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MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS

CHAPTER 5-40-01, REVISION No. 11

NOTE TO USERS

Please find enclosed revision No. 11 of Chapter 5-40-01.

Main modifications and corrections contained in this revision are listed hereafter.

ATA 100 No. REMARKS Chapter 5-40-01 Page 1 Page 2 Page 4 Pages 4 to 11

– New approval date of revision 11

– EASA approval

– Addition of CPCP section

– Creation of page break due to addition of operations and CPCP section – Addition of operations

NOTE TO USERS Page 1 EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

“DASSAULT AVIATION Proprietary Data” 0900400080f2e8de - RELEASED - Certification Repository

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“DASSAULT AVIATION Proprietary Data”

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DASSAULT 3/FALÇON2C

AVIATION

MAINTENANCE MA NUAL

TEMPORARY REVISION

AIRWORTHINESS LIMITATIONS LIST OF TEMPORARY REVISIONS DMD 45184

PAGE INTENTIONNALLY LEFT BLANK EFFECTIVITY: AIRCRAFT WITH SB No. 730 (S.S.I.P.)

"DASSAULT AVIATION Proprietary Data"

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"DASSAULT AVIATION Proprietary Data"

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 1 Revision 11 “DASSAULT AVIATION Proprietary Data”

AIRWORTHINESS LIMITATIONS

This section contains instructions pertaining to Airworthiness of aircraft having exceeded 20000 flights/30000 flying hours and within the 40000 flights/60000 flying hours limit, after application of SB 730 (S.S.I.P.).

These instructions must be imperatively observed by operators.

With respect to the airworthiness of the aircraft, this section is subject to approval by the European Aviation Safety (EASA).

For U.S. Registered aircraft, the Airworthiness Limitations section is EASA approved on behalf of FAA and specifies maintenance required under paragraphs 43.16 and 91.409 of the Federal Aviation Regulations, unless and alternative program has been FAA approved.

PAGES No. REVISION EFFECTIVITY 5-40-01 Page 1 5-40-01 Page 2 5-40-01 Page 3 5-40-01 Page 4 5-40-01 Page 5 5-40-01 Page 6 5-40-01 Page 7 5-40-01 Page 8 5-40-01 Page 9 5-40-01 Page 10 5-40-01 Page 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 Revision 11 AIRCRAFT WITH SB No. 730 (S.S.I.P.)

AIRCRAFT WITH SB No. 730 (S.S.I.P.)

Approved by EASA Date of approval of the original edition : March 14, 1990 Revision 1: February, 1996 Revision 2: October, 1996 Revision 3: April 3, 1998 Revision 4: December 23, 1999 Revision 5: September 23, 2002 Revision 6: February 10, 2003 Revision 7: EASA approved under EASA reference 05782 on July 31, 2007.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 2 Revision 11 “DASSAULT AVIATION Proprietary Data”

Revision 8: This revision 8 is the compilation of the following EASA approved changes, with no further technical change:

– TR001R approved by EASA under change reference M2974.

– CP005R approved by EASA under change reference M2980.

– CP009R approved by EASA under change reference M7022.

The technical content of these sections is approved under the authority of DOA ref EASA.21J.051 by reference R5038.

This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures.

Effective date of this revision: March 15, 2017.

Revision 9: This revision 9 is the integration of the following EASA approved change, with no further technical change:

– CH5-40-CP0004-CPAS approved by EASA under change reference M7035.

The technical content of these sections is approved under the authority of DOA ref EASA.21J.051 by reference R5041.

This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures.

Effective date of this revision: November 29, 2017.

Revision 10: This revision 10 is the integration of the following EASA approved change, with no further technical change:

– CH5-40-CP0012-CPAS approved by EASA.

The technical content of these sections is approved under the authority of DOA ref EASA.21J.051 by reference R5043.

This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures.

Effective dat e of this revision: January 1st, 2019.

Revision 11: This revision 11 is the integration of the following EASA approved change, with no further technical change:

– CH5-40-CP0036-CPAS approved by EASA.

– CH5-40-CP0038-CPAS approved by EASA.

The technical content of these sections is approved under the authority of DOA ref EASA.21J.051 by reference R5049.

This approval means that the revision has been prepared exclusively with already EASA approved data and is released under DOA procedures.

Effective date of this revision: July, 2022.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 3 Revision 11 “DASSAULT AVIATION Proprietary Data”

GENERAL Section 5-40-01: Supersedes the section 5-40-00 of chapter 5 of the FALCON 20-( )5 MAINTENANCE MANUAL (DMD DOC No. 42937). lt is divided into two paragraphs:

A – 5-40-01 Airframe components with limited service life (“SAFE LIFE”).

B – 5-40-01 Mandatory maintenance operations.

IMPORTANT: These instructions must be imperatively observed by the operators.

Failure to comply with these instructions will lead to the immediate suspension of the Airworthiness certificate.

The mandatory nature of these instructions does not in any way reduce the importance of the other tasks, listed in the Recommended Maintenance Program, which must be carried out in agreement with the National Airworthiness Authorities.

The mandatory mainte nance operation time limits given in section 5 -40-01 correspond to results obtained from computations.

In order to reduce down time due to scheduled maintenance, these mandatory operations also appear in section 5 -10, 5-10-01 or 5-20, with time limits corresponding to the aircraft inspections (A, B, Z, C, etc.) or expressed as a number of flights.

An operation required in section 5-40-01 may not necessarily be carried out, provided it was previously performed during an inspection required in sections 5-10 or 5-10-1.

To facilitate scheduling of maintenance operations expressed in “FLIGHTS”, a flight is considered as equivalent to landing except for some specific operation conditions (training aircraft, maritime patrol aircrafts, etc.), see 5-00-00, paragraph 4. E. of document DMD No. 42937.

If an operator installs a secondhand main structural part (example: landing gear), he must note on the aircraft logbook the number of flights or landings accumulated by this part since manufacturing. He must ensure that, during operation, the service life limit of this part, indicated in chapter 5-40-01, will not be exceeded.

Updating of section 5-40-01 When a new maintenance operation has been introduced during a revision of chapter 5 section 5 -40-01, this operation must be carried out when the time at which it is scheduled falls due, unless otherwise specified in the “MAXIMUM TIME LIMIT” column.

When the aircraft inspection have two limits (i.e., 12 years or 7500 flights) the due time will be which ever is reached the first.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 4 Revision 11 “DASSAULT AVIATION Proprietary Data”

CORROSION PREVENTION AND CONTROL PROGRAM (CPCP)

NOTE: Refer to chapter 05-15 for definitions of level 1, 2 and 3 corrosion.

A CPCP is a systematic approach for controlling corrosion in the aircraft's primary structure.

It is a program of maintenance tasks designed to control an aircraft structure to level 1 or better (Chapter 05-15 and EASA AMC 20-20 provide further details). Throughout the whole life of the aircraft, the operator is required to maintain the aircraft structure to corrosion level 1 or better on Principal Structural Elements (PSE, Ref. to list in SRM 51-00-02 RPI).

In order to control the corrosion in the aircraft structure at level 1 or better on PSE’s, the operator must implement a CPCP into his respective maintenance program.

As a guideline to help the operator to implement a CPCP, Dassault Aviation provides a Chapter 5 -15 (baseline) which compiles all the Dassa ult Aviation maintenance recommendations (inspections and their thresholds) required for a standard aircraft. All these chapter 5 -15 operations are scheduled Chapter 5-10 and 5 -20 (if the operator’s maintenance program is compliant with chapter 5 -10 and ch apter 5 -20 operations and intervals, it is compliant with the chapter 5-15 recommendations).

In accordance with the airworthiness mandate for CPCP inclusion in the operator’s maintenance program, it is the operator’s responsibility to take into account “no n-standard” features, such as STC’s, repairs, etc., and add appropriate supplemental CPCP instructions for continued airworthiness to his specific maintenance program.

DASSAULT AVIATION is responsible for monitoring the effectiveness of the Baseline Program and the pertinence of the inspection threshold and, if necessary, for defining changes based on analysis of the operators reported findings.

INSTRUCTIONS FOR CPCP Operators are mandated to report any finding affecting a PSE to DASSAULT AVIATION when level 2 or 3 corrosion is found. This will allow DASSAULT AVIATION to justify periodicity changes and to publish updates of the baseline CPCP.

NOTE: Reporting of level 1 corrosion that is recurrent in the same location or nil finding is also of interest to DASSAULT AVIATION and should be reported to assist in understanding the ageing of the fleet and the possible need for escalation or alleviation of maintenance program.

Responsibilities of the operators (AC 91-56) All additional inspection results, negative or positive, must be reported to the DASSAULT AVIATION manufacturer.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 5 Revision 11 “DASSAULT AVIATION Proprietary Data”

A – Airframe components with limited service life (“SAFE LIFE”) The airframe components with limited service life having a service life lower than or equal to 40000 flights/60000 flight hours are given in the table below.

This list refers only to installations designed or approved by DASSAULT AVIATION and incorporated in the aircraft type design. Other changes such as STC's, PMA (Parts Manufacturer approval) or any major change not approved by the airplane manufacturer, or change of the type of operation, which may have an impact on the airframe components service life, are not included in this document.

COMPONENT

IDENTIFICATION

PART NUMBER LIMITED SERVICE LIFE REMARKS 32 LANDING GEAR/ BRAKES

Nose landing gear leg comprising :

A23659-XX A10-23659-XX A11-23659-XX A23659033-XX A23659023-XX

- Magnesium barrel C48884-9 C48884-10 C1-48884 20 000 landings 20 000 landings 20 000 landings See NOTE (1) (A/C with SB 535) or

- Aluminum barrel D49432-1 40 000 landings See NOTE (1) (A/C with SB 535)

- Rocker C1-48723 C2-48723 40 000 landings 40 000 landings

- Rotating tube C48705 C1-48705 40 000 landings 40 000 landings See NOTE (1) (A/C with SB 535) Telescopic bar A23717 A23717-1 (SB 435) A23717-22 33 000 landings 40 000 landings 20 000 landings

Shock absorber A23660-XXX A23660002-XXX A23660023-XXX 40 000 landings 40 000 landings 40 000 landings

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

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COMPONENT

IDENTIFICATION

PART NUMBER LIMITED SERVICE LIFE REMARKS 32 LANDING GEAR/ BRAKES (cont’d)

Main landing gear leg A23663-XXX (L/H) A23664-XXX (R/H) A10-23663-XXX (L/H) A10-23664-XXX (R/H) A23663023-XXX (L/H) A23664023-XXX (R/H) 40 000 landings 40 000 landings 40 000 landings 40 000 landings 36 000 landings 36 000 landings

See NOTE (2) (Aircraft with SB 535) Shock absorber A23709-XXX (L/H) A23710-XXX (R/H) A23709023-XXX (L/H) A23710023-XXX (R/H) 40 000 landings 40 000 landings 36 000 landings 36 000 landings

Main landing gear actuator A23721-XXX (L/H) 40 000 landings 36 000 landings

See NOTE (3) A23722-XXX (R/H) 40 000 landings 36 000 landings

NOTE (1): One landing on an unpaved runway corresponds to:

– 1.5 landings on a paved runway for the barrel, – 4 landings on a paved runway for the rotating tube.

NOTE (2): One landing on an unpaved runway corresponds to 2 landings on a paved runway for the main landing gear.

NOTE (3): The limited service life is 40,000 landings if the main landing gear actuator was not previously installed on F200 A/C.

Otherwise, the limited service life is 36,000 landings.

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 7 Revision 11 “DASSAULT AVIATION Proprietary Data”

B – Mandatory maintenance operations Operation associated with fatigue, and marked with an asterisk in the following table, may be carried out within the limit of 3750 flights before the threshold attached to S.S.I.P. operations so that they can be integrated in the scheduled inspections of the maintenance cycle.

DESCRIPTION OF OPERATION MM REFERENCE MAXIMUM TIME LIMIT THRESHOLD REPEAT INTERVAL 21 AIR CONDITIONING – Operational test of cabin pressurization in manual mode, A/C with SEMCA pressurization and equipped with pressurization controller P/N 22201E102500 21-31-50 1250 hours – Check of overpressure tightness  Main regulating valve 21-31-10 1250 hours (**)  Emergency regulating valve 21-31-10 1250 hours (**) – Check of overpressure relief valve vacuum supply lines 21-31-10 7500 hours (**) (**) NOTE (8) 25 EQUIPMENT AND FURNISHINGS – Visual inspection of buckle spring of Anjou 18 months (*) Aéronautique safety belts, extensions and see restraint systems type 343 and 343-1 using CN 2002-105 (AB) Anjou Aéronautique Service Bulletin and No. 343-1-25-01 and No. 343-25-02 CN 2002-104 (AB) (*) Life limit of 60 months 27 FLIGHT CONTROLS – Tail plane relay box – Functional test of resetting relay and contactors 27-40-30 5000 hours – Operational test of tail plane control levers 27-40-40 5000 hours 28 FUEL – Removal/Installation of removable center section panel for corrosion inspection if:

– SB 354 not complied with.

– No inspection performed in the past 12 years.

28-00 M.C.I.

NOTE (1) 12 years – Removal/Installation of removable wing panels for corrosion inspection if:

– SB 499 not complied with.

– No inspection performed in the past 12 years 28-00 M.C.I.

NOTE (1) 12 years – Non-destructive test (eddy curent) crack search of the securing screws between fixed and removable center section panel (with panels removed) 28-00-03* 20000 flights 7500 flights or 12 years – Non-destructive test (eddy current) crack search of the wing lower surface panel rabbet areas located between the wing root and rib 9 28-00-04* 20000 flights 3750 flights or 7500 flights NOTE (2)

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MAINTENANCE MANUAL EFFECTIVITY : AIRCRAFT WITH SB No. 730 (S.S.I.P.)

5-40-01 Page 8 Revision 11 “DASSAULT AVIATION Proprietary Data”

DESCRIPTION OF OPERATION MM REFERENCE MAXIMUM TIME LIMIT THRESHOLD REPEAT INTERVAL 28 FUEL (Cont’d) – Non-destructive test (eddy current) crack search of the rabbet areas on the centerwing lower surface panels 28-00-05* 20000 flights 3750 flights or 7500 flights NOTE (2) – Detection and checking of reworked or corroded areas on the lower surface skin on the wings and the center wing (removable panel in position) 28-00-06* 20000 flights 3750 flights or 6 years See NOTE (6) 32 LANDING GEAR/BRAKES – Check for absence of friction points in the door uplock flexible connecting control rods 32-00-6 330 hours – Control and indicating switches. Voltage drop measurement (Before SB 531) 32-30-00 1230 hours 51 STRUCTURE – Detailed anti-corrosion inspection - Renewal of the protection plan by means of preventive and curative anti-corrosion treatment 51-00-00 M.C.I.

NOTE (1) 12 years 52 DOORS – Inspection/Check of passenger door locking and opening control 52-10-1 24 months or 800FH – Checking of operating forces of internal and external control 52-10-1 24 months or 800FH – Check/Lubrication of picking latches, door opening control lever pivot pin and spraying of Teflon on seal 52-10-1 24 months or 800FH – Unlocking test from inside of window emergency exit, RH and LH (EASA Airworthiness Directive No. 2000-0156) 52-20-1 24 months – Functional test of passenger/crew door warning system 52-70-1 800 hours 53 FUSELAGE – Structural inspection - Frame 33 inspection/check 53-10-0 5000FC 5000FC – Visual inspection of the corners of the nose wheel well opening (frame 7 for A/C S/N 1 to 378) 53-30-0* 20000 flights 3750 flights or 6 years – Non-destructive test (Eddy current) of the joggling between the panels at frame 33 in aircraft center line 53-30-02* 20000 flights NOTE (3) or 30000 flights NOTE (4) 2000 flights

2000 flights

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