AD 67-32-04

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AD Number:
67-32-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Pilatus Model PC-6 Series Airplanes
Subject:
Stabilizer Cable Trim Control Clamps
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/17/1967
Make:
Pilatus Aircraft Limited
Model:
PC-6 | PC-6-H1 | PC-6-H2 | PC-6/350 | PC-6/350-H1 | PC-6/350-H2 | PC-6/A | PC-6/A-H1 | PC-6/A-H2 | P...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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 67-32-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-525

AD NUMBER:   67-32-04

SUBJECT HEADING:   Airworthiness Directives; Pilatus Model PC-6 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 17, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   67-32-04 PILATUS: Amdt. 39-525, Part 39, Federal Register December 12, 1967. Applies to Model PC-6 Series Airplanes.
Compliance required as indicated.
(a) To prevent the possibility of stabilizer trim control cable clamps jamming with the cable guide tubes at bulkhead No. 8, accomplish the following:
(1) Within the next 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, inspect guide tubes, P/N 6232.208, for signs of movement or wear in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent.
(2) If signs of movement or wear are detected during the inspection required by paragraph (a)(1), before further flight incorporate the modification required by paragraph (a)(3).
(3) If no signs of movement or wear are detected during the inspections required by paragraph (a)(1), within the next 200 hours' time in service after the effective date of this AD, modify guide tubes, P/N 6232.208, and install an additional support, P/N 6232.468, in accordance with Pilatus Service Bulletin No. 72, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region.
(b) To prevent excessive rubbing of the rudder control cable with its fairlead at bulkhead No. 2, accomplish the following:
(1) Within the next 100 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 cable phenolic fairlead for signs of wear in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an FAA-approved equivalent.
(2) If signs of wear are detected during the inspection required by paragraph (b)(1), within the next 25 hours' time in service replace worn fairlead with a serviceable fairlead.
(3) Within the next 600 hours' time in service after the effective date of this AD, replace the pulley and fairlead assembly with a double pulley assembly in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region.
(c) To prevent excessive rubbing of the stabilizer trim control cable with its pulley at bulkhead No. 11, accomplish the following:
(1) Within the next 100 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 cable and its pulley for signs of wear, in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision or an FAA-approved equivalent.
(2) If signs of wear are detected during the inspection required by paragraph (c)(1), within the next 25 hours' time in service replace worn cable or pulley with a serviceable cable or pulley.
(3) Within the next 600 hours' time in service after the effective date of this AD, modify the double pulley in accordance with Pilatus Service Bulletin No. 74, dated June 1967, or later Swiss Federal Air Office-approved revision, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region.
(d) The repetitive inspections required by paragraphs (a)(1), (b)(1), and (c)(1) may be discontinued following the incorporation of the applicable modification in accordance with paragraphs (a)(3), (b)(3), and (c)(3), respectively.
This amendment effective December 17, 1967.

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