AD 76-05-04

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AD Number:
76-05-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Models 35, 35R, A35 and B35 and Pine Air Model Super- V Airplanes
Subject:
Stabilizer Attach Fitting
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
Make:
Textron Aviation Inc. | KWAD Company
Model:
35 | 35-33 | 35-A33 | 35-B33 | 35-C33 | 35-C33A | 35R | A35 ...Show more
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Superseded AD: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Superseded By: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: 76-05-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2662

AD NUMBER:   76-05-04

SUBJECT HEADING:   Airworthiness Directives; BEECH Models 35, 35R, A35 and B35 and Pine Air Model Super- V Airplanes

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-05-04 BEECH: Amendment 39-2536 as amended by Amendment 39-2662. Applies to Models 35, 35R, A35 and B35 (Serial Numbers D-1 thru D-2680) and Pine Air Model Super-V (Serial Numbers SV-XXX-D-1 thru SV-XXX-D-2680) airplanes, having 1,000 or more hours' time in service.

Compliance required as indicated, unless already accomplished per AD 75-20-04.

To prevent possible stabilizer loss or failure, on those airplanes having the P/N 35- 405130 stabilizer attach fitting, within 50 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,000 hours' time in service, accomplish the following in accordance with Beechcraft Service Instructions 0729-130, Rev. I or later FAA-approved revisions:

A) Remove stabilizer attach bolts, plates and other components necessary to provide access to the stabilizer attach fitting and then remove said fitting.

B) Inspect the stabilizer attach fitting by visual and dye penetrant methods in accordance with the procedures specified in FAA Advisory Circular (AC) 43.13-1A.

C) If as a result of any inspection required herein, a stabilizer attach fitting is found cracked, prior to further flight, replace it with a new or airworthy P/N 35-405130, P/N 35- 650044-1 or P/N 35-405130-3 stabilizer attach fitting.

D) When P/N 35-650044-1 or P/N 35-405130-3 stabilizer attach fitting has been installed the requirements of this AD no longer apply.

E) If a crack is found as a result of any inspection required herein, provide the FAA with written notification thereof utilizing Malfunction and Defect Report (FAA Form 8330-2) stating the location and length of any crack discovered and the total operating time of the airplane or part of the time of discovery. (Reporting approved by the Office of Management and Budget under ONB No. 04-R0174.)

F) Aircraft may be flown in accordance with FAR 21.197 to a base where the repair can be performed.

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

Amendment 39-2536 supersedes AD 75-20-4, Amendment 39-2370.

Amendment 39-2536 became effective March 12, 1976.

While the effective date of this amendment 39-2662 is July 12, 1976, the effective date for determining compliance with AD76-05-04 remains March 12, 1976.

FOOTER: