AD 92-17-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Embraer S.A. | EMB-110P1 | Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes |
| aircraft | Embraer S.A. | EMB-110P2 | Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes |
Unsafe Condition
Severe vibration or loss of control of the airplane caused by excessive free play and lack of rigidity of the rudder trim tab actuating system.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the rudder trim tab actuating system and install reinforcements to the vertical stabilizer rear spar within 500 hours time-in-service. Inspect the system for excessive free play within 300 hours TIS after the modification and every 300 hours TIS thereafter. If free play exceeds 1.0 mm, modify the system before further flight. If parts are unavailable, inspect at 100-hour intervals until modifications are completed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 500 hours time-in-service (TIS) for initial modification. Subsequent inspections within 300 hours TIS and every 300 hours TIS thereafter. If parts unavailable, inspections at intervals not exceeding 100 hours TIS until modifications are done.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
EMBRAER Model EMB-110 Series airplanes (all serial numbers), certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder Trim Tab Actuating System
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_92-17-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-17-02 Document Type: AD Final Rules Docket Number: 92-CE-11-AD Subject Heading: Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes Subject: Rudder Trim Tab Actuating System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/11/1992 Make: Embraer S.A. Model: EMB-110P1 | EMB-110P2 Product Type: Aircraft Product Subtype: Small/Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-17-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-CE-11-AD AMENDMENT: 39-8331 AD NUMBER: 92-17-02 SUBJECT HEADING: Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes ACTION: SUMMARY: DATES: Effective September 11, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-17-02 EMBRAER: Amendment 39-8331. Docket No. 92-CE-11-AD. Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent severe vibration or loss of control of the airplane caused by excessive free play and lack of rigidity of the rudder trim tab actuating system, accomplish the following: NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. (a) Within the next 500 hours time-in-service (TIS), modify the rudder trim tab actuating system and install reinforcements to the vertical stabilizer rear spar in accordance with the instructions in and Figures 1, 2, and 3 of EMBRAER Service Bulletin (SB) 110-027-0089, dated July 19, 1991. NOTE 2: EMBRAER SB 110-27-0089 specifies that the airplane should be modified in accordance with EMBRAER SB 110-27-0060 - "Replacement of Spherical Bearings of Aileron and Rudder Trim Tab Control Systems Rod Ends". This action is required for the affected airplanes by AD 87-01-05, Amendment 39-5490. (b) Within 300 hours TIS after accomplishing the modifications required by paragraph (a) of this AD, and thereafter at intervals not to exceed 300 hours TIS, inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. If free play exceeds 1.0 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. (c) If the parts required by paragraph (a) of this AD have been ordered, but are not available, within the initial 500 hours TIS required by paragraph (a) of this AD, accomplish the following: (1) Inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. (2) If free play exceeds 3.3 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. NOTE 3: The modification procedures in the maintenance manual for the rudder trim tab actuating system if excessive free play exists are the same whether the criteria is 1.0 mm or 3.3 mm. The only difference is the criteria for the magnitude of the free play. (3) Reinspect in accordance with paragraphs (c)(1) and (c)(2) of this AD at intervals not to exceed 100 hours TIS until the modifications required by paragraph (a) of this AD are accomplished, but not to exceed three 100-hour TIS repetitive inspection intervals. (4) When parts become available or 100 hours TIS after the third repetitive inspection required by paragraph (c)(3) of this AD, whichever occurs first, prior to further flight, accomplish the modification required by paragraph (a) of this AD. (d) 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. (e) 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 shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspections, reinforcement, and modifications required by this AD shall be done in accordance with EMBRAER Service Bulletin 110-027-0089, dated July 19, 1991. 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 EMBRAER, P.O. Box 343-CEP, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or EMBRAER Aircraft Corporation, 276 SW 34th Street, Fort Lauderdale, Florida 33315. 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, 800 North Capitol Street, N.W.; 7th Floor, Suite 700; Washington, DC. (g) This amendment becomes effective on September 11, 1992. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_92-17-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 92-17-02 Document Type: AD Final Rules Docket Number: 92-CE-11-AD Subject Heading: Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes Subject: Rudder Trim Tab Actuating System Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/11/1992 Make: Embraer S.A. Model: EMB-110P1 | EMB-110P2 Product Type: Aircraft Product Subtype: Small/Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 92-17-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 92-CE-11-AD AMENDMENT: 39-8331 AD NUMBER: 92-17-02 SUBJECT HEADING: Airworthiness Directives; EMBRAER Model EMB-110 Series Airplanes ACTION: SUMMARY: DATES: Effective September 11, 1992. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 92-17-02 EMBRAER: Amendment 39-8331. Docket No. 92-CE-11-AD. Applicability: EMB-110 Series airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent severe vibration or loss of control of the airplane caused by excessive free play and lack of rigidity of the rudder trim tab actuating system, accomplish the following: NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information. (a) Within the next 500 hours time-in-service (TIS), modify the rudder trim tab actuating system and install reinforcements to the vertical stabilizer rear spar in accordance with the instructions in and Figures 1, 2, and 3 of EMBRAER Service Bulletin (SB) 110-027-0089, dated July 19, 1991. NOTE 2: EMBRAER SB 110-27-0089 specifies that the airplane should be modified in accordance with EMBRAER SB 110-27-0060 - "Replacement of Spherical Bearings of Aileron and Rudder Trim Tab Control Systems Rod Ends". This action is required for the affected airplanes by AD 87-01-05, Amendment 39-5490. (b) Within 300 hours TIS after accomplishing the modifications required by paragraph (a) of this AD, and thereafter at intervals not to exceed 300 hours TIS, inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. If free play exceeds 1.0 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. (c) If the parts required by paragraph (a) of this AD have been ordered, but are not available, within the initial 500 hours TIS required by paragraph (a) of this AD, accomplish the following: (1) Inspect the rudder trim tab actuating system for excessive free play in accordance with the applicable maintenance manual. (2) If free play exceeds 3.3 mm., prior to further flight, modify the rudder trim tab actuating system in accordance with the applicable maintenance manual. NOTE 3: The modification procedures in the maintenance manual for the rudder trim tab actuating system if excessive free play exists are the same whether the criteria is 1.0 mm or 3.3 mm. The only difference is the criteria for the magnitude of the free play. (3) Reinspect in accordance with paragraphs (c)(1) and (c)(2) of this AD at intervals not to exceed 100 hours TIS until the modifications required by paragraph (a) of this AD are accomplished, but not to exceed three 100-hour TIS repetitive inspection intervals. (4) When parts become available or 100 hours TIS after the third repetitive inspection required by paragraph (c)(3) of this AD, whichever occurs first, prior to further flight, accomplish the modification required by paragraph (a) of this AD. (d) 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. (e) 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 shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspections, reinforcement, and modifications required by this AD shall be done in accordance with EMBRAER Service Bulletin 110-027-0089, dated July 19, 1991. 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 EMBRAER, P.O. Box 343-CEP, 12.200 Sao Jose dos Campos, Sao Paulo, Brazil; or EMBRAER Aircraft Corporation, 276 SW 34th Street, Fort Lauderdale, Florida 33315. 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, 800 North Capitol Street, N.W.; 7th Floor, Suite 700; Washington, DC. (g) This amendment becomes effective on September 11, 1992. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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