AD 90-23-04

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AD Number:
90-23-04
Document Type:
AD Final Rules
Docket Number:
90-NM-208-AD
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A320 Series Airplanes
Subject:
Electrical Pitch Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/19/1990
Make:
Airbus SAS
Model:
A320-111 | A320-211 | A320-212 | A320-214 | A320-231 | A320-232 | A320-233
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Superseded AD: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Superseded By: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: 90-23-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-208-AD

AMENDMENT:   39-6793

AD NUMBER:   90-23-04

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

ACTION:  

SUMMARY:  

DATES:   Effective November 19, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-23-04 AIRBUS INDUSTRIE: Amendment 39-6793. Docket No. 90-NM-208-AD.

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

Compliance: Required as indicated, unless previously accomplished.

To prevent the loss of pitch electronic control and resultant reduced controllability of the airplane in the event of the trimmable horizontal stabilizer (THS) actuator control jamming, accomplish the following:

A. Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 7 days, perform a test to check the availability of pitch control through both the SEC 1 and SEC 2, in accordance with Airbus Industrie Service Bulletin A320-27-1031, Revision 1, dated August 15, 1990.

B. If electrical pitch control is not available through both SEC 1 and SEC 2, repair prior to further flight and test again, in accordance with Airbus Industries Service Bulletin A320- 27-1031, Revision 1, dated August 15, 1990. Following repair, repeat the test required by paragraph A. of this AD at intervals not to exceed 7 days.

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 (39-6793, AD 90-23-04) becomes effective on November 19, 1990.

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