AD 74-03-02

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AD Number:
74-03-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives: BEECH Models F33A , V35B, A36, 95-B55, 95-B55A, E55, E55A, 58 and 58A Airplanes.
Subject:
Landing Gear Shock Strut Piston
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/05/1974
Make:
Textron Aviation Inc.
Model:
58 | 58A | 95-B55 | 95-B55A | A36 | E55 | E55A | F33A | V35B
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Superseded AD: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Superseded By: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: 74-03-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1777

AD NUMBER:   74-03-02

SUBJECT HEADING:   Airworthiness Directives: BEECH Models F33A , V35B, A36, 95-B55, 95-B55A, E55, E55A, 58 and 58A Airplanes.


ACTION:  

SUMMARY:  

DATES:   Effective February 5, 1974.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
74-03-02 BEECH: Amendment 39-1777. Applies to Model F33A (Serial Numbers CE- 436 thru CE-463 except CE-439 and CE-462); Model V35B (Serial Numbers D-9469 thru D- 9536 except D-9481, D-9532 and D-9533); Model A36 (Serial Numbers E-425 thru E-475 except E-431); Models 95-B55 and 95-B55A (Serial Numbers TC-1552 thru TC-1607 except TC-1557, TC-1558, TC-1599 and TC-1604); Models E55 and E55A (Serial Numbers TE-914 through TE-940 except TE-919, TE-920 and TE-938); and Models 58 and 58A (Serial Numbers TH-325 thru TH-383 except TH-336, TH-337, TH-363 and TH-382) airplanes.

Compliance: Required as indicated, unless already accomplished per Beechcraft Service Instructions 0612-200 or later FAA-approved revisions.

To check landing gear shock strut pistons for proper hardness, within the next 100 hours' time in service after the effective date of this AD, accomplish the following.

A) Using a portable hardness tester, measure the hardness of the nose gear shock strut piston in an area from 1 inch to 4 inches above the nose wheel fork. The allowable hardness range is from Rockwell Scale C38 to C46 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained.

B) Using a portable hardness tester, measure the hardness of both main gear shock strut pistons in an area 1 inch to 4 inches above the axle socket. The allowable hardness range is from Rockwell Scale C43 1/2 to C50 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained.

C) If a hardness measurement is outside of the hardness range specified in Paragraphs A and/or B of this AD, prior to further flight, replace any defective landing gear shock strut piston with an airworthy piston, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed, provided the landing gear remains down and locked.

This amendment becomes effective February 5, 1974.

FOOTER: