AD 62-23-04

AD Final Rules - DRS_62-23-04.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
62-23-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GENERAL DYNAMICS/CONVAIR Model 30 Aircraft
Subject:
Main Land Gear Door
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/19/1962
Make:
D & R Nevada LLC
Model:
30 | 30A
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Superseded AD: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Superseded By: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: 62-23-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   62-23-04

SUBJECT HEADING:   Airworthiness Directives; GENERAL DYNAMICS/CONVAIR Model 30 Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective October 19, 1962.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   62-23-04 GENERAL DYNAMICS/CONVAIR: Amdt. 497 Part 507 Federal Register October 19, 1962. Applies to All Model 30 Aircraft.

Compliance required as indicated.

As a result of cracking of the main landing gear door upper forward attachment fitting, P/N 30-55153, the following shall be accomplished:

(a) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the preceding 250 hours' time in service, and at intervals thereafter not to exceed 350 hours' time in service following that initial inspection, conduct a close visual and dye penetrant inspection of P/N 30-55153 to detect any cracking of the fitting in the vicinity of the attachment of the door actuator. Particular attention shall be given to the radii between the leg and base of these tee-shaped fittings.

(b) Any fitting inspected per (a) and found to exhibit a crack not exceeding 4 inches in length shall be replaced with an uncracked part or repaired in accordance with General Dynamics/Convair Telegraphic Service Instructions dated August 10, 1962, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region, prior to further flight.

(c) Fittings repaired per (b) shall be reinspected in accordance with the inspection provisions of (a) at intervals not to exceed 100 hours' time in service.

(d) Any fitting inspected in accordance with (a) or (c) and found to exhibit a crack greater than 4 inches in length shall be replaced with an uncracked part prior to further flight.

(e) When fitting, P/N 30-55153, is reworked in accordance with the provisions of General Dynamics/Convair Service Bulletin No. 32-38, or equivalent rework approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region, the inspections prescribed by (a) or (c) may be discontinued.

(f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator, if the request is substantiated by technical data and/or other facts which justify the acceptability of such increased intervals.

(General Dynamics/Convair Alert Service Bulletin No. A32-11, Telegraphic Service Instructions dated August 10, 1962, and Service Bulletin No. 32-38 pertain to this subject.)

This directive effective October 19, 1962.

FOOTER: