AD 67-19-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes |
Unsafe Condition
Cracks in the horizontal stabilizer front spar web from Station 56 to 77.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the front spar web by removing access panels P/N 912-2 and P/N 913-2 (Station 52 to 59) and visually inspect for cracks from Station 56 to 77, or use an FAA-approved equivalent inspection. Repair cracked parts with an FAA-approved repair or replace with inspected or FAA-approved equivalent parts. Discontinue inspections after modifying the spar web with an FAA-approved modification.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the next 25 hours' time in service after the effective date (June 10, 1967) for stabilizers with 13,500+ hours, or before accumulating 13,525 hours' time in service for those with less than 13,500 hours. Thereafter, inspections must occur at intervals not exceeding 250 hours' time in service from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
CANADAIR Model CL-44D4 airplanes with horizontal stabilizers requiring inspection as specified.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Front Spar Web
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_67-19-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-19-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes Subject: Front Spar Web Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1967 Make: Bombardier Inc. Model: CL-44D4 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 67-19-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-431 AD NUMBER: 67-19-03 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes ACTION: SUMMARY: DATES: Effective June 10, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-19-03 CANADAIR: Amdt. 39-431, Part 39, Federal Register June 6, 1967. Applies to CL-44D4 Type airplanes. Compliance required as indicated. To detect cracks in the horizontal stabilizer front spar web, accomplish the following: (a) For horizontal stabilizers with 13,500 or more hours' time in service on the effective date of this AD inspect in accordance with (c) within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 225 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (b) For horizontal stabilizers with less than 13,500 hours' time in service on the effective date of this AD, inspect in accordance with (c) before the accumulation of 13,525 hours' time in service unless accomplished after the accumulation of 13,275 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (c) Remove the horizontal stabilizer leading edge access panels, P/N 912-2 and P/N 913-2 (Station 52 to 59), and visually inspect the front spar web for cracks from Station 56 to 77, or use an FAA-approved equivalent inspection. If a crack is found comply with (d) before further flight. (d) Repair cracked parts with an FAA-approved repair or replace the cracked part with a part of the same part number that has been inspected in accordance with (c) and found free of cracks, or with an FAA-approved equivalent part. (e) The repetitive inspection required by (a) and (b) may be discontinued when the horizontal stabilizer front spar web is modified in accordance with an FAA-approved modification. (f) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs, parts, and modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (g) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective June 10, 1967. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_67-19-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 67-19-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes Subject: Front Spar Web Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/10/1967 Make: Bombardier Inc. Model: CL-44D4 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: 67-19-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-431 AD NUMBER: 67-19-03 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Airplanes ACTION: SUMMARY: DATES: Effective June 10, 1967. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 67-19-03 CANADAIR: Amdt. 39-431, Part 39, Federal Register June 6, 1967. Applies to CL-44D4 Type airplanes. Compliance required as indicated. To detect cracks in the horizontal stabilizer front spar web, accomplish the following: (a) For horizontal stabilizers with 13,500 or more hours' time in service on the effective date of this AD inspect in accordance with (c) within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 225 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (b) For horizontal stabilizers with less than 13,500 hours' time in service on the effective date of this AD, inspect in accordance with (c) before the accumulation of 13,525 hours' time in service unless accomplished after the accumulation of 13,275 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection. (c) Remove the horizontal stabilizer leading edge access panels, P/N 912-2 and P/N 913-2 (Station 52 to 59), and visually inspect the front spar web for cracks from Station 56 to 77, or use an FAA-approved equivalent inspection. If a crack is found comply with (d) before further flight. (d) Repair cracked parts with an FAA-approved repair or replace the cracked part with a part of the same part number that has been inspected in accordance with (c) and found free of cracks, or with an FAA-approved equivalent part. (e) The repetitive inspection required by (a) and (b) may be discontinued when the horizontal stabilizer front spar web is modified in accordance with an FAA-approved modification. (f) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs, parts, and modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (g) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective June 10, 1967. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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