AD 70-21-04

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AD Number:
70-21-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Model DH.114 Heron Series Airplanes
Subject:
Fin to Fuselage Attachment
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/05/1970
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Superseded AD: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Superseded By: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: 70-21-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1089

AD NUMBER:   70-21-04

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Model DH.114 Heron Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 5, 1970.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
70-21-04 HAWKER SIDDELEY: Amendment 39-1089. Applies to de Havilland Model DH.114 "Heron" airplanes.

Compliance is required as indicated.

To prevent failure of the fin to fuselage front attachment brackets at Bulkhead 6, accomplish the following:

(a) For all airplanes, within the next 1200 hours' time in service from the effective date of the AD, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect Bulkhead 6 for cracking or signs of distortion in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB- approved issue or an FAA-approved equivalent. If cracking or signs of distortion are found, accomplish standard repairs before further flight.

(b) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.1891 and 14FS.1892 (pre-modification No. Heron 609), or right-hand and left-hand forward fin attachment fittings, P/Ns 14FS.5007 and 14FS.5008 (post-modification Heron 609) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method.

(c) For airplanes having right-hand and left-hand forward fin attachment fittings, P/Ns 14 FS.4669 and 14 FS.4670 (post-modification No. Heron 869) installed on Bulkhead 6, within the next 300 hours' time in service after the effective date of this AD, unless already accomplished within the last 900 hours' time in service, and thereafter at intervals not to exceed 1200 hours' time in service since the last inspection, visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent. If there is doubt as to the results of this inspection, confirm the results of the inspection by a dye penetrant method.

(d) If cracks are found in a forward fin attachment fitting during the inspections required by paragraphs (b) or (c), accomplish the following before further flight:

(1) Replace both the right-hand and left-hand forward attachment fittings in accordance with de Havilland Aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent.

(2) Visually inspect the fin attachment fittings on Bulkhead 7 and the fin attachment fittings on the fin rear spar for cracks or any other signs of damage, and replace any fittings found to be cracked or damaged with new fittings of the same part number.

(e) For all airplanes, after accomplishing the replacements and inspections specified in paragraph (d), continue to visually inspect the forward fin attachment fittings for cracks in accordance with Hawker Siddeley Technical News Sheet, Series: Heron (114), No. F.15, Issue 3, dated May 4, 1970, or later ARB-approved issue or an FAA-approved equivalent, at intervals not to exceed 1200 hours' time in service since the last replacements and inspections accomplished in accordance with paragraph (d). If cracks are found during any of these inspections, replace the cracked fittings before further flight in accordance with de Havilland aircraft Service Modification No. Heron 869, Amendment No. 1, dated May 15, 1959, or later ARB-approved issue or an FAA-approved equivalent.

This amendment becomes effective November 5, 1970.

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