AD 83-07-04 R1

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AD Number:
83-07-04 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Short Model SC-7 Series 3 Airplanes
Subject:
Flight Control System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/23/1983
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Superseded AD: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Superseded By: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: 83-07-04 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4665

AD NUMBER:   83-07-04 R1

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

ACTION:  

SUMMARY:  

DATES:   Effective June 23, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-07-04 R1 SHORT BROTHERS LTD.: Amendment 39-4604 as amended by Amendment 39-4665. Applies to Model SC-7 Series 3 (all serial numbers) airplanes certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To preclude failure of the primary flight control systems, accomplish the following:
a) Within the next 100 hours time-in-service after the effective date of this AD and at intervals not to exceed 500 hours time-in-service thereafter:
1) Visually inspect the control system linkage connections listed in paragraph a)3) of this AD in accordance with Short Brothers Service Bulletin (SB) No. 27-66, dated November 18, 1977. Each connection typically consists of a clevis (control rod) and rod- end bearing joined by a pin as shown on Figure 1 of SB No. 27-66. Each end of the pin must be secured by a retaining plate bonded to the clevis and one end must have a locking rivet through the pin and clevis.
2) If a retaining plate or locking rivet are found to be loose or detached from the clevis, prior to further flight, repair the connection in accordance with instructions in SB No. 27-66.z.
3) The locations of the control system linkage connections to be inspected are as follows (refer to page 3 of SB No. 27-66):
i) One location in each wing on the aileron control rod.
ii) Twenty-four locations in control rods along the upper fuselage between Stations 96 and 410.

b) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplanes.

c) The repetitive inspections required by this AD may be discontinued upon incorporation of Modification 1674 as described in Revision 1 to Short Brothers SB No. 27-66, dated March 31, 1978, and SB No. 27-68, dated January 19, 1979.

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 or Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

Amendment 39-4604 became effective on April 11, 1983.
This Amendment 39-4665 becomes effective June 23, 1983.

FOOTER: