AD 70-26-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-28-140 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28-150 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28-160 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28-180 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28-235 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-180 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28R-200 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-28S-180 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-32-260 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-32-300 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
| aircraft | Piper Aircraft Inc. | PA-32S-300 | Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes |
Unsafe Condition
Cracks in the stabilator balance weight tube in the area of the attachment bolt holes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the stabilator balance weight tube assembly for cracks using dye penetrant. Remove paint from the tube's attachment bolt holes area. Replace the tube if cracks are found. Inspect stabilator mounting points and install washers if side movement is detected. Visually inspect stabilator fittings for cracks or loose rivets and replace or repair as necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated: I. Aircraft with less than 500 hours total time: inspect at 500 hours total time or within 50 hours time in service after AD effective date, then repeat every 200 hours. II. Aircraft with 500-1000 hours: inspect within 50 hours after AD effective date, then repeat every 200 hours. III. Aircraft over 1000 hours: inspect within 25 hours after AD effective date, then repeat every 200 hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Models PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300, PA-32S-300 with specific serial ranges as listed in the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Stabilizer Balance Weight Tube
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_70-26-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-26-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 20...Show more Subject: Stabilizer Balance Weight Tube Status: Current Citation: This information is not available. Citation Publish Date: 06/18/1971 Effective Date: 06/24/1971 Make: Piper Aircraft Inc. Model: PA-28-140 | PA-28-150 | PA-28-160 | PA-28-180 | PA-28-235 | PA-28R-180 | PA-28R-200 | PA-28S-180 | P...Show more Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 70-26-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1232 AD NUMBER: 70-26-04 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes ACTION: SUMMARY: DATES: Effective June 24, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-26-04 PIPER: Amdt. 39-1134 as amended by Amendment 39-1196 is further amended by Amendment 39-1232. Applies to PA-28-140, Serial Numbers 28-20000 through 28- 26946 and 28-7125000 through 28-7125334. PA-28-150-160-180 and PA-28S-180, Serial Numbers 28-1 through 28-5859 and 28- 7105001 through 28-7105126. PA-28-235, Serial Numbers 28-10001 through 28-11378 and 28-7110001 through 28- 7110011. PA-28R-180, Serial Numbers 28R-30001 through 28R-31270 and 28R-7130001 through 28R-7130005. PA-28R-200, Serial Numbers 28R-30482, 28R-35001 through 28R-35820, and 28R- 7135001 through 28R-7135104. PA-32-260, Serial Numbers 32-04, 32-1 through 32-1297, and 32-7100001 through 32- 7100016. PA-32-300 and PA-32S-300, Serial Numbers 32-15, 32-21, 32-40000 through 32-40974, and 32-7140001 through 32-7140050. Compliance required as indicated, unless already accomplished: I. Aircraft with less than 500 hours total time in service: Inspect in accordance with instructions below at 500 hours total time or within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. II. Aircraft with 500 hours through 1000 hours total time in service: Inspect in accordance with instructions below within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. III. Aircraft with more than 1000 hours time in service: Inspect in accordance with instructions below within the next 25 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. To detect cracks in the stabilator balance weight tube in the area of the attachment bolt holes accomplish the following: 1. Remove tail cone assembly and bulkhead close out plate if so equipped. 2. In the tail cone section, remove safeties from stabilator cable turnbuckles and release cable tension. 3. Disconnect stabilator cables at the balance weight tube assembly. NOTE: Care should be taken as not to misplace the bushing fitted in the tube/cable attachment lugs. 4. Remove the stabilator balance weight tube assembly attachment bolts. 5. Pull stabilator balance weight tube assembly forward and remove from stabilator. (It is not necessary to remove balance weight from tube.) 6. Remove paint from balance weight tube in areas of the stabilator attachment bolt holes. NOTE: Use any commercial paint remover or caustic soda to remove paint; wash part in gasoline to remove any wax. 7. Inspect tube for cracks in this area using dye penetrant. If a crack or cracks are detected replace the balance weight tube assembly with new part. If cracks are not detected, the part may be reinstalled on the airplane after the tube has been cleaned, primed with zinc chromate primer, and painted. NOTE: When a new balance weight tube assembly, Part Number 63578-00V, 65310-00V, or 68432-00V is installed, an initial inspection after 500 hours time in service on the assembly and repetitive inspections at 200 hour intervals will still be required. 8. Inspect stabilator mounting points for possible stabilator side movement. Should side movement be evident, install combination of AN960-416L (Piper code no. 407 585) and AN960-416 (Piper code no. 407 565) washers, as many as necessary to center the stabilator assembly and eliminate any side movement. 9. Visually inspect stabilator fittings (part no. 63567-03) for evidence of cracks and/or loose rivets. a. Should the fitting(s) be cracked, replace with new stabilator fitting(s), part no. 63567-03. b. Remove loose rivets and replace with new rivets. Piper Service Bulletin No. 327 dated 9 December 1970 pertains to this same subject. The installation of a new stabilator balance weight support tube, Part Number 69623-04V, 69623-02V, or 69624-02V, in accordance with Piper Service Letter No. 576 will eliminate the necessity for the initial and repetitive inspections required in Paragraphs I, II and III. NOTE: The above referenced new tubes may be identified by the presence of green paint on the cable attachment lugs. Amendment 39-1134 became effective December 28, 1970. Amendment 39-1196 became effective April 30, 1971. This Amendment 39-1232 becomes effective June 24, 1971. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_70-26-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 70-26-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 20...Show more Subject: Stabilizer Balance Weight Tube Status: Current Citation: This information is not available. Citation Publish Date: 06/18/1971 Effective Date: 06/24/1971 Make: Piper Aircraft Inc. Model: PA-28-140 | PA-28-150 | PA-28-160 | PA-28-180 | PA-28-235 | PA-28R-180 | PA-28R-200 | PA-28S-180 | P...Show more Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 70-26-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1232 AD NUMBER: 70-26-04 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-28-140, 150, 160, 180, 235, PA-28R-180, 200, PA-28S-180, 200, PA32-260, 300 and PA-32S-300 Airplanes ACTION: SUMMARY: DATES: Effective June 24, 1971. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 70-26-04 PIPER: Amdt. 39-1134 as amended by Amendment 39-1196 is further amended by Amendment 39-1232. Applies to PA-28-140, Serial Numbers 28-20000 through 28- 26946 and 28-7125000 through 28-7125334. PA-28-150-160-180 and PA-28S-180, Serial Numbers 28-1 through 28-5859 and 28- 7105001 through 28-7105126. PA-28-235, Serial Numbers 28-10001 through 28-11378 and 28-7110001 through 28- 7110011. PA-28R-180, Serial Numbers 28R-30001 through 28R-31270 and 28R-7130001 through 28R-7130005. PA-28R-200, Serial Numbers 28R-30482, 28R-35001 through 28R-35820, and 28R- 7135001 through 28R-7135104. PA-32-260, Serial Numbers 32-04, 32-1 through 32-1297, and 32-7100001 through 32- 7100016. PA-32-300 and PA-32S-300, Serial Numbers 32-15, 32-21, 32-40000 through 32-40974, and 32-7140001 through 32-7140050. Compliance required as indicated, unless already accomplished: I. Aircraft with less than 500 hours total time in service: Inspect in accordance with instructions below at 500 hours total time or within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. II. Aircraft with 500 hours through 1000 hours total time in service: Inspect in accordance with instructions below within the next 50 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. III. Aircraft with more than 1000 hours time in service: Inspect in accordance with instructions below within the next 25 hours time in service after the effective date of this AD and repeat after each subsequent 200 hours in service. To detect cracks in the stabilator balance weight tube in the area of the attachment bolt holes accomplish the following: 1. Remove tail cone assembly and bulkhead close out plate if so equipped. 2. In the tail cone section, remove safeties from stabilator cable turnbuckles and release cable tension. 3. Disconnect stabilator cables at the balance weight tube assembly. NOTE: Care should be taken as not to misplace the bushing fitted in the tube/cable attachment lugs. 4. Remove the stabilator balance weight tube assembly attachment bolts. 5. Pull stabilator balance weight tube assembly forward and remove from stabilator. (It is not necessary to remove balance weight from tube.) 6. Remove paint from balance weight tube in areas of the stabilator attachment bolt holes. NOTE: Use any commercial paint remover or caustic soda to remove paint; wash part in gasoline to remove any wax. 7. Inspect tube for cracks in this area using dye penetrant. If a crack or cracks are detected replace the balance weight tube assembly with new part. If cracks are not detected, the part may be reinstalled on the airplane after the tube has been cleaned, primed with zinc chromate primer, and painted. NOTE: When a new balance weight tube assembly, Part Number 63578-00V, 65310-00V, or 68432-00V is installed, an initial inspection after 500 hours time in service on the assembly and repetitive inspections at 200 hour intervals will still be required. 8. Inspect stabilator mounting points for possible stabilator side movement. Should side movement be evident, install combination of AN960-416L (Piper code no. 407 585) and AN960-416 (Piper code no. 407 565) washers, as many as necessary to center the stabilator assembly and eliminate any side movement. 9. Visually inspect stabilator fittings (part no. 63567-03) for evidence of cracks and/or loose rivets. a. Should the fitting(s) be cracked, replace with new stabilator fitting(s), part no. 63567-03. b. Remove loose rivets and replace with new rivets. Piper Service Bulletin No. 327 dated 9 December 1970 pertains to this same subject. The installation of a new stabilator balance weight support tube, Part Number 69623-04V, 69623-02V, or 69624-02V, in accordance with Piper Service Letter No. 576 will eliminate the necessity for the initial and repetitive inspections required in Paragraphs I, II and III. NOTE: The above referenced new tubes may be identified by the presence of green paint on the cable attachment lugs. Amendment 39-1134 became effective December 28, 1970. Amendment 39-1196 became effective April 30, 1971. This Amendment 39-1232 becomes effective June 24, 1971. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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