AD 83-12-02

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AD Number:
83-12-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives: Pilatus Model BN-2A MK III Trislander Series Airplanes
Subject:
Rudder Drive Lever Support Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/27/1983
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Superseded AD: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Superseded By: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: 83-12-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4668

AD NUMBER:   83-12-02

SUBJECT HEADING:   Airworthiness Directives: Pilatus Model BN-2A MK III Trislander Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 27, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
83-12-02 PILATUS BRITTEN-NORMAN LTD.: Amendment 39-4668. Applies to Model BN-2A MK III Trislander Series airplanes (all serial numbers), not incorporating Britten- Norman Mod. NB/M/908, certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To prevent the structural failure of the rudder drive lever support assembly and loss of rudder control, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following:

a) Replace the rudder drive lever support assembly attachment rivets with bolts in accordance with the instructions in "Part I" of the "Rectification" section of Britten-Norman Service Bulletin No. BN-2/SB.102, Issue 1, dated May 12, 1977 (hereinafter referred to as the SB).

b) Visually inspect the corners of the two rudder lever mounting channels for cracks in accordance with the "Inspection" section of the SB.

1) If no evidence of cracks in the lever mounting channels is found, repeat the inspection for cracks specified in paragraph b) of this AD at intervals not exceeding 100 hours time-in-service.

2) If cracks less than 0.25 inches in length are found, within the next 25 hours time-in-service, stop drill ends of cracks and install the modification described in "Part 2" of the "Rectification" section of the SB.

3) If cracks greater than 0.25 inches in length are found, before further flight, stop drill end of cracks and install the modification described in "Part 2" of the "Rectification" section of the SB.

c) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane.

d) The repetitive inspections required by paragraph b) of this AD may be discontinued upon installation of the modification as described in "Part 2" of the "Rectification" section of the SB.

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

f) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

This amendment becomes effective on July 27, 1983.

FOOTER: