AD 72-08-02

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AD Number:
72-08-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation Model DH-114 Heron Series 2 Airplanes
Subject:
Main and Damper Jack Bolts
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Superseded AD: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Superseded By: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: 72-08-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1424

AD NUMBER:   72-08-02

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation Model DH-114 Heron Series 2 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 1, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
72-08-02 HAWKER SIDDELEY AVIATION: Amdt. 39-1424. Applies to Model DH- 114 "Heron" Series 2 airplanes.

Compliance is required as indicated.

To prevent failures of the main undercarriage main and damper jack attachment bolts, P/N 14-2U.229 and P/N 14-2U.631, accomplish the following:

(a) For airplanes with main undercarriage units that have any P/N 14-2U.229 main and damper jack attachment bolts installed, within the next 150 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks.

(b) For airplanes with main undercarriage units that have only P/N 14-2U.631 (Modification 1536) main and damper jack attachment bolts installed, within the next 1,200 hours' time in service after the effective date of this AD, unless already accomplished within the last 1,200 hours' time in service, and thereafter at intervals not to exceed 2,400 hours' time in service from the last inspection, remove and visually inspect the attachment bolts for cracks.

(c) If any bolt is found to be cracked during an inspection required by paragraph (a) or (b), before further flight replace the cracked bolt in accordance with subparagraph (1) or (2):

(1) Replace a cracked bolt, P/N 14-2U.229 with either a serviceable bolt of the same part number or replace with a serviceable bolt, P/N 14-2U.631 (Modification 1536), and continue to inspect in accordance with paragraphs (a) or (b) as applicable.

(2) Replace a cracked bolt, P/N 14-2U-631 (Modification 1536), with a serviceable bolt of the same part number and continue to inspect in accordance with paragraphs (a) or (b) as applicable.

This amendment becomes effective May 1, 1972.

FOOTER: