AD 75-18-06

AD Final Rules - DRS_75-18-06.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
75-18-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Bell Models 47B, 47B-3, 47D, 47D-1, 47E, 47G, 47G-2, and 47H-1 Helicopters
Subject:
Tail Rotor Pitch Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/19/1975
Make:
Scotts-Bell 47 Inc
Model:
47B | 47B3 | 47D | 47D1 | 47E | 47G | 47G-2 | 47H-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Superseded AD: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Superseded By: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: 75-18-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2345

AD NUMBER:   75-18-06

SUBJECT HEADING:   Airworthiness Directives; Bell Models 47B, 47B-3, 47D, 47D-1, 47E, 47G, 47G-2, and 47H-1 Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective September 19, 1975.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
75-18-06 BELL: Amendment 39-2345. Applies to Bell Models 47B, 47B-3, 47D, 47D-1, 47E, 47G, 47G-2, and 47H-1 helicopters certificated in all categories that are equipped with a single-row ball bearing, P/N 47-641-146-1 (MRC R4AF4), in the tail rotor pitch control crosshead.

Compliance required within 10 hours' time in service for bearings with more than 40 hours' time in service on the effective date of this AD and prior to attaining 50 hours' time in service for bearings with less than 40 hours' time in service on the effective date of this AD.

To prevent possible failure of the tail rotor pitch control ball bearing due to inadequate lubrication, accomplish the following one-time inspection.

a. Disassemble the tail rotor pitch control crosshead assembly in accordance with Sections VI and VII, Models 47D-1, 47G, and 47G-2 Maintenance and Overhaul Instruction Manual, revised August 15, 1961, or in accordance with equivalent FAA approved procedures to expose the pitch change bearing.

b. Inspect the bearing, P/N 47-641-146-1 (MRC P/N R4AF4) for grease dust shields.

c. Remove any pitch change bearings with two grease dust shields installed before further flight.

d. Install bearings P/N 47-641-146-1 (MRC P/N R4AF4) with only one grease dust shield installed and assemble and rig the tail rotor controls, in accordance with Sections VI and VII, Models 47D-1, 47G, and 47G-2 Maintenance and Overhaul Instruction Manual, revised August 15, 1961, or in accordance with equivalent FAA approved procedures.

e. This AD does not apply to the obsolete design, single-row ball bearings having a single grease dust shield, Norma Hoffman P/N S1RP and New Departure P/N 7R4AX1C. This AD does not apply to the duplex pitch change bearings, P/N 47-641-131-1.

This amendment becomes effective September 19, 1975.

FOOTER: