AD 75-27-07

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AD Number:
75-27-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Pilatus Model PC-6 Airplanes (all variants)
Subject:
Rudder Bars
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/21/1976
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Superseded AD: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Superseded By: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: 75-27-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2479

AD NUMBER:   75-27-07

SUBJECT HEADING:   Airworthiness Directives; Pilatus Model PC-6 Airplanes (all variants)

ACTION:  

SUMMARY:  

DATES:   Effective January 21, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   75-27-07 PILATUS AIRCRAFT LTD. and FAIRCHILD HILLER: Amendment 39- 2479. Applies to Pilatus Model PC-6 airplanes (all variants), serial numbers 338 through 623, manufactured by Pilatus Aircraft Ltd. and serial numbers 2001 through 2067, manufactured by Fairchild Hiller.
Compliance is required as indicated.
To prevent a fatigue failure of the pilot and copilot rudder bar junction welded seam, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the junction fillet welds of the pilot and copilot rudder bars (P/Ns 6232.145, 6232.241, and 116.35.06.004) and determine whether the weld covers the full 360 degrees of the rudder bar tube circumference or only 250 degrees of the rudder bar tube circumference. If the weld is determined to be of the improved 360 degrees design, no further action is required by this AD.
(b) If the fillet weld is found to be of the non-continuous (250 degrees) weld design, visually inspect the rudder bar junction weld for cracks by applying magnaflux or by the dye check method in accordance with paragraph 2.1 of Pilatus Aircraft Ltd. Service Bulletin No. 120, dated January 1973, or an FAA-approved equivalent.
(c) If no cracks are found during the inspection required by paragraph (b) of this AD, within the next 100 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service, visually inspect the rudder bar junction weld for cracks using a 10 power magnifying glass in accordance with paragraph 2.2 of Pilatus Aircraft Ltd. Service Bulletin No. 120, dated January 1973, or an FAA-approved equivalent.
(d) If cracks are found during an inspection required by paragraphs (b) or (c) of this AD, either repair the rudder bar junction weld in accordance with paragraph 2.3 of Pilatus Aircraft Ltd. Service Bulletin no. 120, dated January 1973, or an FAA-approved equivalent, or replace the rudder bars with new rudder bars of the same part number but with improved 360 degrees weld design.
(e) Within the next 100 hours' time in service after accomplishing the repair described in paragraph (d) of this AD, or, if no cracks were found during the inspections required by paragraphs (b) or (c) of this AD, within the next 300 hours' time in service after complying with the inspection requirements of paragraph (b) of this AD, replace the rudder bars, P/N 6232.145, 6232.241, with new rudder bars of the same part number incorporating the continuous full 360 degree fillet weld around the rudder bar circumference.
This amendment becomes effective on January 21, 1976.

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