AD 76-09-02

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AD Number:
76-09-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Beech Models 200, Military A100-1, and C-12A Airplanes
Subject:
Bolt Hole Edge Distance
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/03/1976
Make:
Textron Aviation Inc.
Model:
200 | A100-1 (U-21J) | A200 (C-12A)
Product Type:
Aircraft
Product Subtype:
Small/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Superseded AD: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Superseded By: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: 76-09-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2592

AD NUMBER:   76-09-02

SUBJECT HEADING:   Beech Models 200, Military A100-1, and C-12A Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 3, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-09-02 BEECH: Amendment 39-2592. Applies to Models 200 and Military A100-1 (Serial Numbers BB-3 thru BB-19, BB-21 thru BB-38, BB-40, BB-41, BB-43 thru BB-75 and BB-78) and Model C-12A (Serial Numbers BC-1, BC-2, BC-3, BD-2 and BD-3) airplanes.

Compliance: Required as indicated, unless already accomplished.

To detect inadequate edge distance on the bolt holes in the wing center section lower forward spar cap for attachment of the outer wing panel lower forward spar cap, within the next 100 hours' time in service after the effective date of this AD, accomplish the following:

A) Inspect for proper fit between the wings and center section at the lower forward spar attachment as follows:

1. Using a vernier caliper or a suitable depth gage, graduated in increments of .01-inch, measure the protrusion of the wing spar cap below the center section spar cap at the lower forward wing spar cap below the center section spar cap at the lower forward wing attachment on both the LH and RH sides.

2. If the protrusion does not exceed .10-inch, no further action is necessary.

3. If the protrusion exceeds .10-inch, remove the wing and measure the edge distance of the wing attachment hole in the center section lower spar in accordance with Figure 1. Provide this information to the manufacturer and thereafter operate or modify the airplane in accordance with FAA-approved limitations or instructions provided by the manufacturer.

B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

NOTE: The manufacturer's address is Beech Aircraft Corporation, Commercial Service Operations, Wichita, Kansas 67201.

Beechcraft Service Instruction No. 0775-062 or later approved revisions cover the subject matter of this AD.

This amendment becomes effective May 3, 1976.

FIGURE 1
AD 76-09-02




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