Service Bulletin 

Fokker 70/100 

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June 20/12 SBF100-53-119 

Revision 2, May 08/13 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 Terminating Repair/Modification of the Forward Fuselage 

 Butt-joints at Stringer 8, 37, 42 and 67 between Fuselage Stations 

 3850-5305. 

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. 

B. Concurrent Requirements 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 2 Revision 2, May 08/13 

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. 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) Service Bulletin SBF100-53-118 introduced a repetitive inspection (and, if applicable, 

a temporary repair) on the butt joints at stringers 8, 37, 42 and 67 between fuselage 

stations 3850-5305. The repetitive inspections in that bulletin have subsequently been 

overruled by an inspection task in the Airworthiness Limitation Section (ALS) report 

SE-623 (task numbers 531030-00-11 and 531031-00-05) of the Instructions for 

Continued Airworthiness (ICA). 

(3) If you have found a crack (or cracks) during accomplishment of Service Bulletin 

SBF100-53-118, the aircraft needs to be repaired before further flight with a 

temporary repair according to SBF100-53-118 or with a terminating repair by Part 1 

and/or Part 2, 3, 4A, 4B, 4C, 4D or 4E of this bulletin (SBF100-53-119). 

(4) Repetitive inspections are no longer applicable on aircraft where the terminating 

repair has been accomplished on all four butt joints. 

(5) This Service Bulletin can also be accomplished as a modification (also for aircraft for 

which the inspections are not yet due) to avoid any inspections. 

Reason for Revision 1: 

(1) This revision is made to: 

- Add the removal and installation instructions for the ATC #1 top antenna, the GPS 

 antennas (if installed) and for the Galley area light. 

Reason for Revision 2:

(1) This revision is made to: 

- Incorporate (optional) mod-kits upon request op customers/operators. 

- Clarify what to do with existing bonding rivet (hole)s. These are to be picked up by 

 new solid rivets. 

- Mention the applicable Airworthiness Directive (AD) and new Airworthiness 

 Limitation Section (ALS) Task numbers with respect to this subject. 

D. Description 

(1) This service bulletin is divided in 4 parts as follows: 

Part 1: The Terminating Repair of the Butt Joint at Stringer 8 between Fuselage 

Stations 3850 and 5305. 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 6. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 2: The Terminating Repair of the Butt Joint at Stringer 37 between Fuselage 

Stations 3850 and 5305. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 3: The Terminating Repair of the Butt Joint at Stringer 42 between Fuselage 

Stations 3850 and 5305. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 4A: The Terminating Repair of the Butt Joint at Stringer 67 between Fuselage 

Stations 3850 and 5305 ((Applicable to aircraft 11316 and 11318). 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 9. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 4 Revision 2, May 08/13 

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.

Part 4B: The Terminating Repair of the Butt Joint at Stringer 67 between Fuselage 

Stations 3850 and 5305 (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). 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 9. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 4C: The Terminating Repair of the Butt Joint at Stringer 67 between Fuselage 

Stations 3850 and 5305 (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). 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 9. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 4D: The Terminating Repair of the Butt Joint at Stringer 67 between Fuselage 

Stations 3850 and 5305 (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). 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 9. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

Part 4E: The Terminating Repair of the Butt Joint at Stringer 67 between Fuselage 

Stations 3850 and 5305 (Applicable to aircraft 11521, 11528, 11529, 11532, 

11536 thru 11541, 11543, 11545, 11547, 11549, 11551, 11553 thru 11583, 

11585). 

NOTE: This Part has a different repair area when the repair/modification described 

in the Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, 

see Figure 9. 

This Part tells how to: 

- Get access on the inside of the repair area 

- Remove the applicable fasteners 

- Remove the temporary repair per SBF100-53-118, if applicable 

- Inspect, and remove the cracked part of the butt-strap if applicable 

- Install an insert for the removed part of the butt strap, if applicable 

- Install the external repair strap. 

E. Compliance 

(1) Recommended. 

Fokker Services recommends the accomplishment of this Service Bulletin before the 

aircraft will have accumulated 50,000 FC since new or within 8 months after the date 

of initial issue of this Service Bulletin (June 20, 2012), whichever comes last. 

NOTE: EASA has issued an Airworthiness Directive (AD) 2012-0218 with respect to 

 this subject with the same compliance terms. 

F. Approval 

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

EASA.21J.059. 

G. Manpower 

(1) Approximately 30 man-hours are necessary to do Part 1 of this Service Bulletin on 

one aircraft. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 6 Revision 2, May 08/13 

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.

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. 

(2) Approximately 34 man-hours are 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 1 9,0 9,0 

Modification 

Inspection 2 12,0 6,0 

Installation 1 6,0 6,0 

Testing 1 7,0 7,0 

Total 34,0 28,0 

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

the sealant to cure. 

(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 4A thru 4E of this Service 

Bulletin on one aircraft. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

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. 

(5) 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 1: 

(a) Repair at stringer 8 accomplished between fuselage stations 3850-5305: 

Weight change: + 1,0796 kg (2.380 lb) 

Index change: Mark 0100: - 0.138 

 Mark 0070: - 0.111. 

(b) Repair at stringer 8 accomplished between fuselage stations 4410-5305, in case 

SBF100-53-091 is accomplished (shorter repair strap): 

Weight change: + 0,6763 kg (1.491 lb) 

Index change: Mark 0100: - 0.084 

 Mark 0070: - 0.068. 

(c) Repair at stringer 8 accomplished between fuselage stations 4830-5305, in case 

SBF100-53-105 is accomplished (shorter repair strap): 

Weight change: + 0,3506 kg (0.773 lb) 

Index change: Mark 0100: - 0.043 

 Mark 0070: - 0.034. 

(2) Part 2: 

(a) Repair at stringer 37 accomplished between fuselage stations 3850-5305: 

Weight change: + 1,0907 kg (2.405 lb) 

Index change: Mark 0100: - 0.139 

 Mark 0070: - 0.112. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 8 Revision 2, May 08/13 

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.

(3) Part 3: 

(a) Repair at stringer 42 accomplished between fuselage stations 3850-5305: 

Weight change: + 1,0796 kg (2.380 lb) 

Index change: Mark 0100: - 0.138 

 Mark 0070: - 0.111. 

(4) Part 4A thru 4E: 

(a) Repair at stringer 67 accomplished between fuselage stations 3850-5305: 

Weight change: + 1,0796 kg (2.380 lb) 

Index change: Mark 0100: - 0.138 

 Mark 0070: - 0.111. 

(b) Repair at stringer 67 accomplished between fuselage stations 4410-5305, in case 

SBF100-53-091 is accomplished (shorter repair strap): 

Weight change: + 0,6763 kg (1.491 lb) 

Index change: Mark 0100: - 0.084 

 Mark 0070: - 0.068. 

(c) Repair at stringer 67 accomplished between fuselage stations 4830-5305, in case 

SBF100-53-105 is accomplished (shorter repair strap): 

Weight change: + 0,3506 kg (0.773 lb) 

Index change: Mark 0100: - 0.043 

 Mark 0070: - 0.034. 

I. Electrical Load Data 

(1) Not changed. 

J. Software Accomplishment Summary 

(1) Not applicable. 

K. References 

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

Fokker 70/100 Structural Repair Manual (SRM) 

Fokker 70/100 Illustrated Parts Catalog (IPC) 

Fokker 70/100 Standards and Process Manual (SPM) 

Fokker 70/100 Service Bulletin (SB): 

 - SBF100-53-091 

 - SBF100-53-105 

 - SBF100-53-118. 

Fokker Consumable Material List (CML) 

Fokker internal reference(s): 

 - ECR015861. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

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) 

(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 - X 

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

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

 and/or the 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, see last SB page. 

NOTE: Completion of this form is not a formal part of accomplishment of the Service 

Bulletin itself and hence not a requirement. 

(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 

SBF100-53-119 June 20/12 

Page 10 Revision 2, May 08/13 

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.

2. Material Information

A. Material – Price and Availability 

(1) The materials are local source items. 

(2) You can order the necessary parts as mod kit SB10053119-XU-A. 

B. Material Required 

(1) These parts, which are necessary to complete Part 1 thru 4E of this Service Bulletin 

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

New Part Number Qty Keyword Info Old Part Instructions/

 

AR* 

AR* 

- 

AR* 

AR* 

- 

AR* 

- 

- 

AR* 

- 

- 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

 Number Disposition

- Lint-free cloth Fk05-044** - Local source 

Methyl Ethyl Ketone 

(MEK)*** 

Cleaning solvent Fk11-003 - Local source 

Alodine1201 Coating Fk13-003D** - Local source 

Corrosion resistant 

steel strip. 

(or stainless steel) ~20 x 50 mm. 

t = ~ 0,4 mm. 

- Local source 

F0N1-4311-1AL- Sheet, aluminum, 2024T3 Alclad 

t = 1,2 mm 

(0.050 inch). 

- Local source 

F0N1-4311-1AM- Sheet, aluminum, 

~220 x 1500 mm. 

2024T3 Alclad 

t = 1,4 mm 

(0.055 inch). 

- Local source 

NAS1097AD5-xx CSK rivet or F0N2-6325AD5 - Local source 

NAS1097DD6-xx CSK rivet or F0N2-6328S5 - Local source 

HL11VF5-xx CSK hilok F0N2-1197-5 - Local source 

HL11VF6-xx CSK hilok F0N2-1197-6 - Local source 

HL111VF6-xx CSK oversize hilok F0N18-1220-6 - Local source 

HL70-5 hilok collar F0N2-1181-5 - Local source 

HL70-6 hilok collar F0N2-1181-6 - Local source 

HL79-6 hilok collar F0N18-2230-6 - Local source 

F0N18-9151S05 CSK repair washer or rivet heads - Local source 

F0N18-9151S06 CSK repair washer or rivet heads - Local source 

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

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

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

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

S15-60 Aerodur Aerodur Primer Fk07-008**/*** - Local source 

NOTES: * Use as much as necessary 

** Refer to the CML for material numbers 

*** Or equivalent 

**** Is replaced by new Sealant type per TH5.978. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(2) These local source items are still necessary when a mod kit is ordered. 

New Part Number Qty Keyword Info Old Part Instructions/

 

AR* 

AR* 

AR* 

AR* 

AR* 

AR* 

 Number Disposition

- Lint-free cloth Fk05-044** - Local source 

Methyl Ethyl Ketone 

(MEK)*** 

Cleaning solvent Fk11-003 - Local source 

Alodine1201 Coating Fk13-003D** - Local source 

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

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

S15-60 Aerodur Aerodur Primer Fk07-008**/*** - Local source 

NOTES: * Use as much as necessary 

** Refer to the CML for material numbers 

*** Or equivalent. 

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

New Part Number Qty Keyword Info Old 

Part 

Instructions/

 Numbe

r

Disposition

W21000-009 1 Corrosion resistant 

steel strip. 

20 x 50 mm. 

t = 0,4 mm. 

- - 

W21000-011 4 External repair strap. 220 x 1500 mm. - - 

W21000-013 10 Shims. 20 x 20, 0.8 mm. - - 

W21000-015 10 Shims. 20 x 20, 1.2 mm. - - 

W21000-017 10 Shims. 20 x 20, 1.4 mm. - - 

W21000-019 4 Insert. 45 x 460 mm. - - 

NAS1097AD5-6 2100* CSK rivet or F0N2-6328S5 - - 

NAS1097AD5-10 200* CSK rivet or F0N2-6328S5 - - 

NAS1097DD6-10 14* CSK rivet or F0N2-6328S6 - - 

HL11VF5-6 20 CSK hilok F0N2-1197-5-6 - - 

HL11VF5-7 20 CSK hilok F0N2-1197-5-7 - - 

HL11VF6-3 15 CSK hilok F0N2-1197-6-3 - - 

HL11VF6-4 15 CSK hilok F0N2-1197-6-4 - - 

HL11VF6-5 55 CSK hilok F0N2-1197-6-5 - - 

HL11VF6-6 45 CSK hilok F0N2-1197-6-6 - - 

HL11VF6-7 45 CSK hilok F0N2-1197-6-7 - - 

HL11VF6-8 5 CSK hilok F0N2-1197-6-8 - - 

HL111VF6-3 5 CSK oversize hilok F0N18-1220-6-3 - - 

HL111VF6-4 5 CSK oversize hilok F0N18-1220-6-4 - - 

HL111VF6-5 15 CSK oversize hilok F0N18-1220-6-5 - - 

HL111VF6-6 10 CSK oversize hilok F0N18-1220-6-6 - - 

HL111VF6-7 10 CSK oversize hilok F0N18-1220-6-7 - - 

HL70-5 40 hilok collar F0N2-1181-5 - - 

HL70-6 180 hilok collar F0N2-1181-6 - - 

HL79-6 45 hilok collar F0N18-2230-6 - - 

F0N18-9151S04 850 CSK repair washer - - - 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 12 Revision 2, May 08/13 

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.

F0N18-9151S05 410 CSK repair washer - - - 

F0N18-9151S06 10 CSK repair washer - - - 

F0N18-9152-02 16 CSK repair washer - - - 

F0N18-9152-03 48 CSK repair washer - - - 

NOTES:* Or longer rivet length (must be cut to proper length). 

C. Tooling – Price and Availability 

(1) Not applicable. 

D. Drawings Required 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

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

- For locations of plugs and receptacles, refer to WM. 

- Loosen cable clamps where necessary. 

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

THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY 

INSTRUCTIONS. 

Part 1: The Terminating Repair of the Butt Joint at Stringer 8 between LH Fuselage Stations 

3850 and 5305. 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 6. 

Refer to figures 1 and 6. 

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 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 01A: 

(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. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 14 Revision 2, May 08/13 

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.

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

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

stations 3850 and 5305. 

Refer to figures 1, 4, 5 and 6. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 8 between fuselage station 3870 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

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

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 6. 

(5) Drill out the necessary existing rivets and/or hiloks for the repair of the butt joint. Mark 

the proper fasteners at each location. 

C. Manufacture of an external repair strap. 

Refer to figure 6. 

(1) Manufacture the external repair strap from local source material according to figure 6. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 6. 

(3) Temporary install the external repair strap on the proper fuselage position and mark 

the new rivet/hilok locations according to figure 6, use a pitch according to the 

existing rivet/hilok pattern, 18 – 22 mm. 

(4) On the indicated five (5) locations, if applicable, under the coupling angles install (an) 

additional shim(s). Manufacture the shim(s) from local source material according to 

figure 6. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5- 

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(6) Copy drill the existing fastener holes into the external repair strap. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 16 Revision 2, May 08/13 

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.

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(7) Remove the external repair strap and shims. Deburr 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 F0N18-9151S05 (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 additional shim(s) on the indicated five (5) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

(3) Install the external repair strap with solid rivets, hiloks and interfaying sealant. 

Aerodynamically seal off the edges of the external repair patch. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- AR CSK rivet pn NAS1097AD5-xx or F0N2-6325AD5-x 

- 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

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 housing, ref.IPC chapter 21-26-04 figure 01A: 

(a) Install the attachment bolts with washers which were kept in step A.(3). 

(b) Connect the duct assy’s. 

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

(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. 

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

 documentation the ECR (ECR015861) as “Part 1 of SBF100-53-119” has been 

 performed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 18 Revision 2, May 08/13 

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.

Part 2: The Terminating Repair of the Butt Joint at Stringer 37 between Fuselage Stations 

3850 and 5305. 

Refer to figures 3 and 7. 

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. Especially the ceiling panel in the entrance (with the galley area 

light ref. AMM TASK 33-28-01-000-814) per AMM TASK 25-24-00-000-814 or AMM 

TASK 25-24-00-000-864. 

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

(3) Remove the ATC #1 antenna per AMM TASK 34-54-03-000-814. 

(4) Remove the GPS antenna, if applicable, per AMM TASK 34-43-03-000-814 or AMM 

TASK 34-59-02-000-814 or AMM TASK 34-61-04-000-814. 

B. Preparation for the Terminating Repair of the Butt Joint at Stringer 37 between Fuselage 

Stations 3850 and 5305. 

Refer to figures 3, 4, 5 and 7. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 37 between fuselage station 3870 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR Lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

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

- AR Lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(or stainless steel) strip 

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. 

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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 7. 

(5) Drill out the existing rivets and/or hiloks of the butt joint. Mark the proper fasteners at 

each location. 

C. Manufacture of an external repair strap. 

Refer to figure 7. 

(1) Manufacture the external repair strap from local source material according to figure 7. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 7. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 20 Revision 2, May 08/13 

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.

(3) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 7, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) Remove the mentioned coupling angles and shim(s) at stringer 37, frames 4850, and 

keep for re-installation. 

(5) On the indicated location at stringer 37, approximate station 3960, under the coupling 

angle, install (an) additional shim(s). Manufacture the shim(s) from local source 

material according to figure 7. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(6) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(7) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(8) Remove the external repair patch. Deburr 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 and, if applicable, in the existing external 

reinforcement doubler. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(2) Install the additional shim(s) on the indicated location, under the coupling angle, at 

stringer 37, approximate frame 3960. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

(3) Install the mentioned coupling angles and shim(s) at stringer 37, frames 4850, which 

were kept at step B (4). 

(4) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-x 

- 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 ATC #1 antenna per AMM TASK 34-54-03-400-814 (a new gasket p/n: 

AG282000–03 may be necessary). 

(2) Install the GPS antenna, if applicable, per AMM TASK 34-43-03-400-814 or AMM 

TASK 34-59-02-400-814 or AMM TASK 34-61-04-400-814 (a new gasket p/n: 

AG477000–01 may be necessary). 

(3) Install the insulation blankets in the repair area. 

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

panel in the entrance (with the galley area light, per AMM TASK 33-28-01-400-814) 

per AMM TASK 25-24-00-400-814-A/E or AMM TASK 25-24-00-400-864-B/D. 

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

working area is clean. 

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

 documentation the ECR (ECR015861) as “Part 2 of SBF100-53-119” being 

 performed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 22 Revision 2, May 08/13 

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.

Part 3: The Terminating Repair of the Butt Joint at Stringer 42 between RH Fuselage 

Stations 3850 and 5305. 

Refer to figures 3 and 8. 

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

(1) Remove the door exit sign 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 terminating repair of the butt joint at stringer 42 between fuselage 

stations 3850 and 5305. 

Refer to figures 3, 4, 5 and 8. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 42 between fuselage station 3870 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR lint-free cloth Fk05-044 

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

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

- AR lint-free cloth Fk05-044 

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

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes.. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 8. 

(5) Drill out the existing rivets and/or hiloks of the butt joint. Mark the proper fasteners at 

each location. 

C. Manufacture of an external repair strap. 

Refer to figure 8. 

(1) Manufacture the external repair strap from local source material according to figure 5. 

Use: 

- AR sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 8. 

(3) Temporary install the external repair strap on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 8, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 24 Revision 2, May 08/13 

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.

(5) Copy drill the existing fastener holes into the external repair strap. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(6) Remove the external repair strap. Deburr 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 F0N18-9151S05 (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 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 NAS1097AD5-xx or F0N2-6325AD5-x 

- 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 restoration of 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 51-24-00. 

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

(1) Install the removed insulation blankets. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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 sign above the FWD S/E door, ref. AMM task 33-52-02-400-814-

A. 

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

working area is clean. 

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

 documentation the ECR (ECR015861) as “Part 3 of SBF100-53-119” being 

 performed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 26 Revision 2, May 08/13 

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.

Part 4A: The Terminating Repair of the Butt Joint at Stringer 67 between RH Fuselage 

Stations 3850 and 5305 (Applicable to aircraft 11316 and 11318). 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 9. 

Refer to figures 2 and 9. 

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. Information on HF-2 can be found in 

Fokker report AVWN355. 

(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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(e) Stow the HF-2 wiring behind the avionics tray, 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 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 terminating repair of the butt joint at stringer 67 between fuselage 

stations 3850 and 5305. 

Refer to figures 2, 4, 5 and 9. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 67 between fuselage station 3850 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 28 Revision 2, May 08/13 

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.

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. 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 Aeodur 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 9. 

(5) Drill out the existing rivets and/or hiloks of the butt joint. Mark the proper fasteners at 

each location. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

C. Manufacture of an external repair strap. 

Refer to figure 9. 

(1) Manufacture the external repair strap from local source material according to figure 9. 

Use: 

- AR sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 9. 

(3) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 5, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) On the indicated three (3) locations, if applicable, under the coupling angles install 

(an) additional shim(s). Manufacture the shim(s) from local source material according 

to figure 9. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(6) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 30 Revision 2, May 08/13 

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.

(7) Remove the external repair strap and shims. Deburr 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 F0N18-9151S05 (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 additional shim(s) on the indicated three (3) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

(3) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-x 

- 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. 

(4) Restore paint scheme, refer to AMM, chapter 51-24-00. 

E. Clean up and paint scheme restoration. 

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

working area is clean. 

(2) Restore the original paint scheme according to AMM 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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. 

(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. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 32 Revision 2, May 08/13 

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.

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

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

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

working area is clean. 

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

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

 documentation the ECR (ECR015861) as “Part 4A of SBF100-53-119” being 

 performed. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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 4B: The Terminating Repair of the Butt Joint at Stringer 67 between RH Fuselage 

Stations 3850 and 5305 (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). 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 9. 

Refer to figures 2 and 9. 

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 from 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. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 34 Revision 2, May 08/13 

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.

(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. 

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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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 terminating repair of the butt joint at stringer 67 between fuselage 

stations 3850 and 5305. 

Refer to figures 2, 4, 5 and 9. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 67 between fuselage station 3870 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 – 5285 resp. 4850 – 5285. 

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. Use existing rivets and: 

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

- AR coating pn Alodine 1201 Fk13-003D 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 36 Revision 2, May 08/13 

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.

- 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 9. 

(5) Drill out the existing rivets and/or hiloks of the butt joint. Mark the proper fasteners at 

each location. 

C. Manufacture of an external repair strap. 

Refer to figure 9. 

(1) Manufacture the external repair strap from local source material according to figure 9. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 9. 

(3) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 9, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) On the indicated three (3) locations, if applicable, under the coupling angles install 

(an) additional shim(s). Manufacture the shim(s) from local source material according 

to figure 9. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(6) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(7) Remove the external repair strap and shims. Deburr 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 and, if applicable, in the existing external 

reinforcement doubler. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

- 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 additional shim(s) on the indicated three (3) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

(3) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-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 paint scheme restoration. 

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

working area is clean. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 38 Revision 2, May 08/13 

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.

(2) Restore paint scheme, refer to AMM, chapter 51-24-00. 

F. Installation of the equipment which was removed at 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. 

(b) 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. 

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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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. 

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. 

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

working area is clean. 

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

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

 documentation the ECR (ECR015861) as “Part 4B of SBF100-53-119” 

 being performed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 40 Revision 2, May 08/13 

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.

Part 4C: The Temporary Repair of the Butt Joint at Stringer 67 between RH Fuselage 

Stations 3850 and 5305 (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). 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 9. 

Refer to figures 2 and 9. 

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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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 terminating repair of the butt joint at stringer 67 between fuselage 

stations 3850 and 5305. 

Refer to figures 2, 4, 5 and 9. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 67 between fuselage station 3850 and 5305 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. 

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. For the address 

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

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 42 Revision 2, May 08/13 

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) 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 4. 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 9. 

(5) 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. 

Refer to figure 9. 

(1) Manufacture the external repair strap from local source material according to figure 9. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 9. 

(3) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 9, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(4) On the indicated three (3) locations, if applicable, under the coupling angles install 

(an) additional shim(s). Manufacture the shim(s) from local source material according 

to figure 9. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(6) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(7) Remove the external repair strap and shims. Deburr 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 additional shim(s) on the indicated three (3) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 44 Revision 2, May 08/13 

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.

(3) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-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. 

(4) 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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. 

(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). 

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

working area is clean. 

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

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

documentation the ECR (ECR015861) as “Part 4C of SBF100-53-119” 

being performed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 46 Revision 2, May 08/13 

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.

Part 4D: The Temporary Repair of the Butt Joint at Stringer 67 between RH Fuselage 

Stations 3850 and 5305 (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). 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 9. 

Refer to figures 2 and 9. 

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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 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. 

(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, and keep the attachment parts. 

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

terminal blocks for easy installation, and 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 terminating repair of the butt joint at stringer 67 between fuselage 

stations 3850 and 5305. 

Refer to figures 2, 4, 5 and 9. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 48 Revision 2, May 08/13 

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.

(2) Clean the butt joint at stringer 67 between fuselage station 3850 and 5305 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. 

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (4). 

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 4. 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 49 

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. 

Refer to figure 9. 

(5) 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. 

Refer to figure 9. 

(1) Manufacture the external repair strap from local source material according to figure 9. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 9. 

(3) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 9, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) On the indicated three (3) locations, if applicable, under the coupling angles install 

(an) additional shim(s). Manufacture the shim(s) from local source material according 

to figure 9. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(6) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 50 Revision 2, May 08/13 

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.

Existing rivets F0N2-6323S6-xx must be replaced by rivets NAS1097DD6-xx or 

F0N2-6328S6-xx or by oversize hiloks HL111VF6-xx. 

(7) Remove the external repair strap and shims. Deburr 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 additional shim(s) on the indicated three (3) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 

(3) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-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. 

(4) 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. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 51 

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) 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. 

(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. 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 52 Revision 2, May 08/13 

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) 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. 

(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. 

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

working area is clean. 

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

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

documentation the ECR (ECR015861) as “Part 4D of SBF100-53-119” 

being performed. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 53 

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 4E: The Terminating Repair of the Butt Joint at Stringer 67 between RH Fuselage 

Stations 3850 and 5305 (Applicable to aircraft 11521, 11528, 11529, 11532, 11536 

thru 11541, 11543, 11545, 11547, 11549, 11551, 11553 thru 11583, 11585). 

NOTE: This Part has a different repair area when the repair/modification described in the 

 Service Bulletins SBF100-53-091 or SBF100-53-105 is accomplished, see Figure 9. 

Refer to figures 2 and 9. 

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

(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). 

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

stations 3850 and 5305. 

Refer to figures 2, 4, 5 and 9. 

(1) If applicable, remove all temporary repairs applied per SBF100-53-118. 

(2) Clean the butt joint at stringer 67 between fuselage station 3850 and 5305 on the 

outside. Remove the paint scheme, if necessary, to see the existing solid rivet heads 

and/or hiloks. Use: 

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

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

- AR lint-free cloth Fk05-044 

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

NOTE: If SBF100-53-091 or SBF100-53-105 is applied, this step is only applicable 

between fuselage stations 4464 - 5285 resp. 4850 – 5285. 

Refer to figure 4. 

(4) Close visually inspect for cracks in the butt strap on the inside at this joint. If a crack is 

found than the cracked part of the butt joint must be removed and an insert must be 

installed. If no crack is found continue with step (5). 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 54 Revision 2, May 08/13 

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.

(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.

Or use: 

- 1 corrosion resistant steel strip pn W21000-009. 

(b) Cut the butt strap, remove the cut out part and prepare it for sending. Send the 

cut out part to Fokker Services BV for investigation purposes. 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 rivet holes, treat all bare edges and install 

with sealing compound according to figure 4. 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. 

Or use: 

 - 1 insert pn W21000-019 

 - AR sealant pn PR1436GA1-2 Fk09-016 

 - AR sealant pn PR1436GB1-2 Fk09-017. 

Refer to figure 9. 

(5) Drill out the existing rivets and/or hiloks of the butt joint. Mark the proper fasteners at 

each location. 

C. Manufacture of an external repair strap. 

Refer to figure 9. 

(1) Manufacture the external repair strap from local source material according to figure 9. 

Use: 

- AR Sheet, aluminum pn F0N1-4311-1AM- * ~220 x 1500 mm. 

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

Or use: 

 - 1 external repair strap pn W21000-011 

Refer to figure 5. 

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

Refer to figure 9. 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 55 

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) Temporary install the external repair patch on the proper fuselage positions and mark 

the new rivet/hilok locations according to figure 9, use a pitch according to the 

existing rivet/hilok pattern 18 – 22 mm. 

(4) On the indicated three (3) locations, if applicable, under the coupling angles install 

(an) additional shim(s). Manufacture the shim(s) from local source material according 

to figure 9. Use: 

- AR Sheet, aluminum pn F0N1-4311-1A*- * ~20 x 20 mm. 

NOTE: * 0,2 - 1,6 mm thick 2024T3 Alclad aluminum sheet. 

Or use: 

 - AR Shim pn W21000-013 

 - AR Shim pn W21000-015 

 - AR Shim pn W21000-017 

(5) Drill the new rivet holes (refer to SRM 51-40-02), diameter 4,0 mm for NAS1097AD5-

xx (or F0N2-6325AD5-xx) rivets. (If the holes have become too large, they can be 

drilled to 4,8 mm and rivets NAS1097DD6-xx or F0N2-6328S6-xx must be installed). 

(6) Copy drill the existing fastener holes into the external repair patch. If MS20426AD4-xx 

rivets are found (or existing -4 bonding rivets), enlarge the holes to 4,0 mm for 

installation of NAS1097AD5-xx rivets. Replace existing MS20426AD5-xx rivets by 

NAS1097AD5-xx rivets. Replace existing MS20426AD6-xx rivets by NAS1097AD6-xx 

rivets. If hilok holes (refer to SRM 51-41-01) have become too large, they must be 

drilled to the first oversize or to the next size hilok. For a HL11VF6 the first oversize is 

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

-5 rivet holes have become too large they must be drilled to the next size, diameter 

4,8 mm, and NAS1097DD6-xx rivets must be installed. Existing rivets F0N2-6323S6-

xx must be replaced by rivets NAS1097DD6-xx or F0N2-6328S6-xx or by oversize 

hiloks HL111VF6-xx. 

(7) Remove the external repair strap and shims. Deburr 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 F0N18-9151S05 (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 additional shim(s) on the indicated three (3) locations, under the coupling 

angles. Use: 

- AR Sealant pn PR1436GA1-2 Fk09-016 

- AR Sealant pn PR1436GB1-2 Fk09-017 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 56 Revision 2, May 08/13 

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.

(3) Install the external repair strap 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 NAS1097AD5-xx or F0N2-6325AD5-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. 

(4) Restore paint scheme, refer to AMM, chapter 51-24-00. 

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 the original paint scheme according to AMM 51-21-00. 

F. Installation of the equipment which was removed at 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 34-11-720-815). 

(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). 

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

working area is clean. 

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

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 57 

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 terminating repair has been performed record in the aircraft 

 documentation the ECR (ECR015861) as “Part 4E of SBF100-53-119” 

 being performed. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 58 Revision 2, May 08/13 

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.

The Repair Area of the Butt Joint at Stringer 8 between Stations 3850 and 5305 

below the Passenger Door (Part 1). 

Figure 1 

Repair area 

Passenger 

Door 

Equipment bay 

hatch 127AB
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 59 

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. 

The Repair Area of the Butt Joint at Stringer 67 between Stations 3870 and 5305 

below the Forward Service/Emergency Door (Part 4A thru 4E). 

Figure 2 

Forward 

S/E door 

Equipment bay 

hatch 127AB

Repair area 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 60 Revision 2, May 08/13 

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.

The Repair Area of the Butt Joints at Stringer 37 and 42 between Stations 3870 and 5305 

(Parts 2 and 3). 

Figure 3 

 

Repair area 

Repair area 4850 

3780 3150 

2750 

2220 
Service Bulletin 

Fokker 70/100 

June 20/12 SBF100-53-119 

Revision 2, May 08/13 Page 61 

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. 

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. 

Cut out of the Cracked Part of the Butt Strap on the inside of the Joint 

and Installation of an Insert. 

Figure 4 

Insert to fill the 

removed cracked 

part of the butt strap 

Frame 

butt strap stringer 

Cut out the crack as indicated* 

Typical crack 

Or use pn W21000-019 
Service Bulletin 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 62 Revision 2, May 08/13 

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.

Round of the Edges of the Repair Strap and Aerodynamically Seal the Edges. 

Figure 5

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 
June 20/12 Revision 2, May 08/13 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 conta

written permission of Fokker Services B.V. 

- 

Terminating Repair of the Butt Joint at stringer 8. 

Figure 6. 

New rivets NAS1097AD5-xx, pitch 18 – 22 mm. 

In casis accrepair here, 

In case SBF100-53-091 is accomplished the repair strap must start here, up to sta. 5285 

Sta. 3870 

Sta. 4175 

Sta. 4610 

Sta. 4850

Instalcouplon the

External Repair strap, Material 2024T3 Thickness 1,4 mm = 0.055 inch. 

Or use pn W21000-011 

Or us
SBF100-53-119 Page 64 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 conta

written permission of Fokker Services B.V.

NOTE: Indicated existing rivets (BB/4 and BB/5) are for information only, replace by NAS1097A

Terminating Repair of the Butt Joint at stringer 37. 

Figure 7 (continued on next page) 

New rivets NAS1097AD5-

External Repair strap, Material 2024T3 Thickness 1,4 mm = 0.055 inch. 

Install new rivet in coupling angle using a shim.

Or use pn W21000-011 

Or use pn W21000-013/015/017 
June 20/12 Revision 2, May 08/13 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 conta

written permission of Fokker Services B.V. 

NOTE: Indicated existing rivets (BB/4 and BB/5) are for information only, replace by NAS1097A

Terminating Repair of the Butt Joint at stringer 37. 

Figure 7 (Continued)

External Repair straThickness 1,4 mm 

New rivets NAS1097AD5-xx, pitch 18 – 22 mm.

Remove coupling angles and shim(s), 

keep for re-installation. 

Or use pn W21000-0
SBF100-53-119 Page 66 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 conta

written permission of Fokker Services B.V.

NOTE: Indicated existing rivets (BB/4 and BB/5) are for information only, replace by NAS1097AD5-xx. 

Terminating Repair of the Butt Joint at stringer 42. 

Figure 8

New rivets NAS1097AD5-xx, pitch 18 – 22 mm. 

External Repair strap, Material 2024T3 Thickness 1,4 mm = 0.055 inch. 

New rivets NAS1097AD5-xx, pitch 18 – 22 mm. Or use pn W21000-011 
June 20/12 Revision 2, May 08/13 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 conta

written permission of Fokker Services B.V. 

Terminating Repair of the Butt Joint at stringer 67. 

Figure 9.

Install new rivet in coupling angle using a shim on these 3 locations.

In case SBF100-53-091 is accomplished the repair strap must start here, up to sta. 5285 

New rivets NAS1097AD5-xx, pitch 18 – 22 mm. 

External Repair strap, Material 2024T3 Thickness 1,4 mm = 0.055 inch. 

Or use pn W21000-011 

Or use pn W21000-013/015/017 
Service Bulletin Reporting Quality Form 

Fokker 70/100 

SBF100-53-119 June 20/12 

Page 68 Revision 2, May 08/13 

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.

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 6280 211 or Email: technicalservices@fokker.com