Minimum Equipment List MEL Dornier 328-100.pdf
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AEROLÍNEA DE ANTIOQUIA
MINIMUM EQUIPMENT LIST IN ACCORDANCE WITH: MASTER MINIMUM EQUIPMENT LIST – REV 4 – 11/25/1998 FAA
Dornier 328 – 100 AIRCRAFT DO 328‐120 S/N 3084 DO 328‐120 S/N 3039
02 REVISION 19/03/2013
Minimum Equipment List Do‐328 ‐100
PRELIMINARY
Engineering Department
Page: II Date: 09/03/2012 Revision: Original
Page: III Date: 19/03/2013 Revision: 02
Minimum Equipment List Do‐328 ‐100
Revisions Log The Minimum Equipment List of Dornier 328‐100 fleet, is under the control of the Engineering Department of Aerolínea de Antiquia, ahead of the Fleet Engineer. Only the Fleet Enginner can modify this MEL and log the revision in the next control table, subsequent Authority approval. Revision Date of Revision Acceptance Date Inserted by Original 09/03/2012 01/06/2012 Engineering Dep. 01 08/10/2012 Engineering Dep. 02 19/03/2013 Engineering Dep. REVISION HIGHLIGHTS REVISION No ORIGINAL 1 2
CHANGES Addition Dornier 328 fleet of Aerolínea de Antioquia S.A. “ADA”. Preamble actualization and weather radar required number for departure. General Revision (RAC references, verification with Dispatch Deviation Procedures Guide, weather radar required number for departure, emergency medical kit installed and required number for departure) and Dornier 328 HK 4917 S/N 3039 addition.
NOTE: THIS MANUAL SHOULD BE DISTRIBUTED TO THE NEXT PLACES: ‐ ‐ ‐ ‐ ‐ ‐ ‐ ‐ ‐
Dornier 328‐100 HK 4849 S/N 3084. Dornier 328‐100 HK 4917 S/N 3039. Engineering Department. Maintenance Department. Operations Department. Dispatch Department. Barranquilla Base. Monteria Base. UAEAC.
Engineering Department
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Minimum Equipment List Do‐328 ‐100
Page I II III IV V VI VII VIII IX X XI XII XIII XIV XV XVI XVII XVIII XIX 1‐1 1‐2 1‐3 2‐1 21‐1 21‐2 21‐3 21‐4 21‐5 21‐6 21‐7 21‐8 21‐9 21‐10 21‐11 21‐12 21‐13 22‐1 22‐2 22‐3 22‐4
Revision 02 Original 02 02 02 Original Original Original Original Original Original Original Original Original 02 Original 02 Original Original Original 02 02 Original 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02
Engineering Department
Effective Pages Date Page 19/03/2013 22‐5 09/03/2012 23‐1 19/03/2013 23‐2 19/03/2013 23‐3 19/03/2013 23‐4 09/03/2012 24‐1 09/03/2012 24‐2 09/03/2012 24‐3 09/03/2012 24‐4 09/03/2012 24‐5 09/03/2012 24‐6 09/03/2012 24‐7 09/03/2012 24‐8 09/03/2012 24‐9 19/03/2013 24‐10 09/03/2012 24‐11 19/03/2013 24‐12 09/03/2012 24‐13 09/03/2012 24‐14 09/03/2012 24‐15 19/03/2013 24‐16 19/03/2013 24‐17 09/03/2012 24‐18 19/03/2013 25‐1 19/03/2013 25‐2 19/03/2013 25‐3 19/03/2013 25‐4 19/03/2013 25‐5 19/03/2013 26‐1 19/03/2013 26‐2 19/03/2013 26‐3 19/03/2013 27‐1 19/03/2013 27‐2 19/03/2013 27‐3 19/03/2013 27‐4 19/03/2013 27‐5 19/03/2013 27‐6 19/03/2013 27‐7 19/03/2013 28‐1 19/03/2013
Revision 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02
Date 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013
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Minimum Equipment List Do‐328 ‐100
Page 28‐2 28‐3 28‐4 28‐5 28‐6 28‐7 28‐8 28‐9 28‐10 28‐11 28‐12 28‐13 28‐14 29‐1 30‐1 30‐2 30‐3 30‐4 30‐5 30‐6 30‐7 30‐8 30‐9 30‐10 30‐11 30‐12 30‐13 30‐14 30‐15 30‐16 30‐17 30‐18 30‐19 31‐1 31‐2 32‐1 32‐2 32‐3 33‐1
Revision 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02
Engineering Department
Date 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013
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Revision 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 02 Original 02 02 02 02 02 02 Original Original
Date 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 09/03/2012 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 19/03/2013 09/03/2012 09/03/2012
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Minimum Equipment List Do‐328 ‐100
Acronyms A/C
Aircraft
A – C
Alternating Current
AAS
Anti‐Ice Advisory System
AC
Advisory Circular
ACMP
Alternating Current Main Pump
ACO
Aircraft Certification Office
AD
Airworthiness Directive
ADC
Air Data Computer
ADF
Automatic Direction Finding
ADg
Accidental Damage
ADP
Automatic Data Processing
AECMA
Association Europeenne des Constructeurs de Matériel Aerospatial
AEG
Aircraft Evaluation Group
AEP
Age Exploration Program
AFT
Aft
AHRS
Attitude and Heading Reference System
ALD
Airworthiness Limitations Document
ALI
Airworthiness Limitation Item
AMM
Aircraft Maintenance Manual
APU
Auxiliary Power Unit
ATA
Air Transport Association
ATC
Air Traffic Control
ATPCS
Automatic Take‐off Power Control System
Engineering Department
Minimum Equipment List Do‐328 ‐100
BITE
Built–In Test Equipment
BO
Borescope
CA
Criticality Analysis
CAA
Civil Aviation Authority
CAC
Crew Alerting Computer
Cal
Calendar
CDH
Control Delivery Head
CDL
Configuration Deviation List
CMM
Component Maintenance Manual
CMP
Continuous Maintenance Program
CMR
Certification Maintenance Requirement
CAT
Category
CPCP
Corrosion Prevention and Control Program
CVR
Cockpit Voice Recorder
DC
Direct Current
DCMP
Direct Current Main Pump
DI
Detailed Inspection
DME
Distance Measuring Equipment
DON
Dornier Standard
DPI
Dye Penetrant Inspection
DS
Discard
DT
Damage Tolerance
EC
Eddy Current
ECS
Environmental Control System
Engineering Department
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Minimum Equipment List Do‐328 ‐100
ECTM
Engine Condition Trend Monitoring
ED
Environmental Deterioration
EDU
Engine Diagnostic Unit
EFCV
Ejector Flow Control Valve
EFIS
Electronic Flight Instrument System
ELT
Emergency Locator Transmitter
EMM
Engine Maintenance Manual
EMSG
European Maintenance System Guide
E/POV
Electro–Pneumatic Outflow Valve
EPS
Emergency Power Supply
EPSU
Emergency Power Supply Unit
ERL
Economic Repair Life
EWIS
Electrical Wiring Interconnection System
FAA
Federal Aviation Administration
FADEC
Full Authority Digital Engine Control
FAR
Federal Aviation Regulation
FC
Flight Cycle
FCk
Functional Check
FD
Fatigue Damage
FDR
Flight Data Recorder
FH
Flight Hour
FI
Flight Idle
FL
Flight Level
FLP
Fleet Leader Program
Engineering Department
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Flt
Flight(s)
FMEA
Failure Mode and Effects Analysis
FMEC A
Failure Mode, Effects and Criticality Analysis
FR
Frame
ft
Foot / Feet
FWD
Forward
GPS
Global Positioning System
GPW
Ground Proximity Warning
GPWS
Ground Proximity Warning System
GSE
Ground Support Equipment
GVI
General Visual Inspection
HF
High Frequency
HIRF
High Intensity Radiated Fields
HMU
Hydro‐Mechanical Unit
HP
High Pressure
HSI
Hot Section Inspection
IN
Inspection
IRS
Inertial Reference System
ISC
Industry Steering Committee
ISMP
Integrated Structural Maintenance Program
ITT
Inter Turbine Temperature
JAA
Joint Airworthiness Authorities
JAR
Joint Airworthiness Requirement
L
Liter
Engineering Department
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Minimum Equipment List Do‐328 ‐100
LBA
Luftfahrt Bundesamt
LC
Line Check
LCF
Low Cycle Fatigue
LH
Left Hand
LOC
Locator LP Liquid Penetrant
LP
Low Pressure
LRU
Line Replaceable Unit
LSA
Logistic Support Analysis
LU
Lubrication
MAP
Maintenance Analysis Policy & Procedures
MaPeI
Major Periodic Inspection
MEL
Minimum Equipment List
MII
Major Inspection Interval
MLDIC
Maintenance and Limitations Document for Intensive Care
MLG
Main Landing Gear
MLS
Microwave Landing System
MMEL
Master Minimum Equipment List
MMH/FH
Maintenance Man Hours/Flight Hour
MP
Magnetic Particle
MPD
Maintenance Planning Document
MPDH
Maintenance Program Development Handbook
MPI
Magnetic Particle Inspection
MPP
Maintenance Program Proposal
MR
Manufacturer Recommendation
Engineering Department
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Minimum Equipment List Do‐328 ‐100
MRB
Maintenance Review Board
MSC
Maintenance Steering Committee
MSG–3
Maintenance Steering Group – 3rd task force
MSI
Maintenance Significant Item
MTA
Maintenance Task Analysis
MTBF
Mean Time Between Failure
MTD
Maintenance Task Description
MTH
Month(s)
MWG
Maintenance Working Group
NAA
National Aviation Authority
NDMT
Non‐Deletable Maintenance Task
NDT
Non Destructive Test
NH
High Compressor Speed
NL
Low Compressor Speed
NLG
Nose Landing Gear
NP
Propeller Speed
NR
National Requirement
NRV
Non Return Valve
NTM
Non Destructive Testing Manual
OC
Operational Check
OH
Overhaul
OI
Opportunity Inspection
Oxy
Oxygen
PBE
Protective Breathing Equipment
Engineering Department
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Minimum Equipment List Do‐328 ‐100
PCU
Prop Control Unit
PIN
Part Identification Number
PL
Power Lever
PMP
Primary Maintenance Process
PN
Part Number
POV
Pneumatic Outflow Valve
PPH
Policy and Procedure Handbook
PR+R
Pressure Regulator and Relief Valve
PSEU
Proximity Switch Electronic Unit
PSU
Passenger Service Unit
PT
Power Turbine
PWC
Pratt & Whitney Canada
QPA
Quantity Per Aircraft
Qty
Quantity
R
Rating
RAC
Reglamentos Aeronáuticos de Colombia
RF
Mandatory Retrofit
RH
Right Hand
RPM
Revolutions Per Minute
RS
Restoration
Ref
Reference
Rev
Revision
SB
Service Bulletin
SDI
Special Detailed Inspection
Engineering Department
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Minimum Equipment List Do‐328 ‐100
SIP
Structures Inspection Program
SL
Safe Life
SMP
Standard Maintenance Program
SSI
Structural Significant Item
STA
Station
STBY
Standby
SV
Servicing
TBD
To Be Determined
TBO
Time Between Overhaul
TC
Tire Change
TCAS
Traffic Control Alerting System
TCS
Touch Control Steering
TI
Threshold Inspection
TII
Threshold Inspection Interval
TLD
Time Limited Dispatch
TPS
Temporary Protection System
TT
Tap Test
UT
Ultrasonic Test
VC
Visual Check
VDR
Vendor
VHF
Very High Frequency
VI
Visual Inspection
VIP
Very Important Person
VLF
Very Low Frequency
Engineering Department
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VOR
VHF Omni–directional Radio Range
WF
Fuel Flow
WG
Working Group
WO
W Weight on Wheel
WY
Weekly
XR
X‐Ray
YRS
Years
Engineering Department
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Minimum Equipment List Do‐328 ‐100
Definitions 1. System Definitions. System numbers are based on the Air Transport Association (ATA) Specification Number 100 and items are numbered sequentially. a. "Item" (Column 1) means the equipment, system, component, or function listed in the "Item"column. b. "Number Installed" (Column 3) is the number (quantity) of items normally installed in the aircraft. This number represents the aircraft configuration considered in developing this MMEL. Should the number be a variable (e.g., passenger cabin items) a number is not required. c. "Number Required for Dispatch" (Column 4) is the minimum number (quantity) of items required for operation provided the conditions specified in Column 4 are met. NOTE: Where the MMEL shows a variable number required for dispatch, the MEL must reflect the actual number required for dispatch or an alternate means of configuration control approved the Administrator. d. "Remarks or Exceptions" (Column 5) in this column includes a statement either prohibiting or permitting operation with a specific number of items inoperative, provisos (conditions and limitations) for such operation, and appropriate notes. e. A vertical bar (change bar) in the margin indicates a change, addition or deletion in the adjacent text for the current revision of that page only. The change bar is dropped at the next revision of that page. 2."Airplane/Rotorcraft Flight Manual" (AFM/RFM) is the document required for type certification and approved by the responsible FAA Aircraft Certification Office. The FAA approved AFM/RFM for the specific aircraft is listed on the applicable Type Certificate Data Sheet. 3."As required by FAR/RAC" means that the listed item is subject to provisions (restrictive or permissive) expressed in the Federal Aviation Regulations operating rules. The number of items required by the FAR/RAC must be operative. When the listed item is not required by FAR/RAC it may be inoperative for time specified by repair category. 4. Each inoperative item must be placarded to inform and remind the crewmembers and maintenance personnel of the equipment condition. Engineering Department
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Minimum Equipment List Do‐328 ‐100
NOTE: To the extent practical, placards should be located adjacent to the control or indicator for the item affected; however, unless otherwise specified, placard wording and location will be determined by the operator. 5. "‐" symbol in Column 3 and/or Column 4 indicates a variable number (quantity) of the item installed. 6. "Deleted" in the remarks column after a sequence item indicates that the item was previously listed but is now required to be operative if installed in the aircraft. 7. "ER" refers to extended range operations of a two‐engine airplane which has a type design approval for ER operations and complies with the provisions of Advisory Circular 120‐42A. 8. "Federal Aviation Regulations" (FAR) means the applicable portions of the Federal Aviation Act and Federal Aviation Regulations. 9. "Flight Day" means a 24 hour period (from midnight to midnight) either Universal Coordinated Time (UCT) or local time, as established by the operator, during which at least one flight is initiated for the affected aircraft. 10. "Icing Conditions" means an atmospheric environment that may cause ice to form on the aircraft or in the engine(s). 11. Alphabetical symbol in Column 5 indicates a proviso (condition or limitation) that must be complied with for operation with the listed item inoperative. 12. "Inoperative" means a system and/or component malfunction tothe extent that it does not accomplish its intended purposeand/or is not consistently functioning normally within itsapproved operating limit(s) or tolerance(s). 13. "Notes:" in Column 5 provides additional information for crewmember or maintenance consideration. Notes are used to identify applicable material which is intended to assist with compliance, but do not relieve the operator of the responsibility for compliance with all applicable requirements. Notes are not apart of the provisos. 14. Inoperative components of an inoperative system: Inoperative items which are components of a system which is inoperative are usually considered components directly associated with and having no other function than to support that system. (Warning/caution systems associated with the inoperative system must be operative unless relief is specifically authorized per the MMEL).
Engineering Department
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15. "(M)" symbol indicates a requirement for a specific maintenance procedure which must be accomplished prior to operation with the listed item inoperative. Normally these procedures are accomplished by maintenance personnel; however, other personnel may be qualified and authorized to perform certain functions. Procedures requiring specialized knowledge or skill, or requiring the use of tools or test equipment should be accomplished by maintenance personnel. The satisfactory accomplishment of all maintenance procedures, regardless of who performs them, is the responsibility of the operator. Appropriate procedures are required to be published as part ofthe operator's manual or MEL. 16. "(O)" symbol indicates a requirement for a specific operations procedure which must be accomplished in planning for and/or operating with the listed item inoperative. Normally these procedures are accomplished by the flight crew; however, other personnel may be qualified and authorized to perform certain functions. The satisfactory accomplishment of allprocedures, regardless of who performs them, is the responsibility of the operator. Appropriate procedures are required to be published as a part of the operator's manual or MEL. NOTE: The (M) and (O) symbols are required in the operator's MEL unless otherwise authorized by the Administrator. 17. "Deactivated" and "Secured" means that the specified component must be put into an acceptable condition for safe flight. An acceptable method of securing or deactivating will be established by the operator. 18. "Visual Flight Rules" (VFR) is as defined in FAR Part 91 and RAC 4.2.2.3. This precludes a pilot from filing an Instrument Flight Rules (IFR) flight plan. 19. "Visual Meteorological Conditions" (VMC) means the atmospheric environment is such that would allow a flight to proceed under the visual flight rules applicable to the flight.This does not preclude operating under Instrument Flight Rules. 20. "Visible Moisture" means an atmospheric environment containing water in any form that can be seen in natural or artificial light; for example, clouds, fog, rain, sleet, hail, or snow. 21. "Passenger Convenience Items" means those items related to passenger convenience, comfort or entertainment such as, but not limited to, galley equipment, movie equipment, ash trays, stereo equipment, overhead reading lamps, etc.
Engineering Department
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22. Repair Intervals: All users of an MEL approved under FAR 121, 125, 129 and 135 must effect repairs of inoperative systems or components, deferred in accordance with the MEL, at or prior to the repair times established by the following letter designators: Category A. Items in this category shall be repaired within the time interval specified in the remarks column of the operator's approved MEL. Category B. Items in this category shall be repaired within three (3) consecutive calendar days (72 hours), excluding the day the malfunction was recorded in the aircraft maintenance record/logbook. For example, if it were recorded at 10 a.m. on January 26th, the three day interval would begin at midnight the 26th and end at midnight the 29th. Category C. Items in this category shall be repaired within ten (10) consecutive calendar days (240 hours), excluding the day the malfunction was recorded in the aircraft maintenance record/logbook. For example, if it were recorded at 10 a.m. on January 26th, the 10 day interval would begin at midnight the 26th and end at midnight February 5th. Category D. Items in this category shall be repaired within one hundred and twenty (120) consecutive calendar days (2880 hours), excluding the day the malfunction was recorded in the aircraft maintenance log and/or record. 23. Electronic fault alerting system ‐ General Dornier 328 equipped with Engine Indicating and Crew Alerting Systems (EICAS) provide different priority levels of system messages (WARNING, CAUTION, ADVISORY, STATUS and MAINTENANCE). Any messages that affects airplane dispatch status will be displayed at a STATUS message level or higher. The absence of an EICAS STATUS or higher level (WARNING, CAUTION, ADVISORY) indicates that the system/component is operating within its approved operating limits or tolerances. System conditions that result only in a maintenance level message, i.e. no correlation with a higher level EICAS message, do not affect dispatch and do not require action other than as addressed within an operators standard maintenance program. 24. "Administrative control item" means an item listed by the operator in the MEL for tracking and informational purposes. It may be added to an operator's MEL by approval of the Principal Operations Inspector provided no relief is granted, or provided conditions and limitations are contained in an approved document (i.e. Structural Repair Manual, airworthiness directive, etc.). Engineering Department
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If relief other than that granted by an approved document is sought for an administrative control item, a request must be submitted to the Administrator. If the request results in review and approval by the FOEB, the item becomes an MMEL item rather than an administrative control item. 25. "***" symbol in Column 1 indicates an item which is not required by regulation but which may have been installed on some models of aircraft covered by this MMEL. This item may be included on the operator's MEL after the approving office has determined that the item has been installed on one or more of the operator's aircraft. The symbol, however, shall not be carried forward into the operator's MEL. It should be noted that neither this policy nor the use of this symbol provide authority to install or remove an item from an aircraft. 26. "Excess Items" means those items that have been installed that are redundant to the requirements of the FARs. 27. "Day of Discovery" is the calendar day an equipment/instrument malfunction was recorded in the aircraft maintenance log and or record. This day is excluded from the calendar days or flight days specified in the MMEL for there pair of an inoperative item of equipment. This provision is applicable to all MMEL items, i.e., categories "A, B, C, and D."
Engineering Department
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Minimum Equipment List Do‐328 ‐100
CHAPTER 1 INTRODUCTION
Engineering Department
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1. Preamble The following is applicable for authorized certificate holders operating under Reglamentos Aeronáuticos de Colombia (RAC) Part 4.5: The RAC require that all equipment installed on an aircraft in compliance with the Airworthiness Standards and the Operating Rules must be operative. However, the Rules also permit the publication of a Minimum Equipment List (MEL) where compliance with certain equipment requirements is not necessary in the interests of safety under all operating conditions. Experience has shown that with the various levels of redundancy designed into aircraft, operation of every system or installed component may not be necessary when the remaining operative equipment can provide an acceptable level of safety. A Master Minimum Equipment List (MMEL) is developed by the FAA, with participation by the aviation industry, to improve aircraft utilization and there by provide more convenient and economic air transportation for the public. The FAA approved MMEL includes those items of equipment related to airworthiness and operating regulations and other items of equipment which the Administrator finds may be inoperative and yet maintain an acceptable level of safety by appropriate conditions and limitations; it does not contain obviously required items such as wings, flaps, and rudders. The MMEL is the basis for development of individual operator MELs which take into consideration the operator's particular aircraft equipment configuration and operational conditions. Operator MELs, for administrative control, may include items not contained in the MMEL; however, relief for administrative control items must be approved by the Administrator. An operator's MEL may differ in format from the MMEL, but cannot be less restrictive than the MMEL. The individual operator's MEL, when approved and authorized, permits operation of the aircraft with inoperative equipment. Equipment not required by the operation being conducted and equipment in excess of FAR/UAEAC requirements are included in the MEL with appropriate conditions and limitations. The MEL must not deviate from the AircraftFlight Manual Limitations, Emergency Procedures or with AirworthinessDirectives. It is important to remember that all equipment related tothe airworthiness and the operating regulations of the aircraft notlisted on the MMEL must be operative. Suitable conditions and limitations in the form of placards, maintenance procedures, crew operating procedures and other restrictions as necessary are specified in the MEL to ensure that an acceptable level of safety is maintained.
Engineering Department
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The MEL is intended to permit operation with inoperative items of equipment for a period of time until repairs can be accomplished. It is important that repairs be accomplished at the earliest opportunity. In order to maintain an acceptable level of safety and reliability the MMEL establishes limitations on the duration of and conditions for operation with inoperative equipment. The MEL provides for release of the aircraft for flight with inoperative equipment. When an item of equipment is discovered to be inoperative, it is reported by making an entry in the Aircraft Maintenance Record/Logbook as prescribed by RAC. The item is then either repaired or may be deferred per the MEL or other approved means acceptable to the Administrator prior to further operation. MEL conditions and limitations do not relieve the operator from determining that the aircraft is in condition for safe operation with items of equipment inoperative. When these requirements are met, an Airworthiness Release, Aircraft Maintenance Record/Logbook entry, or other approved documentation is issued as prescribed by RAC. Such documentation is required prior to operation with any item of equipment inoperative. Operators are responsible for exercising the necessary operational control to ensure that an acceptable level of safety is maintained. When operating with multiple inoperative items, the interrelationships between those items and the effect on aircraft operation and crew workload will be considered. Operators are to establish a controlled and sound repair program including the parts, personnel, facilities, procedures, and schedules to ensure timely repair. WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT OF THE PREAMBLE, DEFINITIONS, AND THE CONDITIONS AND LIMITATIONS SPECIFIED IN THE MEL IS REQUIRED. 2. Covered Fleet Aircraft
Model
S/N
Dornier Dornier
DO‐328‐100 mod. 20 DO‐328‐100 mod. 20
3084 3039
Engineering Department
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Minimum Equipment List Do‐328 ‐100
CHAPTER 2 SYSTEMS AND SUBSYSTEMS
Engineering Department
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Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING C 1 0 May be inoperative provided 1 ‐ Cabin AltitudeWarning System operations are conducted at or below 10,000 feet MSL. 2 ‐ Cabin TemperatureControl System C 1 0 May be inoperative provided Manual 1 ‐ Automatic Mode Mode operates normally. C 1 0 May be inoperative provided 2 ‐ Manual Mode Automatic Mode operates normally. 3 ‐ Flight Compartment Temperature ControlSystem C 1 0 May be inoperative provided Manual 1 ‐ Automatic Mode Mode operates normally. C 1 O May be inoperative provided 2 ‐ Manual Mode Automatic Mode operates normally. C 2 0 M) May be inoperative provided: 4 ‐ Recirculation Fans a) Inoperative Fan(s) is deactivated, b) Both ECS Packs operate normally, and c) ECS Flow Mode is operated in HIGH. (M) This item may be performed by a qualified crewmember. To deactivate inoperative fan, pull and secure C/B in cockpit for affected fan using a lockout ring. 5 ‐ EFIS Fan B 1 0 (M) May be inoperative provided: a) Inoperative Fan is deactivated, b) Avionic Fan operates c) Both ECS Packs operate normally, and Engineering Department
Página: 21‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING B 1 0 d) ECS Flow Mode is operated 5 ‐ EFIS Fan in HIGH. (Cont.) (M) This item may be performed by a qualified crewmember. To deactivate inoperative fan, pull and secure C/B in cockpit for affected fan using a lockout ring. B 1 0 (M) May be inoperative provided: 6 ‐ Avionic Fan a) Inoperative Fan isdeactivated, b) EFIS Fan operates normally, c) Both ECS Packs operate normally, and d) ECS Flow Mode is operated in HIGH. (M) This item may be performed by a qualified crewmember. To deactivate inoperative fan, pull and secure C/B in cockpit for affected fan using a lockout ring. C 2 1 (M) (O) One may be inoperative 7 ‐ Heat Exchanger (HX) Fans provided: a) Inoperative Fan is deactivated, b) Single ECS Pack Takeoff and Landing procedures are developed and used, c) Associated Pack is not operated on the ground, d) Associated Pack is not operated in‐flight at airspeeds below 120 KIAS, and e) During single Pack operations, ECS Flow Mode is operated in HIGH. (M) This item may be performed by a qualified crewmember. To deactivate inoperative fan, pull and secure C/B in cockpit for affected fan using a lockout ring. Engineering Department
Página: 21‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING C 2 1 (O) a) Ensure associated ECS Pack is 7 ‐ Heat Exchanger (HX)Fans OFF for all ground operations. (Cont.) b) After take‐off select associated ECS Pack ON with airspeed greater than 120 KIAS, and above 1.500 AGL. c) Prior to landing, select associated ECS Pack OFF at “Before Landing Checklist” with airspeed above 120 KIAS. C 1 0 (O) May be inoperative provided: 8 ‐ ECS ECON Flow Mode a) HIGH Mode operates normally, and b) Flight Planning is based on ECS HIGH Fuel Consumption. (O) Operate ECS flow mode in HIGH during all ECS Operations. 9 ‐ Cabin Pressurization Control System (CPCS) C 1 0 (M) (O) May be inoperative provided: 1 ‐ Automatic System a) Manual Pressurization System operates normally, b) CPCS Automatic Controller is deactivated, c) EICAS CPCS System Page operates normally, d) Dump function is verified to operate normally, and e) Alternate procedures for controlling Pressurization manually are established and used. (O) MAN CABIN ALT Selector as required to follow pressurization schedule. Do not exceed 500 fpm. Do not exceed CABIN DIFF PRESS of 6.75. Do not exceed CABIN ALT of 8000 ft. Engineering Department
Página: 21‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 9 ‐ Cabin Pressurization Control C 1 0 (M) This item may be performed by a qualified crewmember. To deactivate System (CPCS) pull and secure the CPCS AUX and (Cont.) CPCS PRIMARY C/B using a lockout ring. 2 ‐ Automatic and Manual C 2 0 (M) (O) May be inoperative provided: a) Flight restricted to 10,000 systems feet or below, b) Either outflow valve is secured open, and c) Both ECS packs operate normally. (O) a) Flight are restricted to 10.000 ft or below. b) Operate both ECS packs. (M) To secure Electro‐pneumatic OFV in open position a) Press CAB DUMP pushbutton Sw. b) Pull and secure CAB PRESS DUMP, CAB PRESS 1, CAB PRESS 2 C/B. To secure Pneumatic OFV in open position: a) Open the Vacuum Line at the valve. b) Placard Controlled “INOPERATIVE VACUUM LINE DISCONNECTED” C 1 0 (M) May be inoperative provided: 3 ‐ CPCS Backup Module a) CPCS Backup Module is deactivated, and b) EICAS "CPCS MISCOMPARE" Caution Message is removed. (M) This item may be performed by a qualified crewmember. To deactivate, pull and secure the CPCS Backup Module C/B using a lockout ring. Engineering Department
Página: 21‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 9 – Cabin Pressurization Control System (CPCS) (Cont.) C 1 0 (O) May be inoperative provided: 4 ‐ CPCS Digital Display a) System page operates normally, and b) Alternate procedures are established and used to verify landing elevation on the CPCS/OXY page. (O) Using the CPCS/OXY system page, verify landing elevation before each take off. 10 ‐ "MAN" Annunciator Light on C 1 0 (M) Light may fail to illuminate provided: PRESSURIZATION Control AUTO/MAN a) Pressurization AUTO/MAN Pushbutton (Overhead Panel) selection function is verified to operate normally, b) EICAS "CPCS CTRL MODE MAN" Status Message is verified to operate normally, and c) EICAS CPCS System Page operates normally. (M) This item may be performed by a qualified crewmember. a) Select the PRESSURIZATION AUTO/MAN Pushbutton to MAN b) Verify the CPCS CTRL MODE MAN Blue CAS Status Message illuminates on EICAS c) Select the PRESSURIZATION AUT/MAN Pushbutton to AUTO d) Verify the CPCS CTRL MODE MAN Blue CAS Status Message extinguishes. 11 ‐ "MAN" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate COCKPIT Temperature Control Mode provided: Pushbutton (Overhead Panel) a) Cockpit Temperature Control Mode selection function is verified to operate Engineering Department
Página: 21‐6 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions normally, 21 AIR CONDITIONING b) EICAS CPCS System Page 11 ‐ "MAN" Annunciator Light on C 1 0 operates normally, and COCKPIT Temperature Control Mode c) Alternate procedures for Pushbutton (Overhead Panel) determining Cockpit (Cont.) Temperature Control Mode are established and used. (O) Select the cockpit Temp Control Mode Selector to MAN position (Pressed In) or AUTO position (Pressed Out). (M) This item may be performed by a qualified crewmember. With the ECS System Page Displayed: a) Select the Cockpit Temp Control Mode pushbutton In (Flush) b) Note the digital Cockpit Temperature readout is replaced by dashes (‐‐‐) c) Select the cockpit Temp Control Mode Pushbutton to the out position (not flush) d) Note the dashes (‐‐‐) in the Cockpit Temperature readout is replaced by a digital readout of Cockpit temperature. 12 ‐ "MAN" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate CABIN Temperature Control Mode provided: Pushbutton (Overhead Panel) a) Cabin Temperature Control Mode selection function is verified to operate normally, b) EICAS CPCS System Page operates normally, and c) Alternate procedures for determining Cabin Temperature Control Mode are established and used. Engineering Department
Página: 21‐7 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 12 ‐ "MAN" Annunciator Light on C 1 0 (O) Select the cockpit Temp Control Mode Selector to MAN position CABIN Temperature Control Mode (Pressed In) or AUTO position Pushbutton (Overhead Panel) (Pressed Out). (Cont.) (M) This item may be performed by a qualified crewmember. With the ECS System Page Displayed: a) Select the Cockpit Temp Control Mode pushbutton In (Flush) b) Note the digital Cockpit Temperature readout is replaced by dashes (‐‐‐) c) Select the cockpit Temp Control Mode Pushbutton to the out position (not flush) d) Note the dashes (‐‐‐) in the Cockpit Temperature readout is replaced by a digital readout of Cockpit temperature. 13 ‐ Vertical (Pack Valve Open) Flow C 2 0 (M) (O) Light(s) may fail to illuminate Bar Lights on ECS PACK Pushbuttons provided: (Overhead Panel) a) Associated Pack(s) is verified to operate normally, b) Associated PACK Pushbutton "OFF" Annunciator Light(s) is verified to operate normally, c) EICAS ECS System Page operates normally, and d) Alternate procedures for determining associated Pack(s) operational status are established and used. (O) a) Confirm PACK Pushbutton selected ON (IN) or OFF (OUT) b) Verify Pack Valve position Via the Pack Valve Synoptic on ECS system page. Engineering Department
Página: 21‐8 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 13 ‐ Vertical (Pack Valve Open) Flow C 2 0 (M) This item may be performed by a qualified crewmember. Bar Lights on ECSPACK Pushbuttons a) Run associated BLEED (Overhead Panel) selected ON, select affected (Cont.) PACK Pushbutton ON b) With associated BLEED selected ON, select affected PACK Pushbutton ON c) Verify Pack pushbutton OFF, annunciation light extinguishes d) Verify PACK Valve Synoptic on ECS System page show OPEN e) Select PACK Pushbutton OFF (pushbutton Out) f) Verify the associated PACK Pushbutton OFF Annunciator Light illuminates, and that g) The PACK valve synoptic on ECS System page shows Closed. 14 ‐ "OFF" Annunciator Lights on ECS C 2 0 (M) (O) Light(s) may fail to illuminate PACK Pushbuttons (Overhead Panel) provided: a) Associated Pack(s) is verified to operate normally, b) Associated PACK Pushbutton Vertical (Pack Valve Open) Flow Bar Light(s) is verified to operate normally c) EICAS ECS System Page operates normally, and d) Alternate procedures for determining associated Pack(s) operational status are established and used. (O) Ensure PACK Pushbutton is ON (IN) or OFF (OUT). Engineering Department
Página: 21‐9 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 14 ‐ "OFF" Annunciator Lights on ECS C 2 0 (M) This item may be performed by a qualified crewmember. PACK Pushbuttons (Overhead Panel) a) Run associated engine (Cont.) b) With associated BLEED selected ON, select affected PACK Pushbutton ON c) Verify Pack pushbutton Vertical Flow Bar Annunciation Light illuminates d) Verify PACK Valve Synoptic on ECS System page show OPEN e) Select PACK Pushbutton OFF (pushbutton Out) f) Verify the associated Pack pushbutton Vertical Flow Bar Annunciation Light illuminates, and that g) The PACK valve synoptic on ECS System page shows Closed. 15 ‐ "HIGH" Annunciator Light on ECS C 1 0 (M) (O) Light may fail to illuminate FLOW MODE Pushbutton (Overhead provided: Panel) a) ECS FLOW MODE selection function is verified to operate normally, b) EICAS ECS System Page operates normally, and c) Alternate procedures for determining ECS Flow Mode are established and used. (O) a) Select the ECS Flow mode to HIGH, ECS flow mode pushbutton out (not flush), or b) Select the ECS flow mode to ECON (dark), ECS flow mode pushbutton in (flush) c) Confirm ECS flow status on the ECS system page Engineering Department
Página: 21‐10 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 15 ‐ "HIGH" Annunciator Light on ECS C 1 0 (M) This item may be performed by a qualified crewmember. FLOW MODE Pushbutton (Overhead With the ECS system page selected: Panel) a) Select the ECS flow mode (Cont.) pushbutton in (flush) b) Note the HIGH status message on the ECS system page c) Select the ECS flow mode pushbutton to the out position (not flush) d) Note the ECONOMY status message on the ECS system page. 16 ‐ "OFF" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate provided: RECIRC FAN Pushbutton Light a) Recirculation Fans are (Overhead Panel) deactivated, b) Both ECS Packs operate normally, c) "HIGH" Light on ECS FLOW MODE Pushbutton operates d) ECS System is operated in HIGH Mode. (O) Operate the ECS system in the HIGH mode (M) This item may be performed by a qualified crewmember. Pull and secure the recirculation Fans C/B using a lockout ring. 17 ‐ "OFF" Annunciator Light on EFIS C 1 0 (M) (O) Light may fail to illuminate FAN Pushbutton Light (Overhead provided: Panel) a) EFIS Fan is verified to operate normally, b) EFIS FAN Pushbutton "FAIL" Annunciator Light operates normally, c) EICAS "EFIS FAN FAIL" Caution Message operates. Engineering Department
Página: 21‐11 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING d) Alternate procedures for 17 ‐ "OFF" Annunciator Light on EFIS C 1 0 determining EFIS Fan FAN Pushbutton Light (Overhead operational status are Panel) established and used. (Cont.) (O) Ensure that the EFIS FAN pushbutton is selected ON (IN) or OFF (OUT) AS REQUIRED (M) This item may be performed by a qualified crewmember. a) Select the EFIS, AVIONIC and RECIRC FAN pushbutton OFF b) Select the EFIS FANS pushbutton In (Flush) c) Audibly note the operation of the EFIS fans d) Select the EFIS FANS pushbutton to the out position (Not Flush) e) Audibly note that the operation of the EFIS fans ceases. 18 ‐ "FAIL" Annunciator Light on EFIS C 1 0 (M) (O) Light may fail to illuminate FAN Pushbutton (Overhead Panel) provided: a) EFIS Fan is verified to operate normally, b) EFIS FAN Pushbutton "OFF" Annunciator Light operates normally, c) EICAS "EFIS FAN FAIL" Caution Message operates normally, and d) Alternate procedures for determining EFIS Fan operational status are established and used. (O) Ensure that the EFIS FAN pushbutton is selected ON (IN) or OFF (OUT) AS REQUIRED Engineering Department
Página: 21‐12 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 18 ‐ "FAIL" Annunciator Light on EFIS C 1 0 (M) This item may be performed by a qualified crewmember. FAN Pushbutton (Overhead Panel) a) Select EFIS Fan pushbutton (Cont.) ON b) Note EFIS Fan operation audibly c) Pull EFIS Fan C/B d)Note EFIS FAN FAIL Caution illuminates on EICAS e) Reset C/B f) Select EFIS Fan pushbutton OFF g) Note EFIS Fan operation ceases audibly 19 ‐ "OFF" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate AVIONIC FAN Pushbutton (Overhead provided: Panel) a) AVIONIC Fan is verified to operate normally, b) AVIONIC FAN Pushbutton "FAIL" Annunciator Light operates normally, c) EICAS "AVIONIC FAN FAIL" Caution Message operates normally, and d) Alternate procedures for determining AVIONIC Fan operational status are established and used. (O) Ensure that the AVIONIC FAN pushbutton is selected ON (IN) or OFF (OUT) AS REQUIRED (M) This item may be performed by a qualified crewmember. a) Select AVIONIC Fan pushbutton ON b) Note AVIONIC Fan operation audibly c) Pull AVIONIC Fan C/B d)Note AVIONIC FAN FAIL Caution illuminates on EICAS Engineering Department
Página: 21‐13 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 21 AIR CONDITIONING 19 ‐ "OFF" Annunciator Light on C 1 0 e) Reset C/B AVIONIC FAN Pushbutton (Overhead f) Select AVIONIC Fan Panel) pushbutton OFF (Cont.) g) Note AVIONIC Fan operation ceases audibly 20 – “FAIL” Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate provided: AVIONIC FAN Pushbutton (Overhead a) AVIONIC Fan is verified to Panel) operate normally, b) AVIONIC FAN Pushbutton "FAIL" Annunciator Light operates normally, c) EICAS "AVIONIC FAN FAIL" Caution Message operates normally, and d) Alternate procedures for determining AVIONIC Fan operational status are established and used. (O) Ensure that the AVIONIC FAN pushbutton is selected ON (IN) or OFF (OUT) AS REQUIRED (M) This item may be performed by a qualified crewmember. a) Select AVIONIC Fan pushbutton ON b) Note AVIONIC Fan operation audibly c) Pull AVIONIC Fan C/B d)Note AVIONIC FAN FAIL Caution illuminates on EICAS e) Reset C/B f) Select AVIONIC Fan pushbutton OFF g) Note AVIONIC Fan operation ceases audibly
Engineering Department
Página: 22‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 22 – AUTO FLIGHT C 1 0 May be inoperative provided 1 – Autopilot approach minimums do not require it's use. C 2 1 One may be inoperative provided 2 ‐ Control Wheel Disengage Switches the autopilot is not utilized at less than the initial approach altitude. C 2 0 May be inoperative provided Autopilot is not used. 3 ‐ Touch Control Steering (TCS) Switches C 2 0 4 ‐ Go Around (GA) Switches (on Power C 2 0 (O)May be inoperative provided Levers) alternate Go Around Procedures are established and used. (O For go around operations from side(s) with inoperative go around power lever switches: a) Disconnect autopilot with control wheel disengage switches b) Rotate to go around attitude by reference to attitude indicator c) Set go around torque by reference to torque indicators. 5 ‐ Flight Guidance Control Unit C 1 0 May be inoperative provided Autopilot and Flight Director are not used. 1 ‐ Reduced Bank Angle (BANK) C 1 0 May be inoperative provided: Mode a) BANK Mode is not used b) Auto Pilot and Flight Director are not engaged in Heading (HDG) Mode if Reduced Bank Angle Synopticis displayed in either Primary Flight Display (PFD). Engineering Department
Página: 22‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 22 – AUTO FLIGHT 5 ‐ Flight Guidance Control Unit (Cont.) B 1 0 May be inoperative provided: 2 ‐ Navigation (NAV) Mode a) NAV Mode is not engaged. b) Auto Pilot and Flight Director are not engaged if" LNAV," "VOR," "LOC," or "AZ" Mode Annunciations are displayed on either Primary Flight Display (PFD). B 1 0 May be inoperative provided: 3‐ Approach (APP) Mode a) Approach Minimums do not require its use, b) APP Mode is not engaged, and c) Auto Pilot and Flight Director are not engaged if "LOC," "*VOR," or "AZ" Mode Annunciations are displayed on either Primary Flight Display (PFD). C 1 0 May be inoperative provided: 4 ‐ Back Course (BC) Mode a) BC Mode is not engaged, and b) Auto Pilot and Flight Director are not engaged if "BC" Mode Annunciation is displayed on either Primary Flight Display (PFD). B 1 0 May be inoperative provided: 5‐ Flight Level Change (FLCH) Mode a) FLCH Mode is not engaged, and b) Auto Pilot and Flight Director are not engaged if "FLCH" Mode Annunciation is displayed on either Primary Flight Display (PFD). Engineering Department
Página: 22‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 22 – AUTO FLIGHT 5 ‐ Flight Guidance Control Unit (Cont.) B 1 0 May be inoperative provided: 6 ‐ Vertical Speed (VS) Mode a) VS Mode is not engaged, and b) Auto Pilot and Flight Director are not engaged if "VS" Mode Annunciation is displayed on either Primary Flight Display (PFD). 7 – Vertical Navigation (VNAV) Mode C 1 0 May be inoperative provided: a) VNAV is not engaged, and b) Auto Pilot and Flight Director are not engaged if "VALT," "VFLCH," or "VPATH" Mode Annunciations are displayed on either Primary Flight Display (PFD). 8 ‐ "BANK" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided Light Reduced Bank Angle Synoptic operates normally on both Primary Flight Displays (PFD). 9 ‐ "NAV" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided Light "NAV" Mode Annunciations operate normally on both Primary Flight Displays (PFD). 10 ‐ "APP" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided Light "LOC" and "VOR" Mode Annunciations operate normally on both Primary Flight Displays (PFD). 11 ‐ "BC" Pushbutton Annunciation C 1 0 Light may fail to illuminateprovided Light "BC" Mode Annunciationsoperate normally on both PrimaryFlight Displays (PFD). Engineering Department
Página: 22‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 22 – AUTO FLIGHT 5 ‐ Flight Guidance Control Unit (Cont.) 12 ‐ "FLCH" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided "FLCH" Mode Annunciations Light operate normally on both Primary Flight Displays (PFD). 13 ‐ "VS" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided "VS" Mode Annunciations operate Light normally on both Primary Flight Displays (PFD). 14 – “VNAV” Pushbutton C 1 0 Light may fail to illuminate provided "VNAV" Mode Annunciations Annunciation Light operate normally on both Primary "VNAV"PushbuttonAnnunciationLight Flight Displays (PFD). 15 ‐ "ALT" Pushbutton Annunciation C 1 0 Light may fail to illuminate provided "ALT" Mode Annunciations operate Light normally on both Primary Flight Displays (PFD). 16 ‐ "CPL" Pushbutton Annunciation C 2 1 One Light may fail to illuminate Lights provided Flight Director Couple Annunciator Arrows operate normally on both PFD's. B 2 0 Light(s) may fail to illuminate provided Flight Director Couple Annunciator Arrows operate normally on both PFD's. 17 ‐ "AP" Pushbutton Annunciation C 2 1 One Light may fail to illuminate Lights provided Autopilot Status ("AP" & "TCS") Annunciations operate normally on both PFD's. B 2 0 Light(s) may fail to illuminate provided Autopilot Status ("AP" & "TCS") Annunciations operate normally on both PFD's. Engineering Department
Página: 22‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 22 – AUTO FLIGHT 6 –Autopilot Disconnect Warning System C 1 0 May be inoperative provided (Aural and PFD Visual Warnings) Autopilot is not used. 7 ‐ Flight Director C 1 0 May be inoperative provided Takeoff Minimums and/or Approach Minimums do not require its use. 8 ‐ Yaw Damper C 1 0 May be inoperative provided Autopilot is not used. INTENCIONALMENTE EN BLANCO
Engineering Department
Página: 23‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 23 COMMUNICATIONS 1 – Communications Systems (VHF, HF, UHF) D 2 1 (O) May be inoperative provided both 1 ‐ VHF Tx/Rx VHF are operative for IFR and extended overwater flights and is not powered by the hot battery Bus. (O) Verify proper communication with HF Tx/ Rx. D 1 0 (O) One may inoperative provided HF 2 ‐ HF Tx/Rx Tx/Rx are operative for IFR and extended overwater flights and is not powered by the hot battery Bus or essential bus. (O) Verify proper communication with VHF Tx/ Rx. B 1 0 (O) May be inoperative provided: 2 ‐ Passenger Address System a) Alternate, normal and emergency procedures and/or operating restrictions are b) Flight Deck/Cabin Interphone established and used, and System and aural alerting (chime) operates normally. NOTE: Any station that operates normally may be used. (O) Use passenger address system as alternate procedures for all necessary internal communications. NORMAL PROCEDURES: Before take‐ off cabin crew will make a direct voice communications with all passengers. All pre‐flight announcements must be completed prior to take‐off. All in‐ flight announcements are by direct voice communication with passengers. Engineering Department
Página: 23‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 23 COMMUNICATIONS B 1 0 EMERGENCY PROCEDURES: Flight 2 ‐ Passenger Address System deck crew uses interphone to (Cont.) communicate with cabin crew. If required, all emergency announcements will be via direct voice communication with passengers. 3 –Crewmember Interphone System 1 ‐ Flight Deck to Cabin, Cabin B 1 0 (O)May be inoperative provided: a) PA system operates to Flight Deck, Cabin to Cabin normally, and can be used as an alternate communications link between the flight deck and the cabin, and b) Alternate communications procedures between the affected Flight Attendants station(s) and the flight deck are established and used. NOTE: Any station that operates normally may be used. (O) Use passenger address system as alternate procedures for all necessary internal communications; verify that the passenger address system is fully operational prior to flight. 2 ‐ Flight Deck toGround C 1 0 (O) May be inoperative provided alternate procedures are established and used. (O) Handmade signals will be used for communication from Flight deck to ground. 4 ‐ Alerting System (Chime/Light) 1 ‐ Flight Deck Call Light B 1 0 May be inoperative provided the flight deck chime is operative. NOTE: The flight deck chime must always be operative. Engineering Department
Página: 23‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 23 COMMUNICATIONS 4 ‐ Alerting System (Chime/Light) (Cont.) 2 ‐ Flight Attendant Call Light B 1 0 May be inoperative provided: a) PA system is operative, and b) Affected light is not used for Lavatory Smoke Detector Alerting. B 1 0 May be inoperative provided: 3 ‐ Flight Attendant Chime a) PA system is operative, and b) Affected Chime is not used for Lavatory Smoke Detector Alerting. 5 ‐ Prerecorded Passenger C 1 0 (O) May be inoperative provided alternate procedures are established Announcement System and used. (O) All announcements must to be made by the flight attendant 6 ‐ Cockpit Voice Recorder System A 1 0 May be inoperative provided: (CVR) a) Flight Data Recorder (FDR) operates normally, and b) Repairs are made within three flight days. 7 – Microphones 1 ‐ Headset/Boom A 2 0 May be inoperative provided: Microphones a) Hand microphones and Headsets are installed and operate normally, b) Flight Data Recorder (FDR) operates normally, and c) Repairs are made within three flight days. 2 ‐ Hand Microphones D 2 0 8 – SELCAL System C 0 0 May be inoperative provided alternate procedures are established and used. D 0 0 May be inoperative provided procedures do not required its use. Engineering Department
Página: 23‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 23 COMMUNICATIONS C 1 0 May be inoperative provided Radio 9 ‐ Clearance Delivery Head (CDH) Management Units (RMU's) operate normally. 10 ‐ Radio Management Units (RMU's) 1 ‐ Nav/Comm Tuning C 2 1 (O)May be inoperative on one RMUprovided: Function a) Back‐up Engine and Navigation Displays of both RMU's operate normally, b) Clearance Delivery Head (CDH) operates normally, and c) Alternate procedures fortuning Nav/Comm's are established and used. 11 ‐ Passenger‐To‐Flight Attendant B 22 11 (M) Individual Call Buttons may be Call Buttons (Lights and Aural Tones) inoperative provided: a) Associated Seat(s) is Blocked and Placarded "DO NOT OCCUPY", b) Inoperative Call Button Light(s), and associated Aural Tones, failed ON are deactivated, and c) If Lavatory Call Buttons are inoperative, Lavatory is not used for any purpose, and affected Lavatory Door is locked closed and Placarded "INOPERATIVE" ‐ DO NOT ENTER. (M) a) If a call button fails, remove affected bulb and placard seat “DO NOT OCCUPY” Blocking Card. b) If a call light fails, placard seat with “DO NOT OCCUPY” Blocking Card. c) If lavatory call button is inoperative, close and lock the door. Placard the door “INOPERATIVE – DO NOT ENTER”. Engineering Department
Página: 24‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER B 1 0 May be inoperative provided: 1 –Transformer Rectifier Unit (TRU) a) DC Voltmeters and all DC Generator and Main Battery EICAS Failure Indications operate normally, b) Both Main DC Batteries operate normally, c) Main DC Batteries are not used for Engine Starts, and d) After Engine Start, Voltage of each Main DC Battery is verified to be a minimum of 23 Volts. 2 ‐ "FAIL" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate Inverter (INV 1/INV 2) Pushbuttons provided: (Overhead Panel) a) Associated Inverter(s) is verified to operate normally, b) Associated INV Pushbutton "OFF" Annunciator Light operates normally, c) EICAS Electric System Page, operates normally, d) Associated "INV 1, or INV 2 FAIL" EICAS Caution(s) is verified to operate normally, and e) Alternate procedures for determining Inverter operational status are established and used. (O) Confirm position of inverter pushbutton IN (On) or OUT (Off), Reference EICAS for abnormal indications. (M) This item may accomplished by a qualified crewmember. a) With aircraft power ON, and the Electric System Page selected; turn both inverters Engineering Department
Página: 24‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER OFF and insure affected 2 ‐ "FAIL" Annunciator Lights on C 2 0 inverter OFF and insure Inverter (INV 1/INV 2) Pushbuttons affected inverter OFF (Overhead Panel) Annunciator light illuminates. (Cont.) b) Turn affected inverters ON and verify the inverter buses are powered. c) Select the other inverter ON, and pull the C/B to the affected inverter. d) Verify fail message on the electric system page illuminates. e) Reset the C/B. 3 ‐ "OFF" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate provided: Inverter(INV 1/INV a) Associated Inverter(s) is 2)Pushbuttons(Overhead Panel) verified to operate normally, b) Associated INV Pushbutton "FAIL" Annunciator Light operates normally, c) EICAS Electric System Page, operates normally, d) Associated "INV 1, or INV 2 FAIL" EICAS Caution(s) is verified to operate normally, and e) Alternate procedures for determining Inverter operational status are established and used. (O) To determine the associated INV pushbutton is selected to OFF, Verify the pushbutton is selected OUT (Not Flush). (M) This item may accomplished by a qualified crewmember. a) With aircraft power ON, and the Electric System Page Engineering Department
Página: 24‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER selected; turn both inverters 3 ‐ "OFF" Annunciator Lights on C 2 0 OFF and insure affected Inverter (INV 1/INV 2) Pushbuttons inverter OFF and insure (Overhead Panel) affected inverter OFF (Cont.) Annunciator light illuminates. b) Turn affected inverters ON and verify the inverter buses are powered. c) Pull the C/B to the affected inverter. (location is #1 A22 and #2 M9) d) Verify INV 1 or INV 2 fail message on the electric system page illuminates. e) Reset the C/B. 4 ‐ "FAIL" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate provided: Alternator (ALTLH/ALT a) Associated Alternator(s) is RH)Pushbuttons(Overhead Panel) verified to operate normally, b) Associated ALT Pushbutton "OFF" Annunciator Light operates normally, c) EICAS Electric System Page, operates normally, d) Associated "L, or R ALTFAIL" EICAS Caution(s) is verified to operate normally, and e) Alternate procedures for determining Alternator operational status are established and used. (O) Confirm position of inverter pushbutton IN (On) or OUT (Off). Reference EICAS for abnormal indications. (M) This item may be performed by a qualified crewmember. With the display inhibit selected, select associate ALT pushbutton ON, verify associated ALT FAIL amber caution message illuminates on EICAS. Engineering Department
Página: 24‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 5 ‐ "OFF" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate provided: Alternator (ALTLH/ALT RH) a) Associated Alternator(s) is Pushbuttons (Overhead Panel) verified to operate normally, b) Associated ALT Pushbutton "FAIL" Annunciator Light operates normally, c) EICAS Electric System Page, operates normally, d) Associated "L, or R ALT FAIL" EICAS Caution(s) is verified to operate normally, and e) Alternate procedures for determining Alternator operational status are established and used. (O) To determine the associated ALT pushbutton is selected to OFF, Verify the pushbutton is selected OUT (Not Flush). (M) This item may be accomplished by a qualified crewmember. With engines running and propellers out of feather: a) Select both ALT pushbutton ON (Flush) b) Select AC TIE Closed c) Select associated ALT pushbutton OFF (out) d) Observe AC TIE close by monitoring AC TIE pushbutton flow bar annunciation lights e) Select ALT pushbutton ON (Flush) f) Observe the AC TIE open. A 2 1 One may be inoperative provided: 6 – Inverters a) Inverter Failure Indication(s) (EICAS and Overhead Panel) for operative Inverter operatenormally, Engineering Department
Página: 24‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER b) Takeoff, Approach, and A 2 1 6 – Inverters Landing Minimums do not (Cont.) require its use, and c) Operations are limited to two flight days before repairs are made. C 2 1 One may be inoperative provided 7 ‐ DC Voltmeter EICAS Failure Cautions for DC Generators and Main DC Batteries operate normally. 8 ‐ Vertical (Bus Tied) Flow Bar Lights C 2 0 (M) (O) Light(s) may fail to illuminate provided: on Non‐Essential Bus (NON‐ESS 1/2) a) Associated NON‐ESS Pushbuttons (Overhead Panel) Pushbutton(s) is verified to operate normally, b) Associated NON‐ESS Pushbutton "OFF" Light(s) is verified to operate normally, c) EICAS Electrical System Page operates normally, and d) Alternate procedures for determining Non‐Essential Bus status are established and used. (O) Confirm position of NON ESS ½ pushbutton IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications. (M) With DC power applied to the aircraft: a) Select the associated NON ESS pushbutton OUT (Off) and ensure the pushbutton OFF annunciator light illuminates and that the affected bus is unpowered on the ELECTR system page. Engineering Department
Página: 24‐6 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER b) Select the associated NON 8 ‐ Vertical (Bus Tied)Flow Bar Lights C 2 0 ESS pushbutton IN (On), and onNon‐Essential Bus(NON‐ESS ensure the pushbutton OFF 1/2)Pushbuttons(Overhead Panel) annunciator light extinguishes (Cont.) and that the affected bus is powered on the ELECTR system page. 9 ‐ "OFF" Annunciator Lights on Non‐ C 2 0 (M) (O) Light(s) may fail to illuminate provided: Essential Bus (NON‐ESS 1/2) a) Associated NON‐ESS Pushbuttons (Overhead Panel) Pushbutton(s) is verified to operate normally, b) Associated NON‐ESS Pushbutton Vertical Flow Bar Light(s) is verified to operate normally, c) EICAS Electrical System Page operates normally, and d) Alternate procedures for determining Non‐Essential Bus status are established and used. (O) Confirm position of NON ESS ½ pushbutton IN (on) or OUT (off) as required. Reference EICAS for abnormal indications. (M) With DC power applied to the aircraft: a) Select the associated NON ESS pushbutton OUT (off) and ensure the pushbuttons vertical bar (white) annunciator light is extinguished and that the affected bus in unpowered on the ELECTR system page. b) Select the associated NON ESS pushbutton IN (on) and ensure the pushbutton Engineering Department
Página: 24‐7 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER vertical flow bar (white) 9 ‐ "OFF" Annunciator Lights on Non‐ C 2 0 annunciator light is Essential Bus (NON‐ESS 1/2) illuminated and that the Pushbuttons (Overhead Panel) affected bus is powered on (Cont.) the ELECTR system page. 10 ‐ Vertical (Bus Un‐Tied) Flow Bar B 1 0 (M) (O) Light may fail to illuminate provided: Light on DC Bus Tie (TIE) Pushbutton a) DC Bus TIE Pushbutton is (Overhead Panel) verified to operate normally, b) DC Bus TIE Pushbutton Horizontal (Bus Tied) Flow Bar Light is verified to operate normally, c) COLD/CROSS Pushbutton "ON" Light is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining status of Bus Tie Function are established and used. (0) Confirm position of OC BUS TIE Pushbuttons selected IN, Flow Bar Light (BUS TIEO) must illuminate (M) With DC Power applied to only one side (LH or RH), and EXT power not on: a) Select the DC Bus Tie Pushbuttons 0UT (Open) and ensure the Pushbuttons Horizontal Flow Bar (White) Annunciator Light is extinguished and that Bus Voltage is only indicated on one side of the DC Bus Tie on the ELECTR System Page. Engineering Department
Página: 24‐8 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER b) Select the DC Bus Tie 10 ‐ Vertical (Bus Un‐Tied) Flow Bar B 1 0 Pushbutton IN (CLOSED), and Light on DC Bus Tie (TIE) Pushbutton ensure the Pushbutton (Overhead Panel) Horizontal Flow Bar (WHITE). (Cont.) Annunciator Light is illuminated and the Bus Voltage is indicated on both sides of the OC Bus tie on the ELECTR System Page. 11 ‐ Horizontal (Bus Tied) Flow Bar B 1 0 (M) (O) Light may fail to illuminate provided: Light on DC Bus Tie (TIE) Pushbutton a) DC Bus TIE Pushbutton is (Overhead Panel) verified to operate normally, b) DC Bus TIE Pushbutton Vertical (Bus Un‐Tied) Flow Bar Light is verified to operate normally, c) COLD/CROSS Pushbutton "ON" Light is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining status of Bus Tie Function are established and used. (O) Confirm position of DC BUS TIE Pushbutton IN (Tied) or OUT (Un‐Tied) With pushbutton selected IN, Flow Bar Light (BUS TIED) must illuminate (M) With DC Power applied to only one side (LH or RH), and EXT power not on: a) Select the OC Bus Tie Pushbutton OUT (open) and ensure the Pushbutton Horizontal Flow Bar (White) Annunciator Light is extinguished and that Bus Voltage is only indicated on Engineering Department
Página: 24‐9 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER one side of the DC Bus Tie on 11 ‐ Horizontal (Bus Tied) Flow Bar B 1 0 the ELECTR System Page. Light on DC Bus Tie (TIE) Pushbutton b) Select the DC Bus Tie (Overhead Panel) Pushbutton IN (CLOSED), and (Cont.) ensure the Pushbutton Horizontal Flow Bar (WHITE) annunciator Light is illuminated and that Bus Voltage is indicated on both sides of the DC Bus Tie on the ELECTR System Page. (O) Confirm position of DC BUS TIE Pushbutton IN (On) or OUT (Off) as required. With pushbutton selected OUT Flow Bar Light (BUS TIE) must illuminated. (M) With DC Power applied to only one side (LH or LH) , and EXT power not on: a) Select the DC Bus Tie Pushbutton OUT (open) and ensure the Pushbutton Vertical Flow Bar (White) Annunciator Light is illuminated and that Bus Voltage is only indicated on one side of the DC Bus Tie on the ELECTR System Page b) Select the DC Bus Tie Pushbutton IN (CLOSED) , and ensure the Pushbutton Vertical Flow Bar (WHITE) Annunciator Light is extinguished and that Bus Voltage is indicated on both sides of the DC bus Tie on the ELECTR System Page c) Select COL/CROSS Pushbuttons ON (IN) and ensure light illuminates. Engineering Department
Página: 24‐10 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 12 ‐ Essential Bus LED (Bus Powered) C 2 1 Lights (Overhead Panel) 13 ‐ "FAIL" Annunciator Light(s) on DC C 2 0 (M) (O) Light(s) may fail to illuminate provided: Generator (GENLH/RH) Pushbutton(s) a) Associated Generator(s) is (Overhead Panel) verified to operate normally, b) Associated GEN Pushbutton "OFF" Annunciator Light(s) operates normally, c) Associated "L or R DC GEN FAIL" EICAS Caution Message(s) is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining operational status of associated DC Generator(s) are established and used. (0) Confirm position of DG GEN Pushbutton IN (ON) or OUT (Off) as required. Reference EICAS for abnormal indications (M) This item may be completed by a qualified crewmember a) Start the Engine with the affected Generator b) Check the affected Generator “OFF” Annunciator light is OUT (OFF) and illuminated c) Turn Generator ON d) Display the Electric System Page and verify no failure Message illuminates for the affected Generator. Engineering Department
Página: 24‐11 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 14 ‐ "OFF" Annunciator Light(s) on DC C 2 0 (M) (O) Light(s) may fail to illuminate provided: Generator (GENLH/RH) Pushbutton(s) a) Associated Generator(s) is (Overhead Panel) verified to operate normally, b) Associated GEN Pushbutton "FAIL" Annunciator Light(s) operates normally, c) Associated "L or R DC GEN FAIL" EICAS Caution Message(s) is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining operational status of associated DC Generator(s) are established and used. (O) Confirm position of DCGE Pushbutton IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications (M) This item may be completed by a qualified crewmember a) Start the Engine with the affected Generator b) Check the affected Generator "FAIL" Annunciator light is illuminated c) Turn Generator ON d) Display the Electric System Page and verify no failure Message illuminates for the affected Generator. 15 ‐ "FAIL" Annunciator Light(s) on C 2 0 (M) (O) Light(s) may fail to illuminate Main Battery (BAT 1/2) Pushbutton(s) provided: (Overhead Panel) a) Associated Battery(s) is verified to operate normally, Engineering Department
Página: 24‐12 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER b) Associated BAT Pushbutton 15 ‐ "FAIL" Annunciator Light(s) on C 2 0 "OFF" Annunciator Light(s) Main Battery (BAT 1/2) Pushbutton(s) operates normally, (Overhead Panel) (Cont.) c) Associated "BATT 1, or BATT2 FAIL" EICAS Caution Message(s) is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining operational status of associated Main Battery(s) are established and used. (O) Confirm position of BAT 1/2 Pushbutton IN(On) or OUT (Off) as required. Reference EICAS for abnormal indications (M) With external power applied to the aircraft: a) Select associated Battery Switch OFF and verify associated BAT Pushbutton 1"OFF" annunciator lights b) Disconnect associated Battery c) Verify Associated BAT 1 or 2 FAIL Caution illuminates on EICAS and on ELECTR System Page d) Reconnect Battery Engineering Department
Página: 24‐13 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 16 ‐ "OFF" Annunciator Light(s) on C 2 0 (M) (O) Light(s) may fail to illuminate Main Battery (BAT 1/2) Pushbutton(s) provided: (Overhead Panel) a) Associated Battery(s) is verified to operate normally, b) Associated BAT Pushbutton "FAIL" Annunciator Light(s) operates normally, c) Associated "BATT 1, or BATT2 FAIL" EICAS Caution Message(s) is verified to operate normally, d) EICAS ELECTR System Page operates normally, and e) Alternate procedures for determining operational status of associated Main Battery(s) are established and used. (O) To select associated Battery OFF Select BAT Pushbutton to the OUT position (Not Flush). To select the associated Battery ON, select the BAT Pushbutton to the IN position (Flush) (M) With external power applied to the aircraft: a) Disconnect associated Battery b) Verify associated BAT 1 or 2 FAIL 1 Caution illuminates on EICAS and on ELECTR System Page c) Reconnect Battery 17 ‐ "AVAIL" and "ON" Annunciator C 2 1 (O) Either "AVAIL," or "ON" Light may fail to illuminate provided: Lights on DC External(EXT) a) "ON," and "NOT USED" Pushbutton(Overhead Panel) External Power Annunciator Lights on Exterior Panel operate normally, b) Alternate Procedures for determining External Power. Engineering Department
Página: 24‐14 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER availability and operation 17 ‐ "AVAIL" and "ON" Annunciator C 2 1 status are established and Lights on DC External (EXT) used, and Pushbutton (Overhead Panel) c) Alternate Flight (Cont.) Crew/Ground Crew communication procedures for connecting and disconnecting External Power are established and used. (O) For the "AVAIL” light communicate with ground personnel via established hand signals For the "ON” Light: With The External Power selected "ON” by 1) With engines operating: a) Verify the EXT Pushbutton is selected IN (ON), and b) Verify the ON (EXT) blue synoptic message is displayed on the ELECTR System Page 2) With the engines not operating, verify the Non Essential Busses are ON as indicated on the ELECTR System Page or the NON ESS 1/2 Pushbutton ON annunciator lights. 18 ‐ "NOT USED" and "ON" C 2 1 (O) Either "NOT USED," or "ON" Light may fail to illuminate provided: Annunciator Lights on DC External a) "ON," and "AVAIL" External Pushbutton (Exterior Panel) Power Annunciator Lights on Overhead Panel operate normally, b) Alternate Procedures for determining External Power availability and operation status are established andused, and c) Alternate Flight Crew/Ground Crew communication procedures for connecting and Engineering Department
Página: 24‐15 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER Disconnecting External Power 18 ‐ "NOT USED" and "ON" C 2 1 are established and used. Annunciator Lights on DC External Pushbutton (Exterior Panel) (O) For the "AVAIL" Light (Cont.) communicate with ground personnel via established hand signals For the "ON" light: a) Brief the Ramp Supervisor on EXT power status and means to determine EXT Pushbutton "ON" or "AVAIL" lights on the overhead panel b) Prior to leaving the aircraft unattended, ensure boot BAT 1/2 are selected OFF. 19 ‐ Vertical (Bus Un‐Tied) Flow Bar C 1 0 (M) (O) Light may fail to illuminate provided: Light on AC Bus Tie (TIE) Pushbutton a) AC Bus Tie function is (Overhead Panel) verified to operate normally, b) AC Bus TIE Horizontal (Bus Tied) Flow Bar annunciator Light operates normally, c) AC Alternator (ALT LH/RH) Pushbutton "FAIL," and "OFF" Annunciator Lights operate normally, d) EICAS ELECTR Page operates normally, and e) Alternate procedures for determining AC Bus Tie status are established and used. (O) Pushbutton IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications. (M) This item may be completed by aqualified Crewmember. With the DISPLAY INHIBIT Selected. Select associated ALT Pushbutton ON. Verify associated ALT FAIL Amber Caution Message illuminates on EICAS. Engineering Department
Página: 24‐16 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 19 ‐ Vertical (Bus Un‐Tied) Flow Bar C 1 0 With engines running and the propeller out of feather: Light on AC Bus Tie(TIE) Pushbutton a) With the AC TIE Selected (Overhead Panel) OPEN (Out) Select one (Cont.) alternator OFF. b) Note that no AC power is indicated on the AC BUS associated with inoperative alternator on ELECTR System Page. c) Select the AC TIE Pushbutton CLOSED (flush) d) Note that AC Power is indicated on the AC BUS associated with the inoperative alternator on the ELECTR System Page e) AC BUS TIE Pushbutton Horizontal Flow Bar (White) Light is illuminated 20 ‐ Horizontal (Bus Tied) Flow Bar C 1 0 (M) (O) Light may fail to illuminate provided: Light on AC Bus Tie (TIE) Pushbutton a) AC Bus Tie function is (Overhead Panel) verified to operate normally, b) AC Bus TIE Vertical (Bus Un‐ Tied) Flow Bar annunciator Light operates normally, c) AC Alternator (ALT LH/RH) Pushbutton "FAIL," and "OFF" Annunciator Lights operate normally, d) EICAS ELECTR Page operates normally, and e) Alternate procedures for determining AC Bus Tie status are established and used. (0) Confirm position of AC BUS TIE Pushbutton IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications. Engineering Department
Página: 24‐17 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER 20 ‐ Horizontal (Bus Tied) Flow Bar C 1 0 (M) This item may be completed by a qualified Crewmember. With the Light on AC Bus Tie (TIE) Pushbutton DISPLAY INHIBIT Selected, select (Overhead Panel) associated ALT Pushbutton ON. Verify (Cont.) associated ALT FAIL. Amber Caution Message illuminate on EICAS. With engines running and the propeller out feather: a) With the AC TIE Selected OPEN (Out) Select one alternator OFF. b) Note that no AC power is indicated on AC BUS associated with inoperative alternator on ELECTR System Page. c) AC BUS TIE Pushbutton Vertical Flow bar (White) Light is illuminated. d) Select the AC TIE Pushbutton CLOSED (flush) e) Note that AC Power is indicated on the AC BUS associated with the inoperative alternator on the ELECTR System Page 21 ‐ "AVAIL" and "ON" Annunciator C 2 0 May be inoperative provided procedures do not require their use. Light(s) on AC External Power Pushbutton (Overhead Panel) C 2 0 (O) May be inoperative provided alternate procedures for determining availability and operational status of AC External Power are established and used. (O) For the "AVAIL" Light communicate with ground personnel via established hand signals For the "ON" Light: Engineering Department
Página: 24‐18 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 24 ELECTRICAL POWER a) Verify the EXT Pushbutton 21 ‐ "AVAIL" and "ON" Annunciator C 2 0 is selected IN (On) and Light(s) on AC External Power Pushbutton (Overhead Panel) b) Verify the ON (EXT) Blue (Cont.) Synoptic message is displayed on the ELECTR System Page C 1 0 (M) (O) May be inoperative provided 22 ‐ APU Generator APU Generator is selected off. (O) Verify APU GEN sw is selected Off (M) This item may be completed by a qualified Crewmember a) Pull and secure APU GEN circuit breaker b) Placard APU GEN sw" INOPERATIVE" C 1 0 24 – DC External Power System C 1 0 25 – AC External Power System INTENCIONALMENTE EN BLANCO
Engineering Department
Página: 25‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 25 EQUIPMENT/FURNISHINGS A 1 0 (M) (O) Flight Attendant seat maybe 1 ‐ Flight Attendant Seat Assembly inoperative provided: a) Affected Seat or seat assembly is not occupied, b) Flight Attendant displaced by inoperative seat position occupies the passenger Seat most accessible to the inoperative seat, c) Alternate procedures are established and used as published in the crewmembers manuals, d) Folding type Seat is stowed or secured in the retracted position, e) Passenger Seat assigned to the Flight Attendant is placarded "FOR FLIGHT ATTENDANT USE ONLY", and f) Repairs are made within two (2) flight days. (O) Cabin attendant assigned to affected jump seat will occupy a passenger seat as close to, or closer than the nearest seated passenger to the associated exit. On VIP Dornier aircraft this seat will be ID. From this seat the cabin attendant can reach the assigned emergency exit in essentially the same time as from the jump seat. Passenger seat occupied by the Cabin attendant is to be placarded (blocked) for such purpose. (M) This item may be completed by a qualified Crewmember. Ensure the Seat is retracted and placard the Seat with a Seat blocking card. Engineering Department
Página: 25‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 25 EQUIPMENT/FURNISHINGS C 1 1 The Emergency Locator Transmitter 2 ‐ Emergency Locator Transmitter (ELT) must be operative in accordance with R.A.C. 4.2.2.4. NOTE: If the ELT failure occurs in a remote base where the repairs cannot be accomplished, the crew could perform a Ferry flight to a maintenance facility where the repairs could be made. (RAC 4.2.2.4.d.4.). 3 ‐ "Fasten Seat Belt While Seated" Signs C 22 1 One or more Signs or Placards maybe illegible or missing provided a legible Sign or Placard is readable from each occupied Passenger Seat. D 32 0 May be inoperative provided: 4 ‐ Passenger Seat(s) a) Seat does not block an Emergency Exit, b) Seat does not restrict any passenger from access to the main aisle, and c) The affected seat(s) are blocked and placarded "DO NOT OCCUPY". NOTE 1: A seat with an inoperative seat belt is considered inoperative. NOTE 2: Inoperative seats do not affect the required number of Flight Attendants. NOTE 3: Affected seat(s) may include the seat(s) behind and/or adjacent out board seats. D 30 0 May be inoperative and seat 1‐ Recline Mechanism occupied provided seat is secured in the up‐right position. Engineering Department
Página: 25‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 25 EQUIPMENT/FURNISHINGS D 20 0 (O)May be inoperative provided: 4 ‐ Passenger Seat(s) a) Baggage is not stowed (Cont.) underseat with inoperative 2‐Underseat Baggage Restraining bar, Bars b) Associated seat is placarded "DO NOT STOW BAGGAGE UNDER THIS SEAT", and c) Procedures are established to alert Cabin Crew of inoperative restraining bar. (0) Upon report of inoperative Restraining bar on Aircraft Log. Crew will advise Flt. Attendant. Placard affected seat "DO NOT STOWBAGGAGE UNDER THIS SEAT" 5 –Passenger Convenience Items D 32 0 (O) Secure the tray in the closed 1 – Tray tables position and placard INOPERATIVE D 1 0 0) Placard the toilet INOPERATIVE 2 – Toilet and block the seat in the down position with tape D 7 0 (O) If the door will close, placard the 3‐ Overhead bin door latch INOPERATIVE (M) If the door will not close, remove the door from the overhead bin, place a piece of tape across the opening and placard NO STORAGE IN THIS BIN D 10 0 (O) Secure the inoperative armrest in 4‐ Armrest seat the upright position to the seat back. (M) If the armrest cannot be secured in the upright position, remove the armrest form the seat. Engineering Department
Página: 25‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 25 EQUIPMENT/FURNISHINGS 6 ‐ Observer Seat 1 – Primary Observer Seat (Including A 1 0 May be inoperative provided: a) The primary observer seat Associated Equipment) is available with the required minimum safety equipment (safety belt and oxygen) and acceptable to the UAEAC inspector for the performance of official duties, and b) Repairs are made within two flight days. NOTE 1: These provisions are intended to provide for occupancy of the above seats by an UAEAC Inspector when minimum safety equipment (Oxygen and Safety Belt) is functional and the inspector determines the conditions to be acceptable. NOTE 2: The Pilot‐In‐Command will determine if the minimum Safety Equipment is functional for other persons authorized to occupy Observer Seat. 7 ‐ Flight Attendant Flashlight/Holder C 1 0 May be inoperative or missing Assembly(s) provided Cabin Crewmember(s) assigned to associated Seat(s) has an equivalent, operating Flashlight readily available. 8 ‐ First Aid Kits D 1 1 Any in excess of those required by RAC may be opened or missing, provided required distribution of operative Kit(s) is maintained. 9 ‐ Over‐Water Equipment C 36 36 Required on over water operation 1 – Life Vest only (N/A due to ADA operation) C 1 1 Required on over water operation 2 – Life raft only (N/A due to ADA operation. Engineering Department
Página: 25‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 25 EQUIPMENT/FURNISHINGS D 2 0 May be inoperative or missing 10 ‐ Cargo restraint System provided acceptable cargo loading limits from an approved source ie; Cargo Loading manual, Cargo Handling manual, or Weight and Balance document are observed. D 2 0 May be inoperative or missing provided cargo compartment remains empty. 11 ‐ Emergency Medical Kit D 0 0 Any in excess of those required by RAC may be opened or missing provided required distribution of remaining Kit(s) is maintained. 12 ‐ Cockpit Sunvisor C 2 0 May be inoperative provided: a) No visual restrictions to the flight crew, b) Acceptable to flight crew, and c) Affected sunvisor is removed or stowed. 13 ‐ Galley Waste Receptacles Access C 1 0 (M) May be inoperative provided the container is empty and the access is Doors/Covers secured to prevent waste introduction into the compartment. (M) Remove waste from container, secure access door and placard "DO NOT THROW WASTE INSIDE" 14 ‐ Lavatory Door Ashtrays 1 ‐ Airplanes with only one lavatory A 1 0 May be missing provided it is replaced within 3 calendar days. door ashtray installed
Engineering Department
Página: 26‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 26 FIRE PROTECTION D 3 2 Any in excess of those required by 1 ‐ Portable Fire Extinguisher RAC may be inoperative or missing provided: a) The inoperative Fire Extinguisher is tagged "INOPERATIVE," removed from the installed position, and placed out of sight so it can not be mistaken for at functional unit, and b) Required distribution is maintained 2 ‐ Fire Extinguisher Thermal C 5 0 (M) (O) May be inoperative or missing provided: Discharge Discs a) Adequate charge of associated Extinguisher is verified each flight day, and b) Associated Engine Fire Protection Discharge Bottle Lights are tested each flight day. (O) Prior to each takeoff: 1) Select the FIRE PROTECTION TEST switch to the FAIL AGN position and check the AGN lights are illuminated and 2) Ensure the DIS lights in the fire bottle (BTL) buttons are checked to the not Illuminated (M) Remove affected Fire Bottle and perform weight check IA Dornier MM chapter 26. Document task in Maintenance Log on board Aircraft Engineering Department
Página: 26‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 26 FIRE PROTECTION 3 ‐ Lavatory Smoke Detection System C 1 0 May be inoperative provided the lavatory fire extinguisher system operates normally. C 1 0 (M) (O) May be inoperative provided: a) Lavatory waste receptacle remains empty, b) Lavatory door is locked closed and placarded "INOPERATIVE ‐ DO NOT ENTER", and c) Lavatory is not used for any purpose. NOTE 1: These provisos are not intended to prohibit lavatory inspections by crewmembers. Note 2: Lavatory smoke detection system is not required for all‐cargo operations. (M) (O) This item may be performed by qualified flight Crewmember. Ensure Lavatory Smoke Detection System operates normally or remove all waste from Receptacle and close, lock and placard door "INOPERATIVE ‐ DO NOT ENTER" "FUERA DE SERVICIO NO ENTRE" 4 ‐ Lavatory Fire Extinguishing Systems C 1 0 May be inoperative for each lavatory provided associated lavatory smoke detection system operates normally. C 1 0 (M) (O) May be inoperative for each lavatory provided associated: a) Lavatory Waste Receptacle remains empty, b) Lavatory Door is locked closed and placarded "INOPERATIVE ‐ DO NOTENTER", and c) Lavatory is not used for any purpose. Engineering Department
Página: 26‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 26 FIRE PROTECTION 4 ‐ Lavatory Fire Extinguishing Systems C 1 0 NOTE 1: These provisos are not (Cont.) intended to prohibit Lavatory inspections by Crewmembers. NOTE 2: A lavatory fire extinguisher system is not required for all‐cargo operations. (M) (O) This item may be performed by qualified flight Crewmember. Ensure Lavatory Smoke Detection System operates normally or remove all waste from Receptacle and close, lock and placard door "INOPERATIVE ‐ DO NOT ENTER" "FUERA DE SERVICIO NO ENTRE" 5 ‐ Cargo Compartment Smoke D 1 0 Detection System 6 ‐ Cargo Compartment Fire D 1 0 Extinguisher System INTENCIONALMENTE EN BLANCO
Engineering Department
Página: 27‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS B 1 0 (M) (O) May be inoperative provided: 1 ‐ Aileron Trim Indication System a) Normal and Standby Aileron Trim Systems operate normally, b) Aileron Trim Systems are verified to operate through full travel before each departure, and c) At completion of Trim check, Aileron Trim Tab is visually verified in the neutral position, and Aileron Trim is not repositioned unless required in flight. (0) Procedure: 1) With electrical power on the aircraft, operate aileron trim to full down and full up 2) Have outside observer, pilot, or maintenance personnel visually check trim tab on left aileron for movement and position. Trim aileron as needed until trim tab is aligned with aileron trailing edge. 3) Do not move aileron trim until after take‐off. (M) This item may be performed by a qualified Crewmember. Verify Standby and Normal Trim operates normally by running the Trim switches through full range and visually check Trim Tab for movement. B 1 0 (M) (O) May be inoperative provided: 2 ‐ Rudder Trim Indication System a) Rudder Trim System operates normally, Engineering Department
Página: 27‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS b) Rudder Trim System is 2 ‐ Rudder Trim Indication System B 1 0 (Cont.) verified to operate through full travel before each departure, and c) At completion of Trim check Rudder Trim Tab is visually verified in the neutral position, and Rudder Trim is not repositioned unless required in flight. (0) Procedure: 1) With electrical power on the aircraft, operate rudder trim to full left and full right. 2) Have outside observer, pilot, or maintenance personnel visually check rudder trim tab movement and position. Trim rudder as needed until trim tab is aligned with rudder trailing edge. 3) Do not move rudder trim until after take‐off. (M) This item may be performed by a qualified Crewmember. Verify Rudder Trim System operates normally by running the Trim switches through full range and visually check Trim Tab for movement. C 1 0 (M) May be inoperative provided: 3 ‐ Gust Lock System a) An acceptable alternate method of securing the affected Flight Controls is developed and used, and b) Full and free movement of associated Flight Controls is verified before takeoff. Engineering Department
Página: 27‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS C 1 0 (M) Move Gust Lock lever in cockpit 3 ‐ Gust Lock System to the forward position marked OFF (Cont.) (unlocked). Ensure lever is in detent Check movement of flight controls to ensure freedom. Placard Lever "INOP ‐DO NOT USE". 4 ‐ Rudder Limiter System A 1 0 (O) May be inoperative in the Disengaged Mode provided: a) Airspeed is limited to a maximum of 160 KIAS, and b) Operations are limited to two flight days before repairs are made. (O) Procedure: a) Ensure RUD LIMIT pushbutton is pressed (UNLIMIT illuminated) b) Do not exceed 160 KIAS 5 ‐ Normal Aileron Trim System B 1 0 (O) May be inoperative provided: a) Aileron Trim Indication System operates normally, b) Standby Aileron Trim System is verified to operate through full travel before each departure, and c) Standby Aileron Trim System is selected and used throughout flight. (O) Procedure: a) Prior to each departure, ensure standby Aileron Trim operates normally through full travel, and b) Use Standby Aileron Trim System for all aileron trimming operations in flight. Engineering Department
Página: 27‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS 6 ‐ Standby Aileron Trim System B 1 0 (O) May be inoperative provided: a) Aileron Trim Indication System operates normally, b) Normal Aileron Trim System is verified to operate through full travel before each departure, and c) Normal Aileron Trim System is selected and used throughout flight. (O) Procedure: a) Prior to each departure, ensure normal aileron Trim operates normally through full travel, and b) Use normal Aileron Trim System for all aileron trimming operations in flight. 7 ‐ Stick Shaker B 2 1 (M) (O) One may be inoperative provided: a) Inoperative Stick Shaker is deactivated, b) Both Angle of Attack (AOA) Systems operate normally, and c) Before each departure, Stick Pusher and remaining Stick Shaker are verified to operate normally. (O) Perform a Stall System test prior to each takeoff (M) This item may be performed by a qualified Crewmember. Pull and secure affected AOA / Stall Warning C/B using a Lockout ring. Engineering Department
Página: 27‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS 8 ‐ "UNLIMIT" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate Rudder Limiter (RUD LIMIT provided: Pushbutton) (Center Console) a) RUD LIM Pushbutton is verified to operate normally, b) EICAS "RUDDER MAN UNLIMIT" Status Message operates normally, c) EICAS FLT CTRL System Page operates normally, and d) Alternate procedures to confirm Rudder Limiter Status are established and used. (O) Reference Flight Control System Page for Rudder Limiter status (M) This item may be performed by a qualified Crewmember: a) Select RUD LIMT pushbutton OUT b) verify the RUDDER MAN UNLIMIT Blue Status message illuminates on EICAS c) Select the RUD LIMIT Pushbutton IN d)Verify the RUDDER MAN UNLIMIT Blue Status message on EICAS extinguishes 9 ‐ "OFF" Annunciator Light on Stick C 1 0 (M) (O) Light may fail to illuminate provided: Pusher (PUSHER) Pushbutton (Center a) PUSHER Pushbutton is Console) verified to operate normally, b) EICAS "PUSH DISARM" Status Message operates normally, c) EICAS "PUSHER FAIL" Caution Message operates normally, and d) Before each departure, Stick Pusher is verified to operate normally. Engineering Department
Página: 27‐6 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS 9 ‐ "OFF" Annunciator Light on Stick C 1 0 (O) Perform a Stall System test prior to each take‐off Pusher (PUSHER) Pushbutton (Center (M) This item may be performed by a Console) qualified Crewmember (Cont.) a) Push the PUSHER Pushbutton (Spring Loaded) b) Verify the PUSH DISARM Status message illuminates on EICAS c) Conduct Pusher Test and verify Pusher is inoperative d) Trip and Reset the PUSHER CTRL c/b e) Verify PUSHER DISARM Status message on EICAS extinguishes f) Conduct PUSHER Test and verify Pusher operates normally. 10 ‐ Aileron Position Indications C 2 0 (O) May be inoperative provided, before each takeoff, normal Aileron (EICASFLT CTRL Page) control movement is verified by an acceptable alternate means. (O) Crewmembers will visually verify normal Aileron control movement with Captain performing an Aileron flight control check from the flight deck with the Firs Officer positioned outside visually verifying proper Aileron position. 11 ‐Elevator Position Indication (EICAS C 1 0 (O) May be inoperative provided, FLT CTRL Page) before each takeoff, normal Elevator control movement is verified by an acceptable alternate means. (O) Crewmembers will visually verify normal elevator control movement with Captain performing an elevator flight control check from the flight deck with the Firs Officer positioned outside visually verifying proper elevator position. Engineering Department
Página: 27‐7 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 27 FLIGHT CONTROLS 12 ‐Rudder Position Indication (EICAS C 1 0 (O) May be inoperative provided, before each takeoff, normal Rudder FLT CTRL Page) control movement is verified by an acceptable alternate means. (O) Crewmembers will visually verify normal rudder control movement with Captain performing a rudder flight control check from the flight deck with the Firs Officer positioned outside visually verifying proper rudder position. 13 ‐ Spoiler Position Indications (EICAS C 2 0 (O) May be inoperative provided, before each takeoff, normal Spoiler FLT CTRL Page) control movement is verified by an acceptable alternate means. (O) Crewmembers will visually verify normal spoiler control movement with Captain performing an spoiler flight control check from the flight deck with the Firs Officer positioned outside visually verifying proper spoiler position. INTENCIONALMENTE EN BLANCO
Engineering Department
Página: 28‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 1 ‐ Jet Pumps C 2 1 (O) One may be inoperative provided: a) Both Electric Fuel Pumps operate normally, b) Fuel Quantity Indications operate normally, c) Only Jet A or Jet A1 Fuel is used, and d) Unusable Fuel Quantity in affected Wing Tank Group (Inner, Outer, and Feeder Tanks) is increased by 30 lbs. (O) Prior to engine start, select both ELPMPs ON and ensure no ELPMPFAIL Cautions illuminate. Associated ELPMP remains ON continuously from Takeoff to landing unless otherwise directed by Abnormal or Emergency Procedures. C 2 1 (M) (O) One may be inoperative 2 ‐ EICAS Fuel Quantity Indications provided: a) Fuel Quantity in associated Fuel Tank(s) is verified by an acceptable alternate means, b) Associated Fuel Flow and Fuel Remaining Indications operate normally, c) All Fuel Pumps (Electric and Jet) operate normally, d) Fuel Quantity of affected Wing Tank Group is manually entered in the EICAS Fuel System Page prior to Engine start, e) EICAS "FUEL LOW/VMO" Caution operates normally, and f) VMO/MMO is limited to 225KIAS/M.49. Engineering Department
Página: 28‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 2 1 (O) Procedure: C 2 ‐ EICAS Fuel Quantity Indications a) Following each refueling, (Cont.) verify fuel quantity on side with inoperative fuel quantity indication using the magnetic dipstick. b) Prior to engine start, ensure actual fuel load for side with inoperative fuel quantity indication is manually entered on the FUEL System Page. c) Do not exceed 225 KIAS/M.49 (M) This item may be performed by a qualified Crewmember: Verify Fuel Quantity by use of Dipsticks 3 ‐ Magnetic Dipsticks (Magna Sticks) C 4 0 May be inoperative provided acceptable alternate refueling procedure is established and used. C 1 0 May be inoperative provided 4 ‐ Pressure Refueling System acceptable alternate refueling procedures are established and used. C 1 0 May be inoperative provided Manual 1 – Automatic Function Pressure Refueling Function operates normally. C 1 0 May be inoperative provided 2 ‐ Manual Function Automatic Pressure Refueling Function operates normally. C 1 0 3 – Pressure Refueling Cap 5 ‐ Refueling Panel C 1 0 May be inoperative provided: a) Pressure Refueling System is considered inoperative, and b) Acceptable alternate refueling procedures are established and used. Engineering Department
Página: 28‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 6 ‐ EICAS "FUEL TANK TEMP" Caution C 1 0 (O) May be inoperative provided: a) Static Air Temperature (SAT) Indications operate normally, and b) Appropriate AFM Limitations, Procedures, and Performance adjustments are applied. (O) If fuel tank temperature Reading is disable replace tank temperature by SAT. 7 ‐ EICAS "FUELLOW/VMO" Cautions C 2 0 (O)May be inoperative provided: a) Associated EICAS Fuel Quantity Indications operate normally, b) Associated EICAS "FEED TANK LOW" Caution operates normally, and c) VMO/MMO is limited to 225KIAS/M.49. (O) Procedure: a) Monitor fuel indications to maintain adequate fuel reserves. b) Do not exceed 225 KIAS/M. 49 2 0 (M) (O) May be inoperative provided: 8 ‐ Automatic Electric Boost Pump C a) Associated Electric Boost (ELPMP AUTO) Systems Pump (ELPMP) is verified to operate normally, b) EICAS "FUEL JETPMP FAIL," and "FUEL ELPMP FAIL" Cautions operate normally, c) "FAIL" Annunciator Lights on ELPMP and JETPMP Pushbuttons operate normally, and Engineering Department
Página: 28‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL d) Associated ELPMP remains 8 ‐ Automatic Electric Boost Pump C 2 0 ON continuously from Takeoff (ELPMP AUTO) Systems to Landing unless otherwise (Cont.) directed by Abnormal or Emergency Procedures. (O) Turn associated ELPMP ON before Takeoff and leave activated until after Landing unless Abnormal or Emergency Procedures preclude its use (M) This item may be performed by a qualified Crewmember a) Select the associated ELPMP AUTO Pushbutton to AUTO (flush) b) Verify the ELPMP ON Blue Status Message illuminates on the associated side on the FUEL System Page. c) Pull the associated ELPMP c/b and verify "FUEL ELPMP" Caution and "FAIL" ELPMP Annunciation lights illuminate. Reset the c/b d) Verify associated JETPMP "FUEL JETPMP FAIL" Caution and "FAIL" JETPMP annunciation lights illuminate. e) Start associated engine and verify Jet Pump "FUEL JETPMP FAIL" Caution and "FAIL" JETPMP Annunciation lights extinguish. 9 ‐ "FAIL" Annunciator Lights on Jet C 2 0 (M) Light(s) may fail to illuminate Pump (JETPMP) Pushbuttons provided: (Overhead Panel) a) Associated Jet Pump(s) is verified to operate normally b) Associated EICAS "FUEL JETPMP FAIL" Caution is verified to operate normally, Engineering Department
Página: 28‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL c) EICAS FUEL System Page 9 ‐ "FAIL" Annunciator Lights on Jet C 2 0 operates normally, Pump (JETPMP) Pushbuttons d) Remaining Annunciator (Overhead Panel) Lights on affected (Cont.) Pushbutton(s) operate normally, and e) Associated Automatic Electric Boost Pump (ELPMP AUTO) System(s), and associated EICAS Cautions and Pushbutton Annunciation Lights operate normally. (M) This item may be performed by a qualified Crewmember a) Select the associated ELPMP AUTO and ensure that ELPMP ON and ELPMP FAIL Cautions illuminate. Select ELPMP OFF. b) Verify associate Jet pump "FUEL JETPMP FAIL" Caution and "FAIL" JETPMP annunciation lights illuminate. c) Start associated engine and verify Jet Pump "FUEL JETPMP FAIL" Caution and "FAIL" JETPMP Annunciation lights extinguish. 10 ‐ "OFF" Annunciator Lights on Jet C 2 0 (M) (O) Light(s) may fail to illuminate provided: Pump (JETPMP) Pushbuttons a) Associated Jet Pump(s) is (Overhead Panel) verified to operate normally, b) Associated EICAS "FUEL JETPMP FAIL" Caution is verified to operate normally, c) EICAS FUEL System Page operates normally, d) Remaining Annunciator Lights on affected Pushbutton operate normally, Engineering Department
Página: 28‐6 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 2 0 e) Associated Electric Boost 10 ‐ "OFF" Annunciator Lights on Jet C Pump (ELPMP) System(s), and Pump (JETPMP Pushbuttons its associated EICAS Cautions (Overhead Panel) and Pushbutton Annunciation (Cont.) Lights operate normally, and f) Alternate procedures for determining Jet Pump(s) status are established and used. (O) Confirm position of JETPUMP Pushbuttons IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications. (M) This item may be performed by a qualified Crewmember. Prior to engine start, select associated ELPMP ON and ensure no ELPMP FAIL Cautions illuminate. Select ELPMP OFF. With engine running and FUEL System page displayed: a) Select the associated JETPMP Pushbutton OUT (Not Flush) b) Ensure the JETPMP OFF Blue Status message illuminates on the associated side on the FUEL System Page c) Select the JETPMP Pushbutton IN (flush) d) Ensure the JETPMP ON Blue Status message illuminates on the associated side on the FUEL System Page. 11 ‐ "FAIL" Annunciator Lights on C 2 0 (M) Light(s) may fail to illuminate Electric Boost Pump (ELPMP) provided: Pushbuttons (Overhead Panel) a) Associated Electric Boost Pump(s) is verified to operate normally, Engineering Department
Página: 28‐7 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL b) Associated EICAS "FUEL 11 ‐ "FAIL" Annunciator Lights on C 2 0 ELPMP FAIL" Caution is Electric Boost Pump (ELPMP) verified to operate normally, Pushbuttons (Overhead Panel) c) EICAS FUEL System Page (Cont.) operates normally, d) Remaining Annunciator Lights on affected Pushbutton(s) operate normally, and e) Associated Jet Pump System(s), and associated EICAS Cautions and Pushbutton Annunciation Lights operate normally. (M) This item may be completed by a qualified Crewmember. Prior to engine start, select associated ELPMP ON and ensure no ELPMP FAIL Cautions illuminate.Select ELPMP OFF. Prior to engine start with the FUEL System Page displayed: a) Ensure the ELPMP Pushbutton is selected Page displayed b) Pull associated ELPMP circuit breaker c) Note the FUEL ELPMP FAIL Amber Caution Message illuminates on EICAS d) Note the ELPMP FAIL Amber message illuminate on the affected side on the FUEL PAGE. e) Verify associated JET pump “FUEL JETPMP FAIL" Caution and “FAIL JETPMP" Annunciation lights illuminate. f) Start associated engine and verify Jet Pump “FUEL JETPMP FAIL" Caution and “FAIL JETPMP" Annunciation lights extinguish. Engineering Department
Página: 28‐8 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 12 ‐ "ON" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate provided: Electric Boost Pump (ELPMP) a) Associated Electric Boost Pushbuttons (Overhead Panel) Pump(s) is verified to operate normally b) Associated EICAS "FUEL ELPMP FAIL" Caution is verified to operate normally, c) EICAS FUEL System Page operates normally, d) Remaining Annunciator Lights on affected Pushbutton(s) operate normally, e) Associated Jet Pump System(s), and associated EICAS Cautions and Pushbutton Annunciation Lights operate normally, and f) Alternate procedures for determining Electric Boost Pump(s) status are established and used. (O) Confirm position of ELPMP Pushbuttons IN (On) or OUT (Off) as required. Reference EICAS for abnormal indications (M) This item may be performed by a qualified Crewmember; With the FUEL System Page displayed: a) Ensure the associated ELPMP AUTO Pushbutton is selected OFF (Out) b) Select the ELPMP pushbutton IN (flush) c) Verify the ELPMP ON Blue Status message illuminates on the associated side on the FUEL System Page d) Select the ELPMP Pushbutton to AUTO (Out) Engineering Department
Página: 28‐9 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL e) Verify the ELPMP OFF Blue 2 0 12 ‐ "ON" Annunciator Lights on C Status message illuminates on Electric Boost Pump (ELPMP) the associate side on the FUEL Pushbuttons (Overhead Panel) (Cont.) System Page. 13 ‐ "FAIL" Annunciator Lights on C 2 0 (M) Light(s) may fail to illuminate Electric Boost Pump Automatic provided: (AUTO) Pushbuttons (Overhead Panel) a) Associated Electric Boost Pump(s) is verified to operate normally, b) Associated EICAS "FUEL ELPMP FAIL" Caution is verified to operate normally, c) EICAS FUEL System Page operates normally, d) Remaining Annunciator Lights on affected Pushbutton(s) operate normally, and e) Associated Jet Pump System(s), and associated EICAS Cautions and Pushbutton Annunciation Lights operate normally. (M) This item may be performed by a qualified Crewmember; With the FUEL System Page displayed: a) Ensure the ELPMP is selected IN (flush) b) Pull associated ELPMP c/b. c) Note the FUEL ELPMP FAIL Amber Message illuminates on the affected side on the FUEL Page. d) Note the ELPMP FAIL. Amber Message illuminates on the affected side on the FUEL Page. e) Reset the c/b f) Note both ELPMP FAIL cautions extinguish on the FUEL System Page and on EICAS Engineering Department
Página: 28‐10 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 14 ‐ "OFF" Annunciator Lights on C 2 0 (M) Light(s) may fail to illuminate provided: Electric Boost Pump Automatic a) Associated Electric Boost (AUTO) Pushbuttons (Overhead Panel) Pump(s) is verified to operate normally, b) Associated EICAS "FUEL ELPMP FAIL" Caution is verified to operate normally, c) EICAS FUEL System Page operates normally, d) Remaining Annunciator Lights on affected Pushbutton(s) operate normally, and e) Associated Jet Pump System(s), and associated EICAS Cautions and Pushbutton Annunciation Lights operate normally. (M) This item may be performed by a qualified Crewmember. With the engines not running and the ELPMP Pushbutton selected OUT: a) Select the associated ELPMP AUTO pushbutton to AUTO (Flush) b) Verify the ELPMP ON blue Status Message illuminates on the associated side on the FUEL System Page c) Select the associate ELPMP AUTO Pushbutton to OFF (Out) d) Verify the ELPMP OFF Blue Status Message illuminates on the associated side on the FUEL System Page. Engineering Department
Página: 28‐11 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 15 ‐ Vertical (Valve Open) Flow Bars C 2 0 (M) (O) Light(s) may fail to illuminate provided: on LH/RH ENGINE Shut Off Valve a) Associated Engine Fuel Shut (SOV) Annunciator Lights (Overhead Off Valve(s) is verified to Panel) operate normally, b) Associated Engine SOV Annunciator Light Horizontal (Valve Closed) Flow Bar(s) is verified to operate normally, c) EICAS FUEL System Page operates normally, and d) Alternate procedures for determining status of associated Engine Fuel Shut Off Valve(s) are established and used. (O) To observe the status of the FUEL Shut off Valve: a) Display the FUEL System Page. b) Observe that status of the associate Fuel SOV synoptic. (M) This item may be performed by a qualified Crewmember. With the associated Fuel Condition Lever in the Fuel Off position: a) Display the FUEL System Page b) Move the associated Fuel Condition Lever to the FEA position and note the synoptic for the associated Fuel SOV change from closed to Open. c) Move the associated Fuel Condition Lever Back to the MIN position and note the synoptic for the associated fuel SOV change from Open to Closed Engineering Department
Página: 28‐12 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 16 ‐ Horizontal (Valve Closed) Flow C 2 0 (M) (O) Light(s) may fail to Associated Engine Fuel Shut illuminate provided: Bars on LH/RH ENGINE Shut Off Valve a) Off Valve(s) is verified to (SOV) Annunciator Lights (Overhead operate normally, Panel) b) Associated Engine SOV annunciator Light Vertical (Valve Open) Flow Bar(s) is verified to operate normally, c) EICAS FUEL System Page operates normally, and d) Alternate procedures for determining status of associated Engine Fuel Shut Off Valve(s) are established and used. (O) To observe the status of the fuel Shutoff Valve: a) Display the FUEL system Page b) Observe the status of the associated FUEL SOV synoptic (M) This item may be performed by a qualified Crewmember. With the associated fuel Condition Lever in the Fuel OFF position: a) Display the FUEL System Page b) Move the associate fuel Condition Lever to the FEA position and note the synoptic for the associated fuel SOV change from Closed to Open. c) Move the associated fuel Condition Lever back to the MIN position and note the synoptic for the associated fuel SOV change from Open to Closed. Engineering Department
Página: 28‐13 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL 17 ‐ Vertical (Valve Open) Flow Bar on C 1 0 (M) (O) Light may fail to illuminate FUEL Cross Feed (X‐FEED) Annunciator provided: Light (Overhead Panel) a) Fuel Cross Feed System is verified to operate normally, b) Cross Feed Annunciator Light Horizontal (Valve Closed) Flow Bar is verified to operate normally, c) EICAS "FUEL X‐FEED ACTIVE" Status Message is verified to operate normally, d) EICAS "FUEL X‐FEED FAIL" Caution is verified to operate normally, e) EICAS FUEL System Page operates normally, and f) Alternate procedures for determining Cross Feed Status are established and used. (0) Reference EICAS to display "FUEL‐X‐FEED ACTIVE" (Blue advisory message) (M) This item may be performed by a qualified Crewmember. Select the X‐FEED selector to either side and note that the X‐FEED ACTIVE Blue Status Message illuminates normally on the EICAS. 1 0 (M) (O) Light may fail to illuminate 18 ‐ Horizontal (Valve Closed) Flow C provided: Bar on FUEL Cross Feed (X‐FEED) a) Fuel Cross Feed System is Annunciator Light (Overhead Panel) verified to operate normally, b) Cross Feed Annunciator Light Vertical (Valve Open) Flow Bar is verified to operate normally, c) EICAS "FUEL X‐FEED ACTIVE" Status message is verified to operate normally, Engineering Department
Página: 28‐14 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 28 FUEL d) EICAS "FUEL X‐FEED FAIL" 18 ‐ Horizontal (Valve Closed) Flow C 1 0 Caution is verified to operate Bar on FUEL Cross Feed (X‐FEED) normally, Annunciator Light (Overhead Panel) e) EICAS FUEL System Page (Cont.) operates normally, and f) Alternate procedures for determining Cross Feed Status are established and used. (O) Reference EICAS to not display "FUEL‐X‐FEED ACTIVE" (Blue advisory message) (M) This item may be performed by a qualified Crewmember a) Select the X‐FEED selector to either side b) Note that the X‐FEED ACTIVE Blue Status Message Illuminates normally on EICAS. c) Pull X‐FEED circuit breaker associated with the side selected d) Verify the X‐FEED FAIL Caution illuminates on EICAS e) Reset circuit breaker f) Verify the X‐FEED FAIL Caution extinguishes on EICAS g) Select the X‐FEED selector to the center h) Note that the X‐FEED ACTIVE Blue Status Message on EICAS extinguishes. INTENCIONALMENTE EN BLANCO
Engineering Department
Página: 29‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 29 HYDRAULIC POWER 1 ‐ "OFF" Annunciator Light on C 1 0 (M) (O) Light may fail to illuminate provided: Hydraulic Power (HYD PWR) MAIN a) Hydraulic Power Main Pump Pushbutton (Overhead Panel) is verified to operate normally, b) EICAS HYD System Page operates normally, c) EICAS "HYD MAIN PMP FAIL" Caution operates normally, d) EICAS "HYD MAIN PMP INOP" Status Message operates normally e) Alternate procedures to confirm Main Hydraulic Pump operation are established and used before each taxi. (O) After both engines are started with the propellers out of feather but prior to selecting the STBY Hydraulic power to AUTO: a) Verify the HYD PWR MAIN Pushbutton is selected ON (In) b) Verify normal Hydraulic system pressure is indicated on the HYDR System Page. (M) This item may be performed by a qualified Crewmember. With both engines started and the propellers out of feather and the STBY Hydraulic power selected to OFF: a) Select the HYD PWR MAIN Pushbutton out and verify the HYD MAIN PMP INOP status Message illuminated on the CAS display. b) Select the HYD PWR MAIN Pushbutton IN and verify the HYD MAIN PMP INOP Status Message extinguishes and normal Hydraulic pressure is indicated on the HYDR System Page. Engineering Department
Página: 30‐1 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION B 1 0 May be inoperative provided: 1 ‐ Airframe De‐Icing System a) Suction Hold Down Function operates normally, b) Landing Flaps are restricted to a maximum of 20 degrees, and c) Aircraft is not operated in known or forecast icing conditions. 2 ‐ Elevator/Rudder Horn Heater B 2 0 May be inoperative provided: Systems a) Both Elevator/Rudder Horn Heater Selector Switches remain in the OFF Position, and b) Aircraft is not operated in known or forecast icing conditions. 3 ‐ Propeller De‐Icing System B 2 0 May be inoperative provided: a) Both Propeller (PROP) Heat Selector Switches remain in the OFF Position, and b) Aircraft is not operated in known or forecast icing conditions. 4 ‐ Windshield Wiper Systems C 2 0 May be inoperative provided Airplane is not operated in precipitation within 5 nautical miles of airport of takeoff or intended landing. 5 ‐ Pitot Heater Systems B 2 1 (M) (O) One Main (1, or 2) Pitot 1‐ Main (1 & 2) Systems Heating Element may be inoperative provided: a) Standby (STBY) Pitot Heater operates normally, b) Angle of Attack (AOA) Heaters are verified to operate normally, c) Affected Main Pitot Heater is deactivated, Engineering Department
Página: 30‐2 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 5 ‐ Pitot Heater Systems d) Associated PROBES 1, or 2 1‐ Main (1 & 2) Systems B 2 1 Button on Overhead Panel (Cont.) remains ON, as called for on approved Normal Checklists, e) Normal operation of Stall Detection and Prevention system (Stick Shaker and Pusher) is verified to operate normally before each takeoff, and f) Aircraft is not operated in visible moisture or known or forecast icing conditions. (M) Procedure. a) Activate and verify standby (STBY) Pitot Heater and Angle of Attack (AOA) Heaters are operating normally b) Pull and secure the effected Pitot Heater Circuit Breaker using a Lockout Ring. (O) Procedure: a) Verify associated Pitot Heater Probe buttons on the overhead panel are pushed IN b) Perform an operational test of the Stall Detection and Prevention System (Stick Pusher & Shaker) before each takeoff B 1 0 (M) May be inoperative provided: 2 ‐ Standby (STBY) System a) Both Main (1, and 2) Pitot Heater Systems operate normally, b) Total Air Temperature (TAT) Heater Element is verified to operate normally, Engineering Department
Página: 30‐3 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 5 ‐ Pitot Heater Systems c) Standby Pitot Heater is 2 ‐ Standby (STBY) System (Cont.) B 1 0 deactivated, d) Associated STBY PROBE Button on Overhead Panel remains ON as called for on Approved Normal Checklists, and e) Aircraft is not operated in visible moisture or known or forecast icing conditions. (M) Procedure: a) Activate and verify both Main (1 & 2) Pitot Heater Systems operating normally b) Pull and secure the Standby (STBY) Pitot Heater Circuit Breaker using a Lockout Ring 6 ‐ Annunciator Lights on Pitot Heat (PROBES 1, 2, and STBY) Pushbuttons (Overhead Panel) B 3 2 (M) One Light may fail to illuminate 1 ‐ "FAIL" Lights provided: a) Associated Probe Heat System is verified to operate normally, b) Associated EICAS "PITOT FAIL" Cautions are verified to operate normally, and c) EICAS "PITOT HEAT OFF" Caution operates normally. (M) This item may be performed by a qualified Crewmember. With both engines running or ground power connected: a) Select all three PROBE Pushbuttons IN (ON) b) Verify the PITOT HEAT OFF Caution is not displayed on the CAS. Engineering Department
Página: 30‐4 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 6 ‐ Annunciator Lights on Pitot Heat (PROBES 1, 2, and STBY) Pushbuttons (Overhead Panel) c) Pull the associated Pitot B 3 2 1 ‐ "FAIL" Lights (Cont.) Heat c/b d) Verify the PITOT 1 or 2 STBY FAIL Amber Caution message illuminates on the EICAS field e) Reset circuit breaker (s) f) Select the associated PROBE Pushbutton OUT (Off) and verify the PITOT HEAT OFF Caution illuminates on EICAS g) Select the remaining PROBE pushbutton OUT (Off) B 3 2 (M) One Light may fail to illuminate 2 ‐ "OFF" Lights provided: a) Associated Probe Heat System is verified to operate normally, b) Associated EICAS "PITOT FAIL" Cautions are verified to operate normally, and c) EICAS "PITOT HEAT OFF" Caution operates normally. (M) This item may be performed by a qualified Crewmember. With both engines running or ground power connected: a) Select all three PROBE pushbuttons IN (On) b) Verify the PITOT HEAT OFF Amber Caution message is not illuminated on the CAS display c) Select the associate PROBE pushbutton(s) OUT (Off) d) Verify the PITOT HEAT OFF Amber Caution message illuminates on the CAS display. Engineering Department
Página: 30‐5 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION B 2 1 (M) (O) One may be inoperative 7 ‐ De‐Ice Press Sensor provided: a) All remaining Indications on EICAS ICE PROTECT System Page operate normally, b) Both Airfoil Bleed Shut Off Valves (SOV's) operate normally, c) Before dispatch into known or forecast icing conditions all De‐Icer Boots are ground checked and normal inflation and deflation is visually confirmed, and d) Before takeoff into known or forecast icing conditions, adequate De‐ice Pressure from the affected side is verified using EICAS ICE PROTECT System Page Indications. B 2 0 May be inoperative provided aircraft is not operated in known or forecast icing conditions. (O) Procedure: a) After staring one engine: 1) Operate AIRFOIL SINGLE button, and 2) Have outside observer verify that all airfoil de‐ice boots on wings, vertical stabilizer, and horizontal stabilizer inflate and deflate normally. b) Before Takeoff: 1) Select AIRFOIL BLEED associated failed De‐ice press. Sensor to OFF. 2) Operate AIRFOIL SINGLE button. Engineering Department
Página: 30‐6 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 3) Ensure that normal B 2 0 7 ‐ De‐Ice Press Sensor inflation cycle of Airfoil de‐ice (Cont.) boots is noted on the ICE PROTECT System page 4) Select both AIRFOIL BLEED on (Horizontal flow bar) (M) This item may be performed by a qualified Crewmember a) With both engines running, operate airfoil single button and verify that all airfoil de‐ice boots on wings , vertical stabilizer, and horizontal stabilizer boot indications operate normally on EICAS ICE PROTECT System Page. b) Operate both airfoil bleed switches and that the airfoil bleed shut off valves open normally by watching the indication on EICAS ICE PROTECT System Page Indications. A 2 1 (M) One may be inoperative provided: 8 ‐ Engine Intake Deice Systems a) A Visual Inspection of inoperative System, performed once each Flight Day, verifies absence of debonding, delamination or damage to boots or underlying structure, b) Aircraft is not operated in known or forecast icing conditions, and c) Operations are limited to two flight days before repairs are made. Engineering Department
Página: 30‐7 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 8 ‐ Engine Intake Deice Systems A 2 1 NOTE: The Airplane may not be Dispatched with any evidence of (Cont.) debonding, delamination or damage to Boots or underlying Engine Intake structure. A 2 0 (M) May be inoperative provided: a) A Visual Inspection of inoperative System performed once each Flight Day, verifies absence of debonding, delamination or damage to boots or underlying structure b) Aircraft is operated in day VMC conditions, only. c) Aircraft is not operated in known or forecast icing conditions d) Operations are limited to two flight days before repairs are made NOTE: The Airplane may not be Dispatched with any evidence of debonding, delamination or damage to Boots or underlying Engine Intake structure. (M) Visually Inspect the affected intake each flight day for debonding, delamination or damage to the boots or underlying structure. 9 ‐ Ice Detector C 1 0 (M) (O) May be inoperative provided: a) Erroneous Indications are deactivated, and b) Alternate procedures for detection of airfoil icing are developed and used. (O) Visually monitor ice accumulation on wing leading edges, windshield wiper, window frames or other airframe parts visible to pilots. Engineering Department
Página: 30‐8 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 9 ‐ Ice Detector (Cont.) C 1 0 (M) This may be performed by a qualified Crewmember a) Pull and secure c/b for Ice Detection System using a Lockout ring. 10 – TAT Heater System B 1 0 May be inoperative provided: a) Fuel Tank Temperature Indications and Cautions operate normally, and b) Airplane is not operated in known or forecast icing conditions. 11 ‐ Windshield Heat Systems B 2 1 (M) (O) One may be inoperative 1 ‐ Forward Windows provided: a) Approach Minimums do not require its use, b) Affected Window's Heat System is deactivated, c) Affected Window's EICAS "WSHLD HEAT FAIL" Caution is deactivated, d) EICAS "WSHLD HEAT FAIL" Cautions and ICE PROTECT System Page Failure Messages for all remaining Windows operate normally, e) Side Window Heat Systems operate normally, f) Both Air Conditioning Packs operate normally, g) ECS Flow Mode remains in HIGH, h) Feet Airflow Lever on affected side remains in full UP i) Aircraft is not operated in known or forecast icing conditions, and j) Alternate procedures to clear inadvertent Window fogging are established and used. Engineering Department
Página: 30‐9 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 11 ‐ Windshield Heat Systems B 2 1 (O) Procedure: 1 ‐ Forward Windows (Cont.) a) Select the Fleet Airflow Lever to full UP b) Operate the ECS System in HIGH c) Use a clean cloth to wipe the inside surface of a window in the event of fogging. d) Flight into known or forecast icing conditions is prohibited. (M) This item may be performed by a qualified Crewmember a) Pull and secure the affected Windshield (W/S) Heat Front circuit breaker using a lockout ring b) Turn aircraft power ON and select both Windshield Heat Pushbuttons ON (In) c) Verify affected "W/S HEAT FAIL" message is extinguished and all other "W/S HEAT FAIL" message illuminate on the ICE PROTECTION EICAS Page and the "WSHLD HEAT FAIL" CAS message is illuminated d) With an engine running, turn AC BUS 1 & 2 on line and ensure all "W/S HEAT FAIL" messages extinguish. C 2 1 (M) (O) One may be inoperative 2 ‐ Side Windows provided: a) Affected Window's Heat System is deactivated, b) Affected Window's EICAS "WSHLD HEAT FAIL" Caution is deactivated, Engineering Department
Página: 30‐10 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 11 ‐ Windshield Heat Systems c) EICAS "WSHLD HEAT FAIL 2 1 C 2 ‐ Side Windows (Cont.) Caution and ICE PROTECT" Systems Page Failure Messages for all remaining Windows operate normally d) Forward Window Heat Systems operate normally e) Both Air Conditioning Packs operate normally, f) Aircraft is not operated in known or forecast icing conditions, and g) Alternate procedures to clear inadvertent Window fogging are established and used. (O) Use a clean cloth to wipe the inside surface of a window in the event of fogging (M) This item may be performed by a qualified Crewmember a) Pull and secure the affected Windshield (W/S) Heat circuit breaker using a lockout ring b) Turn aircraft power ON and select both Windshield Heat pushbuttons ON (in) c) Verify affected "W/S HEAT FAIL" message is extinguished and all other "W/S HEAT FAIL" messages illuminate on the ICE PROTECTION EICAS Page and the “WSHLD HEAT FAIL" CAS message is illuminated. d) With an engine running, turn A/C BUS 1&2 on line and ensure all "W/S HEAT FAIL" message extinguishes. Engineering Department
Página: 30‐11 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION 12 ‐ "ON" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate ENGINE INTAKE Deice Pushbuttons provided: (Overhead Panel) a) Affected Engine Intake Deice System(s) is verified to operate normally, b) Associated Engine Intake "ENG DEICE FAIL" EICAS Caution(s) operates normally, c) EICAS ICE PROTECT System Page operates normally, and d) Alternate procedures for determining Engine Intake Deice System status are established and used. (O) Select the associated ENGINE INTAKE Pushbuttons to the same position as the ENGINE INTAKE Pushbuttons ON Annunciator Light as required for aircraft operations and monitor ICE PROTECT System Page to verify proper operation of ENGINE INTAKE system by nothing the ENGINE DE‐ICER ON or OFF annunciation as appropriated (M) This item may be performed by a qualified Crewmember. With the associated engine(s) running: a) Select ENGINE INTAKE Pushbutton IN (ON) and verify the "ON" ENGINE DEICER blue Message illuminates on the ICE PROTECT System Page. b) Pull associated ICE PROTECT INTAKE circuit breaker and verify "ENG DEICE FAIL EICAS" Caution illuminates. Reset circuit breaker and verify Caution extinguishes. Engineering Department
Página: 30‐12 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION c) Select ENGINE INTAKE 12 ‐ "ON" Annunciator Lights on C 2 0 ENGINE INTAKE Deice Pushbuttons pushbuttons OUT (Off) and (Overhead Panel) verify the "OFF" ENGINE (Cont.) DEICER Blue Message illuminates on the ICE PROTECT System Page 13 ‐ Horizontal (Valve Open) Flow Bars C 2 0 (M) (O) Light(s) may fail to illuminate provided: on Airfoil Deice BLEED Pushbuttons a) Affected Airfoil Deice Bleed (Overhead Panel) System(s) is verified to operate normally, b) Associated Airfoil Deice BLEED "OFF" Annunciator Light(s) operates normally, c) EICAS ICE PROTECT System Page operates normally, and d) Alternate procedures for determining Airfoil Deice System status are established and used. (O) Prior to each departure, ensure the associated AIRFOIL BLEED Pushbutton is selected IN (flush) and the OFF light has extinguished. (M) With the associated engine running or with both engines running and the non affected AIRFOIL BLEED Pushbutton selected to the OFF position: a) Select the associated AIRFOIL BLEED pushbutton IN (On) and note the OFF light extinguishes b) Activate AIRFOIL SINGLE Pushbuttons and verify proper inflation of surface de‐ice boot. c) Select ICE PROTECT System Page and verify operation by watching surface de‐ice boot indications Engineering Department
Página: 30‐13 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION d) Select the associated 13 ‐ Horizontal (Valve Open) Flow Bars C 2 0 AIRFOIL BLEED Pushbutton on Airfoil Deice BLEED Pushbuttons OUT (Off) and note the OFF (Overhead Panel) light illuminates (Cont.) e) Activate AIRFOILD SINGLE Pushbutton and verify AIRFOIL DEICE FAIL Amber Caution illuminates on CAS Display. 14 ‐ "OFF" Annunciator Lights on C 2 0 (M) (O) Light(s) may fail to illuminate provided: Airfoil Deice BLEED Pushbuttons a) Affected Deice Airfoil Bleed (Overhead Panel) System(s) is verified to operate normally, b) Associated Airfoil Deice BLEED Horizontal (Valve Open) Flow Bar Light(s) operates normally, c) EICAS ICE PROTECT System Page operates normally, and d) Alternate procedures for determining Airfoil Deice System status are established and used. (O) Prior to each departure, ensure the associated AIRFOIL BLEED Pushbutton is selected IN (flush) and the horizontal flow bar is illuminated. If the associated AIRFOIL BLEED pushbutton must be selected OFF, selected OFF, select the pushbutton out and ensure the Horizontal Flow Bar extinguishes. (M) With the associated engine running or with both engines running and the non affected AIRFOIL BLEED Pushbutton selected to the OFF position: a) Select the associated AIRFOIL BLEED pushbutton IN (On) and note the horizontal flow bar (white) is illuminated Engineering Department
Página: 30‐14 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION b) Activate AIRFOIL SINGLE 14 ‐ "OFF" Annunciator Lights on C 2 0 Pushbuttons and verify proper Airfoil Deice BLEED Pushbuttons inflation of surface de‐ice (Overhead Panel) boot. (Cont.) c) Select ICE PROTECT System Page and verify operation by watching surface de‐ice boot indications d) Select the associated AIRFOIL BLEED Pushbutton OUT (Off) and note the horizontal flow bar (white) is extinguished, OFF light illuminates e) Activate AIRFOILD SINGLE Pushbutton and verify AIRFOIL DEICE FAIL Amber Caution illuminates on the CAS Display. 15 ‐ "ON" Annunciator Light on Airfoil C 1 0 (M) (O) Light may fail to illuminate Deice SINGLE Pushbutton (Overhead provided: Panel) a) Airfoil Single Cycle Mode is verified to operate normally, b) EICAS "SINGLE FAIL" Caution operate normally, c) EICAS ICE PROTECT System Page operates normally, and d) Alternate procedures for monitoring Airfoil Deice System SINGLE operation are established and used. NOTE: A SINGLE "ON" Annunciator Light for an inoperative Airfoil Deice System may be inoperative. (O) When the AIRFOIL SINGLE Pushbutton is pressed, verify the Airfoil Deicer system is activated by: a) Visually observing the inflation of the wing deice boots, or Engineering Department
Página: 30‐15 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION b) Observing the inflation 15 ‐ "ON" Annunciator Light on Airfoil C 1 0 sequence and the "SINGLE" Deice SINGLE Pushbutton (Overhead message illuminated on the Panel) ICE PROTECT System Page. (Cont.) (M) With both engine running: a) Press the "AIRFOILD SINGLE” pushbutton b) Verify the "SINGLE" (AIRFOIL DEICER) blue message illuminates on the ICE PROTECT System Page c) Pull ICE PROT AIRF SGL circuit breaker and verify EICAS "SINGLE FAIL" caution illuminates. Reset circuit breaker and verify Caution light extinguishes d) Verify the Airfoil Deice system is activated through on entire cycle. 16 ‐ "FAIL" Annunciator Lights on B 2 1 (M) One Light may fail to illuminate provided: HORNS Heat Pushbuttons (Overhead a) Associated Horn Deice Panel) System is verified to operate normally, b) Associated EICAS "ELEV HEAT FAIL" Caution(s) operate normally, and c) Associated HORN Pushbutton "ON" Annunciator Light(s) operates normally. (M) This item may be performed by a qualified Crewmember. With the engines running and the alternators selected to the OFF positions: a) Select affected LH/RH HORNS Pushbutton(s) ON, b) Verify associated ELEV HEAT FAIL Caution illuminates on EICAS. Engineering Department
Página: 30‐16 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION c) Select alternators ON and 16 ‐ "FAIL" Annunciator Lights on B 2 1 verify ELEV HEAT FAIL Caution HORNS Heat Pushbuttons (Overhead extinguishes. Panel) (Cont.) 17 ‐ "ON" Annunciator Lights on B 2 0 (M) (O) Light(s) may fail to illuminate HORNS Heat Pushbuttons (Overhead provided: Panel) a) Associated Horn Deice System is verified to operate normally, b) Associated EICAS "ELEV HEAT FAIL" Caution(s) operates normally, c) Associated HORN Pushbutton "FAIL" Annunciator Light(s) operates normally, d) Associated EICAS "SHAKER‐ PUSHER ICE" Status Message operates normally, and e) Alternate procedures for determining Elevator and Rudder Horn Anti‐icing System status are established and used. (O) Select both LH/RH HORNS Pushbuttons ON or OFF simultaneously and ensure both are selected to the same position (Both Pushbutton's IN (Flush) for ON, both Pushbutton's OUT for OFF (Not flush). When selecting HORN HEAT to ON ensure the “ON" annunciation light on the unaffected light illuminates. When selecting the HORN HEAT to OFF, ensure the unaffected Pushbutton is dark. (M) This item may be performed by a qualified Crewmember. With the engines running and the alternators selected to the Off position: Engineering Department
Página: 30‐17 Fecha: 19/03/2013 Revisión: 02
Minimum Equipment List Do‐328 ‐100 2‐ Rectification Interval 3‐ Number Installed 1‐ System and Sequence numbers 4‐ Number Required for Dispatch 5‐ Remarks or Exceptions 30 ICE AND RAINPROTECTION a) Select affected LH/RH 17 ‐ "ON" Annunciator Lights on B 2 0 HORNS Pushbutton (s) ON HORNS Heat Pushbuttons (Overhead Panel) b) Verify the associated ELEV (Cont.) HEAT FAIL Caution illuminates on EICAS c) Select alternators ON and verify ELEV HEAT FAIL Caution extinguishes and " SHAKER PUSHER ICE” Blue Status message illuminated on EICAS 18 ‐ "ICE" Annunciator Light on ICE C 1 0 (M) (O) Light may fail to illuminate provided: DETECTOR TEST Pushbutton a) Ice Detector is verified to (Overhead Panel) operate normally, b) EICAS "ICE DETECTOR FAIL" Caution, and "ICE DETECTED" Status Message operate normally, c) EICAS ICE PROTECT System Page operates normally, and d) Alternate procedures for determining airframe ice accretion are established and used. (O) Ice protection will be utilized at any time icing conditions exist;
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