AD 91-23-01

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AD Number:
91-23-01
Document Type:
AD Final Rules
Docket Number:
91-CE-10-AD
Subject Heading:
Airworthiness Directives; Beech Models 77 Airplanes
Subject:
Nose Landing Gear Fork
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/03/1991
Make:
Textron Aviation Inc.
Model:
77
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Superseded AD: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Superseded By: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: 91-23-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-CE-10-AD

AMENDMENT:   39-8070

AD NUMBER:   91-23-01

SUBJECT HEADING:   Airworthiness Directives; Beech Models 77 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 3, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-23-01 BEECH: Amendment 39-8070. Docket No. 91-CE-10-AD.

Applicability: Model 77 (Skipper) airplanes (serial numbers WA-1 through WA-312) that do not have a part number (P/N) 108-820010-653 nose landing gear fork and axle assembly installed, certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To prevent failure of the nose landing gear fork and the airplane damage that could result, accomplish the following:

(a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, fluorescent penetrant inspect the nose landing gear fork for cracks in accordance with the instructions in Beech Service Bulletin (SB) No. 2241, Revision 1, dated January 1991.

(1) If any crack is found, prior to further flight, remove and replace the nose landing gear fork and axle assembly with a (P/N) 108-820010-653 fork and axle assembly, and the requirements of this AD have been accomplished.

(2) If no cracks are found, accomplish the following:

(i) Fluorescent penetrant inspect the nose landing gear fork axle assembly at intervals not to exceed 500 hours TIS after the initial inspection required in paragraph (a) of this AD in accordance with the instructions in Beech SB No. 2241, Revision 1, dated January 1991; and visually inspect the nose landing gear fork axle assembly at every 100- hour TIS interval between the fluorescent penetrant inspections.

(ii) If any crack is found as a result of any of the inspections in paragraph (a)(2)(i) of this AD, prior to further flight, remove and replace the nose landing gear fork and axle assembly with a (P/N) 108-820010-653 fork and axle assembly, and the repetitive inspections are no longer required.

(b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished.

(c) An alternative 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, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office.

(d) The inspections required by this AD shall be done in accordance with Beech Service Bulletin No. 2241, Revision 1, dated January 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC.

This amendment (39-8070, AD 91-23-01) becomes effective on December 3, 1991.

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