AD 76-02-05

AD Final Rules - DRS_76-02-05.html
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AD Number:
76-02-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation Limited Model DH-104 "Dove" Airplanes
Subject:
Engine Mounting Frame
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/30/1976
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Superseded AD: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Superseded By: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: 76-02-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2497

AD NUMBER:   76-02-05

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

ACTION:  

SUMMARY:  

DATES:   Effective January 30, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-02-05 HAWKER SIDDELEY AVIATION LIMITED: Amendment 39-2497. Applies to DH-104 "Dove" airplanes, certificated in all categories.

Compliance is required as indicated.

To prevent possible failure of the lefthand engine mounting frame top tube, and consequent tearing away of the engine, accomplish the following:

(a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, inspect the top tube of the lefthand engine mounting frame, P/N 4EM.201A, for cracks in accordance with paragraph No. 3 of Hawker Siddeley Technical News Sheet (T.N.S.) No. 228, Issue 1, dated April 17, 1972, or an FAA-approved equivalent.

(b) If any cracks are found as a result of an inspection required by this AD, replace the engine mounting frame with a new frame of the same part number or with a serviceable used frame of the same part number which has been inspected in accordance with paragraph (a) of this AD, and continue to inspect the replacement frame for cracks at intervals not to exceed 75 hours' time in service since the last inspection.

(c) If no cracks are found as a result of an inspection required by this AD, continue to inspect the engine mounting frame top tube at intervals not to exceed 75 hours' time in service from the last inspection in accordance with paragraph 3 of Hawker Siddeley Technical News Sheet (T.N.S.) No. 228, Issue 1, dated April 17, 1972, or an FAA-approved equivalent.

This amendment becomes effective January 30, 1976.

FOOTER: