AD 67-29-02

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AD Number:
67-29-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild-Hiller Model F-27 and FH-227 Airplanes
Subject:
Navigation Instruments
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/27/1967
Make:
Maryland Air Industries, Inc.
Model:
F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M | FH-227 | FH-227B | FH-227C | FH-227D | FH-227E
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Superseded AD: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Superseded By: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: 67-29-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-498

AD NUMBER:   67-29-02

SUBJECT HEADING:   Airworthiness Directives; Fairchild-Hiller Model F-27 and FH-227 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 27, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-29-02 FAIRCHILD-HILLER: Amdt. 39-498 Part 39 Federal Register October 25, 1967. Applies to Type F-27 and FH-227 Airplanes.

Unless already accomplished, compliance is required with the next 200 hours' time in service after the effective date of this AD. To compensate for the loss of electrical power to the copilots' flight and navigation instruments (attitude, turn and bank, and gyroscopic direction indicators), in the event of a single ground fault in the D.C. power system, accomplish the following:

(a) In aircraft where the emergency electrical power to operate the copilot attitude indicator, turn and bank indicator, and gyroscopic direction indicator is derived from the D.C. power system, modify the emergency electrical power system for these instruments in a manner such that the emergency electrical power is derived from the right engine driven emergency alternator. Accomplish this by loading the emergency alternator (increasing the power factor to unity) to allow it to adequately power the three (3) instrument systems. The modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

(b) Modifications accomplished in accordance with Fairchild-Hiller FH-227 Service Bulletin 24-1, dated April 25, 1967, or Fairchild-Hiller FH-227 Service Bulletin 24-2, dated May 22, 1967, for the serial number applicable in the Bulletins, or later FAA-approved revisions, are acceptable for showing compliance with this Airworthiness Directive.

(c) Upon request, with substantiating data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.

This amendment effective October 27, 1967.

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