## 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 there in 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 forthese 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 ex ceeded 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

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 there in 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 repair ed 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 there in 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 there in 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 there in 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

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 there in 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 there in 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 there in 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 μ m. 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 there in 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 μ m, 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 si gnals 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 there in 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

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 there in 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 there in 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 there in 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 No crack 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 No crack 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 there in 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

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## 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 there in 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 there in 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 improv e 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