AD 63-15-04

AD Final Rules - DRS_63-15-04.html
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AD Number:
63-15-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GENERAL DYNAMICS Models 340 and 440 Aircraft
Subject:
Nose Landing Gear Rod End Eye-Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/15/1963
Make:
Kelowna Flightcraft R & D Ltd.
Model:
340 | 440
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Superseded AD: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Superseded By: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: 63-15-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-15-04

SUBJECT HEADING:   Airworthiness Directives; GENERAL DYNAMICS Models 340 and 440 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective August 15, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   63-15-04 GENERAL DYNAMICS: Amdt. 584 Part 507 Federal Register July 16, 1963. Applies to All Models 340 and 440 Aircraft.

Compliance required as indicated.

Cracks have been found in the nose landing gear actuating cylinder rod end eyebolt, Peacock P/N C50137-2. To assure that all cracked eyebolts are replaced, accomplish either (a) or (b) as applicable:

(a) If the nose landing gear actuating cylinder rod end eyebolt Peacock P/N C50137- 2, has not been modified in accordance with Convair Service Engineering Report No. 6820-240- 23/340-45/440-45 dated August 24, 1962, or an FAA Western Region, Engineering and Manufacturing Branch approved equivalent modification, within the next 225 hours' time in service after the effective date of this AD, unless already accomplished within the last 775 hours' time in service, and thereafter at periods not to exceed 1,000 hours' time in service from the last inspection, inspect the unmodified eyebolt, where the threaded area is machined for the relief radius, by a dye penetrant method or an FAA approved equivalent method for any indication of cracking. Replace a cracked eyebolt with an uncracked eyebolt, Peacock P/N C50137-2, before further flight and continue the repetitive inspections.

(b) If the nose landing gear actuating cylinder rod end eyebolt, Peacock P/N C50137-2, has been modified in accordance with Convair Service Engineering Report No. 6820- 240-23/340-45/440-45 dated August 24, 1962, or an FAA Western Region, Engineering and Manufacturing Branch approved equivalent modification, within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished within the last 4,500 hours' time in service, and thereafter at periods not to exceed 5,500 hours' time in service from the last inspection, inspect the eyebolt, where the threaded area is machined for the relief radius, by a dye penetrant method or an FAA approved equivalent method for any indication of cracking. Replace a cracked eyebolt with an uncracked eyebolt, Peacock P/N C50137-2, before further flight and continue the repetitive inspections.

(c) When unmodified eyebolts are used as replacement bolts, the inspection periods of (a) are applicable, and if modified eyebolts are used as replacements, the inspection periods of (b) are applicable.

(Convair Service Engineering Report No. 6820-240-23/340-45/440-45 dated August 24, 1962, pertains to this same subject.)

This directive effective August 15, 1963.

FOOTER: