AD 72-14-08 R1

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AD Number:
72-14-08 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CESSNA Models 310, 320, 401, 402, 411 and 421 Series Airplanes
Subject:
Flexible Hose Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/04/1981
Make:
Cessna Aircraft Company
Model:
310 | 310A | 310B | 310C | 310D | 310E | 310F | 310G | 310H | 310I | 310J | 310J-1 | 310K | 310L | 3...Show more
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Superseded AD: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Superseded By: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: 72-14-08 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4215

AD NUMBER:   72-14-08 R1

SUBJECT HEADING:   Airworthiness Directives; CESSNA Models 310, 320, 401, 402, 411 and 421 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 4, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
72-14-08 R1 CESSNA: Amendment 39-1484 as amended by Amendment 39-4215. Applies to Models 310, 320, 401, 402, 411 and 421 series airplanes.

On airplanes having 200 hours or more time-in-service and thereafter at intervals not to exceed 60 hours time-in-service, to determine condition of flammable fluid-carrying flexible hose assemblies in the engine compartment, accomplish the following:

A. Visually, or by any other method approved by FAA, inspect flexible fuel lines as follows:

(1) Pressurize the fuel lines with boost pump momentarily operating in prime position. When accomplishing this test, the mixture control should be in the idle cutoff position. While under pressure, examine all hose exteriors in the engine compartment for evidence of leakage such as wetness and fuel stains.

NOTE: After pressure testing fuel hoses, allow sufficient time for excess fuel to drain overboard from the engine manifold before attempting an engine start.

(2) Examine externally all hoses in the engine compartment for evidence of deterioration or damage such as cracks, cuts, bulges, discoloration, hardness, chafing and excessive wear.

B. Visually, or by any other method approved by FAA, inspect flexible oil lines as follows:

(1) Examine all hose exteriors in the engine compartment for evidence of leakage.

(2) Examine externally all hoses in the engine compartment for evidence of deterioration or damage such as cracks, cuts, bulges, discoloration, hardness, chafing and excessive wear.

C. If, as a result of the inspections required by Paragraphs A or B, leakage or other evidence of deteriorated or damaged hose assembly is found, replace with serviceable hose assembly prior to further flight.

NOTE: Cessna Service Letter ME68-23, dated November 1, 1968, and applicable Cessna Service Manuals pertain to paragraphs A, B, and C.

D. This AD does not apply to the following airplanes which were manufactured with improved fuel and oil system flexible hose assemblies in the engine compartment:

Model	Serial Number
310R	310R0001 and on
402C	402C0001 and on
421C	421C0001 and on

E. This AD does not apply to those airplanes which have improved fuel and oil system flexible hose assemblies installed in the engine compartment in accordance with Cessna Service Information Letter ME81-17 dated July 10, 1981.

F. Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209, telephone (316) 942-4285.

Amendment 39-1484 became effective July 14, 1972.

This amendment 39-4215 becomes effective September 4, 1981.


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