AD 82-03-09

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AD Number:
82-03-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SHORT BROTHERS LIMITED Model SD3-30 Series Airplanes
Subject:
Stub Wing Spar/Stub Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/01/1982
Make:
Short Brothers PLC
Model:
SD3-30
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 82-03-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4308

AD NUMBER:   82-03-09

SUBJECT HEADING:   Airworthiness Directives; SHORT BROTHERS LIMITED Model SD3-30 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 1, 1982.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   82-03-09 SHORT BROTHERS LIMITED: Amendment 39-4308. Applies to Model SD3-30 series airplanes, serial numbers SH3001 through SH3024 inclusive, certificated in all categories.

Compliance required prior to the accumulation of 12,000 landings, or 300 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings.

To prevent fatigue failures of the stub wing spar and stub wing bolted joints, accomplish the following:

(a) Inspect the bolt holes in the stub wing spars for cracks using the eddy current method described in Short Brothers "Non-destructive Test Specification," NDTI RD 1, dated October 1979, and in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraph 2, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent, and for airplane serial numbers SH3008 through SH3013 inclusive, replace the laminated aluminum shims in the stub wing bolted joints with single thickness shims in accordance with Short Brothers Limited Service Bulletin SD3-53-21, Revision 1, dated September 5, 1979, or an FAA-approved equivalent.

(b) If as a result of the inspection in paragraph (a) of this AD, no cracks are found, reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A.15 and 2A.11(b) for the front spar frame, and paragraphs 2A.15 and 2A.12(b) for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent.

(c) If as a result of the inspection required in paragraph (a) of this AD, cracks are found -

(1) Before further flight, except as provided in paragraph (f) of this AD, install Short Brothers Limited SD3-30 Modifications 5514, 5600 and 5790, in accordance with Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent; and

(2) Repair any bolt holes in which cracks are found and fit oversize bolts in accordance with paragraph 2A.11 for the front spar frame, and paragraph 2A.12 for the rear spar frame, of Short Brothers Limited Service Bulletin SD3-53-34, Revision 2, dated December 12, 1979, or an FAA-approved equivalent; and

(3) Reassemble the stub wing in accordance with "ACCOMPLISHMENT INSTRUCTIONS," paragraphs 2A, and 29 through 47, of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, or an FAA-approved equivalent.

(d) If cracks in the stub wing spar bolt holes cannot be removed by the procedure specified in paragraph (c)(2) of this AD, report those findings to the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, AEU-100, FAA, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04- R0174). Additional repair procedures must be approved by that office prior to returning aircraft to service.

(e) Upon incorporation of Short Brothers Limited Service Bulletin SD3-53-39, Revision 1, dated January 14, 1980, the repetitive inspection required by this AD may be discontinued.

(f) In accordance with FAR Sections 21.197 and 21.199, the airplane may be flown to a base where the inspections, modifications, and repairs required by this AD may be accomplished.

(g) If an equivalent means of compliance is used in complying with any paragraph of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.

(h) Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, Brussels, Belgium, may adjust the inspection intervals.

(i) For the purpose of this AD, when conclusive records are not available to show the total number of landings accumulated by a particular part (or assembly), the number of landings may be computed by dividing the airplane time-in-service since the part (or assembly) was installed in the airplane by the operator's fleet average time per flight for his Model SD3-30 series airplanes.

All persons affected by this directive who have not already received the referenced documents from the manufacturer may obtain copies upon request to Short Brothers Limited, P.O. Box 241, Airport Road, Belfast, BT 9DZ, Northern Ireland, Attention: Product Support Manager. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591.

This amendment becomes effective March 1, 1982.

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