AD 73-13-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-34-200 | Airworthiness Directives; Piper Model PA-34-200 Airplanes |
Unsafe Condition
Excessive rudder trim tab free play due to wear in the travel control arm assembly bolt holes or end play in the rudder trim barrel, which could lead to loss of rudder control.
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Required Actions
Within 10 hours time in service after the effective date, determine rudder trim tab free play by measuring displacement in both directions and ensuring it does not exceed 0.125 inches. If free play exceeds 0.125 inches, inspect and replace worn travel control arm assembly (P/N 96220-00) and check rudder trim barrel (P/N 96596-00) for end play, shimming as needed. After adjustments, re-check free play. Repeat inspections every 100 hours time in service unless modified with P/N 760800V.
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Compliance Time
within the next 10 hours time in service after the effective date of this AD
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Affected Aircraft
Piper Model PA-34-200 'Seneca' airplanes, serial numbers 34-E4, 34-7250001 and up.
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Federal Register Abstract
Rudder Trim Tab
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_73-13-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-13-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-34-200 Airplanes Subject: Rudder Trim Tab Status: Current Citation: This information is not available. Citation Publish Date: 09/19/1974 Effective Date: 09/30/1974 Make: Piper Aircraft Inc. Model: PA-34-200 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part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: 73-13-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1964 AD NUMBER: 73-13-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-34-200 Airplanes ACTION: SUMMARY: DATES: Effective September 30, 1974. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-13-01 PIPER: Amendment 39-1665 as amended by Amendment 39-1936 is further amended by Amendment 39-1964. Applies to all Piper Model PA-34-200 "Seneca" airplanes, S/Ns 34-E4, 34-7250001 and up. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, determine the rudder trim tab "free play" as follows: (1) Adjust rudder trim tab to neutral position with rudder trim wheel. (2) Index tab to rudder. Use straight edge at trailing edge, making marks on rudder and tab that coincide. (3) Hold light finger pressure against rudder tab in one direction and measure distance between marks. (4) Reverse direction of finger pressure on rudder tab and measure distance between marks. (5) "Free play" of the rudder tab is the sum of the distances measured in (3) and (4) above and should not exceed .125 inches. (b) If rudder tab "free play" exceeds .125 inches, check the travel control arm assembly, P/N 96220-00 (Ref. Fig. 60, PA-34 parts catalog), for wear at the center bolt and at the bolt attaching the rudder trim rod assembly to the control arm. Replace the arm assembly and associated hardware if there is any noticeable wear or elongation of the bolt holes. (c) Also check for end play in the rudder trim barrel, P/N 96596-00 (Ref. Fig. 34, PA-34 parts catalog). If end play exists, shim between the forward barrel mount support assembly and barrel. Reduce end play to the minimum amount attainable without causing excessive system friction. Note: Shim (P/N 62833-18V) is a laminate made of 10 pieces of .002 inch brass shim stock, although it appears to be one solid piece. The proper thickness of shim material may be obtained by pealing off layers as required. (d) Upon completion of any adjustments, re-check "free play" in accordance with the procedures of (a)(3), (a)(4), and (a)(5) to ascertain that travel is less than .125 inches. (e) Repeat the above inspection every 100 hours time in service after the initial inspection. Piper Service Bulletin No. 390A pertains to this same subject. When the airplane is modified with Piper Rudder Trim Mechanism Kit, Piper P/N 760800V, the repetitive inspections of (e) are no longer required. Piper Service Letter No. 714 pertains to this same subject. Amendment 39-1665 became effective June 18, 1973. Amendment 39-1936 became effective August 30, 1974. This Amendment 39-1964 becomes effective September 30, 1974. FOOTER:
Document Text
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AD Final Rules - DRS_73-13-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 73-13-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-34-200 Airplanes Subject: Rudder Trim Tab Status: Current Citation: This information is not available. Citation Publish Date: 09/19/1974 Effective Date: 09/30/1974 Make: Piper Aircraft Inc. Model: PA-34-200 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: 73-13-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-1964 AD NUMBER: 73-13-01 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-34-200 Airplanes ACTION: SUMMARY: DATES: Effective September 30, 1974. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 73-13-01 PIPER: Amendment 39-1665 as amended by Amendment 39-1936 is further amended by Amendment 39-1964. Applies to all Piper Model PA-34-200 "Seneca" airplanes, S/Ns 34-E4, 34-7250001 and up. Compliance required as indicated. (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, determine the rudder trim tab "free play" as follows: (1) Adjust rudder trim tab to neutral position with rudder trim wheel. (2) Index tab to rudder. Use straight edge at trailing edge, making marks on rudder and tab that coincide. (3) Hold light finger pressure against rudder tab in one direction and measure distance between marks. (4) Reverse direction of finger pressure on rudder tab and measure distance between marks. (5) "Free play" of the rudder tab is the sum of the distances measured in (3) and (4) above and should not exceed .125 inches. (b) If rudder tab "free play" exceeds .125 inches, check the travel control arm assembly, P/N 96220-00 (Ref. Fig. 60, PA-34 parts catalog), for wear at the center bolt and at the bolt attaching the rudder trim rod assembly to the control arm. Replace the arm assembly and associated hardware if there is any noticeable wear or elongation of the bolt holes. (c) Also check for end play in the rudder trim barrel, P/N 96596-00 (Ref. Fig. 34, PA-34 parts catalog). If end play exists, shim between the forward barrel mount support assembly and barrel. Reduce end play to the minimum amount attainable without causing excessive system friction. Note: Shim (P/N 62833-18V) is a laminate made of 10 pieces of .002 inch brass shim stock, although it appears to be one solid piece. The proper thickness of shim material may be obtained by pealing off layers as required. (d) Upon completion of any adjustments, re-check "free play" in accordance with the procedures of (a)(3), (a)(4), and (a)(5) to ascertain that travel is less than .125 inches. (e) Repeat the above inspection every 100 hours time in service after the initial inspection. Piper Service Bulletin No. 390A pertains to this same subject. When the airplane is modified with Piper Rudder Trim Mechanism Kit, Piper P/N 760800V, the repetitive inspections of (e) are no longer required. Piper Service Letter No. 714 pertains to this same subject. Amendment 39-1665 became effective June 18, 1973. Amendment 39-1936 became effective August 30, 1974. This Amendment 39-1964 becomes effective September 30, 1974. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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