AD 79-02-07

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AD Number:
79-02-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation, Limited (British Aerospace) Model DH-104 "Dove" ...Show more
Subject:
Wing to Fuselage Attachment
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/19/1979
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Superseded AD: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Superseded By: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: 79-02-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3399

AD NUMBER:   79-02-07

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation, Limited (British Aerospace) Model DH-104 "Dove" Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 19, 1979.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
79-02-07 HAWKER SIDDELEY AVIATION, LIMITED (BRITISH AEROSPACE): Amendment 39-3399. Applies to DH-104 "Dove" airplanes, all series, certificated in all categories, except those airplanes modified in accordance with STC SA1747WE.

Compliance required as indicated.

To prevent possible failure of the wing to fuselage attachment and loss of wing in flight, accomplish the following:

(a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, remove the port and starboard wing root fairings and inspect the upper three lugs at each end of the center section main spar top boom, P/N 4FS.135 A/1, for cracks using an ultrasonic method of inspection in accordance with Appendix 1 of Hawker Siddeley Aviation, Ltd., Technical News Sheet TNS 237, dated September 9, 1976, (hereinafter referred to as the Technical News Sheet) or an FAA-approved equivalent.

NOTE: This inspection can be conducted with the wing installed.

(b) If no cracks are found during the inspection required by paragraph (a) of this AD, repeat the inspection at intervals not to exceed 1200 flight hours or 2 calendar years, whichever occurs sooner, until the wings are removed for compliance with AD 72-16-07 at which time the area must be further inspected using the ultrasonic and dye penetrant methods in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent. Thereafter, if no cracking is found, continue to inspect the area as follows:

(1) In accordance with the method specified in paragraph (a) of this AD at an interval not to exceed 3 calendar years from each time the area is inspected in conjunction with the wing removal required by AD 72-16-07; and

(2) In accordance with the ultrasonic and dye penetrant methods specified in Appendix 2 of the Technical News Sheet or an FAA-approved equivalent at each time the wings are removed for compliance with AD 72-16-07.

(c) If any cracks are found during any inspection required by this AD to be performed in accordance with the method specified in paragraph (a) of this AD, further inspect by ultrasonic and dye penetrant methods in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent with the wing removed.

(d) If, during any inspection required by this AD, cracking of the lugs is found which is confined to only one of the lugs per side of the aircraft and exists only from the bolt hole towards the outboard end of the lug, the center section carry through boom may remain on the aircraft and continued flight is permitted provided the wing is removed at intervals not to exceed 300 flight hours or 3 months, whichever is sooner, and the cracked lug is inspected for crack propagation and the remaining two lugs are inspected for cracking, all in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent, until the boom is replaced with a new boom of the same part number or a used boom of the same part number determined after inspection in accordance with Appendix 2 of the Technical News Sheet to be crack-free.

(e) If, during any inspection required by this AD, cracking is found in more one lug per side of the aircraft or the cracking of any one lug extends to both sides (inboard and outboard) of the bolt hole or runs from the bolt hole in an inboard direction only, before further flight, replace the carry through boom with a new boom of the same part number or a used boom of the same part number determined after inspection in accordance with Appendix 2 of the Technical News Sheet to be crack-free. Replacement booms must continue to be inspected in accordance with the following schedule:

(1) For used replacement booms, within 3 years from replacement, inspect the lug area in accordance with Appendix 1 of the Technical News Sheet or an FAA-approved equivalent except if any wing removal is required by AD 72-16-07 during that period, inspect in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent concurrently with that wing removal. Thereafter inspect in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD.

(2) For new replacement booms, inspect the lug area in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent with the wing removed prior to accumulating 6 years in service and thereafter in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD. However, if the first inspection required after replacement is not performed in conjunction with a wing removal required by AD 72-16-07, within the next 3 years after that inspection, inspect in accordance with Appendix 1 of the Technical News Sheet or an FAA-approved equivalent except if any wing removal is required by AD 72-16-07 during that period inspect in accordance with Appendix 2 of the Technical News Sheet or an FAA-approved equivalent concurrently with that wing removal and thereafter inspect in accordance with the schedule and inspection methods specified in paragraphs (b)(1) and (b)(2) of this AD.

This amendment becomes effective February 19, 1979.

FOOTER: