AD 73-20-07 R2

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AD Number:
73-20-07 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B-19, 23, A23, A23A, B23, C23, A23-24, A2...Show more
Subject:
Wing Attach Bolts/Brackets
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/03/1982
Make:
Textron Aviation Inc.
Model:
19A | 23 | A23 | A23-19 | A23-24 | A23A | A24 | A24R | B19 | B23 | B24R | C23 | 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Superseded AD: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Superseded By: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: 73-20-07 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4461

AD NUMBER:   73-20-07 R2

SUBJECT HEADING:   Airworthiness Directives; BEECH Models A23-19, 19A, M19A, B-19, 23, A23, A23A, B23, C23, A23-24, A24, A24R, and B24R Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 3, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
73-20-07 R2 BEECH: Amendment 39-1728 as amended by Amendment 39-3732 is further amended by Amendment 39-4461. Applies to Models A23-19, 19A, M19A, B-19 (Serial Numbers MB-1 through MB-708); Models 23, A23, A23A, B23, C23 (Serial Numbers M-1 through M-1576); Models A23-24, A24 (Serial Numbers MA-1 through MA-368); and Models A24R, B24R (Serial Numbers MC-2 through MC-282) certified in all categories.

Compliance: Required as indicated.

To detect cracks or other structural damage to the forward wing attach point brackets (P/N 169-400013-3 and -5(LH) and 169-400013-4 and -6 (RH)), within the next 25 hours' time in service after the effective date of this AD unless previously accomplished on airplanes having more than 100 hours' time in service and thereafter at each normal annual, progressive or 100 hour inspection interval as required by FAR 91.169, accomplish the following:

(a) Remove the seats and sidepanels and visually inspect the forward wing attach brackets, P/N 169-400013-3 and -5 (LH) and 169-400013-4 and -6 (RH), to determine if cracks or other structural damage exists in the area around the attach bolt hole. This inspection is to be performed in accordance with Beech Service Instructions 0042-031, Rev. II.

(b) If as a result of any inspection required herein cracks or other structural damage is discovered, prior to further flight repair the forward wing attach brackets in accordance with Beechcraft Service Instructions 0042-031, or later FAA-approved revisions, or any other repair approved by the Chief, Wichita Aircraft Certification Office, FAA, Wichita, Kansas. To accomplish the repair required herein the aircraft may be flown in accordance with FAR 21.197 to a base where the repair may be performed.

(c) The inspection intervals required in this AD may be adjusted 15 plus or minus hours where required to fit users maintenance cycles if authorized by an FAA Flight Standards Inspector.

(d) When airplanes have been modified by installing all of the new wing attach structural parts listed under materials in Beechcraft Service Instructions No. 0042-031, Rev. II, further compliance with this AD is not required.

(e) Any equivalent method of compliance with this AD must be approved by the Chief, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209.

Amendment 39-1728 became effective October 5, 1973.

Amendment 39-3732 became effective March 21, 1980.

This Amendment 39-4461 became effective on September 3, 1982.

FOOTER: