AD 72-08-03

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AD Number:
72-08-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Model DH-114 "Heron" Airplanes
Subject:
Rudder Control Pedal
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/01/1972
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Superseded AD: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Superseded By: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: 72-08-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1425

AD NUMBER:   72-08-03

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

ACTION:  

SUMMARY:  

DATES:   Effective May 1, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
72-08-03 HAWKER SIDDELEY AVIATION: Amdt. 39-1425. Applies to Hawker Siddeley Model DH-114 "Heron" airplanes.

Compliance is required as indicated.

To detect cracks in the upper arm of the rudder control pedal reversal lever, P/N 4CF.767A, accomplish the following:

(a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished within the last 2,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service from the last inspection, inspect the upper area of the rudder control pedal reversal lever, P/N 4CF.767A, for cracks using a dye penetrant method in accordance with Hawker Siddeley Technical News Sheet Series: "Heron" 114, No. C.F.15, Issue 1, dated October 19, 1970, or later ARB-approved issue or FAA-approved equivalent. If no cracks are found, visually inspect the upper radiused surface of the upper arm of the rudder control reversal lever for marks or other evidence of mechanical damage.

(b) If a crack is found during an inspection required by paragraph (a), before further flight replace the cracked part with a new part of the same part number and continue to inspect in accordance with paragraph (a).

(c) If marks or other evidence of mechanical damage are found during an inspection required by paragraph (a), before further flight smoothly blend out the marks and renew the protective treatment, using a selenious acid treatment, and repaint the part. After refitting the part, continue to inspect in accordance with paragraph (a).

This amendment becomes effective May 1, 1972.

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