AD 87-24-01

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AD Number:
87-24-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER) Model EMB-120 Series Airplanes
Subject:
Main Landing Gear
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/24/1987
Make:
Embraer - Empresa Brasileira de Aeronautica S.A.
Model:
EMB-120 | EMB-120RT
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 87-24-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5767

AD NUMBER:   87-24-01

SUBJECT HEADING:   Airworthiness Directives; EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER) Model EMB-120 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 24, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   87-24-01 EMPRESA BRASILEIRA DE AERONAUTICA S.A. (EMBRAER): Amendment 39-5767. Applies to Model EMB-120 series airplanes, certificated in any category, equipped with outboard main landing gear wheel halves identified by serial numbers in BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987. Compliance required as indicated, unless previously accomplished.

To prevent failure of the main landing gear outboard wheel half, accomplish the following:

A. Within the next 200 landings after the effective date of this AD, inspect the main landing gear outboard wheel halves, part number 300-603, for cracking, using visual and eddy current methods, in accordance with BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987.

1. If a crack is found, prior to further flight replace the wheel half with an airworthy FAA-approved assembly.

2. If no cracks are found, repeat the visual and eddy current inspections at intervals not to exceed 300 landings, until such time as an ultrasonic inspection is accomplished and each affected wheel half is found free of cracks and identified with the impression stamping in accordance with Figure 1 of BF Goodrich Service Bulletin 467, Revision 1, dated June 19, 1987. Any wheel found to be cracked must be replaced prior to further flight with an airworthy FAA- approved assembly.

B. For the purposes of complying with this AD, the number of landings may be determined by substituting one landing for each 1/2 hour of flight, unless the operator substantiates a different flight hours-to-landing ratio. This substantiation must be submitted to and approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region.

C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region.

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.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to BF Goodrich, Aerospace and Defense Division, Aircraft Wheel and Brake Operations, P.O. Box 340, Troy, Ohio 45373. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Central Region, Atlanta Aircraft Certification Office, Suite 210, 1669 Phoenix Parkway, Atlanta, Georgia.

The amendment becomes effective December 24, 1987.

FOOTER: