AD 83-07-16

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AD Number:
83-07-16
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Short Model SC-7 Series 3 Series Airplanes
Subject:
Vertical Fin
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/14/1983
Make:
Short Brothers PLC
Model:
SC-7 Skyvan Series 3
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Superseded AD: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Superseded By: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: 83-07-16
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4618

AD NUMBER:   83-07-16

SUBJECT HEADING:   Airworthiness Directives; Short Model SC-7 Series 3 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 14, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-07-16 SHORT BROTHERS AND HARLAND, LTD.: Amendment 39-4618. Applies to Model SC-7 Series 3 (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 100 hours time-in-service after the effective date of this AD.

To preclude looseness of either vertical fin accomplish the following:
(a) Remove Access Panel Nos. T15, T16, and T17 from the vertical fins in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and paragraph (A) (1) of Shorts Service Bulletin No. 55-53, Original Issue, dated June 25, 1979.

(b) Apply 12-15 in-lbs torque to the 10-32 UNF bolts (one at a time) that attach the fins to the stabilizer (24 bolts in the front spar and 16 bolts in the rear spar).
1. If torque of 12-15 in-lbs can be applied to each bolt without rotating the bolt, replace Access Panel Nos. T15, T16, and T17 in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and return the airplane to service.
2. If a bolt rotates with the application of 12-15 in-lbs of torque, remove each rotating bolt (one at a time) and inspect bolt hole for elongation.
(i) If no elongation of the bolt hole is found, add additional washer under the bolt head or nut (maximum of 2 washers under the nut and 1 under the bolt head), apply 12-15 in-lbs torque to bolt and return airplane to service.
NOTE: If less than 2 full threads protrude past nut after torquing, replace bolt with a bolt of the same type with a grip length increased by one over the original bolt grip length.
(ii) If elongation of the bolt hole is found, reinstall bolts in accordance with paragraphs (b) 1 and 2 of this AD and within 200 hours time-in-service repair in accordance with instructions provided by Short Brothers Ltd., P.O. Box 241, Airport Road, Belfast BT3 9DZ and approved as an equivalent method of compliance in accordance with paragraph (e) of this AD. Replace Access Panel Nos. TI5, T16, and T17 in accordance with Shorts Skyvan Maintenance Manual, Chapter 7-00, Page 6, Figure 4, and return airplane to service.

(c) The compliance times required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections and repairs concurrent with other scheduled maintenance of the airplane.

(d) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished.

(e) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

This amendment becomes effective on April 14, 1983.

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