AD 92-08-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-34-200 | Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes |
| aircraft | Piper Aircraft Inc. | PA-34-200T | Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes |
| aircraft | Piper Aircraft Inc. | PA-34-220T | Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes |
Unsafe Condition
Failure of the torque tube fitting and possible loss of rudder control.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the rudder torque tube fitting to determine if it is steel or aluminum within 50 hours time-in-service after September 14, 1990. If steel, inspect attachment and check bolt torque per Piper SB No. 899. If aluminum, replace with steel fitting before further flight. If steel fitting unavailable, inspect for corrosion and cracks, and perform repetitive inspections every 50 hours TIS. Follow SB No. 899 for installations and use AC 43-13.1A for corrosion treatment.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 50 hours time-in-service after September 14, 1990
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Aircraft Corporation Model PA34-200 (S/N 34-7250001 through 34-7450220), PA34-200T (S/N 34-7570001 through 34-8170092), and PA34-220T (S/N 34-8133001 through 34-8533012)
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder System
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-08-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-08-04 Document Type: AD Final Rules Docket Number: 91-CE-71-AD Subject Heading: Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes Subject: Rudder System Status: Current Citation: This information is not available. Citation Publish Date: 04/15/1992 Effective Date: 05/15/1992 Make: Piper Aircraft Inc. Model: PA-34-200 | PA-34-200T | PA-34-220T Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety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: 92-08-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-CE-71-AD AMENDMENT: 39-8215 AD NUMBER: 92-08-04 SUBJECT HEADING: Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes ACTION: SUMMARY: DATES: Effective May 15, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-08-04 PIPER AIRCRAFT CORPORATION: Amendment 39-8215. Docket No. 91-CE-71-AD. Supersedes AD 90-17-04, Amendment 39-6674. Applicability: Model PA34-200 airplanes (serial numbers (S/N) 34-7250001 through 34-7450220), Model PA34-200T airplanes (S/N 34-7570001 through 34-8170092), and Model PA34-220T airplanes (S/N 34-8133001 through 34-8533012), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the torque tube fitting and possible loss of rudder control, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after September 14, 1990 (the effective date of AD 90-17-04, Amendment 39-6674), inspect to determine whether the rudder torque tube fitting is steel or aluminum. (1) If steel, inspect for proper attachment, and check the bolt torque in accordance with the criteria and instructions in Piper Service Bulletin (SB) No. 899, dated February 10, 1989. If fitting is improperly attached and bolt torque is incorrect, prior to further flight, properly attach fitting and torque to proper criteria as specified in and in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (2) If aluminum, prior to further flight, replace with steel fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (b) If the steel fitting required by paragraph (a)(2) of this AD has been ordered but is not available, prior to further flight, accomplish the following: (1) Visually inspect the aluminum fitting for corrosion. If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (2) Dye penetrant inspect the aluminum fitting for cracks. If found cracked, replace with an aluminum fitting found to be free from cracks and corrosion. (3) Visually inspect the aluminum fitting for proper attachment, cracks, and corrosion at intervals not to exceed 50 hours TIS. (i) If fitting is found improperly attached or hardware is found loose, properly attach fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (ii) If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (iii) If found cracked, replace with aluminum fitting found to be free from cracks and corrosion in accordance with the installation instructions in Piper SB No. 899, dated February 10, 1989. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The checks and installations required by this AD shall be done in accordance with Piper Service Bulletin No. 899, dated February 10, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8215) supersedes AD 90-17-04, Amendment 39-6674. (g) This amendment (39-8215) becomes effective on May 15, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-08-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-08-04 Document Type: AD Final Rules Docket Number: 91-CE-71-AD Subject Heading: Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes Subject: Rudder System Status: Current Citation: This information is not available. Citation Publish Date: 04/15/1992 Effective Date: 05/15/1992 Make: Piper Aircraft Inc. Model: PA-34-200 | PA-34-200T | PA-34-220T 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: 92-08-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 91-CE-71-AD AMENDMENT: 39-8215 AD NUMBER: 92-08-04 SUBJECT HEADING: Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA34-200, PA34-200T and PA34-220T Airplanes ACTION: SUMMARY: DATES: Effective May 15, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-08-04 PIPER AIRCRAFT CORPORATION: Amendment 39-8215. Docket No. 91-CE-71-AD. Supersedes AD 90-17-04, Amendment 39-6674. Applicability: Model PA34-200 airplanes (serial numbers (S/N) 34-7250001 through 34-7450220), Model PA34-200T airplanes (S/N 34-7570001 through 34-8170092), and Model PA34-220T airplanes (S/N 34-8133001 through 34-8533012), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the torque tube fitting and possible loss of rudder control, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after September 14, 1990 (the effective date of AD 90-17-04, Amendment 39-6674), inspect to determine whether the rudder torque tube fitting is steel or aluminum. (1) If steel, inspect for proper attachment, and check the bolt torque in accordance with the criteria and instructions in Piper Service Bulletin (SB) No. 899, dated February 10, 1989. If fitting is improperly attached and bolt torque is incorrect, prior to further flight, properly attach fitting and torque to proper criteria as specified in and in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (2) If aluminum, prior to further flight, replace with steel fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (b) If the steel fitting required by paragraph (a)(2) of this AD has been ordered but is not available, prior to further flight, accomplish the following: (1) Visually inspect the aluminum fitting for corrosion. If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (2) Dye penetrant inspect the aluminum fitting for cracks. If found cracked, replace with an aluminum fitting found to be free from cracks and corrosion. (3) Visually inspect the aluminum fitting for proper attachment, cracks, and corrosion at intervals not to exceed 50 hours TIS. (i) If fitting is found improperly attached or hardware is found loose, properly attach fitting in accordance with the instructions in Piper SB No. 899, dated February 10, 1989. (ii) If any evidence of corrosion is found, remove and treat the corroded area in accordance with AC 43-13.1A. (iii) If found cracked, replace with aluminum fitting found to be free from cracks and corrosion in accordance with the installation instructions in Piper SB No. 899, dated February 10, 1989. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (e) The checks and installations required by this AD shall be done in accordance with Piper Service Bulletin No. 899, dated February 10, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (f) This amendment (39-8215) supersedes AD 90-17-04, Amendment 39-6674. (g) This amendment (39-8215) becomes effective on May 15, 1992. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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