AD 91-12-18

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AD Number:
91-12-18
Document Type:
AD Final Rules
Docket Number:
91-NM-12-AD
Subject Heading:
Airworthiness Directives; British Aerospace Model BAe 146-100A, -200A, and -300A Series Airplanes
Subject:
Fuselage Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/15/1991
Make:
BAE Systems (Operations) Limited
Model:
BAe 146-100A | BAe 146-200A | BAe 146-300A
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Superseded AD: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Superseded By: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: 91-12-18
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-NM-12-AD

AMENDMENT:   39-7030

AD NUMBER:   91-12-18

SUBJECT HEADING:   Airworthiness Directives; British Aerospace Model BAe 146-100A, -200A, and -300A Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective on July 15, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
91-12-18 BRITISH AEROSPACE: Amendment 39-7030. Docket No. 91-NM-12-AD.
Applicability: Model BAe 146-100A, -200A, and -300A series airplanes, which are post-modification HCM00301A or B and pre-modification HCM0l037A, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To prevent reduced structural integrity of the fuselage, accomplish the following:

A. Prior to the accumulation of 1,000 landings, or within 30 days after the effective date of this AD, whichever occurs later, perform a visual inspection of the fuselage skin between Frames 25 and 33 (100A series), Frames 25 and 33B (200A and 300A series) in the area of the fairing panel rubbing strips, including the reinforcing plates at Frames 26 and 29, in accordance with the Accomplishment Instructions of British Aerospace Service Bulletin 53-67, Revision 1, dated February 16, 1990.

1. Chafing damage found up to a maximum depth of 0.0l0 inch and no more than 6 inches in length, must be repaired prior to further flight, in accordance with paragraph 2.A.(2)(a) of the service bulletin.

2. Chafing damage found in excess of 0.0l0 inch in depth and more than 6 inches in length, must be repaired prior to further flight, in accordance with Structural Repair Manual (SRM) 53-00-12, or in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

B. Repeat the inspection required by paragraph A. of this AD at the following intervals:

1. For airplanes without rubbing strip installed: At intervals not to exceed 3,000 landings.

2. For airplanes with rubbing strips installed: At intervals not to exceed 9,000 landings.

C. Accomplishment of Modification No. HCM0l037A, the installation of a new silicone rubber seal with a metal insert, in accordance with British Aerospace Service Bulletin 53-67-01037A, dated October 17, 1989, constitutes terminating action for the repetitive inspections required by paragraph B. of this AD.

D. An alternative method 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, Transport Airplane Directorate.

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.

E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, 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, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington.

This amendment (39-7030, AD 91-12-18) becomes effective on July 15, 1991.

FOOTER: