AD 75-23-06

AD Final Rules - DRS_75-23-06.html
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AD Number:
75-23-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Slingsby Model T59D Kestrel Gliders
Subject:
Rudder Cable
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/27/1976
Make:
Slingsby Aviation Ltd.
Model:
T.59.D Kestrel
Product Type:
Aircraft
Product Subtype:
Glider
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 75-23-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2606

AD NUMBER:   75-23-06

SUBJECT HEADING:   Airworthiness Directives; Slingsby Model T59D Kestrel Gliders

ACTION:  

SUMMARY:  

DATES:   Effective May 27, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   75-23-06 SLINGSBY SAILPLANES: Amendment 39-2417 as amended by Amendment 39-2606. Applies to T59D Kestrel gliders certificated in all categories.

Compliance is required as indicated.

To prevent possible rudder cable failure, accomplish the following:

(a) Within the next 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, inspect the rudder cables for broken wires of any strand at the points the cables leave the top of the rudder pedals throughout the maximum to minimum rudder pedal adjustment range, and also immediately aft of the cable ferrules.

(b) If a broken wire of any strand is found during an inspection required by paragraph (a) of this AD, before further flight, replace the defective cable with a serviceable cable of the same specification or an FAA- approved equivalent cable and continue to comply with paragraph (a).

(c) The repetitive inspections required by this AD may be discontinued after a rudder pedal stop, P/N 59A-45-445, or an FAA approved equivalent is installed as follows:

(1) Remove the instrument panel.

(2) Remove the two screws (self tapping type) retaining the pedal assembly cover (channel section) and remove this cover.

(3) Position the stop to the upper guide tube and push it firmly up against the forward tube support; tighten the bolts.

(4) Replace the pedal assembly cover and instrument panel.

(5) Check controls for full and free operation.

NOTE: Vickers-Slingsby Technical Instruction No. 78, dated March 15, 1976, also covers the installation of the rudder pedal stop.

Amendment 39-2417 became effective November 19, 1975.

This amendment 39-2606 becomes effective May 27, 1976.

FOOTER: