AD 73-19-09

AD Final Rules - DRS_73-19-09.html
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AD Number:
73-19-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters
Subject:
Pitch Link Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/17/1973
Make:
Bell Helicopter Textron Canada Limited
Model:
206A | 206A-1 (OH-58A) | 206B | 206B-1
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Superseded AD: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Superseded By: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: 73-19-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1718

AD NUMBER:   73-19-09

SUBJECT HEADING:   Airworthiness Directives; Bell Model 206A, 206B, 206A-1 and 206B-1 Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective September 17, 1973.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
73-19-09 BELL: Amdt. 39-1718. Applies to Model 206A, 206B, 206A-1 and 206B-1 helicopters equipped with main rotor blade pitch link assemblies, P/N 206-010-330 and 206-010- 342, as applicable, certificated in all categories.

Compliance required within 25 hours time in service after the effective date of this A.D., unless previously accomplished and thereafter at intervals not to exceed 50 hours time in service from the last inspection.

To detect and prevent possible corrosion and cracks in the main rotor blade pitch link tubes, P/N 206-010-330, all dash numbers, accomplish the following:

(a) Inspect the ends and outside diameter surface of each tube for corrosion and cracking, using a 3 power or higher magnifying glass.

(b) Replace corroded or cracked tubes prior to next flight except a helicopter with corroded tubes may be flown in accordance with FAR 21.197 to a base where replacement may be accomplished.

(c) If tubes are replaced or adjusted, track the main rotor blades in accordance with the appropriate model maintenance and overhaul information manual.

(d) Apply corrosion preventive compound, MIL-C-16173, Grade 2, or equivalent, to the exposed threads of the upper and lower clevises, the ends of each tube, the mating faces of the locks and nuts and the top surfaces of the nuts after the nuts are properly torqued on each pitch link assembly.

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection interval specified in this A.D. to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

(Bell Helicopter Company Service Bulletin No. 206-04-2-73-1 dated May 7, 1973 pertains to this subject.)
This amendment becomes effective September 17, 1973.

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