AD 87-02-08

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AD Number:
87-02-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Beech Model A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24, A24,...Show more
Subject:
Stabilator Hinge Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/04/1987
Make:
Textron Aviation Inc.
Model:
19A | 23 | A23 | A23-19 | A23-24 | A23A | A24 | A24R | B19 | B23 | B24R | C23 | C24R | M19A
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Superseded AD: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Superseded By: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: 87-02-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5568

AD NUMBER:   87-02-08

SUBJECT HEADING:   Airworthiness Directives; Beech Model A23-19, 19A, M19A, B19, 23, A23, A23A, B23, C23, A23-24, A24, A24R, B24R and C24R Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 4, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-02-08 BEECH: Amendment 39-5568. Applies to the following serial-numbered airplanes certificated in any category:

MODEL	SERIAL NUMBERS
A23-19, 19A, M19A and B19	MB-1 thru MB-520
B19 Sport 150	MB-521 thru MB-905
23, A23, A23A, B23, C23	M-1 thru M-1361
C23 Sundowner 180	M-1362 thru M-2156, M-2158 thru M- 2392
A23-24, A24	MA-1 thru MA-368
A24R	MC-2 thru MC-95
A24R, B24R, C24R Sierra 200	MC-96 thru MC-795

Compliance: Required prior to further flight on all airplanes and each 100 hours time-in- service (TIS) thereafter for normal and utility category airplanes, and each 25 hours TIS thereafter for acrobatic category airplanes, unless already accomplished.

To preclude failure of the fasteners securing the stabilator hinge assemblies and subsequent loss of pitch control, accomplish the following:

(a) Visually inspect the fasteners securing the stabilator hinge assemblies to the fuselage for looseness or failure in accordance with the "ACCOMPLISHMENT INSTRUCTIONS" in Beech Service Bulletin No. 2182, issued February 1987.

(b) If any fasteners are found loose or failed when conducting the inspections required in paragraph (a) above, prior to further flight, replace all fasteners securing both the right and left hinge assemblies to the fuselage in accordance with the above-referenced service bulletin.

(c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(d) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration (FAA), Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beech Aircraft Corporation, Commercial Service Department, P.O. Box 85, Wichita, Kansas 67201; or may examine the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on March 4, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated January 27, 1987, and is identified as AD 87-02-08.

FOOTER: