AD 62-22-03
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 744 | Airworthiness Directives; VICKERS Model 700 Series Aircraft |
| aircraft | Vickers-Armstrongs (Aircraft Limited) | Viscount 745D | Airworthiness Directives; VICKERS Model 700 Series Aircraft |
Unsafe Condition
Wing flap attachment difficulties due to cracking of bolts and flap support attachment fittings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace specific bolts with new ones every 1,500 or 2,500 landings depending on part number. Inspect for cracks in flap support attachment fittings at specified intervals. Incorporate Modification D.2175 within 400 hours' time in service and replace cracked fittings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Compliance required as indicated.
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Affected Aircraft
Vickers-Armstrongs (Aircraft Limited) Viscount 700 Series Aircraft (Viscount 744, Viscount 745D models).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Flap Attachment
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_62-22-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-22-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; VICKERS Model 700 Series Aircraft Subject: Wing Flap Attachment Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/06/1962 Make: Vickers-Armstrongs (Aircraft Limited) Model: Viscount 744 | Viscount 745D Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 62-22-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-22-03 SUBJECT HEADING: Airworthiness Directives; VICKERS Model 700 Series Aircraft ACTION: SUMMARY: DATES: Effective November 6, 1962. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-22-03 VICKERS: Amdt. 491 Part 507 Federal Register October 5, 1962. Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. As a result of wing flap attachment difficulties the following is required for both flap assemblies: (a) (1) Replace bolts P/N's 72403-2445, 70103-2645, and 70103-2639, at flap support bracket units Nos. 2 and 3 respectively, right and left side with new bolts every 1,500 landings. (2) Replace bolts P/N's 70003-2359 and 70107-467, at flap support bracket units Nos. 1 and 4 respectively, right and left side with new bolts every 2,500 landings. (3) When Modification D.2175 is incorporated and provided the bolts referred to in paragraphs (a)(1) and (a)(2) are replaced with new bolts at the same time, the life of these new bolts is extended as specified in the overhaul schedule listed below: Part Number 72403-2445 - Retirement time 4,500 landings Part Number 70103-2645 - Retirement time 4,500 landings Part Number 70103-2639 - Retirement time 4,500 landings Part Number 70003-2359 - Retirement time 7,500 landings Part Number 70107-467 - Retirement time 7,500 landings (b) Flap beam (supporting bracket) attachment fitting at wing trailing edge false spar member inspection. (1) Within the next 135 hours' time in service after the effective date of this AD and each 135 hours' time in service thereafter, visually inspect for cracks all four lower flap support attachment fittings aft of the wing trailing edge member (false spar) on the right and left sides. The initial inspection is not required if these fittings were thoroughly examined at the time of bolt replacement of paragraph (a). (2) Within the next 385 hours' time in service after the effective date of this AD and each 1,080 hours' time in service thereafter, visually inspect for cracks all the flap support attachment fittings forward of the trailing edge member (false spar), top and bottom, right and left sides at flap positions 2 and 3. (3) Within the next 385 hours' time in service after the effective date of this AD and each 385 hours' time in service thereafter, visually inspect for cracks all top beam attachment fittings aft of the trailing edge member (false spar) on the right and left sides. (c) Replace cracked fittings. (d) Incorporated Vickers Modification D.2175 within the next 400 hours' time in service after the effective date of this AD on aircraft exceeding 3,000 landings, or within 400 hours' time in service upon the accumulation of 3,000 landings on aircraft not exceeding 3,000 landings on the effective date of this AD. Upon incorporation of this modification, the inspections called for in (b)(1), (b)(2), and (b)(3) may be discontinued. (Vickers Viscount 700 Series PTL No. 151, Issue 4 covers this subject.) This supersedes AD 57-07-03. This directive effective November 6, 1962. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_62-22-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-22-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; VICKERS Model 700 Series Aircraft Subject: Wing Flap Attachment Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/06/1962 Make: Vickers-Armstrongs (Aircraft Limited) Model: Viscount 744 | Viscount 745D 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: 62-22-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-22-03 SUBJECT HEADING: Airworthiness Directives; VICKERS Model 700 Series Aircraft ACTION: SUMMARY: DATES: Effective November 6, 1962. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-22-03 VICKERS: Amdt. 491 Part 507 Federal Register October 5, 1962. Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. As a result of wing flap attachment difficulties the following is required for both flap assemblies: (a) (1) Replace bolts P/N's 72403-2445, 70103-2645, and 70103-2639, at flap support bracket units Nos. 2 and 3 respectively, right and left side with new bolts every 1,500 landings. (2) Replace bolts P/N's 70003-2359 and 70107-467, at flap support bracket units Nos. 1 and 4 respectively, right and left side with new bolts every 2,500 landings. (3) When Modification D.2175 is incorporated and provided the bolts referred to in paragraphs (a)(1) and (a)(2) are replaced with new bolts at the same time, the life of these new bolts is extended as specified in the overhaul schedule listed below: Part Number 72403-2445 - Retirement time 4,500 landings Part Number 70103-2645 - Retirement time 4,500 landings Part Number 70103-2639 - Retirement time 4,500 landings Part Number 70003-2359 - Retirement time 7,500 landings Part Number 70107-467 - Retirement time 7,500 landings (b) Flap beam (supporting bracket) attachment fitting at wing trailing edge false spar member inspection. (1) Within the next 135 hours' time in service after the effective date of this AD and each 135 hours' time in service thereafter, visually inspect for cracks all four lower flap support attachment fittings aft of the wing trailing edge member (false spar) on the right and left sides. The initial inspection is not required if these fittings were thoroughly examined at the time of bolt replacement of paragraph (a). (2) Within the next 385 hours' time in service after the effective date of this AD and each 1,080 hours' time in service thereafter, visually inspect for cracks all the flap support attachment fittings forward of the trailing edge member (false spar), top and bottom, right and left sides at flap positions 2 and 3. (3) Within the next 385 hours' time in service after the effective date of this AD and each 385 hours' time in service thereafter, visually inspect for cracks all top beam attachment fittings aft of the trailing edge member (false spar) on the right and left sides. (c) Replace cracked fittings. (d) Incorporated Vickers Modification D.2175 within the next 400 hours' time in service after the effective date of this AD on aircraft exceeding 3,000 landings, or within 400 hours' time in service upon the accumulation of 3,000 landings on aircraft not exceeding 3,000 landings on the effective date of this AD. Upon incorporation of this modification, the inspections called for in (b)(1), (b)(2), and (b)(3) may be discontinued. (Vickers Viscount 700 Series PTL No. 151, Issue 4 covers this subject.) This supersedes AD 57-07-03. This directive effective November 6, 1962. FOOTER:
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Retrieved: Apr 8, 2026
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