AD 87-25-07

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AD Number:
87-25-07
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE Model H.S. 748 Airplanes
Subject:
Engine Support Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/19/1988
Make:
BAE Systems (Operations) Limited
Model:
HS 748 Series 2A | HS 748 Series 2B
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 87-25-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5789

AD NUMBER:   87-25-07

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE Model H.S. 748 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 19, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   87-25-07 BRITISH AEROSPACE: Amendment 39-5789. Applies to all Model H.S. 748 airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.

To prevent severe stress and damage to the engine support structure, accomplish the following:

A. Within the next 6 months after the effective date of this AD, or prior to accumulating 6,000 landings, whichever is later, and thereafter at intervals not to exceed 2,000 landings, perform a visual inspection of the engine subframe/wing attachment assemblies in accordance with paragraph 2A of British Aerospace Service Bulletin 54-29, dated October 1986. Any assembly found to exhibit excessive movement or wear must be repaired, prior to further flight, in a manner approved by the FAA.

B. No later than the next scheduled engine removal after the effective date of this AD or prior to accumulating 6,000 landings, whichever is later, and thereafter at intervals not to exceed 6,000 landings, perform a visual inspection of the engine subframe/wing attachment assemblies while trying to induce movement in accordance with paragraph 2C of British Aerospace Service Bulletin 54-29, dated October 1986. Any components found to be unserviceable must be repaired, prior to further flight, in a manner approved by the FAA.

C. Prior to the next scheduled engine removal after the effective date of this AD, or prior to accumulating 12,000 landings, whichever is later, and thereafter at intervals not to exceed 12,000 landings, perform an inspection with the taper bolt and taper split-bush removed from the engine subframe/wing attachment assemblies in accordance with paragraph 2D of British Aerospace Service Bulletin 54-29, dated October 1986. Any components found to be unserviceable must be repaired, prior to further flight, in a manner approved by the FAA.

D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.

All persons affected by this proposal who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414 Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This amendment becomes effective January 19, 1988.

FOOTER: