REVISION TO AIRCRAFT PUBLICATION: EC175B

PUBLICATION CONCERNED: MMEL

CUSTOMIZATION AIRCRAFT S/N :

CERTIFICATION CODE : A

- The outline of the revision is given below :

This revision of MMEL EC175B variant deals with the Normal Revision 3 Edit.2 of the
EASA Approved EC 175 B MMEL, in order to re-introduce item 25-40-01 in ATA 25 (post
MOD 99A5677-00).

- Check that pages in each supplement and those specified in the list of effective pages.
- Return the acknowledgment card.
- This list of amended pages may be filed (apart from the manual).

DELETED PAGES INSERTED PAGES

Section Pages Date code Section Pages Date code

NR3 00.00.00.P5 1 to 4 18-42 00.00.00.P5 1 to 4 19-07

NR3 00.10.00 1 to 44 18-42 00.10.00 1 to 44 19-07
NR3 25.00.00 1 to 25 18-42 25.00.00 1 to 25 19-07

THE CONTENT OF THE MMEL REVISION

MUST BE BROUGHT TO THE ATTENTION OF MECHANICS AND FLIGHT CREWS.

UPDATE GUIDE - Page 1/2

18-03-2019
 OUTLINE OF THE REVISION

MMEL EC175B EASA

NR3 Date-code (19-07)

Technical description of the project:

ATA modified:
00.00.00.P5: Revised in 19-07: Updated for RN3.

00.10.00: PRELIMINARY NOTES

Item n° Description of the change

5.3.1 MASTER LIST

FUEL TST FAIL message: wording corrections:
MESSAGES ISOLATED
BY AUTOMATIC PWR-UP
(tank 1 instead of Feeder 1, and Feeder tank 2 and Feeder
TST tank 3 instead of Feeder 2 and Feeder 3)

First Item FLOAT NOT ARMED is re-introduced with the

5.4.10 FLOATATION condition:
''Only if MOD 99A05677-00 (Ref EFU update) is installed:''

25.00.00: EQUIPMENT - FURNISHINGS

Item n° Description of the change
25-40-01 EFS:
Auto arming function Item is re-introduced (Post MOD 99A5677-00 only).

UPDATE GUIDE - Page 2/2

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LIST OF EFFECTIVE PAGES - EASA CERTIFICATION

(1) EFFECTIVITY:
• Without indication .......... Applicable to all aircraft.
• A .................................. Specific to EASA.

(2) VARIANT OF STANDARD DEFINITION EFFECTIVITY:

• Without indication .......... Applicable to all aircraft.
• XXXX ............................. Specific to the XXXX aircraft configuration:

DATE
ATA PAGES (1) (2)
CODE
00.00.00.P1 1 18-22 A
00.00.00.P2 1 18-22
00.00.00.P5 1 to 4 19-07 A
00.00.00.P6 1 18-22
00.10.00 1 to 44 19-07
21.00.00 1 to 8 18-22
22.00.00 1 to 11 18-22
23.00.00 1 to 5 18-38
24.00.00 1 to 2 18-22
25.00.00 1 to 25 19-07
26.00.00 1 to 2 18-22
28.00.00 1 to 12 18-22
29.00.00 1 to 2 18-22
30.00.00 1 to 2 18-22
31.00.00 1 to 2 18-22
32.00.00 1 to 4 18-22
33.00.00 1 to 8 18-22
34.00.00 1 to 12 18-38

APPROVED EC 175 B 00.00.00.P5

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DATE
ATA PAGES (1) (2)
CODE
43.00.00 1 18-22
44.00.00 1 18-22
46.00.00 1 to 4 18-22
52.00.00 1 to 3 18-22
56.00.00 1 18-22
63.00.00 1 to 10 18-22
65.00.00 1 to 2 18-22
71.00.00 1 18-22
72.00.00 1 18-22
73.00.00 1 18-22
93.00.00 1 18-22

LOG OF EASA NORMAL REVISIONS

EDITION 2 EASA approval N. 10066956

NORMAL REVISION 0 date code 18-22
on September 24, 2018
(NOT ISSUED)
MMEL ''STP2'' variant removal and re-edition of the MMEL applicable to
Title
all.
Revised
information
All sections (same content than former ''STP2'' variant NR7).
Deleted
None
information
Approved on September 28, 2018
EDITION 2
under the authority of EASA Design
NORMAL REVISION 1 date code 18-38
Organization Approval n. 21J.700
Title Integration of new items (Dual hoist and Polycon WICS).
Revised
information
0.0.P5, ATA 00-10-00 - 23-00-00 - 25-00-00 and correction on ATA 34.
Deleted
None
information
Approved on October 19, 2018
EDITION 2
under the authority of EASA Design
NORMAL REVISION 2 date code 18-42
Organization Approval n. 21J.700
Title Removal of item 25-40-01
Revised
information
0.0.P5, ATA 00-10-00, ATA 25-00-00 .
Deleted
Item 25-40-01 related to FLOAT NOT ARMED message
information

APPROVED EC 175 B 00.00.00.P5

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EDITION 2 EASA approval No. 10069290

NORMAL REVISION 3 date code 19-07 on: March 19, 2019.
Title Re-introduction of item 25-40-01 Post MOD 99A05677-00 (EFU)
Revised
information
0.0.P5, ATA 00-10-00 - 25-00-00 .
Deleted
None
information

FORMER NORMAL REVISIONS OF FIRST EDITION (REMINDER)

EDITION 1 EASA approval N. 10057645

NORMAL REVISION 0 date code 16-04 on April 04, 2016
Title Creation of the document for MMEL ''STP2'' variant.
Revised
None
information
Deleted
None
information
EDITION 1 EASA approval N. 10059195
NORMAL REVISION 1 date code 16-29 on August 31, 2016
Title Incorporation of new items for VIP and SAR configurations.
Revised
00.00.P5, 00.10.00, and ATA 22, 25, 33, 34, creation of ATA 44, 52.
information
Deleted
None
information
Approved on September 29, 2016
EDITION 1
under the authority of EASA Design
NORMAL REVISION 2 date code 16-39
Organization Approval n. 21J.700
Title Incorporation of new ''optional'' item for Ice detector.
Revised 00.00.P5, ATA 00-10-00, addition of ice detector item ATA30 and minor
information corrections on consequences ATA 34 and 46.
Deleted
None
information

APPROVED EC 175 B 00.00.00.P5

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EDITION 1 EASA approval N. 10062557

NORMAL REVISION 3 date code 17-20 on July 10, 2017
Title Incorporation of a new item for FADEC (TLD).
Revised
00.00.P5, ATA 00-10-00, addition of FADEC1 or 2 item ATA 72-02-01.
information
Deleted
None
information
Approved on July 13, 2017
EDITION 1
under the authority of EASA Design
NORMAL REVISION 4 date code 17-24
Organization Approval n. 21J.700
Title Introduction of new optional (EAPS) and minor corrections.
Revised
00.00.P5, 00.00.P6, 00-10-00, and ATA 23 - 25 - 31 - 34 - 63 - 71 - 72 - 73.
information
Deleted
Item Chip Burner moves from ATA 72 to ATA 73 (new)
information
Approved on November 17, 2017
EDITION 1
under the authority of EASA Design
NORMAL REVISION 5 date code 17-35
Organization Approval n. 21J.700
Title Error corrections and improvements.
Revised
00.00.P5, ATA 00-10-00, ATA 25 - 28 and 46.
information
Deleted
None
information
1 - EASA approval N. 10065233
EDITION 1 on April 13, 2018
NORMAL REVISION 6 date code 18-10 2 - EASA approval N. 10065499
on May 09, 2018
1 - NAB and
Title
2 - RDR1700.
Revised 00.00.P5, ATA 00-10-00 - ATA 21 for new item (NAB cooling) added
information and ATA 34 (for RDR1700).
Deleted
None
information
Approved on May 17, 2018
EDITION 1
under the authority of EASA Design
NORMAL REVISION 7 date code 18-14
Organization Approval n. 21J.700
Title Introduction of new items for Public Services configurations.

Revised 00.00.P5, 00.00.P6, ATA 00-10-00 - ATA 22 - ATA 23 - 25 - 26 - 31 - 33 - 34

information - 43 (new) - 46 and 93 (new).
Deleted
None.
information

APPROVED EC 175 B 00.00.00.P5

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PRELIMINARY NOTES

1 PREAMBLE
1.1 INTRODUCTION
The following is applicable for operators under European air operations regulations.
Paragraph 1.c.2 of Annex I to Article 5 (Essential requirements for airworthiness) of
Regulation (EC) No. 216/2008 (the ‘Basic Regulations’) requires that all equipment installed
on an aircraft required for type certification or by operating rules shall be operative.
However, paragraph 2.a.3 of Annex IV to Article 8 (Essential requirements for air operations)
of the Basic Regulations also allows the use 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 of all installed items may not be necessary when the remaining
operative equipment can provide an acceptable level of safety.

1.2 PURPOSE AND LIMITATIONS

This Master Minimum Equipment List (MMEL) is developed by Airbus Helicopters and
approved by EASA to improve aircraft use and thereby providing more convenient and
economic air transportation for the public.
This MMEL includes those items related to airworthiness and IR-OPS and other items the
EASA 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 blades and
rotors.
In order to maintain an acceptable level of safety, the MMEL establishes limitations on the
duration of and conditions for operation with inoperative items.
Unless specifically allowed by this MMEL, an inoperative item may not be removed from the
aircraft.

APPROVED EC 175 B 00.10.00

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1.3 UTILIZATION
Prior to application of the MMEL, check the conditions for dispatch in the paragraph 5 "MMEL
ENTRIES BY MASTER LIST MESSAGE"

The MMEL is the basis for the development of an individual operator’s MELs which take into
consideration the operator’s particular aircraft equipment configuration and operational
conditions.
All items related to the airworthiness and the operational regulations of the aircraft not listed
on the MMEL shall be operative.
Airworthiness Directives supersedes the content of this MMEL.
When an item is discovered to be inoperative, it is reported by making an entry in the
continuing airworthiness record system or the operator’s technical log, as applicable.
For failures occurring in flight, Flight Manual procedures are applicable until the completion of
flight (rotor stopped).
Following sufficient fault identification, the item is then either rectified or deferred following
the MEL or other approved means of compliance acceptable to the competent authority and
the Agency prior to further operation. MEL conditions and limitations do not relieve the
operator from determining that the aircraft is in a condition for safe operation with items
inoperative.
Prior to operation with any item inoperative, acceptance by the crew is required in
accordance with the continuing airworthiness management procedures.
When developing the MEL, compliance with the stated intent of the preamble,
definitions and the conditions and limitations specified in this MMEL is required.

Multiple inoperative items

Operators are responsible for exercising the necessary operational control to ensure that an
acceptable level of safety is maintained. The exposure to additional failures during continued
operation with inoperative systems or components must also be considered.
This MMEL takes into account multiple inoperative items. However, it is unlikely that all
possible combinations of this nature have been accounted for. Therefore, when operating
with multiple inoperative items, the inter-relationships between those items and the effect on
aircraft operation and crew workload shall be considered.

Rectification interval extension

This MMEL has been evaluated taking into account a one-time extension of the rectification
intervals of categories B, C and D.

APPROVED EC 175 B 00.10.00

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2 DEFINITIONS AND EXPLANATORY NOTES

‘Rotorcraft Flight Manual’ means the document required for type certification and approved
by EASA.
‘Alternate procedures are established and used’ or similar statement, means that alternate
procedures (if applicable), to the affected process, must be drawn up by the operator.
‘Any in excess of those required by regulations’ means that the listed item is required by
applicable legislation (or the applicable airspace requirements) and must be operative, only
excess items may be inoperative.
When the item is not required, it may be inoperative for the time specified by its rectification
interval category.
‘As required by applicable regulations‘ means that the listed item of equipment is subject to
certain provisions (restrictive or permissive) expressed in the applicable legislation
(European air operations regulations, Single European Sky legislation or the applicable
airspace requirements).
When the equipment is not required, it may be inoperative for the time specified by its
rectification interval category.
‘Calendar Day’ means a 24-hour period from midnight to midnight based on either UTC or
local time, as selected by the operator. All calendar days are considered to run
consecutively.
‘Commencement of flight’ is the point when an aircraft begins to move under its own power
for the purpose of preparing for take-off.
‘Considered Inoperative’, as used in the dispatch conditions, means that the item must be
treated for dispatch, taxiing and flight purposes as though it were inoperative. The item shall
not be used or operated until the original deferred item is repaired.
Additional actions include:
- documenting the item on the dispatch release (if applicable), placarding, and
- complying with all remarks, exceptions, and related MMEL provisions, including any (M)
and (O) procedures and observing the rectification interval.

APPROVED EC 175 B 00.10.00

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‘Daylight’ means the period between the beginning of morning civil twilight and the end of
evening civil twilight relevant to the local aeronautical airspace; or such other period, as
may be prescribed by the appropriate authority.
‘Day of discovery’ means the calendar day that a malfunction was recorded in the aircraft
maintenance record/log book.
‘Deactivated’ and ‘secured’ means that the specified item must be put into an acceptable
condition for safe flight.
"Extended-overwater flight" means flight overwater at a distance from land as defined in
operating rules in CAT.IDE.H.300 or NCC.IDE.H.227, as applicable.
‘Flight’, for the purposes of this MMEL, means the period of time between the moment
helicopter’s rotor start turning, until the moment the helicopter finally comes to rest at the
end of the flight and rotor is stopped.
‘Item’ means component, instrument, equipment, system or function.
‘Icing Conditions’ means an atmospheric environment that may cause ice to form on the
aircraft or in the engine(s) as defined in the RFM.
‘If installed’ means that the item is either optional or is not required to be installed.
‘Inoperative’ means that the item does not accomplish its intended purpose or is not
consistently functioning within its approved operating limits or tolerances.
‘Is not used’ in the provisos, remarks or exceptions for an MMEL item may specify that
another item relieved in the MMEL ‘is not used’. In such cases, crew members should not
activate, actuate, or otherwise utilize that item under normal operations. It is not necessary
for the operators to accomplish the (M) procedures associated with the item.
However, operations-related provisions, (O) procedures and rectification interval must be
complied with. An additional placard must be affixed, to the extent practical, adjacent to the
control or indicator for the item that is not used, to inform crew members that an item is not
to be used under normal operations.
‘Intended Route’ corresponds to any point on the route including diversions to reach alternate
aerodromes required to be selected by the operational rules.

APPROVED EC 175 B 00.10.00

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‘It is not reasonably practical to repair or replace before commencement of the flight ’
The intention of this proviso is that the aircraft may be dispatched if there are inadequate
available spares or if there are no qualified and authorized personnel on base to perform
the task. The definition is not dependent on whether there is enough time available to
complete the task before the next flight. If the aircraft is at a maintenance base or any other
airport but the spare(s) or manpower is not available, then the aircraft may be dispatched.
As soon as the aircraft lands at an airport where the spares are available and there are
qualified and authorized personnel on base, the defect must be rectified.
‘(M)’ indicates a requirement for a specific maintenance procedure which must be
accomplished. Normally these procedures are accomplished by maintenance personnel
using Work cards from the Aircraft Maintenance Manual (AMM).
The simple maintenance procedures not involving an AMM work card are described directly
in column 5.
‘Master Minimum Equipment List’ means a document approved by EASA that establishes
the aircraft equipment allowed to be inoperative under conditions specified therein for a
specific type of aircraft.
‘Note’ provides additional information for flight crew or maintenance consideration.
‘–’ A dash indicates a variable number of the equipment items either installed (column (3)
"Number Installed") or required (column (4) "Number required for dispatch"), or not
applicable.
‘Number Installed’ is the number of items normally installed in the aircraft. This number
represents the aircraft configuration considered in developing this MMEL. Should the
number be variable (e.g. passenger cabin items), or not applicable, a number is not
required; a ‘–’ is then inserted.
‘Number required for dispatch’ is the minimum number of items required for operation
provided the conditions specified are met. Should the number be variable (e.g. passenger
cabin items) or not applicable, a number is not required; a ‘-’ is then inserted.
‘(O)’ indicates a requirement for a specific operational procedure which must be accomplished
in planning for and/or operating with the listed item inoperative.
‘Placarding’: Each inoperative item must be placarded.
NOTE: To the extent practical, placards should be located adjacent to the control or
indicator for the item affected.

APPROVED EC 175 B 00.10.00

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‘Rectification intervals’: Inoperative items or components must be rectified at or prior to

the rectification intervals established (column (2)) by the following letter designators:
Category A:
No standard interval is specified; however, items in this category shall be rectified in
accordance with the conditions stated in the MMEL.
a) Where a time period is specified in calendar days or flight days, the interval
excludes the day of discovery.
b) Where a time period is specified other than in calendar days or flight days, it shall
start at the point when the anomaly is recorded.
Category B:
Items in this category shall be rectified within three (3) calendar days, excluding the
day of discovery.
Category C:
Items in this category shall be rectified within ten (10) calendar days, excluding the day
of discovery.
Category D:
Items in this category shall be rectified within one hundred and twenty (120) calendar
days, excluding the day of discovery.
‘Remarks or Exceptions’ include statements either prohibiting or allowing operation with
a specific number of items inoperative, provisos (conditions and limitations), notes,
(M) and/or (O) symbols, as appropriate for such operation.
‘Visible Moisture’ means 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.
‘VFR’ means flight performed according to visual flight rules.
‘VMC’ means flight performed according to visual meteorological conditions.
‘IFR’ means flight performed according to instrument flight rules.
‘IMC’ means flight performed according to instrument meteorological conditions.

APPROVED EC 175 B 00.10.00

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3 PRESENTATION
IMPORTANT NOTE
A possible consequence of the equipment failure may be a caution message or a
caution light, raised by avionics. When practical, such consequences are included in
the list of items for information purposes only.

Main messages are listed only and are indicative. Additional messages consecutive to
system malfunction or system inhibition may appear and shall not be considered in
this MMEL.

(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

DISPATCH CONDITIONS.

ATA-number-ref Equipment RI X Y Different conditions may be required for

operations:
Consequences: - when they have a cumulative effect; they
(possibly and are indicated as follows:
for information purposes only) a), b), c) ….
- When they are exclusive, they are listed as
follows: - or - or - …

APPROVED EC 175 B 00.10.00

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4 MMEL MANAGEMENT
4.1 DEFINITIONS
Variant of standard definition and Certification specificities
The "standard" MMEL corresponds to the definition of the basic version and constitutes the
reference for certification.
The "variant" MMEL corresponds to a Type design definition that includes modifications
modifying the standard TC.
Information concerning either a variant of standard definition or specific non-EASA
certification requirements may necessitate adapting the information of the EASA MMEL on
certain items within some ATA chapters. In these cases, specificities are covered by
SUPPLEMENTS for variants of standard definition and by APPENDIX for specific certification
requirements for foreign authorities
A SUPPLEMENT or APPENDIX is a MMEL covering any differences relative to the Standard
aircraft MMEL information, for each affected ATA, by supplementing or modifying standard
MMEL affected items only.
The SUPPLEMENT or APPENDIX is updated as a stand-alone document.

List of effective pages and applicability

The list of effective pages (P5) identifies, for each ATA, all the pages making up the MMEL.
The list of effective pages is supplemented by a log of Normal Revisions.

4.2 GUIDANCE IN THE USE OF SUPPLEMENTS AND APPENDICES

4.2.1 APPLICABILITY
Supplements cover a variant of standard definition linked to design modifications.
Appendices cover specific certification requirements of foreign Authorities.
Supplements and appendices must be used in conjunction with the standard EASA
MMEL.
The applicability (variant of standard definition or foreign Authority) is clearly mentioned in
the relevant Supplement or appendix.
In case of an appendix made due to specific certification requirements of a foreign
Authority, it is applicable for the aircraft which operate under this specific Certification
jurisdiction.

List of MMEL Supplements

The complete list of applicable Supplements is given in ATA 00.00.00.P2.

APPROVED EC 175 B 00.10.00

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4.2.2 MMEL management with supplements and appendices

A supplement or an appendix defines the differences relative to the standard MMEL
recommended by EASA for the aircraft type, by identifying the differences at the latest
revision.
The information presented in the standard EASA MMEL remains applicable except where
superseded by an item in the supplement or in the appendix.
NOTE: Items within the supplement or appendix will use the same reference
number as the corresponding item in the standard EASA MMEL. Where an item in the
supplement or appendix does not appear in the standard MMEL, the number of this item
will be preceded by "S" (for Supplementary) and the sequential reference will commence
from "1" (e.g. S.1 would be the first specific item added in the affected ATA). Such items
will be placed at the end of the related ATA chapter.
A supplement or appendix must always be based upon a defined Normal Revision of the
EASA MMEL with the date-code clearly mentioned. Additional MMEL alleviation provided
by later issues of the standard EASA MMEL must not be used until this supplement or
appendix has been updated to confirm that issue as the base document.

APPROVED EC 175 B 00.10.00

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5 MMEL ENTRIES BY MASTER LIST MESSAGE

The MMEL entries section contains three subsections:
- Messages isolated during automatic and manual clearance test phases on ground,
• At automatic PWR-UP TST
• At Manual P-START TST
• At automatic START-UP TST
• And at manual P-FLT TST
- Master List message entries,
- Other advisories rose.

The master list message alert displayed is an abnormal situation requiring a crew action in
order to clear the related alert.
For such a case, the Master List procedure required by the Flight Manual has to be followed
and there is (if any) a MMEL item to apply for this alert.

When a Master list or when visible system malfunction is triggered, the flight crew and the
maintenance personnel should refer to this section as an entry point of the MEL for dispatch
purpose only.

5.1 H/C STATUS COLUMN

The H/C status column provides a short description of the failure. A master list message may
cover one or several failure modes of the system.
When there are several failures modes associated with different dispatch conditions, it
provides a simple way to identify each failure mode.
The H/C status must be entirely read in order to choose and apply the relevant condition of
dispatch.
The operator is responsible for identifying the failure mode and the applicable condition of
dispatch

5.2 CONDITION OF DISPATCH COLUMN

For each failure mode listed in the H/c status column, the condition of dispatch
column indicates the associated MMEL item (if any) to be applied for the dispatch.

- No dispatch:
It is not permitted to dispatch the aircraft

- Not related to a MEL:

The master list message alert does not report a system failure but a reversible
abnormal condition such as the state of a system or an H/C configuration or an
external condition. This condition is not a system failure and is not related to a
MEL. The corrective action to revert to normal condition is immediate, obvious or
well known by flight crew and/or maintenance personnel.

APPROVED EC 175 B 00.10.00

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5.3 MESSAGES ISOLATED DURING AUTOMATIC AND MANUAL TESTS

5.3.1 MASTER LIST MESSAGES ISOLATED BY AUTOMATIC PWR-UP TST

FADEC NO INPUT

H/C status Condition of dispatch

At least one engine parameter is not received

by the VMS. No dispatch
Possible loss of MOP, N1, TOT, TRQ, N2.

CHIP BURNER

H/C status Condition of dispatch

Engine chip burner device does not operate
Refer to item 73-23
properly.

FIRE EXTING

H/C status Condition of dispatch

Check on fire control panel:
Discriminate unavailable engine extinguishers No dispatch
(amber light 1 or 2)

ENG1 FIRE SENSOR ENG2

H/C status Condition of dispatch

The maintenance confirms that Engine
overheat detector is inoperative No dispatch

The maintenance confirms that the Engine fire

detection is inoperative No dispatch

APPROVED EC 175 B 00.10.00

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CARGO FIRE SNSR

H/C status Condition of dispatch

Check VMS-MAIN page and select "DATA" to
reach the cargo status: Refer to item 26-13-(2)
Cargo Temperature probe 1 validity
Check VMS-MAIN page and select "DATA" to
reach the cargo status: Refer to item 26-13-(2)
Cargo Temperature probe 2 validity
Check VMS-MAIN page and select "DATA" to
reach the cargo status:
Cargo smoke detection Refer to item 26-13-(1)
SMOKE FAIL (On VMS-MAIN page)

L/G SENSOR

H/C status Condition of dispatch

The maintenance check confirms that the
pressure of the affected L/G is abnormal and No dispatch
cannot be reinstated.
The maintenance check confirms that the
pressure of the affected L/G is correct: the
Refer to item 32-60-01
associated pressure monitoring system must
be considered inoperative.

The maintenance checks confirm that any L/G

micro switch is failed. It should be considered Refer to item 32-60-01
inoperative.

GND/FLT SENSOR

H/C status Condition of dispatch

Failure of some sensors and Data used in the
computation of the Ground/Flight conditions.
No dispatch
Consequence possible on AP, Engine logic...
L/G invalid.

APPROVED EC 175 B 00.10.00

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PITOT HEATING

H/C status Condition of dispatch

Un-commanded heating of Pitot while the H/C
is on ground. Not related to a MEL
(Caution with Pitot probe on ground)

ELEC TST FAIL

H/C status Condition of dispatch

Check VMS-ELEC subpage for parameter

validity:
DC bus tie open failure flag. No dispatch
Confirm at least one BTC open on batteries or
GPU.

Check VMS-ELEC subpage for parameter

validity:
DC bus tie closed failure flag. No dispatch
Confirm at least one BTC closed with the 2
generators connected.

Check VMS-ELEC subpage for parameter

validity: No dispatch
LH DC1, DC2 Generator voltage

Check VMS-ELEC subpage for parameter

validity: No dispatch
RH DC1, DC2 Generator voltage

Check VMS-ELEC subpage for parameter

validity: No dispatch
LH DC1, DC2 contactors Status.

Check VMS-ELEC subpage for parameter

validity: No dispatch
RH DC1, DC2 contactors Status

Check EPU status and DC EPU voltage on

No dispatch
VMS-ELEC subpage.

APPROVED EC 175 B 00.10.00

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ELEC TST FAIL

H/C status Condition of dispatch

Check VMS-ELEC subpage for parameter
validity:
LH DC1, DC2 generator Current and/or Refer to item 24-31
GEN1 DISCONNECTED

Check VMS-ELEC subpage for parameter

validity:
RH DC1, DC2 generator Current and/or Refer to item 24-31
DISCONNECTED GEN2

LH DC1, DC2 battery voltage and/or

Refer to item 24-32
BAT1 DISCONNECTED

RH DC1, DC2 battery voltage and/or

Refer to item 24-32
DISCONNECTED BAT2

Check VMS-ELEC subpage for parameter

validity:
Refer to item 24-20
(if installed) AC generator phase and voltage
and/or ALT DISCONN

Check on the clearance test subpage for:

DCEMB1 FAIL, DCEMB2 FAIL and/or No dispatch
EMER GEN DISCONN

Check on the clearance test subpage for:

DCEGS1 FAIL, DCEGS2 FAIL and/or No dispatch
EMER GEN DISCONN

Check on the clearance test subpage for:

DC EMERG FAIL and/or No dispatch
EMER GEN DISCONN

Check on the clearance test subpage for:

DC BUS TIE FAIL and/or No dispatch
ELEC1 BUS TIE FAIL ELEC2

APPROVED EC 175 B 00.10.00

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XMSN TST FAIL

H/C status Condition of dispatch

Check VMS-XMSN subpage. for parameter

validity: Refer to item 63-42
MGB Temp 1 and 2

Check VMS-XMSN subpage for parameter

validity: Refer to item 65-43
TGB Temp

Check VMS-XMSN subpage. for parameter

validity: Refer to item 65-46
IGB Temp

Check VMS-XMSN subpage.

for parameter validity: Refer to item 63-21
MGB Hub bearing chip

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-21
MGB Epicyclical chip

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-21
MGB LH access box chip

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-21
MGB bottom chip

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-23
MGB LH Input high speed chip

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-23
MGB RH Input high speed chip

APPROVED EC 175 B 00.10.00

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XMSN TST FAIL

H/C status Condition of dispatch

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-61-01
MGB Main circuit oil pressure transmitter

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-61-02
MGB Ramp circuit oil pressure transmitter

Check VMS-XMSN subpage for parameter

validity: Refer to item 63-61-03
MGB Stand-by circuit oil pressure transmitter

Check VMS-XMSN subpage for parameter

validity: Refer to item 65-41
TGB Chip

Check VMS-XMSN subpage. (MGB, IGB or

TGB) for parameter validity: Refer to item 65-44
IGB Chip

The maintenance confirms that the Rotor

Refer to item 63-51
Brake is inoperative

Check if --ROTOR BRAKE - on Master list:

The maintenance confirms that the Rotor Refer to item 63-58
Brake lever position sensor is inoperative

The maintenance confirms that the Health

Refer to items 31-31-01 or 31-31-02
Monitoring System (HMS) is inoperative

Check VMS-XMSN subpage (MGB, IGB or

TGB) for parameter validity: Refer to item 63.29
Declutch actuator

APPROVED EC 175 B 00.10.00

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FUEL TST FAIL

H/C status Condition of dispatch

Check VMS-FUEL subpage for

parameter validity:
Tank 1 Fuel level : quantity raw data status
displayed on VMS-FUEL page

and

Refer to item 28-43-01 (1)

Check VMS-FUEL subpage for

parameter validity:
Feeder tank 2 Fuel level: quantity raw data
status
displayed on VMS-FUEL page

and

Refer to item 28-43-01 (4)

APPROVED EC 175 B 00.10.00

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FUEL TST FAIL

H/C status Condition of dispatch

Check VMS-FUEL subpage for

parameter validity:
Feeder tank 3 Fuel level: quantity raw data
status
displayed on VMS-FUEL page

and
Refer to item 28-43-01 (5)

Check VMS-FUEL subpage for

parameter validity:
Tank 4 Fuel level: quantity raw data status
displayed on VMS-FUEL page

and

Refer to item 28-43-01 (2)

APPROVED EC 175 B 00.10.00

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FUEL TST FAIL

H/C status Condition of dispatch

Check VMS-FUEL subpage for

parameter validity:
Intermediate tank Fuel level: quantity raw
data status displayed on VMS-FUEL page

and

Refer to item 28-43-01 (3)

Check VMS-FUEL subpage for

parameter validity:
Both Feeders Fuel gauging displayed on
VMS-FUEL page

and

Refer to item 28-43-01 (6)

APPROVED EC 175 B 00.10.00

19-07 Page 19
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FUEL TST FAIL

H/C status Condition of dispatch

Check VMS-FUEL subpage for

parameter validity:
Low level displayed on VMS-FUEL page

Refer to item 28-43-02

(Step2 and step2+): or

(Step3 or later):

Check VMS-FUEL page:

Fuel gauging default on VMS-FUEL page

Refer to items 28-43-01 ((1) to (6))

Check VMS-FUEL subpage for

parameter validity:
Total fuel quantity
Refer to items 28-43-01 ((1) to (6))

Check VMS-FUEL subpage:

Fuel circuit 1, 2 (pressure transmitter)

parameter validity Refer to item 28-22-02

APPROVED EC 175 B 00.10.00

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FUEL TST FAIL

H/C status Condition of dispatch

Check VMS-FUEL subpage:

Fuel tank 2, 3 (temp. sensor) validity

Refer to item 28-44

Check VMS-FUEL subpage:

Fuel circuit 1, 2 (SOV) validity

No dispatch
(Step2 and step2+): or

(Step3 or later):

Check VMS-FUEL subpage:

Fuel pump validity

(Step2 and step2+): or

Refer to item 28-22-01
(Step3 or later):
(indicate bad switch position only)
- If maintenance confirms one or more fuel
pump malfunction:

APPROVED EC 175 B 00.10.00

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AMC MINOR REDUND (step2 only)

H/C status Condition of dispatch

NOTE
Loss of one to two redundancy of MFD to
AMC signals. Not related to a MEL
As those signals are highly redundant when (refer to FLM section 4.10)
even the next failure will not lead to
degraded functionality.

AIR1 DATA REDUNDANCY

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Co-pilot Air data
Failure of ADU 1 and ADU 4, Refer to item 34-10
providing "Air data 1" parameters (linked to
Pitot 1).

DATA REDUNDANCY AIR2

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Pilot Air data
Failure of ADU 2 and ADU 3, Refer to item 34-10
providing "Air data 2" parameters (linked
to Pitot 2).

AIR 1 DATA FAIL

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Failure of ADU 1 and ADU 4,
Refer to item 34-10
providing "Air data 1" parameters (linked
to Pitot 1).

DATA FAIL AIR 2

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Failure of ADU 2 and ADU 3, Refer to item 34-10
providing "Air data 2" parameters (linked
to Pitot 2).

APPROVED EC 175 B 00.10.00

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MAG HDG REDUND

H/C status Condition of dispatch

Check VMS-RCNF subpage:

No dispatch
HDG 1, HDG 2 rejected by AFCS

HDG1 MAG HDG FAIL HDG2

H/C status Condition of dispatch

Loss of HDG 1 or 2 Refer to item 34-23 or item 34-26-01

APPROVED EC 175 B 00.10.00

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FDRS

H/C status Condition of dispatch

A FDRS component is inoperative

The maintenance check confirms CVR Refer to item 31-32

that the component is inoperative: FDR Refer to item 31-32
The CV/FDR test is inoperative CVFDR Refer to item 31-32

FLT REPORT OVLIM

H/C status Condition of dispatch

Check the exceedance logged on the flight
report page: Not related to a MEL
NOTE: It is definitively cleared only upon (refer to FLM section 3.13)
engine start.

SHOCK SNSR AMC2

H/C status Condition of dispatch

Failure of at least one shock sensor in front of

No dispatch
AMC2.

OAT SENSOR DEG

H/C status Condition of dispatch

The maintenance check confirms the

degradation of OAT sensors: Refer to item 34-14
- loss of one temperature probe

Check on FND the loss of displaying OAT:

The maintenance check confirms the
No dispatch
degradation of OAT sensors:
- loss of both temperature probe

Check on FND the loss of displaying OAT:

The maintenance check confirms the
degradation of OAT sensors: Refer to item 34-14
- Discrepancy detected between two
temperature probes.

APPROVED EC 175 B 00.10.00

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MFD# CPU1 MAJOR DEG MFD#

H/C status Condition of dispatch

FND Refer to item 46-31-01
VMS Refer to item 46-31-01
NAVD Refer to item 46-31-01
Check parameters failure on:
DMAP Refer to item 46-85
HTAWS Refer to item 34-75
EFB Refer to item 46-20

MFD# CPU1 MINOR DEG MFD#

H/C status Condition of dispatch

FND Refer to item 46-31-01
Check page format
VMS Refer to item 46-31-01
degradations:
NAVD Refer to item 46-31-01

MFD# CPU2 MAJOR DEG MFD#

H/C status Condition of dispatch

DMAP Refer to item 46-85
Check parameters failure on: HTAWS Refer to item 34-75
EFB Refer to item 46-20

MFD# CPU2 MINOR DEG MFD#

H/C status Condition of dispatch

DMAP Refer to item 46-85
Check parameters failure on:
HTAWS Refer to item 34-75
Mission functions degraded
EFB Refer to item 46-20

AMC1 CHAN A REDUND AMC2

H/C status Condition of dispatch

Failure of one redundant I/O component of the
No dispatch
corresponding AMC # channel A.

AMC1 CHAN B REDUND AMC2

H/C status Condition of dispatch

Failure of one redundant I/O component of the
No dispatch
corresponding AMC # channel B.

APPROVED EC 175 B 00.10.00

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ATT1 FAIL ATT2

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Refer to item 34-26-01
Failure of AHRS 1 and/or AHRS 2

ATT1 REDUNDANCY

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Failure of one link out of two between No dispatch
IMU 1/AHRS 1 and AMCs

REDUNDANCY ATT2

H/C status Condition of dispatch

Check VMS-RCNF subpage:
Failure of one link out of
No dispatch
two between
IMU 2/AHRS 2 and AMCs

AVIONIC BAY SNSR

H/C status Condition of dispatch

Nose Avionic Bay temperature sensor Refer to item 21-61-00 and

failure. items 21-00-01, 21-20-01.

HOOK FAIL

H/C status Condition of dispatch

Hook system failure

The cargo hook is detected opened. No dispatch

5.3.2 MESSAGES ISOLATED BY MANUAL P-START TST

HYD TST FAIL

H/C status Condition of dispatch

Check on VMS-HYDR page:
No dispatch
The auxiliary hydraulic pressure is fault

APPROVED EC 175 B 00.10.00

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5.3.3 MESSAGES ISOLATED BY AUTOMATIC START-UP TST

HTG + DEMIST DEG

H/C status Condition of dispatch

Check on FND:

No dispatch
If appears even fleetingly:
The maintenance check confirms that the
bleed air valve is in closed position

HTG + DEMIST

H/C status Condition of dispatch

Check on FND:
The maintenance check confirms that the
bleed air valves are in closed position
No dispatch

If appears even fleetingly: bleed air

valve is considered failed

BLEED AIR LEAK

H/C status Condition of dispatch

Check on FND:

No dispatch
With or displayed even
fleetingly: bleed air valve is considered failed

APPROVED EC 175 B 00.10.00

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NR SENSOR

H/C status Condition of dispatch

Check display of ESTIMATED NR

No dispatch
Both sensors are unavailable.

The maintenance confirms that NR display is

coming from single sensor Refer to item 63-44
(NR1 or NR2).

HYD TST FAIL

H/C status Condition of dispatch

Check hydraulic pressure validity on

VMS-HYDR page:
Hydraulic pressure out of range No dispatch
(Hyd. pressure < 160 bar or
Hyd pressure > 190 bar.

APPROVED EC 175 B 00.10.00

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ELEC TST FAIL

H/C status Condition of dispatch

Check electrical parameter validity on VMS-

ELEC subpage and on the clearance test
subpage for:
DC EMERG FAIL and/or No dispatch
EMER GEN DISCONN
Emergency generator internal failure

Check electrical parameter validity on VMS-

ELEC subpage for:
Refer to item 24-20
ALT DISCONN
Degradation of AC generator parameters

Check on the clearance test subpage for :

No dispatch
FLIGHT SHED DISCON,

Check electrical parameter validity on VMS-

ELEC subpage and on the clearance test
subpage for:
No dispatch
DC BUS TIE FAIL and/or
ELEC1 BUS TIE FAIL ELEC2

FUEL TST FAIL

H/C status Condition of dispatch

Check Fuel 1, Fuel 2 low level on Low level display (10 min) is not available
VMS-FUEL subpage and Refer to item 28-43-02
Check on the clearance test subpage for :
FUEL : LOW LVL 1 or Fuel gauging display (20 min and 10 min) is
FUEL : LOW LVL 2 not available
Low level alarm is not available Refer to item 28-43-01 ((4), (5) or (6))

APPROVED EC 175 B 00.10.00

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5.3.4 MESSAGES ISOLATED BY MANUAL P-FLT TEST

AP1 TST FAIL AP2

H/C status Condition of dispatch

Check on VMS-SYST AFCS status for details:

No dispatch
AP1

Check on VMS-SYST AFCS status for details:

No dispatch
AP2

Check on VMS-SYST AFCS status for details:

Refer to item 22-32-01
Cyclic SEMA (Pitch, Roll, yaw)

Check on VMS-SYST AFCS status for details:

Refer to item 22-32-03
Collective SEMA

Check on VMS-SYST AFCS status for details:

Refer to items 22-31-03 and 22-31-04
Collective Force Trims release

Check on VMS-SYST AFCS status for details:

Refer to items 22-31-05 and 22-31-06
Cyclic Force Trims release

Check on VMS-SYST AFCS status for details:

No dispatch
Collective link ( COLL LINK in AFCS strip)

Check on VMS-SYST AFCS status for details:

Refer to item 22-31-01
Cyclic 4-way beep Trim

Check on VMS-SYST AFCS status for details:

Refer to item 22-31-02
Collective beep Trim

Check on VMS-SYST AFCS status for details:

No dispatch
Auto Trim (Pitch, Roll)

Check on VMS-SYST AFCS status for details:

No dispatch
Auto Trim (Yaw)

APPROVED EC 175 B 00.10.00

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AP1 TST FAIL AP2

H/C status Condition of dispatch

Check on VMS-SYST AFCS status for details:

No dispatch
Auto Trim (Collective)

Check on VMS-SYST AFCS status for details:

Refer to item 22-36-00
APCP

Check on VMS-SYST AFCS status for details:

Refer to item 22-14-02
AP UM OFF

Check on VMS-SYST AFCS status for details:

ARINC link between AP No dispatch
( in AFCS strip)

(Step2+ and later):

AFCS test result of Channel A/B not compliant No dispatch
with AFCS test of channel B/A.

AP1 TST ABORTED AP2

H/C status Condition of dispatch

AFCS pre-flight tests interrupted before being

completed.
Not related to a MEL
Check on VMS-SYST AFCS status for details or
restart a test if necessary.

(Single configuration)
------- RA FAIL ------ (Step2) or -------RA TST FAIL------ (Step2+ or later)
or
(Dual configuration)
-RA1 FAIL ------ or ------- FAIL RA2- (Step2+ or later)

H/C status Condition of dispatch

Radio Altimeter test is not passed:

Check on the clearance test subpage for: Refer to item 34-12-00 (single RA)
RA1 TST FAIL or RA2 TST FAIL or
Check RA status on VMS-SYST sub-page for Refer to item 34-12-01 (dual RA)
details

APPROVED EC 175 B 00.10.00

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AVIONIC TST FAIL

H/C status Condition of dispatch

On VMS-SYST, check the parameter validity:

Refer to item 34-55-01
VOR/ILS1

On VMS-SYST, check the parameter validity:

Refer to item 34-55-02
VOR/ILS2

On VMS-SYST, check the parameter validity:

Refer to item 34-52
ADF

On VMS-SYST, check the parameter validity:

Refer to item 34-53
DME

On VMS-SYST, check the parameter validity:

Refer to item 34-42-01
WXR

Refer to item 34-12-00

On VMS-SYST, check the parameter validity:
or
RA, RA1 or RA2
Refer to item 34-12-01

On VMS-SYST, check the parameter validity:

Refer to item 34-27
IESI

On VMS-SYST, check the parameter validity:

Refer to item 34-63
FMS1

On VMS-SYST, check the parameter validity:

Refer to item 34-63
FMS2

On VMS-SYST, check the parameter validity:

Refer to item 34-40-02
GPS1

Refer to item 34-40-01

On VMS-SYST, check the parameter validity:
or
GPS2
Refer to item 34-40-02

On VMS-SYST, check the parameter validity:

Refer to item 34-75
HTAWS

On VMS-SYST, check the parameter validity:

Refer to item 34-74
TCAS

APPROVED EC 175 B 00.10.00

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ATT REDUNDANCY

H/C status Condition of dispatch

Check VMS-RCNF subpage:

Refer to item 34-26-03
Failure of AHRS 3

IESI SIGNAL FAIL

H/C status Condition of dispatch

Check on VMS-RCNF subpage for

Investigation:
Not related to a MEL
Loss or degradation of IESI attitude, air
data performed by AMC

Check on VMS-RCNF subpage for

Investigation:
Not related to a MEL
Loss or degradation of backup SAS
monitoring performed by AMC

Check on VMS-RCNF subpage for

Investigation: Not related to a MEL
Loss of IESI air data function,

Check on VMS-RCNF subpage for

Investigation: Not related to a MEL
Loss of IESI attitude function

MFD XTALK

H/C status Condition of dispatch

Cross talk failure between the MFDs No dispatch

AMC1 CHAN A REDUND AMC2

H/C status Condition of dispatch

AFCS test result of Channel A not
No dispatch
compliant with AFCS test of channel B.

AMC1 CHAN B REDUND AMC2

H/C status Condition of dispatch

AFCS test result of Channel B not compliant
No dispatch
with AFCS test of channel A.

APPROVED EC 175 B 00.10.00

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5.4 MASTER LIST MESSAGE ENTRIES

5.4.1 TEST

PWR-UP TST PENDG

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

PWR-UP TST

H/C status Condition of dispatch

Power up test in progress Not related to a MEL

PWR-UP TST OK

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

PWR-UP TST ABORT

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

P-START TST

H/C status Condition of dispatch

Pre-start test in progress Not related to a MEL

P-START TST OK

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

START-UP TST

H/C status Condition of dispatch

Start-up test in progress Not related to a MEL

APPROVED EC 175 B 00.10.00

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START-UP TST OK

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

P-FLT TST

H/C status Condition of dispatch

Pre-flight test in progress Not related to a MEL

P-FLT TST OK

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

APPROVED EC 175 B 00.10.00

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5.4.2 AUDIO

AUDIO ALERT

H/C status Condition of dispatch

Failure of aural alerting function No dispatch

100 FT+LG MUTE

H/C status Condition of dispatch

Inhibition of the 100 ft crossing alert due to use

of the sling or hoist function (depending on the Not related to a MEL
mission selector position).

100 FT+LG+ACAS MUTE

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

100 FT+LG +TAWS MUTE (Step2 and step2+) or 100 FT+LG +HTAWS MUTE (Step3 or later)

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

TAWS+ACAS MUTE (Step2 and step2+) or HTAWS+ACAS MUTE (Step3 or later)

H/C status Condition of dispatch

Self-explanatory Not related to a MEL

APPROVED EC 175 B 00.10.00

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5.4.3 FDRS

FDRS

H/C status Condition of dispatch

Refer to § 5.3.1 PWR-UP TST

5.4.4 ENGINE

(Step2 and step2+ only): FADEC 1 REDUNDANCY

H/C status Condition of dispatch

Minor control degradation occurred

No dispatch
concerning FADEC 1

(Step2 and step2+ only): REDUNDANCY FADEC 2

H/C status Condition of dispatch

Minor control degradation occurred

No dispatch
concerning FADEC 2

(Step3 or later): ENG 1 LIMITED DISPATCH

H/C status Condition of dispatch

FADEC 1 redundancy that affect next flight Refer to item 72-02-01

(Step3 or later): LIMITED DISPATCH ENG 2

H/C status Condition of dispatch

FADEC 2 redundancy that affect next flight Refer to item 72-02-01

APPROVED EC 175 B 00.10.00

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(Step3 or later): ENG 1 FUEL PRE-CLOGGED

H/C status Condition of dispatch

A high fuel pressure is detected in engine 1. No dispatch

(Step3 or later): FUEL PRE-CLOGGED ENG 2

H/C status Condition of dispatch

A high fuel pressure is detected in engine 2. No dispatch

(Step3 or later): ENG 1 FUEL PRE-CLOGGED ENG 2

H/C status Condition of dispatch

A high fuel pressure is detected in both

No dispatch
engines.

(Step3 or later): ENG 1 USAGE EXPIRED

H/C status Condition of dispatch

Engine exceedance No dispatch

(Step3 or later): USAGE EXPIRED ENG2

H/C status Condition of dispatch

Engine exceedance No dispatch

TRAINING FAIL

H/C status Condition of dispatch

The maintenance confirms that the OEI training
mode is inoperative (induced by other FADEC
degradation)
No dispatch

Check display of on FLI area, or

---FADEC REDUNDANCY--- on Master List

APPROVED EC 175 B 00.10.00

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5.4.5 AIR CONDITIONING

ECS

H/C status Condition of dispatch

The maintenance confirms that internal air
Refer to item 21-90-03
temperature sensor(s) (IAT) are failed.

COCKPIT ECS

H/C status Condition of dispatch

The maintenance confirms that :
Refer to item 21-20-01
- Both cockpit fans are failed
The maintenance confirms that :
- Both air mixing temperature probes (AMT) are Refer to item 21-60 (1) second case
failed
The maintenance confirms that :
Refer to item 21-90-01
- Cockpit air actuator(s)) is/ are failed

COCKPIT FAN

H/C status Condition of dispatch

The maintenance confirms that One fan is
Refer to item 21-20-01
failed

CKPT HTG+DEMIST

H/C status Condition of dispatch

Loss of cockpit heating and demisting
Refer to item 21-40-01
confirmed by the maintenance

COCKPIT COOLING

H/C status Condition of dispatch

The maintenance confirms that cockpit cooling
Refer to item 21-50-01
is inoperative.

CABIN COOLING

H/C status Condition of dispatch

The maintenance confirms that cabin cooling
Refer to item 21-50-02
is inoperative

APPROVED EC 175 B 00.10.00

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CABIN FAN

H/C status Condition of dispatch

The maintenance confirms that One fan is

Refer to item 21-20-02
failed

CABIN ECS

H/C status Condition of dispatch

The maintenance confirms that Both fans are

Refer to item 21-20-02
failed

The maintenance confirms that air mixing

Refer to item 21-60 (2)
temperature probe(s) is/are failed

The maintenance confirms that cabin air

Refer to item 21-90-02
actuator (s) is/are failed

CAB HEATING

H/C status Condition of dispatch

Loss of cabin heating confirmed by the

Refer to item 21-40-02
maintenance (Heating Modulating Valve)

AVIONIC BAY SNSR

H/C status Condition of dispatch

Refer to item 21-61-00 and

Nose Avionic Bay temperature sensor failure.
items 21-00-01, 21-20-01.

5.4.6 PITOT

PITOT1 HEATER FAIL

H/C status Condition of dispatch

The maintenance confirms that the LH Pitot 1
Refer to item 30-31
probe HEATING is inoperative

HEATER FAIL PITOT2

H/C status Condition of dispatch

The maintenance confirms that the RH Pitot 2
Refer to item 30-31
probe HEATING is inoperative

APPROVED EC 175 B 00.10.00

19-07 Page 40
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5.4.7 IESI

IESI PITOT HTR

H/C status Condition of dispatch

The maintenance confirms that the IESI Pitot
Refer to item 30-31
probe HEATING is inoperative

5.4.8 DE-ICING

WSHLD1 HEATER FAIL-- ---------

------- ---- -HEATER FAIL WSHLD2

WSHLD1 HEATER FAIL WSHLD2

H/C status Condition of dispatch

The maintenance confirms that the LH or RH
(or both) Windshield Heating System is Refer to item 30-45
inoperative

5.4.9 SURVEILLANCE

TAWS FAIL (Step2 and step2+) or HTAWS FAIL (Step3 or later)

H/C status Condition of dispatch

Check on FND:

Refer to item 34-75

HTAWS is inoperative

TAWS DEGRADED (Step2 and step2+) or HTAWS DEGRADED (Step3 or later)

H/C status Condition of dispatch

Check on MFD:

Refer to item 34-75

HTAWS is partially inoperative

APPROVED EC 175 B 00.10.00

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DATABASE EXPIRED

H/C status Condition of dispatch

The DATA BASE (for HTAWS, SVS and DMAP)

are outdated
NOTE Not related to a MEL
Corresponding mission system is operative
but data are not reliable

5.4.10 FLOATATION
• Only if MOD 99A05677-00 (Ref EFU update) is installed:

FLOAT NOT ARMED

H/C status Condition of dispatch

The maintenance confirms that the auto arming
Refer to item 25-40-01
function is inoperative

FLOAT TEST FAIL

H/C status Condition of dispatch

The maintenance confirms that the electrical
Refer to item 25-40-02
system for the EFS is inoperative

FLOAT WATER SNSR

H/C status Condition of dispatch

The maintenance confirms that the water
Refer to item 25-40-05
immersion sensor(s) (WIS) is / are inoperative

5.4.11 LANDING GEAR

LG EMRG OVHT HYD2

H/C status Condition of dispatch

The maintenance confirms that the L/G
emergency extension pump temperature Refer to item 29-30-01
sensor is inoperative

APPROVED EC 175 B 00.10.00

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5.4.12 AUTO PILOT

AP ACTUATOR

H/C status Condition of dispatch

Check On AFCS SYST page:
Refer to item 22-32-01
Cyclic SEMA (Pitch, Roll, Yaw)

Check On AFCS SYST page:

Refer to item 22-32-03
Collective SEMA

5.4.13 DUAL RADIO-ALTIMETERS

RA1 FAIL--- ------ or FAIL----RA2-

H/C status Condition of dispatch

One Radio Altimeter is failed:

Refer to item 34-12-01
Check status on RCNF and SYST pages.

APPROVED EC 175 B 00.10.00

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OTHER ADVISORIES ROSE

Displayed on FND
H/C status Condition of dispatch

ACAS is inoperative Refer to item 34-74

ACTUATOR FAILED Displayed on VMS-MAIN page (DATA area)

H/C status Condition of dispatch

The maintenance confirms that

Refer to item 63-29
Clutch/ declutch actuators is inoperative

DATA CARD

H/C status Condition of dispatch

DTD data card is not accessible (No flight data
Not related to MEL
will be downloaded).

DATA CARD FULL

H/C status Condition of dispatch

UMS downloading means inoperable (Data card
Not related to MEL
almost full).

DOWNLOAD FAIL

H/C status Condition of dispatch

UMS data has not been downloaded (software
error or data card issue). Not related to MEL
(UMS memory full).

ATC# CONTROL LOSS on FMS

H/C status Condition of dispatch

FMS displays a transponder failure Refer to item 34-51

APPROVED EC 175 B 00.10.00

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NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25. EQUIPMENT -
FURNISHINGS

25-11-01 Flight crew seats C 2 1 (M) One (LH) may be inoperative or removed
provided:

(a) The horizontal adjustment locking device of

the seat is operational,
(b) The flight is limited to single pilot operation
in VFR with right seat operational,
(c) The affected seat must be blocked and
placarded "DO NOT OCCUPY" to prevent
occupancy,

Maintenance procedure:
- Inoperative seat must be secured,
- Unsecured seat must be removed.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
A seat with an inoperative locking system
(at least one of the two longitudinal or one
of the two vertical locking pin is lost) or
inoperative or missing seat belt or harness,
is considered inoperative.

APPROVED EC 175 B 25.00.00

19-07 Page 1
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NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-11-02 Crew seat components

- For each seat:

(1) Bucket dynamic tilt D 1 0 (M) May be inoperative provided the

associated seat is secured or locked in a
position acceptable to the flight crew member.

Maintenance procedure:
Installation must be secured.
(Refer to AMM, WC 05-52-00, 6-23)

(2) Armrests D 2 0 (M) One or both may be inoperative provided

that:
(a) The inoperative armrest is inspected
(b) The armrest is stowed (locked in up
position).

Maintenance procedure:
Inspection of the inoperative armrest, not to
hinder an emergency evacuation or any other
flight duties.
(Refer to AMM, WC 05-52-00, 6-23)
or
D 2 0 (M) One or both may be inoperative provided
the inoperative armrest is removed.

Maintenance procedure:
Remove the armrest.
(Refer to AMM, WC 05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

19-07 Page 2
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NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-11-02 Crew seat components

(Cont'd)

- For each seat:

(3) Headrest C 1 0 (M) May be inoperative provided that the

inoperative headrest is inspected.

Maintenance procedure:
Inspection of the inoperative headrest, not to
interfere with seat operation.
(Refer to AMM, WC 05-52-00, 6-23)
or
C 1 0 (M) May be missing or removed.

Maintenance procedure:
Remove the headrest.
(Refer to AMM, WC 05-52-00, 6-23)

(4) Lumbar support D 1 0 May be inoperative provided the system of the

associated seat is locked in a position
acceptable to the flight crew member.

25.20 Hand Fire Extinguishers B 2 1 Refer to ATA 26-24.

APPROVED EC 175 B 25.00.00

19-07 Page 3
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-21-01 Passenger Seats C - - (M) One or more may be inoperative provided

(except for VIP configuration) the inoperative seat:
(a) Does not block an emergency exit,
(b) Does not restrict any passenger from
accessing any emergency exit,
(c) Is secured and placarded “DO NOT
OCCUPY”.

Maintenance procedure:
In case of inoperative locking device, the seat
must be removed from the aircraft.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
- A seat with an inoperative or missing seat
belt or harness is considered inoperative.
- Seat with two broken quick releases (not
possible to lock the seat) shall be
removed from the aircraft.
- Seat removal shall be performed in
accordance with certified configurations
(refer to Flight Manual section 6).

or
C - - (M) One or more may be inoperative provided:
(a) the inoperative seat is removed,
(b) At least one row of three seats remains
installed on row 2, 3, 4 or 5.

Maintenance procedure:
Remove the seat.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Seat removal shall be performed in
accordance with certified configurations
(refer to Flight Manual section 6).

APPROVED EC 175 B 25.00.00

19-07 Page 4
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-21-02 Passenger seat

components:
(1) Headrest D 1 0 (M) May be inoperative provided that the
inoperative headrest is inspected.

Maintenance procedure:
Inspection of the inoperative headrest, not to
interfere with seat operation.
(Refer to AMM, WC 05-52-00, 6-23)
or
D 1 0 (M) May be missing or removed for forward
facing seats only.

Maintenance procedure:
Remove the headrest.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Aft facing installed seats require headrest
to be installed and operational.

APPROVED EC 175 B 25.00.00

19-07 Page 5
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-22-00 Attendant seats C - 0 (M) One may be inoperative provided that:

(a) At least three fitting bolts are properly
installed to keep the seat in place,
(b) The affected seat is blocked and
harnesses fastened and placarded
"DO NOT OCCUPY" to prevent
occupancy.

Maintenance procedure:
If the secure cannot be assured, inoperative
seat must be removed.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
A seat with at least one of the 4 fitting
bolts damaged or lost, or with
inoperative or missing seat belt or
harness, is considered inoperative.

25-22-01 Attendant seat

components:
(1) Seat pan folding D 1 0 Seat pan folding system may be inoperative.
system: per
seat

25-22-02 Attendant seat

components:
(2) Headrest: C 1 0 (M) May be inoperative provided that
per headrest is removed from the seat.
seat
Maintenance procedure:
Remove sharp edges and/or possible
headrest hindrance.
Ensure that the headrest do not hurt anyone
in case of hard landing.
(Refer to AMM, WC 05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

19-07 Page 6
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-22-03 Attendant seat

components:
(3) Stowage door

(a) Flight over water C 1 0 (M) the stowage door may be inoperative for
per flight over water provided that:
seat (a) The door is maintained blocked and
closed,
(b) The lifejacket is removed from the seat
and stowed in a place accessible from
the seating occupant,
or
C 1 0 (M) The stowage door may be inoperative for
per flight over water provided that the affected
seat seat is blocked and harnesses fastened and
placarded "DO NOT OCCUPY" to prevent
occupancy.

Maintenance procedure (both cases):

Inoperative door must be correctly closed
and secured.
Unsecured seat must be removed only if
door is not secured.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Adhesive tape may be acceptable means
of closure in case of door locking failure.

APPROVED EC 175 B 25.00.00

19-07 Page 7
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-22-03 Attendant seat

components:
(3) Stowage door

(b) Flight over land C 1 0 (M) The stowage door may be inoperative for
per flight over land provided that:
seat - the door is maintained blocked and closed
position,
or
C 1 0 (M) The stowage door may be inoperative for
per flight over land provided that:
seat - The affected seat is blocked and harnesses
fastened and placarded "DO NOT OCCUPY"
to prevent occupancy.

Maintenance procedure (both cases):

Inoperative door must be correctly closed
and secured.
Unsecured seat must be removed only if
door is not secured.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Adhesive tape may be acceptable means
of closure in case of door locking failure.

APPROVED EC 175 B 25.00.00

19-07 Page 8
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-22-04 Swivel Operator seats C - 0 (M) One or more may be inoperative

provided that:
(a) Mission does not required its use,
(b) Inoperative seat does not block an
emergency exit,
(c) Inoperative seat does not restrict any
passenger from accessing any
emergency access,
(d) Inoperative seat is blocked and placarded
“DO NOT OCCUPY”.

Maintenance procedure:
In case of inoperative locking device, the
seat must be removed from the aircraft.
Seat removal shall be performed in
accordance with certified configurations.
Seat with 2 quick releases broken/not
possible to lock the seat, shall be removed
from the aircraft.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
A seat with an inoperative or missing
seat belt or harness is considered
inoperative.

25-22-05 Swivel Operator seat

components:
(1) Headrest: D 1 0 (M) One or more may be inoperative
per provided that:
seat (a) The inoperative headrest is removed
from the seat,
(b) The aft facing seat with the inoperative
headrest is not occupied during take-off
and landing phases.

Maintenance procedure:
Remove the headrest if necessary.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
FWD facing without headrest may be
occupied for all flight phases.

APPROVED EC 175 B 25.00.00

19-07 Page 9
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NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-22-06 Swivel Operator seat

components:

(1) Longitudinal
adjustment system: C 2 1 (M) One plunger may be inoperative
per provided that the inoperative seat is blocked
seat using remaining plunger (harnesses
fastened) and placarded
“DO NOT OCCUPY”.

Maintenance procedure:
Inoperative seat must be blocked and
placarded “DO NOT OCCUPY”.

(2) Longitudinal
adjustment system: C 2 0 (M) Both plungers may be inoperative
per provided that the seat is locked (whatever in
seat rear or aft position).
or
C 2 0 (M) Both plungers may be inoperative (not
per locked) provided that the seat is removed
seat from the aircraft.

Maintenance procedure:
If 2 plungers are locking, the seat must be
secured or removed.
If no plunger is locking, the seat must be
removed.
(Refer to AMM, WC 05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

19-07 Page 10
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-23-01 Windows mounting D 8 0 One or more may be inoperative provided

points for video camera that flight mission procedures do not require
(If installed) its use,
or
D 8 0 One or more per window (RH or LH) may be
inoperative provided that rings are without
load.

25-23-02 Doors mounting points D 8 0 One or more may be inoperative provided

for video camera that flight mission procedures do not require
(If installed) its use,
or
D 8 0 One or more per door (RH or LH) may be
inoperative provided that rings are without
load.

APPROVED EC 175 B 25.00.00

19-07 Page 11
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(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25.28.00 Foldable footstep D 2 0 (M) One or both may be inoperative provided
installation that operations are conducted with footsteps
(If installed) closed and locked.

Maintenance procedure:
Deactivate and secure the footstep.
(Refer to AMM, WC05-52-00, 6-23)

25-40-01 Emergency Flotation D 1 0 May be inoperative provided:

System (if installed): (a) The manual arming is operative and used,
- Auto arming function (b) The AUTO position is not used,
(Post MOD 99A05677-00 only) (c) The pilot manages the armament of the
- Consequence: system using MAN position according to
FLOAT NOT ARMED FLM SUP.14 procedures and limitations.
on Master list
when testing AUTO mode

25-40-02 Emergency Flotation D 1 0 (M) The Emergency Floatation Electrical

System (if installed): System may be inoperative provided that:
- Electrical system (a) The EFS is not required by operational
- Consequence: regulations,
FLOAT TEST FAIL (b) The 4 emergency floatation electrical
on Master list connectors are disconnected.
NOTE
The EFS is not operational.

Maintenance procedure:
The 4 emergency floatation electrical
connectors are disconnected from the gas
cylinders and connected to their dummy
receptacle.
(Refer to AMM, WC 05-52-00, 6-23)

or
C 1 0 The Emergency Floatation Electrical System
may be inoperative provided that:
(a) The EFS is not required by operational
regulations,
(b) H/C airspeed is limited below EFS VNE.

NOTE
The EFS is not operational.

APPROVED EC 175 B 25.00.00

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(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-40-03 Emergency Flotation D 4 0 (O) The EFS Gas cylinder charge may be
System (if installed): below the required level provided the EFS is
- Gas cylinder charge not required and not used.

Operational procedure:
EFS armament panel is in OFF position.

NOTE
The EFS is not operational.

25-40-04 Emergency Flotation

System (if installed):
- Inflation pushbutton
(on collective pitch levers)

1) Single pilot operation C 2 1 (O) The copilot float inflation pushbutton may
be inoperative provided that the pilot float
inflation pushbutton is verified operative before
each flight.

Operational procedure:
Before each flight, select “OFF” position on the
control panel and push the operative inflation
pushbutton:
- FLOAT INFLATION - caution message is
displayed on Master list. The caution message
disappears when the inflation pushbutton is
released.

APPROVED EC 175 B 25.00.00

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NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-40-04 Emergency Flotation

System (if installed):
- Inflation pushbutton
(on collective pitch levers)

2) Dual pilot operation C 2 1 (O) One float inflation pushbutton (on

collective pitch levers) may be inoperative
provided that the remaining float inflation
pushbutton is verified operative before each
flight.

Operational procedure:
Before each flight, select “OFF” position on the
control panel and push the operative inflation
pushbutton:
- FLOAT INFLATION - caution message is
displayed on Master list. The caution message
disappears when the inflation pushbutton is
released.

25-40-05 Emergency Flotation C 2 0 One or both WIS may be inoperative provided

System (if installed): the collective pushbutton of the pilot at the
- Water Immersion controls is operative.
Sensors (WIS)
- Consequence: NOTE
FLOAT WATER SNSR The inflation of the EFS floats is ordered
on Master list manually by the crew (nominal mode).

25-51-00 Cargo partition net Cargo partition net and device may be
(if installed) inoperative or missing provided that:
D 1 0 - There is no load in the cargo,
or
D 1 0 - The cabin/cargo bulkhead is installed in
addition to the net,
or
D 1 0 - The optional EMS storage system
(item 25-53-00) is used in accordance with
the system load limitations (refer to the
dedicated placards in cargo).

APPROVED EC 175 B 25.00.00

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(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25.52.12 Cargo compartment D - 0 One (or both if installed) may be inoperative

ladder provided that:
(a) The Cargo ladder is not required by
operational regulations
(b) The inoperative Cargo ladder is removed
from the cargo door.

25-53-00 EMS storage system D 1 0 EMS storage system may be inoperative

(if installed) provided that system is not used.

25-62 First Aid Kit D - 1 If required by operational regulations, any in

(if installed) excess of one may be incomplete or missing.

25-63 Emergency Locator D - 0 May be inoperative provided regulations do

Transmitter (ELT) not require its use.
(if installed)

25-64 Automatically Deployable D - 0 May be inoperative provided regulations do

Emergency Locator not require its use.
Transmitter (ADELT)
(If installed)

25.65.00 Safety Cards Holder D 2 0 (O) One or both may be inoperative provided
(If installed) that operational regulations do not require its
use.

Operational procedure:
Check the cards are stowed in another place
accessible to the passengers.

APPROVED EC 175 B 25.00.00

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(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-65-01 Survival Equipment D - - Any in excess of those required may be

(if installed) missing or inoperative.

25-68 Life-Rafts Installation D - - May be inoperative or missing provided that

(if installed, when extended overwater flights are not conducted.
required)

APPROVED EC 175 B 25.00.00

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(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96 Dual Hoist system

(if installed)

25-96-01 Dual Hoists:

(1) Hoists (front/rear hoist) D 2 0 (M) Both hoists may be inoperative (*)
provided that:
(a) Flight mission procedures do not require
the use of hoists,
(b) Both hoists are uninstalled from the beam.

NOTE
(*) The term inoperative is defined as loss
or malfunction of hoist functionality such
as impossibility to reeling in or out the
cable or, erroneous action of the hoist.

Maintenance procedure:
Uninstall both hoists from the beam
(Refer to AMM, WC 05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

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(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96-01 Dual Hoists (cont'd):

(2) Dual Hoists (front/rear hoist) D 2 1 (M) One hoist may be inoperative (*) provided
that:
(a) Hoist mission procedures do not require
two hoists,
(b) Inoperative hoist is uninstalled from the
beam,
(c) Operative hoist shall be in front position,
(d) Hoist selector is set to front hoist position.

NOTE
(*) The term inoperative is defined as loss
or malfunction of hoist functionality such
as impossibility to reeling in or out the
cable or, erroneous action of the hoist.

Maintenance procedure:
• Uninstall the inoperative hoist.
(Refer to AMM, WC 05-52-00, 6-23)

If front hoist failure, then

• Move the rear hoist to front position.
(Refer to AMM, WC 05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

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ITEM (5) REMARKS OR EXCEPTIONS

25-96-02 Dual Hoist system

controls

(1) Hoistman front or rear D 2 1 - (M) One cabin control pendant may be
control pendant inoperative (*) for hoist mission provided that:
(a) Flight mission procedures require only one
hoist,
(b) The rear hoist is uninstalled from the beam,
(c) The inoperative control pendant is removed
from the cabin,
(d) The operative pendant is installed on the
front hoist,
(e) Hoist selector is set to the front hoist.

NOTE
(*) The term “inoperative”, for the control
pendants, is defined as loss or malfunction
of pendants functionality such as
unavailability or erroneous operation.

Maintenance procedure:
- Remove the rear hoist,
- Remove the inoperative pendant,
- Plug the operative pendant to the front hoist.
(Refer to AMM, WC 05-52-00, 6-23)

OR
(See next page)

APPROVED EC 175 B 25.00.00

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ITEM (5) REMARKS OR EXCEPTIONS

25-96-02 Dual Hoist system

controls OR

(1) Hoistman front or rear D 2 1 - (M) One cabin control pendant may be
control pendant inoperative (*) provided that:
(Cont'd) (a) Flight mission procedures do not require
the use of hoists,
(b) Hoist system is deactivated and secured,
(c) Mission selector is not set to HOIST
position.

NOTE
(*) The term “inoperative”, for the control
pendants, is defined as loss or malfunction
of pendants functionality such as
unavailability or erroneous operation.

Maintenance procedure:
- Deactivate the hoist system by pulling the
following hoist breakers on FBP1 & 2:
- FBP1 : B UP HOIST
- FBP1 : HOIST SHEAR
- FBP2 : PR HOIST
- FBP2 : HOIST SHEAR
- With mission selector and hoist selector in
the position which evidenced the failure,
check that the hoist is not reel-in/reel-out
and commands on grip control cannot reel
in/out the front and rear hoists.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Hoist mission is not possible.

APPROVED EC 175 B 25.00.00

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(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96-02 Dual Hoist system

controls

(2) Pilot and/or copilot single D 2 0 (M) One or both single speed control(s) on
speed collective grip collective grip may be inoperative (*) provided
controls that :
(a) Flight mission procedures do not require
the use of hoists,
(b) Hoist system is deactivated and secured,
(c) Mission selector is not set to HOIST
position.

NOTE
(*) The term inoperative is defined as
erroneous reel in or reel out command or
unavailability of the reel-in or reel-out
function of the hoist cable.

Maintenance procedure:
- Deactivate the hoist system by pulling the
following hoist breakers on FBP1 & 2:
- FBP1 : B UP HOIST
- FBP1 : HOIST SHEAR
- FBP2 : PR HOIST
- FBP2 : HOIST SHEAR
- With mission selector and hoist selector in
the position which evidenced the failure,
check that the hoist is not reel-in/reel-out
and commands on cabin control pendants
cannot reel in/out the front and rear hoists.
(Refer to AMM, WC 05-52-00, 6-23)

NOTE
Hoist mission is not possible.

APPROVED EC 175 B 25.00.00

19-07 Page 21
 MASTER MINIMUM EQUIPMENT LIST

(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96-03 Hoist authorization

advisory lights
(Control panel /door
frame)

(1) Control panel light D 2 1 (O) One cabin hoist authorization advisory
or door frame light light may be inoperative.

Operational procedure:
Give the directives by a briefing before the
flight to inform the crew that one advisory light
is inoperative.

(2) Control panel and door D 2 0 - Both hoist authorization advisory lights may
frame lights be inoperative (*) provided that flight mission
procedures do not require the use of hoist
system.
or
D 2 0 - (O) Both hoist authorization advisory lights
may be inoperative (*) for hoist mission
provided that the intercommunication system
between hoist operator and the crew is
operative.

NOTE
(*) The term inoperative means that the
light does not light on (or blink) in case of
hoist mission selected.

Operational procedure:
Give the directives by a briefing before the
flight to inform the crew that advisory lights are
inoperative.

APPROVED EC 175 B 25.00.00

19-07 Page 22
 MASTER MINIMUM EQUIPMENT LIST

(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96-04 Quick Release systems

(1) Electrical Cable D 3 0 One, two or all may be inoperative (*) provided
Quick Release that:
systems (a) Flight mission procedures do not require
(Cabin Control panel, the use of hoist system,
Pilot and Copilot (b) Mission selector is not set to HOIST
collective grip position.
commands) NOTE
(*)the term “inoperative”, for Electrical
Cable Quick Release System, is defined as
unavailability of release command.

(2) Manual cable cutter D 1 0 Manual cable cutter may be inoperative (*)
provided that:
(a) Flight mission procedures do not require
the use of hoist system,
(b) Mission selector is not set to HOIST
position.
NOTE 1
(*) the term “inoperative”, for Manual Cable
Cutter, is defined as not possible to cut or
unavailable.
NOTE 2
Hoist mission is not possible.

APPROVED EC 175 B 25.00.00

19-07 Page 23
 MASTER MINIMUM EQUIPMENT LIST

(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25-96-05 Hoistman ceiling D 4 0 All hoist man ceiling attaching points may be
attachment points inoperative provided that:
(a) Flight mission procedures do not require
the use of hoists,
(b) Mission selector is not set to HOIST
position.
NOTE
Hoist mission is not possible.

D 4 1 (O) Any in excess of one attachment point

may be inoperative for hoist mission if the
number of operative ceiling attaching points is
at least equal to the number of persons
needed for the hoisting mission.

Operational procedure:
Hoistman has to adjust its lanyard or its
hoisting position according to the hoistman
ceiling attaching point used for the mission.

25-97 Single Hoist system

(if installed) D 1 0 (M) May be inoperative provided that:
(a) Flight mission procedures do not require its
use,
(b) Mission selector is not set to HOIST
position,

Maintenance procedure:
Ensure that there is no dormant failure on
rescue hoist system through check before first
flight of the day.
(Refer to AMM, WC 05-52-00, 6-23)

(1) Wireless Intercom

System D 1 0 May be inoperative provided flight mission
procedures do not require its use.

APPROVED EC 175 B 25.00.00

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 MASTER MINIMUM EQUIPMENT LIST

(1) SYSTEM AND SEQUENCE (2) RECTIFICATION INTERVAL

NUMBERS
(3) NUMBER INSTALLED

(4) NUMBER REQUIRED FOR DISPATCH

ITEM (5) REMARKS OR EXCEPTIONS

25.98.00 Sling installation D 1 0 May be inoperative provided that:

(If installed) (a) Flight mission procedures do not require
its use,
(b) Mission selector is not set to SLING
position,
(c) Storage system remains operative.

NOTE
If the storage system is not operative,
the removal parts of the sling
installation must be removed.
(Refer to AMM, WC05-52-00, 6-23)

25.98.01 Sling installation

(If installed)
Sling Measurement Unit D 1 0 (M) May be inoperative provided that the Sling
Measurement Unit is deactivated.
NOTE
The pilot has to know the load
weight and the compatibility of this
weight with the helicopter.

Maintenance procedure:
System is deactivated by pulling out the
associated breaker (RBP1/7PP).
(Refer to AMM, WC05-52-00, 6-23)

APPROVED EC 175 B 25.00.00

19-07 Page 25