AD 64-21-06 R2

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AD Number:
64-21-06 R2
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BOEING VERTOL Model 107-II Helicopters
Subject:
Sockets & Rotor Housings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/07/1980
Make:
Columbia Helicopters, Inc.
Model:
107-II
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Superseded AD: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Superseded By: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: 64-21-06 R2
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3827

AD NUMBER:   64-21-06 R2

SUBJECT HEADING:   Airworthiness Directives; BOEING VERTOL Model 107-II Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective July 7, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
64-21-06 R2 BOEING VERTOL: Amendment 813 Part 507 Federal Register September 10, 1964 as amended by Amendment 39-2156 is further amended by Amendment 39-3827. Applies to Model 107-II helicopters.

Compliance required as indicated.

As a result of a fatigue failure in service of the rotor pitch housing, accomplish the following:

(a) Unless already accomplished within the last 30 hours' time in service, before further flight, inspect the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with 260 or more hours' time in service using magnetic particle inspection method or FAA approved equivalent. To accomplish the inspection, remove rotor blades and rotor hub pitch bearing assemblies. Repeat this inspection at intervals not to exceed 30 hours' time in service.

(b) Inspect, using magnetic particle inspection, the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8 with less than 260 hours' time in service in accordance with (a) prior to the accumulation of 260 hours' time in service.

(c) Conduct a daily visual inspection for cracks in the lug areas of all rotor pitch housings P/N's 107R2553-1, -2, -3, -4, -5, and -6 and blade sockets P/N's 42R1043-7 and -8. This may be accomplished without disassembly from the helicopter.

(d) Unless already accomplished, within the next 50 hours in service on pitch housing 107R2553-8, -10, -14, -16, with 1000 hours or more in service and within the next 100 hours in service on pitch housing 107R2553-7, -9, -13, 15, with 2000 hours or more in service install crack detector wire in accordance with Part I "Installation Procedure" of Boeing Service Bulletin No. 107-343 dated March 10, 1980, or equivalent.

(1) Inspect for cracks in accordance with Part II "Inspection Procedures" of the above Bulletin, or equivalent, the lug area of pitch housings 107R2553-8, -10, -14, -16 with 1000 hours or more in service within the next 50 hours in service and thereafter at intervals not to exceed 25 hours in service, and pitch housing 107R2553-7, -9, -13, -15 with 2000 hours or more in service within the next 100 hours in service and thereafter at intervals not to exceed 50 hours in service.

(2) Unless already accomplished, install crack detector wire in accordance with Part I "Installation Procedure" of the above Bulletin, or equivalent on pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service prior to the accumulation of 1050 hours in service, and on pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service prior to the accumulation of 2100 hours in service.

(3) Inspect pitch housings 107R2553-8, -10, -14, -16 with less than 1000 hours in service in accordance with (1) prior to accumulation of 1050 hours in service. Inspect pitch housings 107R2553-7, -9, -13, -15 with less than 2000 hours in service in accordance with (1) prior to accumulation of 2100 hours in service.

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

(e) If any cracks are found replace the part before further flight with a part found serviceable in accordance with this AD.

(f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance times specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(g) Retire from service all rotor pitch housings P/N's 107R2553-7, -8, -9, -10, -13, - 14, -15, d -16 upon the accumulation of 5,000 hours' total time in service.

This supersedes AD 64-06-08.
Amendment 39-813 was effective September 10, 1964.
Amendment 39-2156 was effective April 9, 1975.
This Amendment 39-3827 is effective July 7, 1980.

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