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 therein 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 Limitation Items (ALI) and 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 therein 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 therein 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 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. 

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 therein 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 

Indexchange: 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 therein 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 therein 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 therein 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 INSPECTION OF FUEL QUANTITY 

INDICATION UNITS (FQTU’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 structure 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 INSPECTION 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 therein 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 THE 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 switch 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 INSPECTION 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 January 1, 2010 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 

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 therein 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 January 1, 2010 except for the inspection that the three probe 

attachment nuts, washers and stud ends are covered with sealant. 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 the 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 therein 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 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. 

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 therein 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 during 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: Vendor

(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 therein 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: Vendor

(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 therein 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: Vendor

(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 (inboard 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 cover 

re/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 cover 

re/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 therein 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: Vendor

(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 therein 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: Vendor

(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 therein 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: Vendor

(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 therein 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: Vendor

(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 therein 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: Vendor

(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 

A69543-403 

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

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 

A69742-403 

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

188-26-15-45SS316 

Notes: 

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. 
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 therein 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 configuration, this CDCCL it is not applicable after the removal and installation 

of a FQTU when no fuel tank access panel(s) was removed. 

3) Operators that have introduced 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 introduced 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 introduced 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 introduced 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 therein 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 therein 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 

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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 

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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:

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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