AD 88-14-05

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AD Number:
88-14-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directive; HOFFMANN AIRCRAFT GES.M.B.H. Model H36 Dimona Gliders
Subject:
Horizontal Tail Surface Mount
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/13/1988
Make:
Diamond Aircraft Industries GmbH
Model:
H-36 DIMONA
Product Type:
Aircraft
Product Subtype:
Glider
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 88-14-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5930

AD NUMBER:   88-14-05

SUBJECT HEADING:   Airworthiness Directive; HOFFMANN AIRCRAFT GES.M.B.H. Model H36 Dimona Gliders

ACTION:  

SUMMARY:  

DATES:   Effective July 13, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
88-14-05 HOFFMANN AIRCRAFT GES.M.B.H.: Amendment 39-5930. Applies to model H36 Dimona motor gliders certificated in any category.

Compliance is required as indicated unless already accomplished.

To prevent failure of the rod end bearing on the front horizontal tail surface mount, accomplish the following:

(a) Within the next ten hours time in service after the effective date of this AD, visually inspect the rod end bearing on the front horizontal tail surface mount using a 5 power or greater magnifying glass for cracks in the area of the threaded shank, in accordance with inspection requirements of paragraph 1 of the Actions section of Hoffmann Aircraft Ges.m.b.h. Service Bulletin (SB) No. 15/2, dated January 20, 1987.

(b) Before further flight, replace cracked rod end bearings (SMXCP 10 M) with a modified rod end bearing, Hirschmann "SMXC 10 special design", in accordance with Work Instruction No. 7, contained in Hoffmann Aircraft Ges.m.b.h. SB No. 15/2, dated January 20, 1987.

(c) Within 50 flight hours after accomplishment of inspection per paragraph (a) of this AD, or prior to August 1, 1988, whichever comes first, replace any rod end bearing (SMXCP 10 M) not replaced in accordance with paragraph (b), in accordance with Work Instruction No. 7, contained in Hoffmann Aircraft Ges.m.b.H. SB No. 15/2, dated January 20, 1987.

(d) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 rue de la Loi B-1040 Brussels, Belgium; telephone No. 513.38.30, Ext. 2710; or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791- 6680.

(e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD.

Hoffmann Aircraft SB No. 15/2, dated January 20, 1987, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Hoffmann Aircraft, Ges.m.b.H., Richard Neutra Gasse 5, A-1214, Vienna, Austria. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 88-ANE-20, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays.

This amendment, 39-5930, becomes effective July 13, 1988.

FOOTER: