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Service Bulletin Fokker Services B.V.
Prepared Function / Note Date poutsma-sp49839 Mar 24/15 Colleague Check doesburg-jd01812 Mar 23/15 Manager Final Approval benthem-eb01865 Mar 24/15 Office of Airworthiness Approval visser-hv01800 Mar 24/15
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049
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
SBF100-57-049
Revision -
WINGS - TORSION BOXES
The One-Time Inspection of the LH and RH Wing Rear Spar Lower Girder from WSTA 2635 to 8700 and 9270 to 12975 and Modification of the Wing Trailing Edge Lower Skin Panels into Access Panels.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
1. General Information A. General
B. Table of Contents
• Section 1: General Information
• Section 2: Planning Information
• Section 3: Material Information
• Section 4: Accomplishment Instructions
• Service Bulletin Quality Reporting Form and attachments (if applicable):
• List of drawings/parts lists
• Parts List Local source (PLL)
• Parts List Supply (PLS)
• Required drawings C. Service Bulletin Revision History
Revision Date (Mmm dd/yy) Reason for Revision
- Refer to footer First Release
WINGS - TORSION BOXES
The One-Time Inspection of the LH and RH Wing Rear Spar Lower Girder from WSTA 2635 to 8700 and 9270 to 12975 and Modification of the Wing Trailing Edge Lower Skin Panels into Access Panels.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
2. Planning Information A. Effectivity
(1) F28 Mark 0070/0100 aircraft serial numbers:
11244 thru 11585.
B. Concurrent Requirements
(1) Not applicable.
C. Reason
(1) An aircraft was found with heavy corrosion on the rear spar lower girder at several spanwise positions. Locally the corrosion damage was such that at small spots almost all effective thickness of the vertical flange of the lower girder was lost.
(2) When performing the zonal inspections in zone 536 and 636 (MRB task 062505- 00-01 and 062605-00-01), the rear spar lower girder between WSTA 9270 and 11794 is hidden from view by the inboard and outboard aileron balancing plates.
Therefore it is possible that corrosion in this area is not found during these routine zonal inspections. Outside this area the rear spar lower girder is directly visible during the same zonal inspections. Nevertheless heavy corrosion was found in this area as well.
(3) Calculations have been made on the reduction in load carrying capability of the wing under the relevant load cases. As a consequence it has been determined that the risk of presence of similar corrosion damages on other aircraft in the fleet is too high and therefore requires a one-time inspection for timely detection and correction.
(4) For the area between WSTA 9270 and 11794 the outer wing trailing edge lower skin has to be removed to get access and enable inspection of the rear spar. The trailing edge structure and the skin panels will be modified to use these skin panels as removable access panels. The zonal inspection will be revised to add the new access panel numbers.
(5) The area between WSTA 8700 and 9270 is excl uded from this Service Bulletin as this area is already covered by the detailed inspection according ALS task 572009-
00-13. However, if not already accomplished, it may be advisable to plan the first accomplishment of subject task simultaneously with the accomplishment of SBF100-57-049.
(6) This Service Bulletin provides allowable (flyable) remaining thickness limits after the blend out of the possible corrosion on the outer wing rear spar lower girder between WSTA 2635 and 12975. These limits are not the absolute minimums.
Smaller remaining thickness (deeper blend outs) may be allowed however must be evaluated on a case by case basis by Fokker Services.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
(7) For repair of the rear spar lower girder outboard WSTA 8200 Service Bulletin SBF100-57-050 will be issued. This Service Bulletin provides a generic repair by replacing (parts of) the lower girders. For repairs inboard WSTA 8200 contact Fokker Services for instructions.
(8) In case of small blend out areas which do not necessitate a replacement of the lower girder Fokker Services can provide customized repairs consisting of local repair angles.
D. Description
(1) This Service Bulletin is divided in two Parts as follows:
Part 1: The One-Time Inspection of the LH and RH Wing Rear Spar Lower Girder from WSTA 9270 to 11794 and Modification of the Wing Trailing Edge Lower Skin Panels into Access Panels.
- Get access and prepare the inspection area.
- Inspect the Rear Spar Lower Girder Area between WSTA 9270 and 11794.
- Corrective actions only applicable in case corrosion is found.
- Restore the surface protection in case paint, sealant and/or corrosion was removed.
- Modification of the trailing edge rebates for installation of the skin panels as removable access panels.
- Modification of the composite skin panels.
- Installation of access panels.
- Report your findings to Fokker Services.
Part 2: The One-Time Inspection of the LH and RH Wing Rear Spar Lower Girder Area from WSTA 2635 to 8700 and 11794 to 12975.
- Get access and prepare the inspection area.
- Inspect the Rear Spar Lower Girder Area from WSTA 2635 to 8700 and 11794 to 12975.
- Corrective actions only applicable in case corrosion is found.
- Restore the surface protection in case paint, sealant and/or corrosion was removed.
- Installation of access panels.
- Report your findings to Fokker Services.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
E. Compliance
(1) Recommended Fokker Services recommends the accomplishment of the Parts of this Service Bulletin within the following periods:
Part 1: Fokker Services recommends the accomplishment of the inspection of the rear spar area from WSTA 9270 to 11794 and modification of the wing trailing edge lower skin panels within 1 000 flight cycles or 1 year from the release date of this Service Bulletin, whichever comes first.
Part 2: Fokker Services recommends the accomplishment of the inspection of the rear spar area from WSTA 2635 to 8700 and 11794 to 12975 within 2 000 flight cycles or 2 years from the release date of this Service Bulletin, whichever comes first.
NOTE: It is expected that EASA will issue an Airworthiness Directive (AD) with respect to this subject with the same compliance terms. Refer to the EASA website for the publication of a Proposed Airworthiness Directive for comments.
F. Approval
(1) The technical content of this document is approved under the authority of DOA ref.
EASA.21J.059.
G. Manpower
(1) Approximately 23 man-hours are 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:
Elapsed time (hours) Removal 2 4.0 2.0 Modification Inspection Installation 1 3.0 3.0 Testing - - - Total 23.0 13.0
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.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
(2) Approximately 12 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:
Elapsed time (hours) Removal 1 5.0 5.0 Modification Inspection Installation 1 5.0 5.0 Testing - - - Total 12.0 12.0
2.0 Instructions Men Man-hours 12 . 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) Direct Current (DC) Loads:
(a) Not changed.
(2) Alternating Current (AC) Loads:
(a) Not changed.
J. Software Accomplishment Summary
(1) Not applicable.
K. References
(1) Fokker 70/100 Aircraft Maintenance Manual (AMM) Fokker 70/100 Maintenance Planning Document (MPD) Fokker 70/100 Maintenance Review Board (MRB) report Fokker 70/100 Non-Destructive Testing (NDT) Manual Fokker 70/100 Structural Repair Manual (SRM) Fokker Consumable Material List (CML) Fokker Standards & Process Manual (SPM) Fokker 100 Service Bulletin (SB):
- SBF100-57-050
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
Fokker internal reference:
- ECR016183.
L. Publications Affected
(1) This Service Bulletin affects the publications listed below:
(a) Maintenance Documentation
- Fokker 70/100 Aircraft Maintenance Manual (AMM) - chapter 06-30
- Fokker 70/100 Illustrated Parts Catalog (IPC) - chapter 57-61
(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.
(4) 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 Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
3. Material Information A. Material – Price and Availability
(1) You can order the necessary parts as mod kit SB10057049-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, are not part of the mod kit:
New Part Number Qty Keyword Info Old Part Instructions/ * 1 *2 Number Disposition
- AR* 3 AR Lint-free cloth Fk05-044* 4 - Local source 2024T3 Alclad AR - Sheet t = 0.8 mm - Local source Aerodur Finish C21/100 AR AR Paint Fk07-027 - Local source Aerodur Primer S15/60 AR AR Primer Fk07-008 - Local source Alodine 1201 or AR AR Conversion coating Fk13-003D - Local source Alodine 1132 Touch-n-Prep Fk13-003E EA9396 AR - Laminating resin TH5.558/9 - Local source Methyl Ethyl Ketone AR AR Cleaning solvent Fk11-003 - Local source MS20426AD5 16 - Solid rivet - - Local source NAS1097AD3 596 - Solid rivet - - Local source Nycote 88 AR AR Skydrol-resistant coating Fk09-008 - Local source PS870A AR - Sealant Fk09-016A - Local source PS870B AR AR Sealant Fk09-017A - Local source Scotchbrite Type A Very Fine AR AR Abrasive material Fk05-007 - Local source NOTES: * 1 Applicable to do Part 1 of this Service Bulletin on 1 aircraft *2 Applicable to do Part 2 of this Service Bulletin on 1 aircraft *3 Use as much as necessary *4 Refer to the CML for material numbers.
(2) These mod kit parts are necessary to do Part 1 of this Service Bulletin on 1 aircraft:
New Part Number Qty Keyword Info Old Part Number Instructions/ Disposition D15003-701*5 27 Tapered plate - - - F0N2-1611V03-03 4 Bolt NSA5030-3-3 - - F0N2-1611V03-04 6 Bolt NSA5030-3-4 - - F0N2-1611V03-05 266 Bolt NSA5030-3-5 - - F0N2-1611V03-06 22 Bolt NSA5030-3-6 - - MS21073L3 66 Anchor nut - - - MS21075L3E 232 Anchor nut - - - NOTE: * 5 Part can also be made locally using 2024T3 Alclad sheet 170×25×2,5 mm. Refer to step F.(4) of Part 1 and figure 7.
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
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) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
4. Accomplishment Instructions
General:
- All Accomplishment Instructions are applicable to the LH and RH wing. Part quantities are provided for each wing separately.
- For CML material number references refer to “MyFokkerFleet.com > Documentation and select CML” and/or AMM chapter 20-30-00.
- For the application of sealing compound refer to AMM chapter 20-32-00 and chapter 51-
23-00.
- For the application of Primer & Paint refer to the AMM chapter 51-21-00.
- 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.
Part 1: The One-Time Inspection of the LH and RH Wing Rear Spar Lower Girder from WSTA 9270 to 11794 and Modification of the Wing Trailing Edge Lower Skin Panels into Access Panels.
A. Get access and prepare the inspection area.
(1) Open access panel 536(636)GB (Fuel tank ventilation sniffle-valve).
Refer to figures 1 and 2.
(2) Remove the two trailing edge lower skin panels between WSTA 9270 and 11794 connected to the rear spar.
NOTE: The skin panels are installed with solid rivets and Hi-Loks. Carefully remove them without damaging the composite skin panels.
(3) Remove any blistered, cracked, flaking or loose paint and/or sealant from the vertical flange of the rear spar lower girder and lower area of the web. Use a nonmetal brush, non-metal scraper, compressed air or any suitable means.
NOTE: For better access to the rear spar the aileron balance plate support beams can be removed (SRM chapter 57-57-02-05 items 280 and 310).
B. Inspect the Rear Spar Lower Girder Area between WSTA 9270 and 11794.
(1) Use the inspection light, magnifying glass and inspection mirror and inspect the rear spar lower girder area for signs of corrosion.
C. Corrective actions only applicable in case corrosion is found.
(1) Remove any corrosion from the vertical flange of the rear spar lower girder and lower area of the web. Use:
- AR Scotchbrite Type A Very Fine (Fk05-007)
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
(2) In case corrosion has been removed measure the remaining thickness at the damage spots in the rear spar lower girder using NDT ultrasonic equipment, refer to the NDT Manual Part 1 chapter 51-00-04 paragraph 12.
(3) Make a note of the locations, size and depths of the damage spots and make overview photos and detail photos.
(4) In case the damage spots have a remaining thickness more than specified in table 1, repair the surface treatment according step (D).
Table 1
WSTA Minimum remaining thickness Original thickness (mm) (mm) 9270 - 11794 1.9 3.56
(5) If the damage spots have a remaining thickness less than specified in table 1, contact Fokker Services for evaluation of the remaining thickness. The limits of table 1 are not the absolute minimums, smaller remaining thickness (deeper blend outs) may be allowable, but need to be evaluated on a case by case basis.
Alternatively do a repair in accordance with SBF100-57-050 or a customized repair advice (local repair angles) from Fokker Services B.V.
D. Restore the surface protection in case paint, sealant and/or corrosion was removed.
NOTE: Restoration of surface coating may be postponed for 500 flight hours in case only paint top coat was removed. In case primer was removed or corrosion was found, restoration of the coating may not be postponed.
(1) In case primer was removed, apply alodine and a new coat of primer. Refer to the AMM chapter 51-21-00. Use:
- AR cleaning solvent Methyl Ethyl Ketone (or equivalent) (Fk11-003)
- AR lint-free cloth - (Fk05-044)
- AR conversion coating Alodine 1201 or (Fk13-003D) Alodine 1132 Touch-n-Prep (Fk13-003E)
- AR primer Aerodur Primer S15/60 (Fk07-008)
(2) In case sealant was damaged and/or removed, apply new sealant with skydrol resistant coating on top of the lower girder and between the lower girder and the skin rebate. Refer to figure 5 and the SRM chapter 51-23-01. Use:
- AR cleaning solvent Methyl Ethyl Ketone (or equivalent) (Fk11-003)
- AR lint-free cloth - (Fk05-044)
- AR sealant PS870B (Fk09-017A)
- AR skydrol-resistant coating Nycote 88 (Fk09-008)
Service Bulletin Fokker Services B.V.
Status:
Released Revision:
- Released date: (Mmm dd/yy) Mar 24/15 Security class:
RESTRICTED F100/70 Generic SB no.:
SBF100-57-049 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 23
(3) In case paint was removed, apply a new paint coat. Refer to the AMM chapter 51-21-00. Use:
- AR cleaning solvent Methyl Ethyl Ketone (or equivalent) (Fk11-003)
- AR lint-free cloth - (Fk05-044)
- AR paint Aerodur Finish C21/100 (Fk07-027) E. Modification of the trailing edge rebates for installation of the skin panels as removable access panels.
Refer to figures 1 and 2.
(1) At the eight (8) rivet positions (indicated as green dots) countersink the holes on the lower side of the structure and install rivets in the reworked holes. Use:
- 8 solid rivets MS20426AD5
(2) Increase the diameter of the indicated bolt holes in the structure to a diameter of 4,9 mm H13.
(3) On the four (4) indicated positions install anchor nuts directly on the structure. Use:
- 8 solid rivets NAS1097AD3
- 4 anchor nuts MS21075L3E
- AR sealant PS870A (Fk09-016A)
(4) Create anchor nuts plates.
(a) Make plates to fit on the indicated positions.
Use at the rear spar and on the rib flanges:
- AR Alclad sheet 2024T3 thickness 0,8 mm;
Use in the pockets of the balance plate support beams:
- 13.5 tapered plates pn D15003-701;
NOTES: - Cut the sheet and tapered plates to size.
- The balance plate support beams have 16 pockets (per wing) in which an anchor nut plate need to be placed. For 11 pockets a complete tapered plate pn D15003-701 is used and cut to size; for 5 pockets the half of a tapered plate pn D15003-701 is used and cut to size. This results in 13.5 tapered plates necessary per wing.
- Tapered plate D15003-701 can also be made locally using material 2024T3 Alclad sheet, 170×25×2,5 mm. For the cross-section refer to figure 7.
(b) Copy drill the bolt hole positions from the structure into the plates and tapered plates. After copy drilling enlarge the diameter to 5,3 mm H13.
(c) Position the anchor nuts as indicated in the figures on the plates and tapered plates, mark the rivets holes and drill the rivets holes for installation of NAS1097AD3 rivets.