AD 85-14-52

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AD Number:
85-14-52
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DeHavilland Model DHC-8-101 Airplanes
Subject:
AFM Limitations -- Flaps
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/31/1985
Make:
Bombardier Inc.
Model:
DHC-8-101
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Superseded AD: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Superseded By: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: 85-14-52
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5184

AD NUMBER:   85-14-52

SUBJECT HEADING:   Airworthiness Directives; DeHavilland Model DHC-8-101 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 31, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   85-14-52 DeHavilland Aircraft of Canada, LTD.: Amendment 39-5184. Applies to all Model DHC-8-101 airplanes, certificated in any category, equipped with flap drive power units, Sunstrand Part Number 734177A or 734177B, Serial Numbers 101, 103-105 inclusive, and 107- 110 inclusive. Compliance is required as indicated, unless previously accomplished.

To reduce the hazards associated with flap drive power unit malfunctions, prior to further flight, accomplish the following:

A. Incorporate the following into the limitations section of the airplane flight manual. This may be accomplished by including a copy of this AD in the airplane flight manual.

1. Flaps extended speed (VFE) is limited to 130 KIAS for all flap angles;

2. Single engine approach training is prohibited;

3. The flap indicator must be monitored to confirm that the selected angle is achieved; and

4. In the event of an engine inoperative approach, flap should be selected as early as possible and landing flap should not be selected until the landing is assured. If the selected flap angle is exceeded, flap must be reselected to 0 degrees and the approach and landing continued at not less than the 0 flap 1.3 VS in figure 5/5A-4-2.

B. Within two weeks after the effective date of this amendment, replace the flap drive power units listed above with 27-2 units modified in accordance with DHC Service Bulletin 8-27-6 dated July 10, 1985, and remove the AFM limitations required by paragraph A., above.

C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to DeHavilland Aircraft of Canada, Ltd., Garrett Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington, or the FAA, New England Region, New York Aircraft Certification Office, 1815 South Franklin Avenue, Room 202, Valley Stream, New York.

This amendment becomes effective December 31, 1985, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD 85-14-52, issued July 18, 1985.

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