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 moen-hm02430 Maintenance Recommendations 11-12-2014 

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Company / dept. : SNEFM Report no. : SE-672_ 

Order no. : D13T90 Issue : 5 

Original issue date : 31-1-2006 Release date : 11-12-2014 

Security class RESTRICTED Status : Released 

 ECR : ECR015105 ECR016135 

ECR016135 

 

Engineering Report 

Airworthiness Limitations Section 

Fokker 70/100 Fuel ALI's and CDCCL's 
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temp. 0863 12-06

Summary:

This report specifies the Fuel Airworthiness Limitation Items (Fuel ALIs) and the Critical Design Configuration 

Control Limitations (CDCCL) required to prevent the development of unsafe conditions within the fuel system. 

This report is inserted into the Airworthiness Limitations Section (ALS) of the Instructions for Continued 

Airworthiness (ICA). 

Please take notice of the following: 

As from MRB report revision 14 the Airworthiness Limitations Section (ALS) is removed from the MRB report 

and published separately in order to harmonize the MRB with other manufacturer platforms and to clearly 

distinguish tasks selected from the MSG-3 process (MRB) from tasks required to meet certification 

requirements (ALS). 

As soon as the ALS is revised an e-mail notification will be sent to the Operators. To receive such a 

notification, “Notification of updates in the Documentation download Center (pdf files)” needs to be selected 

in the personal mailing list on the myfokkerfleet.com website. Furthermore the Airworthiness 

Recommendation Catalogue (ARC) will be updated. As soon as the (new / revised) ALS Airworthiness 

Directive is available, the ARC will be updated again.
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temp. 0863 12-06

Reason for revision:

Issue Description 

5 Generic:

• Fokker logo in header 

• Lay-out of the title/summary page (page 1) changed to the latest Fokker standard (no 

revision bar given). 

Paragraph 2.3

• Fuel ALI 280000-00-06: Task Description amended. 

• Note 2: amended.

 Paragraph 3.2:

• CDCCL 3.3 - Description amended, 

• CDCCL 3.4 - Description amended, 

• CDCCL 8.1 - New, 

• CDCCL 8.2a - New, 

• CDCCL 8.2b - New, 

• CDCCL 9.1a - New, 

• CDCCL 9.1b - New, 

• CDCCL 9.2a - New, 

• CDCCL 9.2b - New, 

• CDCCL 16.3 - Description amended, 

• CDCCL 16.4 - Description amended, 

• CDCCL 23 - Deleted (split in 23.1 & 23.2), 

• CDCCL 23.1 - New, 

• CDCCL 23.2 - New. 
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temp. 0863 12-06

Issue Description 

4 • Paragraph 2.3 

• Fuel ALI 280000-00-01: 

Task Title amended. 

• Fuel ALI 280000-00-02: 

Task Title amended 

Initial interval changed to ‘’NOTE 6”. 

• Fuel ALI 280000-00-05: 

‘’NOTE 1” changed to “NOTE 7”. 

• Fuel ALI 280000-00-23 and 280000-00-24: 

‘’NOTE 5” added. 

• Fuel ALI 280000-00-27: 

Task Description amended. 

Initial interval changed to ‘’NOTE 1”. 

• NOTE 1 thru 4 amended, NOTE 5, 6 and 7 added. 

• Paragraph 3.1: 

• Note added. 

• Column headings: 

- “Applicable to” changed to “Effectivity”, 

- reference “note 5” changed to “note 1”. 

• CDCCL 1.2: Description changed. 

• CDCCL 1.3: Effectivity changed. 

• CDCCL 1.6: Description changed. 

• CDCCL 1.7: Description changed. 

• CDCCL 2.2: Description changed. 

• CDCCL 2.3: Effectivity changed. 

• CDCCL 2.4, 2.5: Vendor name changed. 

• CDCCL 2.6: Description changed. 

• CDCCL 2.7: Description changed. 

• CDCCL 3.1, 3.2: Vendor name changed. 

• New CDCCL 3.3, 3.4 

• CDCCL 12.1, 12.2: Vendor name changed. 

• CDCCL 12.3, 12.4: Component, Description and Effectivity changed. 

• CDCCL 13.1, 13.2: Component and Description changed, CDCCL approved part no. 

deleted. 

• New CDCCL 13.3, 13.4. 

• CDCCL 14.1, 14.2 CDCCL approved part no. deleted. 
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temp. 0863 12-06

• CDCCL 14.3 Deleted. 

• New CDCCL 14.3a, 14.3b. 

• CDCCL 14.4 Deleted. 

• New CDCCL 14.4a, 14.4b. 

• CDCCL 15.1: Vendor name changed. 

• CDCCL 15.2: Effectivity changed. 

• CDCCL 15.3: Vendor name changed. 

• CDCCL 15.4, 15.5: Component, Description and Effectivity changed. 

• New CDCCL 16.3, 16.4. 

• CDCCL 23: Effectivity changed. 

• Note “5” changed to note “1”. 

• Paragraph 3.3: 

• Column headings: 

- “CDCCL reference” changed to “CDCCL number”, 

- reference “note 6” changed to “note 1”. 

• A CDCCL number (AFTS 1 thru 33) is provided for reference purpose only. 

• Note “6” changed to note “1”. 

• Paragraph 4: 

• Typing error removed 

Issue Description 

3 • As a result of SBF100-28-055 (AFTS installation, ECR 015347): 

- New Fuel ALIs 280000-00-07 to -21, 

- New CDCCLs for AFTS. 

• As a result of the Fuel Tank Safety Compliance Package: 

- New Fuel ALI’s 280000-00-06 and 280000-00-22 thru 280000-00-24 

 and 280000-00-27, 

- existing CDCCL’s are redefined. 

- new CDCCL’s are introduced. 

- existing fuel ALI’s are re-defined. 

Note: as tables have been completely rewritten, no revision bars are given. 

Abbreviations added 
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temp. 0863 12-06

Table of Contents 

1. General ....................................................................................................................................................... 6

2. Fuel Airworthiness Limitation Items (ALI) ................................................................................................... 7

2.1. General ............................................................................................................................................... 7

2.2. Exceptional short-term extensions ...................................................................................................... 7

2.3. Fuel ALI tasks and intervals ................................................................................................................ 8

3. Critical Design Configuration Control Limitations (CDCCL) ..................................................................... 13

3.1. General ............................................................................................................................................. 13

3.2. CDCCL description and control ........................................................................................................ 13

3.3. CDCCL description and control (AFTS only) .................................................................................... 21

4. Abbreviations ............................................................................................................................................ 25
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temp. 0863 12-06

1. General 

During the F28 Mk0070 and F28 Mk0100 certification process, certain Maintenance Requirements have 

been identified which must be performed on all aircraft at or before the intervals or times specified in 

order to meet the certification requirements. These mandatory Maintenance Requirements are identified 

as Airworthiness Limitations. 

The Airworthiness Limitations are: 

1. Certification Maintenance Requirements (CMR's) 

CMR's are tasks on Systems & Power Plant where a limiting interval has been established from the 

System Safety Assessment to achieve compliance with the certification requirements as defined in 

JAR/FAR/CS 25.1309. 

2. Airworthiness Limitation Items (ALI's) 

ALI's are tasks in the Structure and System & Power Plant Programs where a limiting interval has 

been established resulting from the Fatigue and Damage Tolerance Assessment to achieve 

compliance with the certification requirements as defined in JAR/FAR/CS 25.571. 

3. Safe Life Items (SLI's) 

SLI's are certain aircraft and engine parts with a retirement (replacement) life. 

4. Fuel Airworthiness Limitation Items: as applied to the Fuel Tank system safety policy, this term 

means fuel system mandatory maintenance inspections determined necessary to ensure that 

unsafe conditions do not arise in the fuel system throughout the operational life of the aircraft. 

5. Critical Design Configuration Control Limitations (CDCCL): as applied to the Fuel Tank system 

safety policy, this term refers to a feature of any aircraft system which must be retained during 

modification, change, repair or scheduled maintenance to ensure that an unsafe condition does not 

develop in the fuel system. 

This report SE-672 specifies the Fuel ALI’s and CDCCL’s. 

Report SE-623 specifies both the ALI's and the SLI's as mentioned under 2 and 3. 

Report SE-473 specifies the CMR’s. 

These reports are inserted into the Airworthiness Limitations Section (ALS) of the Instructions for 

Continued Airworthiness (ICA). For more details on the ALS, reference is made to the MRB report, 

Appendix 1.

Operators are expected to demonstrate to their Airworthiness Authority Maintenance Inspector that the 

required configuration control systems are in place to ensure that CDCCL’s are properly identified and 

managed. 
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temp. 0863 12-06

2. Fuel Airworthiness Limitation Items (ALI) 

2.1. General 

As applied to Fuel Tank system safety policy, this term means fuel system mandatory maintenance 

inspections determined necessary to ensure that unsafe conditions do not arise in the fuel system 

throughout the operational life of the aircraft. 

2.2. Exceptional short-term extensions 

Since Fuel ALI Maintenance/Inspection intervals are generally not determined from calculations in 

which failure rate data is known with a high level of confidence, an exceptional short-term extension 

for a specific Fuel ALI interval may be made on one aircraft for a limited period of time without 

jeopardizing safety. 

The term 'exceptional short-term extension' is defined as an increase in a Fuel ALI interval that may 

be needed to cover an uncontrollable or unexpected situation. Repeated use of such extensions, 

either on the same aircraft or on similar aircraft in the operator's fleet, should not be used as a 

substitute for good management practices. 

Unless noted adjacent to the task, for all Fuel ALI’s identified in this report, it has been accepted by 

the Primary Certification Office (EASA) that short-term extensions up to the following maximum 

values may be granted without consultation with that office. Requests for extensions in excess of 

these values must be submitted with full justification to the Primary Certification Office (EASA) such 

that approval, if granted, can be given prior to their use. 

- Fuel ALI’s controlled by Flight Hours (FH) 

Extensions up to 10% or 500 FH (whichever is the lesser) may exceptionally be granted on Fuel 

ALI intervals quoted in terms of flight hours. 

- Fuel ALI’s controlled by Flight Cycles (FC) 

Extensions up to 5% or 250 FC (whichever is the lesser) may exceptionally be granted on Fuel 

ALI intervals quoted in terms of flight cycles or landings. 

- Fuel ALI’s controlled by Calendar Time (MO) 

Where the repeat interval is 12 months or less, extensions up to 10% or 1 month (whichever is 

the lesser) may exceptionally be granted on Fuel ALI intervals quoted in terms of months. 

Where the repeat interval is greater than 12 months but less than 3 years, extensions up to 2 

months may exceptionally be granted. 

Where the repeat interval is 3 years or greater, extensions up to 3 months may exceptionally be 

granted. 
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temp. 0863 12-06

It is the responsibility of the operator to identify appropriate procedures with his local regulatory 

authority for the control and development of his maintenance program. (Note EASA: The operator 

should keep a record of short term extensions given for Fuel Airworthiness Limitation Items). 

This paragraph is written to confirm to the local regulatory authority that exceptional short-term 

extensions of Fuel ALI intervals are permissible. Approval of such extensions rests with the local 

authority in the same way as it does for any other scheduled maintenance task interval extension. 

2.3. Fuel ALI tasks and intervals 

FUEL AIRWORTHINESS LIMITATION ITEMS 

Tasknumber TASK TITLE / Task Description Interval Effectivity Initial* Repeat* 

280000-00-01 DETAILED INSPECTION OF FUEL 

QUANTITY INDICATING (FQI) TANK 

PROBES AND WIRING IN THE MAIN TANK 

AND COLLECTOR TANK. 

A detailed inspection of the FQIS in the wing tanks shall be 

carried out to verify the following: 

o FQIS wiring and wiring conduits are in good condition, 

free of damage and installed in accordance with the 

design. 

o FQIS probes are clean, free of damage and firmly 

attached. 

o Attachment bolts and rivnuts of the probe attachment 

clamps are completely covered with an undamaged 

layer of sealant. 

o A clearance of minimum 3 mm exists between any metal 

probe part (including its wire terminals) and adjacent 

structure or other adjacent metal part. 

o The tanks are clean and free of debris of any kind. 

Anomalies shall be corrected. 

01/01/2013 8 YR ALL 

280000-00-02 DETAILED INSPECTION OF FUEL 

QUANTITY INDICATING (FQI) TANK 

PROBES AND WIRING OF THE INTEGRAL 

CENTER WING TANK (ICWT). 

A detailed inspection of the FQIS in the ICWT shall be 

carried out to verify the following: 

o FQIS wiring and wiring conduits are in good condition, 

free of damage and installed in accordance with the 

design. 

o FQIS probes are clean, free of damage and firmly 

attached. 

o Attachment bolts and rivnuts of the probe attachment 

clamps are completely covered with an undamaged 

layer of sealant. 

o A clearance of minimum 3 mm exists between any metal 

probe part (including its wire terminals) and adjacent 

structure or other adjacent metal part. 

o The ICWT is clean and free of debris of any kind. 

Anomalies shall be corrected. 

NOTE 6 8 YR ORC W3437 
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FUEL AIRWORTHINESS LIMITATION ITEMS 

Tasknumber TASK TITLE / Task Description Interval Effectivity Initial* Repeat* 

280000-00-03 DETAILED INSPECTION OF THE 

DRAINHOLES AND DRAIN PATHS IN THE 

DRY BAY ZONES. 

A detailed inspection of the drain holes and drain paths in 

the dry bay zones adjacent to fuel tanks shall be carried 

out to verify the following: 

o Dry bay is clean. 

o Drain holes and drain paths are clean and free of any 

obstruction.

Anomalies shall be corrected.

01/01/2009 6000 FH ALL 

280000-00-04 DETAILED INSPECTION OF THE 

ELECTRICAL BONDING (MAIN TANK AND 

COLLECTOR TANK). 

A detailed inspection of the electrical bonding provisions of 

fuel lines, ventilation lines and components inside or 

connected to the wing tanks shall be carried out to verify 

all bonding provisions required per design are present, 

properly installed and in good condition. 

Anomalies shall be corrected.

NOTE 1 8 YR ALL 

280000-00-05 DETAILED INSPECTION OF THE 

ELECTRICAL BONDING (INTEGRAL 

CENTER WING TANK). 

A detailed inspection of the electrical bonding provisions of 

fuel lines, ventilation lines and components inside or 

connected to the ICWT shall be carried out to verify all 

bonding provisions required per design are present, 

properly installed and in good condition. 

Anomalies shall be corrected.

NOTE 7 8 YR ORC W3437 

280000-00-06 OPERATIONAL CHECK OF THE 

AUTOMATIC OFF-SWITCHING OF THE 

POWER SWITCH ON THE FUELING 

CONTROL PANEL. 

It shall be ensured that a cam is installed on the Fueling 

Control Panel access door and functions properly. The 

function of the cam is that it forces the power switch of the 

FCP to the OFF position at closure of the access door. 

Anomalies shall be corrected.

NOTE 2 1200 FH ALL 

280000-00-07 RESTORATION OF AUXILIARY FUEL 

PROCESSING UNIT (AFPU). 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-08 RESTORATION OF AUXILIARY FUEL 

ISOLATION UNITS (AFIU’S). 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-09 DETAILED INSPECTION OF AFTS FUEL 

QUANTITY PROBES AND 

COMPENSATORS. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 
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FUEL AIRWORTHINESS LIMITATION ITEMS 

Tasknumber TASK TITLE / Task Description Interval Effectivity Initial* Repeat* 

280000-00-10 DETAILED INSPECTION OF FUEL 

QUANTITY INDICATION SYSTEM WIRING, 

EQUIPMENT BONDING PROVISIONS AND 

LEVEL SWITCH ASSEMBLIES INSTALLED 

INSIDE THE AFTS TANK CELLS. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-11 FUNCTIONAL CHECK OF SUMP DRAIN 

VALVE AND AIR INLET CHECK VALVE 

INSIDE AFTS TANK CELL. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-12 DETAILED INSPECTION OF BONDING OF 

AFTS VENT/OVERFLOW LINE AND 

BONDING AND INSTALLATION OF 

LIGHTNING PROTECTION BARS IN RH 

WING ROOT FAIRING AND SPACE 

BETWEEN FRONT AND AUXILIARY SPAR. 

NOTE 3 6000 FH Mk0100, 

Post ECR 

015347 

280000-00-13 INSPECTION OF PURGE/DRAIN 

PROVISIONS FOR SHROUDS OF AFTS 

FILL/TRANSFER AND VENT/OVERFLOW 

LINES IN RH WING ROOT FAIRING SPACE. 

NOTE 3 6000 FH Mk0100, 

Post ECR 

015347 

280000-00-14 DETAILED INSPECTION OF AFTS 

TRANSFER/FILL VALVE (TFV) AND 

OVERFLOW VALVE (OFV) ACTUATOR 

INSTALLATION IN DRY BAYS. 

NOTE 3 1 YR Mk0100, 

Post ECR 

015347 

280000-00-15 FUNCTIONAL CHECK OF BONDING 

PROVISIONS OF AUXILIARY FUEL 

PROCESSING UNIT (AFPU) AND AUXILIARY 

FUEL ISOLATION UNITS (AFIU’S). 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-16 INSPECTION OF AFTS WARNING PLACARD 

ADJACENT TO FORWARD CARGO DOOR. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-17 LEAK TEST OF SHROUDS AND SLEEVES 

OF THE AFTS FILL/TRANSFER AND 

VENTILATION/OVERFLOW LINES. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-18 INSPECTION OF SHROUDS AND SLEEVES 

OF AFTS FILL/TRANSFER AND 

VENT/OVERFLOW LINES, AND AFTS 

PURGE/DRAIN SYSTEM. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-19 INSPECTION OF AFTS TANK AIR INLET 

ASSEMBLY AND FUNCTIONAL CHECK OF 

CHECK VALVES OUTSIDE THE TANKS. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-20 DETAILED INSPECTION OF AFTS SAFE 

HARNESSES. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 

280000-00-21 DETAILED INSPECTION OF AFTS TANK 

CELLS TO AIRCRAFT STRUCTURE 

BONDING PROVISIONS. 

NOTE 3 8 YR Mk0100, 

Post ECR 

015347 
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FUEL AIRWORTHINESS LIMITATION ITEMS 

Tasknumber TASK TITLE / Task Description Interval Effectivity Initial* Repeat* 

280000-00-22 OPERATIONAL CHECK OF THE 

COLLECTOR TANK LOW LEVEL WARNING 

SYSTEM. 

It shall be verified through performing an operational test 

that the collector tank low level warning system functions 

properly. 

Anomalies shall be corrected.

01/01/2013 2400 FH ALL 

280000-00-23 DETAILED INSPECTION OF THE FQIS 

PROBE FOOTPRINT COATING IN THE 

WING TANKS. 

It shall be verified that the tank structure below each FQIS 

probe (footprint area) in the wing tanks is completely 

covered with a sealant and that this coating is undamaged. 

In case of damage the coating shall be repaired. 

Note: The footprint area is the area covered by the 

projection (parallel to the probe centerline) of the 

cross section of the probe outer tube, enlarged by a 

factor of three, on the tank bottom structure. 

NOTE 4 8 YR ALL 

NOTE 5 

280000-00-24 DETAILED INSPECTION OF THE FQIS 

PROBE FOOTPRINT COATING IN THE 

INTEGRAL CENTER WING TANK. 

It shall be verified that the tank structure below each FQIS 

probe (footprint area) in the ICWT is completely covered 

with a sealant and that this coating is undamaged. 

In case of damage the coating shall be repaired. 

Note: The footprint area is the area covered by the 

projection (parallel to the probe centerline) of the 

cross section of the probe outer tube, enlarged by a 

factor of three, on the tank bottom structure.

NOTE 4 8 YR ORC W3437 

NOTE 5 

280000-00-25 Reserved 

280000-00-26 Reserved 

280000-00-27 DETAILED INSPECTION OF THE 

ELECTRICAL BONDING (CENTER WING 

TANK). 

A detailed inspection of the electrical bonding provisions of 

the CWBT fueling/transfer manifold and connected fuel 

lines, of the ventilation line between suction relief valve 

and front spar (if installed) and of the CWT compartment 

drain manifold with connected fuel lines and flame arrester 

shall be carried out to verify that all bonding provisions 

required per design are present, properly installed and in 

good condition. 

Anomalies shall be corrected.

NOTE 1 8 YR Pre 

ECR 90023 

* Not later than 
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Note 1: The initial inspection shall be done not later than 1/1/2013 except for bonding provisions introduced 

with SBF100-28-069. 

For bonding installed with SBF100-28-069, the initial inspection date is the accomplishment date of 

SBF100-28-069. 

Note 2: If SBF100-28-063 is applicable, the initial inspection date is the accomplishment date of the check for 

correct operation of the cam in accordance with SBF100-28-063. 

If SBF100-28-063 is not applicable, the initial inspection date is 1200 FH after the issue date 

(January 15th, 2013) of issue 4 of report SE-672. 

Note 3: The initial inspection date is the accomplishment date of SBF100-28-055. 

Note 4: The initial inspection date is the accomplishment date of SBF100-28-067.

Note 5: Task is applicable after accomplishment of SBF100-28-067. 

Note 6: The initial inspection shall be done not later than 1/1/2013 except for aircraft modified in accordance 

with SBF100-28-075. 

For aircraft post SBF100-28-075, the initial inspection date is the accomplishment date of SBF100-

28-075. 

Note 7: The initial inspection shall be done not later than 1/1/2013 except for bonding provisions introduced 

with SBF100-28-069 and/or SBF100-28-075. 

For bonding installed with SBF100-28-069 and/or SBF100-28-075, the initial inspection date is the 

accomplishment date of that SB. 
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3. Critical Design Configuration Control Limitations (CDCCL) 

3.1. General 

As applied to the Fuel Tank system safety policy, this term refers to a feature of any aircraft system 

which must be retained during modification, change, repair or scheduled maintenance to ensure that 

an unsafe condition does not develop in the fuel system. 

Note: AMM task 28-00-01-910-812 contains a table that shows the relation between access panel 

 and the applicable CDCCL related AMM task(s). 

. 

3.2. CDCCL description and control 

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

1.1 FQIS probes in 

wing tanks 

It shall be ensured that the FQIS probes 

in the wing tanks are installed such, that 

no metal part of the probe (including its 

wire terminals) is closer than 3 mm to 

adjacent structure or other adjacent 

metal part. 

All N.A. N.A. 

1.2 FQIS probes in 

wing tanks 

It shall be ensured that the two 

mounting provisions for each wing tank 

FQIS probe are undamaged, firmly 

attached to their tank mounting bracket 

and that the attachment bolts and rivnuts are completely covered with an 

undamaged layer of a sealant approved 

for the purpose . 

All N.A. N.A. 

1.3 Coating on wing 

tank structure 

below FQIS 

probes 

It shall be ensured that the tank 

structure below each FQIS probe 

(footprint area) in the wing tanks is 

completely covered with an undamaged 

coating of a sealant approved for the 

purpose. 

Note: The footprint area is the area 

covered by the projection (parallel 

to the probe centerline) of the 

cross section of the probe outer 

tube, enlarged by a factor of 

three, on the tank bottom 

structure. 

Post 

 SBF100-28-067 

N.A. N.A. 

1.4 FQIS probes 

wing tanks 

It shall be ensured that only FQIS 

probes with a part number approved by 

the TCH under Fuel Tank Safety 

requirements for installation in the wing 

tanks will be installed on the aircraft. 

All Smith 

Industries 

0209KTU01 

0209KTU02 

0209KTU03 

0209KTU04 

0209KTU05 

0209KTU06 

0209KTU07 

0209KTU09 

0209KTU10 

0210KTU01 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

1.5 FQIS probes 

wing tanks 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Smith 

Industries 

0209KTU01 

0209KTU02 

0209KTU03 

0209KTU04 

0209KTU05 

0209KTU06 

0209KTU07 

0209KTU09 

0209KTU10 

0210KTU01 

1.6 FQIS wiring in 

wing tanks 

It shall be ensured that the FQIS wiring 

in the wing tanks is undamaged and 

correctly installed. 

All N.A. N.A. 

1.7 FQIS wiring in 

wing tanks 

It shall be ensured that any repairs of 

FQIS wiring in the wing tanks are 

carried out following TCH-approved 

procedures. 

All N.A. N.A. 

2.1 FQIS probes in 

ICWT 

It shall be ensured that the FQIS probes 

in the ICWT are installed such, that no 

metal part of the probe (including its 

wire terminals) is closer than 3 mm to 

adjacent structure or other adjacent 

metal part. 

A/C with ICWT N.A. N.A. 

2.2 FQIS probes in 

ICWT 

It shall be ensured that the two 

mounting provisions for each ICWT 

FQIS probe are undamaged, firmly 

attached to their tank mounting bracket 

and that the attachment bolts and rivnuts are completely covered with an 

undamaged layer of a sealant approved 

for the purpose. 

A/C with ICWT N.A. N.A. 

2.3 Coating on 

ICWT structure 

below FQIS 

probes 

It shall be ensured that the tank 

structure below each FQIS probe 

(footprint area) in the ICWT tank is 

completely covered with an undamaged 

coating of a sealant approved for the 

purpose. 

Note: The footprint area is the area 

covered by the projection (parallel 

to the probe centerline) of the 

cross section of the probe outer 

tube, enlarged by a factor of 

three, on the tank bottom 

structure. 

A/C with ICWT, 

Post 

 SBF100-28-067 

N.A. N.A. 

2.4 FQIS probes 

ICWT 

It shall be ensured that only FQIS 

probes with a part number approved by 

the TCH under Fuel Tank Safety 

requirements for installation in the ICWT 

will be installed on the aircraft. 

A/C with ICWT Smith 

Industries 

0270KTU01 

0270KTU02 

2.5 FQIS probes 

ICWT 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

A/C with ICWT Smith 

Industries 

0270KTU01 

0270KTU02 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

2.6 FQIS wiring in 

ICWT 

It shall be ensured that the FQIS wiring 

in the ICWT is undamaged and correctly 

installed. 

A/C with ICWT N.A. N.A. 

2.7 FQIS wiring in 

ICWT 

It shall be ensured that any repairs of 

FQIS wiring in the ICWT are carried out 

following TCH approved procedures. 

A/C with ICWT N.A. N.A. 

3.1 FQIS probe 

CWBT 

It shall be ensured that only a FQIS 

probe with a part number approved by 

the TCH under Fuel Tank Safety 

requirements for installation in the 

CWBT will be installed on the aircraft. 

A/C with CWBT Smith 

Industries 

0108KTU03 

0108KTU04 

3.2 FQIS probe 

CWBT 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

A/C with CWBT Smith 

Industries 

0108KTU03 

0108KTU04 

3.3 In-line fuse 

assemblies in 

wiring of CWBT 

level sensor 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in two of the three wires to the 

level sensor in the CWBT, close to 

receptacle J0428B in zone 165, and 

that the fuse assemblies are 

undamaged 

A/C with CWBT, 

Post 

 SBF100-28-078 

N.A. N.A. 

3.4 In-line fuse 

assemblies in 

wiring of CWBT 

level sensor 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in two of the three wires 

to the level sensor in the CWBT. 

A/C with CWBT, 

Post 

 SBF100-28-078 

Fokker 

Services 

W48006-405 

4 FQIS wiring 

outside fuel 

tanks 

It shall be ensured that repairs of any 

wiring near or adjacent to any FQIS 

wiring external to the fuel tanks will not 

jeopardize fuel tank safety through 

increasing the risk of a hot short of 

FQIS wires. 

All N.A. N.A. 

5 Bonding of fuel 

lines, ventilation 

lines and 

components, 

wing tanks 

It shall be ensured that the configuration 

and quality of the bonding provisions of 

fuel lines, ventilation lines and 

components inside or connected to the 

wing tanks are conforming to the design 

(ref. NC 4.610/xxx). 

All N.A. N.A. 

6 Bonding of fuel 

lines, ventilation 

lines and 

components, 

ICWT 

It shall be ensured that the configuration 

and quality of the bonding provisions of 

fuel lines, ventilation lines and 

components inside or connected to the 

ICWT are conforming to the design (ref. 

NC 4.610/xxx). 

A/C with ICWT N.A. N.A. 

7 Bonding of fuel 

lines, ventilation 

lines and 

components, 

CWBT 

It shall be ensured that the configuration 

and quality of bonding provisions of fuel 

lines and ventilation lines connected to 

the CWBT and of the drain line of the 

CWBT compartment are conforming to 

the design (ref. NC 4.610/xxx). 

A/C with CWBT N.A. N.A. 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

8.1 Anti-spray cover 

re/defueling 

shut-off valve 

It shall be ensured that an anti-spray 

cover is in place at the wing tank 

re/defueling shut-off valve, covering its 

discharge port, and that it is firmly 

attached and undamaged. 

All N.A. N.A. 

8.2a Anti-spray cover 

re/defueling 

shut-off valve 

It shall be ensured that only an antispray cover with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

A/C s/n 11242 

thru 11441 

Fokker 

Services 

A69218-009 

(LH & RH) 

8.2b Anti-spray cover 

re/defueling 

shut-off valve 

It shall be ensured that only an antispray cover with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

A/C s/n 11442 & 

up 

Fokker 

Services 

D69239-401 (LH) 

D69239-402 (RH) 

9.1a Flame trap main 

wing tank vent 

system 

It shall be ensured that a flame trap is 

properly installed in each main wing 

tank vent line. 

All N.A. N.A. 

9.1.b Flame 

trap/flame 

arrester main 

wing tank vent 

system 

It shall be ensured that only a flame trap 

or flame arrester with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

All Fokker 

Services 

AMAL 

A69543-401 

A69543-403 

188-26-15-45FA188-206-15-45SS 

188-26-15-45SS316 

9.2a Flame trap 

center wing 

tank 

compartment 

drain line 

It shall be ensured that a flame trap is 

properly installed in the center wing tank 

compartment drain line. 

A/C with CWBT N/A N/A 

9.2b Flame 

trap/flame 

arrester center 

wing tank 

compartment 

drain line 

It shall be ensured that only a flame trap 

or flame arrester with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

A/C with CWBT Fokker 

Services 

AMAL 

A69742-401 

A69742-403 

188-26-15-45FA188-206-15-45SS 

188-26-15-45SS316 

10 Anti-splash 

provisions in 

main wing tanks

It shall be ensured that the anti-splash 

plates are in place at the main tank fuel 

entry openings (in top hat stringers 

inboard and outboard of the rib at wing 

station 4700) and are firmly attached 

and undamaged. 

All N.A. N.A. 

11.1 Boost-pump It shall be ensured that only a boost 

pump with a part number approved by 

the TCH under Fuel Tank Safety 

requirements will be installed on the 

aircraft. 

All Intertechnique 229432 

229945 

11.2 Boost-pump It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Intertechnique 229432 

229945 

12.1 Collector Tank 

Level float 

switch 

It shall be ensured that only a collector 

tank level float switch assembly with a 

part number approved by the TCH 

under Fuel Tank Safety requirements 

will be installed on the aircraft. 

All Flight 

Refueling 

3515000-135 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

12.2 Collector Tank 

Level float 

switch 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Flight 

Refueling 

3515000-135 

12.3 In-line fuse 

assemblies in 

wiring of 

collector tank 

level float 

switch 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in the power supply wire and in 

the return wire of the collector tank level 

float switch, close to the point where the 

wiring enters the conduit to the tank wall 

feed-through, and that the fuse 

assemblies are undamaged. 

Post 

 SBF100-28-068

N.A. N.A. 

12.4 In-line fuse 

assemblies in 

wiring of 

collector tank 

level float 

switch 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in the power supply wire 

and in the return wire of the collector 

tank level float switch. 

Post 

 SBF100-28-068

Fokker 

Services 

W48006-403 

13.1 Re/ defuelling 

shut-off valve 

It shall be ensured that only a 

re/defuelling shut-off valve with a part 

number approved by the TCH under 

Fuel Tank Safety requirements will be 

installed on the aircraft. 

All Parker 

Hannifin 

2630486M3 

2630486M4 

13.2 Re/ defuelling 

shut-off valve 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Parker 

Hannifin 

2630486M3 

2630486M4 

13.3 In-line fuse 

assemblies in 

wiring of 

solenoid of 

re/defuelling 

shut-off valve 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in the power supply wire and in 

the return wire of the solenoid of the 

re/defueling shut-off valve, close to the 

point where the wiring enters the tank, 

and that the fuse assemblies are 

undamaged. 

Post 

 SBF100-28-068 

N.A. N.A. 

13.4 In-line fuse 

assemblies in 

wiring of 

solenoid of 

re/defuelling 

shut-off valve 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in the power supply wire 

and in the return wire of the solenoid of 

the re/defueling shut-off valve. 

Post 

 SBF100-28-068 

Fokker 

Services 

W48006-401 

14.1 Level control 

pilot valve 

It shall be ensured that only a level 

control pilot valve with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

All Parker 

Hannifin 

2630427 

2630427M1 

14.2 Level control 

pilot valve 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Parker 

Hannifin 

2630427 

2630427M1 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

14.3a In-line fuse 

assembly in 

wiring of LCPV 

solenoid 

It shall be ensured that the over-current 

protection fuse assembly is properly 

installed in the power supply wire of the 

LCPV solenoid, close to the point where 

the wiring enters the tank, and that the 

assembly is undamaged. 

Post 

 SBF100-28-042, 

Pre 

 SBF100-28-068 

N.A. N.A. 

14.3b In-line fuse 

assemblies in 

wiring of LCPV 

solenoid 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in the power supply wire and in 

the return wire of the solenoid of the 

LCPV, close to the point where the 

wiring enters the tank, and that the fuse 

assemblies are undamaged. 

Post 

 SBF100-28-068 

N.A. N.A. 

14.4a In-line fuse 

assembly in 

wiring of LCPV 

solenoid 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in the wiring of the 

LCPV solenoid. 

Post 

 SBF100-28-042, 

Pre 

 SBF100-28-068 

Fokker 

Services 

W48006-401 

14.4b In-line fuse 

assemblies in 

wiring of LCPV 

solenoid 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in the power supply wire 

and in the return wire of the solenoid of 

the LCPV. 

Post 

 SBF100-28-068 

Fokker 

Services 

W48006-401 

15.1 Overflow valve It shall be ensured that only an overflow 

valve with a part number approved by 

the TCH under Fuel Tank Safety 

requirements will be installed on the 

aircraft. 

All Flight 

Refueling 

1608555 

1608565 

15.2 Overflow valve In case of opening and closing of tank 

access panel 526BB and/or 626BB, It 

shall be ensured that the sense line and 

wiring conduit (hoses) to the wing 

overflow valve remain routed and 

clamped in accordance with the 

configuration defined in SBF100-28-

050. 

Post 

 SBF100-28-050 

N.A. N.A. 

15.3 Overflow valve It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Flight 

Refueling 

1608555 

1608565 

15.4 In-line fuse 

assemblies in 

wiring of the 

overflow valve 

reed switch 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in the power supply wire and in 

the return wire of the overflow valve 

reed switch, close to the point where the 

wiring enters the tank, and that the fuse 

assemblies are undamaged. 

Post 

 SBF100-28-068 

N.A. N.A. 

15.5 In-line fuse 

assemblies in 

wiring of the 

overflow valve 

reed switch 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in the power supply wire 

and in the return wire of the overflow 

valve reed switch. 

Post 

 SBF100-28-068

Fokker 

Services 

W48006-403 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

16.1 Level sensor 

ICWT 

It shall be ensured that only a level 

sensor with a part number approved by 

the TCH under Fuel Tank Safety 

requirements will be installed on the 

aircraft. 

A/C with ICWT Smiths 

Industries 

0104KLS-1 

16.2 Level sensor 

ICWT 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

A/C with ICWT Smiths 

Industries 

0104KLS-1 

16.3 In-line fuse 

assemblies in 

wiring of the 

ICWT level 

sensors 

It shall be ensured that an over-current 

protection fuse assembly is properly 

installed in two of the three wires to 

each of the two level sensors in the 

ICWT, close to the point where the 

wiring enters the tank, and that the fuse 

assemblies are undamaged. 

A/C with ICWT, 

Post 

 SBF100-28-078 

N.A. N.A. 

16.4 In-line fuse 

assemblies in 

wiring of the 

ICWT level 

sensors 

It shall be ensured that only a fuse 

assembly with a part number approved 

by the TCH under Fuel Tank Safety 

requirements for the specific application 

will be installed in two of the three wires 

to each of the two level sensors in the 

ICWT. 

A/C with ICWT, 

Post 

 SBF100-28-078 

Fokker 

Services 

W48006-405 

17.1 Transfer-pump 

CWBT/ICWT 

It shall be ensured that only a CWT 

transfer pump with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

A/C with CWBT or 

ICWT 

Intertechnique 218386-6 

17.2 Transfer-pump 

CWBT/ICWT 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

A/C with CWBT or 

ICWT 

Intertechnique 218386-6 

18 FWC It shall be ensured that only a FWC with 

a part number approved by the TCH 

under Fuel Tank Safety requirements 

will be installed on the aircraft. 

A/C with CWBT or 

ICWT 

Honeywell 80-0610-3-55 

19.1 CPT It shall be ensured that only a CPT with 

a part number approved by the TCH 

under Fuel Tank Safety requirements 

will be installed on the aircraft. 

All Smiths 

Industries 

0102KIP01-002 

0102KIP01-007 

0102KIP01-017 

0102KIP02-018 

0102KIP01-021 

0106KIP02-022 

0201KIP01-003 

0202KIP02-004 

0201KIP03-001 

0202KIP02-002 

0202KIP04-002 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description Effectivity Vendor 

(note 1) 

CDCCL-approved 

part no. 

(note 1) 

19.2 CPT It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

All Smiths 

Industries 

0102KIP01-002 

0102KIP01-007 

0102KIP01-017 

0102KIP02-018 

0102KIP01-021 

0106KIP02-022 

0201KIP01-003 

0202KIP02-004 

0201KIP03-001 

0202KIP02-002 

0202KIP04-002 

20.1 ICWT switching 

unit 

It shall be ensured that only a ICWT 

switching unit with a part number 

approved by the TCH under Fuel Tank 

Safety requirements will be installed on 

the aircraft. 

A/C with ICWT Smiths 

Industries 

0201KSS01 

20.2 ICWT switching 

unit 

It shall be ensured that the approved 

component maintenance and repair 

procedures are adhered to during shop 

maintenance. 

A/C with ICWT Smiths 

Industries 

0201KSS01 

21 Drain holes and 

drain paths of 

wing dry bay 

zones 

It shall be ensured that the drain holes 

and drain paths of the dry bay zones 

adjacent to the wing tanks are open and 

unobstructed. 

All N.A. N.A. 

22 Protection 

plates in keel 

tunnel below 

ICWT 

It shall be ensured that the protection 

plates between ICWT bottom skin and 

bleed air duct in the keel tunnel are in 

place and properly installed, and that 

the drain provision for the space 

between protection plate and ICWT 

bottom skin is properly installed and has 

an open flow path. 

A/C with ICWT Fokker 

Services 

D31188-023 

D31188-025 

D31188-027 

23.1 Switch 

operating cam - 

Fuelling Panel 

switch 

In case of replacement or 

removal/installation of the Fueling 

Control Panel (FCP) , the access door 

to the FCP or the FCP power switch 

operating cam mounted on the access 

door it shall be verified after installation 

that the switch operating cam is 

installed and functions correctly. 

A/C S/N’s 11244 

thru 11441, 

A/C S/N’s 11442 

and up if pre 

SBF100-28-042 

or pre SBF100-

28-068. 

N.A. N.A. 

23.2 Switch 

operating cam - 

Fuelling Panel 

switch 

It shall be ensured that only a FCP 

power switch operating cam with a part 

number approved by the TCH under 

Fuel Tank Safety requirements will be 

installed. 

A/C S/N’s 11244 

thru 11441 if post 

SBF100-28-063, 

A/C S/N’s 11442 

and up. 

Fokker 

Services 

D48127-009 

Note 1: Vendor and part number data is only provided where the CDCCL consists of control of part 

number(s) at the installation or of control of application of proper maintenance / repair procedures 

of the part. 
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temp. 0863 12-06

3.3. CDCCL description and control (AFTS only) 

Note: The Auxiliary Fuel Tank System (AFTS) for F28 Mk0100 is installed in accordance with 

SBF100-28-055 (ECR 015347). 

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description (part number) 

(note 1)

Applicable 

to: 

AFTS 1 AFTS bonding 

provisions in RH wing 

tank. 

It shall be assured that the bonding configuration and 

condition of the AFTS vent/overflow line in the RH wing 

tank is maintained after each tank entry. 

Mk0100, 

Post ECR 

015347 

AFTS 2 AFTS bonding 

provisions in RH wing 

root fairing space and 

space between front and 

auxiliary spar. 

1) It shall be assured that the bonding configuration 

and condition of the bonding of the AFTS vent/overflow 

line in the RH wing root fairing space and space 

between front and auxiliary spar is maintained after 

each entry. 

2) It shall be assured that the configuration and 

condition of the bonding provisions on the diverter rods 

in the RH wing root fairing space are maintained after 

each entry. 

Mk0100, 

Post ECR 

015347 

AFTS 3 AFTS diverter rods in 

RH wing fairing root 

space 

It shall be assured that a minimum distance is 

maintained between the diverter rods in the RH wing 

root fairing and the transfer/vent lines. 

Mk0100, 

Post ECR 

015347 

AFTS 4 Shielding box AFTS 

transfer line in RH wing 

fairing root space. 

It shall be assured that the shielding box is present, 

undamaged and correctly installed. 

Mk0100, 

Post ECR 

015347 

AFTS 5 AFTS purge/drain 

system provisions in RH 

wing root fairing space. 

It shall be assured that: 

a) the drain system configuration is intact, and 

b) the connections are secure, and 

c) the parts are free of damage, and 

d) the flow paths are open. 

Mk0100, 

Post ECR 

015347 

AFTS 6 AFTS fill/transfer and 

vent/overflow flexible 

hoses inside AFT 

compartment. 

It shall be assured that only replacement parts with 

part number 5945-2811-331-XXX are installed. 

Mk0100, 

Post ECR 

015347 

AFTS 7 AFTS fill/transfer and 

vent/overflow shrouds 

and sleeves inside AFT 

compartment. 

1) It shall be assured that the shrouds and sleeves are 

free of damage after each compartment entry. 

Mk0100, 

Post ECR 

015347 

AFTS 8 2) It shall be assured that the shrouds are free from 

leaks each time parts are reconnected. 

AFTS 9 3) It shall be assured that only replacement parts with 

part number 5945-2811-331-XXX or part number 

5945-2811-101-XXX are installed. 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description (part number) 

(note 1)

Applicable 

to: 

AFTS 10 AFTS bleed-air blast 

shield (protection plates) 

inside AFT 

compartment. 

It shall be assured that the heat shield between the 

bleed-air duct and the aux fuel tanks is present, 

undamaged and correctly installed. 

Mk0100, 

Post ECR 

015347 

AFTS 11 AFTS FWD and MID 

tank purge/drain system 

inside AFT 

compartment. 

It shall be assured that: 

a) the drain system configuration is intact, and 

b) the connections are secure, and 

c) the parts are free of damage, and 

d) the flow paths are open. 

Mk0100, 

Post ECR 

015347 

AFTS 12 AFTS restrictor in bleedair supply line. 

It shall be assured that only a replacement part with 

part number W98823-023 is installed 

Mk0100, 

Post ECR 

015347 

AFTS 13 AFTS FWD and MID 

tank air inlet 

configuration. 

It shall be assured that the air inlet configuration 

consisting of bleed-air line, check valves and cabin air 

inlet duct plus flame-arrester are correctly installed and 

free of damage. 

Mk0100, 

Post ECR 

015347 

AFTS 14 Bonding provisions 

between AFTS tanks 

and aircraft structure. 

It shall be assured that the bonding straps are present, 

correctly installed and free of damage. 

Mk0100, 

Post ECR 

015347 

AFTS 15 AFPU It shall be assured that only a replacement AFPU with 

part number 22492-057 is installed. 

Mk0100, 

Post ECR 

015347 

AFTS 16 AFPU bonding 

provisions. 

It shall be assured during AFPU installation that the 

connector and receptacle pins and bushes are in good 

condition. 

Mk0100, 

Post ECR 

015347 

AFTS 17 AFPU installation. It shall be assured that the AFPU is properly installed 

and undamaged. 

Mk0100, 

Post ECR 

015347 

AFTS 18 AFIU It shall be assured that only a replacement AFIU with 

part number 201-5-954-051 is installed. 

Mk0100, 

Post ECR 

015347 

AFTS 19 AFIU bonding 

provisions. 

It shall be assured during AFIU installation that the 

connector and receptacle pins and bushes are in good 

condition. 

Mk0100, 

Post ECR 

015347 

AFTS 20 AFIU installation It shall be assured that the AFIU is properly installed 

and undamaged. 

Mk0100, 

Post ECR 

015347 

AFTS 21 AFPU safe harness It shall be assured that the configuration of the wire 

harness between the AFPU and the tank connections 

is intact and the harness is: 

a) Free of damage, and 

b) Clamped properly, and 

c) Separated from other wiring. 

Mk0100, 

Post ECR 

015347 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description (part number) 

(note 1)

Applicable 

to: 

AFTS 22 AFIU safe harnesses It shall be assured that the configuration of the wire 

harnesses between AFIU 1 and 2, and the tank 

connections are intact and the harnesses are: 

a) Free of damage, and 

b) Clamped properly, and 

c) Separated from other wiring. 

Mk0100, 

Post ECR 

015347 

AFTS 23 AFTS level switches It shall be assured that only a replacement level switch 

with part number 200-5-797-XX is installed. Mk0100, 

Post ECR 

014347 

AFTS 24 AFTS pressure switches It shall be assured that only a replacement pressure 

switch with part number 12H0096D (4.5 psi) or part 

number 12H0096-101D (10 psi) is installed. 

Mk0100, 

Post ECR 

015347 

AFTS 25 AFTS FQI and 

compensator probes. 

It shall be assured that only a replacement FQI probe 

with part number 22003-9 or compensator probe with 

part number 22004-9 is installed 

Mk0100, 

Post ECR 

015347 

AFTS 26 FQI wiring inside AFTS 

tanks 

It shall be assured during each tank entry that the 

insulation of the wiring inside the tank is free of 

damage. 

Mk0100, 

Post ECR 

015347 

AFTS 27 Level switches inside 

AFTS tanks 

It shall be assured during each tank entry that the level 

switch assembly parts are properly secured and 

undamaged. 

Mk0100, 

Post ECR 

015347 

AFTS 28 Bonding provisions 

within the AFTS tanks 

It shall be assured during each tank entry that the 

bonding provisions within the tank are undamaged. 

Mk0100, 

Post ECR 

015347 

AFTS 29 Bonding provisions 

AFTS tank cell 

interconnects 

It shall be assured that new spring clips are installed 

on the interconnect gland whenever tanks are 

installed. 

Mk0100, 

Post ECR 

015347 

AFTS 30 AFTS fuel/no-air valve It shall be assured that only a replacement fuel/no-air 

valve with part number 200-5-482-69 (base assy) and 

42260-11 (float) is installed. 

Mk0100, 

Post ECR 

015347 

AFTS 31 AFTS sump drain valve It shall be assured that only a replacement sump drain 

valve with part number 79C20C is installed. 

Mk0100, 

Post ECR 

015347 

AFTS 32 AFTS valve actuators in 

tank dry-bays. 

1) Each time the dry-bay is opened it shall be assured 

that the actuator wire loom and bonding provisions 

are undamaged. 

Mk0100, 

Post ECR 

015347 

2) It shall be assured that only a replacement valve 

assy with part number 236535-1 is installed. 
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temp. 0863 12-06

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL 

number 

Component(s) Description (part number) 

(note 1)

Applicable 

to: 

AFTS 33 AFTS limitation placard 

adjacent to forward AFT 

compartment door. 

It shall be assured that a placard with the following 

limitation text is present: 

ACCESS FOR AUTHORISED PERSONNEL ONLY. 

CARRYING OF CARGO, LUGGAGE OR BALLAST IS 

PROHIBITED 

Mk0100, 

Post ECR 

015347 

Note 1: Part number data is only provided where the CDCCL consists of control of part number(s) at the 

installation or of control of application of proper maintenance / repair procedures of the part. 
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temp. 0863 12-06

4. Abbreviations 

A/C Aircraft 

AFIU Auxiliary Fuel Isolation Unit 

AFPU Auxiliary Fuel Processing Unit 

AFTS Auxiliary Fuel Tank System 

ALI Airworthiness Limitations Item 

ALS Airworthiness Limitations Section 

ARC Airworthiness Recommendations Catalogue 

CDCCL Critical Design Configuration Control Limitation 

CMR Certification Maintenance requirement 

CPT Combined Processor Totalizer 

CS Certification Specifications 

CWT Center Wing Tank 

CWBT Center Wing Bag Tank 

EASA European Aviation Safety Agency 

ECR Engineering Change Request 

FAR Federal Aviation Regulation 

FC Flight Cycles 

FC Finish Code 

FCP Fuel Control Panel 

FH Flight Hour 

FQI Fuel Quantity Indication 

FQIS Fuel Quantity Indication System 

FWC Flight Warning Computer 

FWD Forward 

ICA Instructions for Continued Airworthiness 

ICWT Integral Centerwing Tank 

JAR Joint Aviation Requirement 

LCPV Level Control Pilot Valve 

MID Middle 

Mk Mark 

MLG Main Landing Gear 

MO Months 

MRB Maintenance Review Board 

N.A. Not Applicable 

NC Norm Constructie (Dutch) / Design Standard 

OFV Overflow Valve 

RH Right Hand 

SB Service Bulletin 

SLI Safe Life Item 

TH Technical Handbook 

TCH Type Certificate Holder 

TFV Transfer / Fill Valve 

YR Year