SERVICE BULLETIN No. 966
Piper PA-18 Super Cub · Service Bulletins
Overview
This Service Bulletin No. 966 addresses critical maintenance issues for the Piper PA-18-150 Super Cub, specifically focusing on the replacement of tail surfaces and corrosion protection for the vertical fin. It is mandatory for affected aircraft to comply within six months or at the next scheduled maintenance. The bulletin is divided into two parts: Part I details the replacement of tail surfaces due to premature internal corrosion, while Part II outlines the sealing of the vertical fin to prevent further corrosion. The document includes specific instructions, required materials, and compliance timelines, ensuring that aircraft owners and maintenance personnel can effectively address these safety concerns.
- Affected Model: Piper PA-18-150 Super Cub
- Compliance Time: Within 6 months or at the next scheduled maintenance
- Serial Numbers Affected: 1809002 to 1809052
- Replacement of tail surfaces due to corrosion is mandatory
- Sealing of vertical fin tubes is also required to prevent corrosion
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
- 1994
- Pages
- 11
- File size
- 502 KB
- Publisher
- www.univair.com
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In this document
Part I: Tail Surfaces Replacement
Part I of the bulletin mandates the replacement of the tail surfaces on affected PA-18-150 Super Cubs due to evidence of premature internal corrosion. The affected serial numbers range from 1809002 to 1809052. Compliance is required within six months or at the next maintenance event. The section provides detailed instructions for removing old surfaces and installing new ones, including necessary hardware and finishing procedures.
Part II: Vertical Fin Corrosion Protection
Part II requires the sealing of the leading edge and tail post tubes of the vertical fin for the same aircraft model. The affected serial numbers are similar to those in Part I. Instructions include cutting access holes, applying sealant, and ensuring proper curing. Compliance is also required within six months or at the next maintenance event.
Instructions for Tail Surfaces Replacement
The bulletin provides step-by-step instructions for replacing the tail surfaces, including disconnecting cables, removing old hardware, and installing new components. It emphasizes the importance of inspecting the condition of stabilizer liner tubes and ensuring proper rigging of control surfaces after installation.
Materials Required
The bulletin lists specific parts required for compliance, including rudder and stabilizer assemblies, as well as liner tubes. It also mentions the availability of these parts through Piper Field Service Facilities.
Logbook Entry
A logbook entry is required to document compliance with both parts of the Service Bulletin, ensuring that maintenance records are up to date.
Safety notes
- Failure to comply with this Service Bulletin may compromise aircraft safety due to structural integrity issues.
- Ensure proper sealing of the vertical fin to prevent future corrosion.
Full document text
Piper Aircraft Corporation 2926 Piper Drive Vero Beach, Florida, U.S.A. 32960 SERVICE BULLETIN No. 966 PIPER CONSIDERS COMPLIANCE MAI'-JDATORY January 21, 1994 This Service Bulletin is divided into TWO (2) PARTS. Check each PART for subject and serial numbers affected. SUBJECT: MODELS AFFECTED: PA-18-150 Super Cub PART I TAIL SURFACES REPLACEMENT SERIAL NUMBERS AFFECTED: 1809002, 1809004 1hrough 1809011 1809013 through 1809032 1809034 through 1809038 1809043 through 1809045 1809047, 1809050 through 1809052 COMPLIANCE TIME: Within the next six (6) months or at the next regularly scheduled maintenance event, whichever occurs first. PURPOSE: After the initial production of the re-introduced Super Cub, it was discovered that soC1e field aircraft showed evidence of premature internal corrosion in the steel tube structure of the vertical fin and the five tail surfaces (stabilizers, elevators, and rudder). Analysis of the corroded areas indicates that over time the integrity of the structure will be compromised and any rework of the internal steel tubes on the control surfaces would be impractical or uneconomical. Therefore, PART I of this Service Bulletin requires the replacement of the tail surfaces with new ones which incorporate improved internal treatment processes during manufacture. PART II of this Service Bulletin requires the sealing of the leading edge and tail post tubes of the vertical fin. APPROVAL: The technical contents of this Service Bulletin have been approved by the FAA. (OVER) ATA: 5500 PAGE 2 OF 11 SERVICE BULLETIN NO. 9 6 6 INSTRUCTIONS: 1. Gain access to the rudder and elevator cable turnbuckles and release tension on these cables. 2. Disconnect navigation/anti-collision light wiring at the knife splices located at the lower leading edge of the ruddec. (if installed) 3. Remove the necessary hardware, springs and stabilizer tailbrace wires and remove control surfaces from the aircraft. NOTE: Prior to continuing with the Instructions in this PART. compliance with PART II would be advisable. 4. The new tail surfaces come complete with filler and prime finish. (Aerotec Inc. process) 5. Apply desired finish following the procedures specified by the finish supplier and/or refer to the latest revision of AC43.13 for details on fabric aircraft finishing. NOTE: Approved finishes are catalyzed polyurethanes. Enamel finishes are not recommended. 6. Inspect condition of forward and aft stabilizer liner tubes. If these tubes are difficult to remove during disassembly or exhibit signs of corrosion or damaged/elongated bolt holes, the liner tube(s) must be replaced. The liner tube bore within the fuselage may require cleaning also. 7. Install new tail surfaces. Use the attached illustrations as follows: - Stabilizer Installation - Stabilizer Installation and Rigging Sketch 1 and 2 Sketch 3 Sketch 4 Sketch 5 Sketch 6 Sketch 7 - Elevator Installation - Bungee Installation - Rudder Installation - Tailwheel Steering Installation 8. Check for proper control surface continuity and rigging. 9. Connect navigation/anti-collision light wiring and operationally check (if installed). · 0. Make appropriate logbook entry of compliance with PART I of this Service Bulletin. MATERIAL REQUIRED: Che each per aircraft: Rudder Assembly Stabilizer L. Stabilizer R Elevator R. Elevator L. Tube - Rear Liner Tube - Liner AVAILABILITY OF PARTS: Piper PIN 14773-008 12790-806 12790-807 12789-807 12789-806 86062-079 86062-080 Your Piper Field Service Facility SERVICE BULLETIN NO. 966 PAGE 3 OF 11 PART II SUBJECT: Vertical Fin Corrosion Protection MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-18-150 Super Cub 1809001 through 1809011 1809013 through 1809032 1809034 through 1809038 1809043 through 1809045 1809047, 1809050 through 1809052 1809054 COMPLIANCE TIME: Within the next six (6) months or at the next regularly scheduled maintenance event. whichever occurs first. PURPOSE· PART II of this Service Bulletin requires the complete sealing of the forward and aft tubes of the vertical fin (leading edge and tail posts). INSTRUCTIONS: 1. On the top aft portion of the vertical fin, cut a hole in the fabric to allow entrance to the aft post of the fin (the aft post is open-ended at this point). Per manufacturer's instructions, thoroughly mix a sufficient amount of Thiokol MC-236 (or equivalent) sealant and fill the aft post completely. NOTE: Once the sealant begins to exit the bottom of the tail post, place a strip of metal, wood or phenolic to the bottom of the post to allow the sealant to dam-up and fill the post. When the sealant has jelled the strip should be removed to complete curing of the sealant. 2. After the sealant has cured, cover the hole created above the aft post using the 'dollar patch' technique. Please note that cure times may vary with ambient temperatures and weather conditions. 3. Remove the navigation antenna, if installed, at the upper forward end of the vertical fin to access the leading edge tube top. NOTE: For those aircraft not equipped with a navigation antenna, install antenna doublers, Piper Part Number 14313-00 on each side of the upper forward vertical fin. Once the adhesive is allowed to cure, cut out the inside periphery of the doublers to access the leading edge tube top. 'Q() PAGE 4 OF 11 SERVICE BULLETIN NO. 9 6 6 INSTRUCTIONS !CONT'D.l: 3. (CONT'D) Per manufacturer's instructions, thoroughly mix a sufficient amount of Thiokol MC-236 (or equivalent) sealant and fill the forward/leading edge tube completely. NOTE: When filling the forward/leading edge tube, ensure that sealant does not enter the stabilizer jackscrew mechanism at the base of the tube. 4. Re-install the navigation antenna and operationally check navigation equipment. For aircraft not . equipped with a navigation antenna, fabricate and install cover plates after the sealing operation. Cover plate size should be consistent with those o! the doublers.
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5. Paint dollar patch and the fabricated cover plates (if no navigation antenna installed) to match the color of the aircraft . 6. Make logbook entry of compliance with PART II of this Service Bulletin. MATERIAL REQUIRED: One (1) each dollar patch, two (2) each cover plates, Thiokol MC-236 Sealant, Piper PiN 279·060 (1 gal. container) as required. Material, hardware or sealants may be obtained/fabricated locally or through your local Piper Field Service Facility. Refer to the attached sketches or the Parts Catalog for appropriate part numbers. AVAILABILITY OF PARTS: Local procurement/fabrication, or your Piper Field Service Facility. EFFECTIVITY DATE: This Service Bulletin is effective upon receipt. SUMMARY: There is no factory participation applicable to this Service Bulletin. However, special pricing does apply for the Material Required in PART I. The suggested list price for the five tail surfaces of is $8,369.33 pius $238.00 crating. For 180 days from the effective date of this release, Piper will offer these five surfaces for a total of $6,695.50. In addition Piper will allow $3,000.00 credit for the old flight control surfaces when replaced and returned to Piper in the original crates of the new flight control surfaces. This offer will not be extended beyond 180 days. Please contact your Piper Field Service Facility to arrange for compliance with this Service Bulletin in accordance with the Compliance Time indicated. NOTE: If you are no longer in possession of this aircraft, please forward this information to the present Owner/Operator and notify the factory of address/ownership corrections. Changes should include model, serial number, current owner's name and address. Corrections/Changes should be directed to: Piper Aircraft Corporation Attn: Customer Services 2926 Piper Drive Vero Beach, FL 32960 SERVICE BULLETIN NO. 966 GREASE AIRCRAFT DUALITY GENERAL PURPOSL, ALL WEATHER 401-273 ~\'"'"404·887 PAGE 5 OF 11 400~ (TYPICAL RIGHT AND LEFT SIDE) 407-56' (TYPICAL RIGHT AND LEFT SIDE} 404-887 (TYPICAL RIGHT AND LEFT SIDE} HARDWARE part No. 400-443 407-564 404-887 STABIL'lZER INSTAUATION Nom!I!!C!a!ure auantHv Bolt-AN3-12A Washer-AN960-10 Nut- MS20 3 65-1 03 2 C 4 4 4 A. Identify the LEFT stabilizer and lay it on a suitable work surface. Apply a thin coat of all weather grease to the inside ends of the front and rear stabilizer tubes, then install the front and rear liner tubes in their proper locations and secure with the same hardware as removed. B. Apply a thin coat of grease to the exposed ends of the liner tubes then install the stabilizer onto the aircraft until the stabilizer is tight against the mounting brackets. C. Apply grease to the inside of the front and rear tubes of the RIGHT stabilizer and install it onto the ends of the liner tubes that protrude from the side of the fuselage. It may be necessary to have a second person hold the left stabilizer as a back up. D. Make sure the drain grommets on the trailing edges of both stabilizers are on the bottom of both surfaces. SKETCH 1 - STABILIZER INSTALLATION PAGE 6 OF 11 SERVICE BULLETIN NO. 966 401·274 \..~=~:~ ~ 10556-00.2 ~82732.072 e-- ---.ol07-56~ ~404-887 =~~·: HARDWARE STABILIZER INSTALLATION ®--- 1 Pan No. Nomenclature O!!l!nlhll 407-56--4 401-266 Bolt - AN3·5A 2 401-274 Bolt- AN3·15A 2 401-315 Boh • AN4·15A 1 404-887 Nul- MS20365-1032C 4 404-888 Nut • MS20365-42BC 2 407-564 Washer. AN960·10 4 40131..003 Radius Washer 2 82732.072 Bushing 4 SKETCH 2- STABILIZER INSTALLATION SERVICE BULLETIN NO. 966 PAGE 7 OF 11 A. Place the tail of the aircraft on a sawhorse so the stabilizers are at a comfortable height, then place a level across the rear seat cross tube and level the fuselage laterally by deflating a tire. B. Place a 30 inch level on top of the LEFT stabilizer trailing edge tube and adjust the lower brace wire end fittings evenly while lifting up on the stabilizer until the surface is level. C. Level the RIGHT stabilizer in the same manner as the left, making sure that equal threads are exposed at each end of the lower wires. D. Tighten both upper wires evenly and recheck the levelness of the horizontal stabilizers but do not bother with the vertical fin at this time. E. When the stabilizers are level tighten all wires evenly until a deflection of 1i2 inch yields 10 pounds when the middle of one of the upper and lower wires is pulled in a 90 degree direction with a fish scale. F. Adjust the vcrtica! fin to a perpendicu!ar position by placing the level vertically along side of the fin trailing edge tube and mcve the upper portion of the fin to the left or right by loosing one of the upper wires and tightening the other wire equally to maintain the wire tension but yet move the fin to a perfectly vertical position. G. Make sure all (8) jam nuts on the wire end fittings are tightened snugly. SKETCH 3- STABILIZER INSTALLATION AND RIGGING PAGE 8 OF 11 HARDWARE: 424-224 . 400-003 400-053 401-266 Nomenclature Quantity Pin -AN394-55 stl. fit. head. 4 Bolt - AN4-6A 1 Bolt- AN3-6 1 Bolt - AN3-5A6 1 SE.RVICE BULLETIN NO. 966 NOTE: Identify the lett and right e~vatora •nd verity thai the drain grommefls ilfll on the bottom trding edge of each one. HARDWARE ELEVATOR INSTALLATION (cont.) Part No. 407-565 407-564 408-445 404-888 404-100 404-887 424-051 Nomenclature Washer- AN960-416 Washer- AN960-1 o Washer- PIN 80122-86 Nut - MS20365-428C Nut - AN31 0-3 Nut- MS2036S-1032C Colter Pin - AN380-2-2 Quantity 2 4 8 1 1 1 4 SKETCH 4- ELEVATOR INSTALLATION SERVICE BULLETIN NO. 966 PAGE 9 OF 11 ELEVATOR HORN YOKE ASSEMBLY STABiliZER ADJUSTMENT STABILIZER AJUSTMENT CABLE SKETCH 5 - BUNGEE INSTALLATION PAGE 10 OF 11 HARDWARE: RUDDER INSTALLATION Part No. Nomenclature Quantity 400-672 Bolt- AN23-10 2 407-564 Washer- AN960-10 2 404-100 Nut- AN310-3 2 42~51 Cotter Pin - AN380-2-2 2 424-224 Pin - AN394-55 stl. fit. head 2 408-445 Washer- AN960- 4 424-051 Cotter Pin- AN380-2-2 4 SERVICE BULLETIN NO. 966 RUDDER RUDDER HORN AND CABLE ATIACHMENT. NOTE: NO RUDDER CABLE TENSION SEE NOTE 424-224 [TYPICAL 2 PLACeS) SKETCH 6 - RUDDER INSTALLATION SERVICE BULLETIN NO. 966 PAGE110F11 l FUSELAGE TAilWHEa ASSEMBLY SKETCH 7 • TAILWHEEL STEERING INSTALLATION