AD 77-17-03

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AD Number:
77-17-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Bell Model 212 and 205A-1 Helicopters
Subject:
Tail Rotor Blade Pitch Horn
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/19/1977
Make:
Bell Helicopter Textron, Inc.
Model:
205A-1 | 212
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Superseded AD: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Superseded By: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: 77-17-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3009

AD NUMBER:   77-17-03

SUBJECT HEADING:   Airworthiness Directives; Bell Model 212 and 205A-1 Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective August 19, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-17-03 BELL: Amendment 39-3009. Applies to Model 212 helicopters, S/N 30502 through 30804, 30806 through 30810, 30812, 30814, 30815, 30817, 30818, 30820 through 30825, 30827, 30828, 30829, and to Model 205A-1 helicopters, S/N 30001 through 30247, equipped with tail rotor blades, P/N 212-010-750, certificated in all categories.

Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished and thereafter at intervals not to exceed 100 hours' time in service from the last inspection.

To detect possible cracks in each tail rotor blade pitch change horn, P/N 212-010-716-5 and -9, accomplish the following:

(a) Remove the bolt and barrel nut of the control rod and clean the external surfaces of the pitch change horns.

(b) Inspect the horns for cracks, particularly in the barrel nut and bushing area using a dye penetrant or equivalent inspection method.

(c) If a crack is found, replace the affected pitch change horn before further flight in accordance with the Model 212 Overhaul Manual, paragraphs 65-58 and 65-63, or Models 205A/205A-1 Maintenance and Overhaul Instructions, paragraphs 3-41 and 3-43, as appropriate.

(d) Install the blade's control rod bolt and barrel nut as specified in the instructions in paragraphs 65-57 Model 212 Maintenance Manual or 3-40 Models 205/205A-1 Maintenance and Overhaul Instructions, as appropriate.

(e) After installation of pitch change horns, P/N 212-010-716-11, this AD is no longer applicable.

(f) 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 intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.

(g) The manufacturer's instructions identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Textron, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas.

(Bell Helicopter Textron Service Bulletin Nos. 212-77-7 and 205-77-5 dated March 11, 1977, pertain to this subject.)

This amendment becomes effective August 19, 1977.

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