AD 63-17-07

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AD Number:
63-17-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft
Subject:
Horizontal Stabilizer Attach Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/13/1963
Make:
Sud Aviation
Model:
Caravelle SE 210 Model VIR
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Superseded AD: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Superseded By: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: 63-17-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-17-07

SUBJECT HEADING:   Airworthiness Directives; SUD AVIATION Model SE 210 Caravelle VIR Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective September 13, 1963.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   63-17-07 SUD AVIATION: Amdt. 603 Part 507 Federal Register August 14, 1963. Applies to SE 210 Caravelle VIR Aircraft.

Compliance required before 4,000 hours' time in service.

To prevent fatigue failure of the horizontal stabilizer attach fittings, accomplish the following:

(a) On all aircraft except aircraft with Serial Numbers 62, 129, and subsequent, install a reinforced fitting on the forward and aft faces of each horizontal stabilizer forward attachment fitting at frame 65, and replace the existing skin doublers with larger and heavier doublers. Make these modifications in accordance with Sud Service Bulletin No. 53-22 (Modification 1039) or FAA approved equivalent.

(b) On all aircraft except aircraft with Serial Numbers 62, 134, 138, 140, 156, and subsequent, machine a cutout in the horizontal mounting flange of the horizontal stabilizer attachment fitting and replace the bolts attaching these fittings to frame 65 by new forged bolts installed with spherical bearing face washers. Make these modifications in accordance with Sud Service Bulletin No. 53-24 (Modification 1124) or an FAA approved equivalent.

(c) When the modifications required by paragraphs (a) and (b) have been incorporated, the engine reverse thrust r.p.m. limitations specified in Airplane Flight Manual SE 210-651, Section 1.2.1B, revised October 16, 1962, and Airplane Flight Manual SE 210-650, Section 1.2.1A, revised October 16, 1962, may be removed from the respective Airplane Flight Manuals. If the aforementioned limitations are removed, the original limitations are removed, the original limitations appearing in the Airplane Flight Manual apply.

This directive effective September 13, 1963.

FOOTER: