AD 87-24-51 R1

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AD Number:
87-24-51 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; SAAB-FAIRCHILD Model SF-340A Series Airplanes
Subject:
Engine Control Cables
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/02/1988
Make:
Saab AB, Saab Aerosystems
Model:
340A (SAAB SF340A)
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Superseded AD: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Superseded By: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: 87-24-51 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5894

AD NUMBER:   87-24-51 R1

SUBJECT HEADING:   Airworthiness Directives; SAAB-FAIRCHILD Model SF-340A Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 2, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   87-24-51 R1 SAAB-FAIRCHILD: Amendment 39-5822 as amended by Amendment 39- 5894. Applies to all Model SF-340A series airplanes, certificated in any category.

Compliance is required as indicated, unless previously accomplished.

To prevent a reduction in airplane controllability or propeller/engine overspeed due to sheared engine power control cable pins, accomplish the following:

A. Prior to the accumulation of 25 flight hours time-in-service after the effective date of this amendment, unless accomplished within the last 175 flight hours time-in-service, and thereafter at intervals not to exceed 200 flight hours time-in-service, inspect the engine power control cables, part numbers C82146-1 or C82146-2, located between the hydro mechanical engine control units and the propeller control units, for axial play, in accordance SAAB Service Bulletin SF340-76A-024, Revision 2, dated February 15, 1988.

B. If axial play is detected during the inspection required by paragraph A., above, replace the cable with an airworthy cable assembly prior to further flight, and repeat the inspections required by paragraph A. at intervals not to exceed 200 flight hours time-in-service.

C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.

D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to SAAB Scania, Product Support, S-58188, Linkoping, Sweden. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

TAD 87-24-51 was issued November 17, 1987, and became effective upon receipt. Amendment 39-5822 became effective January 27, 1988. This Amendment, 39-5894, becomes effective May 2, 1988.

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