Ercoupe Service Bulletin 29 Revision C
ERCO 415 Ercoupe · Service Bulletins
Overview
This document is Service Bulletin No. 29, Revision C, for the ERCOUPE aircraft, detailing mandatory inspection procedures for the outer wing panel to identify corrosion. It outlines compliance requirements, inspection procedures, and necessary documentation for affected aircraft models.
- Mandatory inspection of outer wing panels for corrosion is required.
- Affected models include Ercoupe 415-C, 415-CD, 415-D, 415-E, and 415-G.
- Inspection must be completed within the next 100 hours of operation or at the next periodic inspection.
- Installation of inspection openings is recommended for better access during inspections.
- Use FAA Advisory Circular AC 43-4A for corrosion identification and treatment.
- Log book entry is required to document compliance with the service bulletin.
- Continued inspections are required at each 100 hours and annual inspection.
- Weight and balance change from this procedure is negligible.
Document
Source
Originally published by univair.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 1999
- File size ·
- 303 KB
- Publisher ·
- univair.com
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Inspection opening diameter (in) ·
- 3.50
What is the Ercoupe Service Bulletin 29 Revision C?
The Ercoupe Service Bulletin 29 Revision C is a service bulletins for the ERCO 415 Ercoupe, dated 1999.
Where does the Ercoupe Service Bulletin 29 Revision C come from?
This copy of the Ercoupe Service Bulletin 29 Revision C was originally published by univair.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Ercoupe Service Bulletin 29 Revision C published?
The Ercoupe Service Bulletin 29 Revision C — the ERCO 415 Ercoupe service bulletins on file — is dated 1999.
Most owners only have the POH. Here's the essential set for the ERCO 415 Ercoupe.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More ERCO 415 Ercoupemanuals & documents
In this document
Subject
Visual inspection of outer wing panel structure for evidence of corrosion.
Compliance
Inspection required within the next one hundred hours of operation or at the next periodic inspection, whichever occurs first.
Procedure
Steps for preliminary inspection, cutting inspection openings, and conducting the inspection for corrosion.
Inspection Procedure
Inspect the wing panel structure for corrosion and unrepaired damage using the openings made.
Required Documentation
Make log book entry stating compliance with Service Bulletin No. 29C.
Continued Inspections
At each 100 hours and annual inspection, remove cover plates and inspect outer wing panel for corrosion or damage.
Safety notes
- Caution: Alter opening locations if they interfere with skin stiffeners on metal skinned wings.
- Repair or replace any parts considered unairworthy prior to further operation.
Full document text
ERCOUPE SERVICE BULLETIN No. 29 SUBJECT: Mandatory Outer Wing Revision C Panel Inspection DATE: July 8, 1999 MANDATORY SERVICE BULLETIN SERVICE BULLETIN NO. 29, REVISION C OUTER WING PANEL INSPECTION July 8, 1999 SUBJECT: Visual inspection of outer wing panel structure for evidence of corrosion. MODELS AFFECTED: All Ercoupe 415-C, 415-CD, 415-D, 415-E and 415-G aircraft. All Forney F-1 and F-1A aircraft. All Alan A-2 and A-2A aircraft. All Mooney M10 aircraft. COMPLIANCE: Inspection required within the next one hundred hours of operation or at the next periodic inspection, whichever occurs first. STATEMENT OF DIFFICULTY: There have been field reports of severe corrosion in the outer wing panel structure of several aircraft. The most effective means of preventing corrosion damage is early identification and correction. However, the original design configuration does not provide adequate means for routine visual examination of the wing panels during periodic inspections. Consequently, this Service Bulletin provides for the installation of strategically placed inspection openings to allow for complete visual access to the wing panel structure, and calls for an inspection to establish the current condition of the structure. The inspection openings will then allow routine inspections to be accomplished as required under FAR Part 43, Appendix D, (f). Revision C of this Service Bulletin provides some clarifications to Revision B. If Service Bulletin No. 29 Rev. B has been complied with, then only the continued inspection procedures of Step 7 below need to be accomplished. Univair Aircraft Corporation page 1 of 4 Service Bulletin No. 29, Rev. C July 8, 1999 PROCEDURE: 1. The following optional procedure is intended only as a preliminary inspection to determine if a major corrosion problem exists, prior to installing the permanent inspection openings in the wing panels. If equipment is available, cut borescope hole in center of inspection opening locations as shown on diagram SB-29, Rev. B. Inspect wing interior and make preliminary assessment of wing condition. FAA Advisory Circular AC 43-4A, "Corrosion Control for Aircraft", dated 7/25/91 or later, should be used to identify and treat corroded areas. Service Memos 45, 58, 58A, 64 and Service Bulletin No. 27 concern outer wing panel structure and should be reviewed at this time. If preliminary examination reveals conditions that are not repairable through an inspection opening, remove wing covering as required and repair or replace unairworthy parts prior to further operation. Replace covering. Install inspection openings and covers per Steps 2, 3, and 5. If borescope equipment is not available, proceed to Step 2. 2. Inspection opening location - Locate inspection openings on the lower wing surface per the enclosed diagram, SB-29, Rev. B. Aircraft with factory covered metal skinned wings may already have existing inspection openings. SB-29, Rev. B, includes these openings. CAUTION: If the opening locations specified by the diagram interfere with any skin stiffeners on metal skinned wings, alter the opening location to clear the stiffener. 3. Cutting procedure - Metal skinned wings - Cut 3.50 inch diameter inspection openings at the locations of No. 2 above and deburr. Fabric covered wings- Remove finish to bare fabric at the locations of No.2 above. Attach reinforcing ring (P/N 483-15) with Rand-0-Bond, Super Seam or cement approved for use with covering process STC. If the wing is covered with synthetic fabric, it is recommended that a cover patch be applied over the inspection ring to prevent the ring peeling away from the fabric surface. Apply finish as required to touch-up area surrounding reinforcing ring. Carefully cut out center opening of ring. NOTE: The four outboard inspection openings in each wing may have already been installed per Service Bulletin No. 27. 4. Inspection procedure - Using the openings made in Step 3 above, inspect the wing panel structure for corrosion and unrepaired damage. FAA Advisory Circular AC 43-4A, Univair Aircraft Corporation page2of4 Service Bulletin No. 29, Rev. C July 8, 1999 "Corrosion Control for Aircraft", dated 7/25/91 or later, should be used to identify and treat corroded areas. Service Memos 45, 58, 58A, 64 and Service Bulletin No. 27 concern outer wing panel structure and should be reviewed at this time. Service Memo 45 regarding leading edge skin dents applies to Ercoupes Serial Nos. 1 to 112. Use heavier gage sheet metal to replace dented leading edge skins on these aircraft. Service Memo 58 stresses the importance of maintaining the fabric on fabric covered wings. It also details the inspection and repair of the wing tip splice on Ercoupes Serial Number 4893 and earlier. If the wing tip splice is held with countersink rivets they should be replaced with larger diameter universal head rivets in accordance with Service Memo 58. Service Memo 58A reiterates the importance of compliance with Service Memo 58. Service Memo 58A suggests the replacement of countersink rivets in the wing tip splice with universal head rivets when fabric is being replaced whether the rivets are loose or not. Univair Aircraft Corporation strongly recommends the replacement of countersink rivets in the wing tip splice with universal head rivets in accordance with Service Memo 58 as soon as practical. Service Memo 64 announces the availability of repair kit S.A 24 to simplify repair of damage to the inboard end of the outer wing panel rear spar, providing the damage does not extend outboard of a point 15 inches from the inner rib. If the rear spar attach fitting or the rear spar around the fitting is corroded, kit S.A. 24 may be installed to replace the corroded fitting and the inboard 15 inches of the rear spar. Service Bulletin No. 27 details procedures for inspection of suspected wing tip damage. Repair or replace any parts considered unairworthy prior to further operation.
Show full textShow less
5. Cover plate installation - After inspection is complete, install cover plates (PIN 483-10) in each opening. On metal skinned wings, secure each cover plate at the leading edge with one 4 X 3/8 TRA sheet metal screw. 6. Required documentation- Make log book entry stating compliance with Service Bulletin No. 29C. Weight and balance change is considered negligible. 7. Continued inspect'ons- At each 100 ~ 'lur and annual inspection, remove the cover plates installed per Step 3 am inspect outer wing panel for corrosion or damage per Step 4 as required by, '.\R Part 43, Appendix 0 (f). Repair or replace corroded or damaged parts l required. Univair Aircraft Corporation page 3of4 Service Bulletin No. 29, Rev. C July 8, 1999 1l ••0 •• " I' ~ r ~- ---- $ . "" w > "" 0,__ f-- 0 co