AD 69-04-02

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AD Number:
69-04-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CESSNA Model A188 Airplanes
Subject:
Throttle Bellcrank Bracket
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/03/1969
Make:
Cessna Aircraft Company
Model:
A188
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 69-04-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-722

AD NUMBER:   69-04-02

SUBJECT HEADING:   Airworthiness Directives; CESSNA Model A188 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 3, 1969.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-04-02 CESSNA: Amdt. 39-722. Applies to Model A188 airplanes with Continental Motors Corporation IO-520-D (300 HP) engines, Serial Numbers 188-0001 through 188-0478 with the exception of Serial Numbers 188-0441, 188-0443, 188-0444, 188-0447, 188-0448, 188- 0453, 188-0460, 188-0462 through 188-0465, 188-0468 through 188-0476.

Compliance: Required as indicated.

To prevent failure of the throttle control bellcrank and the throttle and mixture support shaft, unless already accomplished, perform the following:

(1) Within 10 hours' time in service after the effective date of this AD, visually inspect the throttle control bellcrank P/N 0750163-1 for cracks or broken welds around the welded center boss. If cracks or a broken weld is found, replace the bellcrank with a strengthened Cessna P/N 0750163-4 in accordance with Cessna Service Letter SE68-28, Supplement No. 1, or an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. If this strengthened part P/N 0750163-4 is not available, P/N 0750163-1 may be installed. The aircraft may then be operated not to exceed 100 hours at which time P/N 0750163-4 must be installed prior to further flight.

(2) If any cracks are found during the inspection required by Paragraph (1), a description of such cracks and the time in service as of the date of said inspection should be reported to the local General Aviation District Office on FAA Form FAA-1226. (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174.)

(3) Within 10 hours' time in service after the effective date of this AD, replace the throttle and mixture control support shaft with P/N 0750173-2 and roll pin P/N MS-16562-16 in accordance with Cessna Service Letter SE68-28, dated October 8, 1968, or equivalent modification approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region.

This amendment becomes effective March 3, 1969.


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