AD 91-05-02

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AD Number:
91-05-02
Document Type:
AD Final Rules
Docket Number:
90-CE-20-AD
Subject Heading:
Airworthiness Directives SOCATA Models TB 20 and TB 21 airplanes
Subject:
Landing Gear Mount
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/25/1991
Make:
SOCATA
Model:
TB 20 | TB 21
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Superseded AD: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Superseded By: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: 91-05-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-CE-20-AD

AMENDMENT:   39-6887

AD NUMBER:   91-05-02

SUBJECT HEADING:   Airworthiness Directives SOCATA Models TB 20 and TB 21 airplanes

ACTION:  

SUMMARY:  

DATES:   ; Effective March 25, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-05-02 SOCATA: Amendment 39-6887. Docket No. 90-CE-20-AD.

Applicability: Models TB 20 and TB 21 airplanes (serial numbers (S/N) 1 through 1051, except S/N 1040 and S/N 1042), certificated in any category.

Compliance: Required as indicated after the effective date of this AD, unless already accomplished.

To prevent structural failure of the fuselage frame in the area of the landing gear attachment, accomplish the following:

(a) On airplanes with more than 1,500 hours time-in-service (TIS) on the effective date of this AD, within the next 100 hours TIS after the effective date of this AD and, thereafter, at intervals not to exceed 500 hours TIS, visually inspect the fuselage frame No. 0 for cracks in the area of the engine mount and landing gear mount in accordance with the instructions in Aerospatiale Service Bulletin (SB) No. 42/1, dated July 1990. Prior to further flight, repair any cracked frames found in accordance with the instructions in the above SB.

(b) On airplanes with less than 1,500 hours TIS on the effective date of this AD, within the next 100 hours TIS or prior to accumulating 1,600 hours TIS, whichever occurs later, and, thereafter, at intervals not to exceed 500 hours TIS, visually inspect the fuselage frame No. 0 for cracks in the area of the engine mount and landing gear mount in accordance with the instructions in Aerospatiale SB No. 42/1, dated July 1990. Prior to further flight repair any cracked frames found per the instructions in the above SB.

(c) The repetitive inspections specified in paragraphs (a) and (b) of this AD are no longer required when the airplane has been modified in accordance with Socata Kit 9152.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

(e) An alternate method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Aircraft Certification Office, Europe, Africa, Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office.

(f) All persons affected by this directive may obtain copies of the documents referred to herein upon request to Aerospatiale Aeroport Tarbes-Ossum-Lourdes, B.P. 930 65009 Tarbes, France; Telephone 62.51.7300; or may examine the service information at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

This amendment (39-6887, AD 91-05-02) becomes effective on March 25, 1991.

FOOTER: