Airbus EC120 MSM 120 - MSM-05 - E - MC02 - A4 - VOL01-1 - Low
Airbus EC120 MSM 120 - MSM-05 - E - MC02 - A4 - VOL01-1 - Low
Airbus EC120 MSM 120 - MSM-05 - E - MC02 - A4 - VOL01-1 - Low
Chapter 05
MASTER SERVICING MANUAL (MSM)
Airbus Helicopters
Direction Technique Support
Aroport International Marseille Provence 13725 Marignane Cedex FRANCE
Contact: contact.msm.ah@airbus.com
Issue date
2014.05.15
Revision 002
2016.04.28
MSM
RECORD OF REVISIONS
MSM
LOEDU
1 Update
Refer to the "Update" Document Unit
D.U.
Type Date
D.U.
Type Date
TITLE
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05-11-00
2016.04.28
05-20-00
R
-
2016.04.28
LOEDU
TABLE OF CONTENTS
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05-20-02
2014.05.15
HIGHLIGHTS OF THE
REVISION
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05-21-00
2016.04.28
05-21-01
R
-
TECHNICAL
PUBLICATIONS
2014.05.15
05-21-02
2016.04.28
GLOSSARY
2014.05.15
05-22-00
2016.04.28
STRUCTURE OF THE
MSM
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05-22-01
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05-22-02
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2015.04.09
05-23-00
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05-23-02
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-
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R
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BREAKDOWN OF THE
MSM
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05-25-00
SB INCORPORATED
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05-26-00
05-10-00
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05-24-02
2014.05.15
2015.04.09
2014.05.15
2015.04.09
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LOEDU
Page 1
MSM
TABLE OF CONTENTS
TITLE
HIGHLIGHTS OF THE REVISION
1 GENERAL
2 OUTLINE OF THE REVISION
3 DETAILED DESCRIPTION
TECHNICAL PUBLICATIONS
1 THE DOCUMENTATION
2 OPERATING DOCUMENTS
3 MAINTENANCE DOCUMENTS
4 IDENTIFICATION DOCUMENTS
5 SPECIAL DOCUMENTS
6 VENDOR'S DOCUMENTS
GLOSSARY
STRUCTURE OF THE MSM
1 GENERAL STRUCTURE OF THE MSM
2 BREAKDOWN OF THE MSM
2.1 Identification of the DUs
2.2 Task codes
2.3 List Of Effective Document Units (LOEDU)
3 CLASSIFICATION OF INFORMATION
UPDATE OF THE MSM
1 REVISION OF THE MSM
2 UPDATE OF THE MSM
2.1 Update procedure
2.2 Identification of the modifications
3 CUSTOMER COMPLEMENT (CC): ISSUED ON A GREEN BACKGROUND
4 EFFECTIVITY
BREAKDOWN OF THE MSM
1 PURPOSE OF THE MSM
2 CHANGES TO THE MSM
3 HELICOPTER MAINTENANCE
4 TYPES OF MAINTENANCE
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TITLE
5 DEFINITION OF THE MAINTENANCE MODES
5.1 Hard time maintenance
5.2 On-Condition maintenance
5.3 Condition monitoring maintenance
6 EFFECTIVITY - RESPONSIBILITY
7 MAINTENANCE INTERVAL
7.1 Daily checks
7.1.1 15 FH // 7 D inspection
7.1.2 Inspection of optional installations
7.1.3 Cold weather and very cold weather routine check
7.2 Scheduled operations
8 MAINTENANCE RELATED TO EQUIPMENT MANUFACTURER DOCUMENTATION
USE OF THE MSM
1 ADAPTATION OF THE MSM
2 INFORMATION FEEDBACK FROM THE OPERATOR TO THE MANUFACTURER
3 IN-SERVICE MONITORING
3.1 Airframe monitoring
3.2 Monitoring of components
4 COMPONENT PART NUMBERS
4.1 Definition
4.2 Part number with a different letter
4.3 Applicability of the limits
4.4 Changes to Part Numbers
5 LIMITS
5.1 Flight Hours
5.2 Calendar time
5.2.1 Airframe initial aging date
5.2.2 Initial aging date for components
5.3 Cycles
5.4 Provisional limitations
5.5 Periodic and Perform Once limits
5.6 Performance interval
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TITLE
5.7 Specific and severe atmospheric operating conditions
5.8 Maximum limit value
5.8.1 Definition of the margin
5.8.2 Application of the margin
5.8.3 Specification of the margin
5.8.4 Example of how the margin is used
6 HELICOPTER-SERIALIZATION OF THE COMPONENTS
6.1 Principle
6.2 Identification marking
7 TRANSFER OF A COMPONENT (PART OR ASSEMBLY) FROM ONE HELICOPTER TO ANOTHER
HELICOPTER
8 RECORDING
9 SCHEDULED MAINTENANCE CHECKS MAINTENANCE OPERATIONS
9.1 Particular inspection cases
9.2 Rules of procedure
10 MAINTENANCE CODES (MC)
11 CONTENT OF A TASK
SB INCORPORATED
End of the Document Unit
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TABLE OF CONTENTS
Page 3
MSM
GENERAL
-
Check that the content of the sections is in accordance with the List Of Effective Document Units
(LOEDU).
Return the acknowledgment card.
DETAILED DESCRIPTION
D.U. STRUCTURE OF THE MSM updated
SB 53A015R1 integrated.
25/21/00/000/000/010, Pilot and copilot harnesses, 100 FH // 12M : Work card modified.
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MSM
TECHNICAL PUBLICATIONS
1
THE DOCUMENTATION
The technical documentation intended for operators is mainly broken down into five groups:
OPERATING DOCUMENTS
-
MAINTENANCE DOCUMENTS
-
The Illustrated Parts Catalog (IPC) contains all the spare parts necessary to ensure continued
serviceability of the helicopter.
SPECIAL DOCUMENTS
-
The Aircraft Maintenance Manual (AMM) specifies the maintenance procedures necessary to service
the helicopter.
The System Description Section (SDS) comprises part 1 of the AMM and explains how the systems
operate.
The Wiring Diagram Manual (WDM) combines all the helicopter wiring diagrams.
IDENTIFICATION DOCUMENTS
-
The Master Servicing Manual (MSM) is intended particularly for those responsible for helicopter
maintenance. It specifies the maintenance limits.
The Airworthiness Limitations Section (ALS) is intended for those responsible for helicopter
maintenance. It defines the mandatory limits and checks.
The FLight Manual (FLM) is intended for flight crews. It specifies the limits, standard and emergency
procedures and helicopter performance data.
The Master Minimum Equipment List (MMEL) specifies the minimum list of equipment necessary for
flight.
Service Bulletins (SB), Alert Service Bulletins (ASB) and Emergency Alert Service Bulletins
(EASB) are intended to inform the operators of instructions introduced following new events (incidents,
modifications, etc.). These documents supplement the helicopter documents and are incorporated
in the latter by updates if necessary.
Information Notices (IN) and Safety Information Notices (SIN) are documents issued for information.
Their purpose is to remind operators of existing maintenance procedures, or to inform them of changes
validated by Airbus Helicopters and undergoing introduction.
VENDORS DOCUMENTS
-
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This documentation comprises the following vendors manuals: Vendors Service Bulletins (SBV),
Engine Maintenance Manual (EMM) and Component Maintenance Manual (CMM).
TECHNICAL PUBLICATIONS
Page 1
MSM
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Page 2
MSM
GLOSSARY
(-):
Not indicated
&:
//:
:
And
Or
Paragraph
ALF:
ALS:
AMM:
ASB:
BFF:
CLN:
CLeaNing
CM:
Condition Monitoring
CMM:
D:
Day
DI:
Detailed Inspection
DRN:
DRaiNing
DS:
DU:
EASA:
DiScard
Document Unit
European Aviation Safety Agency
ED:
Expiry Date
EMM:
FH:
Flight Hour
FLM:
FLight Manual
FM:
Log card
FT:
GR:
GVI:
Functional Test
Ground Run
General VIsual check (Visual inspection with access equipment and standard tools)
HC:
Hoist Cycle
HT:
JAA:
LOEDU:
LC:
LUB:
M:
MC:
MGB:
MMEL:
LUBrication
Month
Maintenance Code
Main Gear Box
Master Minimum Equipment List
MP/N:
MRH:
MSM:
NPT:
OC:
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GLOSSARY
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OPC:
OPerating Cycles
OPH:
OPerating Hours
OTL:
P:
P/N:
PO:
RC:
P-check
Part Number
Perform Once
Roping Cycle
RIG:
RiggInG
RS:
RTQ:
ReStoration
Readjustment of the TorQue loading
SB:
SC:
Service Bulletin
Sling Cycle
SDI:
SLL:
S/N:
SVC:
TBO:
TCK:
TGB:
TRH:
TSI:
TSM:
VC:
WC:
WGH:
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GLOSSARY
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MSM
05-10-00, which lists the components subject to a Time Between Overhauls (TBO), as well as the
corresponding limits.
05-11-00, which lists the components subject to an Operating Time Limit (OTL), as well as the
corresponding limits.
05-20-00 (daily check), 05-20-02 (periodic interval 15 FH//7 D).
05-21-00 (periodic interval 100 FH//12 M), 05-21-01 (periodic interval 100 FH) and 05-21-02 (periodic
interval 12 M).
05-22-00 (periodic interval 500 FH//24 M), 05-22-01 (periodic interval 500 FH) and 05-22-02 (periodic
interval 24 M).
05-23-00 (periodic interval 1500 FH//72 M) and 05-23-02 (periodic interval 72 M).
05-24-02 (periodic interval 144 M).
05-25-00 (specific periodic interval).
05-26-00 (perform once time limits to be complied with a limited number of times).
These sections specify the maintenance operations to be performed on the helicopter, periodically or a limited
number of times, regardless of the operating conditions.
2.1
The title of the manual at the top right hand side of the page,
The effectivity (helicopter type and version) marked at the bottom left hand side of the page,
The date code of the DU at the bottom left hand side of the page below the effectivity (format:
year.month.day),
The number or title of the DU at the bottom right hand side of the page,
The page number at the bottom right hand side of the page.
The end of each Document Unit is identified by "End of the Document Unit" on the last page.
2.2
Task codes
The DUs in sections 05-10-00, 05-11-00, 05-20-0x, 05-21-0x, 05-22-0x, 05-23-0x, 05-24-02, 05-25-00,
05-26-00 comprise maintenance tasks. These tasks are identified by a unique code specific to Airbus
Helicopters, comprising a group of 15 characters.
Example:
The first four digits (24/36/01/000/000/050) correspond to the ATA chapter/section breakdown.
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MSM
The fifth and sixth digit (24/36/01/000/000/050) are used to subdivide an ATA chapter/section
comprising several subjects into individual subjects.
The seventh to fifteenth digit (24/36/01/000/000/050) are used to identify the tasks per ATA
chapter/section/subject.
2.3
The Document Unit (DU): this column specifies the number of the DU or the title of the DU
(example: 05-21-00).
The type: this column is coded with the letter "R" if the DU is revised, "D" if the DU is destroyed,
"N" if the DU is new, or has no code for DUs which are unchanged.
The date: this column indicates the DU date code.
CLASSIFICATION OF INFORMATION
The DUs in sections 05-10-00, 05-11-00, 05-20-0x, 05-21-0x, 05-22-0x, 05-23-0x, 05-24-02, 05-25-00 and
05-26-00 are classed in increasing order according to ATA 100 numbering.
End of the Document Unit
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MSM
Update procedure
The user is responsible for updating his documentation each time he receives a revision or a new
issue from the manufacturer. The MSM is updated using the new LOEDU which specifies which DU
must be inserted (new DU), replaced (revised DU) or removed (deleted DU). A deleted DU is issued
with the wording "DU TO BE REMOVED FROM THE MANUAL" in the revision concerned.
Once the MSM has been updated, the date code of each DU indicated at the bottom left hand side of
each page must correspond with the LOEDU.
The beginning of the MSM includes a "HIGHLIGHTS OF THE REVISION" page which explicitly
summarizes the modifications made to each revision or new issue.
NOTE
After updating, the "RECORD OF REVISIONS" page at the
beginning of the MSM must be completed (date, name and
signature).
2.2
LOEDU,
Table of contents,
Highlights of the revision.
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MSM
A supplement to the LIST OF EFFECTIVE DOCUMENT UNITS lists the Customer Complement Document
Units. The Basic Manual Revisions (on a white background) are completely separate from the Customer
Complement Revisions (issued on a green background).
EFFECTIVITY
The operator must check the effectivity of the MSM used (correctly updated) for the helicopter concerned.
The effectivity (helicopter type and version) is indicated on the cover page and is repeated at the bottom of
each page comprising the MSM DUs.
End of the Document Unit
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MSM
HELICOPTER MAINTENANCE
Helicopter maintenance consists in applying all the operations specified in the various sections of the MSM.
It must be performed by personnel with the required qualifications.
Maintenance includes the monitoring, servicing and reconditioning of a helicopter's components, as specified
in the various manuals, taking into account the information that the manufacturer makes known to the operator
via Alert Service Bulletins, Service Bulletins, Safety Information Notice, Information Notice etc.
TYPES OF MAINTENANCE
Preventive Maintenance:
Preventive maintenance consists of all the scheduled, and generally repetitive, operations to check and
maintain a given operating condition.
Corrective Maintenance:
Corrective maintenance consists of all the operations that are performed after detection of a fault or failure in
order to re-establish the initial operating condition.
Remedial Maintenance:
Remedial maintenance consists of all the operations initiated to permanently correct a failure, and to partially
or wholly eliminate the preventive and corrective maintenance of this failure.
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MSM
The modes (defined below) differ mainly in how the replacement (or repair) of a component with a serviceable
component is initiated. With the first two modes, the aim is to replace (or repair) the component before it fails,
whereas in the third mode, to replace it after it fails.
5.1
NOTE
The time limits assigned to components guarantee flight
safety with regard to the flight load fatigue alteration of
components with no external deterioration. These time limits are not a commercial guarantee because a component
may be removed due to wear, fretting corrosion or scoring,
etc., before the expiry of the time limits.
5.2
On-Condition maintenance
A component subject to On-Condition maintenance must be inspected periodically to confirm:
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MSM
In both cases, the component is kept in service until the next inspection. The component must
be removed from service when it reaches the criterion for removal, or made serviceable again as
per the instructions given in the documentation.
The visual inspection is aimed at the overall external appearance of the component (no distortion,
failure, cracks, scratches, signs of heating or wear, etc.), which would modify its original condition.
STANDING INSTRUCTIONS RELATIVE TO CONDITION: Surface deterioration and deterioration to
protection and paint on all helicopter components must be examined and treated without delay in
accordance with the applicable instructions (criteria, then reworking).
5.3
EFFECTIVITY - RESPONSIBILITY
The limits assigned to the component part numbers listed in the MSM are applicable to material:
acquired directly from Airbus Helicopters or through the Airbus Helicopters subsidiaries or distribution
network,
purchased from the equipment vendors listed in our spare part catalogs, either directly or through
their own distribution network.
In all cases, the manufacturing source is specified in the "airworthiness document" (JAA Form One or
equivalent).
Airbus Helicopters will not carry out repairs on components which were procured other than through the
Airbus Helicopters distribution network.
MAINTENANCE INTERVAL
7.1
Daily checks
The purpose of the daily checks is to ensure the serviceability of the aircraft for the flights.
The daily checks are broken down as follows:
7.1.1
15 FH // 7 D inspection
The 15 FH // 7 D inspection is intended to check the operational availability of the helicopter
between 2 checks.
This check must be performed at the latest at 15 flight hours without exceeding 7 days.
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MSM
7.1.2
The helicopter flies 15 hours within less than 7 days. The 15 FH // 7 D inspection must
be performed at the latest at 15 flight hours;
The helicopter flies less than 15 flight hours within 7 days. The 15 FH // 7 D inspection
must be performed at the latest at 7 days;
The helicopter is grounded during 7 days or more. The 15 FH // 7 D inspection must
be performed before resuming flights.
The purpose of these checks is to ensure the operational availability of the helicopter
for flight and they must be performed by:
a maintenance-qualified personnel,
or
In compliance with the criteria specified in Maintenance Manual, the mechanic will decide:
Either to authorize flights while monitoring the defective component (in such a case
the mechanic must inform the pilot of the criteria which must be observed to continue
the flights of the day),
or to carry out the remedial actions before resuming flights.
7.1.3
any modification to the definition that has been embodied on the aircraft,
any possible change in the limit interval of the component modified.
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MSM
7.2
Scheduled operations
It is aimed at checking the overall condition of the helicopter through detailed visual checks of the
systems and equipment (no distortion, failure, cracks, scratches, corrosion, signs of heating, wear,
impacts, etc.).
It is supplemented:
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MSM
IN-SERVICE MONITORING
3.1
Airframe monitoring
The in-service monitoring of the airframe must be recorded in the helicopter logbook.
3.2
Monitoring of components
All the components listed in section 05-10-00 and 05-11-00 of the MSM are to be monitored in service,
unless "not to be monitored in service" is specifically mentioned in the task.
The in-service monitoring of components consists in recording the date of installation, the number of
flight hours and/or the calendar time and/or the cycles logged on the equipment log card (FM).
If the component does not have a log card (component monitored via the log card of its higher
assembly or component without a serial number, etc.), before installation, the operator must organize
his documentation in order to comply with the inspection intervals and limits relating to this component
(refer to Standard Practices Manual Work Card 20.08.05.101).
These records must be kept if the component is transferred from one helicopter to another.
All the documentation must be organized to enable recording of all the parameters used to comply
with the limits.
Definition
Manufacturer Part Number (MP/N): This is the identification number of the component marked
on the identification plate or directly on the component.
Airbus Helicopters Part Number (P/N): This is the Airbus Helicopters part number which
is associated with the manufacturer's part number (MP/N) for components which are not
manufactured by Airbus Helicopters.
The part numbers of the components (part or assembly) which are given in the MSM are the
manufacturer's part numbers (MP/N).
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MSM
In the case of components which are not manufactured by Airbus Helicopters, the MP/N is followed
by the associated P/N (in brackets).
Example:
In some cases the P/N is not specified, in this case it is replaced by a hyphen.
4.2
4.3
4.4
LIMITS
A component or a maintenance operation can be subject to one or more limits, expressed in:
5.1
flight hours,
calendar time,
cycles.
Flight Hours
5.2
Calendar time
Calendar time can be expressed:
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in Months (M),
in Days (D),
MSM
from the date marked on the equipment label (ED: Expiry Date).
5.2.1
5.2.2
The initial aging date for a component and a dynamic component to be taken into
account is generally the date of first installation or first destorage, to be recorded on the
equipment log card. In this case, there are no other specifications in the MSM tasks.
The storage time before installation is therefore not to be taken into account on the
condition that storage was in accordance with the applicable documentation, except
for the following specific cases.
For some components, the aging date to be taken into account is the date of
manufacture marked on the Log Card (FM). In this case, TSM (Time Since
Manufacture) is specified in each task concerned in the MSM.
Specific cases:
Components or dynamic components are sometimes subject to a limit since installation and
a limit since manufacture. In this case, both limits followed by TSI (Time Since Installation)
and TSM (Time Since Manufacture) are indicated, as per the following example:
NOTE
If there is no log card, when the component arrives in the
stores, it is advisable to create a "Follow-up Sheet" and to
fill out the helicopter logbook when the component is installed. When the component is installed on the helicopter,
the applicable date is the date of manufacture marked on
the component's identification plate.
NOTE
Dynamic components, which have been subject to work in
a specialized workshop or long-term storage in accordance
with the applicable instructions during this period, may be
subject to an extension to this calendar time limit.
In this case the operator must make a request with the Airbus Helicopters Technical Support Department and obtain
approval from the manufacturer and the Airworthiness Authorities.
5.3
Cycles
According to the component, the cycles can be expressed either as:
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MSM
1 LC = 1 takeoff/landing.
5.4
Provisional limitations
The limits for which additional fatigue tests indicate the possibility of an extension, are identified by
code "P" (Provisional). This code (P) follows the value of the limit in the tasks concerned.
The operator should therefore store the component in question after removal, pending a service life
extension.
5.5
Periodically: the maintenance operation must be performed at the latest when the indicated
limit is reached.
NOTE
For operational reasons, the maintenance operation can
be performed before the limit is reached, however, the maximum interval between two maintenance operations must
be complied with.
or
Once only: the maintenance operation must be performed once only, when the indicated limit is
reached.
It must not be performed before the limit is reached.
These maintenance operations are identified by a dotted line around the task and by code
PO (Perform Once) in front of the limit value.
These operations can be performed either:
- After installation of a component removed from the same helicopter,
- After the introduction to service of a new, overhauled or repaired component,
- After installation of a component originating from another helicopter,
- Each time after the component is installed.
The start of the maintenance operation is specified in each task concerned.
Example:
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MSM
5.6
Performance interval
Some components and maintenance operations are assigned several performance limits separated
by the "//" or "&" sign.
In the case of limits separated by the "//" sign, the maintenance operation must be performed
when the first limit is reached.
The next limit at which the component is to be rejected or the maintenance operation is to be
performed will once again be the first limit reached.
In the case of limits separated by the "&" sign, the maintenance operation must be performed at
each limit indicated.
Example 1:
Section 05-10-00
. A load release unit hook performs 1000 SC over a period of 60 M (TSI). The first limit reached by
the load release unit hook therefore is 60 M; it must be removed for overhaul (TBO) and returned to
service for another period.
. After overhaul, the load release unit hook is installed on a helicopter and then performs 1500 SC
in 48 M (TSI). The first limit reached by the load release unit hook is therefore 1500 SC. It must
therefore be removed for another overhaul (TBO).
Example 2:
Section 05-26-00
The maintenance operation must be performed once at 10 FH and once at 100 FH after installation.
The maintenance operation must be repeated only if the component is removed then reinstalled or
replaced.
5.7
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MSM
. Combination of high ambient temperatures and humidity levels (from +28C (+82.4F) and
75% relative humidity).
Salt-laden atmosphere:
. Ship-based or,
. Based for more than 50% of its time less than 1 km from the coast or,
. Spending more than 50% of its time in offshore flight at low altitude (below 1,000 feet).
Cold weather:
. Temperatures observed or forecast from -10C to -30C (+14F to -22F).
The scheduled maintenance relating to these operating conditions is covered with all the MSM tasks.
These operating conditions require not only the operations specified in the MSM and standard
maintenance operations, but also the preventive measures recommended in AMM task 12-30-00,
3-3. Since the interval is not specified, the operator must reapply the measures according to his
own experience in the corresponding conditions.
5.8
5.8.2
5.8.3
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MSM
X is the limit value for performing the maintenance operation and Y is the margin value
added to the limit value.
After using the first margin value (partially or completely), the next maintenance operation
is to be performed again within the X+Y interval, that is to say before the next maximum
limit value.
6.1
Principle
Any components used on EC120 helicopters with serial numbers from 8001 up to 8999 inclusive must
be identified by indelible marking of the letters (HC) near to the part numbers of these components.
For example : - [HC] C632A0201054 for a main module used on an EC120 helicopter with a serial
number from 8001 up to 8999 inclusive.
No additional identification is necessary for a component used on a helicopter with a serial number
from 1001 up to 7999 inclusive.
6.2
Identification marking
The identification marking is to be recorded on the component at the latest upon its first removal.
However, the log card of the component concerned or of its next higher assembly is to be completed
as soon as the component is installed on the helicopter.
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When a component or assembly, either new, revised or from another aircraft, is fitted on an aircraft, the
operator must record in the aircraft log book or the equipment log card its origin and the number of hours
available before the next removal.
RECORDING
In all cases record the transfer information and calculation on the log card of the component concerned.
An individual log card must be drawn up if the component has been monitored via the log card of its higher
assembly.
9.2
Rules of procedure
Even though it is not indicated for each check, whenever possible, confirm that the surrounding
structure is in good condition: it is free from cracks, the condition of the riveting, the protection
of the sealant beads.
During an inspection, if the results are not conclusive or if a fault is found on an assembly, a
component or an attachment, do the detail checks that will confirm the condition and determine
the steps to be taken.
Before installing a component on the aircraft, the operator must check its condition.
Before you start the work:
10
LUBrication/SerViCing (LUB/SVC)
This includes work such as routine lubrication and servicing, filling/topping-up of oils, fluids, liquids
and checking of pressures.
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A general visual check is a visual inspection, without removal, to detect and assess deterioration or
incorrect operation of a component or assembly. This check may require access equipment, ladders
or platforms, and inspection means, mirror, light or screwdriver. The doors and hatches are opened
or removed in order to access the components.
CLeaNing (CLN)
To remove dirt and/or foreign bodies from a system or surface. Cleaning may require removal of the
component, such as for a filter for example.
DiScard (DS)
A component is withdrawn from service at a specified limit. Discarding normally applies to parts such as
cartridges, containers, cylinders, batteries, etc.
ReStoration (RS)
This work involves restoring a component to a specific standard. Restoration can vary from cleaning
or replacing detail parts to a complete overhaul.
WeiGHing (WGH)
The aim is to remove the equipment in order to weigh it using scales, to check its integrity and to make
sure that there are no losses.
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DRaiNing (DRN)
Draining/replenishing consists in replacing all the fluid, liquid, oil or fuel in a component.
RiggInG (RIG)
Rigging consists in adjusting a control channel or a set of components which must have an operating
range in operation.
11
CONTENT OF A TASK
Section 05-1x-00
Section 05-2x-0x
End of section
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MSM
EC 120 B
2016.04.28
MSM
SB INCORPORATED
Airbus Helicopters is required to issue Service Bulletins (SB) subsequent to new events (incidents, etc).
The information contained in the SBs is incorporated in the MSM if, and only if:
The SB contains new periodic checks, or modifies the existing MSM limitations.
the
the
the
the
SB N
Subject
ATA
Incorporation date
62-010
62-21
63-012
63-22
05-007
Calendar check for corrosion on main rotor head attack beams 62-21
05-009
62-32
05-010R1
25-67
05A011
25-67
62-004 R1
62-21
05-013
24-36
25A026
25-67
53A015
53-50
2015.04.09
53-50
2016.04.28
EC 120 B
2016.04.28
SB INCORPORATED
Page 1
MSM
05-10-00
D.U.
TITLE
ATA 24
ELECTRICAL POWER
ATA 25
ATA 63
ATA 65
ATA 67
EC 120 B
2016.04.28
05-10-00
Page 1
MSM
Task Number
Description/Remarks
MP/N (PN)
Margin
24 - ELECTRICAL POWER
24-36 STARTER/GENERATOR
24/36/01/000/000/050
Starter generator
160SG140Q1
160SG140Q1XL
(7050A4243037)
(7050A4243050)
900 FH X A
100 FH
160SG140Q-4
(7050A4243054)
1000 FH X A
320 FH
524-061
(704A46101021)
2400 FH X A
240 FH
SKURKA.
24/36/01/000/000/500
Starter generator
SKURKA.
24/36/02/000/000/150
Starter generator
AUXILEC.
(7050A4259001)
A
//
60 M X A
1500 SC X A
180 D
150 SC
Epicyclic module
C632A0101051
(-)
A
//
2000 FH X A
288 M X A
200 FH
180 D
C632A0101052
(-)
A
//
5000 FH X A
288 M X A
300 FH
180 D
63/21/00/000/000/260
Epicyclic module
EC 120 B
2016.04.28
05-10-00
Page 2
MSM
Task Number
Description/Remarks
MP/N (PN)
Margin
Main module
C632A0201051
(-)
A
//
2000 FH X A
288 M X A
200 FH
180 D
C632A0201052
C632A0201053
(-)
(-)
A
//
3750 FH X A
288 M X A
300 FH
180 D
C632A0201054
(-)
A
//
5000 FH X A
288 M X A
300 FH
180 D
63/22/00/000/000/620
Main module
63/22/00/000/000/630
Main module
TGB
C652A0101051
C652A0101054
(-)
(-)
A
//
1800 FH (P) A
288 M X A
180 FH
180 D
C652A0101052
C652A0101053
(-)
(-)
A
//
2500 FH (P) A
288 M X A
250 FH
180 D
C652A0101055
(-)
A
//
5000 FH X A
288 M X A
300 FH
180 D
4000 FH X A
240 M X TSM
300 FH
180 D
65/21/00/000/000/050
TGB
65/21/00/000/000/060
TGB
Servocontrol
SC5091
SC5091-1
(7050A4673005)
(7050A4673006)
A
//
TSM or Overhaul.
EC 120 B
2016.04.28
05-10-00
Page 3
MSM
05-11-00
D.U.
TITLE
ATA 21
AIR CONDITIONING
ATA 25
ATA 26
FIRE PROTECTION
ATA 31
ATA 62
MAIN ROTOR
ATA 65
EC 120 B
2016.04.28
05-11-00
Page 1
MSM
Task Number
Description/Remarks
MP/N (PN)
Margin
A
//
150 FH
180 D
21 - AIR CONDITIONING
21-51 COOLING
21/51/00/000/000/050
Belt
4PK730
(7050A3632293)
1500 FH X A
72 M X A
Battery pack
JE2-1978-3
JE2-1978-3NG
(N6742450122)
(NR003100026)
A
//
A ED X A
1 OPHX A
0A
0A
JOLLIET JE2/JE2NG.
1 OPH = 1 hour of operation except for testing or operation for an unknown duration.
25/63/02/000/000/060
Battery pack
ELT90A2560102001
(-)
A
//
48 M X TSM
1 OPHX A
0A
0A
SOCATA.
Battery unit assy (emergency locator transmitter battery unit + shock detector battery unit).
1 OPH = 1 hour of operation except for testing or operation for an unknown duration.
25/63/03/000/000/100
Battery pack
S1820516-99
(-)
A
//
A ED X A
1 OPHX A
0A
0A
Cylinder
215494-0
215494-1
(7050A4256002)
(7050A4256009)
180 M
X TSM
0A
Return the equipment to an approved repairer for Overhaul and replacement of the bare cylinder.
EC 120 B
2016.04.28
05-11-00
Page 2
MSM
Task Number
Description/Remarks
MP/N (PN)
Margin
25/67/00/000/000/150
Float
215674-0
215674-1
215674-2
215674-3
215675-0
215675-1
215675-2
215675-3
(7050A4256000)
(7050A4256005)
(7050A4256007)
(7050A4256020)
(7050A4256001)
(7050A4256006)
(7050A4256008)
(7050A4256021)
180 M
X TSM
0A
If you wish to apply for an extension, return the assembly in question to the manufacturer for it to be examinated.
Remove the complete assembly after a ditching.
25/67/00/000/000/200
Cover assembly
215732-0
215732-1
215733-0
215733-1
216826-0
216826-1
216827-0
216827-1
(-)
(-)
(-)
(-)
(-)
(-)
(-)
(-)
180 M
X TSM
180 D
26 - FIRE PROTECTION
26-22 CABIN EXTINGUISHER
26/22/00/000/000/050
(T262M50T0002)
60 M
X TSM
0A
(S262A10T1001)
(704A32810008)
120 M
X TSM
0A
26/22/00/000/000/100
(-)
48 M
X A
146 D
THOMEN DC20.
EC 120 B
2016.04.28
05-11-00
Page 3
MSM
Task Number
Description/Remarks
MP/N (PN)
Margin
62 - MAIN ROTOR
62-31 SWASHPLATE ASSEMBLY
62/31/00/000/000/050
Swashplate - Bearing
7050A3623013
(7050A3623013)
3000 FH X A
0A
7050A3623019
(7050A3623019)
5300 FH X A
0A
3000 FH X A
0A
FAG.
62/31/00/000/000/060
Swashplate - Bearing
SNR.
(-)
EC 120 B
2016.04.28
05-11-00
Page 4
MSM
05-20-00
BFF
ALF
D.U.
TITLE
ATA 05
05-20-00
EC 120 B
2014.05.15
BFF
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Check before the first flight of the day (BFF) - Optional equipments
AMM 05-30-00, 6-2
0A
Inspection.
Note: Operations can be carried out by an aircrew member.
VC
05/30/00/000/000/010
0A
Cold weather
Very cold weather
Inspection.
VC
05/30/00/000/000/020
Check after the last flight of the day (ALF) - Optional equipments
AMM 05-30-00, 6-2
0A
Inspection.
Note: Operations can be carried out by an aircrew member.
VC
05/30/00/000/000/030
0A
Cold weather
Very cold weather
Inspection.
VC
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-20-00
EC 120 B
2014.05.15
BFF
Page 2
MSM
05-20-02
15 FH // 7 D
D.U.
TITLE
ATA 05
05-20-02
EC 120 B
2014.05.15
15 FH // 7 D
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Daily check
AMM 05-30-00, 6-1
0A
0A
0A
0A
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-20-02
EC 120 B
2014.05.15
15 FH // 7 D
Page 2
MSM
05-21-00
100 FH // 12 M
D.U.
TITLE
ATA 25
ATA 32
LANDING GEAR
ATA 56
ATA 62
MAIN ROTOR
ATA 63
ATA 64
TAIL ROTOR
ATA 65
ATA 71
POWER PLANT
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
10 FH
36 D
(7050A4252005)
(7050A4252001)
(7050A4252012)
Check.
DI
Bench harnesses
AMM 25-22-00, 6-2
FHEC1-310002-01
FHEC1-31EC03-01
10 FH
36 D
(7050A3252003)
(7050A3252010)
Check.
DI
10 FH
36 D
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 2
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
32 - LANDING GEAR
32-17 SKIS
32/17/00/000/000/010
Ski
AMM 32-17-00, 6-2
10 FH
36 D
Detailed check.
DI
Transparent panel
AMM 56-11-00, 6-2
AMM 56-11-00, 6-3
AMM 56-31-00, 6-1
10 FH
36 D
Check.
After SB 56-002.
GVI
62 - MAIN ROTOR
62-21 MAIN ROTOR HUB
62/21/00/000/000/765
10 FH
36 D
10 FH
36 D
Greasing.
LUB
62/21/00/000/000/770
Anti-vibrator
Greasing.
LUB
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 3
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Swashplate
AMM 62-31-00, 3-1
10 FH
36 D
Greasing.
LUB
10 FH
36 D
10 FH
36 D
10 FH
36 D
Check.
FT|DI
Flexible coupling
Visual check.
GVI
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 4
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
63/11/00/000/000/210
10 FH
36 D
10 FH
36 D
Play check.
DI
Starting interlock
Functional test.
FT
64 - TAIL ROTOR
64-21 TAIL ROTOR HUB
64/21/00/000/000/050
Blade/Bearing
AMM 64-21-00, 6-1
10 FH
36 D
10 FH
36 D
Play checks.
DI
64/21/00/000/000/100
Blade/Shroud
Play checks.
DI
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 5
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
64/21/00/000/000/150
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
64-21-00,
6-4
6-5
6-6
6-7
6-8
6-9
6-10
6-11
6-12
6-13
6-14
6-15
6-16
10 FH
36 D
Cover plate
AMM 65-11-00, 6-19
10 FH
36 D
10 FH
36 D
10 FH
36 D
Visual check.
VC
65/11/00/000/000/750
Bearing
Greasing.
LUB
65/11/00/000/000/850
Flexible coupling
Visual check.
VC
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 6
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
10 FH
36 D
Inspection.
FT|DI
71 - POWER PLANT
71-63 SAND FILTER
71/63/00/000/000/000
Sand filter
AMM 71-63-00, 6-1
10 FH
36 D
Condition check.
GVI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-21-00
EC 120 B
2016.04.28
100 FH // 12 M
Page 7
MSM
05-21-01
100 FH
D.U.
TITLE
ATA 52
DOORS
ATA 62
MAIN ROTOR
05-21-01
EC 120 B
2015.04.09
100 FH
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
52 - DOORS
52-33 PANEL OF COMMUNICATION
52/33/00/000/000/000
10 FH
Condition check.
To be carried out on the aircraft with rear bench removed.
GVI
62 - MAIN ROTOR
62-11 MAIN ROTOR BLADES
62/11/00/000/000/210
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-21-01
EC 120 B
2015.04.09
100 FH
Page 2
MSM
05-21-02
12 M
D.U.
TITLE
ATA 24
ELECTRICAL POWER
ATA 25
ATA 26
FIRE PROTECTION
ATA 34
NAVIGATION
ATA 53
FUSELAGE
05-21-02
EC 120 B
2016.04.28
12 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
24 - ELECTRICAL POWER
24-33 BATTERY
24/33/00/000/000/060
Battery
150CH-1
151CH-1
151CH-2
CMM 24.33.96
CHECK 2.C
(7050A4243027)
(7050A4243040)
(7050A4243039)
36 D
Check.
DI
Cylinder
AMM 25-67-00, 6-2
CMM 25.69.32
0A
Condition check.
Check to be performed during the first assembly and to initiate from this one.
GVI
25/67/00/000/000/100
Bracket
AMM 25-67-00, 6-3
36 D
05-21-02
EC 120 B
2016.04.28
12 M
Page 2
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
26 - FIRE PROTECTION
26-22 CABIN EXTINGUISHER
26/22/00/000/000/075
36 D
Weighing.
TSM
WGH
34 - NAVIGATION
34-00 NAVIGATION
34/00/00/000/000/030
36 D
EE0033 A ou B.
Check and charge the battery.
FT
53 - FUSELAGE
53-50 AFT FUSELAGE
53/50/00/000/000/310
Tail boom
AMM 53-50-00, 6-3
36 D
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-21-02
EC 120 B
2016.04.28
12 M
Page 3
MSM
05-22-00
500 FH // 24 M
D.U.
TITLE
ATA 05
ATA 21
AIR CONDITIONING
ATA 23
COMMUNICATIONS
ATA 24
ELECTRICAL POWER
ATA 25
ATA 28
FUEL SYSTEM
ATA 29
HYDRAULIC POWER
ATA 31
ATA 32
LANDING GEAR
ATA 33
LIGHTING SYSTEM
ATA 34
NAVIGATION
ATA 52
DOORS
ATA 53
FUSELAGE
ATA 55
STABILIZER
ATA 62
MAIN ROTOR
ATA 63
ATA 65
ATA 67
ATA 71
POWER PLANT
ATA 76
ENGINE CONTROLS
ATA 79
ENGINE OIL
ATA 88
ELECTRICAL HARNESSES
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Do a ground check
FLM Section 8
50 FH
73 D
GR
21 - AIR CONDITIONING
21-00 AIR CONDITIONING
21/00/00/000/000/000
P2 indicating system
AMM 21-41-00, 5-1
50 FH
73 D
50 FH
73 D
50 FH
73 D
50 FH
73 D
P2 indicating system
Check.
GVI
21-51 COOLING
21/51/00/000/000/150
Belt
Check of tension.
DI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 2
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
21/51/00/000/000/250
MGB compressor
AMM 20-10-00, 6-1
AMM 21-51-00, 8-1
50 FH
73 D
23 - COMMUNICATIONS
23-00 COMMUNICATIONS
23/00/00/000/000/050
Communication system
AMM 23-00-00, 6-1
50 FH
73 D
Inspection.
VC
24 - ELECTRICAL POWER
24-00 ELECTRICAL POWER
24/00/00/000/000/100
50 FH
73 D
50 FH
73 D
Inspection.
VC
24-33 BATTERY
24/33/00/000/000/100
Functional test.
FT
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 3
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Cable-cutter
AMM 25-61-00, 6-1
50 FH
73 D
50 FH
73 D
50 FH
73 D
JOLLIET JE2/JE2NG.
Installation check.
DI|FT
25/63/02/000/000/160
ELT96A2560000000
(704A45737043)
SOCATA.
Installation check.
DI|FT
28 - FUEL SYSTEM
28-00 FUEL SYSTEM
28/00/00/000/000/050
Fuel system
AMM 28-00-00, 6-1
50 FH
73 D
Condition check.
GVI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 4
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
28/00/00/000/000/060
Strainers
AMM 28-00-00, 6-3
50 FH
73 D
50 FH
73 D
50 FH
73 D
28-22 DISTRIBUTION
28/22/00/000/000/100
Functional test.
FT
28-42 INDICATING
28/42/00/000/000/150
Check.
DI
29 - HYDRAULIC POWER
29-00 HYDRAULIC POWER
29/00/00/000/000/050
Servocontrol - Accumulator
AMM 29-00-00, 6-1
50 FH
73 D
Pressure check.
NPT
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 5
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
50 FH
73 D
Check.
GVI
32 - LANDING GEAR
32-12 LANDING GEAR
32/12/00/000/000/050
Landing gear
AMM 32-12-00, 6-1
50 FH
73 D
Detailed check.
DI
33 - LIGHTING SYSTEM
33-00 LIGHTING SYSTEMS
33/00/00/000/000/050
Lighting system
AMM 33-00-00, 6-1
50 FH
73 D
Installation check.
DI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 6
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
34 - NAVIGATION
34-00 NAVIGATION
34/00/00/000/000/050
Navigation system
AMM 34-00-00, 6-1
50 FH
73 D
Installation check.
DI
52 - DOORS
52-10 STANDARD CABIN DOORS
52/10/00/000/000/000
50 FH
73 D
50 FH
73 D
50 FH
73 D
Inspection/Check.
GVI
52/10/00/000/000/100
Condition check.
GVI
Functional test.
FT
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 7
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
50 FH
73 D
50 FH
73 D
50 FH
73 D
Condition check.
GVI
52/50/00/000/000/210
Inspection/Check.
DI
Functional test.
FT
53 - FUSELAGE
53-00 FUSELAGE
53/00/00/000/000/200
Fuselage
AMM 53-00-00, 6-1
AMM 53-00-00, 6-2
50 FH
73 D
Visual check.
GVI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 8
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
50 FH
73 D
50 FH
73 D
50 FH
73 D
50 FH
73 D
53-53 FENESTRON
53/53/00/000/000/150
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 9
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
55 - STABILIZER
55-11 HORIZONTAL STABILIZER
55/11/00/000/000/000
Horizontal stabilizer
AMM 55-11-00, 6-1
50 FH
73 D
Detailed check.
DI
62 - MAIN ROTOR
62-11 MAIN ROTOR BLADES
62/11/00/000/000/150
50 FH
73 D
Inspection.
Check every 100 FH (marge 10 FH) for 500 FH, if a defect (inside the limits)
is found : blade skin separation or blade leading edge stainless steel strip
separation, cracks in the stainless steel leading edge.
If no development is noted during this period, return to the normal inspection cycle.
DI
62/11/00/000/000/160
Attachment components
AMM 62-11-00, 6-4
50 FH
73 D
Detailed check.
DI
50 FH
73 D
Check.
DI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 10
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
62/21/00/000/000/790
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
6-2
6-3
6-4
6-5
6-6
6-7
6-8
6-9
6-10
6-11
6-12
6-13
6-14
6-15
6-16
6-17
6-18
6-19
6-20
50 FH
73 D
50 FH
73 D
50 FH
73 D
Condition check.
GVI
62/21/00/000/000/795
Split ring
Detailed check.
DI
Rotating swashplate
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 11
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
62/31/00/000/000/160
Rotating swashplate
AMM 62-31-00, 6-6
7050A3623019
50 FH
73 D
(7050A3623019)
50 FH
73 D
50 FH
73 D
50 FH
73 D
50 FH
73 D
Greasing.
LUB
62/32/00/000/000/330
Play check.
DI
62/32/00/000/000/360
Scissor link
Check.
In the case of default constated inside the rings of the scissor link (inside the limits) make sure
of the absences of the following hard points CT 62-32-00, 6-7 every 100 FH (marge 10 FH).
DI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 12
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
62/32/00/000/000/370
50 FH
73 D
50 FH
73 D
Detailed check.
DI
62/32/00/000/000/400
Scissor bolt
Play checks.
DI
50 FH
73 D
50 FH
73 D
50 FH
73 D
Condition check.
GVI
Flexible coupling
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 13
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
MGB
AMM 12-10-00, 3-2
AMM 63-22-00, 3-1
50 FH
73 D
50 FH
73 D
50 FH
73 D
Rotor brake
Condition check.
GVI
Condition check.
GVI
50 FH
73 D
Check.
DI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 14
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
65/11/00/000/000/900
50 FH
73 D
50 FH
73 D
50 FH
73 D
50 FH
73 D
Detailed check.
DI
TGB
Oil change.
DRN
65/21/00/000/000/350
TGB
Condition check.
GVI
50 FH
73 D
Condition check.
GVI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 15
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
50 FH
73 D
50 FH
73 D
Condition check.
GVI
67-31 SERVOCONTROLS
67/31/00/000/000/150
Servocontrol
71 - POWER PLANT
71-00 POWER PLANT
71/00/00/000/000/100
50 FH
73 D
Condition check.
GVI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 16
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
71-41-00,
6-1
6-2
6-3
6-4
6-6
6-7
6-8
6-9
6-10
6-11
50 FH
73 D
Detailed check.
DI
50 FH
73 D
Detailed check.
DI
76 - ENGINE CONTROLS
76-11 ANTICIPATOR BALL-TYPE CONTROL
76/11/00/000/000/000
50 FH
73 D
Condition check.
GVI
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 17
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Ball end-fitting
AMM 12-20-00, 6-1
50 FH
73 D
50 FH
73 D
L'HOTELLIER.
Check.
DI
76/12/00/000/000/050
Check.
DI
79 - ENGINE OIL
79-21 ENGINE OIL COOLING
79/21/00/000/000/050
50 FH
73 D
Condition check.
GVI
88 - ELECTRICAL HARNESSES
88-00 ELECTRICAL HARNESSES
88/00/00/000/000/050
Electrical harnesses
AMM 88-00-00, 6-1
50 FH
73 D
Check.
GVI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 18
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
05-22-00
EC 120 B
2016.04.28
500 FH // 24 M
Page 19
MSM
05-22-01
500 FH
D.U.
TITLE
ATA 24
ELECTRICAL POWER
05-22-01
EC 120 B
2016.04.28
500 FH
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
24 - ELECTRICAL POWER
24-36 STARTER/GENERATOR
24/36/01/000/000/200
Starter generator
160SG140Q-4
50 FH
SKURKA.
Check the brushes.
DI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-22-01
EC 120 B
2016.04.28
500 FH
Page 2
MSM
05-22-02
24 M
D.U.
TITLE
ATA 24
ELECTRICAL POWER
ATA 53
FUSELAGE
ATA 62
MAIN ROTOR
ATA 63
05-22-02
EC 120 B
2016.04.28
24 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
24 - ELECTRICAL POWER
24-33 BATTERY
24/33/00/000/000/070
Battery
150CH-1
151CH-1
151CH-2
CMM 24-33-96
CHECK 2.D
CHECK 2.E
CHECK 2.F
(7050A4243027)
(7050A4243040)
(7050A4243039)
73 D
73 D
Overhaul.
DI
24/33/00/000/000/080
Battery
150CH-1
151CH-1
151CH-2
53 - FUSELAGE
53-50 AFT FUSELAGE
53/50/00/000/000/300
Tail boom
AMM 53-50-00, 6-2
AMM 53-50-00, 6-3
73 D
05-22-02
EC 120 B
2016.04.28
24 M
Page 2
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
62 - MAIN ROTOR
62-21 MAIN ROTOR HUB
62/21/00/000/000/360
73 D
Detailed check.
Only concerns the aircraft before serial number 1498 and from 8001 to 8029
included not having applied SB 62-004 to the revision 1.
DI
62/21/00/000/000/410
73 D
Detailed check.
Only concerns the aircraft before serial number 1498 and from 8001 to 8029
included not having applied SB 62-004 to the revision 1.
DI
Lower housing
AMM 63-22-00, 6-3
73 D
Check of corrosion inside the bores of the tapered pin attaching cones of the
MGB lower casing MP/N C632A2104102 or C632A2115101.
GVI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-22-02
EC 120 B
2016.04.28
24 M
Page 3
MSM
05-23-00
1500 FH // 72 M
D.U.
TITLE
ATA 25
ATA 28
FUEL SYSTEM
ATA 29
HYDRAULIC POWER
ATA 62
MAIN ROTOR
ATA 65
05-23-00
EC 120 B
2016.04.28
1500 FH // 72 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
150 FH
180 D
150 FH
180 D
Check.
DI
Check.
DI
28 - FUEL SYSTEM
28-12 INTERNAL TANKS
28/12/00/000/000/200
Anti-spillage valve
AMM 28-12-00, 6-2
150 FH
180 D
Check.
DI
29 - HYDRAULIC POWER
29-00 HYDRAULIC POWER
29/00/00/000/000/000
150 FH
180 D
Draining.
DRN
05-23-00
EC 120 B
2016.04.28
1500 FH // 72 M
Page 2
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
62 - MAIN ROTOR
62-21 MAIN ROTOR HUB
62/21/00/000/000/820
62-21-00,
62-21-00,
62-21-00,
62-21-00,
62-21-00,
6-21
6-22
6-23
6-24
6-25
150 FH
180 D
Swashplate
AMM 62-31-00, 6-6
150 FH
180 D
Clearance check.
DI
Flexible coupling
AMM 65-11-00, 6-4
150 FH
180 D
150 FH
180 D
Detailed check.
DI
65/11/00/000/000/350
Detailed check.
DI
05-23-00
EC 120 B
2016.04.28
1500 FH // 72 M
Page 3
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
65/11/00/000/000/400
Splined flange
AMM 65-11-00, 6-7
150 FH
180 D
150 FH
180 D
150 FH
180 D
150 FH
180 D
150 FH
180 D
150 FH
180 D
Detailed check.
DI
65/11/00/000/000/450
Bearing
Detailed check.
DI
65/11/00/000/000/650
Damper
Adjustment check.
RIG
65/11/00/000/000/700
Forward shaft
Detailed check.
DI
65/11/00/000/000/710
Rear shaft
Detailed check.
DI
65/11/00/000/000/720
Cover plate
Detailed check.
DI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-23-00
EC 120 B
2016.04.28
1500 FH // 72 M
Page 4
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
05-23-00
EC 120 B
2016.04.28
1500 FH // 72 M
Page 5
MSM
05-23-02
72 M
D.U.
TITLE
ATA 05
05-23-02
EC 120 B
2016.04.28
72 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
Dynamic systems
AMM 05-40-00, 6-1
180 D
Detailed check.
Perform the first check at 144 M (marge 180D).
DI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-23-02
EC 120 B
2016.04.28
72 M
Page 2
MSM
05-24-02
144 M
D.U.
TITLE
ATA 05
05-24-02
EC 120 B
2014.05.15
144 M
Page 1
MSM
Task Number
Description/ Remarks
Documentation
Margin
Initial
180 D
Detailed check.
DI
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
05-24-02
EC 120 B
2014.05.15
144 M
Page 2
MSM
05-25-00
D.U.
TITLE
ATA 05
ATA 24
ELECTRICAL POWER
ATA 25
ATA 26
FIRE PROTECTION
ATA 32
LANDING GEAR
ATA 62
MAIN ROTOR
ATA 64
TAIL ROTOR
ATA 65
EC 120 B
2016.04.28
05-25-00
Page 1
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
Dynamic systems
AMM 05-40-00, 6-1
Tropical and damp atmosphere
Salt-laden atmosphere
Sand-laden and/or dust-laden atmosphere
48 M
146 D
18 D
Detailed check.
Perform the first check at 96 M (marge 180 D).
DI
24 - ELECTRICAL POWER
24-33 BATTERY
24/33/00/000/000/050
Battery
150CH-1
151CH-1
151CH-2
CMM 24.33.96
CHECK 2.B
(7050A4243027)
(7050A4243040)
(7050A4243039)
6M
Check.
DI
24-36 STARTER/GENERATOR
24/36/01/000/000/000
Starter generator
160SG140Q1
160SG140Q1XL
300 FH X
30 FH
SKURKA.
Check the brushes.
DI
EC 120 B
2016.04.28
05-25-00
Page 2
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
24/36/02/000/000/050
Starter generator
AMM 24-36-02, 6-1
600 FH X
60 FH
1200 FH X
120 FH
AUXILEC.
Check the brushes.
DI
24/36/02/000/000/100
Starter generator
AUXILEC.
Replacing bearings and brushes.
DS
6M
18 D
6M
18 D
1M
3D
JOLLIET JE2/JE2NG.
Functional test.
FT
25/63/02/000/000/100
SOCATA.
Emergency locator transmitter self-test (3 consecutive phases).
FT
25/63/03/601/000/050
EC 120 B
2016.04.28
05-25-00
Page 3
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
Cylinder
A
//
215494-0
36 M X
1 OPCX
0A
0A
(7050A4256002)
Proof test.
1 OPC = 1 utilization (ditching or untimely percussion of the inflation cylinder).
To be returned to the manufacturer or to an approved workshop.
Interval starting from the date of manufacture (TSM), then from the date of the last proof test.
NPT
25/67/00/000/000/030
Cylinder
A
//
215494-1
60 M X
1 OPCX
0A
0A
(7050A4256009)
Proof test.
1 OPC = 1 utilization (ditching or untimely percussion of the inflation cylinder).
To be returned to the manufacturer or to an approved workshop.
Interval starting from the date of manufacture (TSM), then from the date of the last proof test.
NPT
25/67/00/000/000/110
Bracket
AMM 25-67-00, 6-3
18 M
54 D
18 M
54 D
300 FH X
0A
Condition check.
GVI
25/67/00/000/000/300
Float
Condition check.
GVI
25/67/00/000/000/305
Float
PRE ASB 25A026
Detailed check.
DI
EC 120 B
2016.04.28
05-25-00
Page 4
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
25/67/00/000/000/310
Cover assembly
AMM 25-67-00, 6-4
18 M
54 D
Check.
TSM
DI
25/67/00/000/000/350
A
//
500 FH X
12 M X
50 FH
36 D
A
//
500 FH X
18 M X
50 FH
54 D
A
//
24 M X
500 SC X
73 D
50 SC
Test.
Check to be performed on and from initial installation.
FT
25/67/00/000/000/360
26 - FIRE PROTECTION
26-22 CABIN EXTINGUISHER
26/22/00/000/000/150
6M
18 D
Condition check.
GVI
EC 120 B
2016.04.28
05-25-00
Page 5
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
32 - LANDING GEAR
32-17 SKIS
32/17/00/000/000/030
Ski
AMM 32-17-00, 6-1
25 FH X
2 FH
25 FH X
2 FH
A
//
100 FH X
3M X
10 FH
9D
A
//
100 FH X
3M X
10 FH
9D
Condition check.
GVI
62 - MAIN ROTOR
62-11 MAIN ROTOR BLADES
62/11/00/000/000/200
Anti-vibrator
AMM 62-21-00, 3-1
Tropical and damp atmosphere
Salt-laden atmosphere
Sand-laden and/or dust-laden atmosphere
Greasing.
LUB
EC 120 B
2016.04.28
05-25-00
Page 6
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
Swashplate
AMM 62-31-00, 3-1
A
//
100 FH X
3M X
10 FH
9D
64 - TAIL ROTOR
64-21 TAIL ROTOR HUB
64/21/00/000/000/255
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
Detailed check.
DI
64/21/00/000/000/260
Splined flange
Detailed check.
DI
64/21/00/000/000/270
Outer bearing
Detailed check.
DI
64/21/00/000/000/280
Inner bearing
Detailed check.
DI
EC 120 B
2016.04.28
05-25-00
Page 7
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
64/21/00/000/000/290
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
Detailed check.
DI
64/21/00/000/000/300
Blade assembly
Detailed check.
DI
64/21/00/000/000/310
Stepped bolt
Detailed check.
DI
64/21/00/000/000/320
Detailed check.
DI
64/21/00/000/000/330
Detailed check.
DI
64/21/00/000/000/340
Pitch-change spider
Detailed check.
DI
EC 120 B
2016.04.28
05-25-00
Page 8
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
64/21/00/000/000/350
Fairing assembly
AMM 64-21-00, 6-14
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
A
//
1000 FH X
24 M X
100 FH
73 D
Detailed check.
DI
64/21/00/000/000/360
Hub plate
Detailed check.
DI
64/21/00/000/000/370
Bearing
AMM 65-11-00, 3-1
A
//
100 FH X
3M X
10 FH
9D
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
EC 120 B
2016.04.28
05-25-00
Page 9
MSM
05-26-00
D.U.
TITLE
ATA 25
ATA 28
FUEL SYSTEM
ATA 53
FUSELAGE
ATA 62
MAIN ROTOR
ATA 63
ATA 64
TAIL ROTOR
ATA 65
ATA 67
EC 120 B
2015.04.09
05-26-00
Page 1
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
Float
AMM 25-67-00, 6-5
CMM 25.69.32
PO A
&
&
72 M
108 M
144 M
X
X
X
180 D
180 D
180 D
28 - FUEL SYSTEM
28-00 FUEL SYSTEM
28/00/00/000/000/250
Strainers
AMM 28-00-00, 6-3
PO A
&
10 FH X
100 FH X
1 FH
10 FH
2 FH X
8 FH
53 - FUSELAGE
53-37 CABIN ANTIVIBRATORS
53/37/00/000/000/010
PO A
EC 120 B
2015.04.09
05-26-00
Page 2
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
62 - MAIN ROTOR
62-00 MAIN ROTOR
62/00/00/000/000/750
Main rotor
AMM 20-10-00, 6-1
AMM 62-00-00, 6-2
Each time after the component is installed
PO A
2 FH X
8 FH
100 FH X
PO A
200 FH X
&
After the introduction to service of a new, overhauled or repaired component
10 FH
20 FH
Inspection.
GVI
PO A
2 FH X
8 FH
PO A
2 FH X
8 FH
EC 120 B
2015.04.09
05-26-00
Page 3
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Initial
MGB
AMM 12-10-00, 3-2
30 FH X
PO A
AMM 63-22-00, 3-1
After the introduction to service of a new, overhauled or repaired component
5 FH
64 - TAIL ROTOR
64-21 TAIL ROTOR HUB
64/21/00/000/000/000
Tail rotor
AMM 20-10-00, 6-1
AMM 64-21-00, 6-3
Each time after the component is installed
PO A
2 FH X
8 FH
TGB
AMM 12-10-00, 3-2
30 FH X
PO A
After the introduction to service of a new, overhauled or repaired component
5 FH
Draining.
DRN
Servocontrol
AMM 20-10-00, 3-2
AMM 67-31-00, 4-2
Each time after the component is installed
PO A
2 FH X
8 FH
EC 120 B
2015.04.09
05-26-00
Page 4
MSM
Task Number
Description/
Remarks
Documentation
Interval
Margin
Mechanic
Date
Inspector
Date
Name :
Signature :
Stamp :
Signature :
Initial
EC 120 B
2015.04.09
05-26-00
Page 5