Service Bulletin 

Fokker 70/100 

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Revision 2 2 2 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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.

FUSELAGE

 Forward Fuselage - The One-Time External Inspection and Temporary Repair of the Butt Joints 

at Stringers 8, 37, 42 and 67 between Stations 3850 and 5305. 

1. Planning Information

A. Effectivity 

(1) F28 Mark 0070/0100 aircraft serial numbers: 

11268 thru 11283, 11286, 11289, 11291, 11293, 11295, 11300, 11303, 11306, 

11308, 11310, 11312 thru 11314, 11316, 11318, 11321, 11323 thru 11335, 11337, 

11338, 11340, 11345, 11346, 11349, 11352 thru 11361, 11365 thru 11370, 11372, 

11373, 11376 thru 11380, 11387, 11388, 11391, 11392, 11395 thru 11399, 

11403 thru 11408, 11411 thru 11419, 11425 thru 11428, 11432, 11435, 11436, 

11438, 11439, 11444 thru 11450, 11456 thru 11460, 11464 thru 11469, 

11475 thru 11479, 11481 thru 11506, 11509, 11511 and 11513 thru 11585. Unless 

modified in accordance with SBF100-53-119. 

B. Concurrent Requirements 

(1) Not applicable. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 2 Revision 2, Oct 16/12 

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.

C. Reason 

(1) A crack was reported at a butt joint on the forward fuselage above the passenger 

door. Investigation revealed that, depending on the configuration of the aircraft, four 

butt joints in the forward fuselage have a similar design and a repetitive inspection is 

required. 

(2) The repetitive inspection has been incorporated into revision 10 of report SE-623 in 

the Airworthiness Limitations Section (ALS) of the Instructions for Continued 

Airworthiness, tasks 531030-00-11 and 531031-00-05. The repetitive inspection 

accomplishment instructions have been incorporated in the Non Destructive Testing 

Manual (NDTM). 

(3) This Service Bulletin provides the one-time inspection accomplishment instructions in 

parts 1 & 2. 

(4) When crack indications are found the applicable butt joint has to be repaired before 

further flight. The temporary repair is available in this Service Bulletin parts 3, 4, 5 & 6. 

Reason for Revision

(1) This revision is made to: 

 - Delete the requirements for the repetitive inspections from this Service Bulletin. 

 - Add reference for the repetitive inspections to the ALS (report SE-623) of the 

Instructions for Continued Airworthiness. 

 - Change step C.(3) of Part 2 and figure 4A for clarity. 

D. Description 

(1) This Service Bulletin is divided in 6 Parts as follows: 

Part 1: The Manufacturing of the Calibration Plate for the Inspection. 

This Part tells how to: 

- Manufacture the calibration plate for the inspection according Part 2. 

Part 2: The One-Time External Inspection of the Butt Joint at Stringer 8, 37, 42 and 

67 between Stations 3850 and 5305 

This Part tells how to: 

- Carry out the external inspection of the butt joint at stringer 8, 37, 42 and 67 

between Stations 3850 and 5305, using Low Frequency Eddy Current (LFEC). 

NOTE: Frame bays that are temporary repaired do not require the repetitive 

inspection, refer to the ALS (report SE-623) of the Instructions for Continued 

Airworthiness. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

Part 3: The Temporary Repair of the Butt Joint at Stringer 8. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 4: The Temporary Repair of the Butt Joint at Stringer 37. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 5: The Temporary Repair of the Butt Joint at Stringer 42. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 6A: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 

11316 and 11318). 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 6B: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 

11268 thru 11275, 11277, 11279, 11293, 11321, 11323 thru 11330, 11332, 

11335, 11359, 11361, 11367, 11378, 11387, 11388, 11396, 11397, 11404, 

11432, 11438, 11439, 11444 thru 11446, 11450, 11456, 11460, 11468, 

11475 thru 11477, 11483 thru 11490, 11492 thru 11497, 11499, 11500, 

11502 thru 11505, 11509, 11511, 11513, 11515 thru 11520, 11522 thru 

11527 and if 

POST- SBF100-23-028: 11370, 11376, 11377, 11405, 11407, 11411 thru 

11419, 11425 thru 11427, 11435, 11436, 11449, 11457, 11458, 11464, 

11465, 11467, 11469, 11479, 11481, 11482, 11506 and 11514). 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 4 Revision 2, Oct 16/12 

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.

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 6C: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 

11276, 11278, 11280 thru 11283, 11286, 11289, 11291, 11295, 11300, 

11303, 11306, 11308, 11310, 11312 thru 11314, 11331, 11333, 11334, 

11337, 11338, 11345, 11346, 11349, 11357, 11358, 11365, 11366, 11372, 

11373, 11379, 11380, 11391, 11392, 11398, 11399). 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 6D: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 

11340, 11352 thru 11356, 11360, 11368, 11369, 11395, 11403, 11406, 

11408, 11428, 11447, 11448, 11459, 11466, 11478, 11491, 11498, 11501 

and if 

PRE - SBF100-23-028: 11370, 11376, 11377, 11405, 11407, 11411 thru 

11419, 11425 thru 11427, 11435, 11436, 11449, 11457, 11458, 11464, 

11465, 11467, 11469, 11479, 11481, 11482, 11506 and 11514). 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

Part 6E: The Temporary Repair of the Butt Joint at Stringer 67(Applicable to aircraft 

11521, 11528, 11529, 11532, 11536 thru 11541, 11543, 11545, 11547, 

11549, 11551, 11553 thru 11583, 11585). 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the cracked part of the butt-strap 

- Install an insert for the removed part of the butt strap 

- Install the external repair strap. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

E. Compliance 

(1) Recommended. 

Fokker Services recommends the accomplishment of Part 2 of this Service Bulletin at 

the following times: 

The inspection has to be carried out before the aircraft exceeds a total number of 

35,000 flight cycles (FC) since new or within 8 months after the date of issue of this 

Service Bulletin, whichever comes later. 

NOTE 1: An alternative inspection method is a Visual Detailed Inspection of the butt 

joint(s) from the inside. Only note that to gain access to the inspection area 

from the inside several components must be removed. After the inspection 

has been performed all components that are removed must be reinstalled 

and tested, all in accordance with the applicable AMM procedures. 

NOTE 2: 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 the Airworthiness Directive. 

NOTE 3: This Service Bulletin covers the interim actions required to assure 

continued airworthiness. When the temporary repair has been performed 

on one or more frame bays, these frame bays no longer require the 

repetitive inspection as incorporated in the ALS (report SE-623) of the 

Instructions for Continued Airworthiness. The mandatory terminating 

repair/modification is presented in SBF100-53-119 (issued June 2012) and 

has a compliance before the aircraft will have accumulated 50,000 FC 

since new. 

F. Approval 

(1) The technical content of this document is approved under the authority of DOA nr. 

EASA.21J.059. 

G. Manpower 

(1) Approximately 2 man-hours are necessary to manufacture the special inspection 

calibration tool according Part 1 of this Service Bulletin. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Manufacturing 1 2,0 2,0 

Total 2,0 2,0 

NOTE: This estimate does not include the time necessary for the sealant to cure. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 6 Revision 2, Oct 16/12 

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.

(2) Approximately 1 man-hour is necessary to do Part 2 of this Service Bulletin on one 

aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal - - - 

Modification 

Inspection 1 1,0 1,0 

Installation - - - 

Testing - - - 

Total 1,0 1,0 

(3) Approximately 30 man-hours are necessary to do Part 3 of this Service Bulletin on 

one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 8,0 8,0 

Modification 

Inspection 2 12,0 6,0 

Installation 1 5,0 5,0 

Testing 1 5,0 5,0 

Total 30,0 24,0 

NOTE 1: This estimate does not include the time necessary for the paint to dry and/or 

the sealant to cure. 

(4) Approximately 30 man-hours are necessary to do Part 4 of this Service Bulletin on 

one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 8,0 8,0 

Modification 

Inspection 2 12,0 6,0 

Installation 1 5,0 5,0 

Testing 1 5,0 5,0 

Total 30,0 24,0 

NOTE 1: This estimate does not include the time necessary for the paint to dry and/or 

the sealant to cure. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

(5) Approximately 30 man-hours are necessary to do Part 5 of this Service Bulletin on 

one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 8,0 8,0 

Modification 

Inspection 2 12,0 6,0 

Installation 1 5,0 5,0 

Testing 1 5,0 5,0 

Total 30,0 24,0 

NOTE 1: This estimate does not include the time necessary for the paint to dry and/or 

the sealant to cure. 

(6) Approximately 30 man-hours are necessary to do Part 6A thru 6E of this Service 

Bulletin on one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 8,0 8,0 

Modification 

Inspection 2 12,0 6,0 

Installation 1 5,0 5,0 

Testing 1 5,0 5,0 

Total 30,0 24,0 

NOTE 1: This estimate does not include the time necessary for the paint to dry and/or 

the sealant to cure. 

(7) 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) Part 3 thru 6E: 

(a) Repair accomplished on one stringer (8, 37, 42 or 67) between sta 3850-4175: 

1 Weight change: + 0,076 kg (0.168 lb), per butt joint repair. 

Index change: Mark 0100: - 0.010 

 Mark 0070: - 0.008. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 8 Revision 2, Oct 16/12 

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.

(b) Repair accomplished on one stringer (8, 37, 42 or 67) between sta 4610-4850: 

1 Weight change: + 0,074 kg (0.164 lb), per butt joint repair. 

Index change: Mark 0100: - 0.009 

 Mark 0070: - 0.008. 

I. Electrical Load Data 

(1) Not changed. 

J. Software Accomplishment Summary 

(1) Not applicable. 

K. References 

(1) Fokker 70/100 Airworthiness Limitations Section (ALS) 

Fokker 70/100 Structural Repair Manual (SRM) 

Fokker 70/100 Aircraft Maintenance Manual (AMM) 

Fokker 70/100 Illustrated Parts Catalog (IPC) 

Fokker 70/100 Maintenance Review Board (MRB) document 

Fokker 70/100 Standards and Process Manual (SPM) 

Fokker 70/100 Maintenance Planning Document (MPD) 

Fokker 70/100 Service Bulletin: 

 - SBF100-53-091 

 - SBF100-53-105 

 - SBF100-53-119 

Fokker Consumable Material List (CML) 

Fokker internal reference(s): 

 - ECR015819. 

L. Publications Affected 

(1) This SB affects the publications listed below: 

(a) Maintenance Documentation

Not affected. 

(b) Maintenance Programs

- Fokker 70/100 Maintenance Planning Document (MPD) 

- Fokker 70/100 Airworthiness Limitations Section (ALS) 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

(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 

- Damage Tolerance of Fatigue Critical Structure X - 

- Certification Maintenance Requirements (CMR) - X 

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

incorporated in the MRB, the Airworthiness Limitations Sections (ALS) 

and/or AMM document(s) within one calendar year from the date of 

issue of this Service Bulletin. Until then, no actions are required. 

(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 “Reporting Quality Form” of this SB. Refer to the last 

page of this SB. 

(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"). 

M. Interchangeability or Intermixability of Parts 

(1) Not applicable. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 10 Revision 2, Oct 16/12 

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.

2. Material Information

A. Material – Price and Availability 

(1) The materials are local source items. 

B. Material Required 

(1) These parts, which are necessary to complete Part 1 and/or Part 3 thru 6E of this 

Service Bulletin on 1 aircraft, are not part of the mod kit. 

New Part Number Qty Keyword Info Old Part Instructions/

 *1 *

2 Number Disposition

Alodine1201 - AR* Coating Fk13-003D** - Local source 

Corrosion resistant 

steel strip 

- AR* Strip ~20 x 50 mm 

t=0,4 mm 

- Local source 

HL11VF5-xx - AR* CSK hilok - - Local source 

HL11VF6-xx - AR* CSK hilok - - Local source 

HL111VF6-xx - AR* CSK hilok - - Local source 

HL70-5 - AR* CSK collar - - Local source 

HL70-6 - AR* CSK collar - - Local source 

HL79-6 - AR* CSK collar - - Local source 

F0N1-4311-1AK- *3

 AR* - Sheet, aluminum 2024T3 Alclad - Local source 

F0N1-4311-1AL- *4

 AR* - Sheet, aluminum 2024T3 Alclad - Local source 

F0N1-4311-1AM- *5

 - AR* Sheet, aluminum 2024T3 Alclad - Local source 

F0N18-9151S04 - AR* CSK repair washer - - Local source 

F0N18-9151S05 - AR* CSK repair washer - - Local source 

F0N18-9151S06 - AR* CSK repair washer - - Local source 

F0N18-9152-02 - AR* CSK repair washer - - Local source 

F0N18-9152-03 - AR* CSK repair washer - - Local source 

NAS1097DD4-XX - AR* CSK rivet - - Local source 

NAS1097DD5-XX - AR* CSK rivet - - Local source 

NAS1097DD6-XX - AR* CSK rivet - - Local source 

PR1436GA1-2 AR* AR* Sealant Fk09-016** - Local source 

PR1436GB1-2 - AR* Sealant Fk09-017** - Local source 

S15-60CRME52700 - AR* Aerodur Primer Fk07-008** - Local source 

NOTES: * Use as much as necessary 

** Refer to the CML for material numbers 

*

1

 Applicable to Part 1 

*

2

 Applicable to Part 3 thru 6E 

*

3

 1,0 mm (0.040 inch) 2024T3 Alclad aluminum sheet 

*

4

 1,2 mm (0.050 inch) 2024T3 Alclad aluminum sheet 

*

5

 1,4 mm (0.055 inch) 2024T3 Alclad aluminum sheet. 

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

(a) Not applicable. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

C. Tooling – Price and Availability 

(1) The following special tools are required to accomplish Part 2 of this Service Bulletin: 

Part Number Specification Reference Supplier

ELOTEST-B1SB Phase analysis EC tester S0137* Rohmann 

SPT4039 Sliding probe, reflection 

type, 1-100 kHz 

- Servicing Europe 

NDT 

CR-RE-TF180 Interconnecting cable - Servicing Europe 

NDT 

SB10053118PLATE Calibration plate - Local source** 

NOTES: * Reference number when ordering at Fokker services BV. 

 ** Calibration plate pn SB10053118PLATE has to be manufactured in 

accordance with Part 1 of this Service Bulletin. 

NOTE: Any other equipment may be used, provided that the specifications in the 

table and the sensitivity requirements as specified in step C. of Part 2 are 

met. 

Calibration procedures may vary when using other equipment. 

D. Drawings Required 

(1) Not applicable. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 12 Revision 2, Oct 16/12 

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.

3. Accomplishment Instructions

General: 

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

AMM task 20-30-00-910-xxx-A (Consumable Material List). 

- For Standards and Process Manual (SPM) references, refer to 

“Myfokkerfleet.com/Documentation/SPM”. 

- For the application of Alodine 1201 (Fk13-003D), refer to the AMM, chapter 51-22-00. 

- For the application of primer and paint, refer to the AMM, chapter 51-21-00. 

- For the application of sealant PR1436GA1-2 (Fk09-016) and PR1436G-B1-2 (Fk09-017) 

refer to the AMM, chapter 51-23-00. 

- For the removal/installation of solid rivets, refer to the SRM, chapter 51-40-02. 

- For the installation of hiloks, refer to the SRM chapters 51-41-01. 

- For drilling and dimpling procedures, refer to the SRM, chapter 51-21-02. 

- For drilling and countersinking procedures, refer to the SRM, chapter 51-22-01. 

- For machining procedures, refer to the SRM chapter 51-22-02. 

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

THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY 

INSTRUCTIONS. 

Part 1: The Manufacturing of the Calibration Plate for the Inspection 

Refer to figure 1. 

A. Manufacturing of the calibration plate. 

(1) Manufacture 2 plates A in accordance with figure 1 “Plate A”. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AK- * 

NOTE: * 1,0 mm (0.040 inch) thick 2024T3 Alclad aluminium sheet. 

(2) Manufacture 1 x plate B in accordance with figure 1 “Plate B”. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AL- * 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminium sheet. 

(a) Make a small hole with a Ø 1,0 mm drill in plate B on the indicated position. 

(b) Make a 10 mm long saw cut of 0,2 (± 0,1) mm wide with a fretsaw or hacksaw. 

B. Assembly of the special tool. 

(1) Assemble the special tool in accordance with figure 1 and use the plates 

manufactured in step A.(1) and A.(2). Use: 

- AR Sealant, interfaying PR1436GA1-2* Fk09-016 

NOTE: * Or equivalent 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

C. Identification. 

(1) Identify the special tool with pn SB10053118PLATE. Engrave the part number or use 

a permanent marker. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 14 Revision 2, Oct 16/12 

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.

Part 2: The One-Time External Inspection of the Butt Joint at Stringer 8, 37, 42 and 67 

between Stations 3850 and 5305. 

NOTE 1: Aircraft that have a temporary (Fokker Services approved) repair on a specific 

location do not require inspection at that specific location. 

NOTE 2: Aircraft which are post SBF100-53-105 at stringer 8 and 67 do not need to perform 

this inspection, since this modification covers the inspection area. 

A. Preparation of the of the inspection area. 

Refer to figures 5, 6 and 7. 

(1) Clean the area to be inspected from any dirt with a lint-free cloth moistened with 

cleaning agent. 

(2) Remove chipped and/or excessive paint. Refer to NDTM, Part 1, chapter 51-00-06. 

B. The following special tools are required for the LFEC sliding probe inspection: 

Part Number Specification Reference Supplier

ELOTEST-B1SB Phase analysis EC tester S0137* Rohmann 

SPT4039 Sliding probe, reflection 

type, 1-100 kHz 

- Servicing Europe NDT 

CR-RE-TF180 Interconnecting cable - Servicing Europe NDT 

SB10053118PLATE Calibration plate - Local source** 

NOTES: * Reference number when ordering at Fokker services BV. 

 ** Calibration plate pn SB10053118PLATE has to be manufactured in 

accordance with Part 1 of this Service Bulletin. 

NOTE: Any other equipment may be used, provided that the specifications in the 

table and the sensitivity requirements as specified in step C. are met. 

Calibration procedures may vary when using other equipment. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

C. Calibration of the measuring equipment. 

Refer to figures 2, 3 and 4. 

INSTRUMENT SETTINGS 

(a) Y/X or Y/time base Y/X 

(b) Frequency (kHz) 8.0 

(c) Axis spread Y/X (dB) 3/0 

(d) Bandwidth MF 

(e) Preamplifier (dB) 12 

(f) Gain (dB) As required 

(g) Phase (degrees) As required 

(h) Filter (Hz) LP: 50 

(i) Gate ON 

(j) Alarm OFF 

Initial instrument settings 

Table 1 

(1) Adjust the instrument according to table 1. Set the balance point at 25% Full Screen 

Height (FSH) and set the gate to 50% FSH as indicated in figure 4A. 

(2) Position a non-conductive ruler in such a way that a straight scan can be made with 

the center mark of the probe along one skin edge of the butt joint. Refer figure 3. 

NOTE: Centering halfway the splice may cause a non-relevant lift-off signal. 

(3) Slide the probe to position I and balance the instrument. Then slide the probe across 

position II and back. Adjust Phase to get the slot signal in vertical direction as shown 

in figure 4A and adjust Gain until the slot signal is 75% FSH, refer figure 4B. 

NOTE: The slot indication from position II is used for sensitivity setting. An actual 

crack indication may increase gradually. 

D. Inspection of the butt joint. 

Refer to figures 2, 3, 4, 5, 6 and 7. 

(1) Switch the alarm to ON. Inspect the area between the frames using a non-conductive 

ruler. For the inspection areas refer to figures 5, 6 and 7. 

(2) Position the probe at a skin corner along one skin edge of the butt joint and balance 

the instrument. Refer to figure 3. 

(3) Perform a scan along each skin edge (refer to figure 3) and monitor the signal. 

NOTE: A misalignment of the ruler will decrease the detectability of cracks and may 

cause deviating signatures. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 16 Revision 2, Oct 16/12 

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.

(4) Mark every position where the signal passes the 50% FSH gate and looks like the slot 

signals given in figure 4B. 

(5) If no indications above 50% FSH are measured continue with step F. 

E. Verification of inspection results. 

(1) Check the sensitivity setting on the calibration plate. Balance the probe on the aircraft 

at an opposite skin corner or at a frame position without rivets in the inspection area 

and rescan the marked area(s). 

NOTE: Adjacent to a through crack an indication may increase gradually and exceed 

75% FSH, unlike the saw-cut in the calibration plate. 

(2) If a crack indication of 50% FSH or more is found, write down the location, orientation 

and the length of the crack. 

F. After inspection procedure. 

(1) If a crack indication of less than 50% FSH has been found continue with step G. If an 

indication of 50% FSH or more is found repair the applicable frame bay(s) in 

accordance with the following part, refer to table 2. 

Crack indication found at 

the butt joint of: 

Refer to the following part 

for the temporary repair 

STR 8 Part 3 

STR 37 Part 4 

STR 42 Part 5 

STR 67 Part 6 

Table 2 

Refer to figures 14 and 15. 

(2) Fill out the enclosed Reporting Form of figure 14 for the crack indications at STR 8 

and 67. Fill out the enclosed Reporting Form of figure 15 for the crack indications at 

STR 37 and 42. 

Send the filled out reporting form back to Fokker Services BV. For the address refer 

to SBF100-00-001 (Service Bulletin Introduction). 

NOTE: This feed-back is essential for further determination of subsequent actions. 

G. Job close up 

(1) If necessary restore the aircraft paint scheme. Refer to the Aircraft Maintenance 

Manual (AMM), chapter 51-21-00. 

(2) Remove all tools and materials from the work area and make sure the area is clean. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

Part 3: The Temporary Repair of the Butt Joint at Stringer 8. 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the area to be repaired. The 

below procedure describes the complete removal of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) Remove the avionics cooling air filter, ref. AMM Task 21-26-04-000-814-A. 

(3) Remove the avionics cooling air filter housing, ref.IPC chapter 21-26-04 figure 01: 

(a) Disconnect the duct assy’s. 

(b) Remove and keep the attachment bolts and washers. 

(4) Remove the (blower) fan and/or ducting, ref. AMM Task 21-26-01-000-814-A. 

(5) Remove the bleed air distribution ducting as far as necessary, ref. AMM 

Task 36-12-05-000-814-A. 

(6) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 8 between fuselage 

stations 3870-4175 and/or 4610-4850. 

(1) Clean the butt joint at stringer 8 between fuselage station 3870-4150 and/or 4610-

4850 on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 8 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 18 Revision 2, Oct 16/12 

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.

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 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. 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the bleed air distribution ducting, if necessary, ref. AMM Task 36-12-05-400-

814-A. 

(3) Install the (blower) fan and/or ducting, ref. AMM Task 21-26-01-400-814-A. 

(4) Install the avionics cooling air filter, ref. AMM Task 21-26-04-400-814-A. 

(5) Install the avionics cooling air filter housing, ref.IPC chapter 21-26-04 figure 01A: 

(a) Install the attachment bolts, item 40 and 50, with washers item 60 which were 

kept in step A.(3). 

(b) Connect the duct assy’s, items 110 and 120. 

(6) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

G. Close the equipment hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 20 Revision 2, Oct 16/12 

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.

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 3 of SBF100-53-118” has 

been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 21 

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. 

Part 4: The Temporary Repair of the Butt Joint at Stringer 37. 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the entrance area. 

(1) Remove the necessary entrance ceiling panels to get access to the repair area, ref. 

AMM Task 25-24-00. 

(2) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 37 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 37 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 37 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 22 Revision 2, Oct 16/12 

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.

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 23 

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. 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the removed ceiling panels, ref. AMM Task 25-24-00. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 4 of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 24 Revision 2, Oct 16/12 

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.

Part 5: The Temporary Repair of the Butt Joint at Stringer 42. 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the entrance area. 

(1) Remove the door exit sing above the FWD S/E door, ref. AMM task 33-52-02-000-

814-A. 

(2) Remove the entrance side wall panel above the FWD S/E door to get access to the 

repair area, ref. IPC 25-23-00-10 view F. 

(3) If necessary remove side wall panels at the FWD S/E door, ref. IPC 25-23-01-015. 

(4) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 42 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 42 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 42 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 25 

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. 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 26 Revision 2, Oct 16/12 

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.

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) If applicable install the side wall panels at the FWD S/E door, ref. IPC 25-23-01-015. 

(3) Install the entrance side wall panel above the FWD S/E, ref. IPC 25-23-00-10 view F. 

(4) Install the door exit sing above the FWD S/E door, ref. AMM task 33-52-02-400-814-

A. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 5 of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 27 

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. 

Part 6 A: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 11316 

and 11318). 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the to be repaired area. The 

below procedure describes the complete remove all of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) The removal of equipment from the avionics rack in Zone 128. 

(a) Remove and keep the HF-1 Transceiver (refer to AMM, chapter 23-11-01). 

(b) Remove and keep the HF-2 Transceiver (refer to AMM, chapter 23-11-01). 

(c) Remove and keep the ABS control unit (refer to AMM, chapter 32-48-02), if 

applicable. 

(3) Loosen the HF-1 wiring from the avionics rack. 

(a) On the avionics rack disconnect plug P 3471B. 

(b) On the avionics rack loosen receptacle J 3471A, keep the attachment parts. 

(c) Loosen HF-1 plug P 0276B from the mounting tray, keep the attachment parts. 

(d) Loosen the ground studs GS0527 and GS0531, first identify the ground studs for 

easy installation, keep the attachment parts. 

(e) Stow the HF-1 wiring behind the avionics rack, remove and keep clamps if 

necessary. 

(4) Loosen the HF-2 wiring from the avionics tray. 

(a) On the avionics rack disconnect plug P 3470B. 

(b) On the avionics rack loosen receptacle J 3470A, keep the attachment parts. 

(c) Loosen HF-2 plug P 3388B from the mounting tray, keep the attachment parts. 

(d) Loosen the ground studs GS0538 and GS0541 first identify the ground studs for 

easy installation, keep the attachment parts. 

(e) Stow the HF-2 wiring behind the avionics tray, remove and keep clamps if 

necessary. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 28 Revision 2, Oct 16/12 

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.

Step (5) is applicable if ABS mounting tray and wiring is installed. 

(5) Loosen the ABS wiring from the avionics tray. 

(a) On the avionics rack disconnect plugs P 4082A and P 4083A. 

(6) Disconnect the cooling ducting. 

(a) Disconnect the cooling supply duct by removing the clamp or the tie-wrap. 

(b) Disconnect the cooling exhaust duct by removing the clamp or the tie-wrap. 

(7) Remove the avionics rack. 

(a) Remove and keep the four screws and washers that attach the avionics rack to 

the frame. 

(b) Carefully remove the avionics rack from the frame. 

NOTE: Take care NOT to damage the wave guide while working on the RH side 

 of the equipment bay compartment 

(8) Remove the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-000-824-A. 

(9) Remove the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-000-914-A. 

(10) Remove the RH surface-work platform, ref IPC 25-71-05. 

(11) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 67 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 67 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 67 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 29 

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. 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 30 Revision 2, Oct 16/12 

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.

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the RH surface-work platform, ref IPC 25-71-05. 

(3) Install the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-000-914-A. 

(4) Install the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-000-824-A. 

(5) Installation of the Avionics rack in Electrical Bay, Zone 128. 

(a) Install the avionics rack on the frame. Attach it with the four screws and washers. 

For electrical bonding at the location of the mounting screws (code NC4.610-

940), refer to electrical bonding procedures in the WM chapter 20-13-05. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 31 

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) Perform a bonding test on the avionics rack according to the WM Part 1 chapter 

20-13-05, maximum bonding value is 2 milli-ohm. 

(6) Connect the cooling ducting. 

(a) Connect the cooling supply duct. Install the removed clamp or tie-wrap. 

(b) Connect the cooling exhaust duct. Install the removed clamp or tie-wrap. 

Step (7) is applicable if ABS mounting tray and wiring is installed. 

(7) Install the ABS wiring on the avionics tray. 

(a) On the mounting rack connect plug P 4082A and P4083A. 

(8) Install the HF-2 wiring on the avionics tray. 

(a) Route the wiring and install the removed clamps. 

(b) Install the ground studs GS0538 and GS0541 (code NC4.610-900), refer to 

electrical bonding procedures in the WM chapter 20-13-05. 

(c) Install the receptacle J 3470A. 

(d) Connect the plug P 3470B. 

(e) Install the HF-2 plug P 3388B on the mounting tray. 

(9) Install the HF-1 wiring on the avionics tray. 

(a) Route the wiring and install the removed clamps. 

(b) Install the ground studs GS0527 and GS0531 (code NC4.610-900), refer to 

electrical bonding procedures in the WM chapter 20-13-05. 

(c) Install the receptacle J 3471A. 

(d) Connect the plug P 3471B. 

(e) Install the HF-1 plug P 0276B on the mounting tray. 

(10) Install the equipment from the avionics rack in Zone 128. 

(a) Install the HF-1 Transceiver (refer to AMM, chapter 23-11-01). 

(b) Install the HF-2 Transceiver (refer to AMM, chapter 23-11-01). 

(c) Do the HF-1 and HF-2 system operational test (refer to AMM 23-11-00-710-815). 

Steps (11) and (12) are applicable if ABS control unit was removed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 32 Revision 2, Oct 16/12 

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.

(11) Install the ABS control unit (refer to AMM, chapter 32-48-02). 

(12) Do the ABS system operational test (refer to AMM 32-48-00-710-815). 

(13) Install the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-400-824-A. 

(14) Install the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-400-914-A. 

(15) Install the removed insulation blankets. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Close the equipment bay hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 6A of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 33 

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. 

Part 6 B: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 11268 

thru 11275, 11277, 11279, 11293, 11321, 11323 thru 11330, 11332, 11335, 11359, 

11361, 11367, 11378, 11387, 11388, 11396, 11397, 11404, 11432, 11438, 11439, 

11444, 11445, 11446, 11450, 11456, 11460 thru 11463, 11468, 11475 thru 11477, 

11483 thru 11490, 11492 thru 11496, 11497, 11499, 11500, 11502 thru 11505, 

11509, 11511, 11513, 11515 thru 11520, 11522 thru 11527 and if 

POST- SBF100-23-028: 11370, 11376, 11377, 11405, 11407, 11411 thru 11419, 

11425 thru 11427, 11435, 11436, 11449, 11457, 11458, 11464, 11465, 11467, 

11469, 11479, 11481, 11482, 11506 and 11514). 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the to be repaired area. The 

below procedure describes the complete remove all of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) Removal of equipment out of the Avionics rack in the Electrical Bay, Zone 128. 

(a) Open access panel 127AB and get access to the electrical bay. 

(b) The removal of equipment from the avionics rack in Zone 128. 

1 Remove and keep the HF-1 Transceiver (refer to AMM, chapter 23-11-01), if 

applicable. 

2 Remove and keep the TCAS computer (refer to the AMM, chapter 34-46-01), 

if applicable. 

3 Remove and keep the ABS control unit (refer to AMM, chapter 32-48-02), if 

applicable. 

Step (3) is applicable if HF-1 mounting tray and wiring is installed. 

(3) Loosen the HF-1 wiring from the avionics tray. 

(a) On the avionics rack disconnect plug P 3471B. 

(b) On the avionics rack loosen receptacle J 3471A, keep the attachment parts. 

(c) Loosen HF-1 plug P 0276B from the mounting tray, keep the attachment parts. 

(d) Loosen the ground studs GS0527 and GS0531, first identify the ground studs for 

easy installation, keep the attachment parts. 

(e) Stow the HF-1 wiring behind the avionics rack, remove and keep clamps if 

necessary. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 34 Revision 2, Oct 16/12 

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.

Step (4) is applicable if TCAS mounting tray and wiring is installed. 

(4) Loosen the TCAS wiring from the avionics tray. 

(a) On the avionics rack disconnect plug P 4284B. 

(b) On the avionics rack loosen receptacle J 4284A, keep the attachment parts. 

(c) On the avionics rack disconnect plug P 4110B. 

(d) On the avionics rack loosen receptacle J 4110A, keep the attachment parts. 

(e) Loosen TCAS plug P 4097B from the mounting tray, keep the attachment parts. 

(f) Loosen the ground studs GS0805 and GS0806, first identify the ground studs for 

easy installation, keep the attachment parts. 

(g) Loosen the terminal blocks TB4111A, TB4112A and TB4113A, first identify the 

terminal blocks for easy installation, keep the attaching parts. 

(h) Stow the TCAS wiring behind the avionics rack, remove and keep clamps if 

necessary. 

Step (5) is applicable if ABS mounting tray and wiring is installed. 

(5) Loosen the ABS wiring from the avionics tray. 

(a) On the avionics rack disconnect plugs P 4082A and P 4083A. 

(6) Disconnect the ducting. 

(a) Disconnect the cooling supply duct by removing the clamp or the tie-wrap. 

(b) Disconnect the cooling exhaust duct by removing the clamp or the tie-wrap. 

(7) Remove the avionics rack. 

(a) Remove and keep the four screws and washers that attach the avionics rack to 

the frame. 

(b) Carefully remove the avionics rack from the frame. 

NOTE: Take care NOT to damage the wave guide while working on the RH side 

of the equipment bay compartment. 

(8) Remove the RH surface-work platform, ref IPC 25-71-05. 

(9) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 67 between fuselage 

stations 3870-4150 and/or 4610-4850. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 35 

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. 

(1) Clean the butt joint at stringer 67 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 67 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 36 Revision 2, Oct 16/12 

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.

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 37 

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. 

(1) Install the removed insulation blankets. 

(2) Install the RH surface-work platform, ref IPC 25-71-05. 

(3) Installation of the Avionics rack in Electrical Bay, Zone 128. 

(a) Install the avionics rack on the frame. Attach it with the four screws and washers. 

For electrical bonding at the location of the mounting screws (code NC4.610-

940), refer to electrical bonding procedures in the WM chapter 20-13-05. 

(b) Perform a bonding test on the avionics rack according to the WM Part 1 chapter 

20-13-05, maximum bonding value is 2 milli-ohm. 

(4) Connect the cooling ducting. 

(a) Connect the cooling supply duct. Install the removed clamp or tie-wrap. 

(b) Connect the cooling exhaust duct. Install the removed clamp or tie-wrap. 

Step (5) is applicable if HF-1 mounting tray and wiring is installed. 

(5) Install the HF-1 wiring on the avionics tray. 

(a) Route the wiring and install the removed clamps. 

(b) Install the ground studs GS0527 and GS0531 (code NC4.610-900), refer to 

electrical bonding procedures in the WM chapter 20-13-05. 

(c) Install the receptacle J 3471A. 

(d) Connect the plug P 3471B. 

(e) Install the HF-1 plug P 0276B on the mounting tray. 

Step (6) is applicable if TCAS mounting tray and wiring is installed. 

(6) Install the TCAS wiring on the avionics tray. 

(a) Route wiring and install the removed clamps. 

(b) Install the ground studs GS0805 and GS0806 (code NC4.610-900), refer to 

electrical bonding procedures in the WM chapter 20-13-05. 

(c) Install the receptacle J 4284A. 

(d) Connect the plug P 4284B. 

(e) Install the receptacle J 4110A. 

(f) Connect the plug P 4110B. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 38 Revision 2, Oct 16/12 

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.

(g) Install the TCAS plug P 4097B on the mounting tray. 

(h) Install the terminal blocks TB4111A, TB4112A and TB4113A. 

Step (7) is applicable if ABS mounting tray and wiring is installed. 

(7) Install the ABS wiring on the avionics tray. 

(a) On the mounting rack connect plug P 4082A and P4083A. 

Steps (8) and (9) are applicable if TCAS Computer was removed. 

(8) Install the TCAS computer (refer to the AMM, chapter 34-46-01). 

(9) Do the TCAS functional test (refer to AMM 34-46-00-720-815). 

Steps (10) and (11) are applicable if HF-1 transceiver was removed. 

(10) Install the HF Transceiver 1 (refer to AMM, chapter 23-11-01). 

(11) Do the HF-1 system operational test (refer to AMM 23-11-00-710-815). 

Steps (12) and (13) are applicable if ABS control unit was removed. 

(12) Install the ABS control unit (refer to AMM, chapter 32-48-02). 

(13) Do the ABS system operational test (refer to AMM 32-48-00-710-815). 

(14) Install the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-400-824-A. 

(15) Install the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-400-914-A. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Close the equipment bay hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 6B of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 39 

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. 

Part 6 C: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to aircraft 11276, 

11278, 11280 thru 11283, 11286, 11289, 11291, 11295, 11300, 11303, 11306, 

11308, 11310, 11312 thru 11314, 11331, 11333 thru 11334, 11337 thru 11338, 

11345 thru 11346, 11349, 11357 thru 11358, 11365 thru 11366, 11372 thru 11373, 

11379 thru 11380, 11391 thru 11392, 11398 thru 11399). 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the to be repaired area. The 

below procedure describes the complete remove all of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) The removal of equipment from the avionics rack in Zone 128. 

(a) Remove and keep the ADC-1 (refer to the AMM, chapter 34-12-01). 

(b) Remove and keep the ADC-2 (refer to AMM, chapter 34-12-01). 

(c) Remove and keep the Weather Radar Transceiver (refer to AMM, chapter 34-41-

01). 

(3) Behind the avionics rack, loosen the Weather Radar waveguide quick disconnect 

coupling. 

(4) On the avionics rack disconnect plugs P 3778B, P 0458B, P 0333B, P 3762B, 

P 0337B and P 0335B. 

(5) Disconnect the cooling ducting. 

(a) Disconnect the cooling supply duct by removing the clamp or the tie-wrap. 

(b) Disconnect the cooling exhaust duct by removing the clamp or the tie-wrap. 

(6) Remove the avionics rack. 

(a) Remove and keep the four screws and washers that attach the avionics rack to 

the frame. 

(b) Carefully remove the avionics rack from the frame. 

(7) Remove the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-000-824-A. 

(8) Remove the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-000-914-A. 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 40 Revision 2, Oct 16/12 

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.

NOTE: Take care NOT to damage the wave guide while working on the RH side of 

 the equipment bay compartment. 

(9) Remove the RH surface-work platform, ref IPC 25-71-05. 

(10) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 67 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 67 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 67 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 41 

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. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 42 Revision 2, Oct 16/12 

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.

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the RH surface-work platform, ref IPC 25-71-05. 

(3) Installation of the Avionics rack in Electrical Bay, Zone 128. 

(a) Install the avionics rack on the frame. Attach it with the four screws and washers. 

For electrical bonding at the location of the mounting screws (code NC4.610-

940), refer to electrical bonding procedures in the WM chapter 20-13-05. 

(b) Perform a bonding test on the avionics rack according to the WM Part 1 chapter 

20-13-05, maximum bonding value is 2 milli-ohm. 

(4) On the mounting rack install the connectors P 3778B, P 0458B, P 0333B, P 3762B, 

P 0337B and P 0335B. 

(5) Attach the Weather Radar waveguide quick disconnect coupling behind the avionics 

tray. 

(6) Connect the cooling ducting. 

(a) Connect the cooling supply duct. Install the removed clamp or tie-wrap. 

(b) Connect the cooling exhaust duct. Install the removed clamp or tie-wrap. 

(7) Install the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-400-824-A. 

(8) Install the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-400-914-A. 

(9) Install the equipment on the avionics rack in Zone 128. 

(a) Install the ADC-1 (refer to the AMM, chapter 34-12-01). 

(b) Install the ADC -2 (refer to AMM, chapter 34-12-01). 

(c) Install the Weather Radar Transceiver (refer to AMM, chapter 34-41-01). 

(10) Do the tests. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 43 

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. 

(a) Do the Leak Check of the Pitot Static System (refer to AMM 34-11-00-790-815). 

(b) Do the ADC-1 and ADC-2 functional test (refer to AMM 34-12-00-720-825). 

(c) Do the weather radar system functional test (refer to AMM 34-41-00-720-815). 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Close the equipment bay hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 6C of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 44 Revision 2, Oct 16/12 

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.

Part 6 D: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to 11340, 11352 

thru 11356, 11360, 11368, 11369, 11395, 11403, 11406, 11408, 11428, 11447, 

11448, 11459, 11466, 11478, 11491, 11498, 11501 and if 

PRE - SBF100-23-028: 11370, 11376, 11377, 11405, 11407, 11411 thru 11419, 

11425 thru 11427, 11435, 11436, 11449, 11457, 11458, 11464, 11465, 11467, 

11469, 11479, 11481, 11482, 11506 and 11514). 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the to be repaired area. The 

below procedure describes the complete remove all of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) The removal of equipment from the avionics rack in Zone 128. 

(a) Remove and keep the TCAS computer (refer to the AMM, chapter 34-46-01). 

(b) Remove and keep the Baseband Unit (refer to AMM, chapter 23-14-08), if 

applicable. 

(c) Remove and keep the Power Supply Unit (refer to AMM, chapter 23-14-09), if 

applicable. 

(d) Remove and keep the Radio Frequency Unit (refer to AMM, chapter 23-14-10), if 

applicable. 

(3) Loosen the Air phone wiring from the avionics trays. 

(a) On the upper tray disconnect plugs, ground studs etc., if necessary for avionics 

rack removal. 

(b) On the lower tray disconnect plugs, ground studs etc., if necessary for avionics 

rack removal. 

(c) Stow the Air phone wiring behind the avionics rack, remove and keep clamps if 

necessary. 

(4) Loosen the TCAS wiring from the avionics tray. 

(a) On the avionics rack disconnect plug P 4284B. 

(b) On the avionics rack loosen receptacle J 4284A, keep the attachment parts. 

(c) On the avionics rack disconnect plug P 4110B. 

(d) On the avionics rack loosen receptacle J 4110A, keep the attachment parts. 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 45 

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) Loosen TCAS plug P 4097B from the mounting tray, keep the attachment parts. 

(f) Loosen the ground studs GS0805 and GS0806, first identify the ground studs for 

easy installation, keep the attachment parts. 

(g) Loosen the terminal blocks TB4111A, TB4112A and TB4113A, first identify the 

terminal blocks for easy installation, keep the attaching parts. 

(h) Stow the TCAS wiring behind the avionics rack, remove and keep clamps if 

necessary. 

(5) Disconnect the cooling ducting. 

(a) Disconnect the cooling supply duct by removing the clamp or the tie-wrap. 

(b) Disconnect the cooling exhaust duct by removing the clamp or the tie-wrap. 

(6) Remove the avionics rack. 

(a) Remove and keep the four screws and washers that attach the upper rack to the 

lower rack. Remove the upper rack. 

(b) Remove and keep the four screws and washers that attach the lower avionics 

rack to the frame. 

(c) Carefully remove the lower avionics rack from the frame. 

(7) Remove the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-000-824-A. 

(8) Remove the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-000-914-A. 

NOTE: Take care NOT to damage the wave guide while working on the RH side of 

 the equipment bay compartment. 

(9) Remove the RH surface-work platform, ref IPC 25-71-05. 

(10) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 67 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 67 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 67 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 46 Revision 2, Oct 16/12 

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.

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 50 mm. t = ~ 0,4 mm.

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 47 

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. 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the RH surface-work platform, ref IPC 25-71-05. 

(3) Installation of the lower and upper Avionics rack in Electrical Bay, Zone 128. 

(a) Install the lower avionics rack on the frame. Attach it with the four screws and 

washers. For electrical bonding at the location of the mounting screws (code 

NC4.610-940), refer to electrical bonding procedures in the WM chapter 20-13-

05. 
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(b) Install the upper avionics rack on the lower avionics rack. 

(c) Perform a bonding test on the avionics rack upper and lower according to the 

WM Part 1 chapter 20-13-05, maximum bonding value is 2 milli-ohm. 

(4) Connect the cooling ducting. 

(a) Connect the cooling supply duct. Install the removed clamp or tie-wrap. 

(b) Connect the cooling exhaust duct. Install the removed clamp or tie-wrap. 

(5) Install the silencer ducting and riser duct(s), as necessary, ref. AMM 

Task 21-20-00-400-824-A. 

(6) Install the avionics cooling supply ducting, if applicable, ref. AMM 

Task 21-20-00-400-914-A. 

(7) Install the TCAS wiring on the avionics tray. 

(a) Install the wiring and install the removed clamps. 

(b) Install the ground studs GS0805 and GS0806 (code NC4.610-900), refer to 

electrical bonding procedures in the WM chapter 20-13-05. 

(c) Install the receptacle J 4284A. 

(d) Connect the plug P 4284B. 

(e) Install the receptacle J 4110A. 

(f) Connect the plug P 4110B. 

(g) Install the TCAS plug P 4097B on the mounting tray. 

(h) Install the terminal blocks TB4111A, TB4112A and TB4113A. 

(8) Install the Air phone wiring on the avionics tray. 

(a) Route the wiring and install the removed clamps. 

(b) On the upper tray connect plugs, ground studs etc. 

(c) On the lower tray’s connect plugs, ground studs etc. 

(9) Install the equipment on the avionics rack in Zone 128. 

(a) Install the TCAS computer (refer to the AMM, chapter 34-46-01) and do the 

TCAS functional test (refer to AMM 34-46-00-720-815). 

(b) Install the Baseband Unit and do the after-installation test (refer to AMM, chapter 

23-14-08), if it was removed. 
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(c) Install the Power Supply Unit and do the after-installation test (refer to AMM, 

chapter 23-14-09), if it was removed. 

(d) Install the Radio Frequency Unit and do the after-installation test (refer to AMM, 

chapter 23-14-10), if it was removed. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Close the equipment bay hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 6D of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions. 
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Part 6 E: The Temporary Repair of the Butt Joint at Stringer 67 (Applicable to 11521, 11528, 

11529, 11532, 11536 thru 11541, 11543, 11545, 11547, 11549, 11551, 11553 thru 

11583, 11585). 

Refer to figures 16, 17 and 18. 

A. Get access to the repair area from the inside through the equipment bay compartment. 

NOTE: Only remove the necessary components that cover the to be repaired area. The 

below procedure describes the complete remove all of all components to provide 

full access between stations 3850 and 5305. 

(1) Open and temporary store the equipment bay hatch 127AB, ref. AMM Task 06-30-01-

ZZ1-810-A, and get access to the electrical bay. 

(2) The removal of equipment from the avionics rack 1 in Zone 135. 

(a) Remove and keep the grey polycarbonate protection plates on the aft side of the 

avionics rack by loosening and keeping of the bolts and clip nuts. 

(b) Remove and keep the ADC-2 (refer to AMM, chapter 34-12-01). 

(c) Remove and keep the Weather Radar Transceiver (refer to AMM, chapter 34-41-

01). 

(3) Remove the RH surface-work platform, ref IPC 25-71-05. 

(4) Remove the insulation blankets in the repair area. 

B. Preparation for the temporary repair of the butt joint at stringer 67 between fuselage 

stations 3870-4150 and/or 4610-4850. 

(1) Clean the butt joint at stringer 67 between fuselage station 3870-4150 and/or 4610-

4850on the outside. Remove the paint scheme, if necessary, to see the existing solid 

rivet heads. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

(2) Clean the inside at stringer 67 where the temporary repair must be applied. Use: 

- AR lint-free cloth Fk05-044 

- AR Methyl Ethyl Ketone (or equivalent) Fk11-003. 

Refer to figures 16 and 17. 

(3) Close visually inspect for cracks in the butt strap on the inside at this joint. Remove 

the cracked part of the butt joint and install an insert 

(a) Temporary slide/install a sacrificial thin corrosion resistant steel (or stainless 

steel) strip between the butt strap and the outer skin, at the location of the cut, to 

avoid cutting in the skin. Use: 

- AR corrosion resistant steel ~20 x 50 mm. t = ~ 0,4 mm.
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(or stainless steel) strip 

(b) Cut the butt strap and sent the cut out part to Fokker Services BV. For the 

address refer to SBF100-00-001 (Service Bulletin Introduction). 

(c) Remove the sacrificial thin corrosion resistant steel (or stainless steel) strip. 

(d) Manufacture an insert, pick up existing fastener holes, treat all bare edges and 

install with sealing compound according to figure 17. Use existing rivets and: 

- AR sheet, aluminum pn F0N1-4311-1AL- * - 

- AR coating pn Alodine 1201 Fk13-003D 

- AR primer (not in holes) pn S15/60 Aerodur Fk07-008 

- AR sealant pn PR1436GA1-2 Fk09-016 

- AR sealant pn PR1436GB1-2 Fk09-017. 

NOTE: * 1,2 mm (0.050 inch) thick 2024T3 Alclad aluminum sheet. 

(4) Drill out the necessary fasteners for the repair of the butt joint. Mark the proper 

fasteners at each location. 

C. Manufacture of an external repair strap. 

(1) Manufacture the external repair strap from local source material according to figure 

17. Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * as required. 

NOTE: * 1,4 mm (0.055 inch) thick 2024T3 Alclad aluminum sheet. 

Refer to figure 18. 

(2) Round off the edges of the external repair strap with a radius of R=t. 

(3) Copy drill the existing fastener holes into the external repair strap. Instead of the 

original type of rivets NAS1097DD4-XX, NAS1097DD5-XX, NAS1097DD6-XX must 

be used. If -4 or -5 rivet holes have become too large, they must be drilled to the next 

size and NAS1097DD5-XX or NAS1097DD6-XX must be installed. If -6 Hilok holes or 

-6 rivet holes have become too large, they must be drilled to the first oversize Hilok 

HL111VF6-xx and for a HL11VF5 the next size HL11VF6-xx is applicable. 

(4) Remove the external repair strap. Deburr and countersink all holes and protect all 

bare aluminum with Alodine and primer. Use: 

- AR Coating pn Alodine 1201 Fk13-003D 

- AR Primer (not in holes) pn S15/60 Aerodur Fk07-008. 

D. Installation of the external repair strap. 

(1) Install countersunk repair washers (refer to SRM 51-43-04) with interfaying sealant in 

the existing countersinkings in the outer skin. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK repair washers pn F0N18-9151S04 (or rivet heads) 

- AR CSK repair washers pn F0N18-9151S05 (or rivet heads) 
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- AR CSK repair washers pn F0N18-9151S06 (or rivet heads) 

- AR CSK repair washers pn F0N18-9152-02 

- AR CSK repair washers pn F0N18-9152-03. 

(2) Install the external repair strap and, if applicable, with solid rivets, hiloks and 

interfaying sealant. Aerodynamically seal off the edges of the external repair strap. 

Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097DD4-xx or F0N2-6328S4-xx 

- AR CSK rivet pn NAS1097DD5-xx or F0N2-6328S5-xx 

- AR CSK rivet pn NAS1097DD6-xx or F0N2-6328S6-xx 

- AR CSK hilok pn HL11VF5-xx F0N2-1197-5 

- AR CSK hilok pn HL11VF6-xx F0N2-1197-6 

- AR CSK oversize hilok pn HL111VF6-xx F0N18-1220-6 

- AR hilok collar pn HL70-5 F0N2-1181-5 

- AR hilok collar pn HL70-6 F0N2-1181-6 

- AR hilok collar pn HL79-6 F0N18-2230-6. 

 

(3) Restore paint scheme, refer to AMM, chapter 51-21-00. 

E. Clean up and restore paint scheme. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Restore paint scheme, refer to AMM, chapter 51-21-00. 

F. Installation of the equipment which was removed in step A. 

(1) Install the removed insulation blankets. 

(2) Install the RH surface-work platform, ref IPC 25-71-05. 

(3) Installation of equipment from the avionics rack in Zone 135. 

(a) Install the grey polycarbonate protection plates on the aft side of the avionics rack 

by fastening the bolts with the clip nuts. 

(b) Install the ADC-2 (refer to AMM, chapter 34-12-01). 

(c) Install the Weather Radar Transceiver (refer to AMM, chapter 34-41-01). 

(4) Do the tests. 

(a) Do the Leak Check of the Pitot Static System (refer to AMM 34-11-00-790-815). 

(b) Do the ADC-2 functional test (refer to AMM 34-12-00-720-825). 

(c) Do the weather radar system functional test (refer to AMM 34-41-00-720-815). 
Service Bulletin 

Fokker 70/100 

Apr 10/12 SBF100-53-118 

Revision 2, Oct 16/12 Page 53 

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except with the prior written permission of Fokker Services B.V. 

G. Job close up. 

(1) Remove all tools, materials and equipment from the working area. Make sure that the 

working area is clean. 

(2) Close the equipment bay hatch 127AB, ref. AMM Task 06-30-01-ZZ1-810-A. 

NOTE: If this temporary repair has been performed record in the aircraft 

documentation when and on which frame bay(s) “Part 6E of SBF100-53-118” 

has been performed, for easy determination of applicability of future actions.
Service Bulletin 

Fokker 70/100 

SBF100-53-118 Apr 10/12 

Page 54 Revision 2, Oct 16/12 

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Pos. Description t Dimensions Material Remarks 

A Sheet 1,0 200 x 49 2024T3 Alclad 2x 

B Sheet 1,2 200 x 80 2024T3 Alclad - 

C Sealant 0,2 - PR1436GA1-2 or equivalent 

D Crack - 10,0 x 0,2 ±0,1 Saw cut Pre drill Ø 1,0 mm 

E Tool no. - - Engrave/mark SB10053118PLATE 

All dimensions in mm

The Manufacturing of the Calibration Plate. 

Figure 1 

A 

B

A

C

4 

4 

10 

200 

49

2,0

100 80 

E

Ø 1,0 

SB10053118PLATE 

D
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Apr 10/12 SBF100-53-118 

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Slot position on Calibration Plate. 

Figure 2 

Typical Scan Pattern on the Butt Joint. 

Figure 3 

I II I

SB10053118PLATE 

PROBE 

Scan pattern 

Typical crack 

in butt strap

Probe starting point 

Frame 

Non-conductive 

ruler
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Screen Indications. 

Figure 4 

Crack indication 

Lift-off indication 

 

0%

25%

50%

75%

100%

0

2

4

6

8

10 8 6 5 4 2 0

B 

 

0%

25%

50%

75%

100%

0

2

4

6

8

10 8 6 5 4 2 0

A 
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Apr 10/12 SBF100-53-118 

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The Inspection Area of the Butt Joint at Stringer 8 between Stations 3850 and 5305 

below the Passenger Door. 

Figure 5 

Inspection area STR 8 

Refer to figure 8 for aircraft pre SBF100-53-091 configuration 

Refer to figure 9 for aircraft post SBF100-53-091 configuration 
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The Inspection Area of the Butt Joint at Stringer 37 and 42 between Stations 3850 and 5305. 

Figure 6

Inspection area STR 37 

Refer to figure 10 

Inspection area STR 42 

Refer to figure 11 
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The Inspection Area of the Butt Joint at Stringer 67 between Stations 3850 and 5305 

below the Forward Service and Emergency Door. 

Figure 7 

Inspection area STR 67 

Refer to figure 12 for aircraft pre SBF100-53-091 configuration 

Refer to figure 13 for aircraft post SBF100-53-091 configuration 
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Inspection Area of Stringer 8 for aircraft pre SBF100-53-091 configuration. 

Figure 8 

STA 3870 

STA 4175 

STA 4610 

STA 4850 

A B 

STA 3870 

STA 4175 

STA 4610 

Detail A 

STR 8A STR 8A 
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Inspection Area of Stringer 8A for aircraft in post SBF100-53-091 configuration. 

Figure 9 

STA 3870 

STA 4175 

STA 4610 

STA 4850 

A 

Reinforcement plate in accordance with SBF100-53-091 

STA 4610 

STA 4850 

Detail A 

STR 8A 
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Inspection Area of Stringer 37. 

Figure 10 
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Inspection Area of Stringer 42. 

Figure 11 
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Inspection Area of Stringer 67 in pre SBF100-53-091 configuration. 

Figure 12 

A 

STA 3870 

STA 4175 

STA 4610 

STR 67 STR 67 

B 

Detail A 
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Inspection Area of Stringer 67 in post SBF100-53-091 configuration. 

Figure 13 

A 

Detail A

STA 4610 

STA 4850 

STR 67 

Reinforcement plate in accordance with SBF100-53-091 
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Operator: Aircraft Serial Number: Flight cycles: Flight hours: 

Indicate on the figure the crack location & direction and fill in the table the length of the crack. 

Crack number: Stgr no: (8 or 67) Crack length: (mm or inch) Position*: (mm or inch) 

* Distance FWD crack tip to nearest FWD frame. 

Reporting Form Stringers 8 and/or 67. 

Figure 14 

External 

reinforcement 

doubler 

STA 3870 

STA 4175 

STA 4610 

STR 8A STR 8A 

STA 3870 

STA 4175 

STA 4610 

STR 67 STR 67 
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Operator: Aircraft Serial Number: Flight cycles: Flight hours: 

Indicate on the figure the crack location & direction and fill in the table the length of the crack 

Crack number: Stgr no: (37 or 42) Crack length: (mm or inch) Position*: (mm or inch) 

* Distance FWD crack tip to nearest FWD frame. 

Reporting Form Stringers 37and/or 42. 

Figure 15

STR 42 

STA 4175 

STA 3870 

STR 37 

STA 4610 

STR 37 

STA 4150 

STR 42 

STA 4850 

STA 4610 
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NOTES: * Use a sacrificial CRES strip to avoid cutting in the outer skin. Be careful when 

making the cutout. 

Do not affect the crack line, this is necessary for investigation. 

After the cracked part has been removed, make a smooth cut of the cracked 

part suitable to install an insert, refer to figure 17. 

Cut out of the Cracked Part of the Butt Strap. 

Figure 16 

 

Cut out the crack as indicated* 

Typical crack 
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Installation of the External Repair Strap. 

Figure 17 

Insert to fill the removed 

cracked part of the butt strap 

Frame 

butt strap

External repair strap 

Extend the external repair strap two rows stringer

of fasteners past the cut out on both sides.
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Round of the Edges of the Repair Strap and Aerodynamically Seal the Edges. 

Figure 18

Aerodynamically seal 

all the edges 

Aerodynamically seal 

all the edges 

A A

Section A-A

(before application of sealant) 

Section A-A

(after application of sealant) 

Round-off 

edges 

R (R = t) 

t 

External repair strap 

External repair strap 
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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 (are) 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