AD 64-05-03

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AD Number:
64-05-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives, GENERAL DYNAMICS Models 22, 22M, 30 and 30A Aircraft
Subject:
Aileron Trim Gearbox Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/23/1964
Make:
D & R Nevada LLC
Model:
22 | 22M | 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Superseded AD: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Superseded By: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: 64-05-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   64-05-03

SUBJECT HEADING:   Airworthiness Directives, GENERAL DYNAMICS Models 22, 22M, 30 and 30A Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective March 23, 1964.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   64-05-03 GENERAL DYNAMICS: Amdt. 688 Part 507 Federal Register February 21, 1964. Applies to All Models 22, 22M, 30 and 30A Aircraft.

Compliance required as indicated.

To prevent slipping of the aileron trim tab dial assembly in relation to the cable drum within the aileron and rudder trim gearbox assembly; to insure that the gear teeth on the aileron trim tab dial gear are not damaged; and to ascertain that the inside rim of the aileron trim tab dial gear is not rubbing against the sides of the hub of the aileron and rudder trim gear box, accomplish the following:

(a) Within 500 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 500 hours' time in service from the last check, perform an operational check (see Maintenance Manual) to determine that the aileron trim tab dial indicator and the aileron trim tab deflections correspond throughout the operational range and that the aileron trim tab control knob and dial work properly without evidence of binding or slippage. If there is any evidence that the aileron trim tab dial indicator and the aileron trim tab deflections do not correspond throughout the operational range or if there is any evidence of binding or slippage in the operation of the aileron trim tab control knob and dial, rework the aircraft per (b)(1) and (b)(2) before further flight. After compliance with paragraph (b) the checks required by this paragraph may be discontinued.

(b) Within 1,500 hours' time in service after the effective date of this AD unless the modification has already been accomplished:

(1) Pin the aileron trim drum shaft to the shaft gear and the aileron trim tab dial to the aileron trim tab gear per General Dynamics/Convair 880 Service Bulletin No. 27-27, 880M Service Bulletin No. 27-34, or 990 Service Bulletin No. 27-52, as applicable, or an FAA Western Region Engineering and Manufacturing Branch approved equivalent.

(2) Conduct a visual inspection of the aileron trim tab dial gear and hub of the support within the aileron and rudder trim gearbox assembly and if there is any evidence that the gear teeth on the aileron trim tab dial gear are damaged or there is any evidence that the inside of the rim of the aileron trim tab dial gear is rubbing the hub of the support, rework the hub of the support and replace any damaged aileron trim tab dial gear with a new gear in accordance with General Dynamics/Convair 880 Service Bulletin No. 27-70, 880M Service Bulletin No. 27-37 or 990 Service Bulletin No. 27-62, as applicable, or an FAA Western Region Engineering and Manufacturing Branch approved equivalent.

(General Dynamics/Convair 880 Service Bulletin Nos. 27-27 and 27-70, 880M Service Bulletins Nos. 27-34 and 27-37 and 990 Service Bulletins Nos. 27-52 and 27-62 cover this same subject.)

This directive effective March 23, 1964.

FOOTER: