Service Bulletin 

Fokker 70/100 

Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17

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

Page 18 19 20 21 

Revision - - - - 

May 15/12 SBF100-53-121 

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

Section 4 - The Permanent Repair/Modification of the Rear Pressure Bulkhead below Beam 

XI between BL425L & BL425R. 

1. Planning Information

A. Effectivity 

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

11244 thru 11256, 11258 thru 11283, 11285, 11286, 11288 thru 11316, 

11318 thru 11341 and 11343 thru 11585. 

(2) F28 Mark 0100 aircraft serial numbers 11257, 11284, 11287, 11317 and 11342 are 

excluded from the effectivity as their Rear Pressure Bulkheads are already inspected 

& repaired at this location. Dedicated repair/modification procedures are issued for 

these aircraft with references CAS-18947-HOP4DC, CAS-29765-YMY1L3, CAS30605-WZQ6KX and CAS-31697-YKG14K. These repaired aircraft are considered as 

being post this Service Bulletin and post SBF100-53-121. 

B. Concurrent Requirements 

(1) Before, or at the same time as, you do this SB, you must do: 

SBF100-53-120 - FUSELAGE - Section 4 - The One-Time Inspection of the Rear 

 Pressure Bulkhead below Beam XI between BL425L & BL425R. 

C. Reason 

(1) Until now on three aircraft cracks were reported in the Rear Pressure Bulkhead 

(RPBH) Web just below the Horizontal Beam XI between BL425L & BL425R, the 

center web bay below the pressure relief valves. 

(2) A new repetitive inspection will be applicable per ALS Task 534106-00-05, with a 

threshold of 30.000 FC. Services Bulletin SBF100-53-120 has been issued to 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 2 

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.

introduce a one-time inspection for those aircraft which have already exceeded or are 

very close to this threshold. 

(3) If a crack (or cracks) or crack indications are found during accomplishment of Bulletin 

SBF100-53-120 or ALS Task 534106-00-05, Service Bulletin SBF100-53-121 tells 

you how to make the permanent repair/modification. 

(4) After accomplishment of Part 1 or Part 2, ALS task 534106-00-05 is no longer 

applicable. 

(5) This Service Bulletin can also be accomplished as a modification before or during 

accomplishment of SBF100-53-120 or the ALS inspections to avoid (further) repetitive 

ALS inspection as mentioned above. 

D. Description 

(1) This Service Bulletin is divided into two parts as follows; 

Part 1: The Permanent Repair/Modification of the Rear Pressure Bulkhead 

below Beam XI between BL425 LH & RH (applicable to aircraft in Pre 

SBF100-53-095 RECAES configuration). 

This part tells you how to: 

- Get access to the working area 

- Remove the cracked part of the rear pressure bulkhead, if applicable 

- Install a filler for the removed cracked part, if applicable 

- Install a repair patch on the forward side of the rear pressure bulkhead 

- Close up the working area. 

Part 2: The Permanent Repair/Modification of the Rear Pressure Bulkhead 

below Beam XI between BL425 LH & RH (applicable to aircraft in Post 

SBF100-53-095 RECAES configuration). 

This part tells you how to: 

- Get access to the working area 

- Remove the cracked part of the rear pressure bulkhead, if applicable 

- Install a filler for the removed cracked part, if applicable 

- Install a repair patch on the forward side of the rear pressure bulkhead 

- Close up the working area. 

E. Compliance 

(1) Optional. 

F. Approval 

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

EASA.21J.059. 

 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

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. 

G. Manpower 

(1) Approximately 14 man-hours are necessary to do Part 1 or Part 2 of this Service 

Bulletin on one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 3,0 3,0 

Modification 

Inspection 1 3,0 3,0 

Installation 1 10,0 10,0 

Testing - - - 

Total 16,0 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) Part 1:

(a) Weight change: + 0,63 kg (1.38 lb) 

Index change: Mark 0100: 0.048 

 Mark 0070: 0.035 

(2) Part 2:

(a) Weight change: + 0,62 kg (1.36 lb) 

Index change: Mark 0100: 0.047 

 Mark 0070: 0.034 

I. Electrical Load Data 

(1) Not changed. 

J. Software Accomplishment Summary 

(1) Not applicable. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 4 

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. 

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

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

K. References 

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

Fokker 70/100 Airworthiness Limitations Section (ALS) 

Fokker 70/100 Structural Repair Manual (SRM) 

Fokker 70/100 Illustrated Parts Catalog (IPC) 

Fokker Consumable Material List (CML) 

Fokker 70/100 Service Bulletin (SB): 

 - SBF100-53-095 

 - SBF100-53-120 

Fokker internal reference: 

 - ECR 015827 

Fokker reference numbers; 

- CAS-18947-HOP4DC (applicable for aircraft 11284) 

- CAS-29765-YMY1L3 (applicable for aircraft 11257) 

- CAS-30605-WZQ6KX (applicable for aircraft 11287) 

- CAS-31697-YKG14K (applicable for aircrafts 11317 and 11342) 

L. Publications Affected 

(1) This SB affects the publications listed below: 

(a) Maintenance Documentation

- Fokker 70/100 Aircraft Maintenance Manual (AMM) - chapter 53-41 

(b) Maintenance Programs

- Fokker 70/100 Airworthiness Limitations Section (ALS) 

- 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 

- Fuel Tank Safety (FTS) - X 

- Damage Tolerance of Fatigue Critical Structure X - 

- Certification Maintenance Requirements (CMR) - X 

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

incorporated in the MRB, the Airworthiness Limitations 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. 

 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

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. 

(d) Operational Documentation

- Fokker 70/100 Weight and Balance Manual (WBM). 

(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 

SBF100-53-121 May 15/12 

Page 6 

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. 

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

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

2. Material Information

A. Material – Price and Availability 

(1) The materials are local source items. 

B. Material Required 

(1) These parts, which are necessary to complete Part 1 or Part 2 of this Service Bulletin 

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

New Part Number Qty Keyword Info Old Part 

Number

Instructions/

Disposition

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

Methyl Ethyl 

Ketone (MEK) 

AR* Cleaning solvent Fk11-003**/*** - Local source 

Corrosion resistant 

steel strip 

~20 x 

60 mm 

(or stainless steel) t = ~ 0,4 mm - Local source 

FRF01401-82035 ~1100 x 

150mm 

Sheet aluminum 2024T3 Alclad 

t=1,6 mm 

- Local source 

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

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

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

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

HL12VF6-6 AR* Protruding Hi-lok bolts F0N2-1204-6-6 - Local source 

HL110VF6-6 AR* Protruding 1st 

oversize Hi-lok bolts 

F0N18-1221-6-

6 

- Local source 

HL410VF6-6 AR* Protruding 2nd 

oversize Hi-lok bolts 

F0N18-1321-6-

6 

 Local source 

HL86PB6 AR* Collar for Hi-lok bolt F0N2-1207-6 - Local source 

HL79-6 AR* Collar for 1st oversize 

Hi-lok bolts 

F0N18-2230-6 Local source 

HL84-6 AR* Collar for 2nd oversize 

Hi-lok bolts 

F0N18-2330-6 Local source 

MS20470AD5 AR* Protruding rivet - - Local source 

MS20470AD6 AR* Protruding rivet - - Local source 

MS20470DD5 AR* Protruding rivet - - Local source 

MS20470DD6 AR* Protruding rivet - - Local source 

NOTES: * Use as much as necessary 

** Refer to the CML for material numbers. 

 *** Or equivalent 

 ****for PR1436GA1-2 refer to TH5.951/1 for alternative sealant, for 

PR1436GB1-2 refer to TH5.951/2 for alternative sealant. 

 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

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. 

C. Tooling – Price and Availability 

(1) Not applicable. 

D. Drawings Required 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 8 

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” and 

select CML. 

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

“MyFokkerFleet.com/Documentation” and select SPM. 

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

- For the application of Sealing compound PR1436G-A (Fk09-016) 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 blind rivets, refer to the SRM chapters 51-40-03, 51-40-04 

and 51-40-05. 

- For the removal/installation of Hi-lok bolts, refer to SRM, chapter 51-41-01 

- For the application of Primer and Paint, refer to the AMM, chapter 51-21-00. 

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

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

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

THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY 

INSTRUCTIONS. 

Part 1: The Permanent Repair/Modification of the Rear Pressure Bulkhead below Beam XI 

between BL425 LH & RH (applicable to aircraft in Pre SBF100-53-095 RECAES 

configuration). 

A. Preparation 

(1) Gain access to the rear side of the rear pressure bulkhead. 

(a) Open access door 315AB (refer to AMM 06-30-03-ZZ1-810-A) and get access to 

the rear side of the rear pressure bulkhead. 

(b) Make sure the APU is switched off and cannot be switched on (refer to AMM 

chapter 49-10). 

Refer to figure 1 

(c) Clean the repair/modification and remove sealant and/or excessive or flaked 

paint. Use: 

- AR Lint-free cloth (Fk05-044) 

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

(2) Gain access to the forward side of the rear pressure bulkhead. 

(a) Remove the rear cabin attendant seat(s) (refer to AMM chapter 25-21). 

(b) Remove the aft cabin attendant panel (refer to IPC chapter 25-21-04 figures 03 

thru 03F). 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

Page 9 

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. 

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

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

(c) Move the insulation blankets away from the area between BL425L and BL425R. 

Open the BL0 joint between the LH and RH pressure bulkhead insulation 

blankets by removing the tape. 

Refer to figure 1 

(d) Clean the repair/modification area and remove sealant and/or excessive or flaked 

paint. Use: 

- AR lint-free cloth (Fk05-044) 

- AR methyl ethyl ketone (or equivalent) (Fk11-003) 

B. Perform repair/modification on the forward side of the rear pressure bulkhead 

Refer to figures 1 and 3 

(1) Remove and keep the two strips (refer to SRM 53-65-02-05/-05A item 310): 

- 2 strips pn D35015-061 keep 

Refer to figure 1 

(2) Inspect for cracks in rear pressure bulkhead, inspect according to SBF100-53-120. If 

a crack is found the cracked part must be cut out and an insert must be installed. If no 

crack is found continue with step (4). 

(3) Remove the crack, if applicable. 

(a) Remove the applicable rivets in beam XI. 

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

steel) strip between the beam XI and the aft pressure bulkhead, at the location of 

the crack cut out, to avoid cutting in the beam. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 60 mm. t = ~ 0,4 mm.

(c) Cut out the crack in the aft pressure bulkhead, use a radius of at least 6mm. 

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

(e) Manufacture an insert of material 2024T3, thickness 1,6 mm. Size as necessary 

to keep a gap of 1,0 mm between the filler and the cut out edge. Treat all bare 

aluminum parts with alodine and primer. Use: 

- AR aluminum sheet 2024T3 Alclad t=1,6 mm - 

- AR coating pn Alodine 1201 (Fk13-003D) 

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

Refer to figure 1, 2 and 3 

(4) Remove the existing rivets and Hi-Loks in the aft pressure bulkhead at the location 

where the repair patch will be installed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 10 

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) Manufacture a repair patch material 2024T3 with a thickness of 1,6mm. 

- AR aluminum sheet 2024T3 Alclad t=1,6 mm. 

(6) Temporary install the repair patch (on the forward side of the aft pressure bulkhead) 

with the insert when applicable, and mark the (new) rivet/Hi-lok locations according to 

figure 1, use a rivet pitch between 18-22mm. 

Refer to figure 2 and 3 

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

MS20470AD5 rivets. If the holes have become too large, they must be drilled to 4,8 

mm for next size rivets MS20470AD6. 

(8) Copy drill the existing four Hi-Lok holes into the repair patch for HL12VF6 (diameter 

MIN 4,737mm-MAX 4,813mm ). If Hi-Lok holes have become too large, they must be 

drilled to the first oversize (hole diameter MIN 5,067mm-MAX 5,143mm). For 

HL12VF6 use first oversize Hi-lok HL110VF6. 

(9) Copy drill the existing MS20470DD6 solid rivet holes, diameter 4,8mm. If existing -6 

rivet holes have become too large they must be drilled to the next size, diameter 6,4 

mm, and MS20470AD8 must be installed. 

(10) Remove the repair patch and insert when applicable. Deburr all holes and treat all 

bare aluminum parts with Alodine and primer. Use: 

- AR coating pn Alodine 1201 (Fk13-003D) 

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

Refer to figure 1, 2 and 3 

(11) Install the repair patch and insert when applicable on the forward side of the rear 

pressure bulkhead. Treat all bare aluminum parts with alodine and primer and install 

with sealing compound. Install the strips removed in step (1) at the original location on 

top of the repair patch. Use: 

- 2 strips pn D35015-061 kept 

- 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) 

- AR protruding Hi-lok bolts pn HL12VF6-6 F0N2-1204-6-6 

- AR protruding 1st oversize 

Hi-lok bolts 

pn HL110VF6-6 F0N18-1221-6-6 

- AR protruding rivet pn MS20470AD5 - 

- AR protruding rivet pn MS20470AD6 - 

- AR protruding rivet pn MS20470DD5 - 

- AR protruding rivet pn MS20470DD6 - 

- AR collars pn HL86PB6 F0N2-1207-6 

- AR collars for 1st oversize Hi-lok 

bolts 

pn HL79-6 F0N18-2230-6 

 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

Page 11 

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. 

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

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

C. Re-install the equipment which was removed at step A. 

(1) Put the pressure bulkhead insulation blankets back into position and close the joint 

in-between with tape (refer to AMM 25-28-00-400-814-A). Use: 

- AR Adhesive tape F0N1-5956-50 (Fk05-203) 

(2) Install the aft cabin attendant panel. Refer to IPC chapter 25-21-04 figures 03 thru 

03F. 

(3) Install the rear cabin attendant seat(s) (refer to AMM chapter 25-21). 

D. Job close up. 

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

working area is clean. 

(2) Record in the aircraft documentation that the permanent repair according 

ECR 015827 (Part 1 of SBF100-53-121) has been performed. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 12 

Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. 

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

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

Part 2: The Permanent Repair/Modification of the Rear Pressure Bulkhead below Beam XI 

between BL425 LH & RH (applicable to aircraft in Post SBF100-53-095 RECAES 

configuration). 

A. Preparation 

(1) Gain access to the rear side of the rear pressure bulkhead. 

(a) Open access door 315AB (refer to AMM 06-30-03-ZZ1-810-A) and get access to 

the rear side of the rear pressure bulkhead. 

(b) Make sure the APU is switched off and cannot be switched on (refer to AMM 49-

10) 

Refer to figure 4 

(c) Clean the repair/modification area and remove sealant and/or excessive or flaked 

paint. Use: 

- AR Lint-free cloth (Fk05-044) 

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

(2) Gain access to the forward side of the rear pressure bulkhead. 

(a) Remove the rear cabin attendant seat(s) (refer to AMM chapter 25-21). 

(b) Remove the aft cabin attendant panel (refer to IPC chapter 25-21-04 figures 03 

thru 03F). 

(c) Move the insulation blankets away from the area between BL425L and BL425R. 

Open the BL0 joint between the LH and RH pressure bulkhead insulation 

blankets by removing the tape. 

 Refer to figure 4 

(d) Clean the repair/modification area and remove sealant and/or excessive or flaked 

paint. Use: 

- AR lint-free cloth (Fk05-044) 

- AR methyl ethyl ketone (or equivalent) (Fk11-003) 

B. Perform repair/modification on the forward side of the rear pressure bulkhead 

Refer to figures 4 and 6 

(1) Remove and keep the two strips (refer to SRM 53-65-02-05/-05A item 310); 

- 2 strips pn D35015-061 keep 

Refer to figure 4 

(2) Inspect for cracks in rear pressure bulkhead, inspect according to SBF100-53-120. If 

a crack is found the cracked part must be cut out and an insert must be installed. If no 

crack is found continue with step (4). 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-121 

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) Remove the crack, if applicable 

(a) Remove the applicable rivets in beam XI. 

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

steel) strip between the beam XI and the aft pressure bulkhead, at the location of 

the crack cut out, to avoid cutting in the beam. Use: 

- AR corrosion resistant steel 

(or stainless steel) strip 

~20 x 60 mm. t = ~ 0,4 mm.

(c) Cut out the crack in the aft pressure bulkhead, use a radius of at least 6mm. 

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

(e) Manufacture an insert of material 2024T3, thickness 1,6mm. Size as necessary 

to keep a gap of 1,0 mm between the filler and the cut out edge. Treat all bare 

aluminum parts with alodine and primer. Use: 

- AR aluminum sheet 2024T3 Alclad t=1,6 mm - 

- AR coating pn Alodine 1201 (Fk13-003D) 

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

Refer to figure 4, 5 and 6 

(4) Remove the existing rivets and Hi-Loks in the aft pressure bulkhead at the location 

where the repair patch will be installed. 

(5) Manufacture a repair patch material 2024T3 with a thickness of 1,6mm. 

- AR aluminum sheet 2024T3 Alclad t=1,6 mm. 

(6) Temporary install the repair patch (on the forward side of the aft pressure bulkhead) 

with the insert when applicable, and mark the (new) rivet/Hi-lok locations according to 

figure 1, use a rivet pitch between 18-22mm. 

Refer to figure 5 and 6 

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

MS20470AD5 rivets. If the holes have become too large, they must be drilled to 4,8 

mm for next size rivets MS20470AD6. 

(8) Copy drill the existing four Hi-Lok holes into the repair patch for HL110VF6 (diameter 

MIN 5,067mm-MAX 5,143mm). If Hi-Lok holes have become too large, they must be 

drilled to the second oversize (hole diameter MIN 5,461mm-MAX 5,537mm). For 

HL110VF6 use second oversize Hi-lok HL410VF6. 

(9) Copy drill the existing MS20470DD6 solid rivet holes, diameter 4,8mm. If existing -6 

rivet holes have become too large they must be drilled to the next size, diameter 6,4 

mm, and MS20470AD8 must be installed. 
Service Bulletin 

Fokker 70/100 

SBF100-53-121 May 15/12 

Page 14 

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) Remove the repair patch and insert when applicable. Deburr all holes and treat all 

bare aluminum parts with Alodine and primer. Use: 

- AR coating pn Alodine 1201 (Fk13-003D) 

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

Refer to figure 4, 5 and 6 

(11) Install the repair patch and insert when applicable on the forward side of the rear 

pressure bulkhead. Treat all bare aluminum parts with alodine and primer and install 

with sealing compound. Install the strips removed in step (1) at the original location on 

top of the repair patch. Use: 

- 2 strips pn D35015-061 kept 

- 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) 

- AR protruding 1st oversize Hi-lok 

bolts 

pn HL110VF6-6 F0N18-1221-6-

6 

- AR protruding 2nd oversize Hi-lok 

bolts 

pn HL410VF6-6 F0N18-1321-6-

6 

- AR protruding rivet pn MS20470AD5 - 

- AR protruding rivet pn MS20470AD6 - 

- AR protruding rivet pn MS20470DD5 - 

- AR protruding rivet pn MS20470DD6 - 

- AR Collars for 1st oversize Hi-lok 

bolts 

pn HL79-6 F0N18-2230-6 

- AR Collars for 2nd oversize Hi-lok 

bolts 

pn HL84-6 F0N18-2330-6 

C. Re-install the equipment which was removed at step A. 

(1) Put the pressure bulkhead insulation blankets back into position and close the joint 

in-between with tape (refer to AMM 25-28-00-400-814-A). Use: 

- AR Adhesive tape F0N1-5956-50 (Fk05-203) 

(1) Install the aft cabin attendant panel. Refer to IPC chapter 25-21-04 figures 03 thru 

03F. 

(2) Install the rear cabin attendant seat(s) (refer to AMM chapter 25-21). 

D. Job close up. 

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

working area is clean. 

(2) Record in the aircraft documentation that the permanent repair according 

ECR 015827 (Part 2 of SBF100-53-121) has been performed. 
May 15/12 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information conta

written permission of Fokker Services B.V. 

Rear Pressure Bulkhead repair patch layout Pre SBF100-53-095 RECAES configurat

Figure 1 
SBF100-5

Page 16 Copyright All rights reswritten permission of F

53-121 

served by Fokker Service

Fokker Services B.V.

s B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential b

Rear Pres

AA

asis subject to the provis

ssure Bulkh

AA

sions of an agreement. R

head repair;

F

eproduction or disclosur

 detail I, Pre

Figure 2 

e to third parties of this d

e SBF100-5

ocument or any part the

3-095 REC

reof, or the use of any in

AES config

formation conta

uration 

Se

When Web P
May 15/12 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information conta

written permission of Fokker Services B.V. 

Rear Pressure Bulkhead repair; detail II, Pre SBF100-53-095 RECAES configuratio

Figure 3 
SBF100-53-121 Page 18 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.

Rear Pressure Bulkhead repair patch layout Post SBF100-53-095 RECAES configurat

Figure 4 
May 15/12 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential basis subject to the provisions of an agreement. Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information conta

written permission of Fokker Services B.V. 

Rear Pressure Bulkhead repair; detail III, Post SBF100-53-095 RECAES configuratio

Figure 5 

A (see figure 2)A 
SBF100-5

Page 20 Copyright All rights reswritten permission of F

53-121 

erved by Fokker Service

Fokker Services B.V.

s B.V. (The Netherlands). This document has been supplied by Fokker Services B.V. to its customers on a confidential b

Aft pressu

asis subject to the provis

ure bulkhea

ions of an agreement. R

d repair; de

F

eproduction or disclosur

tail IV, Pos

Figure 6 

re to third parties of this d

st SBF100-5

ocument or any part the

3-095 REC

reof, or the use of any in

AES config

formation conta

uration 
Service Bulletin Reporting Quality Form 

Fokker 70/100 

May 15/12 SBF100-53-115 

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. 

Service Bulletin Reporting Quality Form 

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

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

corrective actions to further improve the quality of our Service Bulletins. 

We thank you for the time you have taken in completing this form.

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

Chapters * 1 2 3 4 

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

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

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

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

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

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

g) Timely delivery of the SB □ □ □ □

If you have had difficulties with one of the chapters of this Service Bulletin and/or one of your 

rating(s) is (are) lower than 3, please give a short description of the issue. 

Comments:

Operator: Date:

Name / Title: 

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

Technical Services, Quality Department 

P.O. Box 1357 

2130 EL Hoofddorp 

The Netherlands 

Fax: +31 (0) 88 6280111 or Email : technicalservices@fokker.com