AD 63-20-02

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AD Number:
63-20-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CESSNA Model 190 and 195 Series Airplanes
Subject:
Wing Spar Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/08/1963
Make:
Cessna Aircraft Company
Model:
190 | 195 | 195A | 195B
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Superseded AD: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Superseded By: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: 63-20-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-20-02

SUBJECT HEADING:   Airworthiness Directives; CESSNA Model 190 and 195 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 8, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
63-20-02 CESSNA: Amdt. 628 Part 507 Federal Register October 3, 1963. Applies to All Models 190 and 195 Series Aircraft.

Compliance required as indicated.

As a result of a fatal accident involving fatigue failure of the front wing spar fuselage carry through lower cap the following corrective action is required:

(a) Within 10 hours' time in service after the effective date of this AD, conduct the following visual and X-ray inspections in accordance with Cessna Service Letter 190/195-1 dated May 13, 1960, or FAA approved equivalent unless already accomplished within the last 100 hours' time in service:

(1) Inspect using X-ray method for cracks in the lower cap of the front spar carry through member at both left and right sides of the fuselage in the area of the two most inboard steel rivets;

(2) Remove rear spar to fuselage attachment bolts and visually inspect these bolts using at least a 4-power magnifying glass for evidence of wear or partial shear failures;

(3) Visually inspect the rear spar to fuselage fittings of both the wing structure and carry through structure including the bolt bushings for wear or hole elongation;

(4) Visually inspect the steel plates of the rear spar to fuselage attachment fittings on the wing for cracks using at least a 4-power magnifying glass; and

(5) If any of the defects specified are found replace the parts with new parts or make an FAA approved repair and accomplish the modification required by (b) before further flight.

(b) Within 10 hours' time in service after the effective date of this AD, accomplish the fuselage front spar modification specified in Cessna Service Letter 63-40, dated September 27, 1963. This specifies replacement of the five existing inboard lower cap high shear steel pins with NAS 464P7-A64 bolts and attachment of two 1/2 x l 3/4 4130 steel reinforcement bars on each side of the lower spar cap in accordance with Cessna Service Kits Nos. SK-195-3 and SK-195-4, dated September 23, 1963.

(c) At each periodic inspection after the accomplishment of (b), visually inspect for cracks the visible portion of the lower spar cap and reinforcement bars at the inboard bolt location. If cracks are found, replace the cracked part with a new part or make an FAA approved repair before further flight.

This supersedes AD 61-17-01.

This directive effective October 8, 1963.


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