DR400 Maintenance Schedule Is5 Amdt7 April2015

Doc. no. 1001586GB DR400 AIRWORTHINESS LIMITATIONS & MAINTENANCE SCHEDULE

Issue 5 - March 2013 of 36

C.E.A.P.R. 1, route de Troyes

21121 DAROIS – France Tel. + 33 (0)3 80 35 25 22 Fax. + 33 (0)3 80 35 25 25

Website: www.ceapr.com

DR400

AIRWORTHINESS LIMITATIONS

&

MAINTENANCE SCHEDULE

This document together with the DR400 Maintenance Manual (doc n° 1001606), contain appropriate instructions for continued airworthiness as described in § CS 23.1529 of Certification Specifications CS 23.

The English version of this document is a courtesy translation of its original French version. In case of any difficulty, reference should be made to the French original issue.

ISSUE 5 dated

MARCH 2013 Document n°1001586


of 36 Issue 4 - July 2006



TABLE OF CONTENT

List of current pages

Record of amendments

Chapter I AIRWORTHINESS LIMITATIONS

Chapter II MAINTENANCE SCHEDULE

Section 1 General instructions

Section 2 Time between inspections and weighing

Section 3 Instructions for maintenance, operation and stocking of components and equipments

Section 4 Specific maintenance operations

Section 5 Control flights

Section 6 Maintenance operations table


of 36 Amendment 7 dated April 2015 Issue 5 - March 2013

LIST OF CURRENT PAGES

Amendment Date

Cover ...................................................Original ...........................March 2013

1st page ..............................................Original ...........................March 2013

Table of content ...................................Original ...........................March 2013

List of current pages.................................. 7 .................................. April 2015

Record of amendments ............................ 7 .................................. April 2015

Chapter I - Airworthiness limitations Amendment Date

All the pages ........................................Original ...........................March 2013

Chapter II - Maintenance schedule

Amendment Date

Section 1 ..............................................Original ...........................March 2013

Section 2 .............................................Original ...........................March 2013

Section 3 .................................................. 5 .................................. June 2014



Section 6 .................................................. 7 .................................. April 2015 Annex ............................................... 7 .................................. April 2015


Issue 5 - March 2013 Amendment 7 dated April 2015 of 36

RECORD OF AMENDMENTS

Amendment 1 dated April 2013

PAGE TO DELETE PAGE TO INSERT REASON

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pages” original Page 5 of 36 “Record of

amendments” original Annex original in section 6


pages” Amdt 1 Page 5 of 36 “Record of

amendments” Amdt 1 Annex (all pages), amdt 1

dated April 2013

Updating Updating Modification of annex part of section 6, line 57-20.

Amendment 2 dated June 2013


Page 4 of 36 “List of current pages” Amdt 1 Page 5 of 36 “Record of amendments” Amdt 1 Section 3

Annex (all pages), amdt 1 dated April 2013

Page 4 of 36 “List of current pages” Amdt 2 Page 5 of 36 “Record of amendments” Amdt 2 Section 3 Amdt 2

Annex (all pages), amdt 2 dated June 2013

Updating Updating Modification of table 2 Modification of “Additional instructions”

Modification of annex part of section 6, line 71-55.



Page 4 of 36 “List of current pages” Amdt 2 Page 5 of 36 “Record of amendments” Amdt 2 Section6 Annex (all pages),

amdt 2 dated June 2013

Page 4 of 36 “List of current pages” Amdt 3 Page 5 of 36 “Record of amendments” Amdt 3 Section6 Annex (all pages),

amdt 3 dated June 2013

Updating Updating Modification of annex part of section 6, line 27-130 and line 57-70.

Amendment 4 dated October 2013




Updating Updating Modification of table 2

Note: Each "record of amendments" page must be kept in the manual throughout its life.

The availability of all the pages allows giving a chronological account of changes.



RECORD OF AMENDMENTS (follow-up)



Page 4 of 36 “List of current pages” Amdt 4 Page 5 of 36 “Record of amendments” Amdt 4 Page 6 of 36 Section 3 Amdt 4

Section 6 Annex (all pages),

Amdt 3 dated June 2013

Page 4 of 36 “List of current pages” Amdt 5 Page 5 of 36 “Record of amendments” Amdt 5 Page 6 of 36 Record of amendments follow up” Amdt 5

Section 3 Amdt 5

Section 6 Amdt 5 Annex (all pages),


Updating Updating Modification of table 2 and “additional instructions” Modification of section 6 and annex part of section 6, lines 27-110, 55-10, 55-20, 55-80, 75-40.

Amendment 6 dated October 2014


Page 4 of 36 “List of current pages” Amdt 5 Page 5 of 36 “Record of amendments” Amdt 5 Page 6 of 36 “Record of amendments follow up” Amdt 5 Section 6 Amdt 5 Annex (all pages),


Page 4 of 36 “List of current pages” Amdt 6 Page 5 of 36 “Record of amendments” Amdt 6 Page 6 of 36 Record of amendments follow up” Amdt 6 Section 6 Amdt 6 Annex (all pages),

Amdt 6 dated october 2014

Updating Updating Updating Modification of annex part of section 6, lines 27-110



RECORD OF AMENDMENTS (follow-up)

Amendment 7 dated April 2015




amendments” Amdt 5 Page 6&7 of 36 “Record of

amendments follow up” Amdt 7 Section 6 Amdt 6 Annex (all pages), Amdt 6 dated October 2014



amendments” Amdt 6 Page 6&7 of 36 Record of

amendments follow up” Amdt 7 Section 6 Amdt 7 Annex (all pages), Amdt 7 dated April 2015

Updating Updating Updating Addition of Note 29 & 30 Modification of annex part of section 6, lines 21.20/ 24.10/ 24.120/ 25.10/ 27.10/ 27.20/ 27.150/ 31.10/ 32.50/ 32.55/ 32.220/ 53.10/ 53.30/ 57.10/ 57.70/ 61.10/ 61.20/ 73.100/ 75.30/ 75.50

Note: Each "record of amendments" page must be kept in the manual throughout its life.

The availability of all the pages allows giving a chronological account of changes.

Doc. no. 1001586GB Chapter I DR400 AIRWORTHINESS LIMITATIONS


Chapter I

DR400


The airworthiness limitations are approved by the European Aviation Safety Agency (EASA).

Any change in the chapter "AIRWORTHINESS LIMITATIONS" shall be

presented to the European Aviation Safety Agency for approval.

Doc. no. 1001586GB Chapter I DR400 AIRWORTHINESS LIMITATIONS

of 36 Issue 5 - March 2013


The DR400 airplanes, any model, are not subject to Airworthiness limitations.

Note 1: The Airworthiness Limitations of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-01 engine” (DR400/135CDI) are included in the following documents:

- Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-01, Operation & Maintenance Manual TAE 125-01. - Doc. AMM-60-01, Supplement Airplane Maintenance Manual Robin DR400/135CDI –

TAE 125-01.

Note 2: The Airworthiness Limitations of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-02-99 engine and installation of FADEC backup battery” (DR400/135CDI) are included in the following documents:

- Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-02, Operation & Maintenance Manual TAE 125-02-99. - Doc. AMM-60-02, Supplement Airplane Maintenance Manual Robin DR400/135CDI –

CENTURION 2.0.

Note 3: The Airworthiness Limitations of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-02-114” (DR400/155CDI) are included in the following documents:

- Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-02, Operation & Maintenance Manual TAE 125-02-99. - Doc. AMM-60-02S, Supplement Airplane Maintenance Manual Robin DR400/155CDI –

CENTURION 2.0S.

Doc. no. 1001586GB Chapter II DR400 MAINTENANCE SCHEDULE


Chapter II

DR400

MAINTENANCE SCHEDULE

Maintenance schedule applicable to DR400 all models except DR400 RP and 125i:

DR 400/125 DR 400/140 DR 400/160 DR 400/180 DR 400/180 R DR 400/2+2 DR 400/120 DR 400/140 B (*) DR 400/120 A DR 400/160 D DR 400/120 D DR 400/180 S DR 400/100 DR 400 NGL DR 400/200 R DR 400/500

(*) Note: Specificity of DR 400/140 B with STC EASA 10014219: TAE 125 engine installation (DR 400/135CDI, DR 400/155CDI) is described in TAE documents.

This document is proposed as a sample and contains all data from manufacturer useful to make the maintenance schedule dedicated to the plane and approved. The reference regulation applied is the one of EASA together with the French specificities taken into account.



SECTION 1

GENERAL INSTRUCTIONS

A. GENERAL

The owner/operator or the person in charge for the management of the continued airworthiness must make sure that the inspections appearing in the maintenance schedule are carried out in the prescribed intervals.

Nothing of what is contained or omitted in the maintenance schedule discharges the owner/operator from the responsibility to make sure that the aircraft is maintained airworthy.

The maintenance schedule must hold account of the operational requirements, as well as all requirements of maintenance rising from the modifications or repairs.

The modifications made to the maintenance manual must be accepted by the qualified services.

The owner/operator must modify its maintenance schedule according to directives of the qualified services, the publications delivered by the manufacturers (service bulletins, revisions to the maintenance documents…), the maintenance documents of the manufacturers following a modification. This update is carried out within one year as from the diffusion of the requirement of the authority or the recommendations of the manufacturer. A personalized follow-up must be set up to carry out these inspections in waiting of their insertion in the program.

The specificities of the country in which the aircraft is registered must be taken into account.

B. DEFINITION OF MAINTENANCE

Maintenance, with preventive vocation for all the components taking part in the airworthiness condition, is composed of the whole of the operations which contribute to maintain the aircraft on a satisfactory level of safety. It incorporates generally:

inspections: examinations of various levels, having for goal to objectively recognize the state of a component;

specific actions, predetermined or not: interventions for purpose of conservation, like corrective actions resulting from the;

replacements of components in the given term;

Particular operations having the aim of making sure of continued operational features or consecutive to certain unforeseeable occurrences.

Accordingly, the maintenance schedule is a document which describes the operations necessary to maintain the aptitude of an aircraft for being operated, in particular as regards aptitude for the flight, of maintenance of the equipment as of the means of radio communication/navigation whose presence on board is required by the regulation.

The application of the airworthiness directives is managed in a way personalized to each airplane.



C. COMPLEX MAINTENANCE TASKS – FLIGHT SAFETY SENSITIVE MAINTENANCE TASKS

Complex maintenance tasks referred to in M.A. 801 (b), 2. : 1) The modification, repair or replacement by riveting, bonding, laminating, or welding of

any of the following airframe parts: a. a box beam; b. a wing stringer or chord member; c. a spar; d. a spar flange; e. a member of a truss-type beam; f. the web of a beam; g. a corrugated sheet compression member in a wing or tail surface; h. a wing main rib; i. a wing or tail surface brace strut; j. an engine mount; k. a fuselage longeron or frame; l. a member of a side truss, horizontal truss or bulkhead; m. a seat support brace or bracket; n. a seat rail replacement; o. a landing gear strut or brace strut; p. an axle; q. a wheel.

2) The modification or repair of any of the following parts:

a. Aircraft skin if the work requires the use of a support, jig or fixture; b. A load-bearing part of a control system, including a control column, pedal, shaft,

quadrant, bell crank, torque tube, control horn and forged or cast bracket, but excluding:

- the swaging of a repair splice or cable fitting, and - the replacement of a push-pull tube end fitting that is attached by riveting;

and

c. Any other structure, not listed in (1), which a manufacturer has identified as primary structure in its maintenance manual, structural repair manual or instructions for continuing airworthiness.



Flight safety sensitive maintenance tasks (M.A. 402(a)):

- The tasks for which the manufacturer's documentation has explicitly planned an independent inspection;

- At least: a practical work on a control system which, in case of errors, could lead to a failure, a malfunction or a defect threatening flight safety. A control system is a system of the aircraft which may change the flight path, the flight attitude or the propulsive force of the aircraft, Notably the flight controls, the engine and propeller, the related control systems and the associated operating mechanisms.

Examples of possibly sensitive maintenance tasks:

- Installation, setting and adjustment of flight controls. - Installation of engines, propellers on aircraft. - Overhaul calibration or adjustment of components such as engines, propellers,

transmissions and gearboxes. It is the responsibility of the person who issues the “aircraft Certificate of Release to Service” (CRS) to assess how critical is the maintenance task carried out so as to determine the need for an independent inspection. It must also take into account for this evaluation; knowledge on how experienced is the person who performed the tasks involved. Under AMC at § M.A. 402(a), “independent inspection” means an inspection carried out by a person other than the one that made the task to be checked.

However for airplanes less than 2730 kg that are not complex motorized airplanes, alternate solutions may be proposed for the approval of the authority (example: self-inspection, if not simply taking in the same order, the steps already completed, but including verification points that do not assume to know how was performed the task to be checked).

A special inspection shall be carried out after any flight safety sensitive maintenance task unless otherwise specified by Part-145 or agreed by the competent authority.



C. TERMINOLOGY

Flight time Definition Breakdown time since the aircraft starts moving towards the runway by means of its own power plant till the time it stops at the end of the flight.

Routine inspection Overall inspection or test of good jettisoning. It enables to check the good working order of an assembly of the aircraft without forcing to a removal.

Visual investigation or visual check It is one of the components of the above mentioned routine inspection. The aim is to ensure carefully that a given element is in good serviceable conditions. This investigation is carried out visually, “in situ”. Example: Search for cracks or corrosion.

Detailed inspection Consists in a complete examination of a part or an assembly with removal if necessary in order to detect defective parts and foresee which ones could lead to catastrophe.

Detailed investigation or detailed check It is one of the components of the detailed inspection. It consists in an accurate examination of an element either visually, after removal, or with the help of magnifying glass or the help of another means of investigation (dye-penetrant inspection, magnetic particle inspection, eddy current…).

Verification It is one of the components of both routine inspection and detailed inspection. It is an operation through which an element is checked to ensure its compliance, or state, possibly using a measuring instrument. Example: verification of the tension of control cables.

Bench test Complete operating test following removal of the equipment on a bench test in a workshop. It leads to establish technical records.

Operational test Operation only necessary to make sure that a system or equipment is in good working condition. These tests do not require any special equipment or any special installation other than those required on the aircraft (power supply). They must be comparable to those carried out by the operation crew.

Functional test This test is only used to ascertain that a system or component functions in every way according to the minimum acceptable specification in relation to the original design of the system or the equipment. This test can require a11itional ground equipment and must be more detailed and precise than operational test. The definition of this test must include all means necessary to conduct these tests allowing the possibility of maintaining the reliability of systems or equipment at an acceptable level. Requires a report to be done.

Calendar time inspection (aging inspection) Consists in a routine or detailed inspection depending on the maintenance operation table column, with calendar time interval, to detect defective parts or conditions due to aging (storage …).



Global Test Test using radiation, with no removal, by means of specialized benches.

Life Limit Time after which a life timed equipment must be replaced (example for radio: ELT batteries).

D. ABBREVIATIONS

ADF: Automatic Direction Finder

AD: Airworthiness Directive

CN: Airworthiness Directive (Consigne de Navigabilité)

DGAC: French authority (Direction Générale de l’Aéronautique Civile)

ED: Detailed examination (Examen Détaillé)

ER: Maintenance and repair (Entretien et Réparation)

EV: Visual investigation or visual check (Examen Visuel)

GSAC: French authority (Groupement pour la Sécurité de l’Aviation Civile)

h: Flight hours

IFR: Instrument Flight Rule

IRB: Radio equipment (Installation Radioélectrique de Bord)

OE: Maintenance facility (Organisme d’Entretien)

PB: Bench test (Essai – Passage – au Banc)

PH: Propeller time between overhaul (Potentiel Hélice)

PM: Engine time between overhaul (Potentiel Moteur)

RBDA: Emergency locator Transmitter ELT (Radio-Balise à Détection Automatique)

RG: Complete overhaul (Révision Générale)

ROS: Standing Waves Ratio SWR (Rapport d’Ondes Stationnaires)

SB: Service Bulletin

SL: Service Lettre

TAE: Thielert Aircraft Engines

TFAR: Time between servicing (Temps de Fonctionnement Avant Révision)

TG: Global Test (Test Global)

TL: Time between overhaul TBO (Temps Limite d’utilisation avant R.G.)

VA: One year interval inspection (Visite Annuelle)

VE: Condition check (Vérification de l’Etat)

VFR: Visual Flight Rules

VHF: Very High Frequency radio equipment

VL: Life limit (Vie Limite)



E. REFERENCE MAINTENANCE DOCUMENTS (latest issue): Maintenance of DR400 must be performed with document n°1001586 and following engine and propellers documents:

Document Reference

DR400 Maintenance manual Doc. 1001606 GB

DR400/500 Maintenance manual Doc. 1001870 GB

DR400 Service Bulletins (current issue)

DR400 Service Letters (current issue)

Lycoming Engine Service Bulletins (current issue)

Service Letters (current issue)

Service Instructions (current issue)

Operator’s manual O-235 and O-290 series 60297-9

Operator’s manual O-320 series 60297-30

Operator’s manual O-360 series, IO-360 60297-12

Propellers Operation and installation manual of various propeller manufacturers

Various

Note 1: The maintenance schedule of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-01 engine” (DR400/135CDI) comprises the following documents: - Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-01, Operation & Maintenance Manual TAE 125-01. - Doc. AMM-60-01, Supplement Airplane Maintenance Manual Robin DR400/135CDI –

TAE 125-01. - TAE Service Bulletins (SB) & Service Letters (SL) (current issue). - MT-Propeller Operation and installation manual (ATA 61-01-24 E-124) & current SBs. Note 2: The maintenance schedule of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-02-99 engine and installation of FADEC backup battery” (DR400/135CDI) comprises the following documents: - Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-02, Operation & Maintenance Manual TAE 125-02-99. - Doc. AMM-60-02, Supplement Airplane Maintenance Manual Robin DR400/135CDI –

CENTURION 2.0. - TAE Service Bulletins (SB) & Service Letters (SL) (current issue). - MT-Propeller Operation and installation manual (ATA 61-01-24 E-124) & current SBs.

Note 3: The maintenance schedule of DR400 fitted with STC EASA 10014219 “Installation of TAE 125-02-114 engine” (DR400/155CDI) comprises the following documents:

- Doc. 1001586, DR400 Airworthiness limitations & Maintenance schedule. - Doc. OM-02-02, Operation & Maintenance Manual TAE 125-02-99. - Doc. AMM-60-02S, Supplement Airplane Maintenance Manual Robin DR400/135CDI –

CENTURION 2.0S. - TAE Service Bulletins (SB) & Service Letters (SL) (current issue). - MT-Propeller Operation and installation manual (ATA 61-01-24 E-124) & current SBs.


Issue 5 – March 2013 of 36

F. OPERATING CHARACTERISTICS – BREAKDOWN OF HOURS.

This maintenance schedule is established for a more or less 500 hours annual flight hours. The hours applicable to life limit and periodicity are counted-down block – block (1st turn of wheel to final stop).

Cycles and landings may be taken into account in the follow-up of the airplane.

G. UPDATING OF MAINTENANCE SCHEDULE

Any modification to the maintenance schedule content must be recorded as an amendment showing the summary of the changes to the manual and the reasons of these changes.

This updating has to be done within one year from the decision of the requirements of the authorities or the recommendations of the manufacturer.



SECTION 2

TIME BETWEEN INSPECTIONS

The aircraft must be inspected in accordance with the interval of periodic inspection per table 1. The intervals of inspection may vary within the tolerances set.

Instructions and detailed procedures related to maintenance schedule are listed in section 6.The maximum periodicity of an inspection is marked by a dot () in the relevant column.

REMINDER: MAINTENANCE INSTRUCTIONS ARE NECESSARILY CUMULATIVE Example 1: a 500 h maintenance inspection shall include instructions planned at 50 h, 100 h and 500 h. Example 2: a 3 year maintenance inspection shall include instructions planned at 1 year and 3 years.

For maintenance operations listed as routine / or detailed and with calendar time, the calendar time inspection must only be performed if no routine or detailed inspection has been performed within the calendar time interval. Example: for operation « item 25.20 », the one year interval inspection will be performed only if 100 hour routine inspection has not been done within the one year interval.

Tolerances A certain amount of tolerance is given in which to perform inspection operations, to enable a more flexible use of the aircraft. Thus, inspections related to aircraft operation may be made to coincide with calendar type inspections. Note: Permissible tolerances cannot be cumulated. Example: if a 100 h inspection is performed at 110 h, this same inspection cannot be subsequently performed at 220 h but only after a maximum of 210 h. Therefore, such tolerances cannot lead to eliminate one 100 h inspection out of ten.

Table 1: interval of periodic inspection

OPERATION PERIODICITY TOLERANCE

50 h 50 hours 10 h

100 h 100 hours 10 h

500 h 500 hours 30 h

1000 h 1000 hours 30 h

2000 h 2000 hours 30 h

1 year 1 year 1 month

3 years 3 years 2 months

6 years 6 years 2 months

Note: The tolerances apply neither to the airworthiness limitations, nor with the airworthiness directives, unless otherwise specified.



Weigting

Refer to Aircraft flight manual, maintenance manual….

First interval: 5 years. A weighing form with inventory is to be filled out.

Time between two weighings shall not exceed 60 months. It is tolerated that this expiry is deferred to the 1st grounding of the airplane for planned inspection occurring immediately after 60 months (cf. fascicule GSAC P-61-10).

Weighing must be carried out:

- after:

> a major modification

> a major repair

> a main conversion of interior equipment

> complete painting of the aircraft.

- each time a modification insufficiently precise of the condition of the aircraft does not allow the update weight and balance record by a simple calculation.


Issue 5 - March 2013 amendment 5 dated June 2014 of 36

SECTION 3

COMPONENTS AND EQUIPMENTS MAINTENANCE, USE AND STORAGE PRACTICES

The overhaul of the engines, propellers, components and equipment and the other maintenance inspections to be carried out apart from the routine intervals are carried out in accordance with the indications described in table 2.

Refer to manufacturer’s documentation at latest issue for engine and propellers.

Table 2: Various particular checks

Components with life time

DESIGNATION REFERENCE LIMIT Note 1

INTERVENTION OBSERVATIONS

REMARKS

Air filter (foam) 56.18.08.015 100 h / 1 year To exchange Serial no. > 2209 Model> year 1992

note 2

Air filter (cartridge)

56.12.59.010 56.23.02.200 56.28.10.200 56.11.13.000 57.34.00.010

200 h / 1 year To exchange Serial no. < 2210

note 2

Instrument panel vibration isolators

2000h / 10 years To exchange

Ducts (engine surrounding)

CEAPR (see catalogue)

10 years To exchange

Elastomer flexible line


10 years To exchange Excepted teflon

Vacuum system suction hoses


10 years To exchange

“Flûtes” and “1/4 d’onde” exhaust silencer elastometric mountings


500 h / 5 years To exchange

Filter of the suction regulator (vacuum system)

100 h / 1 an To exchange

AIRBORNE Mandatory

Service Instruction.

Service Letter 59

Control gyro air filter of vacuum system.

500 h / 1 year To exchange

AIRBORNE Mandatory

Service Instruction.

Service Letter 59


of 36 amendment 5 dated June 2014 Issue 5 - March 2013

DESIGNATION REFERENCE LIMIT INTERVENTION OBSERVATIONS

REMARKS

Aileron and flap deflection blocks (if wooden made only).

1000 h / 3 years To exchange

Seal bead (ceramic) on 4-into-1 exhaust system

50 h To exchange

Towing cable (MAAG)

1 year To exchange

ELT KANNAD 406 AF-COMPACT

6 years

Battery pack to replace and

associated tests to perform

Doc 08038E Ref. 0145599E

Installation manual Operation manual

ELT KANNAD INTEGRA AF

6 years

Battery pack to replace and

associated tests to perform

Doc 09081C Ref. 0146259C

Installation manual Operation manual

GADRINGER harness

79.40.07.000 12 years To exchange

Note 1: the tolerances of table 1 of section 2 apply to limits of above table 2. Note 2: dusty conditions: replacement of filter every 50 hours.

Radio-navigation equipments:

Refer to national regulation of the country in which the airplane is registered.

On-board instrumentation Maintenance “on condition” unless otherwise specified by instrument maker. Additional instructions

DESIGNATION REFERENCE LIMIT INTERVENTION OBSERVATIONS

REMARKS

Magnetic compass ////////////////////// 2 years Compass swinging Compass swinging

everytime radio installation is modified

Tachometer ///////////////////// 3 years or 1 year for IFR

Control ////////////////////////////

SAM MD302 standby instruments module

//////////////////// 6 years Battery to replace Mid Continent Manual

number 9017782

POSSIBLE POSTPONEMENT OF MAINTENANCE OPERATIONS AND SERVICE INTERVALS OF THE EQUIPMENTS OR AIRPLANE SUB-ASSEMBLY

For airplanes registered in France, refer to OSAC document: Procédure P-04-00 « Autorisations exceptionnelles dans le domaine de la navigabilité ».

For other countries (airplanes not registered in France), refer to national regulation.



SECTION 4

SPECIAL MAINTENANCE INSPECTIONS

This section provides the special inspections of an aircraft following abnormal events such as:

After:

Overweight landing. Landing on unapproved runway,

Flight in excessive turbulent atmosphere,

Flight in hail,

Engine or propeller limits exceeded,

Aircraft limits exceeded,

Too high and gusty wind conditions (effects on control surfaces, etc.),

etc.

In the demonstrated lack of manufacturer's recommendation or instruction developed in the maintenance schedule, the aircraft that has encountered an exceptional event will not be airworthy any longer and inspection procedures for the return to service of the aircraft shall be developed, approved and carried out before further flight.

Any person who performs maintenance work has to use the methods, techniques, practices, parts, materials, tools, equipment and test equipment recommended by the manufacturer.

It is recommended to draw one’s inspiration from document: Advisory Circular AC 43.13 « Acceptable methods, techniques, and practices – Aircraft inspection and repair ». This section is intended to clarify the requirements for the inspection of aircraft after abnormal events; there is also general advice on how to perform these inspections. Aircraft Certification specifies their use within certain limits which determine so-called normal operating. In the case of exceeding these limits due to abnormal operating conditions, or that the aircraft was at risk or constraints for which it was not designed, the integrity of the structure or the good operation of the engine and of its systems may be compromised. In the presence of any indication or evidence that the limits have been exceeded, or the aircraft has been damaged, an inspection of the aircraft must be performed to ensure it is still airworthy. The following paragraphs provide an overview of the inspections required after some of the more frequent abnormal operating conditions. The procedures described are not intended to be exhaustive and do not assert to consider all possibilities. It is the person performing the inspection duty to assess the circumstances of each case and decide on appropriate action. In case of doubt, one will contact the manufacturer or the competent civil aviation department. It is normally expected that the inspections described in this section are carried out by a qualified mechanic. It is even common that only the pilot of the aircraft is able to assess the severity of the incident or there is nobody else who can decide what action to take. To take



into account situations where the services of a mechanic are not available, it is recommended that the following procedure be applied. Abnormal operating conditions, including, without limitation, those described in this section, must absolutely be recorded in the log book. Wherever possible, the registration should give an idea of the seriousness of the incident. An inspection of the aircraft will then have to be performed before the next flight; it will preferably be carried out by a mechanic with the appropriate qualifications. If it is impossible to obtain the services of a mechanic, the pilot of the aircraft will perform the inspection. In this case, the inspection will necessarily be limited to areas which are not subject to the issuance of a certificate for return to service after maintenance, that is to say, the inspection does not require disassembly of parts. If the pilot feels that the aircraft is in a satisfactory condition for the intended flight, it shall make an entry to that effect in the logbook, so a full inspection takes place upon return of the aircraft. The pilot will then take the planned flight or the flight segments until it reaches the facility where the remaining steps of the inspection can be made. No special flight permit is required in the circumstances. On the first occasion, the mechanic, with appropriate qualifications, shall inspect and approve the aircraft for return to service. If, to the opinion of the pilot, the aircraft is not airworthy, or if the severity of the incident is such that its airworthiness is questionable, even after a satisfactory preliminary inspection, the aircraft shall then be inspected by a mechanic who will sign the approval for return to service after the inspection, so that the airplane can resume its flight. In the following paragraphs, no distinction is made between actions that may be part of the preliminary inspection by the pilot and the actions taken by the mechanic. If there is any doubt as to the airworthiness of the aircraft, take off will not be allowed before the mechanic has signed approval for return to service after maintenance. Hard or overweight landing.

The landing gear of an aircraft is designed to withstand the impact of landing within certain weight limits and at a given rate of descent. Exceeding one or the other of these parameters during a landing will almost certainly damage the landing gear or its supporting structure. Landing gear may also suffer excessive stress when the airplane lands drifting, so that the front or tail wheel touches the runway before the main landing gear for example. However, if it is known or suspected that there was a hard landing, consult the flight crew to determine the landing conditions and whether the pilot heard noise characteristics of a structural damage. Damage caused by a hard landing primarily affects the landing gear and its supporting structure in the wing or fuselage, as well as the wing-to-fuselage connection points, the engine mount and attachment. Secondary damage can occur to the structure and the upper and lower surfaces of the fuselage, as well as the structure and wing skin, depending on the configuration and load of the aircraft. Because of the many factors involved, it would be impossible to give detailed instructions on how to perform the inspection, it varies depending on the type of incident and the aircraft type. However, preliminary inspection made after the incident should normally cover the following points:

Landing gear Remove the fairings. Check tires for creeping on wheel, flat, bumps, cuts, loss of pressure and any abnormal

dilation



Check the wheels and brakes for leaks, cracks or other damage; Inspect axles and torque links to check if they are bent or damaged; Check oleo struts for leaks and other; Detailed inspection of the undercarriage attachment and of adjacent structures by

looking for cracks or other damage and checking for play; this inspection may require removal of critical fastening bolts to allow to perform meticulous non-destructive testing;

Inspect structural elements adjacent to the attachment points of the undercarriage, looking for cracks, deformations, rivets or bolts showing play;

Inspect access doors and fairings to check if they are damaged or distorted; Jack airplane; have the nose wheel steering mechanism operate. Make sure of the easy sliding of the gear shock strut (after deflation, put a hose on the

valve not to lose hydraulic fluid).

Wings, fuselage Inspect extrados and intrados wing skin for damages; Search for traces of seepage or leakage of fuel at the wing tanks; Inspect the wing-to-fuselage junction fairings for cracks and signs of having moved; Make sure that the flight controls move freely and with full deflection; Inspect the balancing weights, the support of flight servo-unit; look for cracks on the

brackets and joints of the control surfaces and make sure that the control surfaces are free of damage and they do not jam in operation;

Inspect the fuselage skin for wrinkling or other damage; Make sure that emergency devices are not activated (Emergency Locator Transmitter); Check for deformation of pipes and ducts, or if they are leaking;

Engine Make sure that the engine and propeller controls move freely and with full travel; Inspect the engine mount and supports and make sure they are not damaged nor

distorted; check the tubular frames ensuring that they are not bent nor show cracked welds; check attachment bolts for damage or play;

Make sure rotary assemblies move fully free. Sparking plugs must be removed to make sure that propeller and inner parts of the engine rotate or move freely;

Inspect engine cowlings for wrinkling or distortion and make sure fasteners are in good condition;

Check for evidence of oil leakage, fuel leakage or hydraulic fluid leakage ; Inspect the battery support and attachments; Check proper alignment of the propeller shaft.

Tail assembly Make sure control surfaces move freely; Look for cracks in the joints of the rudder and stabilator; inspect the control surfaces for

cracks and distortion, particularly around the balance weight supports; Inspect the attachment points and fairings of the stabilizer, as well as the trim system

and its supports; make sure there is neither distortion nor play.

Structure - Skin Check the surface of the wing at the spar (integrity of trailing edge at wing rib no. 8

when moving the wing tip, signs of broken sticks, peeling of plywood, torn rib lacing knots etc.).

Inspection of the attachment of the stabilator bearings (peening, bruising of wood).



Propeller Inspect spinner and blades ends for shocks

Ground runs If the inspection has revealed no major structural deformation, then a ground run can be performed to make sure all systems and controls are working properly. It will include a general check for leaks, engines running. Flight through severe turbulence

Damage that can occur to an aircraft flying through turbulence are of the same type as the damage caused by a hard landing, except that they will be more evenly distributed and that the landing gear, wheels and brakes are likely to remain intact . During a flight in such conditions, the aircraft structure is subjected to sudden acceleration or transverse vertical, the effects of these can be multiplied by the inertia of the heavy components such as engines, fuel tanks. We can then expect that damage occurs to the main attachment points, including wing-to-fuselage or tail-to-fuselage attachments, as well as engine-to-cell attachment. Damage can also occur in parts of the wings, of the fuselage, of the stabilizer or of the control surfaces where the bending moment is at maximum, roughly half length thereof; deformation thus caused will result in wrinkle coating or cause other damage of this kind. The inspection performed after a flight turbulence report should include the "hard or overweight landing" inspections except, in most cases, the steps involved in the inspection of the landing gear. In all cases:

- Detailed inspection of the engine mount attachments - Visual inspection of all control surfaces, of their bearings and control levers. - Check the free movement of flight controls throughout their operating range. - Make sure of the proper sliding of the canopy (condition of rails).

Further dismantling and, in some cases, removal of parts of the coating may be necessary to permit inspection of the support structure in areas where there has been damage to the coating

Speed limits or load factor exceeded

In cases where it is reported that the aircraft has exceeded its approved speed limits or load factor, the inspection required is the same as that specified for a flight through severe turbulence. In cases where the exceeded limit applies to a given configuration, e.g. lowering limits of the flaps, the required inspection may then be limited to areas of the cell that were affected.

Incidents related to a burst tire If a tire burst during taxiing, takeoff or landing, fragments of the tire can damage parts of the aircraft which are in line with the wheel disc. Damage may also occur due to the fact that the wheel rolls on a paved runway and it transmits shocks to the leg of the landing gear and its supporting structure.



In most cases, the wheel concerned will be repaired or put out of operation. In addition, the following checks should be performed: Inspect the other wheels, the tire of which did not burst ; Inspect the brakes of the landing gear involved and look for signs of damage. The

cause of the burst can be overheating brakes that were not loose enough; it will then be necessary, when replacing the wheel, to pay a special attention to the condition of operation of the brakes, especially in regard to the frictionless rotation of the wheel, once the brakes are released;

examine the leg of the landing gear in question, including pipes and hydraulic hoses, looking for signs of damage or leaks of hydraulic fluid;

Inspect the supporting structure and the attachment points of the leg of the landing gear, looking for cracks, warped panels or loose rivets. In some cases, it may be required to remove some critical resistant structural support bolts in order to proceed to non-destructive testing;

Inspect the adjacent parts of the wing skin or of the fuselage for evidence of damage.

Strong wind or jet blast

Aircraft parked can be significantly damaged by strong wind or by the blast produced by a jet or propeller of other aircraft taxiing or performing a ground run in the vicinity. Small aircraft are particularly vulnerable to this type of damage that may be caused by the blast itself or by thrown debris. Following such incidents, inspect the aircraft as follows: Check control surfaces for deformation or other signs of internal damage. Control surface deflections; Flight Controls: make sure of the free movement of controls, inspect the cables at

pulleys level, check stops, inspect joints (lever and bell crank). Check whole cell, including windshields, for impact damage such as chips and marks,

and check if the engine air inlets, cooling ducts, etc. contain debris; If the blast was strong enough to move the entire plane, the need to conduct an internal

inspection to discover structural elements damaged, or a verification of symmetry of the whole aircraft, or both must be considered.

Landing gear: inspect the landing gear struts for deformation, crack initiation. Check the condition of axles. Inspect landing gear attachments to the fuselage and the wing. Check the condition of tires.

Bad fuelling

This kind of incident includes refueling with contaminated fuel. When it is realized that an aircraft tanks were filled with contaminated fuel or with fuel a degree inadequate, it must be determined if the fuel has already reached the engine. If by chance the problem is detected before the fuel reached the running engine, it is enough to drain all the fuel with care. To this end, the aircraft (or tanks concerned) will be emptied of all the fuel, making sure that the tanks are arranged so that the drain outlet is located at their lowest point. After draining and once the tanks are filled with clean fuel, finally supply lines must be cleaned and the engine operation checked by performing a ground runs. If the engines were supplied with polluted fuel, applicable corrective actions depend on the type of engine and type of pollution. One must refer to the maintenance manual and the



certification of the type of engine concerned or to the data sheets of the type certificate for additional details.

Significant change in climatic conditions

Check the tension of the flight control cables at each significant change of climatic conditions (temperatures).

Salty or tropical atmosphere

Close inspection for corrosion of all metal part every year.

Shock on propeller

Refer to AD 2004-10-14. Refer to propeller manufacturer document.

Impact on the leading edge of the wing

Damage to the wings of aircraft made of wood and fabric very often require repair. It was noted that further damage outside the impact area exposed, could often be caused to the structure of the wings. Therefore, in the context of flight safety, when a shock on the leading edge of the wings causes damage requiring repair, it is recommended to completely remove covering of the wing affected by the incident. This covering removal should allow a thorough inspection of the wooden structure and glued joints to make sure of the integrity of the wings before a return to service of the aircraft. Depending on how important is the shock, the wing main spar deforms to the rear in a flexion / torsion in the horizontal plane which can cause secondary cracks sometimes appearing at a certain distance from the main damage. If the spar exceeds the elastic limit, following the impact, the damage is transmitted to the spar itself. Cracks are formed in the grain direction of the plywood coating at the extrados and/or extrados (45 °) and more rarely against the direction of the fibers at the splice scarf joints of the plywood. Unsticking between the spar caps and the upper and lower surface coatings may also occur. In the case of an impact on the leading edge of an aircraft wing with a dihedral (aircraft type: Jodel, DR ...) a visual inspection allows, firstly, to measure the deformations at the dihedral rib tail by inspecting the lower and upper fabric at this level. If internal failure, the fabric relaxes with the deformation of the ribs rods.

Repair: Any repairs that would not have been already approved must be the subject of a record of repair submitted to EASA for approval.



SECTION 5

CONTROL FLIGHT

Control flights must be carried out at the end of the achievement of certain maintenance operations; the cases of current liability and the methods of their execution are defined below.

1. Case of liability

1.1. Complete control flight (see paragraphs 3 & 4)

A complete control flight consists of:

checking aircraft general performance as laid out in flight manual (take-off, climbing, and bearing) and the correct operation of various systems.

And,

carrying out procedures which do not usually apply to flight operations (especially emergency procedures).

A complete control flight shall be carried out:

after a 2000 h / 6 year inspection,

or

after major repairs following an accident unless an exemption was obtained when approval of the repair.

1.2. Abbreviated control flight

An abbreviated control flight only consists of checking some aircraft system functions that are directly or indirectly related to the work carried out.

An abbreviated control flight must be carried out when, at the completion of a maintenance operation, a ground test is not sufficient to make sure the airplane is operating correctly, specially:

after an intervention on the flight controls, except exemption after demonstration, planned in the maintenance schedule accepted by the qualified services, or



after replacement or reinstallation (*) of the engine (except for single engine fitted with fixed pitch propeller. An exemption can however be obtained from the qualified services, for the aircraft maintained within an approved framework, when it was shown by at least two consecutive control flights that the operations of replacement or reinstallation were carried out in a fully satisfactory way; the demonstration of reinstallation is worth only for the reinstallation; no exemption can be granted for a replacement relating to more half of the engines installed; or

when, after a design change or a repair of the aircraft, the need to carry out a control flight is stated in the design change file or approved repair file or

for the radio installations, after a maintenance inspection which required demounting and the bench test of the equipment, or after a routine inspection by the method known as of “global test”.

(*) Replacement is the removal of an engine followed by the installation of another engine, and reinstallation is the removal and reinstallation of an engine to its original position without any major intervention (such as the replacement of module) being carried out on this engine.

2. Remarks

At each control flight, check the carbon monoxide CO ratio during climb and during cruise. The CO ratio should permanently be lower than 50 ppm. Use an electronic portable CO detector with 1 ppm resolution. During measurements, take the precision of the detector into consideration.



A. DR400/135 CDI or DR400/155CDI reception / in flight control record

CEAPR DR400/135 CDI or DR400/155 CDI reception / in flight control record

Flight data Date Model Regist. Serial nr Location Pilot Mass / C QFE ZP Temp. Wind

Fuel on board Left hand Main Right hand Sup. LH Sup. Rear Sup. RH Total

Flight time Dep. Park. Take off Landing Ret. Park. Time Total

Flight 1

Flight 2

Flight 3

Engine S/N: RPM prop % power MAP P rail TH2O T oil P oil T gear Fuel flow T ecu A T ecu B

After start-up

Take-off

Climb FL 30

Climb FL 60

Cruise full throttle FL 50

Cruise 72% FL 50

Idle

Speeds Stall Cruise High speed

Trim mini Warning Stall PG 72% Adjustments VFE VNE OBS

VS 1 Vi = Vi = Ball Ailerons

VS 0 T° = T° = RPM:

Accessories and equipment

Painting aspect Fuselage Elevat. Rudder RH Flap RH

Aileron RH wing Cowlings Spinner LH wing LH Flap LH Aileron

Lights Nav lights Strobe Taxi light Ldg light

Flight controls Ailerons Elevator Rudder Elev. Tab Rud. Tab PA

Engine controls Throttle Mixture Carbu Propeller Friction Alt Air Cut. Mag Cut. Rich

Engine Instruments Oil Pr. Oil T° Cyl. T° Carb. T° EGT PA FF fuel Pres RPM Amp. Volt.

Brakes and gears LH Brake RH Brake Park. Straight ahead Steering Gnd Clear. Fonc. TR Sec. TR

Electric power supply Charge Voltage Breakers Regul. Alternat.

Instrument panel Painting Placards Markings Inst. Light Cab. Light Light test Shock m. Hourmeter Suction

Flight instruments Air speed Alti 1. Alti. 2 Vert. speed Ball ind. Horiz. 1 Horiz. 2 Dir.Gyro HSI Inst. Pan. Ind Compass

Avionic VHF 1 VHF 2 VOR 1 VOR 2 ATC MKR DME GPS ADF ILS

Listening Loud Speak Mike 1 Mike 2 Headph. 1 Headph. 2 Intercom ELT

Fuel LH gauge Pres. Sens. RH gauge Aux. LH Aux Rear Aux. RH Select LP warn LL warn

Seats Harnesses Belts Adjust. Fasten.

Air conditioning LH air vent RH air vent Defrost. Front heat. Rear Heat.

Canopy Sliding Latch Plexi Sun shield Tightness Jettison.

REMARKS CORRECTIVE ACTIONS VISA

Visa of reception pilot after corrective actions completed:

Formulaire 087-0A

Check the carbon monoxide CO ratio during climb and during cruise. The CO ratio should permanently be lower than 50 ppm. Use a portable electronic CO detector with 1 ppm resolution. During measurements, take the precision of the detector into consideration.



4. Complete control flight program – Lycoming engine

C.E.A.P.R.

Flight data Date Model Regist. Serial nr Location Pilot Mass / C QFE ZP Temp. Wind

Fuel on

board Left hand Main Right hand Supp. Rear Total

Flight time Dep. Park. Take off Landing Ret. Park. Time

Flight 1

Flight 2

Flight 3

Moteur Oil pres. Oil Temp. Cyl. Temp. Carb. Temp. Fuel Pres. RPM

Manifold

Pres. Fuel Flow Carb. Heat Mag. 1 Mag. 2

After start-up

Run up

1800 rpm

Take off

Climb

Cruise full

throttle

Cruise 75%

Idle

Speeds

Trim mini Warning Stall PG 75% VFE VNE OBS

VS 1 Ball Ailerons

VS 0 RPM:

Painting aspect Fuselage Elevator Rudder RH flap RH aileron RH wing Cowlings Spinner LH wing LH flap LH aileron

Lights Nav lights Strobe Taxi light Landing light

Flight controls Ailerons Elevator Rudder Elevator tab Rudder tab PA

Engine controls Throttle Mixture Carbu Propeller Friction Alt. air Cut. Mag Cut. Mixture

Engine instruments Oil pres. Oil Temp. Cyl. Temp Carb. Temp. EGT PA FF Fuel Pres. RPM Amp. Volt.

Brakes and gears LH Brake RH Brake Park. Straight ahead Steering Gnd Clear.

Electric

power supplyCharge Voltage Breakers Régul. Alternat.

Instrument

panelPainting Placards Markings Inst. Light Cab. Light Light test Shock m. Hourmeter Suction

Flight

instrumentsAir speed Alti 1. Alti. 2 Vert. Speed Ball indic. Horiz. 1 Horiz. 2 Dir. Gyro HSI

Turn & bank

indic.Compass

Avionics VHF 1 VHF 2 VOR 1 VOR 2 ATC MKR DME GPS ADF ILS

Listening Loud speaker Mike 1 Mike 2 Headset 1 Headset 2 Intercom ELT

Fuel LH gauge Press. Sens. RH gauge Aux. rear Select LP Alarm LL Alarm

Seats Harnesses Belts Adjust. Latch.

Air conditioning LH air vent RH air vent Defrost. Front heat. Rear heat.

Canopy Sliding Latch Plexi Tightness Jettison.

VISA

Reception / in flight control record

DR 400 - Lycoming

Temps de vol total

Stall Cruise High speed

Adjustments

Accessories and equipment

REMARKS CORRECTIVE ACTIONS

Formulaire 087-0B

Visa of reception pilot after corrective

actions completed: Check the carbon monoxide CO ratio during climb and during cruise. The CO ratio should permanently be lower than 50 ppm. Use a portable electronic CO detector with 1 ppm resolution. During measurements, take the precision of the detector into consideration.



SECTION 6

MAINTENANCE OPERATIONS TABLE

Following notes are related to right hand column of the maintenance operations table. Note 1: Refer to Lycoming documentation (operator’s manual, SB, SL SI…).

Note 2: Dusty conditions: cleaning of the filter element every 25 flight hours.

Note 3: Refer to the relevant maintenance manual issued by the manufacturer of the magneto.

Note 4: If the aircraft is equipped with a carbon detector (stuck inside the cabin), the removal of the exchanger will occur every 500 hours.

Note 5: The overhaul of the starter is linked to the general overhaul of the engine: refer to the latest issue of SI n°1157 Textron-Lycoming.

Note 6: Refer to the latest issue of the propeller Owner’s manual and to instructions (refer to section 1, §F).

Note 7: Before filling the oleo strut with hydraulic fluid, check the travel of the sliding leg.

Note 8: Cleaning of the fuel filter needs to shut off the fuel cock: test its efficiency.

Note 9: The fuel cock is to be disassembled only in an approved workshop.

Note 10: Refer to the manufacturer’s documentation depending on the equipment of the aircraft.

Note 11: Alternator belt: refer to Textron-Lycoming SI n°1129.

Note 12: Refer to section “Special maintenance inspections”.

Note 13: For DR400/140B equipped with STC EASA. 10014219, refer to Operation &

Maintenance Manual TAE and/or Supplement Airplane Maintenance Manual (refer to section 1, §F).

Note 14: Not applicable to DR400/140B equipped with STC EASA. 10014219.

Note 15: Serial number > 2209

Note 16: Serial number < 2210

Note 17: Serial number < 2216

Note 18: « flûtes » Option

Note 19: Silencer « APR » Option

Note 20: Refer to SB 020602 DR400 – Elevator – Anti-tab – Inspection procedures

Note 21: Refer to SB 169 Brake fluid reservoir cap

Note 22: DR400/160 and DR400/180: model before 1988.

Note 23: Removal of wheel and gear leg fairings shall be done every 50 hours after using the airplane on grass airfield.

Note 24: Operation shall also be done when exchanging the tires.

Note 25: Concerns luggage compartment door with part number 28.18.46.010. Aircraft serial number from 2210 on.



Note 26: Refer to SB 031104. 6 years or at least before the end of the engine life limit, whichever comes first.

Note 27: Refer to mandatory Service bulletin Lycoming no. 480 at latest issue.

Note 28: Refer to mandatory Service bulletin 120205

Note 29: In the event of significant use on surface coated, dusty or degraded (area start-up,

fixed point, taxiiage, take-off and landing in grass, sand, dirt or any surface in hard not maintained), the operation is to be carried out every 50 h.

Note 30: Only for aircraft fitted with electrical rudder trim P/N 32.18.00.000 (mounted on aircraft

after 1992). For other electrical rudder trim, the operation is to be carried out every 50 h.

Maintenance operation table

The maintenance operation table is the subject of the following annex.

Models concerned X: applicable O: option

Doc. 1001586GB ANNEX


DR 400 Maintenance schedule

Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

21 0 X X X X X X X HEATING AND VENTILATINGl l l l l l l l

ME1001606, sec13

ME1001606, sec16, §16-10

21 10 X X X X X X XHeating: Check tightness of heating installation,

especially in the vicinity of heat exchangerl l l l l l l l 13

21 20 X X X X X X XCheck flexible ducts and clamps. Check

attachment byside engine controlsl l l l l l l 13

21 30 X X X X X X XClose examination of the hot air distribution box,

flexible controls. Test for good operating.l l l l l l

21 40 X X X X X X X

Ventilation: Check state of flexible ducts,

proofness of duct and plastic inlet bonded along

fuselage aft sides. Test of aerators.

l l l l l

21 50 X X X X X X XCheck cleanliness of lateral intake vent holes

and cabin air ventsl l l l l l l

21 60 X X X X X X X

Rear passengers ventilation: removal of the

aerators and close examination of the expansion

box (moisture, rotten areas, lack of protective

paint, etc.).

l l l l

21 70 X

Close examination of flexible ducts of the rear

passenger ventilation: from the fin root air inlet to

the expansion box located under the fuselage

arm-rest.

l l l l l l l

l l X X X X X X X l l l l l l l l l l

23 0 X X X X X X X RADIO-NAV EQUIPMENTl l l l

l l l10

ME1001606, sec15

23 10 X X X X X X XClose examination of antennas, bases and fixing

elements.l l l l l

23 20 X X X X X X X

Inspection of each coax-cable on all the length,

particularly when crossing bulkheads and

attachments.

l l l l l

23 30 X X X X X X XDetailed examination of radio racks and fixing

(search for cracks etc.).l l

23 40 X X X X X X XTest of Emergency Locator Transmitter. Check

attachments.l l l l l l l


24 0 X X X X X X X ELECTRICAL POWERl l l l l l l l

ME1001606, sec12

ME1001606, sec16, §16-9

24 10 X X X X X

Battery: detailed inspection of the battery in

order to detect possible leaks. Particularly check

around terminals.

l l l l l l l 13

24 20 X X X X X

Remove the battery and check the support

frame, the fixing area of the firewall (seek for

corrosion signs, cracks, defective fixing). Verify

the battery charge. Check electrolyte density and

level. Clean and protect the terminals with

grease.

l l l l l l l13

ME1001606, sec12, §12-1

24 30 X X

Battery: detailed inspection of the battery in

order to detect possible leaks. Particularly check

around terminals.

l l l l l l l ME1001606, sec16, §16-9

24 40 X X

Remove the battery and check the support

frame, the fixing area of the firewall (seek for

defective fixing, glue cracks…). Verify the battery

charge. Check electrolyte density and level.

Clean and protect the terminals with grease.

l l l l l l l ME1001606, sec16, §16-9

24 50 X X X X X X X

Close examination of master relay and starter

relay. Ensure that contacts are well-protected

with insulator caps. Check attachment to firewall.

l l l l ME1001606, sec12, §12-3

24 60 X X X X X X XCheck all electrical wires (burn traces, wear).

Check for efficient attachment.l l l l 13

24 70 X X X X X X X Check alternator belt tensioning. l l l l11, 13

Textron Lycoming SI 1129

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Issue 5 - march 2013 Page 1 Amendment 7 April 2015




Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

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24 80 X X X X X X XRemoval of the alternator. Check ball bearings,

brushes, collector, attachments, diodes.l l l 13

24 90 X X X X X X X

Into cabin and fuselage

Detailed inspection of electrical wires over

complete length (behind instrument panel,

behind upholsteries, inside the fuselage…),

removing parts to allow access.

l l l

24 100 X X X X X X X Verify the good operating of cabin lights. l l l l l l l

24 110 X X X X X X X

Verify the good operating of wingtip

position/strobe lights, landing and taxi lights,

anticollision lights, rotating beacon. Check

glasses and fixing elements.

l l l l l l l

24 120 X X X X X X X Check presence of spare fuses. l l l l l l l 14

24 130 X X X X X X X

Check for good operating conditions the voltage

regulator and the charge drop warning light. l l l l 13


25 0 X X X X X X X SEATS l l l l l l l l ME1001606, sec14

25 10 X X X X X X XCheck sliding of each seat and locking

mechanism.l l l l

25 20 X X X X X X X Grease the locking mechanism. l l l l l l l

25 30 X X X X X X XDetailed examination of the fixing elements (seat

on structure).l l l l

25 40 X X X X X X XBending test of the back of the front seats in

order to point out possible cracks.l l l l

25 50 X X X X X X XRemoval of bottom cushion and visual

inspection of frame tubes for cracks.l l l

25 60 X X X X X X X

Seat belts or harnesses:

Close inspection of belts or harnesses. Check

anchor bolts.

l l l l l l l

25 70 X X X X X X X Check buckles for good operating. l l l l

25 80 X X X X X X X Test of the inertia reel safety belts operating. l l l l l l l

25 90 X X X X X X X

Upholsteries: check state of upholsteries,

attachments, particularly in rudder bar travel

area as well as in the seat slide control

mechanism.

l l l l l l


27 0 X X X X X X X FLIGHT CONTROLS l l l l l l l l ME1001606, sec6

27 10 X X X X X X XCheck all flight controls for free operating from

stop to stop (stabilator, rudder, ailerons)l l l l l l l

27 20 X X X X X X XEnsure that there is no abnormal play in the

controls.l l l l

27 30 X X X X X X X

Check the good operating of the elevator trim

control from block to block when stick is full nose

down and full nose up.

l l l l

27 40 X X X X X X XIndex guide tube: look for friction points and

marks of perforation in the elbowsl l l

27 50 X X X X X X X Verification of the control cable tensioning. l l l l l l l12

ME1001606, sec6, §6-1

27 60 X X X X X X XVisual inspection of pulleys, supports, cable

guides.l l l

27 70 X X X X X X X

Release the tension of cables and check them

for wear at each contact zone (pulleys, guides):

no damage acceptable. Visual examination of

the pulleys, test of rolling.

l l l l lFlight safety

sensitive !

27 80 X X X X X X XRemoval of all cables and check over complete

length: no damage acceptable.l l

Flight safety

sensitive !

27 90 X X X X X X X

Visual inspection of rudder bars, bearings, dual

control column sticks, dual control rods,. Check

the good condition of rod end bearings and axles

(crack, corrosion).

l l l l l

27 100 X X X X X X X

Removal of rudder pedals to check fixing axis of

rudder cables and of front wheel guide (link rod).

Replacement of the fixing screws of the rudder

pedals bearings.

l lFlight safety

sensitive !





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

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27 110 X X X X X X X

Mechanical control: Detailed examination of the

elevator trim mechanism including control gear

box, control flexible shaft, rigid sleeve. State of

slides, axles, attachment parts, spherical joint of

the deflection control system.

Electrical control: visual inspection of system,

check good condition of axles and actuator

cylinder. Visual inspection of attachment parts

and pyramid structure, actuator's attachment

points.

l l l l l

Ref & MM

Flight safety

sensitive !

27 120 X X X X X X X

Detailed examination of the flap root rib. Make

sure the fastening rivets of the rib (equipped with

floating anchor nuts) are in good condition.

l l20

BS 020602

27 130 X X X X X X X

Inside the cabin, remove the plastic beautifier in

order to carry out a detailed inspection of the flap

control mechanism. Condition of axles, safety-

pins, no crack, no wear on the “lock-in position”

aluminium plate.

Electrical control: visual inspection of system,

check good condition of axles and actuator

cylinder.

l l l l l l lFlight safety

sensitive !

27 140 X X X X X X X

Detailed examination of the control rod located

under the wings. State of bearings, swagings

corrosion, wear.

l l l l l l lFlight safety

sensitive !

27 150 O O O O O O OCheck the cable for good rolling-up when the

rudder trim is operatingl l l l l l l 30

27 160 O O O O O O O

Rudder trim. Check the route of the cables

around the pulleys. State of pulleys, axles,

presence of the safety screws (preventing

cables from sliping out of the pulleys).

l l l l l l l

27 170 O O O O O O OAutopilot. Check state of the servo: fixings, servo

cable to control cable attachment.l l l l l l l

27 180 X

After removal of the central fairing and cabin

protection, close examination of the flaps control.

State of axles, presence and efficiency of the

safety pins. Good operating of the electro-

mechanical control. Check of attachments.

l l l lFlight safety

sensitive !

27 190 O O O O O O OAutopilot. Verification, adjustment of the friction

clutch of the servosl l

Flight safety

sensitive !


31 0 X X X X X X X AIRSPEED CIRCUIT l l l l l l l l ME1001606, sec10

31 10 X X X X X X X Cleanliness of the pitot and static pressure linel l l l l l l

29

31 20 X X X X X X X

Inspection of the static line (route, fixings,

crushing). ll

l l l l l

31 30 X X X X X X X

Check state of the pitot line, fixings and tubes

fitting. l

l

l l l l l

31 40 X X X X X X X Detailed inspection of fixings and dampers l l l


32 0 X X X X X X X LANDING GEARS l l l l l l l l ME1001606, sec7

32 10 X X X X X X X

Remove the wheel fairings and leg fairings and

check them for good state. Visual inspection of

the sliding leg (search for leaks, traces of

corrosion, nicks, wear areas…).

l l l l l l l 23

32 20 X X X X X X X

Visual examination of the fixed strut (look for

cracks, corrosion), of the torque links, axles and

plastic bushes of the torque links.

l l l l l l

32 30 X X X X X X X

Check of the play in the bushings of the

compass (nose landing gear & main landing

gear)

l l l l l l

32 40 X X X X X X XFill-in and check of the hydraulic fluid level of the

oleo-strut.l l l l 7





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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)

32 50 X X X X X X X Inflate tires. l l l l l l l l

32 55 X X X X X X X Inflate oleo-strut. l l

32 60 X X X X X X XRemoval of the sliding leg. Dye penetrant test of

the axle-to-leg weldings. Replace O-rings.l l

32 70 X X X X X X X

Main landing gears

visual inspection of the main landing gear

attachment bolts.

l l l l ME1001606, sec7, §7-3

32 80 X X X X X X X

Main landing gears

Remove the main landing gear. Dye penetrant

test of struts and links after external chemical

cleaning.

l l ME1001606, sec7, §7-3

32 90 X X X X X X X

Main landing gears

Detailed examination of the main landing gear

housing, of the fixing bolts and structures round

about.

l l ME1001606, sec7, §7-3

32 100 X X X X X X X

Nose landing gear

Check the support frame and the friction

moment of the anti-shimmy device.

Replacement of the anti-shimmy washer when

friction moment not achieved. Ensure that main

axle, two axle bearings, nut and lock washer are

in good operating condition.

l l l l ME1001606, sec7, §7-2-13

32 110 X X X X X X X

Nose landing gear

Detailed inspection of the centering control

mechanism: attachment of the bar, adjustment

of the cam operating point; chack cam and latch

for wear.

l l l l ME1001606, sec7, §7-2

32 120 X X X X X X X

Nose landing gear

Check steering rods (state of rod ends, wear of

rod bulkhead).

l l l l l l l ME1001606, sec7, §7-2

32 130 X X X X X X X

Nose landing gear

Remove the nose landing gear. Dye penetrant

test of the strut, supporting plates and links after

external chemical cleaning.

l l ME1001606, sec7, §7-2

32 140 X X X X X X X

Nose landing gear

Visual inspection of the supporting plate

(between strut and main axle): seek for cracks

around the welding areas.

l l l l l l l ME1001606, sec7, §7-2

32 150 X X X X X X XWheels:

check tires for possible cuts and defectsl l l l l ME1001606, sec7, §7-4

32 160 X X X X X X XWheels

Visual check of wheel hub for cracksl l l l ME1001606, sec7, §7-4

32 170 X X X X X X X

Wheels

Check marking to make sure that the tire is not

slipping

l l l l l ME1001606, sec7, §7-4

32 180 X X X X X X XWheels

Check state of bearings (manually or by ear)l l l l l l l ME1001606, sec7, §7-4

32 190 X X X X X X X

Wheels : Remove wheels. Check state of ball

bearings and inner and outer seating faces.

Lubricate ball bearings.

l l l l l24

ME1001606, sec7, §7-4

32 200 X X X X X X X Wheels : Check inner tube and valve (wear) l l l24

ME1001606, sec7, §7-4

32 210 X X X X X X X Brake system: check brake disk and linings l l l l l l l ME1001606, sec8

32 220 X X X X X X XBrake system: check brake fluid reservoir (level,

vent holes, leaks).l l l l l l l

21

BS 169

ME1001606, sec8

32 230 X X X X X X X

Brake system: Close inspection of the complete

brake circuits from wheel to hydraulic fluid

reservoir (seek for leaks from fittings, abnormal

wear of piping..).

l l l l ME1001606, sec8

32 240 X X X X X X X

Brake system: Make sure that master cylinder

and parking valve are correctly operating

(efficiency).

l l l l l l l ME1001606, sec8

32 250 X X X X X X XBrake system: Drain the brake circuit. Replace

hydraulic brake fluid. Bleed the brake circuit.l l ME1001606, sec8






Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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Cale

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(years

)

37 0 X X X X X X X VACUUM SYSTEM l l l l l l ME1001606, sec10

37 10 X X X X X X X

Visual inspection of hoses, engine side and

cabin side. ll

l l l l

37 20 X X X X X X X

Detailed inspection of the dry air vacuum pump,

attachments, fittings, vents. l l l l l13


53 0 X X X X X X X FUSELAGE l l l l l l l l ME1001606, sec4

53 10 X X X X X X X

Visual check of all the fuselage covering. Seek

for crushing, cracks, distorsion, peeled off

painting…

l l l l l l l

53 20 X X X X X X X

Detailed inspection of the fuselage cover. Close

examination of internal fuselage structure (seek

for rooted away areas, stringer gluing…).

l l l l l l l

53 30 X X X X X X XDetailed examination of the firewall bulkhead,

particularly around the battery area.l l l l l l l l 13, 14

53 40 X X X X X X X

Visual inspection of the cabin wooden floor after

removal of the carpet and upholsteries. Cleaning

of floor, carpet and upholsteries.

l l l l l l

53 50 X X X X X X XDetailed examination of the central airframe

section (wing attachment) and fixing bolts.l l l l

53 60 X X X X X X X Make sure that water drain holes are free. l l l l l l

53 70 X X X X X X X

Look for glue cracks, crushing, all over the rear

part of the fuselage. Check the tail skid shoe and

its fixing bolts.

l l l l l l l

53 80 X X X X X X X

Close examination of the rectangular section

structural bars holding the wing. Carefully check

the fixing bolts and the corresponding inside

fuselage structure

l l l l l

53 90 O O O O

Luggage compartment door (P/N 28.18.46.010)

Visual inspection of seal for tightness.

Replacement on condition.

Visual inspection of door casing adhesive on

fuselage dome.

Visual inspection of luggage compartment door

hinge and swivel fitting condition.

Check the two latch locks work properly,

possible adjustment of force.

Lubricate protect the locks.

l l l l 25


54 0 X X X X X X X POWERPLANT BRACKET l l l l l l ME1001606, sec4

54 10 X X X X X X XCheck the efficient sealing of the firewall from

the structural bulkhead (gluing, sealing).l l l l l l

54 20 X X X X X X X

Detailed inspection of the engine mount

attachment (crushing under plates, inside the

cabin).

l l l l l l

54 30 X X X X XSwivelling engine mount: state of the pivot points

(bores, corrosion,…) and bolts.l l l l l l 14

54 40 X X X X X X X

Checking and re-tightening of the fixing bolts

(crossing the firewall) with adding of a washer if

necessary.

l l l l l l


55 0 X X X X X X X CONTROL SURFACES l l l l l l l ME1001606, sec6

55 10 X X X X X X X

Overall inspection of the rudder (fabric covering,

painting, structures). Particularly check the tail

light area. Make sure there is no play between

bellcrank and structure.

l l l l l l l

55 20 X X X X X X X

Overall inspection of the horizontal stabilator

(fabric covering, painting, structures). Detailed

inspection of the sunk-in control lever zone

(crushing).

l l l l l l l

55 30 X X X X X X X

Remove the access panels, fin root fairing to

inspect the horizontal stabilator bearings and

brackets as well as the fin supporting frame.

l l l l l l l





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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(ho

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)

Deta

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)

Cale

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(years

)

55 40 X X X X X X XCheck axles, bolts, bearings of the stabilator

pivot points (wear…).l l l l

55 50 X X X X X X XMake sure that blocks are in good condition

(mould, cracks, fixing…).l l

55 60 X X X X X X XCheck the gap between bolts and bearings of

the rudder pivot point.l l l

55 70 X X X X X X XCheck the hinge axles of rudder and hinge

fixation on vertical stabilizer and rudderl l l l

55 80 X X X X X X X

Remove the rudder. Close inspection of bolts

and bearings (wear). Reassemble the rudder

and check deflection angles.

l l lFlight safety

sensitive !

55 90 X X X X X X X Make sure that the drain holes are free. l l l l l l

55 100 X X X X X X X

Visual inspection of the balancing weight

supporting tube and fixing on stabilator spar

(corrosion of the tube, state of bolts).

l l l l lFlight safety

sensitive !

55 110 X X X X X X X Visual inspection of anti-tab control surfaces l l l l l l l

55 120 X X X X X X XCheck the play in anti-tab control surface piano

hinge.l l l l

55 130 X X X X X X X

Remove the anti-tab surface, check hinge and

pins (wear, corrosion). Reassemble the anti-tab

surface and check deflection.

l l l l l lFlight safety

sensitive !

55 140 X X X X X X XGrease the bearings and axles of the rudder and

stabilator pivot points.l l l l l l


56 0 X X X X X X X CANOPY l l l l l l l ME1001606, sec4

56 10 X X X X X X XCheck the locking system for good operation

and sliding guides for smooth travelling.l l l l l l l

56 20 X X X X X X XCheck glasses for good state and correct

assembly (crazing, cracks, sealing).l l l l l l l

56 30 X X X X X X X

Check the efficiency of the bonding between

glasses and frame all along the periphery

(depending on fixing mode).

l l l l l l l 15

56 40 X X X X X X

Inspection of the rivets and screws fixing the

glasses on the frame (depending on fixing

mode).

l l l l 14

56 50 X X X X X X X

Remove the sliding canopy. Check sliding

guides. Make sure the jettison system is well

operating.

l l l l l lFlight safety

sensitive !

56 60 O XCheck the adjustable rear view mirror for good

operating, fixation and sealing.l l l l l l l


57 0 X X X X X X X WINGS l l l l l l l l ME1001606, sec4

57 10 X X X X X X X

Check the state of the whole fabric covering

(cracks, rib lacing, tear…). EV of painting at

leading edge level, at spar level and between

wing tanks and main spar to make sure of no

possible ingress of water.

l l l l l l l

57 20 X X X Dismantle tanks for moisture and mold. l l

57 30 X X X X X X XCheck the ribs and the rear spar (aileron and

flaps) with slight thumb pressing.l l l l l l

57 40 X X X X X X X

Verify the state of the step area and the

protective sheet located at the trailing edge

(wear, sealing…).

l l l l l

57 50 X X X X X X X

General state of aileron control surface.

Particularly check the trailing edge strip of wood,

the fixing areas and the deflection blocks.

l l l l l l l

57 60 X X X X X X X

General state of the flaps. Look for loosen rivets,

defective hinge and good condition of the rib

where the control lever is attached.

l l l l l l l

57 70 X X X X X X XCheck condition and grease the flaps hinges and

axles of flaps control levers.l l l l l l l

57 80 X X X X X X X

Check condition and grease the axles of aileron

hinges. Check fixation of hinges to wing small

spar and aileron spar. Check aileron control

cable fork end bolts.

l l l l





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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)

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)

Cale

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(years

)

57 90 X X X

Make sure that the sealing between the wing

tanks and the spar is good as well as the sealing

of the screw fixing the removable aluminium

sheet located between tanks and leading edge

frame.

l l l

57 100 X X X X X X XMake sure that water drain holes (lower surface)

are free.l l l

57 110 X X X X X X X

Remove the aileron control access panel. Close

examination of the cables, pulleys, fixing

elements.

l l l lFlight safety

sensitive !

57 120 X X X X X X XMain bolts: Remove the main nut and spacer in

order to detect possible corrosion.l l

Flight safety

sensitive !

57 130 X X X X X X X

Removal flaps. Close inspection of the rear spar,

hinges, blocks, control bellcranks, bolts…

Reassembly of the flaps and ailerons. Check

control deflection angles.

l l lFlight safety

sensitive !

57 140 X X X X X X X

Removal of ailerons. Close inspection of the rear

spar, hinges, blocks, control bellcranks, bolts…

Reassembly of the flaps and ailerons. Check

control deflection angles.

l lFlight safety

sensitive !

57 150 O XVerify the attachment of the rear view mirror and

the good sealing of the screws (if equipped).l l l l


61 0 X X X X X X X PROPELLERl l l l l l l l

ME1001606, sec5

ME1001606, sec16

61 10 X X X X X X XMake sure that propeller blades display no

defects (cracks, nicks, dents…).l l l l 6, 29

61 20 X X X X X X XCheck the good state of the spinner and fixing

elements (cracks, nicks…).l l l l l 6, 14

61 30 X X X X X X X

Wooden propeller

Verification of torque loading of the propeller

bolts. Close examination of spinner, flange and

fixing bolts.

l l l l l l l l

61 40 X X X X X X XWooden propeller “fixed pitch”

Check propeller trackl l l l 6

61 50 X X X X X X X

Wooden propeller

Removal of spinner and propeller for overall

investigation, particularly check blade roots,

seating faces, bores.

l l l

6

Flight safety

sensitive !

61 60 X X

“Constant speed” propeller

Lubrication of the propeller hub according to the

“Propeller owner’s manual and logbook”

l l l l l l6

ME1001606, sec16, §16-3


71 0 X X X X X X X LYCOMING & THIELERT POWERPLANT l l l l l l l

71 10 X X X X X X XCheck engine cowlings, condition of laminate

structure, attachments…l l l l

71 20 X X X X X X X

Detailed inspection of the engine mount

(distortion, cracks, corrosion, worn areas…).

State of welding.

l l l l l l l 13


X X X X X X XLYCOMING POWERPLANT

l l l l l l l l

1, 14

ME1001606, sec5

ME1001606, sec16

71 30 X X X X X X XCheck engine baffles (cracks, safety conditions,

baffle fabric).l l l l

71 40 X X X X X X XCheck sandwich engine mounts (cracks,

burning). l l l l l l l ME1001606, sec5, §5-13

71 50 X X X X X X X

Drain the engine oil (when warm). Remove the

oil strainer and check for metal particles or

replace cartridge oil filter and cut open it to look

for metal particles. Cleaning.

l l l l l 27

71 55 X X X X X X X Visual inspection of the remote oil filter l l





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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(ho

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)

Deta

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(ho

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)

Cale

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(years

)

71 60 X X X X X X X

Inspection of oil cooler. Check for good condition

of honeycomb structure, leaks, fittings,

attachment points.

l l l l

71 70 X X X X X X X Check oil tubing. Overall state, fittings… l l l l l l l

71 80 X X X X X X XClose examination of the oil breather;

attachment, possible obstruction.l l l l l l l

71 90 XDetailed examination of the louver frame and its

fixation to the engine cowling.l l l l ME1001606, sec16, §16-6

71 100 X

Operating test of the louver in manual and

automatic mode. Make sure that a functional gap

remains around it.

l l l l l ME1001606, sec16, §16-6

71 110 X

Check the good operating condition and grease

the louver hinge, and the bolt of the control rod.

State of the rubber lip seal.

l l l l l l l l ME1001606, sec16, §16-6

71 120 XCheck the crossing of the louver control rod for

water proofness.l l l l l l l ME1001606, sec16, §16-6

71 130 X

Close examination of the louver linear actuator,

fixing elements and control linkage (axles, bolts,

bracket, bellcrank...).

l l l l ME1001606, sec16, §16-6


72 0 X X X X X X XTHIELERT Centurion 1.7, 2.0 & 2.0S

POWERPLANT13


73 0 X X X X X X X FUEL CIRCUITl l l l l l l l

ME1001606, sec9

ME1001606, sec16, §16-8

73 10 X X X X X X X Visual check of fuel tubing (state, cure date). l l l l l l l 13

73 20 X X X X X X XClose examination of inlet and outlet engine

driven pump fittings.l l l l

73 30 X X X X X Drain carburettor. l l l l l l l14

ME1001606, sec5, §5-5

73 40 X X X X X X X

Close examination of fuel pressure sending unit,

fuel pressure warning gauge, adaptor and

attachments. Check state of lines.

l l l l 13

73 50 X X X X X X X

Clean the decanting filters and their housing.

Check gathered particles for further investigation

if needed. Replacement depending on condition.

l l l l l l l l8, 13

ME1001606, sec9, §9.8

73 60 X X X X X X X

Detailed inspection of the tanks (seek for leaks,

corrosion, wear…), of the fixing strips (wear) and

outlet fitting.

l l l l l 13

73 70 O X X X Optional tank: detailed inspection for leaks. l l l l l l 13, 22

73 80 X X X X X X X

Close examination of the complete fuel line from

the tank to the engine driven pump (tubing,

hoses, selector, fittings, pump, filter…).

l l l 13

73 90 X X X X X X X

Check and calibration of the fuel transmitter

gauge. Make sure that the corresponding label is

correct.

l l l l13

ME1001606, sec9, §9.6

73 100 X X X X X X X Check the efficiency of vent lines. l l l l l l l 29

73 110 X X X X X X

Fittings or aluminium tubes using sqeezed

rubber element: check the inner tube diameter

for narrowing.

l l 14

73 120 X X X

A. P. R. fuel selector cock:

Removal of the fuel selector cock in order to

verify the length of the opening travel. Close

examination of the fuel cock control.

Fuel cock tightness test.

l l9

ME1001606, sec9, §9.9.9

73 130 X X X

Test the efficiency of fuel low level warning

lights. Operating conditions of “end of travel”

switches connecting these lights.

l l l l l

73 140 X X

Close examination of the electric fuel pump:

fittings, tightening, electrical connectors, fixing

parts, drain.

l l l l l l ME1001606, sec16, §16-8

73 150 X X

Detailed inspection of the fuel tubing and fittings

of the injection circuit (flexible hoses, distributor,

rigid pipes…) drain tubing.

l l l l l l l ME1001606, sec16, §16-8





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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(ho

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74 0 X X X X X X X IGNITION3, 14

ME1001606, sec5, §5-9


75 0 X X X X X X X AIR INTAKEl l l l l l l l

ME1001606, sec5

ME1001606, sec16

75 10 X X X X X

Visual inspection of carburettor heat box, good

condition of flap shutter, of its axles and

bearings.

l l l l l l l 14

75 20 X X X X X X X Check air filter. Clean. l l l l l l l l 2, 13

75 30 XCleaning and check of the wire mesh of the air

intake heat exchangerl l l l l l l l 14

75 40 X

Removal of the flexible duct from the exchanger

to the carburetor box and check of the air intake

system Removal of the mesh filter between box

and conduct for detailed inspection

l l l l l l 28

75 50 X X X X X Check air duct leading to the carburettor. l l l l l l l 2, 14, 16

75 60 X XDetailed inspection of coupling sleeve (bad

condition, tear…). Replace when damaged.l l l l l l l 17

75 70 X X X X X X Check air intake pipe. l l l l l l l 2, 13, 15

75 80 X XCheck the attachments of the filter casing to the

baffles and the removable filter gridl l l l l l

75 90 X XDetailed examination of the automatic alternate

air valve.l l l l l l l l

75 100 X X

Check efficiency and adjust the alternate air

valve spring setting. Check flexible control for

good operation.

l l l l l l


76 0 X X X X X X XLYCOMING ENGINE CONTROLS

l l l l l l l

14

ME1001606, sec5, §5-10

ME1001606, sec16

76 10 X X X X X X X

Mixture control: check control for good operating

conditions (sleeve, attachment of the sleeve…).

Check cable stop tightening per maintenance

manual.

l l l l l lBS111205

ME1001606, sec5

76 20 X X X X X X X

Throttle control: check for good operating

conditions (sleeve, attachment of the sleeve,

bracket…).

l l l l l l

76 30 X X X X XCarburettor heat control: state of the flexible

control, fixings and bracket.l l l l l l l

76 40 X X

Throttle control: check attachments under

engine crankcase, ball joint assy. Grease. Check

for good operating conditions.

l l l l l l l

76 50 X X

Propeller control: check fixing and state of the

ball joint actuating the regulator lever. Make sure

of good operating conditions of the control along

the whole travel. Check the flexible sleeve and

the rigid guide behind the instrument panel.

l l l l l l l

76 60 X X

Propeller control: detailed examination of the

supporting bracket located at the rear of the

engine (cracks, wear, corrosion…).

l l l





Sec Rep

120

140B

160

180

180R

200R

500

TASKS 50 100 500 1000 2000 1 3 6

Notes

Remarks

Manuals references

Models concerned Ro

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(ho

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)

Deta

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(ho

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)

Cale

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(years

)


77 0 X X X X X X X ENGINE CONTROLS l l l l l l l l ME1001606, sec5, §5-11

77 10 X X X X X XMake sure of good operating of the fuel pressure

drop warning lightl l l l l 13

77 20 X X

Fuel pipe connected to fuel flow instrument:

detailed inspection along the complete length.

Particularly check the fittings and the areas

subject to wear against other parts (bulkhead

crossing).

l l l l l l l l


78 0 X X X X X X X EXHAUST SYSTEMl l l l l l l l

ME1001606, sec5, §5-12

ME1001606, sec16

78 10 X X X X X X X

Detailed examination of the exhaust

components: flanges, formed tubes, muffler

(look for leaks, cracks, sign of corrosion…).

l l l l 13

78 20 X X X X X X XDetailed examination of the exhaust cabin and

carburettor heat shrouds.l l l l l l l l 14

78 30 X X X X X X XRemoval of cabin heat exchangers and check of

muffler for cracks.l l l l l l l 4, 14

78 40 X X X X XRemoval of heat exchanger for internal

inspection.l l l 14

78 50 O O O O O O ODetailed inspection of flexible ducts bends and

shock absorber mountings.l l l l l l l l 14, 18

78 60 O O O O O O ORemoval of hydro formed ball joints. Cleaning

and application of grease on contact areas.l l l l l l l 14, 18

78 70 O O O O O O O

Inspection before cleaning of the connecting part

between mufflers and silencer (cracks, leaks,

good condition of the fixing clamps), of the

flexible duct and of the silencer all over its length

(cracks, loose rivets…)

l l l l l l l 14, 19


79 0 X X X X X X X OIL SYSTEM l ME1001606, sec5

79 10 X X X X X X XOil line between engine and oil pressure switch:

careful cleaning of the oil hose and connectors,

including the restricted fitting.

l26

BS 031104


80 0 X X X X X X X STARTER l l l l ME1001606, sec5, §5-14

80 10 X X X X X X XExamination of the starter, fixing bolts, state of

gears, state of electrical connections and wiring l l l l 14

80 20 X X X X X X XRemoval and overhaul of starter (ball bearing,

carbon brushes…)

5, 14

Textron Lycoming SI 1157


86 0 X X TOWINGl l l l l l l l

14

ME1001606, sec15, §15-8

86 10 X X X

Towing hook: greasing of all moving parts, axles.

Check and lubrication of the hook release

control cable and handle.

l l l l l l l lDR 400/140B avec STC

EASA 10014219 (155CDI)

86 20O O

"MAAG" cable winding system: refer to the

manufacturer's manual.

86 30 O O

Unwind the towing cable out and check it

completely.

Adjust the unwinding brake to get a cable

tension of 60 N.

Inspection and cleaning of the winding drum as

well as the guide-tubes.

Check the adjustment of the pressure switch

and the correct operating of the electrical clutch.

l l l l l l l l

86 40 O O

Dismantling and close examination of the

unwinding brake. l l l l l l


DR400 Maintenance Schedule Is5 Amdt7 April2015

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Transcript of DR400 Maintenance Schedule Is5 Amdt7 April2015