Service Bulletin 

 Fokker Services B.V. 

 Prepared Function / Note Date 

 jeffrey.keetlaer Feb 11/15 

 Colleague Check 

 doesburg-jd01812 Jan 28/15 

 Manager Final Approval 

 benthem-eb01865 Feb 13/15 

 Office of Airworthiness Approval 

 visser-hv01800 Feb 16/15 

Status: 

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F100/70 Generic SB no.: 

SBF100-53-129 

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 

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EASA approved procedure for electronic sign-off

F100/70 Generic SB 

SBF100-53-129 

Revision - 

FUSELAGE - CENTER FUSELAGE

The Repair of the Skin Connection Angle and/or Pressure Bulkhead at Station 14911 

(12447), Stringer 67 (RH side) 
Service Bulletin 

Fokker Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

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SBF100-53-129 

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Page 1 of 21 

1. General Information

A. General 

(1) Not applicable. 

B. Table of Contents 

• Section 1: General Information 

• Section 2: Planning Information 

• Section 3: Material Information 

• Section 4: Accomplishment Instructions 

• Service Bulletin Quality Reporting Form 

and attachments (if applicable): 

• List of drawings/parts lists 

• Parts List Local source (PLL) 

• Parts List Supply (PLS) 

• Required drawings 

C. Service Bulletin Revision History 

Revision Date (Mmm dd/yy) Reason for Revision 

- Refer to footer First Release 

 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

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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 

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Page 2 of 21 

2. Planning Information

A. Effectivity 

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

11258, 11272 thru 11286, 11290, 11291, 11293, 11295, 11296, 11300, 11303, 

11306 thru 11308, 11310 thru 11316, 11318 and 11320 thru 11585. 

NOTE: Aircraft serial numbers 11471 and 11502 have been repaired in 

 accordance with the instructions of CAS-38062, respectively CAS-41986, 

 and can be identified in the aircraft records as to comply with the repair 

 requirements of this Service Bulletin (SBF100-53-129).

B. Concurrent Requirements 

(1) Not applicable. 

C. Reason 

(1) Service experience has shown that cracking can occur in the pressure bulkhead 

webplate and skin connection angle on the RH side at station 14911 (station 

12447 for F28 Mark 0070), stringer 67 of aircraft fuselage section 2 before the 

existing threshold per ALS task 533016-00-03 (F28 Mark 0100) or 533016-01-03 

(F28 Mark 0070). Therefore an additional one-time inspection has been introduced 

with SBF100-53-128. If cracks have occurred on the pressure bulkhead webplate 

and/or skin connection angle these can be repaired in accordance with this Service 

Bulletin (SBF100-53-129). 

D. Description 

(1) This Service Bulletin tells you how to: 

- Gain access to the aft side, forward side and outside of the pressure bulkhead 

webplate and skin connection angle 

- Remove the necessary parts 

- Repair the found cracks 

- Reinstall the removed parts 

- Close up the work area. 
Service Bulletin 

Fokker Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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 

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Page 3 of 21 

E. Compliance 

(1) Optional 

Fokker Services recommends the accomplishment of the Service Bulletin in 

accordance with the instructions of SBF100-53-128. 

NOTE: Repair per this Service Bulletin SBF100-53-129 can also be incorporated 

as preventative modification. This will, however, not affect the ALS 

inspection interval. 

F. Approval 

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

EASA.21J.059. 

G. Manpower 

(1) Approximately 46 man-hours are necessary to do this Service Bulletin on one 

aircraft. 

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

Elapsed time

(hours)

Removal 1 6.0 6.0

Modification

Inspection

Installation 2 24.0 12.0

Testing - - -

Total 46.0 26.0

8.0

Instructions Men Man-hours

2 16.0

 

NOTE: This estimate does not include the time necessary for the paint to dry 

and/or the sealant to cure. 

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

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

Introduction, section 2.C., “Manpower”). 

H. Weight and Balance 

(1) Weight change: To be determined by weighing of the modkit (in kg). 

Index change: (-0.02421) x Weight change (in kg). 

Example: 3,00 kg weight change has an index change of -0.07263 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 4 of 21 

I. Electrical Load Data 

(1) Direct Current (DC) Loads: 

(a) Not changed. 

(2) Alternating Current (AC) Loads: 

(a) Not changed. 

J. Software Accomplishment Summary 

(1) Not applicable. 

 
Service Bulletin 

Fokker Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

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Page 5 of 21 

K. References 

Fokker 70/100 Airworthiness Limitation Section (ALS) 

Fokker 70/100 Structural Repair Manual (SRM) 

Fokker Consumable Material List (CML) 

Fokker Standards & Process Manual (SPM) 

Fokker 70/100 Service Bulletin (SB): 

- SBF100-53-128 

Fokker internal reference: 

 - ECR 16144. 

L. Publications Affected 

(1) This Service Bulletin affects the publications listed below: 

(a) Maintenance Documentation

- Fokker 70 Structural Repair Manual (SRM) - chapter 53-21 

- chapter 57-11 

- Fokker 100 Structural Repair Manual (SRM) - chapter 53-31

- chapter 57-11 

(b) Maintenance Programs

- Fokker 70/100 Maintenance Planning Document (MPD). 

(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 

- Fokker 70/100 Airworthiness Limitations Section (ALS): 

• Fuel Tank Safety (FTS) - X 

• Damage Tolerance of Fatigue Critical Structure (FCS) X - 

• Certification Maintenance Requirements (CMR) - X 

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

incorporated in the MRB, the Airworthiness Limitations 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 Service Bulletin has been carried out on the 

applicable aircraft. 

(3) You have the possibility to send your SB feedback to Fokker Services per “Service 

Bulletin Reporting Quality Form”. This form is located on the last Service Bulletin 

page. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

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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. 

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Page 6 of 21 

(4) For incorporation of this Service Bulletin Appendix 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 Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 7 of 21 

3. Material Information

A. Material – Price and Availability 

(1) You can order the necessary parts as mod kit SB10053129-XU-A. 

(2) You can contact your Fokker Services Customer Support Manager for the price 

and lead-time of this mod kit. 

B. Material Required 

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

and are not part of the mod kit, are described in attachment Part List Local (PLL). 

Material List Description Aircraft Effectivity

SB10053129-XU-A Parts List Local (PLL) All 

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

are described in attachment Part List Supply (PLS) 

Material List Description Aircraft Effectivity

SB10053129-XU-A Parts List Supply (PLS) All 

C. Tooling – Price and Availability 

(1) Not applicable. 

D. Tooling Required 

(1) Not applicable. 

 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 8 of 21 

4. Accomplishment Instructions

General: 

- In general, use (A)MM chapter 20, standard practices-airframe, as guide line for the 

aircraft modification. 

- Loosen the cable clamps where necessary. 

- Remove and discard the cable ties where necessary. 

- Use cable ties and lacing tape where necessary. 

- For CML material number references refer to “MyFokkerFleet.com > Documentation and 

select CML” and/or AMM chapter 20-30-00. 

- For Standards and Process Manual (SPM) references refer to “MyFokkerFleet.com > 

Documentation and select SPM”. 

- For drilling procedures refer to SRM chapter 51-22-01. 

- For the application of sealing compound refer to AMM chapter 20-32-00 and 

chapter 51-23-00. 

- For information on removal/installation of rivets refer to SRM chapter 51-40-02 and/or 

TH6.3002 (solid rivets) and SRM chapter 51-40-04 and/or SPM TH6.3106 (blind rivets). 

- For the installation of Hi-Lok bolts refer to SRM chapter 51-41-01 and/or SPM TH6.3403. 

- For the installation of bolts and screws refer to SRM chapter 51-43-01 and/or SPM 

TH6.3400. 

- For the application of Primer & Paint refer to the AMM chapter 51-21-00 and/or SPM 

TH6.7370. 

- For the application of Alodine refer to AMM chapter 51-22-00 and SRM chapter 51-24-01. 

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

THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY 

INSTRUCTIONS. 

A. Clear the area round the lower wing to fuselage section on the RH side. 

B. Open access panel 178BR. 

C. Remove the nose fairing assembly in accordance with AMM 53-63-00-000-824-A. 

D. Remove the rear wall panels in the forward cargo compartment; refer to 

AMM 25-51-00-000-824-A. 

Refer to figures 1, 2 and 3 

E. If necessary remove the bleed air duct in accordance with AMM 30-11-09-000-814-A to 

gain clearance at the aft side of the repair area. 

F. Disconnect the electrical wiring connector P1695B (zone 165) and remove the cable 

clamp and bracket. 
Service Bulletin 

Fokker Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 9 of 21 

G. Remove the corresponding electrical wiring receptacle J1695A from the pressure 

bulkhead at station 14911 (12447) by removing the bolts, nuts and washers. 

Keep/discard: 

- 4 Bolts NAS600-5P Discard 

- 4 Washers AN960KD4L Keep 

- 4 Nuts MS21042L04. Keep 

H. Drill out the applicable fasteners and remove the stringer couplings. See figure 1. 

I. In case of a new crack, or one that has grown since repair postponement per SBF100-

53-128 step 4.F.(2), which has not yet been stop drilled, stop drill action must be 

accomplished now. For allowable crack length and stop drill requirements refer to 

SBF100-53-128. 

Refer to figures 5 and 6 

J. For installation of the external repair strip (in step Y. (1)), it is necessary to cut the 

fairing angle profile on which the nose fairing assembly is installed to the fuselage. 

(1) Drill out the applicable rivets, remove and keep the fairing profile connection 

angles. 

(2) Cut the angle next to the skin connection strip, see figure 6. Remove sharp edges 

and corners. 

K. Clean the area which requires to be repaired. Use: 

- AR Cleaning cloth Fk05-044 

- AR Methyl Ethyl Ketone Fk11-003. 

Refer to figures 1 and 2 

L. Prepare the filler plate for installation. 

(1) Trim the filler plate as required with corresponding structure. Use: 

- 1 Filler plate p/n W31100-007. 

M. Prepare the pressure bulkhead repair plate for installation. 

(1) Trim the internal repair plate as required with corresponding structure. Use: 

- 1 Pressure bulkhead repair plate p/n W31100-005. 

N. Copy drill the existing solid fastener holes in the filler plate and pressure bulkhead 

repair plate. 

O. Determine the new solid rivet hole positions on the filler plate and pressure bulkhead 

repair plate in accordance with SRM 51-40-02 and drill the new fastener holes in 

accordance with SRM 51-22-01 to accommodate MS20470AD5 rivets. Figures 1 and 2 

show the rivet pattern, the precise pattern has to be determined in-situ. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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 

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Page 10 of 21 

Refer to figures 2 and 3 

P. Prepare the first repair angle for installation. 

(1) Trim the repair angle to the proper length and shape as shown in figures 2 and 3. 

Use: 

- 1 First repair angle p/n W31100-001. 

Q. Prepare the second repair angle for installation. 

(1) Trim the repair angle to the proper length and shape as shown in figures 2 and 3. 

Use: 

- 1 Second repair angle p/n W31100-003. 

R. Copy drill the existing fastener holes from the vertical flange of the wing connection 

angle and pressure bulkhead into the repair parts in accordance with SRM 51-41-01 to 

accommodate first oversize Hi-Loks bolts p/n HL110VF6. 

S. Copy drill the existing fastener holes from the fuselage skin into the repair angles in 

accordance with SRM 51-41-01 to accommodate Hi-Loks bolts p/n HL10VF6 and 

p/n HL11VF6. 

T. Prepare the stringer connection angles and shims for installation at stringer 67 and 68. 

(1) Copy drill the fastener holes from the fuselage skin and stringers into the stringer 

connection angles and shims. Use: 

- 2 Connection angle p/n W31100-009 

- 2 Connection angle p/n W31100-011 

- 2 Shims p/n W31100-013. 

Refer to figures 3 and 6 

U. Prepare the external repair strip for installation on the skin coupling. 

(1) Trim the repair strip to the proper length and shape as shown in figure 3. Use: 

- 1 External repair strip p/n W31100-015. 

(2) Copy drill the two aft existing fastener rows, corresponding with the fuselage skin 

and skin connection angle, into the repair part in accordance with SRM 51-41-01 to 

accommodate Hi-Loks bolts p/n HL10VF6 and one Hi-Lok bolt p/n HL11VF6. 

NOTE: The two holes in the corner of the skin connection angle which attaches 

 the end of the fairing profile angle are left as is i.e. not to be copy drilled 

 and not to be plugged. Refer to figure 6. 

(3) Countersink one hole in the external repair strip to accommodate the Hi-Lok bolt 

p/n HL11VF6, which is located underneath the fairing profile angle. 
Service Bulletin 

Fokker Services B.V. 

Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

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SBF100-53-129 

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 

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Page 11 of 21 

(4) Copy drill the forward two fastener rows from the fuselage skin coupling into the 

external repair strip in accordance with SRM 51-22-01 and SRM 51-41-01 to 

accommodate solid fasteners MS20470AD5, Hi-Loks bolts p/n HL10VF6 and one 

Hi-Lok bolt p/n HL11VF6. 

(5) Countersink the second hole in the external repair strip to accommodate the 

Hi-Lok bolt p/n HL11VF6. 

V. Locally manufacture a repair angle for the nose fairing connection angle, which has 

been cut off in step 4. J. Use the same flange dimensions as the original angle. Use: 

- AR Sheet p/n F0N1-4311-1AM2024T3 (TH5.322) 1,4 mm. 

(1) Copy drill the holes into the repair angle except for the two outer fastener holes 

which are located near the corner of the skin connection angle. These two 

fasteners are omitted. 

W. Provide surface treatment to all bare material in accordance with SRM 51-24-01. Use: 

- AR Conversion coating Alodine 1201 Fk13-003D 

- AR Primer Aerodur S15/60 Fk07-008. 

Refer to figure 2 

X. Install the repair parts on the pressure bulkhead, see figure 2 

(1) Position and wet install the filler plate (p/n W31100-007) pressure bulkhead repair 

plate (p/n W31100-005), first repair angle (p/n W31100-001) and second repair 

angle (p/n W31100-003) at station 14911 (12447). Use: 

- 22 Hi-Lok collars p/n HL79-6 

- 2 First oversize Hi-Lok bolts p/n HL110VF6-5 

- 6 First oversize Hi-Lok bolts p/n HL110VF6-7 

- 7 First oversize Hi-Lok bolts p/n HL110VF6-8 

- 7 First oversize Hi-Lok bolts p/n HL110VF6-9 

- AR Solid rivets p/n MS20470AD5 

- AR Sealant p/n PR1782B 

- 1 First repair angle p/n W31100-001 

- 1 Second repair angle p/n W31100-003 

- 1 Pressure bulkhead repair 

plate 

p/n W31100-005 

- 1 Filler plate p/n W31100-007 

- AR Washer p/n NAS1149D0332K. 

NOTE: In case a Hi-Lok bolt is too long, use one or two washers underneath the 

 collar per SRM 51-41-01 paragraph 7. 
Service Bulletin 

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Status: 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

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with the prior written permission of Fokker Services B.V. 

Page 12 of 21 

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

Y. Install the repair parts on the fuselage skin coupling, see figures 3 and 4 

(1) Position and wet install the external repair strip (p/n W31100-015), stringer 

connection angles (p/n W31100-009/-011), shims (p/n W31100-013 and p/n 

W31100-017 if required) and the locally fabricated fairing angle manufactured in 

step V. Use conical washers to fill the existing countersinking. Use: 

- 2 Conical washers p/n F0N18-9151R06 

- 32 Hi-Lok collars p/n HL70-6 

- 4 Hi-Lok bolts p/n HL10VF6-5 

- 8 Hi-Lok bolts p/n HL10VF6-6 

- 7 Hi-Lok bolts p/n HL10VF6-7 

- 11 Hi-Lok bolts p/n HL10VF6-8 

- 2 Hi-Lok bolts p/n HL11VF6-7 

- AR Solid rivets p/n MS20470AD5 

- AR Sealant p/n PR1782B 

- 2 Stringer connection angles p/n W31100-009 

- 2 Stringer connection angles p/n W31100-011 

- 2 Shims p/n W31100-013 

- 1 External repair strip p/n W31100-015 

- 2 Shims (if required) p/n W31100-017. 

(1) Reinstall the fairing profile connection angles which are removed and kept in step 

J.(1), see figures 5, 6 and 7. Use: 

- AR Solid rivets MS20470AD4. 

Refer to Aircraft Maintenance Manual (AMM) 

Z. Apply paint primer and a topcoat to the repair parts in accordance with AMM 51-21-00. 

Use: 

- AR Primer Aerodur S15/60 Fk07-008 

- AR Topcoat Aerodur C21/100 Fk07-027. 

AA. Install the electrical wiring receptacle J1695A from the pressure bulkhead at 

station 14911 (12447). Use the nuts and washers which you kept in step G and new 

bolts. Use: 

- 4 Bolts p/n NAS600-6P. 

BB. Connect the electrical wiring connector P1695B (zone 165) and reinstall the cable 

clamp and bracket. 

(1) Perform the following after installation tests to ensure that disconnected electrical 

systems work properly, refer to AMM 28-21-01, 30-11-01, 30-11-02, 30-11-06 and 

30-11-08. 

CC. If removed in step G. install the bleed air duct in accordance with AMM 

30-11-09-400-814-A to restore the area in original condition. 
Service Bulletin 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

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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. 

Page 13 of 21 

DD. Job close-up 

(1) Install the rear wall panels in the forward cargo compartment; refer to 

AMM 25-51-00-400-824-A. 

(2) Install the nose fairing assembly in accordance with AMM 53-63-00-400-824-A 

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

area is clean. 

(4) Close access panel 178BR. 

 
Service Bulletin 

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Revision: 

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Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

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F100/70 Generic SB no.: 

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Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained therein for purposes other than explicitly allowed by the aforesaid agreement, is not permitted except 

with the prior written permission of Fokker Services B.V. 

Page 14 of 21 

NOTE: The shown picture is of an aircraft with integral center wing tank. 

 

Station 

14911 (F100) 

12447 (F70)

External repair strip 

p/n W31100-015 Second repair angle 

p/n W31100-003 

First repair angle 

p/n W31100-001 

Filler plate 

p/n W31100-007 

Pressure bulkhead 

repair plate 

p/n W31100-005 

Internal Repair Overview 

Figure 1 

Crack 

Remove and reinstall 

Z-profile 
Service Bulletin 

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Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 15 of 21 

 

Internal View of Repair on Pressure Bulkhead 

Figure 2 

MS20470AD5 rivets (new positions) 

MS20470AD5 rivets (existing positions), if 

necessary due to hole tolerance use next 

size MS20470DD6 rivets. 

HL110VF6 Hi-Loks (existing positions) 

Second repair angle 

p/n W31100-003 

Remove and reinstall 

Z-profile 

External repair strip 

p/n W31100-015 

First repair angle 

p/n W31100-001 

Filler plate 

p/n W31100-007 

Pressure bulkhead 

repair plate 

p/n W31100-005 

Crack 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 16 of 21 

 

External View of Repair on outer skin 

Figure 3

HL11VF6 Hi-Lok bolts (existing positions) 

STGR 66 

STGR 67 

STGR 68 

STGR 69 

MS20470AD5 rivets (existing positions), if 

necessary due to hole tolerance use next 

size MS20470DD6 rivets. 

HL10VF6 Hi-Lok bolts (existing positions) 

External repair strip 

p/n W31100-015 

Stringer connection angle 

p/n W31100-009

Second repair angle 

p/n W31100-003 

First repair angle 

p/n W31100-001 

Shim 

p/n W31100-017 

Shim 

p/n W31100-013 

Stringer connection angle

p/n W31100-011 

View Z4 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 17 of 21 

 

Stringer Connection Angle Cross Section View 

Figure 4 

View Z4

MS20470AD5 rivets (existing positions), if 

necessary due to hole tolerance use next 

size MS20470DD6 rivets. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 18 of 21 

 

Detail see figure 6 

External View of Nose Fairing Angle 

Figure 5 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 19 of 21 

 

Skin connection 

angle cut line 

Remove this part of the 

skin connection angle 

Install repair angle 

External View of Nose Fairing Angle 

Figure 6 

Remove / reinstall 

connection angle 

Remove / reinstall 

connection angle 

Rivets not to 

be re-installed 

Drill out rivets of anchor nut angle 

(connection with skin angle) 

View A 

B 

B 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 20 of 21 

Cross section B-B 

Repaired situation 

Anchor nut angle 

Repair angle 

External repair strip 

p/n W31100-015 

Skin 

Cross section B-B 

Original situation 

Anchor nut angle 

Original skin angle 

Skin 

Rivet 

p/n MS20470AD4 

Cross Section View of Nose Fairing Angle 

Figure 7 
Service Bulletin Quality Reporting Form 

Fokker Services B.V. 

 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Feb 16/15 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-129 

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. 

Page 21 of 21 

SB Title: The Repair of the Skin Connection Angle and/or Pressure Bulkhead at Station 14911 (12447), 

Stringer 67 (RH side)

Use this Service Bulletin Quality Reporting Form to tell us your perception of the quality of the Service 

Bulletin. The reported data that you provide to us will be used to analyze areas of difficulties and to take 

corrective actions to further improve the quality of our Service Bulletins. We thank you for the time you 

have taken in completing this form. 

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

Chapters * 1 2 3 4 

a) Quality rating of this SB (overall) □ □ □ □

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

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

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

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

f) Quality rating of the Illustrations or Drawings (if applicable) □ □ □ □

g) Timely delivery of the SB □ □ □ □

If you have had difficulties with one of the chapters of this Service Bulletin and/or one of your rating(s) is 

lower than 3, please give a short description of the issue. 

Comments:

Operator: Date:

Name / Title: 

Please return this form to: Fokker Services B.V. 

Engineering, Quality Department 

P.O. Box 1357 

2130 EL Hoofddorp 

The Netherlands 

Fax: +31 (0) 88 6280111 or E-mail: technicalservices@fokker.com
 

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. 

 

Status:

Released

Revision:

-

Released date:

Feb 16/15

Security class:

RESTRICTED

F100/70 Generic SB no:

SBF100-53-129

Service Bulletin

Fokker Services B.V.

Page 1 of 1

List of Drawings / Parts Lists

Drawing Sheet Issue Title

SB10053129-XU-A PLL A Parts List Local (PLL) for SB10053129-XU-A

SB10053129-XU-A PLS A Parts List Supply (PLS) for SB10053129-XU-A
Parts List Supply (PLS) 

All rights reserved. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any 

information contained therein for purpose other than provided for by this document, is not permitted without prior and 

express written permission of Fokker Services B.V. EASA approved procedure for electronic sign-off 

Keyword : MATLISTDescription :Program : F28

Rel. to EB/SB : SBF100-53-12Rel. to EB/SB Issue : - Part Release Date : 13-02-2015

AssemblyPart Number Rev Seq Keyword DescriptionSB10053129-XU-A A 5 MATLISTAssembly StructureQty UoM Part Number Keyword Info Old Part Number 2 ea F0N18-9151R06 WASHER - - 4 ea HL10VF6-5 BOLT F0N2-1196-6-5 - 8 ea HL10VF6-6 BOLT F0N2-1196-6-6 - 7 ea HL10VF6-7 BOLT F0N2-1196-6-7 - 11 ea HL10VF6-8 BOLT F0N2-1196-6-8 - 2 ea HL110VF6-5 BOLT F0N18-1221-6-5 - 6 ea HL110VF6-7 BOLT F0N18-1221-6-7 - 7 ea HL110VF6-8 BOLT F0N18-1221-6-8 - 7 ea HL110VF6-9 BOLT F0N18-1221-6-9 - 2 ea HL11VF6-7 BOLT F0N2-1197-6-7 - 32 ea HL70-6 COLLAR F0N2-1181-6 - 22 ea HL79-6 COLLAR F0N18-2230-6 - 4 ea NAS600-6P SCREW - - 1 ea W31100-001 ANGLE - - 1 ea W31100-003 ANGLE - - 1 ea W31100-005 PLATE - - 1 ea W31100-007 PLATE - - 2 ea W31100-009 ANGLE - - 2 ea W31100-011 ANGLE - - 2 ea W31100-013 SHIM - - 1 ea W31100-015 STRIP - - 2 ea W31100-017 SHIM - - 
Parts List Local (PLL) 

All rights reserved. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any 

information contained therein for purpose other than provided for by this document, is not permitted without prior and 

express written permission of Fokker Services B.V. EASA approved procedure for electronic sign-off 

Keyword : MATLISTDescription :Program : F28

Rel. to EB/SB : SBF100-53-12Rel. to EB/SB Issue : - Part Release Date : 13-02-2015

AssemblyPart Number Rev Seq Keyword DescriptionSB10053129-XU-A A 5 MATLISTAssembly StructureQty UoM Part Number Keyword Info Old Part Number AR 5-701-1 PRIMER - - AR AL0DINE1201 COATING - - AR C21-100-064095 ENAMEL - - AR MS20470AD4 RIVET - - AR MS20470AD5 RIVET - - AR NAS1149D0332K WASHER - - AR PR1782B1 SEALANT - - Full Part NumbersPart Number Full Part NumberAL0DINE1201 ALODINE1201