AD 60-16-03

AD Final Rules - DRS_60-16-03.html
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AD Number:
60-16-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; DOUGLAS All DC3 Series Aircraft
Subject:
Geared Rudder Tab
Status:
Current
Citation:
(Federal Register: August 6, 1960)
Citation Publish Date:
08/06/1960
Effective Date:
Make:
The Boeing Company
Model:
DC3-G102 | DC3-G102A | DC3-G103A | DC3-G202A | DC3A-S1C3G | DC3A-S1CG | DC3A-S4C4G | DC3A-SC3G ...Show more
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Superseded AD: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Superseded By: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: 60-16-03
CITATION:   [Federal Register: August 6, 1960]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   60-16-03

SUBJECT HEADING:   Airworthiness Directives; DOUGLAS All DC3 Series Aircraft

ACTION:  

SUMMARY:  

DATES:  

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
60-16-03 DOUGLAS: Amdt. 188 Part 507 Federal Register August 6, 1960. Applies to All DC3 Series Aircraft With Geared Rudder Tab Installations Based On Data Approved Prior to the Effective Date of This Airworthiness Directive.

Compliance is required as indicated.

(a) In order to correct rudder force reversal tendencies on existing installations, the following shall be accomplished:

(1) Within two weeks after the effective date of this directive and until the aircraft has been flight tested or modified in accordance with this directive, a placard shall be placed in the aircraft in full view of the pilot which reads as follows:

"Possible rudder force reversal and/or rudder lock may be experienced in this aircraft if rudder application is not coordinated with lateral control. Avoid yawed flight."

This placard shall be retained in the airplane and complied with until either of the applicable procedures described in (2) have been accomplished.

(2) To remove the placard, either of the following procedures must be accomplished:

(i) INSPECTION AND TEST OF THE GEARED TAB INSTALLATION.

(a) Check the rigging of the geared rudder tab installation in accordance with the manufacturer's approved installation data to prove conformity of this installation prior to the required flight test below. The results of the rigging check must be recorded in the aircraft logbook and signed by the individual making the check.

(b) Contact the nearest FAA Regional Office and make arrangements through the Flight Test Branch for having the aircraft tested. The results of this flight test must be recorded in the aircraft logbook and signed by the individual conducting the flight test.

(c) If the rudder control characteristics in the flight test are found to meet the requirements of Civil Air Regulations, Part 4a, Sections 4a.758-T (or Civil Air Regulations, Part 4b, Section 4b.157), the placard in paragraph (1) may be removed.

(d) If the rudder control characteristics in the flight test are found not to meet the requirements of Civil Air Regulations, Part 4a, Section 4a.758-T (or Civil Air Regulations, Part 4B, Section 4b.157), the placard may not be removed until a corrective design modification has been made, officially inspected and flight tested, and found to comply with the above regulations.

(ii) REPLACEMENT WITH AN APPROVED NEW OR MODIFIED GEARED TAB INSTALLATION.
At such time as a "fix" or a new design installation has been developed, officially inspected and flight tested, and found to comply with the regulations, such an FAA approved modification or design may be installed in accordance with the manufacturer's specifications, a rigging and installation check made and recorded in the aircraft logbook by the individual who made the check. No mandatory flight tests will be necessary for such installations and the above-mentioned placard may be removed at this time.

(b) To preclude the installation on other aircraft of geared tabs of the same design which may have rudder force reversal tendencies, the following shall be accomplished prior to each approval:

(1) An official flight test shall be arranged with the nearest FAA Regional Office to determine that the installation complies with the regulations. The results of this flight test, as well as the prior inspection for conformity with approved installation data, must be recorded in the aircraft logbook and signed by the individuals conducting the installation inspection and flight test.

This directive shall become effective 30 days after the date of its publication in the Federal Register.


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