AD 89-03-07

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AD Number:
89-03-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; British Aerospace Model HP 137 Mk.1, Jetstream Models 200 and 3101 Airplanes
Subject:
Main Wing Spar Attachment
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/26/1989
Make:
British Aerospace Regional Aircraft
Model:
H.P. 137 Jetstream Mk. 1 | Jetstream Series 200 | Jetstream Series 3101
Product Type:
Aircraft
Product Subtype:
Small/Large 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Superseded AD: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Superseded By: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: 89-03-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6118

AD NUMBER:   89-03-07

SUBJECT HEADING:   Airworthiness Directives; British Aerospace Model HP 137 Mk.1, Jetstream Models 200 and 3101 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 26, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   89-03-07 BRITISH AEROSPACE (BAe) PLC: Amendment 39-6118.

Applicability: Model HP 137 Mk l Jetstream Model 200, and Jetstream Model 3101 (includes Model 3100) (all serial numbers) airplanes certificated in any category.

Compliance: Required as indicated in the body of the AD after the effective date of this AD, unless already accomplished.

To prevent reduction of strength of the main wing spar attachment structure, accomplish the following:

(a) Upon the accumulation of 4,000 landings or within the next 400 landings, whichever occurs later, and thereafter at intervals of 2,000 landings, visually or dye penetrant inspect, as required, the Part Number (P/N) 13707B99 and P/N 13707B100 shear angles for cracks as described in BAe Alert Service Bulletin (ASB) Jetstream 57-A-JA880144, dated June 14, 1988, Section 2, ACCOMPLISHMENT INSTRUCTIONS.

(1) If a crack is detected that is 1-1/2 inch (37 mm) in total length, or 1 inch (25 mm) vertically or longer, prior to further flight modify the airplane in accordance with BAe Modification JM5303, dated June 14, 1988, by replacing the shear angles with P/N 13707B125 and P/N 13707B126 shear angles.

(2) If a crack is detected that is less than 1 inch vertically or 1-1/2 inch total length, re-inspect the shear angles thereafter at intervals not to exceed 100 landings, and prior to an additional 400 landings modify the airplane in accordance with BAe Modification JM5303, dated June 14, 1988.

(b) If no record of landings is available, 1 hour time-in-service equals 2 landings may be used in determining the compliance times in this AD.

(c) The inspections described in paragraph (a) above are not required when the airplane's left and right shear angles have been modified by BAe Modification JM5303, dated June 14, 1988.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

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

All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace PLC, Manager, Product Support, Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment (39-6118, AD 89-03-07) becomes effective on February 26, 1989.

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