# Service Bulletin Fokker Services B.V.

Prepared Function / Note Date moen-hm02430 Dec 09/14 Colleague Check gelder-rg02568 Dec 09/14 Manager Final Approval
benthem-eb01865 Dec 11/14 Office of Airworthiness Approval reinier.vanoosten Dec 11/14

Status: Released Revision: 3 Released date: ( Mmm dd/yy 

### ) Dec 11/14 Security class: UNCLASSIFIED F28 Generic SB no.: SBF28-28-050

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V.
EASA approved procedure for electronic sign-off 

# F28 Generic SB

SBF28-28-050

Revision 3

FUEL - GENERAL

Introduction of Fuel Airworthiness Limita tion Items (ALI) a nd Critical Design Configuration Control Limitations ( CDCCL) for the F28 Mk1000/2000/3000/4000.

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 1

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## This Service Bulletin cancels Service Bulletin SBF28-28-055



## 1. Planning Information

A. Effectivity

(1) F28 aircraft serial numbers: 11003 thru 11241 11991 and 11992

(2) Production version of this modification: Not applicable.

B. Concurrent Requirements

(1) Not applicable.

C. Reason (1) In accordance with the requirements of SFAR no. 88 Amendment 21-78 and INT/POL/25/12 Fuel Tank Safety, a safety review has been conducted on the F28 Mk1000/2000/3000/4000 fuel tank system and components that affect fuel tank system safety.

Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17

Revision 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3

Page 18 19 20

Revision 3 3 3 FUEL

" This Service Bulletin is associated with the Fuel Tank Safety Program. "

Fuel - Introduction of Fuel Airworthiness Limitation Items (ALI) and Critical Design Configuration Control Limitations (CDCCL) for the F28 Mk1000/2000/3000/4000.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 2 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## Reason for Revision

(2) This revision is made to:

- Amend the Fuel ALI Task Descriptions to include the TASK DESCRIPTION in accordance with Maintenance Manual 28-00-01, pageblock 601 (Fuel ALI’s 280000-01 thru -08),

- Add reference ECR016135,

- Delete “Note 1” (applicable for Fuel ALI 280000-01),

- Amend “Note 3” (applicable for Fuel ALI 280000-05),

- Amend “Note 4” (applicable for Fuel ALI 280000-06),

- Re-identification of CDCCL 7 into CDCCL 7.1 and introduction of CDCCL 7.2,

- Introduction of CDCCL 25.1a, 25.1b, 25.2a, 25.2b,

- Amend “Note 2” applicable for CDCCL 1.1,

- Make a reference to Maintenance Manual 28-00-01, pageblock 601 for the Fuel ALI tasks maintenance inspection procedures.

- Make a reference to Maintenance Manual 28-00-01, pageblock 201 for:

o a list of access panels in relation to the CDCCL inspection(s),

o an overview of CDCCL affected sections in the Maintenance Manual,

- Amend the reference to the current EASA AD in the first NOTE in the Compliance paragraph.

D. Description

(1) Based on the results of the safety review, this Service Bulletin specifies the Fuel Airworthiness Limitation Items (ALI) and the Critical Design Configuration Control Limitations (CDCCL) required to prevent the development of unsafe conditions within the fuel system. Fuel Airworthiness Limitation Items (ALI): 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 airplane. Critical Design Configuration Control Li mitations (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. 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.

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 3

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## E. Compliance

(1) Recommended.

Fokker Services recommends to incorporate and to adhere to the information in this Service Bulletin in accordance with the compliance terms as specified in the (new or revised) EASA Airworthiness Directive

NOTE : EASA Airworthiness Directive 2014-0110, has been issued with respect to this subject.

NOTE: It is expected that EASA will issue a (new or revised) Airworthiness Directive (AD) with respect to this subject with the same compliance terms. Refer to the EASA website for the publication of a Proposed Airworthiness Directive for comments.

F. Approval

(1) The technical content of this document is approved under the authority of DOA ref. EASA.21J.059.

G. Manpower

(1) None.

H. Weight and Balance

(1) Weight change: None Index change: None.

I. Electrical Load Data

(1) Not changed.

J. Software Accomplishment Summary

(1) Not applicable.

K. References

(1) Fokker internal reference(s):

- Fokker Services report TE-0901, - ECR016135.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 4 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## L. Publications Affected

(1) This SB affects the publications listed below:

(a) Maintenance Documentation

- F28 Maintenance Manual (MM) - F28 Illustrated Parts Catalog (IPC) - F28 Wiring Diagram Manual (WDM)

(b) Maintenance Programs

- F28 Maintenance Program

The affected maintenance program change is described in:

“3. Accomplishment Instructions”.

(c) Special Instructions for Continued Airworthiness (ICA)

The effect of this Service Bulletin on the special ICA is as follows:

YES NO - Electrical Wiring Interconnection System (EWIS) - X - Fuel Tank Safety (FTS) X -

NOTE : If “YES”, the changed ICA is described in the “Accomplishment Instructions” of this SB.

(d) Operational Documentation

Not affected.

(2) You have the possibility to send your SB feedback to Fokker Services per “Quality Reporting Form”. This form is located on the last SB page.

(3) For incorporation of this Service Bulletin in your documentation refer to SBF28-00-001 (Service Bulletin Introduction, section 4 "Incorporation of Service Bulletins in Documentation of Fokker Services").

M. Interchangeability or Intermixability of Parts

(1) Not applicable.

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 5

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## 2. Material Information

A. Material – Price and Availability

(1) Not applicable.

B. Material Required

(1) Not applicable.

C. Tooling – Price and Availability

(1) Not applicable.

D. Drawings Required

(1) Not applicable.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 6 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## 3. Accomplishment Instructions

A. Fuel Airworthiness Limitation Items

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 airplane.

Note: Maintenance Manual 28-00-01, pageblock 601 provides the maintenance inspection procedures for all Fuel ALI tasks.

FUEL AIRWORTHINESS LIMITATION ITEMS

Tasknumber Task Description Interval Effectivity Initial* Repeat*

280000-01 DETAILED INSPECTI ON OF FUEL QUANTITY INDICATION UNITS (FQT U’s) AND WIRING IN THE MAIN AND COLLECTOR TANK. A detailed inspection of the FQIS in the main and collector 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 

### A clearance of minimum 3 mm exists between

any metal probe part (including its wire terminals, excluding spring clips around plastic parts) and adjacent struct ure or other adjacent metal part

o 

### The tanks are clean and free of debris of any

kind.
Anomalies shall be corrected. 01/01/2010 4 YR ALL

280000-02 DETAILED INSPEC TION OF ELECTRICAL BONDING (MAIN 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. 01/01/2010 (see note 2) 4 YR ALL

280000-03 DETAILED INSPECTION OF THE DRAIN-HOLES IN THE DRY BAY ZONES. A detailed inspection of the drain holes and drain paths in the dry bay zones adjacent to wing 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. 01/01/2010 4 YR ALL

280000-04 Deleted

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 7

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## FUEL AIRWORTHINESS LIMITATION ITEMS

Tasknumber Task Description Interval Effectivity Initial* Repeat*

280000-05 DETAILED INSPECTION OF THE ATTACHMENT OF THE PROBES OF THE FUEL QUANTITY TANK UNITS. A detailed inspection of the attachment of the FQIS probes in the wing tanks shall be carried out to verify that the probe is firmly attached to its mounting flange and that the three attachment nuts, washers and stud ends of the probe attachment are completely covered with an undamaged layer of sealant.
Anomalies shall be corrected. 01/01/2010 (see note 3) 4 YR ALL

280000-06 OPERATIONAL CHECK OF THE AUTOMATIC OFF-SWITCHING OF TH E POWERSWITCH ON THE FUELING CONTROL PANEL.
It shall be ensured that the cam installed on the Fuel Load Limit Control Panel (FLLCP) access door functions properly. The function of the cam is that it forces the power sw itch of the FLLCP to the OFF position at closure of the access door.
Anomalies shall be corrected. 15/07/2012 (see note 4) 1200 FH A/C with CWT, post SBF28-28- 052

280000-07 FUNCTIONAL TEST OF THE COLLECTOR TANK LOW WARNING SYSTEM AND MAIN TANK TO COLLECTOR TANK TRANSFER SYSTEM. It shall be verified through performing a functional test that the collector tank low level warning system and main tank to collector tank transfer system function properly.
Anomalies shall be corrected. 01/08/2015 3000 FH ALL

280000-08 DETAILED INSPEC TION OF ELECTRICAL BONDING (CENTER WING TANK). A detailed inspection of the electrical bonding provisions of the CWT 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. 01/08/2015 (see note 5) 4 years A/C with CWT

* Not later than.

Notes:

1) DELETED

2) The initial inspection shall be done not later than Ja nuary 1, 2010 except for bonding provisions introduced through SBF28-28-058 and SBF28-28-059. For bonding in stalled with SBF28-28-058 or SBF28-28-059 the initial inspection date is the accomplishment date of that applicable Service Bulletin with which the bonding provisions have been introduced.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 8 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V.



### 3) The initial inspection shall be done not later than Januar y 1, 2010 except for the insp ection that the three probe attachment nuts, washers and stud ends are covered with seal ant. For this inspection, the initial inspection date is the accomplishment date of SBF28-28-054 with which the sealant has been introduced.

4) 

### The initial inspection date is the accomplishment date of th e check of the function of the cam in accordance with step D of part 2 of SBF28-28-052.

5) 

### The initial inspection shall be done not later than August 1, 2015 except for bonding provisions introduced through SBF28-28-058 and SBF28-28-059. For bonding installed with SBF28-28-058 or SBF28-28-059 the initial inspection date is the accomplishment date of that applicable Service Bulletin with which the bonding provisions have been introduced.

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 9

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## B. 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 document, 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 m onths 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. It is the operator's responsibility 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 Limitations) This paragraph in the Fuel Airworthiness Limitation Item document 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.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 10 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## C. 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 dur ing modification, change, repair or scheduled maintenance to ensure that an unsafe condition does not develop in the fuel system.

Note: Maintenance Manual 28-00-01, pageblock 201 gives a list of access panels in relation to the CDCCL inspection(s) and an overview of CDCCL affected sections in the Maintenance Manual.

CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (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, excluding spring clips around plastic parts) is closer than 3 mm to adjacent structure or other adjacent metal part. All A/C (note 2) N.A. N.A.

1.2a FQIS probes in wing tanks It shall be assured that the three mounting nuts connecting the wing tank FQIS probes to the mounting plate are fixed. A/C pre SBF28-28- 054 N.A. N.A.

1.2b FQIS probes in wing tanks It shall be ensured that each FQIS probe in the wing tanks is firmly attached to its mounting flange and that the three attachment nuts, washers and stud ends of the probe attachment are completely covered with an undamaged layer of sealant approved for the purpose. A/C post SBF28-28- 054 (note 3) N.A. N.A.

1.3 FQIS probes in 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 A/C Simmonds Precision 391057-06097 391057-06245 391057-06096 391057-06095 391057-06098 391057-06246 391057-06094 391057-06093 391057-06092 (positions 1 to 9 respectively) 391063-04003, 391063-04003M (position10)

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 11

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)
1.4 FQIS probes in wing tanks It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C Simmonds Precision 391057-06097 391057-06245 391057-06096 391057-06095 391057-06098 391057-06246 391057-06094 391057-06093 391057-06092 (positions 1 to 9 respectively) 391063-04003, 391063-04003M (position10) 1.5 FQIS wiring in wing tanks It shall be ensured that the FQIS wiring in the wing tanks is undamaged and correctly installed. All A/C N.A. N.A.

1.6 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 A/C N.A. N.A.

1.7 FQIS wiring in wing tanks It shall be ensured that a by-pass wire is installed between the cable shield and the outside surface of the plug housing at the in-tank coaxial plugs of the FQIS shielded wiring at the locations EK15- 710, 2EK15-720, EK24-710, 2EK24-720, EK26-731, 2EK26-741. A/C sn. 11003 - 11041, 11991 - 11994 if post SBF28-28-053 N.A. N.A.

1.8 FQIS wiring in wing tanks For the in-tank coaxial plugs of the FQIS shielded wiring at the locations EK12- 731, 2EK12-741, EK15-710, 2EK15-720, EK18-710, 2EK18-720, EK21-710, 2EK21-720, EK24-710, 2EK24-720, EK26-731 and/or 2EK26-741 it shall be ensured that in the event a plug is replaced only a plug with a part number approved by the TCH under Fuel Tank Safety requirements for the specific application will be installed. A/C sn. 11042 - 11241 Souriau

Bendix 20P227-1 20P227-2 20P228-1

6197-1 6187-1 6194-1

2.1 FQIS probe in CWT 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 CWT will be installed on the aircraft. A/C with CWT Simmonds Precision 391088-001, 391088-007

2.2 FQIS probe in CWT It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT Simmonds Precision 391088-001, 391088-007

3 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 A/C N.A. N.A.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 12 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)
4 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 A/C N.A. N.A.

5 Bonding of fuel lines, ventilation lines and components, CWT It shall be ensured that the configuration and quality of bonding provisions of fuel lines and ventilation lines connected to the CWT and of the drain line of the CWT compartment are conforming to the design (ref. NC 4.610 /xxx). A/C with CWT N.A. N.A.

6 Anti-splash provisions in main wing tanks It shall be ensured that below the openings in upper skin top hat stringers 2.32 – 2.35 just inboard and outboard of the closed rib at wing station 4700 four closing plates (inboar d side) and a fuel release bracket (outboard side) are in place and that these are firmly attached and undamaged. All A/C N.A. N.A.

7.1 Anti-spray coverre/defueling shutoff 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 A/C N.A. N.A.

7.2 Anti-spray coverre/defueling shutoff 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. All A/C Fokker Services A69218-009 (LH & RH)

8.1 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 A/C Intertechnique SA 2090JFA

8.2 Boost-pump It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C Intertechnique SA 2090JFA

9.1 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 A/C FR-HiTemp (currently: Eaton Aerospace Ltd) 3515000-127 3515000-135

9.2 Collector tank level float switch It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C FR-HiTemp (currently: Eaton Aerospace Ltd) 3515000-127 3515000-135

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 13

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)

9.3a In-line fuse assembly 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 of the collector tank level float switch, close to the point where the wiring enters the tank, and that the fuse assembly is undamaged. A/C post SBF28-28- 049, pre SBF28-28- 056 (note 4) N.A. N.A.

9.3b 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 signal wire of the collector tank level float switch, close to the point where the wiring enters the tank, and that the fuse assemblies are undamaged. A/C post SBF28-28- 056 N.A. N.A.

9.4a In-line fuse assembly 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 of the collector tank level float switch. A/C post SBF28-28- 049, pre SBF28-28- 056 (note 4) Fokker Services W48006-403

9.4b 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 signal wire of the collector tank level float switch. A/C post SBF28-28- 056 Fokker Services W48006-403

10.1 Re/defueling shutoff valve It shall be ensured that only a re/defueling shut-off valve with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. All A/C Parker Hannifin Corporation 2630486M3 2630486M4

10.2 Re/defueling shutoff valve It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C Parker Hannifin Corporation 2630486M3 2630486M4

10.3 In-line fuse assemblies in wiring of solenoid of re/defueling 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. A/C post SBF28-28- 056 N.A. N.A.

10.4 In-line fuse assemblies in wiring of solenoid of re/defueling 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. A/C post SBF28-28- 056 Fokker Services W48006-401

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 14 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)
11.1 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 A/C Parker Hannifin Corporation 2630427 2630427B 2630427M1

11.2 Level control pilot valve It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C Parker Hannifin Corporation 2630427 2630427B 2630427M1

11.3a 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. A/C post SBF28-28- 051, pre SBF28-28- 056 (note 5) N.A. N.A.

11.3b 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. A/C post SBF28-28- 056 N.A. N.A.

11.4a 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 power supply wire of the LCPV solenoid. A/C post SBF28-28- 051, pre SBF28-28- 056 (note 5) Fokker Services W48006-401

11.4b 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. A/C post SBF28-28- 056 Fokker Services W48006-401

12.1 Main tank 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 A/C FR-HiTemp (currently: Eaton Aerospace ltd) 1608565 1608555

12.2 Main tank overflow valve It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. All A/C FR-HiTemp (currently: Eaton Aerospace ltd) 1608565 1608555

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 15

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)

12.3 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. A/C post SBF28-28- 056 N.A. N.A.

12.4 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. A/C post SBF28-28- 056 Fokker Services W48006-403

13.1 Transfer-pump CWT 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 CWT Intertechnique SA 2090E01A (only A/C sn 110020) 2090E01B

13.2 Transfer-pump CWT It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT Intertechnique SA 2090E01A (only A/C sn 110020) 2090E01B

14.1 Analogue fuel quantity indicator wing tanks It shall be ensured that only an analogue fuel quantity indicator with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C pre SBF28-28- 039, pre SBF28-28- 043 Simmonds Precision 393084-031 393084-22825 393084-22488

14.2 Analogue fuel quantity indicator wing tanks It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C pre SBF28-28- 039, pre SBF28-28- 043 Simmonds Precision 393084-031 393084-22825 393084-22488

15.1 Analogue fuel quantity Indicator CWT It shall be ensured that only an analogue fuel quantity indicator with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C with CWT, pre SBF28-28-043 Simmonds Precision 393084-036 393084-054

15.2 Analogue fuel quantity Indicator CWT It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT, pre SBF28-28-043 Simmonds Precision 393084-036 393084-054

16.1 Analogue load limit controller wing tanks It shall be ensured that only an analogue load limit controller with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C pre SBF28-28- 039, pre SBF28-28- 043 Simmonds Precision 384369-01488 384369-01825

16.2 Analogue load limit controller wing tanks It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C pre SBF28-28- 039, pre SBF28-28- 043 Simmonds Precision 384369-01488 384369-01825

17.1 Analogue load limit controller CWT It shall be ensured that only an analogue load limit controller with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C with CWT, pre SBF28-28-043 Simmonds Precision 384369-020 384369-023

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 16 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)
17.2 Analogue load limit controller CWT It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT, pre SBF28-28-043 Simmonds Precision 384369-020 384369-023

18.1a Digital fuel quantity Indicator (2-tank system only) It shall be ensured that only a digital fuel quantity indicator with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 2300-03-1

18.1b Digital fuel quantity Indicator (2 and 3 tank systems) It shall be ensured that only a digital fuel quantity indicator with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C post SBF28-28- 043 Smiths industries 2300-03-2

18.2a Digital fuel quantity Indicator (2-tank system only) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 2300-03-1

18.2b Digital fuel quantity Indicator (2 and 3 tank systems) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C post SBF28-28- 043 Smiths industries 2300-03-2

19.1a Digital calibration trim unit wing tanks (2-tank system only) It shall be ensured that only a digital calibration trim unit with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 4215-01

19.1b Digital calibration trim unit wing tanks (2 and 3 tank systems) It shall be ensured that only a digital calibration trim unit with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C post SBF28-28- 043 Smiths industries 4215-03

19.2a Digital calibration trim unit wing tanks (2-tank system only) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 4215-01

19.2b Digital calibration trim unit wing tanks (2 and 3 tank systems) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C post SBF28-28- 043 Smiths industries 4215-03

20.1 Digital calibration trim unit CWT It shall be ensured that only a digital calibration trim unit with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C with CWT, post SBF28-28-043 Smiths industries 4215-13

20.2 Digital calibration trim unit CWT It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT, post SBF28-28-043 Smiths industries 4215-13

21.1a Digital load limit controller (2 tank system only) It shall be ensured that only a digital load limit controller with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 2300-03-1

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 17

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## CRITICAL DESIGN CONFIGURATION CONTROL LIMITATIONS

CDCCL number Component(s) CDCCL Description Effectivity: V endo r

(note 1) CDCCL-approved part numbers (note 1)
21.1b Digital load limit controller (2 and 3 tank systems) It shall be ensured that only a digital load limit controller with a part number approved by the TCH under Fuel Tank Safety requirements will be installed on the aircraft. A/C with CWT, post SBF28-28-043 Smiths industries 2300-03-2

21.2a Digital load limit controller (2 tank system only) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C post SBF28-28- 039, pre SBF28-28- 043 Smiths industries 2300-03-1

21.2b Digital load limit controller (2 and 3 tank systems) It shall be ensured that the approved component maintenance and repair procedures are adhered to during shop maintenance. A/C with CWT, post SBF28-28-043 Smiths industries 2300-03-2

22 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 A/C N.A. N.A.

23 Drain system of center wing box It shall be ensured that the drain holes and drain paths of the drain system of the center wing box that houses the CWT bladder tanks are open and unobstructed. A/C with CWT N.A. N.A.

24 Switch operating cam - fueling panel power switch In case of replacement or removal/installation of the Fuel Load Limit Control Panel (FLLCP) , the access door to the FLLCP or the FLLCP power switch operating cam mounted on the access door it shall be verified after (re)installation that a switch operating cam with a part number approved by the TCH under Fuel Tank Safety requirements is installed and functions correctly. A/C with CWT, post SBF28-28-052 (note 6) Fokker Services A42509-089

25.1a 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 A/C N/A N/A

25.1b 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 A/C Fokker Services

AMAL A69543-401 A69543-403188-26-15-45FA188-206-15-45SS 188-26-15-45SS316
25.2a 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 CWT N/A N/A

25.2b 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 CWT Fokker Services

AMAL A69742-401 A69742-403188-26-15-45FA188-206-15-45SS 188-26-15-45SS316



### Notes:

1) Vendor and part number data is onl y provided where the CDCCL consists of control of part number(s) at the installation or of control of application of pr oper maintenance / repair procedures of the part.

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 18 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

### 2) For aircraft in the post SBF28-57-098 co nfiguration, this CDCCL it is not applic able after the removal and installation of a FQTU when no fuel tank access panel(s) was removed. 3) Operators that have introduc ed changes to the manuals in accordance with the instructions in the original issue of MCNM-F28-037 (attached to the original issue of SBF28-28- 054) must make additional changes to the manuals in accordance with the instructions in revision 1 of MCNM F28-037. 4) Operators that have introduc ed changes to the manuals in accordance with the instructions in the original issue of MCNM-F28-035 (attached to the original issue of SBF28-28- 049) must make additional changes to the manuals in accordance with the instructions in revision 1 of MCNM F28-035. 5) Operators that have introduc ed changes to the manuals in accordance with the instructions in the original issue of MCNM-F28-034 (attached to the original issue of SBF28-28- 051) must make additional changes to the manuals in accordance with the instructions in revision 1 of MCNM F28-034. 6) Operators that have introduc ed changes to the manuals in accordance with the instructions in the original issue of MCNM-F28-033 (attached to the original issue of SBF28-28- 052) must make additional changes to the manuals in accordance with the instructions in revision 1 of MCNM F28-033.

# Service Bulletin Fokker F28

Jun 30/06 SBF28-28-050 Revision 3, Dec 11/14 Page 19

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

## D. Abbreviations.

A/C Aircraft AD Airworthiness Directive ALI Airworthiness Limitation Items CDCCL Critical Design Configuration Control Limitations CWT Center Wing Tank DOA Design Organisation Approval EASA European Aviation Safety Agency EWIS Electrical Wiring Interconnection System FH Flight Hours FC Flight Cycles FLLCP Fuel Load Limit Control Panel FTS Fuel Tank Safety FQIS Fuel Quantity Indication System ICA Instructions for Continued Airworthiness LCPV Level Control Pilot Valve MO Month Mk Mark NC Norm Constructie (Dutch) / Design Standard SB Service Bulletin TCH Type Certificate Holder YR Year

# Service Bulletin Fokker F28

SBF28-28-050 Jun 30/06 Page 20 Revision 3, Dec 11/14

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained there in for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except with the prior written permission of Fokker Services B.V. 

# Service Bulletin Quality Reporting Form

Use this Service Bulletin Quality Reporting Form to tell us your perception of the quality of the Service Bulletin. The reported data that you provide to us will be used to analyze areas of difficulties and to take corrective actions to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form.

* Rate the scale of 1 to 4, with 1 the lowest score and 4 the highest score. Chapters * 

## 1 2 3 4

a) Quality rating of this SB (overall) 

# □ □ □ □
b) Quality rating of the Planning Information 

# □ □ □ □
c) Quality rating of the Material Information 

# □ □ □ □
d) Quality rating of the Accomplishment Instructions 

# □ □ □ □
e) Quality rating of the Test Instructions (if applicable) 

# □ □ □ □
f) Quality rating of the Illust rations or Drawings (if applicable) 

# □ □ □ □
g) Timely delivery of the SB 

# □ □ □ □

If you have had difficulties with one of the chapters of this Service Bulletin and/or one of your rating(s) is lower than 3, please give a short description of the issue.

Comments:

Operator: Date:

Name / Title:

Please return this form to: Fokker Services B.V. Technical Services, Quality Department P.O. Box 1357 2130 EL Hoofddorp The Netherlands Fax: +31 (0) 88 6280111 or Email: technicalservices@fokker.com