AD 90-24-03

AD Final Rules - DRS_90-24-03.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
90-24-03
Document Type:
AD Final Rules
Docket Number:
90-CE-69-AD
Subject Heading:
Airworthiness Directives; FAIRCHILD AIRCRAFT (SWEARINGEN AIRCRAFT) Models SA26, SA226, and SA227 Ser...Show more
Subject:
Rudder Trim Link Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/25/1991
Make:
M7 Aerospace LLC
Model:
SA226-AT | SA226-T | SA226-TC | SA226-T(B) | SA227-AC (C-26A) | SA227-AT | SA227-BC (C-26A) | SA227-...Show more
Product Type:
Aircraft
Product Subtype:
Small/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Superseded AD: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Superseded By: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: 90-24-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-CE-69-AD

AMENDMENT:   39-6837

AD NUMBER:   90-24-03

SUBJECT HEADING:   Airworthiness Directives; FAIRCHILD AIRCRAFT (SWEARINGEN AIRCRAFT) Models SA26, SA226, and SA227 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 25, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-24-03 FAIRCHILD AIRCRAFT (SWEARINGEN AIRCRAFT): Amendment 39-6837. Final copy of Priority Letter 90-24-03. Docket No. 90-CE-69-AD.

Applicability: SA26, SA226, and SA227 series airplanes (all serial numbers), certificated in any category.

Compliance: Required within the next 15 hours time-in-service or 10 calendar days after receipt of this AD, whichever occurs first, unless already accomplished.

To prevent aerodynamic vibration, structural deformation, and possible loss of control of the airplane, accomplish the following:

(a) Visually inspect the rudder trim tab link assemblies (Part Numbers 27-42025-001 through 27-42025-009 as installed) as follows:

(1) Remove the fairing strip between the vertical fin and rudder.

(2) Check each connecting rod end for freedom of movement and corrosion around the bearing as follows:

(i) Move the rudder trim system from full left to full right deflection and check for any indications of corrosion or binding in the rod end fittings.

(ii) If necessary, remove the bolt connecting the actuator and each rod end and check the bearings for freedom of movement.

(iii) Check the bolts connecting the rudder actuator to each rod end to insure each bolt is oriented vertically.

(3) If either rod end is corroded, prior to further flight replace the affected rod end with a serviceable part.

(4) If the rudder trim mechanism is incorrectly installed, or if either rod end bearing is binding, prior to further flight replace the affected connecting rod and rod end assembly with serviceable parts.

(5) If corrosion or binding is not found, reinstall the fairing strip and return the airplane to service.

NOTE 1: Fairchild Aircraft Service Notes 26-SN-061, 226-SN-162, and 227-SN-074 pertain to the subject of this AD.

NOTE 2: Although not required by this AD, the inspections specified in this AD should be included in the regular aircraft maintenance program.

(b) Airplanes may be flown in accordance to FAR 21.197 and 21.199 to a location where this AD may be accomplished.

(c) An alternate method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, Southwest Region, FAA, Fort Worth, Texas 76193-0150; Telephone (817) 624-5150.

NOTE 3: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Airplane Certification Office, Fort Worth, Texas 76193-0150.

This amendment (39-6837, AD 90-24-03) becomes effective on January 25, 1991, as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-24-03, issued November 20, 1990, which contained this amendment.

FOOTER: