AD 94-21-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | DHC-8-102 | Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes |
| aircraft | Bombardier Inc. | DHC-8-103 | Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes |
| aircraft | Bombardier Inc. | DHC-8-106 | Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes |
Unsafe Condition
The potentiometer stops installed on the nose wheel steering are too short to limit excessive uncontrolled potentiometer movement in the event of a mechanical link failure between the rudder pedals and the potentiometer.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Modify the potentiometer lever stops on the nose wheel steering in accordance with de Havilland Service Bulletin S.B. 8-32-99, Revision 'A,' dated July 26, 1993. An alternative method of compliance or adjustment of the compliance time may be used if approved by the FAA.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 6 months after the effective date of this AD (November 14, 1994).
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
de Havilland Model DHC-8-102, -103, and -106 series airplanes, serial numbers 003 through 334 inclusive.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Nose Wheel Steering
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_94-21-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 94-21-01 Document Type: AD Final Rules Docket Number: 94-NM-06-AD Subject Heading: Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes Subject: Nose Wheel Steering Status: Current Citation: Federal Register: October 13, 1994 (Volume 59, Number 197) Citation Publish Date: 10/13/1994 Effective Date: 11/14/1994 Make: Bombardier Inc. Model: DHC-8-102 | DHC-8-103 | DHC-8-106 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 94-21-01 CITATION: [Federal Register: October 13, 1994 (Volume 59, Number 197)] PAGE NUMBER: [Page 51840] DOCKET NUMBER: 94-NM-06-AD AMENDMENT: 39-9044 AD NUMBER: 94-21-01 SUBJECT HEADING: Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 series airplanes, that requires modification of the potentiometer lever stops on the nose wheel steering. This amendment is prompted by a report that the potentiometer stops installed currently on these airplanes are too short to limit excessive uncontrolled potentiometer movement in the event of a mechanical link failure. The actions specified by this AD are intended to prevent the airplane from departing the runway during takeoff or landing in the event of the failure of the mechanical link between the rudder pedals and the potentiometer. DATES: Effective November 14, 1994. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 14, 1994. ADDRESSES: The service information referenced in this AD may be obtained from Bombardier Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Bradford Chin, Electronics Engineer, Systems and Equipment Branch, ANE-173, FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6427; fax (516) 791-9024. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8-100 series airplanes was published in the Federal Register on April 7, 1994 (59 FR 16574). That action proposed to require modification of the potentiometer lever stops on the nose wheel steering. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. The commenter supports the rule. After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that 48 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. The cost for required parts will be minimal. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $7,920, or $165 per airplane. The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 94-21-01 DE HAVILLAND, INC.: Amendment 39-9044. Docket 94-NM-06-AD. Applicability: Model DHC-8-102, -103, and -106 series airplanes, serial numbers 003 through 334 inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the airplane from departing the runway during takeoff or landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the potentiometer lever stops on the nose wheel steering in accordance with de Havilland Service Bulletin S.B. 8- 32-99, Revision 'A,' dated July 26, 1993. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with de Havilland Service Bulletin S.B. 8-32-99, Revision 'A,' dated July 26, 1993. 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 Bombardier Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 14, 1994. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_94-21-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 94-21-01 Document Type: AD Final Rules Docket Number: 94-NM-06-AD Subject Heading: Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes Subject: Nose Wheel Steering Status: Current Citation: Federal Register: October 13, 1994 (Volume 59, Number 197) Citation Publish Date: 10/13/1994 Effective Date: 11/14/1994 Make: Bombardier Inc. Model: DHC-8-102 | DHC-8-103 | DHC-8-106 Product Type: Aircraft Product Subtype: 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: 94-21-01 CITATION: [Federal Register: October 13, 1994 (Volume 59, Number 197)] PAGE NUMBER: [Page 51840] DOCKET NUMBER: 94-NM-06-AD AMENDMENT: 39-9044 AD NUMBER: 94-21-01 SUBJECT HEADING: Airworthiness Directives; de Havilland Model DHC-8-100 Series Airplanes ACTION: Final rule SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 series airplanes, that requires modification of the potentiometer lever stops on the nose wheel steering. This amendment is prompted by a report that the potentiometer stops installed currently on these airplanes are too short to limit excessive uncontrolled potentiometer movement in the event of a mechanical link failure. The actions specified by this AD are intended to prevent the airplane from departing the runway during takeoff or landing in the event of the failure of the mechanical link between the rudder pedals and the potentiometer. DATES: Effective November 14, 1994. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of November 14, 1994. ADDRESSES: The service information referenced in this AD may be obtained from Bombardier Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. FOR FURTHER INFORMATION CONTACT: Bradford Chin, Electronics Engineer, Systems and Equipment Branch, ANE-173, FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6427; fax (516) 791-9024. SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain de Havilland Model DHC-8-100 series airplanes was published in the Federal Register on April 7, 1994 (59 FR 16574). That action proposed to require modification of the potentiometer lever stops on the nose wheel steering. Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received. The commenter supports the rule. After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. The FAA estimates that 48 airplanes of U.S. registry will be affected by this AD, that it will take approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $55 per work hour. The cost for required parts will be minimal. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $7,920, or $165 per airplane. The total cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES." List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39 - AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g); and 14 CFR 11.89. § 39.13 - [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: REGULATORY TEXT: 94-21-01 DE HAVILLAND, INC.: Amendment 39-9044. Docket 94-NM-06-AD. Applicability: Model DHC-8-102, -103, and -106 series airplanes, serial numbers 003 through 334 inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the airplane from departing the runway during takeoff or landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the potentiometer lever stops on the nose wheel steering in accordance with de Havilland Service Bulletin S.B. 8- 32-99, Revision 'A,' dated July 26, 1993. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with de Havilland Service Bulletin S.B. 8-32-99, Revision 'A,' dated July 26, 1993. 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 Bombardier Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 14, 1994. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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