AD 89-04-07
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes |
| aircraft | Bombardier Inc. | CL-44J | Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes |
Unsafe Condition
Wing failure due to exfoliation corrosion on the wing upper skin.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a visual inspection of the upper wing skin area between the front and rear spars over the total wing span for corrosion, including raised blistering or bulging, in accordance with Canadair Alert Wire 44T-1340/2431. If corrosion exceeds 20 sq.in. in any one skin panel, conduct a non-destructive testing inspection and repair prior to further flight. If corrosion is 20 sq.in. or less, repair within 900 hours time-in-service or 6 months. Submit inspection results to Canadair.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 225 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 12 months.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bombardier Inc. Model CL-44D4 and CL-44J series airplanes, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Upper Wing Skin
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_89-04-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-04-07 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes Subject: Upper Wing Skin Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/07/1989 Make: Bombardier Inc. Model: CL-44D4 | CL-44J Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 89-04-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6141 AD NUMBER: 89-04-07 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes ACTION: SUMMARY: DATES: Effective March 7, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-04-07 CANADAIR: Amendment 39-6141. Applicability: Model CL-44D4 and CL-44J series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent wing failure due to exfoliation corrosion on the wing upper skin, accomplish the following: A. Within 225 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 12 months, perform a visual inspection of the upper wing skin area between the front and rear spars over the total wing span for corrosion, including raised blistering or bulging, in accordance with Canadair Alert Wire 44T-1340/2431, dated October 28, 1988. 1. If the extent of such corrosion exceeds 20 sq.in. in any one skin panel, between chordwise joints, prior to further flight conduct a non-destructive testing (NDT) inspection, using ultrasonic or eddy current inspection techniques, to determine the skin thickness, in accordance with the Alert Wire. Repair the corrosion area prior to further flight, in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. 2. If the extent of such corrosion exists within an area equal to or less than 20 sq.in. in any one skin panel, between chordwise joints, repair corrosion area within 900 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first. Repair must be accomplished in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. B. Within 48 hours after performing the inspections required by paragraph A., above, submit a report of results to Canadair, in accordance with Canadair Alert Wire 44T- 1340/2431, dated October 28, 1988. The report must include information as to the extent and location of the corrosion, and the inspection method used. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of 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 Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6141, AD 89-04-07) becomes effective March 7, 1989. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_89-04-07.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-04-07 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes Subject: Upper Wing Skin Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/07/1989 Make: Bombardier Inc. Model: CL-44D4 | CL-44J 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: 89-04-07 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-6141 AD NUMBER: 89-04-07 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 and CL-44J Series Airplanes ACTION: SUMMARY: DATES: Effective March 7, 1989. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-04-07 CANADAIR: Amendment 39-6141. Applicability: Model CL-44D4 and CL-44J series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent wing failure due to exfoliation corrosion on the wing upper skin, accomplish the following: A. Within 225 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 12 months, perform a visual inspection of the upper wing skin area between the front and rear spars over the total wing span for corrosion, including raised blistering or bulging, in accordance with Canadair Alert Wire 44T-1340/2431, dated October 28, 1988. 1. If the extent of such corrosion exceeds 20 sq.in. in any one skin panel, between chordwise joints, prior to further flight conduct a non-destructive testing (NDT) inspection, using ultrasonic or eddy current inspection techniques, to determine the skin thickness, in accordance with the Alert Wire. Repair the corrosion area prior to further flight, in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. 2. If the extent of such corrosion exists within an area equal to or less than 20 sq.in. in any one skin panel, between chordwise joints, repair corrosion area within 900 hours time-in-service or 6 months after the effective date of this AD, whichever occurs first. Repair must be accomplished in accordance with a method approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. B. Within 48 hours after performing the inspections required by paragraph A., above, submit a report of results to Canadair, in accordance with Canadair Alert Wire 44T- 1340/2431, dated October 28, 1988. The report must include information as to the extent and location of the corrosion, and the inspection method used. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of 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 Bombardier, Inc., Canadair Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6141, AD 89-04-07) becomes effective March 7, 1989. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.