AD 90-20-03

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AD Number:
90-20-03
Document Type:
AD Final Rules
Docket Number:
90-CE-16-AD
Subject Heading:
Airworthiness Directives; Wytwornia Sprzetu Komunikacyjnego Pzl-Mielec Models M18 and M18A Series Airplanes
Subject:
Aileron Hinge
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/17/1990
Make:
Polskie Zaklady Lotnieze Spolka zo.o
Model:
PZL M18 | PZL M18A
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Superseded AD: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Superseded By: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: 90-20-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-CE-16-AD

AMENDMENT:   39-6723

AD NUMBER:   90-20-03

SUBJECT HEADING:   Airworthiness Directives; Wytwornia Sprzetu Komunikacyjnego Pzl-Mielec Models M18 and M18A Series Airplanes

ACTION:   Final rule

SUMMARY:  

DATES:   Effective October 17, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   90-20-03 WYTWORNIA SPRZETU KOMUNIKACYJNEGO PZL-MIELEC: Amendment 39-6723. Docket No. 90-CE-16-AD.

Applicability: Models M18 and M18A (Dromader) (Serial Numbers 1Z00-101 through 1Z021-07) airplanes, certificated in any category.

Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals of 500 hours TIS until the aileron hinge is replaced with improved parts, unless already accomplished.

To prevent failure of the aileron control system, accomplish the following:

(a) Visually inspect with a 5x magnifying glass, or with fluorescent penetrant or magnetic crack detection methods, as appropriate, all aileron control system hinges for cracks and deformation in accordance with the instructions in PZL-Mielec, Mandatory Engineering Bulletin (MEB) No.K/02.132/89, approved September 7, 1989; Revised April 4, 1990.

(1) If cracks or damage are found on any aileron hinge, prior to further flight remove the aileron and replace the aileron hinge with an aileron hinge having Engineering Change Notice (ECN) 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD.

(2) If no cracks or damage are found to any aileron hinge, repeat the above inspection every 500 hours TIS until all aileron hinges are replaced with an aileron having ECN 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD.

(b) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(c) 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 Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30 extension 2710/2711; Facsimile (322) 230.05.34.

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 Office.

All persons affected by this directive may obtain copies of the document referred to herein upon request to Wytwornia Sprzetu Komunikacyjnego PZL-Mielec 39-301 Mielec, Poland; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.

This amendment (39-6723, AD 90-20-03) becomes effective on October 17, 1990.

FOOTER: