AD 81-14-05

AD Final Rules - DRS_81-14-05.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
81-14-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD. Model KV 107-II and KV 107-IIA Helicopters
Subject:
Pitch Bearing Housings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/09/1981
Make:
Kawasaki Heavy Industries, Limited
Model:
KV107-II | KV107-IIA
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 81-14-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4149

AD NUMBER:   81-14-05

SUBJECT HEADING:   Airworthiness Directives; KAWASAKI HEAVY INDUSTRIES, LTD. Model KV 107-II and KV 107-IIA Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective July 9, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-14-05 KAWASAKI HEAVY INDUSTRIES, LTD.: Amendment 39-4149. Applies to Model KV 107-II and KV 107-IIA helicopters, certificated in all categories.

Compliance required as indicated, unless already accomplished.

To prevent fatigue failure of the rotor pitch housing, accomplish the following:

(a) For aft rotor pitch bearing housings, P/N's 107R2553-8, -10, -14, and -16:

(1) Prior to the accumulation of 1,000 hours time in service, or within the next 50 hours time in service after the effective date of this AD, whichever occurs later, install crack detector wires on pitch bearing housings in accordance with Part I, "Installation Procedure," of Kawasaki Service Bulletin No. KSB-V107-615, dated September 10, 1980 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent.

(2) Within the next 50 hours time in service after the effective date of this AD, inspect the lug area of the pitch bearing housings for cracks in accordance with Part II, "Inspection Procedure," of the Service Bulletin, or an FAA-approved equivalent, and continue to inspect at intervals not to exceed 25 hours time in service.

(b) For forward rotor pitch bearing housings, P/N's 107R2553-7, -9, -13, and -15:

(1) Prior to the accumulation of 2,000 hours time in service, or within the next 100 hours time in service after the effective date of this AD, whichever occurs later, install crack detector wires on pitch bearing housings in accordance with Part I, "Installation Procedure," of the Service Bulletin, or an FAA-approved equivalent.

(2) Within the next 100 hours time in service after the effective date of this AD, inspect the lug area of the pitch bearing housings for cracks in accordance with Part II, "Inspection Procedure," of the Service Bulletin, or an FAA-approved equivalent, and continue to inspect at intervals not to exceed 50 hours time in service.

(c) Conduct a visual inspection for cracks in the lug area of blade sockets, P/N's 42R1043-11, -12, -13, and -14, at intervals not to exceed 50 hours time in service. This may be accomplished without disassembly from the helicopter.

(d) If any cracks are found as a result of the inspections required by paragraphs (a), (b), and (c) of this AD, before further flight, replace with a serviceable part of the same part number, or an FAA-approved equivalent, and continue to inspect in accordance with this AD.

(e) Retire from service all rotor pitch bearing housings, P/Ns 107R2553-7, -8, -9, -10, -13, -14, -15, and -16, prior to the accumulation of 5,000 hours time in service.

(f) If an equivalent means of compliance is used in complying with this AD, that equivalent means must be approved by the Chief, Airworthiness District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii.

(g) Upon request of an operator and submission of substantiating data, the Chief, Airworthiness District Office, Pacific-Asia Region, may upon recommendation of the cognizant FAA aviation safety inspector adjust the compliance time specified in this AD.

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 Kawasaki Heavy Industries, Ltd., Aircraft Division, Kawasakicho, Kakamigahara, Gifu Prefecture, Japan. The documents may also be examined at the FAA, Pacific-Asia Region, Airworthiness District Office, 300 Ala Moana Blvd., Room 7321, Honolulu, Hawaii 96850, and Rules Docket, Room 916, 800 Independence Avenue, SW., Washington, DC 20591.

This amendment becomes effective July 9, 1981.

FOOTER: