# Dassault Service Bulletin 730: No revision named

- Rights: © Dassault Aviation. Filed by the FAA in regulations.gov docket FAA-2023-1495, the docket of AD 2023-20-05. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Dassault Service Bulletin 730](https://openairdocs.org/service-documents/dassault/sb-730.md)
- Title as filed: MF 20-5 w SB 730 Chapter 5-40 Rev 11
- Pages: 15
- PDF: https://openairdocs.org/files/sha256/12/a3/12a3a1ead06b8455898a9cf0095cdbaf18527b821488301f0a666550ba007509
- Page: https://openairdocs.org/service-documents/dassault/sb-730/file/12a3a1ead06b

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

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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 
 
Page 8 
 
 
 
– 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.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
AIRCRAFT WITH SB No. 730 (S.S.I.P.) 
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.) 
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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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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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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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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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Revision 11 “DASSAULT AVIATION Proprietary Data” 
 
 
 
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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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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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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DESCRIPTION OF OPERATION MM REFERENCE MAXIMUM TIME LIMIT THRESHOLD REPEAT INTERVAL 
53 FUSELAGE (Cont’d)    
– Non-destructive test (Eddy current) of the fuselage 
frame work around the windows at frames 15-18 
and 27 (skin or reinforcements) (longitudinal 
cracks) 
53-30-04* 20000 flights 3750 flights 
 or 
7500 flights 
NOTE (2) 
– Non-destructive test (Eddy current) of upper 
fuselage skin between frames 26 and 33 and 
between stringers 5 LH and 5 RH 
53-30-05* 25000 flights 3750 flights 
or 6 years 
– Non-destructive testing (Eddy current) of the 53-30-06* 20000 flights 3750 flights 
cockpit window frames   or 6 years 
– Non-destructive test (ultrasonic) of window frame 
vertical posts on windows secured with screws 
53-30-07 M.C.I. 
NOTE (1) 
6 years 
– Removal/Installation of trim for visual inspection 
of flight compartment glass panel frames 
53-30-14 20000 flights 3750 flights 
or 6 years 
– Non-destructive test (Eddy current) of windshield 
frame lower recesses (front, pilot and copilot 
windshield) 
53-30-15 20000 flights 3750 flights 
or 6 years 
– Stringer and reinforcement/skin interfaces spot 
welded between frames 33 and 40 
53-30-4 M.C.I. 
NOTE (1) 
12 years 
 Check for absence of corrosion using Eddy    
current inspection method    
(Aircraft S/N 3 to 384 and 392)    
– Stringer and reinforcement/skin interfaces spot 
welded between frames 0 and 33 
53-30-40 M.C.I. 
NOTE (1) 
12 years 
 Check for absence of corrosion using Eddy    
current inspection method    
(Aircraft S/N 3 to 384 and 392)    
– Inspection and check of fillets (French D.G.A.C. 
Airworthiness Directive No. 96-092-021 (B)) 
53-50-0-3D A inspection

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DESCRIPTION OF OPERATION 
 
MM 
REFERENCE 
MAXIMUM TIME LIMIT 
 
THRESHOLD 
REPEAT 
INTERVAL 
55 STABILIZERS    
– Movable tail plane - Inspection for corrosion and 
protection 
55-10-40 M.C.I. 
NOTE (1) 
3750 lights 
or 6 years 
 Endoscope inspection and spraying    
 Visual inspection of forward and aft spars and 
angle brackets 
   
– Stiffeners/skin panels interfaces spot welded on 
fin 
55-30-10 M.C.I. 
NOTE (1) 
12 years 
 Check for absence of corrosion using Eddy 
current inspection method (Aircraft S/N 3 to 
384 and 392) 
   
– Removal/Installation of horizontal and vertical 
stabilizers (M.C.I.) for: 
55-50-00 M.C.I. 
NOTE (1) 
12 years 
 Checking fittings and bores    
 Detailed corrosion inspection    
 Anti-corrosion protection of fittings    
 Installing a new fin hinge pin (SB 711)    
 Detailed corrosion inspection on:    
- the drive tubes of elevators coupling, 
- the inner drive tubes of each elevator. 
   
– Non-destructive test of fitting holes on:  M.C.I. 
NOTE (1) 
7500 flights 
or 12 years 
 Ultrasonic on: 55-50-01 
  
- All fuselage stub/fin/horizontal stabilizer 
fittings (stabilizers installed) 
NOTE (5)   
 Eddy current on: 55-50-03   
- aft fin mount (on fin side) 
- horizontal stabilizer hinges (on horizontal 
stabilizer side) 
- stub trailing edge (fin connection) 
- stub leading edge 
- fin leading edge

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DESCRIPTION OF OPERATION 
 
MM 
REFERENCE 
MAXIMUM TIME LIMIT 
THRESHOLD REPEAT INTERVAL 
 
76 ENGINE CONTROLS 
 
 
76-20-10 
  
– Functional tests of fuel shut-off valves (check for 
non-jamming in “open” position) 
10000 hours 
   
NOTE (1):  If an aircraft has reached 20000 flights/30000 F .H. without a Major Corrosion Inspection (M.C.I.)  
already performed this inspection is automatically scheduled as a prerequisite to the S.S.I.P.  
Service Bulletin No. 730. 
Tolerance: To avoid aircraft down time for logistic reasons, the manufacturer authorizes 
exceptionally a maximum tolerance of plus 6 months on the repeat interval of the M.C.I. 
(12 years). 
NOTE (2): The periodicity of three inspections: 28-00-04*, 28-00-05* and 53-30-04* is 3750 flights for 
reworked or repaired structure, and 7500 flights for a sound structure. 
NOTE (3): Threshold when corrosion has been found and repaired. 
NOTE (4): Threshold when structure is sound after a previous corrosion inspection. 
NOTE (5): The recommended repeat interval for operation 55-50-01 (stabilizers installed) is: 
– For A/C without SB 711: "every 4 years" 
– For A/C with SB 711: C inspection 
See also Chapter 5-10-00. 
NOTE (6): The check will be carried out on all panels every 7500 flights. 
The check to be carried out at 3750 flights will only concern areas in which defects were detected 
during the previous mapping. 
NOTE (8): This task must be performed on components. The value of the interval given for each component 
considers its cumulated presence on one or several aircraft. 
 
Unless specified (landings  for example), the  unit of  the interval is  expressed in measurable  
aircraft level figures (aircraft flight hours, aircraft cycles or age) and not in component operating  
time.

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