AD 88-24-51

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AD Number:
88-24-51
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Boeing Model DHC-8-100 Series Airplanes
Subject:
Elevator Control System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/27/1989
Make:
Bombardier Inc.
Model:
DHC-8-101 | DHC-8-102 | DHC-8-103 | DHC-8-106
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Superseded AD: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Superseded By: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: 88-24-51
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6107

AD NUMBER:   88-24-51

SUBJECT HEADING:   Airworthiness Directives; Boeing Model DHC-8-100 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 27, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   88-24-51 BOEING CANADA, DE HAVILLAND DIVISION: Amendment 39-6107. Final copy of telegraphic airworthiness directive, issued December 9, 1988.

Applicability: Model DHC-8-100 series airplanes, Serial Numbers 1 through 126, certificated in any category.

Compliance: Required within the next 50 hours time-in-service, unless previously accomplished.

To preclude the possibility of deformation or jamming of the elevator control system, accomplish the following:

A. Remove inspection panels 121 BL and 121 BR or the floor panel in flight compartment aft of center console, and inspect the elevator control quadrant levers, Item 160/Part Numbers 82710146-101 (left side) and 82710146-102 (right side), for correct installation. Ensure that the curved portion of each lever points forward.

B. If both left and right levers curve forward, no further action is necessary and the inspection panels may be reinstalled.

C. If either lever curves rearward, inspect the associated push rod for evidence of bending or binding. Replace, prior to further flight, any incorrectly installed levers and damaged push rods with new or serviceable units, as applicable.

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, FAA, New England Region.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office.

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 Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York.

Amendment 39-6107 was effective earlier to all recipients of Telegraphic AD T88-24-51, issued December 9, 1988.

This amendment (39-6107, AD 88-24-51) becomes effective January 27, 1989.

FOOTER: