AD 90-08-01

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AD Number:
90-08-01
Document Type:
AD Final Rules
Docket Number:
90-NM-40-AD
Subject Heading:
Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes
Subject:
Door Lifting Rod
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/20/1990
Make:
ATR - GIE Avions de Transport R gional
Model:
ATR42-300 | ATR42-320
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Superseded AD: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Superseded By: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: 90-08-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-40-AD

AMENDMENT:   39-6567

AD NUMBER:   90-08-01

SUBJECT HEADING:   Airworthiness Directives; AEROSPATIALE Model ATR42-300 and ATR42-320 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 20, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-08-01 AEROSPATIALE: Amendment 39-6567. Docket No. 90-NM-40-AD.

Applicability: Model ATR42-300 and ATR42-320 series airplanes, on which Modification 1236 has been installed (or which have been retrofitted in accordance with Aerospatiale Service Bulletin ATR42-52-0019), and Modification 2440 has not been installed.

Compliance: Required as indicated, unless previously accomplished.

To prevent simultaneous rupture of the passenger/crew door lifting device compensation rod and its fail-safe cable, accomplish the following:

A. Within l5 days after the effective date of this AD, and thereafter at intervals not to exceed 250 hours time-in-service, inspect the upper part of the rod to ensure that the area is free from dents, scratches, or other damage, and inspect the fail-safe cable for damage, in accordance with Part A of Aerospatiale Service Bulletin ATR42-52-0042, Revision 1, dated January 31, 1990.

1. If damage to the rod is 0.2mm deep or more, prior to further flight, replace the rod with a serviceable part in accordance with the service bulletin.

2. If damage to the rod is less than 0.2mm deep, perform local blend out and apply protection (alodine, primer, and finish paint), in accordance with the service bulletin.

3. If a wire of the fail-safe cable is damaged, prior to further flight, replace the cable with a serviceable cable.

B. Within 15 days after the effective date of this AD, modify the rod installation and install heat shrink tubing at the upper end of the fail-safe cable, in accordance with Part B of Aerospatiale Service Bulletin ATR42-52-0042, Revision 1, dated January 31, 1990.

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, Northwest Mountain Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington.

This amendment (39-6567, AD 90-08-01) becomes effective on April 20, 1990.

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