AD 89-03-15

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AD Number:
89-03-15
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DORNIER Models Do28 D and Do28 D-1 Airplanes
Subject:
Horizontal Tail Rivets
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/03/1989
Make:
Dornier Luftfahrt GmbH
Model:
Do 28 D | Do 28 D-1
Product Type:
Aircraft
Product Subtype:
Small/Large 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Superseded AD: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Superseded By: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: 89-03-15
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6130

AD NUMBER:   89-03-15

SUBJECT HEADING:   Airworthiness Directives; DORNIER Models Do28 D and Do28 D-1 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 3, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   89-03-15 DORNIER: Amendment 39-6130.

Applicability: Models Do28 D and Do28 D-1 (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 100 hours time-in-service and every 100 hours time-in-service thereafter after the effective date of this AD, unless already accomplished.

To preclude the loss of the horizontal tail, accomplish the following:

(a) Visually inspect in accordance with Dornier Service Bulletin No. 1110-3204, dated April 15, 1988, as follows:

(1) Inspect the rivet connections between the left hand and right hand horizontal tail bearing fittings and the lateral skins for loose rivets. If loose rivets are found, before further flight replace the loose rivets in accordance with Dornier Service Bulletin No. 1110-3204, and

(2) Inspect the rear fuselage frame 10420 and the corner gusset for cracks. If cracks are detected, before further flight repair as follows:

(i) For cracks less than 25mm (.98 inch), stop drill the crack in accordance with Dornier Service Bulletin No. 1110-3204.

(ii) For cracks 25mm or longer (.98 inch or more), repair the airplane in accordance with instructions from Dornier approved by the Manager, Aircraft Certification Staff, AEU-100.

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

(c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium.

All persons affected by this directive may obtain a copy of the document referred to herein upon request to Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium; or Dornier GmbH, P.O. Box 2160, D- 8000 Munchen 66, Federal Republic of Germany; or may examine this document at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment (39-6130, AD 89-03-15) becomes effective on March 3, 1989.

FOOTER: