AD 78-10-01

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AD Number:
78-10-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Models D18C, D18S, E18S, E18S-9700, G18S, H-18, C-45G, TC-45G, C-45...Show more
Subject:
Lower Rudder Torque Tube
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/17/1978
Make:
Textron Aviation Inc.
Model:
3N | 3NM | C-45G | C-45H | D18C | D18S | E18S | E18S-9700 | G18S | H18 | JRB-6 | TC-45G | TC-45J
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 78-10-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3210

AD NUMBER:   78-10-01

SUBJECT HEADING:   Airworthiness Directives; BEECH Models D18C, D18S, E18S, E18S-9700, G18S, H-18, C-45G, TC-45G, C-45H, TC-45J (SNB-5), JRB-6, 3N, 3M, and 3NM Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 17, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-10-01 BEECH: Amendment 39-3210. Applies to Beech Models D18C, D18S, E18S, E18S-9700, G18S, H-18, C-45G, TC-45G, C-45H, TC-45J (SNB-5), JRB-6, 3N, 3M and 3NM modified in accordance with STC SA1243WE, SA1016WE, or SA360WE.

To preclude failure of the lower rudder torque tube, accomplish the following; unless already accomplished:

(a) Within the next 30 days after the effective date of this AD visually inspect the lower rudder torque tube for cracks in the area of the access hole as noted in figure 1 of this AD. (Reference Part Number 452606-7).

(b) If no cracks are found, reinspect at intervals not to exceed 30 days from the prior inspection.

(c) If cracks are found, prior to further flight:

(1) If any crack exceeds 1/2 inch in length, replace with a like serviceable unit, Part Number 452606-7, and reinspect per paragraph (d);

(2) If cracks are 1/2 inch or less in length, repair per a method approved by the Chief, Aircraft Engineering Division, FAA Western Region, and reinspect per paragraph (d);

(d) Reinspect at intervals not to exceed 30 days from repair, replacement, or prior inspection.

(e) The requirements of this AD may be terminated when modifications are incorporated which are approved by the Chief, Aircraft Engineering Division. Submit proposed modifications schemes to:

Chief, Aircraft Engineering Division
FAA Western Region
P.O. Box 92007
Worldway Postal Center
Los Angeles, California 90009

for review and approval.

This amendment becomes effective May 17, 1978.







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