AD 86-26-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | DHC-8-101 | Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes |
| aircraft | Bombardier Inc. | DHC-8-102 | Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes |
Unsafe Condition
Failure of the fore rudder upper and lower mounting brackets and fin rear spar web.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Within 100 hours time-in-service after the effective date, and every 200 hours thereafter, conduct visual inspections of the mounting brackets per SB 8-55-7. If cracks are found, inspect the spar web and reinforce brackets with Modification 8/0647. Replace cracked spar web with new web or approved repair. Install Modification 8/0647 within 500 hours time-in-service. Special flight permits may be issued under FAR 21.197/199.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service. Within 500 hours time-in-service after the effective date for Modification 8/0647 installation.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
DeHavilland Model DHC-8-101 and -102 series airplanes equipped with upper and lower fore rudder mounting brackets P/N 85530097-105 and -107.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Rudder Mounting Brackets
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_86-26-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 86-26-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes Subject: Rudder Mounting Brackets Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/05/1987 Make: Bombardier Inc. Model: DHC-8-101 | DHC-8-102 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 86-26-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5496 AD NUMBER: 86-26-01 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes ACTION: SUMMARY: DATES: Effective January 5, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 86-26-01 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5496. Applies to all Model DHC-8-101 and - 102 series airplanes, certificated in any category, equipped with upper and lower fore rudder mounting brackets, P/N's 85530097-105 and -107. Compliance required as indicated, unless previously accomplished. To prevent the failure of the fore rudder upper and lower mounting brackets and fin rear spar web accomplish the following: A. Within the next 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service, conduct a visual inspection of the upper and lower fore rudder mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 1. If cracks are found in the mounting brackets, prior to further flight: a. Conduct a visual inspection of the upper spar web for cracks in the vicinity of the mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. b. Reinforce the fore rudder mounting brackets by installing de Havilland Modifications 8/0647 in accordance with the Accomplishment Instruction of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 2. If, after accomplishing the visual inspection required by paragraph A.1.a., above, cracks are found in the spar web, prior to further flight, replace the cracked spar web with a new web in accordance with de Havilland Dash 8 Maintenance Manual (PSM 1-8-2), or accomplish an FAA-approved repair. B. Within 500 hours time-in-service after the effective date of this AD, install de Havilland Modification 8/0647 in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. Prior to installation of Modification 8/0647, conduct the visual inspections required by paragraph A., above, and perform the repair required by paragraph A.2., above, if necessary. C. Incorporation of de Havilland Modification 8/0647 constitutes terminating action for the repetitive inspection of paragraph A.., above. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division of Boeing of Canada Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective January 5, 1987. FOOTER:
Document Text
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AD Final Rules - DRS_86-26-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 86-26-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes Subject: Rudder Mounting Brackets Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/05/1987 Make: Bombardier Inc. Model: DHC-8-101 | DHC-8-102 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: 86-26-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5496 AD NUMBER: 86-26-01 SUBJECT HEADING: Airworthiness Directives; DeHavilland Model DHC-8-101 and -102 Series Airplanes ACTION: SUMMARY: DATES: Effective January 5, 1987. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 86-26-01 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5496. Applies to all Model DHC-8-101 and - 102 series airplanes, certificated in any category, equipped with upper and lower fore rudder mounting brackets, P/N's 85530097-105 and -107. Compliance required as indicated, unless previously accomplished. To prevent the failure of the fore rudder upper and lower mounting brackets and fin rear spar web accomplish the following: A. Within the next 100 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 200 hours time-in-service, conduct a visual inspection of the upper and lower fore rudder mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 1. If cracks are found in the mounting brackets, prior to further flight: a. Conduct a visual inspection of the upper spar web for cracks in the vicinity of the mounting brackets in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. b. Reinforce the fore rudder mounting brackets by installing de Havilland Modifications 8/0647 in accordance with the Accomplishment Instruction of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. 2. If, after accomplishing the visual inspection required by paragraph A.1.a., above, cracks are found in the spar web, prior to further flight, replace the cracked spar web with a new web in accordance with de Havilland Dash 8 Maintenance Manual (PSM 1-8-2), or accomplish an FAA-approved repair. B. Within 500 hours time-in-service after the effective date of this AD, install de Havilland Modification 8/0647 in accordance with the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin No. 8-55-7, dated October 3, 1986. Prior to installation of Modification 8/0647, conduct the visual inspections required by paragraph A., above, and perform the repair required by paragraph A.2., above, if necessary. C. Incorporation of de Havilland Modification 8/0647 constitutes terminating action for the repetitive inspection of paragraph A.., above. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division of Boeing of Canada Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment becomes effective January 5, 1987. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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