AD 87-18-03

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AD Number:
87-18-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; ROBINSON HELICOPTER COMPANY Model R22 Series Helicopters
Subject:
Main Rotor Pitch Link Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/25/1988
Make:
Robinson Helicopter Company
Model:
R22 | R22 ALPHA | R22 BETA | R22 MARINER
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Superseded AD: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Superseded By: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: 87-18-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5875

AD NUMBER:   87-18-03

SUBJECT HEADING:   Airworthiness Directives; ROBINSON HELICOPTER COMPANY Model R22 Series Helicopters

ACTION:  

SUMMARY:  

DATES:   Effective April 25, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-18-03 ROBINSON HELICOPTER COMPANY: Amendment 39-5875. Final copy of priority letter AD 87-18-03. Applies to Model R22 series helicopters, certificated in any category, Serial Numbers 0580 through 0644, and helicopters which have had the A258-1 main rotor pitch link assembly, A258-2 fitting, A258-3 link or A258-4 link assembly replaced between August 15, 1986, and May 7, 1987.

Compliance required as indicated, unless already accomplished.

(a) Prior to further flight after the effective date of this AD, visually inspect main rotor pitch link assembly A258-1 (two per aircraft) as follows:

(1) Remove paint and visually inspect the A258-1 pitch link assembly employing a 3X or greater magnifying glass.

(2) If a crack is found in the A258-2 upper fitting, replace it with a like serviceable part, prior to further flight.

(3) If a crack is found in the A258-3 lower link, replace the A258-1 pitch link assembly with a like serviceable part, prior to further flight.

NOTE: The A258-3 lower link and the B163-1 rod end make up the lower end A258-4 link assembly, as shown in Figure 2 of Robinson Helicopter Company Service Bulletin No. 57, dated May 11, 1987.

(4) Replace the A258-2 upper fitting in the pitch link assembly using the following steps.

NOTE: Reference the procedure given in Part B of Robinson Helicopter Company, Service Bulletin No. 57, dated May 11, 1987.

(i) Color code swashplate arms, pitch horns, and both pitch control link rod ends. If matching color marks are lost or length of pitch link assembly changes, a track and balance of the main rotor blades per Section 10.200, Track and Balance, dated May 22, 1987, or Robinson Helicopter Company maintenance manual or an approved equivalent.

(ii) Remove pitch links and measure overall length using a caliper or large micrometer. Record length to nearest 0.001 inch.

(iii) Disassemble pitch link. Do not remove rod end attached to A258-3 link assembly. Replace A258-2 fitting with like serviceable part.

(iv) Reassemble pitch link(s), keeping overall length to within plus minus 0.005 of length measured before disassembly.

(v) Install on helicopter, and torque attaching bolts to 100 inch-lbs., plus nut drag per Section 8.412, Swashplate Installation, dated May 22, 1987, of Robinson Helicopter Company maintenance manual or an approved equivalent.

(vi) Touch up paint using an epoxy primer and grey exterior paint. Mark all joints with a torque stripe.

(b) If no cracks are found in a link assembly, upper fitting or lower link, after visual inspection in paragraph (a)(1), the helicopter may be returned to service for an interval of time not to exceed 10 hours time in service.

(c) Prior to each flight during the time interval specified in paragraph (b), visually check for cracks in the link assembly. The checks required by this AD may be performed by the pilot and must be recorded in accordance with FAR Section 43.9.

(d) Within the next 10 hours time in service after receipt of this AD, remove and replace A258-2 fittings with serviceable parts. Conduct a dye penetrant or equivalent inspection for crack indications in the A258-3 link. Install airworthy parts in accordance with paragraph (a) (4).

(e) Replacement of all A258-2 fittings specified in this AD with serviceable fittings and inspection of the A258-3 links terminates action for these repetitive checks required by this AD.

(f) An alternate method of compliance with this AD which provides an equivalent level of safety, may be approved by the Manager, Western Aircraft Certification Office, FAA, P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007.

This amendment becomes effective on April 25, 1988, as to all persons except those persons to whom it was made immediately effective by priority letter AD 87-18-03, issued August 28, 1987, which contained this amendment.

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