Service Bulletin 

 Fokker Services B.V. 

 Prepared Function / Note Date 

 jeffrey.keetlaer Oct 24/14 

 Colleague Check 

 doesburg-jd01812 Oct 24/14 

 Manager Final Approval 

 aroon.siriphant Nov 11/14 

 Office of Airworthiness Approval 

 visser-hv01800 Nov 12/14 

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Released date: (Mmm dd/yy) 

Nov 12/14 

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F100/70 Generic SB no.: 

SBF100-53-128 

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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EASA approved procedure for electronic sign-off

F100/70 Generic SB 

SBF100-53-128 

Revision - 

FUSELAGE - CENTER FUSELAGE

A One-Time Inspection of the Skin Connection Angle and Pressure Bulkhead at 

Station 14911 (12447), Stringer 67 (RH side) 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 1 of 14 

1. General Information

A. General 

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 

 

FUSELAGE

Fuselage Section 2 - A One-time Inspection of the Skin Connection Angle and 

 Pressure Bulkhead at Station 14911 (12447), Stringer 67 

 (RH side) 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 2 of 14 

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, if exceeding 

30.000 FC at the release date of this Service Bulletin. 

NOTE: Reportedly aircraft serial numbers 11359, 11367, 11397, 11471, 11499 

and 11502 have already been inspected in accordance with the 

requirements of SBF100-53-128 and can therefore be identified in the 

aircraft records as post SBF100-53-128. 

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 is required to 

investigate if cracks have occurred on the pressure bulkhead webplate and/or skin 

connection angle. 

(2) This Service Bulletin provides flyable crack limits and refers to applicable repair 

instructions per Service Bulletin SBF100-53-129, if necessary. 

D. Description 

(1) This Service Bulletin tells you how to: 

- Gain access to the aft side/outside of the RH pressure bulkhead webplate and 

skin connection angle. 

- Inspect the pressure bulkhead webplate and skin connection angle for cracks 

- Report finding (paragraph 4. E. (2)) 

- Repair, if applicable, in accordance with SBF100-53-129 

- Close up the work area. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 3 of 14 

E. Compliance 

(1) Recommended 

Fokker Services recommends the accomplishment of this Service Bulletin only for 

aircraft exceeding 30.000 FC at the release date of this Service Bulletin as follows: 

- Within 2000 FC from the release date of this Service Bulletin for aircraft with 

less than 40.000 FC at the release date of this Service Bulletin. 

- Within 750 FC from the release date of this Service Bulletin for aircraft with 

40.000 FC or more at the release date of this Service Bulletin. 

NOTE: It is expected that EASA will issue an Airworthiness Directive (AD) with 

respect to this subject with the same compliance terms. Refer to the 

EASA website for the publication of a (Proposed) Airworthiness Directive 

for comments. 

F. Approval 

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

EASA.21J.059. 

G. Manpower 

(1) Approximately 1 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 - - -

Modification

Inspection

Installation - - -

Testing - - -

Total 1.0 1.0

1.0

Instructions Men Man-hours

1 1.0

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

panel and (if required) to remove the wing to fuselage fairing. 

(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”). 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 14 

H. Weight and Balance 

(1) Weight change: None. 

Index change: None. 

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. 

K. References 

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

Fokker 100 Service Bulletin (SB): 

 - SBF100-53-129 (to be issued). 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 5 of 14 

L. Publications Affected 

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

(a) Maintenance Documentation

Not affected. 

(b) Maintenance Programs

Not affected. 

(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. 

M. Interchangeability or Intermixability of Parts 

(1) Not applicable. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 6 of 14 

3. Material Information

A. Material – Price and Availability 

(1) Not applicable. 

B. Material Required 

(1) Not applicable. 

C. Tooling – Price and Availability 

(1) Not applicable. 

D. Tooling Required 

(1) Not applicable. 

 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 14 

4. Accomplishment Instructions

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

B. Put the access platform 1 m (3 ft) in position near the access panel 178BR. 

C. Open access panel 178BR 

D. If necessary, clean the inspection area and the items to be inspected. 

Refer to figures 1, 2 and 3 

E. Perform a detailed inspection of the pressure bulkhead web plate and skin connection 

angle at station 14911(station 12447 for F28 Mark 0070), adjacent to the stringers 

66/67 from the aft side. 

(1) Use an inspection lamp and magnifying glass to inspect the pressure 

 bulkhead web plate and skin connection angle adjacent to the stringers 66/67 for 

 signs of cracks and/or damage, see figures 1, 2 and 3. 

(2) Send an inspection report to the Technical Services Department of Fokker 

 Services B.V. via the knowledge center in the Q&A database on 

 MyFokkerfleet.com or technicalservices@fokker.com. Also report to Fokker 

 Services B.V. when NIL findings are found during the inspection. 

 This report must include: 

(a) The aircraft serial number, 

(b) The total number of flight cycles and flight hours of the aircraft, 

(c) A sketch or photo’s to show the location of the crack(s) and/or damaged 

part(s), if applicable, 

(d) The length of each crack, if applicable. 

NOTE: Every inspection result must be reported to Fokker Services B.V. even 

 when no cracks are found. 

F. In case cracks are found during the inspection described in the previous steps, the 

following flyable crack limits are applicable: 

(1) In case the skin connection angle (longeron) is cracked, but the pressure bulkhead 

webplate is not cracked, a repair must be performed per SBF100-53-129 at the 

next convenient opportunity but within 4000 FC, whichever comes first. 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 14 

(2) In case a crack is found in the pressure bulkhead webplate (with or without a crack 

in the skin connection angle (longeron)) which does not reach the vertical stiffener 

(BL800R), the crack must be stop-drilled and re-inspected after 2000 FC. If no 

crack growth beyond the stop drill hole is found after 2000 FC, it must be repaired 

per SBF100-53-129 at the next C-check or within 4000 FC after crack detection, 

whichever comes first. 

(3) In case the crack has reached the vertical stiffener (BL800R) or if crack growth 

beyond the stop drill hole is found after 2000FC (ref. step (2) above), a repair must 

be performed in accordance with SBF100-53-129 before further flight or contact 

Fokker Services B.V. for an analysis and possible repair postponement based on 

the crack finding. 

(a) In case such a request is sent to Fokker Services, it is necessary to remove 

the forward wing-to-fuselage body fairing in accordance with AMM 53-63-00-

000-824-A. Inspect the skin connection angle from the external side of the 

aircraft behind the forward wing-to-fuselage body fairing attachment profile. 

Also inspect the fuselage skin and skin strip for cracks emanating from below 

the attachment profile just below stringer 67. See figures 4 and 5 for an 

indication of the crack location. 

G. Job close-up 

(1) Close access panel 178BR and install fairing panel 168AR (if removed) according 

AMM task 53-63-00-400-824-A. 

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

area is clean. 
Status: 

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RESTRIC

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with the prior written

class: 

CTED 

reserved by Fokker Ser

closure to third parties of

n permission of Fokker Se

rvices B.V. (The Netherla

f this document or any pa

ervices B.V. 

Figure 1 – 

Revision: 

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ands). This document ha

art thereof, or the use of 

Overall vie

F100/70 G

SBF100-5

as been supplied by Fok

any information containe

ew of inspec

R

N

Generic SB no

3-128 

kker Services B.V. to its

ed therein for purposes o

ction locatio

Fok

Released date

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.: 

s customers on a confide

other than explicitly allow

on (RH side)

Service

kker Serv

e: (Mmm dd/yy) 

ential basis subject to th

wed by the aforesaid agre

)

e Bulletin

ices B.V.

he provisions of an agree

eement, is not permitted 

Page 9 of 14

ement. 

except 

4 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 10 of 14 

Figure 2 – Overview of crack location (RH side) 

Crack location in 

pressure bulkhead 

webplate and skin 

connection angle. 

View in DOF 

Existing fairing 

frame repair per 

SRM 53-80-02 

repair number 7 

Webplate of 

Frame 14911 (12447) 

Stringer 67 

Stringer 66 

Center wing 

lower skin 

Vertical 

stiffener

BL800R
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 11 of 14 

Figure 3 – Close up of crack location (RH side) 

Pressure bulkhead 

webplate crack 

Skin connection 

angle crack 

View in DOF The webplate on the rear side 

of frame 14911 (12477) 

Vertical 

stiffener 

BL800R 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 12 of 14 

 

Figure 4 – Overview of skin connection angle crack location (RH Side) 

Close-up view 

figure 5 

View Z4 

Stringer 66 

Stringer 67 

Crack 
Service Bulletin 

Fokker Services B.V. 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 14 

 

Figure 5 – Close-up of skin connection angle crack location (RH Side) 

View Z4
Service Bulletin Quality Reporting Form 

Fokker Services B.V. 

 

Status: 

Released 

Revision: 

- 

Released date: (Mmm dd/yy) 

Nov 12/14 

Security class: 

RESTRICTED 

F100/70 Generic SB no.: 

SBF100-53-128 

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 14 of 14 

SB Title: A One-Time Inspection of the Skin Connection Angle and 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