AD 69-12-07

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AD Number:
69-12-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Bell Model 206A Helicopters
Subject:
Magnesium Tail Boom
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/21/1969
Make:
Bell Helicopter Textron Canada Limited
Model:
206A
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 69-12-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-781

AD NUMBER:   69-12-07

SUBJECT HEADING:   Airworthiness Directives; Bell Model 206A Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective July 21, 1969.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-12-07 BELL: Amdt. 39-781. Applies to Bell Model 206A helicopters, Serial Nos. 4 through 153, equipped with the magnesium tail boom assembly, Part No. 206-031-004-1 or -3.

Compliance required as indicated.

To prevent failure of the magnesium tail boom due to fatigue cracks, accomplish the following:

(a) Before the first flight of each day after the effective date of this AD:

(1) Remove the tail rotor drive shaft cover.

(2) Inspect the skin adjacent to the rivet holes for cracks in the following areas, using a three-power or higher magnifying glass:

(i) The tab attachment of the drive shaft cover to the tail boom.

(ii) The area adjacent to the rivnut attachment of the tail rotor gear box fairing to the tail boom.

(iii) The horizontal stabilizer attachment fittings.


(3) Repair tail booms with only one skin crack less than one inch in length if the crack is located in an area described in (a)(2)(ii) or (iii) above, by stop drilling and deburring the holes.

(4) Remove and replace tail booms with any other skin crack, in accordance with Paragraphs 8-37 through 8-47 of the Model 206A Maintenance and Overhaul Instructions.

(b) Within 25 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 25 hours' time in service from the last inspection:

(1) Remove the tail rotor drive shaft cover and the gear box fairing.

(2) Inspect the skin adjacent to the rivet holes for cracks in the following areas, using a three-power or higher magnifying glass:

(i) The tab attachment of the drive shaft cover to the tail boom.

(ii) The rivnut attachments of the tail rotor gear box fairing to the tail boom.

(iii) The horizontal stabilizer attachment fittings.

(3) Repair tail booms with only one skin crack less than one inch in length if the crack is located in an area described in (b)(2)(ii) or (iii) above, by stop drilling and deburring the holes.

(4) Remove and replace tail booms with any other skin crack, in accordance with Paragraphs 8-37 through 8-47 of the Model 206A Maintenance and Overhaul Instructions, before further flight.

(5) Inspect tail rotor balance and balance, if necessary, in accordance with Paragraph 2A on Page 2 of Bell Service Bulletin No. 206A-7 dated August 22, 1968, or later FAA-approved revision or in accordance with an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration.

(c) Remove and replace magnesium tail booms with 400 or more hours' time in service on the effective date of this AD within 100 hours' time in service therefrom.

(d) Remove and replace magnesium tail booms with less than 400 hours' time in service on the effective date of this AD, prior to accumulating 500 hours' time in service.

(e) Remove and replace all subsequent replacement magnesium tail booms prior to accumulating 500 hours' time in service.

(Bell Helicopter Company Service Bulletin No. 206A-7 dated August 22, 1968, pertains to this subject).
This amendment becomes effective July 21, 1969.

FOOTER: