SERVICE BULLETIN No. 819
Piper PA-22 Colt · Service Bulletins
Overview
This Service Bulletin No. 819 issued by Piper Aircraft Corporation addresses corrosion issues in the fuselage door frame tube of several aircraft models, including the Piper PA-22 Colt. The bulletin is considered mandatory for compliance within 25 flight hours or six months, whichever comes first. It outlines the inspection and repair procedures necessary to ensure the structural integrity of the fuselage is maintained. The bulletin emphasizes the importance of addressing excessive rust and corrosion found between steel tubing and preformed sheet steel, which can compromise the aircraft's safety. Detailed instructions for inspection, repair, and corrosion protection are provided, along with material specifications and compliance logging requirements.
- Compliance is mandatory within 25 flight hours or 6 months.
- Inspect for corrosion in door frames, windshields, and baggage areas.
- Use .032" 4130N steel for replacement parts with a 0.12" minimum bend radius.
- Coat blind areas with corrosion inhibitors like hot linseed oil.
- Document compliance with a logbook entry.
Document
Source
Originally published by www.univair.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Service Bulletins
- Year
- 1986
- Pages
- 3
- File size
- 156 KB
- Publisher
- www.univair.com
Most owners only have the POH. Here's the essential set for the Piper PA-22 Colt.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More Piper PA-22 Coltmanuals & documents
See all 13 →- Airworthiness Directive ScheduleAirworthiness Directives
- SERVICE LETTER NO. 1302Checklist
- Project Materials ListSystems Description
- Type Acceptance ReportOther Documents
- AAIB Bulletin: 9/2013Other Documents
- PIPER Tri-Pacer with Lycoming O290, O320 EngineSystems Description
- Tri-PacerPerformance Data
- Piper Aircraft Corporation Parts CatalogWeight And Balance
- Airworthiness Directive 281/64Airworthiness Directives
- Airplane Flight Manual for the Piper PA-22 ColtFlight Manual
- AILERON - RUDDER INTERCONNECT REMOVALType Certificate
- Piper Service Letters, Bulletins, Memos and AidsWeight And Balance
In this document
Purpose
The bulletin highlights the risk of excessive rust and corrosion between steel tubing and preformed sheet steel in the fuselage, particularly in door frames, windshields, and baggage areas. If not addressed, this corrosion can compromise the structural integrity of the aircraft.
Compliance Time
Operators are required to comply with the bulletin within 25 hours of flight or within six months, whichever occurs first.
Instructions for Inspection and Repair
The bulletin provides step-by-step instructions for inspecting the affected areas, including removing fabric and preformed sheet steel, inspecting the tubing, and applying corrosion protection. Specific materials, such as .032" 4130N steel, are recommended for replacement parts.
Material Required
The materials needed for compliance will be determined by inspection, and local procurement from shop stock is suggested.
Logbook Entry
After completing the required actions, an appropriate logbook entry must be made to document compliance with this Service Bulletin.
Safety notes
- Failure to address corrosion can compromise fuselage integrity.
Full document text
Piper Aircraft Corporation Vero Beach, Florida, U.S.A. FAA Approved SUBJECT: MODELS AFFECTED: J-4 Coupe J-5 Cruiser PA-12 Super Cruiser PA-14 Family Cruiser PA-15 Vagabond PA-16 Clipper PA-17 Vagabond PA-20 Pacer PA-22 Tripacer and Colt SERVICE BULLETIN No. 819 ********************************** : PIPER CONSIDERS : : COMPLIANCE MANDATORY : ********************************** Date February 28, 1986 S Fuselage Door Frame Tube Corrosion: Repair and Protection. SERIAL NUMBERS AFFECTED: 4-401 through 4-1649 5-02 through 5-1389 12-02 through 12-4036 14-01 through 14-523 15-01 through 15-388 16-01 through 16-736 17-01 through 17-215 20-01 through 20-1121 22-01 through 22-9848 COMPLIANCE TIME: Within the next twenty-five (25) hours of flight, but not to exceed six (6) months. PURPOSE: Reports have been received of the presence of excessive rust and corrosion between steel tubing and preformed sheet steel material, which is welded to the tubing in the door frames, windshield, and baggage areas of the fuselage. The preformed sheet steel can be in the shape of a channel, angle or variation of either which, when welded to the tubing' in certain locations, can create a blind area. If these conditions exist and are left uncorrected, the structural integrity of the fuselage will be compromised. REFERENCE: FAA Advisory Circular AC43.13-1A Acceptable Methods, Techniques and Practices - Aircraft Inspection and Repair. INSTRUCTIONS: 1. Unless an acceptable alternate method of inspection is approved by the F.A.A., remove the fabric from the door frame, windshield, and baggage areas which are constructed with preformed steel sheet welded over steel tubing. (Ref. drawing). 2. In the door frame(s), windshield and baggage areas, remove the preformed sheet steel from the tubing. Exercise care when smoothit.-, dressing or cleaning the welds to prevent damage to the tubing. 3. Inspect tubing; repair or replace as required, and add ~~rrosion protection per AC43 .13-1A. (over) ATA: 5300 SERVICE BULLETIN NO. 819 PAGE 2 OF 3 INSTRUCTIONS: - (Con't.) 4. Install new sheet steel parts fabricated from .032" 4130N steel with a 0.12" minimum bend radius to replace original parts. Tack weld 3/8" lengths on 2" spacing. (See attached Sketch for shapes). 5. Whether or not any repairs are required, coat the blind area between the preformed sheet steel and the tubing with hot linseed oil, paralketone, or other corrosion inhibitor. 6. Clean and refinish exterior of structure per individual preference with good quality aircraft grade primer. 7. Repair or replace fabric as required per AC43.13-1A, or applicable Supplemental Type Certificate. 8. Make an appropriate logbook entry of compliance with this Service Bulletin. MATERIAL REQUIRED: AVAILABILITY OF PARTS: EFFECTIVITY DATE: To be determined by inspection. Local procurement from shop stock. This Service Bulletin is effective upon receipt. SUMMARY: If you are no longer in possession of this aircraft, please forward this information to the present owner. SERVICE BULLETIN NO. 819 PAGE 3 OF 3 FIG. I FIG. 5 FIG. 6 ---gFIG. 2 FIG. 3 B bFIG. 7 FIG.8 TYPICAL FUSELAGE FRAME ASSEMBLY IAFITICI.E SHOWN IS PA-22) gFIG.9 FIG.4 FIG.IO