AD 93-17-11

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AD Number:
93-17-11
Document Type:
AD Final Rules
Docket Number:
93-NM-41-AD
Subject Heading:
Airworthiness Directives; De Havilland Models DHC-8-100 Series and DHC-8-300 Series Airplanes
Subject:
Horizontal Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/08/1993
Make:
Bombardier Inc.
Model:
DHC-8-101 | DHC-8-102 | DHC-8-103 | DHC-8-106 | DHC-8-301 | DHC-8-311 | DHC-8-315
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 93-17-11
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   93-NM-41-AD

AMENDMENT:   39-8682

AD NUMBER:   93-17-11

SUBJECT HEADING:   Airworthiness Directives; De Havilland Models DHC-8-100 Series and DHC-8-300 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 8, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-17-11 DE HAVILLAND, INC.: Amendment 39-8682. Docket 93-NM-41-AD.

Applicability: Model DHC-8-100 series airplanes, serial numbers 003 through 315 inclusive, 317 through 344, inclusive, and 346 through 349 inclusive; and Model DHC-8-300 series airplanes, serial numbers 100 through 319 inclusive, 321 through 337 inclusive, 339, 341, and 342; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced strength and fail-safe capability of the structural attachment of the horizontal stabilizer to the airplane, accomplish the following:

(a) Within 250 landings after the effective date of this AD, perform a one-time magnetic particle inspection of the horizontal stabilizer midspar attachment bolts to detect cracks at the radius transition between the bolt head and shank in accordance with de Havilland Alert Service Bulletin S.B. A8-55-18, dated February 5, 1993.

(b) If any crack is found in a bolt, prior to further flight, replace both midspar attachment bolts with serviceable bolts in accordance with de Havilland Alert Service Bulletin S.B. A8-55-18, dated February 5, 1993.

(c) As of the effective date of this AD, no person shall install a midspar attachment bolt, part number MS21250-10070, on any airplane unless, prior to installation, the bolt has been inspected using magnetic particle techniques to detect cracks in accordance with de Havilland Alert Service Bulletin S.B. A8-55-18, dated February 5, 1993.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO.

(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) The inspection and replacement shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-55-18, dated February 5, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This amendment becomes effective on October 8, 1993.

FOOTER: