documentation completeness

1/7

Most owners only have the POH. Here's the essential set for the DORNIER 328-100.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins on file
Type Certificate (TCDS)

More DORNIER 328-100manuals & documents

In this document

Power Lever Aural Alert Test

This test must be performed daily if the aircraft is equipped with the power lever aural alert function. It involves checking the sound of alerts when power levers are manipulated.

Engine Start Procedures

Details the steps to be taken after engine start, including checks for external power, hydraulic pressure, and system tests required before the first flight.

Nuisance Power Lever Aural Alert

Describes the procedure to follow if a nuisance aural alert occurs, including pulling circuit breakers to silence the alert and the need for maintenance if the issue persists.

Temporary Revisions

Lists the temporary revisions that must be inserted into the manual, including the pages affected and the actions required for record-keeping.

Daily System Tests

Outlines the tests that must be performed daily, including the NP Overspeed Governor Test and the Power Lever Aural Alert Test.

Ground Tests

Specifies the ground tests to be conducted after maintenance, including the Enrichment Solenoid Test and the NP Overspeed Governor Test.

Safety notes

If the aural alert persists with both latch handles released, maintenance action is required before takeoff.
Be aware of deactivated power lever alert function if circuit breakers are pulled.
Ensure that power lever latch handles are not lifted before touchdown.

Full document text

Dornier 328 - 100 Airplane Flight Manual Normal Procedures T E M P 0 R A R Y 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

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(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 .JJ f 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 J J 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 Date 20.07. '20'10 Signature NOTE: This Temporary Revision deletes and replaces TR 04-077 GCT Design Organisation GmbH EASA approved Design Organisa!ioil EASA. 21J.033 11~. Released by: Approved by EASA under Approval No. /100 PI3J 1 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. Mod 30, Option 040-011 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 II 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 In flight (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

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