AD 69-25-06

AD Final Rules - DRS_69-25-06.html
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AD Number:
69-25-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes
Subject:
Aileron Lever
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/03/1970
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Superseded AD: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Superseded By: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: 69-25-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-887

AD NUMBER:   69-25-06

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation, Ltd Model DH-104 Dove Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 3, 1970.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-25-06 HAWKER SIDDELEY AVIATION, LTD: Amdt. 39-887. Applies to Model DH-104 Dove Airplanes which have aileron lever P/N 4 WA.315 installed.

Compliance is required as indicated unless already accomplished.

To prevent fatigue failure of the aileron lever, accomplish the following:

(a) Visually inspect the aileron lever, P/N 4 WA.315 for cracks at the lugs for the attachment of the connecting rod and in the counterbored portion which receives the mass balance arm within the next 50 hours' time in service after the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. If evidence of cracks is found, verify using dye penetrant or other FAA-approved equivalent inspection methods.

(b) If cracks are found during the inspection required by paragraph (a), before further flight, install a new forged aileron lever, P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.

(c) If no cracks are found during the inspections required by paragraph (a), within the next 1,000 hours' time in service after the effective date of this AD, install a new forged aileron lever P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.

(d) The inspection required in paragraph (a) may be discontinued after the new aileron lever, P/N 4 WA.491 or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region is installed.

(Hawker Siddeley Aviation, Ltd. Technical News Sheet CT (104) No. 151, Issue 4, dated 14 July 1969 covers this subject.)

This supersedes Amendment 454, Part 507 (27 F.R. 5793) AD 62-14-02.
This amendment becomes effective January 3, 1970.

FOOTER: