AD 90-19-01

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AD Number:
90-19-01
Document Type:
AD Final Rules
Docket Number:
90-CE-18-AD
Subject Heading:
Airworthiness Directives; PILATUS AIRCRAFT, LTD. AND FAIRCHILD-HILLER Model PC-6 series airplanes ...Show more
Subject:
Rudder Pedal Support
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/15/1990
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Superseded AD: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Superseded By: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: 90-19-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-CE-18-AD

AMENDMENT:   39-6719

AD NUMBER:   90-19-01

SUBJECT HEADING:   Airworthiness Directives; PILATUS AIRCRAFT, LTD. AND FAIRCHILD-HILLER Model PC-6 series airplanes manufactured by Pilatus Aircraft, Ltd., (Serial Number (S/N) 1 through 824), and to Model PC-6 airplanes manufactured by Fairchild-Hiller (S/N 2001 and up)

ACTION:  

SUMMARY:  

DATES:   Effective October 15, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-19-01 PILATUS AIRCRAFT, LTD., AND FAIRCHILD-HILLER: Amendment 39-6719. Docket No. 90-CE-18-AD.

Applicability: Model PC-6 series airplanes manufactured by Pilatus Aircraft, Ltd., (Serial Number (S/N) 1 through 824), and to Model PC-6 airplanes manufactured by Fairchild-Hiller (S/N 2001 and up) (all variants) fitted with welded steel rudder pedal supports, certificated in any category.

Compliance: Required initially within the next 50 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals of 100 hours TIS, unless already accomplished. To preclude failure of the welded steel rudder pedal supports, accomplish the following:

(a) Visually inspect the rudder pedal support for cracks using a 10x magnifying glass in accordance with:

(1) Alert Service Bulletin No. PC6-A-162 for those airplanes built by Pilatus Aircraft, Ltd.; or

(2) Service Bulletin No. PC6-27-15 for those airplanes built by Fairchild-Hiller.

(b) If cracks are found, prior to further flight, repair or replace the rudder pedal support with a serviceable airworthy unit in accordance with the instructions contained in the appropriate Service Bulletin listed in paragraph (a) of this AD.

(c) The repetitive 100 hour TIS inspections may be discontinued upon installation of a rudder pedal support manufactured from a machine casting Pilatus Part Number 116.35.06.104.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished.

(e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Pilatus Aircraft, Ltd., Product Support Department, CH6370 Stans, Switzerland, or Maryland Air Industries, Top Flight Airpark, Route 12, Box 102, Showalter Road, Hagerstown, Maryland 21740; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

This amendment (39-6719, AD 90-19-01) becomes effective on October 15, 1990.

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