Service Bulletin 

Fokker 70/100 

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

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

May 15/12 SBF100-53-120 

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 One-Time Inspection 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) Not applicable. 

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. Refer to figure 1. 

(2) These cracks were found during maintenance in the area. Investigation revealed that 

a repetitive inspection in this area is necessary with a threshold of 30 000 flight cycles 

(FC). Because many aircraft have already exceeded this amount of flight cycles the 

one-time inspection as presented in this Service Bulletin is necessary. 

(3) The repetitive inspection will be added to the Airworthiness Limitations Section (ALS) 

document as task 534106-00-05 within a year after the date of issue of this Service 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 May 15/12 

Page 2 

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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.

Bulletin. This inspection is a high frequency eddy current inspection on the forward 

side of the Rear Pressure Bulkhead. 

(4) The necessary one-time inspection can be done by performing a close visual detailed 

inspection on the rear side of the Rear Pressure Bulkhead or by performing an NDT 

inspection on the forward side of the Rear Pressure Bulkhead. The choice between 

close visual detailed or NDT inspection can be done on the operator’s discretion. 

Refer to figure 2 for a flow schematic giving an overview of the information given in 

this step and the following 2 steps. 

(5) In case the close visual detailed inspection on the rear side of the Rear Pressure 

Bulkhead as described in Part 1 of this Service Bulletin is chosen and cracks are 

found, the area needs to be repaired permanently before further flight. 

In case no cracks are found during the visual inspection on the rear side the NDT 

inspection on the forward side of the Rear Pressure Bulkhead as described in Part 2 

of this Service Bulletin may be postponed and needs to be performed within 1 year 

after the date of the visual inspection. The postponed NDT inspection in that case 

qualifies as the first accomplishment of ALS task 534106-00-05 without possibility for 

repair postponement. 

(6) In case the NDT inspection on the forward side of the Rear Pressure Bulkhead as 

described in Part 2 of this Service Bulletin is chosen and cracks are found, it must 

subsequently be verified visually on the rear side whether the crack is already through 

the thickness of the Rear Pressure Bulkhead Web. If the crack is indeed through the 

thickness, the area needs to be repaired permanently before further flight. 

In case the NDT inspection and the subsequent visual inspection on the rear side 

reveal cracks which are not through the thickness of the Rear Pressure Bulkhead, the 

area needs to be repaired permanently within 1 year after the date of the inspection. 

In case the NDT inspection reveals no cracks the NDT inspection qualifies as the first 

accomplishment of ALS task 534106-00-05. 

(7) For the expected interval of the repetitive inspection of ALS task 534106-00-05 refer 

to All Operators Message AOF100.176 (released together with this Service Bulletin). 

(8) The permanent repair for the cracks at Rear Pressure Bulkhead Beam XI is 

introduced with Service Bulletin SBF100-53-121. The permanent repair removes the 

need for the repetitive inspection in accordance with ALS task 534106-00-05. 

The permanent repair can also be performed (without crack findings after this onetime inspection) as precautionary measure to cancel the repetitive inspection. 

D. Description 

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

Part 1: The close visual detailed inspection at the rear side of the Rear Pressure 

 Bulkhead just below beam XI between BL425L and BL425R. 

This Part tells you how to: 

- Gain access to the inspection area at the rear side of the RPBH 

- Perform the close visual detailed inspection at the rear side of the RPBH 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-120 

Page 3 

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

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

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

Part 2: The NDT inspection at the forward side of the Rear Pressure Bulkhead just 

 below beam XI between BL425L and BL425R. 

This Part tells you how to: 

- Gain access to the inspection area at the forward side of the Rear Pressure 

Bulkhead (RPBH) by removing interior parts and insulation and to the inspection 

area at the rear side of the RPBH 

- Calibrate the high frequency eddy current (HFEC) inspection instruments 

- Perform the HFEC inspection at the forward side of the RPBH 

- When cracks are found perform a close visual detailed inspection at the rear side 

of the RPBH 

- Reinstall the insulation and interior parts (in case no permanent repair is 

necessary or no cracks are found). 

E. Compliance 

(1) Recommended. 

Fokker Services recommends the accomplishment of this Service Bulletin before the 

aircraft exceeds 30 000 flight cycles or within 1 year after the date of issue of this 

Service Bulletin, whichever comes last. 

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 nr. 

EASA.21J.059. 

G. Manpower 

(1) Approximately 1,0 man-hour is necessary to do Part 1 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 - - - 

Modification 

Inspection 1 1,0 1,0 

Installation - - - 

Testing - - - 

Total 1,0 1,0 

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

and/or the sealant to cure. 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 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.

(2) Approximately 5,0 man-hours are necessary to do Part 2 of this Service Bulletin on 

one aircraft. 

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

Instructions Men Man-hours Elapsed time 

(hours) 

Removal 1 2,0 2,0 

Modification 

Inspection 1 1,0 1,0 

Installation 1 2,0 2,0 

Testing - - - 

Total 5,0 5,0 

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

and/or the sealant to cure. 

(3) 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: None 

Index change: None. 

I. Electrical Load Data 

(1) Not changed. 

J. Software Accomplishment Summary 

(1) Not applicable. 

K. References 

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

Fokker 70/100 Airworthiness Limitations Section (ALS) 

Fokker 70/100 All Operators Message: 

 - AOF100.176 

Fokker 70/100 Structural Repair Manual (SRM) 

Fokker 70/100 Illustrated Parts Catalog (IPC) 

Fokker 70/100 Maintenance Planning Document (MPD) 

Fokker 70/100 Non-Destructive Testing Manual (NDTM) 

Fokker Consumable Material List (CML) 

Fokker 70/100 Service Bulletin (SB): 

 - SBF100-53-121 

Fokker reference numbers: 

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

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

Fokker 70/100 

May 15/12 SBF100-53-120 

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. 

 - 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

Not affected. 

(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. 

(d) Operational Documentation

Not affected. 

(2) Report to Fokker Services that this SB has been carried out on the applicable aircraft. 

In addition, if cracks are found, submit the Feedback Form of figure 6 on page 16. 

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 

SBF100-53-120 May 15/12 

Page 6 

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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.

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 this Service Bulletin on 1 aircraft, are 

not part of the mod kit. 

New Part Number Qty Keyword Info Old Part 

Number

Instructions/

Disposition

- AR* Cloth, Lint free Fk05-044** - Local source 

MEK AR* Solvent, Methyl Ethyl Ketone Fk11-003** - Local source 

F0N1-5956-50 AR* Tape, Adhesive Fk05-203** - Local source 

NOTES: * Use as much as necessary 

** Refer to the CML for material numbers. 

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

(a) Not applicable. 

C. Tooling – Price and Availability 

(1) The following equipment was used to develop this procedure: 

Item Specification Part Number Reference Make

(1) Phase Analysis EC Tester MIZ21A - Zetec 

(2) Pencil probe, 50-500 kHz 

shielded, angled 

SPT905-50B - Servicing 

Europe NDT 

(3) Interconnection cable 

for HF probe 

CZ21TF6 - Servicing 

Europe NDT 

(4) Calibration block, std. 

Aluminum 

S0027 NDTM Part 1 

51-00-06 

Fokker 

Services BV 

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

table above and the sensitivity requirement as given in the Accomplishment 

Instructions step 3.B. are met. Calibration procedure may vary when using 

other equipment. 

D. Drawings Required 

(1) Not applicable. 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-120 

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. 

3. Accomplishment Instructions

General: 

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

select CML. 

- For information about eddy current inspection methods, refer to the NDTM Part 1 51-00-06. 

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

THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY 

INSTRUCTIONS. 

PART 1: The close visual detailed inspection at the rear side of the Rear Pressure Bulkhead 

just below beam XI between BL425L and BL425R. 

A. Preparation 

Refer to figures 1 and 3. 

(1) Gain access to the inspection area on the rear side of the Rear Pressure Bulkhead 

(RPBH) just below beam XI between BL425L and BL425R. 

(a) Open access panel 315 AB (APU compartment door). 

(2) Clean the inspection area on the rear side of the RPBH with a lint-free cloth 

moistened with cleaning agent. Use: 

- AR lint-free cloth - Fk05-044 

- AR solvent, Methyl Ethyl Ketone MEK Fk11-003.

B. Inspect the rear side of the RPBH web below beam XI between BL425 LH and RH close 

visually. 

Refer to figures 1, 3 and 4 (Figures 3 and 4 show the forward side of RPBH, close visual 

inspection is to be done at the rear side). 

(1) Inspect close visually for cracks in the area at the rear side of the RPBH directly 

below beam XI. 

NOTE: A crack type 2 will initially not be visible from the rear side. This is not a 

 concern as long as the crack is not detectable through contamination of the 

 area like in figure 1. 

C. Inspection results 

(1) If a crack is found, make a permanent repair according Service Bulletin 

SBF100-53-121 before further flight and report the crack findings back to Fokker 

Services using the Feedback Form of figure 6 on page 16. 

(2) If no crack is found, the NDT inspection on the forward side of the Rear Pressure 

Bulkhead as described in Part 2 of this Service Bulletin may be postponed and needs 

to be performed within 1 year after the date of the visual inspection. 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 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.

PART 2: The NDT inspection at the forward side of the Rear Pressure Bulkhead just below 

beam XI between BL425L and BL425R. 

A. Preparation 

Refer to figure 3. 

(1) Gain access to the forward side of the RPBH between BL425L and BL425R. 

(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. Discard the tape. 

(2) Clean the inspection area on the forward side of the RPBH just below beam XI 

between BL425L and BL425R with a lint-free cloth moistened with cleaning agent and 

remove sealant and/or excessive or flaked paint. Use: 

- AR lint-free cloth - Fk05-044 

- AR solvent, Methyl Ethyl Ketone MEK Fk11-003.

(3) Make sure the paint thickness at the inspection area is less than 300 μm. Refer to 

NDTM Part 1 51-00-06, paragraph 6.C. 

B. Calibrate the instruments. 

(1) Initial instrument settings for High Frequency inspection. 

NOTE: Operate the instrument according to the manufacturer’s instructions. 

(a) FREQ (kHz) 300 

(b) PRB DIFF-MD 

(c) PRB GAIN As Required 

(d) V SCL 0.1 

(e) H SCL 0.3 

(f) PHASE (degrees) As Required 

(g) FILTER OFF 

(h) MODE X-Y 

(i) ALARM ON 

(2) Adjust the alarm box and the balance point as indicated in figure 5. 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-120 

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. 

(3) Put the probe on a slot free area of the calibration block and balance the instrument. 

NOTE: When the inspection area is painted and the paint thickness is less than 

300 μm, use a non-conductive foil on the calibration block with the same 

thickness as the paint layer. Refer to NDTM Part 1 51-00-06, paragraph 

6.C. 

(4) Adjust the phase angle to get a horizontal lift-off line, refer to figure 5. 

(5) Slide the probe across the 0,5 mm slot of the calibration block and adjust the 

sensitivity until the tip of the slot signature is within the alarm box (90 degree phase 

difference with lift-off), refer to figure 5. 

C. Inspect the forward side of the Rear Pressure Bulkhead web below beam XI between 

BL425L and BL425R using high frequency eddy current method. 

(1) Put the probe on a crack free area and balance the instrument. 

(2) Scan the Rear Pressure Bulkhead web below beam XI according figure 4. 

(3) Mark the locations where the signal passes the threshold and looks like the slot signal 

in figure 5. 

D. NDT inspection results 

(1) Compare the suspected signals with the signals from the calibration block. A possible 

crack is indicated when the signal passes the alarm box threshold and the signal 

looks the same as the slot signal from the calibration block. 

(2) Remove the paint and primer locally and inspect the possible crack(s) visually, using 

a strong light source and a magnifying glass. 

(3) When no crack is found, continue with step H, Job Close up. 

(4) When a crack is found: 

(a) When a crack is found during the NDT inspection which was not postponed as 

described in paragraph 1.C.(5). “Reason”, continue with step E to make a close 

visual inspection on the rear side of the Rear Pressure Bulkhead to determine 

whether the cracks are through the thickness of the web. 

(b) When a crack is found during the NDT inspection which was postponed (for a 

maximum period of a year) after the initial visual inspection of Part 1, make a 

permanent repair according Service Bulletin SBF100-53-121 before further flight 

and report the crack findings back to Fokker Services using the Feedback Form 

of figure 6 on page 16. 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 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.

E. Preparation for the close visual inspection on the rear side of the Rear Pressure 

Bulkhead. 

(1) Gain access to the inspection area on the rear side of the Rear Pressure Bulkhead 

(RPBH) just below beam XI between BL425L and BL425R. 

(a) Open access panel 315 AB (APU compartment door). 

(2) Clean the inspection area on the rear side of the RPBH with a lint-free cloth 

moistened with cleaning agent. Use: 

- AR lint-free cloth - Fk05-044 

- AR solvent, Methyl Ethyl Ketone MEK Fk11-003.

F. Inspect the rear side of the RPBH web below beam XI between BL425 LH and RH close 

visually. 

Refer to figures 1, 3 and 4 (Figures 3 and 4 show the forward side of the RPBH, close 

visual inspection is to be done at the rear side). 

(1) Inspect close visually for cracks in the area at the rear side of the RPBH directly 

below beam XI. 

NOTE: A crack type 2 will initially not be visible from the rear side. This is not a 

 concern as long as the crack is not detectable through contamination of the 

 area like in figure 1. 

G. Visual inspection results 

(1) If a crack is found to be through the thickness of the web, make a permanent repair of 

the area according Service Bulletin SBF100-53-121 before further flight. 

(2) If no crack is found to be through the thickness of the web, the permanent repair of 

the cracks found on the forward side of the Rear Pressure Bulkhead during the NDT 

inspection may be postponed and must be performed within 1 year after the date of 

the NDT inspection. 

(3) Report the crack findings of step G. back to Fokker Services using the Feedback 

Form of figure 6 on page 16. 

H. Job close up (in case no cracks are found during the NDT inspection or the permanent 

repair of cracks is postponed) 

(1) When necessary restore the aircraft paint scheme and sealant at the inspection area. 

Refer to the Structural Repair Manual (SRM) chapter 51-24-01. 

(2) 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.

(3) Install the aft cabin attendant panel removed in step A.(1)(b). Refer to IPC chapter 25-

21-04 figures 03 thru 03F. 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-120 

Page 11 

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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. 

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

(5) Remove all equipment, tools and materials from the work area and make sure the 

area is clean. 

(6) In case no cracks are found during the NDT inspection, note the accomplishment of 

this Service Bulletin as the first accomplishment of Airworthiness Limitations Section 

task 534106-00-05 in the aircraft records. 

 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 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.

 

View on rear side of Rear Pressure Bulkhead 

Crack through thickness of web just below beam XI 

Figure 1 

BEAM XI 

BL425R 
Service Bulletin 

Fokker 70/100 

May 15/12 SBF100-53-120 

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. 

Flow schematic for inspection possibilities and postponements 

Figure 2 

 

Selection of initial inspection 

Visual on rear side RPBH NDT on front side RPBH 

No crack Crack Crack No crack 

NDT within one year Visual on rear side RPBH 

No further action. SB 

accomplishment can be 

recorded as first 

accomplishment of ALI. 

No crack Crack Crack No crack 

No further action. SB 

accomplishment can be 

recorded as first 

accomplishment of ALI. 

Repair before further flight Repair within one year 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 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.

General View of the Inspection Area 

Looking from Cabin Area against DOF 

Figure 3 

BL 1050R BL 1050L 

BL 425R BL 425L

STRIP 

(TYP) 

 INSPECTION AREA 

AT THE BEAM FLANGE LOWER EDGE AND 

POCKET EDGE OF BEAM XI 

XI XI 

XIII 

XII 

X 

IX 

VIII 

VII 

VI 

V 

IV 
May 1

Copyright A

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except with 

15/12 

All rights reserved by Fok

on or disclosure to third 

the prior written permiss

TYPICAL CRAC

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Crack type 1 

Crack type 2 

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agreement. 

ot permitted 
Service Bulletin 

Fokker 70/100 

SBF100-53-120 May 15/12 

Page 16 

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.

Crack Findings Feedback Form 

• Please indicate cracks in the figure below with: 

- length, 

- type (refer to figure 4 for crack types) 

- and whether they are completely through the thickness of the web. 

• Send the Feedback Form back to Fokker Services - Technical Services: 

technicalservices@fokker.com 

Operator 

Aircraft sn 

Flight Cycles 

Date 

View looking on forward side of Rear Pressure Bulkhead 

Crack Findings Feedback Form 

Figure 6 

BL 425R BL 425L 
Service Bulletin Reporting Quality Form 

Fokker 70/100 

May 15/12 SBF100-53-120 

Page 17 

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

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

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

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 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