AD 67-06-03

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AD Number:
67-06-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; ERCOUPE Model 415C, 415CD, 415D, E, G and F1 Aircraft
Subject:
Rudder bellcrank
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
02/11/1967
Effective Date:
02/11/1967
Make:
Univair Aircraft Corporation
Model:
415-C | 415-CD | 415-D | F-1 | F-1A | 415-E | 415-G
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-770: West Certification Branch
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 67-06-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-349

AD NUMBER:   67-06-03

SUBJECT HEADING:   Airworthiness Directives; ERCOUPE Model 415C, 415CD, 415D, E, G and F1 Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-06-03 ERCOUPE: Amdt. 39-349 Part 39 Federal Register February 11, 1967. Applies to Models 415C, 415CD, 415D, E, G, and F1 Series Airplanes, Serial Numbers 1 through 5714 inclusive, Except Those Airplanes Modified in Accordance with Either Ercoupe Service Memorandum No. 63 or Air Products Document No. 110.

Compliance required as indicated.

To prevent loss of rudder control, accomplish the following:

(a) Before further flight, after the effective date of this AD, with the nosegear raised off the ground, inspect the rudder control system by checking the rudder controls from the cockpit for freedom of movement through the entire range of rudder control travel. If any restriction or impediment on the normal freedom of movement of the rudder controls is apparent, the cause thereof must be determined prior to further flight. If it is determined that the restriction or impediment is caused by binding in the rudder bellcrank at the stabilizer, before further flight, modify the rudder bellcrank assembly in a manner prescribed in (c) of this AD.

(b) If the rudder bellcrank assembly is not modified as a result of findings made during the inspection provided in (a), then it must be modified in a manner prescribed in (c) of this AD within fifty (50) hours time in service after the effective date of this AD.

(c) Modify the rudder bellcrank assembly in accordance with any one of the following -

(1) One of the two methods contained in Alon Service Bulletin No. 14, dated February 3, 1967; or

(2) The method contained in Ercoupe Service Memorandum No. 63 (available upon request from Alon, Inc., Municipal Airport, McPherson, Kansas); or,

(3) Any other method approved as equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Agency, Central Region.

This directive effective February 11, 1967.

FOOTER: