AD 90-08-10 ACTIVE

90-08-10 FAIRCHILD INDUSTRIES, INC.: Amendment 39-6573. Docket No. 89-NM-265-AD.

Applicability: All Model F-27 and FH-227 series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent reduced structural capability of the wing due to undetected fatigue cracks, accomplish the following:

A. Within 25 hours time-in-service after August 21, 1989 (the effective date of AD 89-15-01, Amendment 39-6292), perform a dye penetrant inspection for cracks in the wing outer panel upper surface stringer splice fitting, in accordance with Fairchild Industries Service Bulletin F27-51-8, dated April 22, 1974, [reference paragraph 2A(6)(e), page 5; and Figure 14, page 24] or Fairchild Industries Service Bulletin FH227-51-4, dated January 17, 1979 [reference paragraph 2A(6)(e), page 5; and Figure 14, page 23], as appropriate, and Maryland Air Industries Alert Service Letters F27-681 and FH227-57-6, both dated June 29, 1989, as appropriate.

B. If cracks are found in the wing outer panel upper surface stringer splice fittings, prior to further flight, accomplish the following:

1. If cracks found are less than or equal to .100 inch on the Model F-27 series airplanes, or less than or equal to .075 inch on the Model FH-227 series airplanes, perform the blending operation in accordance with Maryland Air Industries Drawing No. D27-7723, dated July 27, 1989. Perform a dye penetrant inspection after the blending operation to ensure that all damaged material has been removed. Pay particular attention to the maximum torque value and gaps as shown on Maryland Industries Drawing D27-7723, dated July 27, 1989.

2. If cracks found are more than .100 inch on the Model F-27 series airplanes, or more than .075 inch on the Model FH-227 series airplanes, replace aluminum fittings with new steel fittings, in accordance with Maryland Air Industrie Drawing No. 27-133008, dated July 28, 1989.

NOTE: For thoseairplanes that have removed and replaced the wing outer panel upper surface stringer splice fittings, with serviceable parts, in accordance with AD 89-15-01, Amendment 39-6292, accomplish the requirements of paragraph C., below. Included in this group of airplanes are those that were granted an alternate means of compliance to the requirement of replacement with serviceable parts.

C. Within one year time-in-service after the effective date of this AD, replace all aluminum fittings part number (P/N) 27-133008-21 with a new steel fitting, P/N 27-133008-23, in accordance with Maryland Air Industries Drawing No. 27-133008, dated July 28, 1989.

D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who willeither concur or comment and then send it to the Manager, New York Aircraft Certification Office, ANE-170, FAA, New England Region.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Maryland Air Industries, Inc., Hagerstown, Maryland 21740. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the New York Aircraft Certification Office, FAA, New England Region, 181 South Franklin Avenue, Valley Stream, New York.

Airworthiness Directive 90-08-10 supersedes AD 89-15-01, Amendment 39-6292.

This amendment (39-6573, AD 90-08-10) becomes effective on May 14, 1990.