AD 90-22-08

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AD Number:
90-22-08
Document Type:
AD Final Rules
Docket Number:
90-NM-199-AD
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A320-231 Series Airplanes
Subject:
Rear Engine Mount Nuts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/05/1990
Make:
Airbus
Model:
A320-231
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Superseded AD: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Superseded By: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:
AIRWORTHINESS DIRECTIVES FINAL RULES: 90-22-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-199-AD

AMENDMENT:   39-6781

AD NUMBER:   90-22-08

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A320-231 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 5, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-22-08 AIRBUS INDUSTRIE: Amendment 39-6781. Docket No. 90-NM-199-AD.

Applicability: All Model A320-231 series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To detect cracks in the rear engine mount barrel nuts, and to prevent reduced structural integrity of the rear engine support structure, accomplish the following:

A. Within 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 700 hours time-in-service, perform a visual inspection of the rear engine mount barrel nuts, in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0085/90, dated April 3, 1990. If a nut is cracked, replace with a new nut, prior to further flight, in accordance with the Operator Information Telex. Following replacement of the nut, continue the visual inspections at intervals not to exceed 700 hours time-in-service in accordance with the AOT.

NOTE: This Airbus Industrie telex references International Aero Engines (IAE) Service Bulletin No. V2500-NAC-71-0071, Revision 3, dated March 30, 1990, for additional information.

B. On each day that flying occurs, perform a torque check of the rear engine mount bolts in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0087/90, dated April 4, 1990. Any bolt which does not meet the appropriate torque limits specified in the AOT must be retorqued prior to further flight.

NOTE: This Airbus Industrie telex references IAE Service Bulletin No. V2500-NAC-71- 0071, Revision 3, dated March 30, 1990, for additional information.

C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113.

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 information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington.

This amendment (39-6781, AD 90-22-08) becomes effective on November 5, 1990.

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