AD 76-07-04

AD Final Rules - DRS_76-07-04.html
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AD Number:
76-07-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes
Subject:
Nose Landing Gear
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/12/1976
Make:
de Havilland Aircraft Co., Ltd., The
Model:
D.H.114 Heron Series 2A | D.H.114 Heron Series 2DA | D.H.114 Heron Series 2X
Product Type:
Aircraft
Product Subtype:
Small/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Superseded AD: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Superseded By: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: 76-07-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2563

AD NUMBER:   76-07-04

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation Ltd Model DH-114 Heron Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 12, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-07-04 HAWKER SIDDELEY AVIATION LTD: Amendment 39-2563. Applies to de Havilland Model DH-114 "Heron" airplanes certificated in all categories which have not been altered in accordance with Heron Modification 1612.

Compliance is required as indicated.

To detect cracks in the nose landing gear inner casing, and prevent the possible collapse of the nose landing gear upon landing, accomplish the following:

(a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter, at intervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casing for cracks in accordance with paragraphs 3.1 and 3.2 of section 3 entitled "Inspection" of Hawker Siddeley Aviation Ltd., Technical News Sheet No. U.17, Issue 1, dated September 17, 1973, or an FAA-approved equivalent.

(b) If any cracks are found during an inspection required by paragraph (a) of this AD, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (a) of this AD. Continue to inspect the replacement casing for cracks in accordance with Hawker Siddeley Aviation Ltd., Technical News Sheet, No. U.17, Issue 1, dated September 17, 1973, or an FAA-approved equivalent at intervals not to exceed 600 hours time in service from replacement.

This amendment becomes effective April 12, 1976.

FOOTER: