AD 91-12-04

AD Final Rules - DRS_91-12-04.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
91-12-04
Document Type:
AD Final Rules
Docket Number:
90-NM-290-AD
Subject Heading:
Airworthiness Directives; GENERAL DYNAMICS Model 240, T-29, and C-131A (Military) Series Airplanes
Subject:
Elevator Hinge Pins
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/25/1991
Make:
Kelowna Flightcraft R & D Ltd.
Model:
240 Series
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Superseded AD: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Superseded By: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: 91-12-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-290-AD

AMENDMENT:   39-7015

AD NUMBER:   91-12-04

SUBJECT HEADING:   Airworthiness Directives; GENERAL DYNAMICS Model 240, T-29, and C-131A (Military) Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 25, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-12-04 GENERAL DYNAMICS (CONVAIR): Amendment 39-7015. Docket No. 90-NM-290-AD.
Applicability: Model 240, T-29, and C-131A (Military) series airplanes, including all airplanes converted to turbopropeller power, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent loss of the elevator hinge pins, accomplish the following:

A. Within 50 hours time-in-service or 60 days after the effective date of this AD, whichever occurs first, remove the elevator and conduct a visual inspection of the elevator hinge pins and bearings, in accordance with Part I of the Accomplishment Instructions of General Dynamics, Convair Division Service Bulletin 600 (240D) 55-4, dated September 21, 1990 (hereinafter referred to as "SB 55-4").

NOTE: Inspections previously accomplished in accordance with the Accomplishment Instructions of Alert Service Bulletin 600 (240D) 55-A4, dated March 1, 1990, are considered to comply with the requirements of this AD.

B. Any hinge pins, bushings, or tapered bushings found which do not conform to the dimensional limitations specified in Part I of SB 55-4, must be replaced prior to further flight.

C. Any cracked bearing plate assemblies or nut assemblies, and any loose, chattering, dry, or seized bearings, P/N AN201KP10A, must be replaced prior to further flight.

D. When the elevator is reinstalled, determine if proper mating of the tapered bushing and pin surfaces exists, in accordance with Part I of SB 55-4. If proper mating does not exist, the pin must be reworked prior to further flight, in accordance with Part II of SB 55-4.

E. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO.

The inspection and repair requirements shall be done in accordance with General Dynamics, Convair Division Service Bulletin 600 (240D) 55-4, dated September 21, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Dynamics, Convair Division, P.O. Box 85377, San Diego, California 92138, Attention: Chief, Aircraft Logistical Support, Mail Zone 92-2920. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C.

This amendment (39-7015, AD 91-12-04) becomes effective on July 25, 1991.

FOOTER: