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Service Bulletin Fokker Services B.V.
Prepared Function / Note Date jeffrey.keetlaer Feb 11/15 Colleague Check doesburg-jd01812 Jan 28/15 Manager Final Approval benthem-eb01865 Feb 13/15 Office of Airworthiness Approval visser-hv01800 Feb 16/15
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129
Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
EASA approved procedure for electronic sign-off
F100/70 Generic SB
SBF100-53-129
Revision -
FUSELAGE - CENTER FUSELAGE
The Repair of the Skin Connection Angle and/or Pressure Bulkhead at Station 14911 (12447), Stringer 67 (RH side)
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 1 of 21
1. General Information A. General
(1) Not applicable.
B. Table of Contents
• Section 1: General Information
• Section 2: Planning Information
• Section 3: Material Information
• Section 4: Accomplishment Instructions
• Service Bulletin Quality Reporting Form and attachments (if applicable):
• List of drawings/parts lists
• Parts List Local source (PLL)
• Parts List Supply (PLS)
• Required drawings C. Service Bulletin Revision History
Revision Date (Mmm dd/yy) Reason for Revision
- Refer to footer First Release
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 2 of 21
2. Planning Information A. Effectivity
(1) F28 Mark 0070/0100 aircraft serial numbers:
11258, 11272 thru 11286, 11290, 11291, 11293, 11295, 11296, 11300, 11303, 11306 thru 11308, 11310 thru 11316, 11318 and 11320 thru 11585.
NOTE: Aircraft serial numbers 11471 and 11502 have been repaired in accordance with the instructions of CAS-38062, respectively CAS-41986, and can be identified in the aircraft records as to comply with the repair requirements of this Service Bulletin (SBF100-53-129).
B. Concurrent Requirements
(1) Not applicable.
C. Reason
(1) Service experience has shown that cracking can occur in the pressure bulkhead webplate and skin connection angle on the RH side at station 14911 (station 12447 for F28 Mark 0070), stringer 67 of aircraft fuselage section 2 before the existing threshold per ALS task 533016-00-03 (F28 Mark 0100) or 533016-01-03 (F28 Mark 0070). Therefore an additional one-time inspection has been introduced with SBF100-53-128. If cracks have occurred on the pressure bulkhead webplate and/or skin connection angle these can be repaired in accordance with this Service Bulletin (SBF100-53-129).
D. Description
(1) This Service Bulletin tells you how to:
- Gain access to the aft side, forward side and outside of the pressure bulkhead webplate and skin connection angle
- Remove the necessary parts
- Repair the found cracks
- Reinstall the removed parts
- Close up the work area.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 3 of 21
E. Compliance
(1) Optional Fokker Services recommends the accomplishment of the Service Bulletin in accordance with the instructions of SBF100-53-128.
NOTE: Repair per this Service Bulletin SBF100-53-129 can also be incorporated as preventative modification. This will, however, not affect the ALS inspection interval.
F. Approval
(1) The technical content of this document is approved under the authority of DOA ref.
EASA.21J.059.
G. Manpower
(1) Approximately 46 man-hours are necessa ry to do this Service Bulletin on one aircraft.
This table of manpower will help you to schedule and do this Service Bulletin:
Elapsed time (hours) Removal 1 6.0 6.0 Modification Inspection Installation 2 24.0 12.0 Testing - - - Total 46.0 26.0
8.0 Instructions Men Man-hours 21 6 . 0
NOTE: This estimate does not include the time necessary for the paint to dry and/or the sealant to cure.
(2) The estimated hours are for direct labor done by experienced personnel. They are calculated based on the conditions given in SBF100-00-001 (Service Bulletin Introduction, section 2.C., “Manpower”).
H. Weight and Balance
(1) Weight change: To be determined by weighing of the modkit (in kg).
Index change: (-0.02421) x Weight change (in kg).
Example: 3,00 kg weight change has an index change of -0.07263
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 4 of 21
I. Electrical Load Data
(1) Direct Current (DC) Loads:
(a) Not changed.
(2) Alternating Current (AC) Loads:
(a) Not changed.
J. Software Accomplishment Summary
(1) Not applicable.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 5 of 21
K. References Fokker 70/100 Airworthiness Limitation Section (ALS) Fokker 70/100 Structural Repair Manual (SRM) Fokker Consumable Material List (CML) Fokker Standards & Process Manual (SPM) Fokker 70/100 Service Bulletin (SB):
- SBF100-53-128 Fokker internal reference:
- ECR 16144.
L. Publications Affected
(1) This Service Bulletin affects the publications listed below:
(a) Maintenance Documentation
- Fokker 70 Structural Repair Manual (SRM) - chapter 53-21
- chapter 57-11
- Fokker 100 Structural Repair Manual (SRM) - chapter 53-31
- chapter 57-11
(b) Maintenance Programs
- Fokker 70/100 Maintenance Planning Document (MPD).
(c) Special Instructions for Continued Airworthiness (ICA) The effect of this Service Bulletin on the special ICA is as follows:
YES NO
- Electrical Wiring Interconnection System (EWIS) - X
- Fokker 70/100 Airworthiness Limitations Section (ALS):
• Fuel Tank Safety (FTS) - X
• Damage Tolerance of Fatigue Critical Structure (FCS) X -
• Certification Maintenance Requirements (CMR) - X NOTE: If “YES”, when not already incorporated, the changed ICA will be incorporated in the MRB, the Airworthiness Limitations Section (ALS) and/or the AMM document(s) within one calendar year from the date of issue of this Service Bulletin. Until then, no actions are required.
(d) Operational Documentation Not affected.
(2) Report to Fokker Services that this Service Bulletin has been carried out on the applicable aircraft.
(3) You have the possibility to send your SB feedback to Fokker Services per “Service Bulletin Reporting Quality Form”. This form is located on the last Service Bulletin page.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 6 of 21
(4) For incorporation of this Service Bulletin Appendix in your documentation refer to SBF100-00-001 (Service Bulletin Introduction, section 4 “Incorporation of Service Bulletins in Documentation of Fokker Services”).
M. Interchangeability or Intermixability of Parts
(1) Not applicable.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 7 of 21
3. Material Information A. Material – Price and Availability
(1) You can order the necessary parts as mod kit SB10053129-XU-A.
(2) You can contact your Fokker Services Customer Support Manager for the price and lead-time of this mod kit.
B. Material Required
(1) These parts, which are necessary to complete this Service Bulletin on 1 aircraft and are not part of the mod kit, are described in attachment Part List Local (PLL).
Material List Description Aircraft Effectivity SB10053129-XU-A Parts List Local (PLL) All
(2) These mod kit parts, which are necessary to do this Service Bulletin on 1 aircraft, are described in attachment Part List Supply (PLS) Material List Description Aircraft Effectivity SB10053129-XU-A Parts List Supply (PLS) All C. Tooling – Price and Availability
(1) Not applicable.
D. Tooling Required
(1) Not applicable.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 8 of 21
4. Accomplishment Instructions
General:
- In general, use (A)MM chapter 20, standard practices-airframe, as guide line for the aircraft modification.
- Loosen the cable clamps where necessary.
- Remove and discard the cable ties where necessary.
- Use cable ties and lacing tape where necessary.
- For CML material number references refer to “MyFokkerFleet.com > Documentation and select CML” and/or AMM chapter 20-30-00.
- For Standards and Process Manual (SPM) references refer to “MyFokkerFleet.com > Documentation and select SPM”.
- For drilling procedures refer to SRM chapter 51-22-01.
- For the application of sealing compound refer to AMM chapter 20-32-00 and chapter 51-23-00.
- For information on removal/installation of rivets refer to SRM chapter 51-40-02 and/or TH6.3002 (solid rivets) and SRM chapter 51-40-04 and/or SPM TH6.3106 (blind rivets).
- For the installation of Hi-Lok bolts refer to SRM chapter 51-41-01 and/or SPM TH6.3403.
- For the installation of bolts and screws refer to SRM chapter 51-43-01 and/or SPM TH6.3400.
- For the application of Primer & Paint refer to the AMM chapter 51-21-00 and/or SPM TH6.7370.
- For the application of Alodine refer to AMM chapter 51-22-00 and SRM chapter 51-24-01.
WARNING: BE CAREFUL WHEN YOU USE THE CONSUMABLE MATERIALS. OBEY
THE INSTRUCTIONS AND MANUFACTURER'S HEALTH AND SAFETY INSTRUCTIONS.
A. Clear the area round the lower wing to fuselage section on the RH side.
B. Open access panel 178BR.
C. Remove the nose fairing assembly in accordance with AMM 53-63-00-000-824-A.
D. Remove the rear wall panels in the forward cargo compartment; refer to AMM 25-51-00-000-824-A.
Refer to figures 1, 2 and 3 E. If necessary remove the bleed air duct in accordance with AMM 30-11-09-000-814-A to gain clearance at the aft side of the repair area.
F. Disconnect the electrical wiring connector P1695B (zone 165) and remove the cable clamp and bracket.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 9 of 21
G. Remove the corresponding electrical wiring receptacle J1695A from the pressure bulkhead at station 14911 (12447) by removing the bolts, nuts and washers.
Keep/discard:
- 4 Bolts NAS600-5P Discard
- 4 Washers AN960KD4L Keep
- 4 Nuts MS21042L04. Keep H. Drill out the applicable fasteners and remove the stringer couplings. See figure 1.
I. In case of a new crack, or one that has grown since repair postponement per SBF100- 53-128 step 4.F.(2), which has not yet been stop drilled, stop drill action must be accomplished now. For allowable crack length and stop drill requirements refer to SBF100-53-128.
Refer to figures 5 and 6 J. For installation of the external repair strip (in step Y. (1)), it is necessary to cut the fairing angle profile on which the nose fairing assembly is installed to the fuselage.
(1) Drill out the applicable rivets, remove and keep the fairing profile connection angles.
(2) Cut the angle next to the skin connection strip, see figure 6. Remove sharp edges and corners.
K. Clean the area which requires to be repaired. Use:
- AR Cleaning cloth Fk05-044
- AR Methyl Ethyl Ketone Fk11-003.
Refer to figures 1 and 2 L. Prepare the filler plate for installation.
(1) Trim the filler plate as required with corresponding structure. Use:
- 1 Filler plate p/n W31100-007.
M. Prepare the pressure bulkhead repair plate for installation.
(1) Trim the internal repair plate as required with corresponding structure. Use:
- 1 Pressure bulkhead repair plate p/n W31100-005.
N. Copy drill the existing solid fastener holes in the filler plate and pressure bulkhead repair plate.
O. Determine the new solid rivet hole positi ons on the filler plate and pressure bulkhead repair plate in accordance with SRM 51-40-02 and drill the new fastener holes in accordance with SRM 51-22-01 to accommodate MS20470AD5 rivets. Figures 1 and 2 show the rivet pattern, the precise pattern has to be determined in-situ.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 10 of 21
Refer to figures 2 and 3 P. Prepare the first repair angle for installation.
(1) Trim the repair angle to the proper length and shape as shown in figures 2 and 3.
Use:
- 1 First repair angle p/n W31100-001.
Q. Prepare the second repair angle for installation.
(1) Trim the repair angle to the proper length and shape as shown in figures 2 and 3.
Use:
- 1 Second repair angle p/n W31100-003.
R. Copy drill the existing fastener holes from the vertical flange of the wing connection angle and pressure bulkhead into the repair parts in accordance with SRM 51-41-01 to accommodate first oversize Hi-Loks bolts p/n HL110VF6.
S. Copy drill the existing fastener holes from the fuselage skin into the repair angles in accordance with SRM 51-41-01 to accommodate Hi-Loks bolts p/n HL10VF6 and p/n HL11VF6.
T. Prepare the stringer connection angles and shims for installation at stringer 67 and 68.
(1) Copy drill the fastener holes from the fuselage skin and stringers into the stringer connection angles and shims. Use:
- 2 Connection angle p/n W31100-009
- 2 Connection angle p/n W31100-011
- 2 Shims p/n W31100-013.
Refer to figures 3 and 6 U. Prepare the external repair strip for installation on the skin coupling.
(1) Trim the repair strip to the proper length and shape as shown in figure 3. Use:
- 1 External repair strip p/n W31100-015.
(2) Copy drill the two aft existing fastener rows, corresponding with the fuselage skin and skin connection angle, into the repair part in accordance with SRM 51-41-01 to accommodate Hi-Loks bolts p/n HL10VF6 and one Hi-Lok bolt p/n HL11VF6.
NOTE: The two holes in the corner of the skin connection angle which attaches the end of the fairing profile angle are left as is i.e. not to be copy drilled and not to be plugged. Refer to figure 6.
(3) Countersink one hole in the external repair strip to accommodate the Hi-Lok bolt p/n HL11VF6, which is located underneath the fairing profile angle.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Feb 16/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-53-129 Copyright All rights reserved by Fokker Services B.V. (The Netherlands). This document has been supplied by Fokker Services B.V . to its customers on a confidential basis subject to the provisions of an agreement.
Reproduction or disclosure to third parties of this document or any part thereof, or the use of any information contained 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.
Page 11 of 21
(4) Copy drill the forward two fastener rows from the fuselage skin coupling into the external repair strip in accordance with SRM 51-22-01 and SRM 51-41-01 to accommodate solid fasteners MS20470AD5, Hi-Loks bolts p/n HL10VF6 and one Hi-Lok bolt p/n HL11VF6.
(5) Countersink the second hole in the external repair strip to accommodate the Hi-Lok bolt p/n HL11VF6.
V. Locally manufacture a repair angle for the nose fairing connection angle, which has been cut off in step 4. J. Use the same flange dimensions as the original angle. Use:
- AR Sheet p/n F0N1-4311-1AM- 2024T3 (TH5.322) 1,4 mm.
(1) Copy drill the holes into the repair angle except for the two outer fastener holes which are located near the corner of the skin connection angle. These two fasteners are omitted.
W. Provide surface treatment to all bare material in accordance with SRM 51-24-01. Use:
- AR Conversion coating Alodine 1201 Fk13-003D
- AR Primer Aerodur S15/60 Fk07-008.
Refer to figure 2 X. Install the repair parts on the pressure bulkhead, see figure 2
(1) Position and wet install the filler plate (p/n W31100-007) pressure bulkhead repair plate (p/n W31100-005), first repair angle (p/n W31100-001) and second repair angle (p/n W31100-003) at station 14911 (12447). Use:
- 22 Hi-Lok collars p/n HL79-6
- 2 First oversize Hi-Lok bolts p/n HL110VF6-5
- 6 First oversize Hi-Lok bolts p/n HL110VF6-7
- 7 First oversize Hi-Lok bolts p/n HL110VF6-8
- 7 First oversize Hi-Lok bolts p/n HL110VF6-9
- AR Solid rivets p/n MS20470AD5
- AR Sealant p/n PR1782B
- 1 First repair angle p/n W31100-001
- 1 Second repair angle p/n W31100-003
- 1 Pressure bulkhead repair plate p/n W31100-005
- 1 Filler plate p/n W31100-007
- AR Washer p/n NAS1149D0332K.
NOTE: In case a Hi-Lok bolt is too long, use one or two washers underneath the collar per SRM 51-41-01 paragraph 7.