AD 81-22-02

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AD Number:
81-22-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GENERAL DYNAMICS Model 340 and 440 Airplanes
Subject:
Elevator Outer Torque Tube
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/29/1981
Make:
Kelowna Flightcraft R & D Ltd.
Model:
340 | 440 | Military C-131B | Military C-131D | Military C-131E | Military C-131F/R4Y-1
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 81-22-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4236

AD NUMBER:   81-22-02

SUBJECT HEADING:   Airworthiness Directives; GENERAL DYNAMICS Model 340 and 440 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 29, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   81-22-02 GENERAL DYNAMICS: Amendment 39-4236. Applies to Model 340, 440 and military models eligible for civil use under Type Certificate 6A6, and all such model airplanes converted to turbopropeller power, certificated in all categories.

Compliance required as indicated, unless already accomplished.

To prevent potential loss of elevator control resulting from loosening and ultimate shearing of the elevator flange to outer torque tube aluminum (rivet) fasteners, accomplish the following:

(a) Within 250 hours' additional time in service after the effective date of this AD, unless previously accomplished within 450 hours' time in service prior to the effective date of this AD, and at intervals not to exceed 700 hours' time in service thereafter, conduct a visual inspection of both left and right hand elevator outer torque tube assembly P/N 340-3540304 attachment to flange P/N 240-3540320 for evidence of loose or sheared rivets in accordance with the accomplishment instructions of paragraph two (2) of General Dynamics Convair Division Service Bulletin 640(340D)27-6 dated February 23, 1981 (hereinafter referred to as SB 640(340D)27-6).

If any loose or sheared rivets in the elevator torque tube to flange attachment are found, replace all rivets with interference fitting steel fasteners in accordance with paragraph two (2) of SB 640(340D)27-6 prior to return of aircraft to service.

(b) The inspections required by this AD may be terminated when all 12 torque tube to flange attachment aluminum rivets are replaced by interference fitting steel fasteners with a minimum tensile strength of 160,000 psi in accordance with paragraph two (2) of SB 640(340D)27-6.

(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD.

(d) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western-Pacific Region.

(e) Reports of the discrepancies found are requested. The reports should cite: Airplane "N" number and serial number, nature of defect and part identification, total airplane operating hours, time since last inspection and AD compliance paragraph.

Forward reports to Chief, Engineering and Manufacturing Branch, FAA Western- Pacific Region by mail within 10 days of discovery. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.)

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to General Dynamics, Attn: Mr. Larry Hayes, Manager, Product Support, Convair Division, P.O. Box 80877, San Diego, California 92138. These documents may also be examined at FAA Western-Pacific Region Office, Office of the Regional Counsel, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261, and at FAA Headquarters, Rules Docket in Room 916, 800 Independence Avenue, S.W., Washington, D.C. 20591.

This amendment becomes effective October 29, 1981.

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