Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 1 

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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. 

1. Planning Information

A. Effectivity 

(1) F28 Mark 0070/0100 aircraft serial numbers: 11244 thru 11585. 

B. Concurrent Requirements 

(1) Not applicable. 

C. Reason 

(1) The design review of the F28 Mk0070/0100 fuel system in accordance with the 

guidelines related to FAA SFAR 88 and JAA INT/POL/25/12 revealed that an unsafe 

condition may develop in the wing fuel tanks and in the integral center wing tank (if 

installed in aircraft serial numbers 11442 thru 11585). 

(2) Based on the F28 Mk0070/0100 Fuel Tank Safety related design review it was 

concluded that the absence of electrical insulation material between a wing or integral 

center wing tank FQIS probe and the bottom of the tank structure could, under certain 

conditions, result in an ignition source inside the tank. 

(3) This Service Bulletin introduces measures to prevent the ignition source below the 

FQIS probes. 

(4) A similar ignition source cannot develop in Center Wing Bag Tanks (installed in 

aircraft serial numbers 11244 thru 11441) because the FQIS probe is isolated from 

the tank structure and other metal parts by the rubber bags. 

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

Revision - - - - - - - - - - - - - - 

Attachments Not applicable 

FUEL

 “This Service Bulletin is associated with the Fuel Tank Safety Program” 

Wing and Integral Center Wing Tanks - Introduction of Sealing Compound on the footprint area of 

the FQIS probes. 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 2 

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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. Description 

(1) This Service Bulletin is divided into 2 parts as follows: 

- Part 1: The probes in the Wing Tanks (applicable to aircraft serial 

numbers 11244 thru 11585) 

- This Part tells you how to apply sealant, approved for the purpose, 

below the probes in the wing tanks. 

- Part 2. The probes in the Integral Center Wing Tank (ICWT) (applicable to 

aircraft serial numbers 11442 thru 11585 if equipped with an ICWT) 

- This Part tells you how to apply sealant, approved for the purpose 

below the probes in the ICWT. 

E. Compliance 

(1) Recommended. 

Fokker Services recommends the accomplishment of Part 1 and Part 2 (if 

applicable) of this Service Bulletin not later than 1 July 2018.

NOTE: Because of the required tank opening it is efficient to do this Service 

Bulletin concurrently with a scheduled tank inspection before the above 

compliance date. 

NOTE: It is expected that EASA will issue an 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 nr. 

EASA.21J.059. 

G. Manpower. 

(1) Approximately 6 man-hours are necessary to do this Service Bulletin on one aircraft 

without Integral Center Wing Tank. 

This table of manpower will help you to schedule and do this Service Bulletin: 

Instructions Men Man-hours Elapsed time 

(hours) 

Removal - - - 

Modification 

Inspection 2 6,0 3,0 

Installation 

Testing - - - 

Total 6,0 3,0 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 3 

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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) Approximately 8 man-hours are necessary to do this Service Bulletin on one aircraft 

with Integral Center Wing Tank. 

This table of manpower will help you to schedule and do this Service Bulletin: 

Instructions Men Man-hours Elapsed time 

(hours) 

Removal - - - 

Modification 

Inspection 2 8,0 4,0 

Installation 

Testing - - - 

Total 8,0 4,0 

NOTE: This estimate does not include the time necessary for gaining access to 

the fuel tanks, ventilation of the fuel tanks, the paint to dry and/or the 

sealant to cure. 

(3) The estimated hours are for direct labor done by experienced personnel. They are 

calculated based on the conditions given in SBF100-00-001 (Service Bulletin 

Introduction, section 2.C., "Manpower"). 

H. Weight and Balance 

(1) Weight change: None 

Index change: None. 

I. Electrical Load Data 

(1) Not affected. 

J. Software Accomplishment Instructions 

(1) Not applicable. 

K. References 

(1) Fokker 70/100 Aircraft Maintenance Manual (AMM) 

Fokker Consumable Material List (CML) 

Fokker 70/100 Service Bulletin (SB): 

 - SBF100-28-069 

Fokker internal reference(s): 

 - ECR 15105. 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 4 

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

- Fokker 70/100 Aircraft Maintenance Manual (AMM) - chapter 28-00 

- chapter 28-41 

NOTE: See attached Manual Change Notification MCNM F100-144. 

(b) Maintenance Programs

- Fokker 70/100 Maintenance Review Board (MRB) 

- Fokker 70/100 Maintenance Planning Document (MPD) 

- Fokker 70/100 Customized Maintenance Program (CMP). 

(c) Special Instructions for Continued Airworthiness (ICA)

This Service Bulletin requires a revision to the Instructions for 

Continued Airworthiness (ICA) for: 

YES NO 

- Electrical Wiring Interconnection System (EWIS) - X 

- Fuel Tank Safety (FTS) X - 

- Damage Tolerance of Fatigue Critical Structure - X 

NOTE: If “YES”, when not already incorporated, the changed ICA will be 

incorporated in the MRB document within one calendar year from 

the date of issue of this Service Bulletin. Until then, the CDCCL 

and FUEL ALI items (applicable for probes in the wing tanks and 

in the integral center wing tank) as specified below shall be 

followed. 

FUEL ALI: It shall be verified that the tank structure below each FQIS probe 

(footprint area) in the wing tanks is covered with a sealant 

approved for the purpose and that this coating is undamaged. In 

case of damage the coating shall be repaired. 

NOTE: The footprint area is the area covered by the projection 

(parallel to the probe centerline) of the cross section of 

the probe outer tube, enlarged by a factor of three, on 

the tank bottom structure. 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 5 

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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 ALI: It shall be verified that the tank structure below each FQIS probe 

(footprint area) in the ICWT is covered with a sealant approved for 

the purpose and that this coating is undamaged. In case of 

damage the coating shall be repaired. 

NOTE: The footprint area is the area covered by the projection 

(parallel to the probe centerline) of the cross section of 

the probe outer tube, enlarged by a factor of three, on 

the tank bottom structure. 

Inspection interval for FUEL ALI’s: 

The inspection interval for the Fuel ALI’s is 8 years. The first repeat inspection must be 

performed within 8 years after accomplishment of this SB. 

NOTE: The Fuel ALI’s shall be performed in accordance with the 

instructions in AMM task 28-41-00-200-836A (wing tank) and if 

applicable AMM task 28-41-00-200-846A (integral center wing 

tank), both included in the attached MCNM F100-144. 

CDCCL: It shall be ensured that the tank structure below each wing tank 

FQIS probe (footprint area) in the wing tanks is covered with an 

undamaged coating of a sealant approved for the purpose. 

NOTE: The footprint area is the area covered by the projection 

(parallel to the probe centerline) of the cross section of 

the probe outer tube, enlarged by a factor of three, on 

the tank bottom structure. 

CDCCL: It shall be ensured that the tank structure below each ICWT FQIS 

probe (footprint area) in the ICWT is covered with an undamaged 

coating of a sealant approved for the purpose. 

NOTE: The footprint area is the area covered by the projection 

(parallel to the probe centerline) of the cross section of 

the probe outer tube, enlarged by a factor of three, on 

the tank bottom structure. 

NOTE: CDCCL’s shall be performed in accordance with the instructions in 

AMM tasks 28-00-00-200-846A, 28-41-01-400-814A (wing tank) 

and if applicable AMM task 28-41-02-400-814B (integral center 

wing tank), all changed in accordance with the instructions in 

attached MCNM F100-144. 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 6 

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) Operational Documentation

Not affected. 

(2) Report to Fokker Services that this SB has been carried out on the applicable aircraft. 

Send to Fokker Services the “Service Bulletin Reporting Quality Form” of this SB, see 

last SB page. 

(3) For incorporation of this Service Bulletin in your documentation refer to 

SBF100-00-001 (Service Bulletin Introduction, section 4 “Incorporation of Service 

Bulletins in Documentation of Fokker Services”). 

(4) Accomplishment of this SB is only complete with incorporation of the manual 

changes, per the ref MCNM, Temporary Revision or general revision. 

M. Interchangeability or Intermixability of Parts 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

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. 

2. Material Information

A. Material – Price and Availability 

(1) You can order the necessary parts against list price. 

B. Material Required 

(1) These parts, which are necessary to complete this Service Bulletin on 1 

aircraft, are not part of the mod kit. 

NOTE: The sealant mentioned below is approved for the purpose of preventing an 

ignition source in the fuel tanks. 

New Part Number Qty Keyword Info Old Part Number Instructions/

Disposition

PR-1422B * Sealant FK09-002 - Local source 

NOTES: * Use as much as necessary. 

(2) These mod kit parts are necessary to do this Service Bulletin on 1 aircraft. 

(a) Not applicable. 

C. Tooling – Price and Availability 

(1) Not applicable. 

D. Drawings Required 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 8 

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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

General: 

- For CML material number references, refer to “Myfokkerfleet.com/Documentation/CML”. 

- For the application of sealant refer to the AMM, chapter 51-23-00. 

WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY 

THE INSTRUCTIONS AND MANUFACTURER’S HEALTH AND SAFETY 

INSTRUCTIONS. 

WARNING: OBEY THE SAFETY PRECAUTIONS GIVEN AMM 28-00-00. JET FUEL IS 

EXPLOSIVE AND POISENOUS. 

A. Prepare the aircraft. 

(1) Remove the electrical power from the aircraft (Refer to AMM, chapter 24-00-00). 

(2) Disconnect the batteries (Refer to AMM, chapter 24-33-01). 

(3) Put up warning signs to tell persons: “DO NOT CONNECT THE BATTERIES” and 

“DO NOT CONNECT THE ELECTRICAL POWER”. 

Part 1: The probes in the Wing Tanks (applicable to all aircraft serial numbers). 

A. Apply sealant on the footprint area below the FQIS probes on the bottom of the Tanks. 

(1) Drain the RH and LH Wing Tanks, refer to AMM chapter 12-11-03. 

(2) For the LH wing remove the access panel(s) 522AZ, 523AB, 524AB, 524BB, 525AB, 

526AB, 526BB, 526CB, 526DB. 

NOTE: For aircraft in the post SBF100-57-041 configuration retain the access panel 

gaskets. 

(3) For the RH wing remove the access panel(s) 622AB, 623AB, 624AB, 624BB, 625AB, 

626AB, 626BB, 626CB, 626DB. 

NOTE: For aircraft in the post SBF100-57-041 configuration retain the access panel 

gaskets. 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 9 

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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. 

(4) Mark the location and the area of the footprint area on the bottom of the tank structure 

below the wing tank FQIS probes, refer to figures 1 and 2. 

Note: The footprint area is the area covered by the projection (parallel to the probe 

centerline) of the cross section of the probe outer tube, enlarged by a factor 

of three, on the tank bottom structure. 

(5) Disconnect the applicable FQIS probe from its brackets and temporarily hold the 

probe in position. 

(6) Prepare the surface(s) for the application of sealing compound in accordance with 

AMM Task 20-32-00-910-812-A. 

(7) Apply the sealant layer on the tank structure with a brush at the marked 

location(s)/area(s). Cover the stringers, frames, stiffeners and dome-nuts on the tank 

bottom in the foot print area. 

Use a sealant approved for the use, refer to section 2 Material Information. 

(8) Install the FQIS probe in accordance with AMM TASK 28-41-01-400-814-A (CDCCL). 

B. Install the LH and RH wing tank access panels. 

(1) Remove all tools, materials and equipment from the work area. 

(2) Do the tank closure inspection in accordance with AMM Task 28-00-00-200-846 

(CDCCL) before installation of the access panels. 

NOTE: For aircraft in pre SBF100-57-041 configuration follow the instruction for 

closing the access panels in AMM chapter 28-11-02. 

For aircraft in post SBF100-57-041 configuration follow the instruction for 

closing the access panels as below. 

(3) Install the gasket retained in step A.(2) or A.(3) of Part 1 on the access panel and 

mark the gasket on the identification block as the gasket can be re-used. 

(4) Install the access panel with the screws to the aircraft. 

(5) Tighten the screws of all access panels with a 0 – 10 Nm (0 – 88 lbf.in) torque wrench 

to between 2,8 and 3,5 Nm (25 and 31 lbf.in; 3/16 in diam. Screws) or 6,4 and 7,7 Nm 

(56 and 68 lbf.in; 1/4 in diam. Screws). 

(6) Let the gasket set for half an hour. 

(7) After half an hour retighten the screws with a 0 – 10 NM (0 – 88 Lbf.in) torque wrench 

to between 2,8 and 3,5 Nm (25 and 31 lbf.in; 3/16 in diam. Screws) or 6,4 and 7,7 Nm 

(56 and 68 lbf.in; 1/4 in diam. Screws). 

(8) Refuel the main fuel tanks (Refer to the AMM, chapter 12-11-01). 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 10 

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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. 

(9) Check for fuel leakage from the access panels. 

Part 2: The probes in the integral center wing tank (applicable to aircraft serial numbers 

11442 thru 11585, if equipped with an Integral Center Wing Tank). 

A. Apply sealant on the footprint area below the FQIS probes on the bottom of the Tank. 

(1) Drain the Integral Center Wing Tank (ICWT), refer to AMM chapter 12-11-03. 

(2) Remove the access panel(s) 153TZ and 154RZ in the rear of the forward cargo 

compartment (Refer to the AMM, chapter 28-12-03). 

(3) Remove the access panel(s) 175AZ and 175BZ of the center wing tank. 

(4) Mark the location and the area of the footprint area on the bottom of the tank structure 

below the ICWT FQIS probes refer to figures 1 and 2. 

Note: The footprint area is the area covered by the projection (parallel to the probe 

centerline) of the cross section of the probe outer tube, enlarged by a factor 

of three, on the tank bottom structure. 

(5) Disconnect the applicable FQIS probe from its brackets and temporarily hold the 

probe in position. 

(6) Prepare the surface(s) for the application of sealing compound in accordance with 

AMM Task 20-32-00-910-812-A. 

(7) Apply the sealant layer on the tank structure with a brush at the marked 

location(s)/area(s). Cover the stringers, frames, stiffeners and dome-nuts on the tank 

bottom in the foot print area. 

Use a sealant approved for the use, refer to section 2 Material Information. 

(8) Install the FQIS probe in accordance with AMM TASK 28-41-02-400-814-A (CDCCL). 

B. Install the access panels. 

(1) Remove all tools, materials and equipment from the work area. 

(2) Perform the tank closure inspection in accordance with AMM, TASK 28-00-00-200-

846 (CDCCL). 

(3) Install the access panel(s) 175AZ and 175BZ of the integral center wing tank in 

accordance with AMM, TASK 28-12-03-200-846. 

Note: For aircraft Post-Mod SBF100-28-069, AMM, TASK 28-12-03-200-846 is a 

CDCCL. 

(4) Reconnect the batteries (Refer to AMM, chapter 24-33-01). 

(5) Make sure electrical power is available (Refer to AMM, chapter 24-00-00). 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

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. 

(6) Refuel the integral center wing tank (Refer to the AMM, chapter 12-11-01). 

(7) Check for fuel leakage from the access panels. 

(8) Install the access panel(s) 153TZ and 154RZ in the rear of the forward cargo 

compartment (Refer to the AMM, chapter 28-12-03). 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 12 

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. 

Application of brush type sealant on the tank bottom structure 

Figure 1 
Service Bulletin 

Fokker 70/100 

Sep 02/11 SBF100-28-067 

Page 13 

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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. 

xxxxx area covered with sealant 

Application of brush type sealant on the tank bottom structure 

Figure 2 
Service Bulletin 

Fokker 70/100 

SBF100-28-067 Sep 02/11 

Page 14 

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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 Reporting Quality Form 

Use this Service Bulletin Reporting Quality 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 Illustrations 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 231 

2150 AE Nieuw-Vennep 

The Netherlands 

Fax: +31 (0) 252 627211 or Email : technicalservices@fokker.com
Manual Change Notification – Maintenance Documentation 

Fokker 70/100 

SEP 02/11 MCNM F100-144

Page 1 of 6 

MCNM-F100-144 

Subject : Fuel – Application of a Non-Conductive Layer of Sealant with a High Dielectric 

Strength on the Tank-Structure, in the Footprint-Area of the FQIS Probes. 

Reason : This MCN is issued to provide you with the changes on the content(s) of the affected 

manual(s), due to the introduction of SBF100-28-067. 

Effectivity : Refer to SBF100-28-067. 

Compliance : Once you have determined the applicability of this MCN for one or more of your 

aircraft, incorporate this information into the applicable manual(s). 

Publications 

affected : The Aircraft Maintenance Manual (AMM). 

Change Note : 

 AMM

 Update Task 28-00-00-200-846-A, as follows: 

− Make sure that the Task is in accordance with the change notes given in MCNMF100-140 − At the end of the Task, add a new Fig. 28-00-00-990-406-A00 as shown on Figure 1 

of the MCNM 

− At the top of Subtask 28-00-00-210-136-A00/A01 (as applicable), add a reference to 

Fig. 28-00-00-990-406-A00 after the existing reference to Fig. 28-00-00-990-386-A00 

− If your manual contains Subtask 28-00-00-210-136-A00, then add the following step 

(2), and re-identify the existing steps accordingly: 

 (2) Inspection of the footprint area below the probe(s) in the work area 

NOTE: The footprint area on the tank-structure (zone 500/600) is the projection of the 

cross-section of the probe outer-tube (parallel to the probe centreline), 

increased by a factor of three (Refer to Fig. 28-00-00-990-406-A00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on 

the stringers, frames, stiffeners and dome-nuts (as applicable). 

(a) Do a check of the position and dimension of the footprint area on the tank-structure. 

(b) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(c) Apply a new layer of sealant (Refer to Task 28-41-01-400-814 for corrective action), 

if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

− If your manual contains Subtask 28-00-00-210-136-A01, then add the following step 

(2), and re-identify the existing steps accordingly: 
Manual Change Notification – Maintenance Documentation 

Fokker 70/100 

SEP 02/11 MCNM F100-144

Page 2 of 6 

 (2) Inspection of the footprint area below the probe(s) in the work area 

NOTE: The footprint area on the tank-structure (zone 175/500/600) is the projection of 

the cross-section of the probe outer-tube (parallel to the probe centreline), 

increased by a factor of three (Refer to Fig. 28-00-00-990-406-A00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on 

the stringers, frames, stiffeners and dome-nuts (as applicable). 

(a) Do a check of the position and dimension of the footprint area on the tank-structure. 

(b) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(c) Apply a new layer of sealant (Refer to Task 28-41-01-400-814/28-41-02-400-814 for 

corrective action), if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

 Add a new Task 28-41-00-200-836-A, and do as follows: 

− Use this title for the new Task: 

Detailed Inspection of the FQIS Probe Footprint Coating in the Wing Tanks (Refer to MPD 

280000-00-23) 

− Add this text below the title of the new Task: 

This maintenance procedure affects Fuel Tank Safety. It is related to a fuel system ALI 

(Airworthiness Limitation Item). Strictly adhere to the contents of this task to make sure 

that unsafe conditions do not develop. 

− Use this procedure for the new Task: 

WARNING: OBEY THE SAFETY PRECAUTIONS GIVEN IN 28-00-00-860-813 AND 

28-11-00-860-813. JET FUEL IS EXPLOSIVE AND POISONOUS. 

A. Defuel the aircraft (Refer to Task 12-11-01-650-833 for more data). 

B. Drain the aircraft fuel tanks (Refer to Task 12-11-03-600-813 for more data). 

C. Remove the access panels 522AB, 523AB, 524AB, 524BB, 525AB, 526BB, 526DB, 

622AB, 623AB, 624AB, 624BB, 625AB, 626BB and 626DB (Refer to Task 28-11-02-

000-814 for more data). 

D. Examine the footprint area below the probes 

NOTE: The footprint area on the tank-structure (zone 500/600) is the projection of the 

cross-section of the probe outer-tube (parallel to the probe centreline), 

increased by a factor of three (Refer to Fig. 28-41-00-990-436-A00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on 

the stringers, frames, stiffeners and dome-nuts (as applicable). 
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Page 3 of 6 

(1) Do a check of the position and dimension of the footprint area on the tank-structure. 

(2) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(3) Apply a new layer of sealant (Refer to Task 28-41-01-400-814 for corrective action), 

if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

E. Install the access panels 522AB, 523AB, 524AB, 524BB, 525AB, 526BB, 526DB, 

622AB, 623AB, 624AB, 624BB, 625AB, 626BB and 626DB (Refer to Task 28-11-02-

400-814 for more data). 

F. Refuel the aircraft (Refer to Task 12-11-01-650-813 for more data). 

G. Do a check for fuel leakage at the access panels that you installed. 

− At the end of the new Task, add a new Fig. 28-41-00-990-436-A00 as shown on 

Figure 1 of this MCNM. 

 If your manual contains Task 28-41-02-400-814-B, then add a new Task 28-41-00-200-846-

A, and do as follows: 

− Use this title for the new Task: 

Detailed Inspection of the FQIS Probe Footprint Coating in the Integral Center Wing Tank 

(Refer to MPD 280000-00-24) 

− Add this text below the title of the new Task: 

This maintenance procedure affects Fuel Tank Safety. It is related to a fuel system ALI 

(Airworthiness Limitation Item). Strictly adhere to the contents of this task to make sure 

that unsafe conditions do not develop. 

− Use this procedure for the new Task: 

WARNING: OBEY THE SAFETY PRECAUTIONS GIVEN IN 28-00-00-860-813 AND 

28-12-00-860-813. JET FUEL IS EXPLOSIVE AND POISONOUS. 

A. Defuel the aircraft (Refer to Task 12-11-01-650-833 for more data). 

B. Drain the aircraft fuel tanks (Refer to Task 12-11-03-600-813 for more data). 

C. Remove the access panels 175AZ and 175BZ (Refer to Task 28-12-03-000-814 for 

more data). 

D. Examine the footprint area below the probes 

NOTE: The footprint area on the tank-structure (zone 175) is the projection of the crosssection of the probe outer-tube (parallel to the probe centreline), increased by a 

factor of three (Refer to Fig. 28-41-00-990-446-A00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on 

the stringers, frames, stiffeners and dome-nuts (as applicable). 

(1) Do a check of the position and dimension of the footprint area on the tank-structure. 
Manual Change Notification – Maintenance Documentation 

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SEP 02/11 MCNM F100-144

Page 4 of 6 

(2) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(3) Apply a new layer of sealant (Refer to Task 28-41-02-400-814 for corrective action), 

if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

E. Install the access panels 175AZ and 175BZ (Refer to Task 28-12-03-400-814 for 

more data). 

F. Refuel the aircraft (Refer to Task 12-11-01-650-813 for more data). 

G. Do a check for fuel leakage at the center wing-tank access-panel drain-hole in the 

belly fairing. 

− At the end of the new Task, add a new Fig. 28-41-00-990-446-A00 as shown on 

Figure 1 of this MCNM. 

 Update Task 28-41-01-400-814-A, as follows: 

− Make sure that the Task is in accordance with the change notes given in MCNMF100-140 − At the end of the Task, add a new Fig. 28-41-01-990-044-A00 as shown on Figure 1 

of the MCNM 

− Add a new Subtask after Subtask 28-41-01-210-014-A00, that contains this text: 

 Subtask 28-41-01-210-034-A00 

 (Refer to Fig. 28-41-01-990-024-A00) 

 (Refer to Fig. 28-41-01-990-044-A00) 

 Inspection of the footprint area below the probes 

NOTE: Start of Fuel System CDCCL affected section. 

NOTE: The footprint area on the tank-structure (zone 500/600) is the projection of the crosssection of the probe outer-tube (parallel to the probe centreline), increased by a 

factor of three (Refer to Fig. 28-41-01-990-044-A00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on the 

stringers, frames, stiffeners and dome-nuts (as applicable). 

(1) Temporarily hold the tank probe (3) in position for installation, to do a check of the 

footprint area on the tank-structure. 

(2) Do a check of the position and dimension of the footprint area on the tank-structure. 

(3) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(4) Use a brush, to apply a new layer of sealant (Material No. Fk09-002), if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

NOTE: End of Fuel System CDCCL affected section. 
Manual Change Notification – Maintenance Documentation 

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SEP 02/11 MCNM F100-144

Page 5 of 6 

 If your manual contains Task 28-41-02-400-814-B, then update this Task as follows: 

− Make sure that the Task is in accordance with the change notes given in MCNMF100-140 

− At the end of the Task, add a new Fig. 28-41-02-990-044-B00 as shown on Figure 1 

of the MCNM − Add a new Subtask after Subtask 28-41-02-210-014-B00, that contains this text: 

 Subtask 28-41-02-210-034-B00 

 (Refer to Fig. 28-41-02-990-024-B00) 

 (Refer to Fig. 28-41-02-990-044-B00) 

 Inspection of the footprint area below the probes 

NOTE: Start of Fuel System CDCCL affected section. 

NOTE: The footprint area on the tank-structure (zone 175) is the projection of the crosssection of the probe outer-tube (parallel to the probe centreline), increased by a 

factor of three (Refer to Fig. 28-41-02-990-044-B00). 

NOTE: In the footprint area, there must be a layer of sealant (Material No. Fk09-002) on the 

stringers, frames, stiffeners and dome-nuts (as applicable). 

(1) Temporarily hold the tank probe (8) in position for installation, to do a check of the 

footprint area on the tank-structure. 

(2) Do a check of the position and dimension of the footprint area on the tank-structure. 

(3) Make sure that the layer of sealant in the footprint area on the tank-structure is not 

damaged. 

(4) Use a brush, to apply a new layer of sealant (Material No. Fk09-002), if: 

- There is no sealant in the footprint area 

- The footprint area does not contain a layer of sealant on the full surface 

- The layer of sealant in the footprint area is damaged 

- The position/dimension of the footprint area is not correct. 

NOTE: End of Fuel System CDCCL affected section. 

NOTE: If you have a Documentation Revision Service (DRS) with Fokker Services, this 

information will be included into your manuals at the earliest opportunity. 
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SEP 02/11 MCNM F100-144

Page 6 of 6 

Footprint-Area below Tank Probes – Inspection/Check 

Figure 1