AD 81-07-05
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft |
| aircraft | Bombardier Inc. | CL-44J | Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft |
Unsafe Condition
Failure of the nose landing gear crossbeam due to cracks and corrosion.
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Required Actions
Conduct inspections for cracks and corrosion using dye penetrant and a 10-power glass, and eddy current procedure as specified in Canadair SIC No. 431-CL44. Replace or repair a cracked crossbeam prior to further flight with approved parts. Remove and reprotect corrosion, and adjust inspection intervals with FAA approval.
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Compliance Time
Within the next 30 days after the effective date of this AD, unless already accomplished within the last 60 days. Subsequent inspections at intervals not to exceed 65 hours in service or 30 days, 650 hours or 90 days, or 1300 hours or 180 days, whichever occurs first.
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Affected Aircraft
Bombardier Inc. Models CL-44D4 and CL-44J aircraft with nose landing gear crossbeam P/N 44-85082 or P/N 44-85082-2.
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Federal Register Abstract
Nose Landing Gear Crossbeam
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_81-07-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-07-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft Subject: Nose Landing Gear Crossbeam Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/31/1981 Make: Bombardier Inc. Model: CL-44D4 | CL-44J Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 81-07-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4067 AD NUMBER: 81-07-05 SUBJECT HEADING: Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft ACTION: SUMMARY: DATES: Effective March 31, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-07-05 CANADAIR: Amendment 39-4067. Applies to all Canadair Models CL-44D4 and CL44J aircraft certificated in all categories with nose landing gear crossbeam, P/N 44-85082 or P/N 44-85082-2. Compliance required as indicated. A. To prevent failure of the nose landing gear crossbeam, accomplish the following: 1. Within the next 30 days after the effective date of this AD, unless already accomplished within the last 60 days, conduct the following inspections for cracks and corrosion: (a) Using dye penetrant and a 10-power glass, inspect the forward and aft external faces as detailed in paragraph 3.2 and shown in Figure 1 of Canadair Service Information Circular (SIC) No. 431-CL44, dated June 11, 1980, or an approved equivalent inspection. (b) Using eddy current procedure, inspect the pivot pin taper bore as detailed in paragraph 3.3 and shown in Figure 2 of SIC No. 431-CL44, or an approved equivalent inspection. 2. Within the next 65 hours in service or 30 days, whichever occurs first, after the initial inspection specified in paragraph A1, conduct a visual inspection of the forward and aft external faces as detailed in paragraph 3.1 as shown in Figure 1 of SIC No. 431-CL44, or an approved equivalent inspection. 3. The inspection specified in paragraph A2 shall be repeated at intervals not to exceed 65 hours in service or 30 days, whichever occurs first, from the previous visual inspection. The inspection specified in paragraph A1(a) shall be repeated at intervals not to exceed 650 hours in service or 90 days, whichever occurs first. The inspection specified in paragraph A1(b) shall be repeated at intervals not to exceed 1300 hours in service or 180 days, whichever occurs first. B. A cracked crossbeam must be replaced prior to further flight with a part of the same number or equivalent, or repaired by an approved method. An acceptable replacement part is a Britannia crossbeam, Messier P/N 200192-302, conforming to Aviation Traders (Engineering) Limited (ATL) Modification No. 44/094 and Drawing No. 78-41-039, in accordance with paragraph 5.3 of SIC No. 431-CL44. C. Remove any corrosion found in the inspection areas and reprotect the surface in accordance with instructions in paragraph 6.0 on SIC No. 431-CL44, or equivalent. D. All replacement or repaired crossbeams must be inspected for cracks immediately prior to installation, in accordance with paragraphs A1(a), A1(b), and A2, and at repetitive intervals in accordance with paragraph A3. E. The aircraft may be flown in accordance with FAR 21.197, to a base where the inspection or repair can be performed. F. Equivalent means of accomplishing the repairs, equivalent inspections, and parts must be approved by the Chief, Aircraft Certification Division, FAA Northwest Region. G. Upon submissions of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection intervals specified in this AD. The manufacturer's specification and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Canadair Limited, P.O. Box 6087, Montreal, Quebec, Canada H3C 3G9, Attention: Mr. W. Remington, Airworthiness Coordinator. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This AD supersedes AD 74-26-03. This amendment becomes effective March 31, 1981. FOOTER:
Document Text
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AD Final Rules - DRS_81-07-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 81-07-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft Subject: Nose Landing Gear Crossbeam Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 03/31/1981 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: 81-07-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4067 AD NUMBER: 81-07-05 SUBJECT HEADING: Airworthiness Directives; CANADAIR Models CL-44D4 and CL44J Aircraft ACTION: SUMMARY: DATES: Effective March 31, 1981. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 81-07-05 CANADAIR: Amendment 39-4067. Applies to all Canadair Models CL-44D4 and CL44J aircraft certificated in all categories with nose landing gear crossbeam, P/N 44-85082 or P/N 44-85082-2. Compliance required as indicated. A. To prevent failure of the nose landing gear crossbeam, accomplish the following: 1. Within the next 30 days after the effective date of this AD, unless already accomplished within the last 60 days, conduct the following inspections for cracks and corrosion: (a) Using dye penetrant and a 10-power glass, inspect the forward and aft external faces as detailed in paragraph 3.2 and shown in Figure 1 of Canadair Service Information Circular (SIC) No. 431-CL44, dated June 11, 1980, or an approved equivalent inspection. (b) Using eddy current procedure, inspect the pivot pin taper bore as detailed in paragraph 3.3 and shown in Figure 2 of SIC No. 431-CL44, or an approved equivalent inspection. 2. Within the next 65 hours in service or 30 days, whichever occurs first, after the initial inspection specified in paragraph A1, conduct a visual inspection of the forward and aft external faces as detailed in paragraph 3.1 as shown in Figure 1 of SIC No. 431-CL44, or an approved equivalent inspection. 3. The inspection specified in paragraph A2 shall be repeated at intervals not to exceed 65 hours in service or 30 days, whichever occurs first, from the previous visual inspection. The inspection specified in paragraph A1(a) shall be repeated at intervals not to exceed 650 hours in service or 90 days, whichever occurs first. The inspection specified in paragraph A1(b) shall be repeated at intervals not to exceed 1300 hours in service or 180 days, whichever occurs first. B. A cracked crossbeam must be replaced prior to further flight with a part of the same number or equivalent, or repaired by an approved method. An acceptable replacement part is a Britannia crossbeam, Messier P/N 200192-302, conforming to Aviation Traders (Engineering) Limited (ATL) Modification No. 44/094 and Drawing No. 78-41-039, in accordance with paragraph 5.3 of SIC No. 431-CL44. C. Remove any corrosion found in the inspection areas and reprotect the surface in accordance with instructions in paragraph 6.0 on SIC No. 431-CL44, or equivalent. D. All replacement or repaired crossbeams must be inspected for cracks immediately prior to installation, in accordance with paragraphs A1(a), A1(b), and A2, and at repetitive intervals in accordance with paragraph A3. E. The aircraft may be flown in accordance with FAR 21.197, to a base where the inspection or repair can be performed. F. Equivalent means of accomplishing the repairs, equivalent inspections, and parts must be approved by the Chief, Aircraft Certification Division, FAA Northwest Region. G. Upon submissions of substantiating data by an owner or operator, through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the inspection intervals specified in this AD. The manufacturer's specification and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Canadair Limited, P.O. Box 6087, Montreal, Quebec, Canada H3C 3G9, Attention: Mr. W. Remington, Airworthiness Coordinator. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This AD supersedes AD 74-26-03. This amendment becomes effective March 31, 1981. FOOTER:
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