AD 87-13-02

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AD Number:
87-13-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Pilatus Model BN-2A Mk III, BN-2A Mk III-1, BN-2A Mk 111-2, and BN-2A Mk 1...Show more
Subject:
Elevator Trim Tab Assemblies
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/27/1987
Make:
B-N Group Ltd.
Model:
BN2A MK. III | BN2A MK. III-2 | BN2A MK. III-3
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Superseded AD: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Superseded By: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: 87-13-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5649

AD NUMBER:   87-13-02

SUBJECT HEADING:   Airworthiness Directives; Pilatus Model BN-2A Mk III, BN-2A Mk III-1, BN-2A Mk 111-2, and BN-2A Mk 111-3 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 27, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-13-02 PILATUS BRITTEN-NORMAN, Ltd.: Amendment 39-5649. Applies to Models BN-2A Mk III, BN-2A Mk III-1, BN-2A Mk 111-2, and BN-2A Mk 111-3 (all serial numbers) Trislander airplanes certificated in any category.

Compliance: Required within 30 days after the effective date of this AD, unless already accomplished, and every 24 calendar months thereafter. To prevent structural failure of the elevator trim tab operating rods, accomplish the following:

(a) Remove the two (2) elevator trim tab operating rod assemblies in accordance with the instructions contained in the "INSPECTION" section of Pilatus Britten-Norman, Ltd., Mandatory Service Bulletin (MSB) No. BN-2/SB.179, Issue 1, dated January 30, 1987 (hereinafter referred to as MSB BN-2/SB.179).

(1) Disassemble one end of each control rod and visually examine the rod (tube) internally and externally for corrosion, rust, or cracks.

(i) If any corrosion, rust, or crack is found, before further flight, replace the control rod and accomplish paragraphs (a) (1) through (a) (3) of this AD on the replacement unit.

(ii) If no defect is found, clean and apply corrosion protection to the rod in accordance with the "RECTIFICATION" instructions of MSB BN-2/SB.179, and

(2) Visually inspect each ball end or fork fitting and sleeve (Part Number (P/N) NB-45- 2627), after removing any surface rust, for pitting, discoloration, or cracks. If any evidence of corrosion, pitting, discoloration, or crack is found, before further flight:

(i) Replace the defective part with a serviceable unit.

(ii) Remove the fitting and sleeve from the other end of the associated control rod and repeat the inspection specified in paragraph (a) (2) of this AD.

(3) Reassemble the control rods in accordance with the "RECTIFICATION" instructions of MSB BN-2/SB.179.

(4) Reinstall the control rod in accordance with the "RETURNING THE AIRCRAFT TO SERVICE" instructions of MSB BN-2/SB.179.

(b) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished.

(c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 10O0 Brussels, Belgium.

All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman, Ltd., Bembridge, Isle of Wight, England; or may examine the document referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment, 39-5649, becomes effective on July 27, 1987.

FOOTER: