AD 78-09-04

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AD Number:
78-09-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes
Subject:
Main Spar Bottom Boom Lugs
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/24/1978
Make:
de Havilland Aircraft Co., Ltd., The
Model:
D.H. 104 Dove Series 1A | D.H. 104 Dove Series 2A | D.H. 104 Dove Series 5A | D.H. 104 Dove Series 5...Show more
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 78-09-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3200

AD NUMBER:   78-09-04

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 24, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-09-04 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-3200. Applies to Model DH-104 "Dove" airplanes, all series, certificated in all categories, except those airplanes incorporating Hawker Siddeley Model DH-104 Modification 779.

Compliance is required as indicated.

To detect cracking and prevent possible failure of the lugs of the lower center section main spar wing to fuselage attachment, accomplish the following:

(a) Within one month after the effective date of this AD, unless already accomplished within the last month, and thereafter at intervals not to exceed two months from the last inspection, remove the lower wing to fuselage fairings and inspect the center section main spar bottom boom lugs for cracks using an ultrasonic inspection method in accordance with appendix 1 of Hawker Siddeley Aviation, Limited Technical News Sheet (TNS) 238, issue 2, dated January 24, 1977, or an FAA-approved equivalent.

(b) The repetitive inspections required by paragraph (a) of this AD may be terminated upon incorporation of a steel lower boom in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent.

(c) Within two months after accomplishing six repetitive inspections under paragraph (a) of this AD, a steel lower boom must be incorporated in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent.

(d) If any crack is found during an inspection required by paragraph (a) of this AD, before further flight, replace the boom with a steel boom in accordance with Hawker Siddeley Model DH-104 Modification 779, or an FAA-approved equivalent.

This amendment becomes effective May 24, 1978.

FOOTER: