AD 77-01-08

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AD Number:
77-01-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Rockwell International Model 112 Airplanes
Subject:
Engine Failure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/14/1977
Make:
Commander Aircraft Corporation
Model:
112
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Superseded AD: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Superseded By: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: 77-01-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2805

AD NUMBER:   77-01-08

SUBJECT HEADING:   Airworthiness Directives; Rockwell International Model 112 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 14, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-01-08 ROCKWELL INTERNATIONAL: Amendment 39-2805. Applies to Model 112 airplanes (Serial Numbers 3 through 470) certificated in all categories.

Compliance required as indicated. To prevent engine failure due to loss of engine oil from failure of the engine oil pressure tube assembly, accomplish the following:

a. As a part of each preflight check, after the effective date of this airworthiness directive, conduct a visual check of the P/N 46320-1 copper oil pressure tube assembly for cracks and oil leakage, particularly in the areas where the copper tube and its fittings attach. If any cracks or leakage are detected, remove and replace such assembly as described in paragraph c below before further flight.

b. Within the next ten hours' time in service after the effective date of this airworthiness directive and thereafter at intervals not to exceed ten hours' time in service, accomplish the following:

(1) Remove the upper engine cowling.

(2) Clean the copper oil pressure tube assembly, P/N 46320-1, with an oil soluble solvent.

(3) Start and operate the engine until it is warm enough to respond smoothly to throttle changes (monitor oil temperature and cylinder head temperature gauges to maintain temperatures within limits), then stop the engine.

(4) Check the copper oil pressure tube assembly, P/N 46320-1, for cracks, chaffing, or any signs of oil leakage.

(5) If any of the conditions in step 4 above are detected, remove and replace such assembly as described in paragraph c below before further flight.

(6) Part I(1)(b) of Rockwell International Service Bulletin No. SB-112-46 dated November 2, 1976, refers to this same subject.

A pilot may perform the requirements of items a and b above pursuant to the provisions of FAR 43.3(h).

NOTE: For the requirements regarding the listing of compliance and method of compliance with paragraphs a and b of this AD in the aircraft permanent maintenance record, see FAR 91.173.

c. Within 50 hours' time in service after the effective date of this airworthiness directive, remove the P/N 46320-1 copper oil pressure tube assembly, the P/N 46080-1 elbow, the AN919-0 reducer, and the P/N 46136-47 hose assembly and replace them with P/N 46136-63 hose assembly and P/N 46080-3 elbow in accordance with Part II of Rockwell Commander Service Bulletin No. SB-112-46 dated November 2, 1976, or later FAA DOA approved revision. Previous compliance with Rockwell Commander Service Letter No. SL-112-26, June 3, 1976, satisfies this airworthiness directive.

d. The checks required by paragraphs a and b of this airworthiness directive are no longer required after paragraph c of this airworthiness directive is accomplished.

e. 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. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Customer Service Department, Avenue, Bethany, Oklahoma 73008. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Region Office in Fort Worth, Texas.

f. Any alternate equivalent method of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration.

This amendment becomes effective on January 14, 1977.

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