AD 82-01-02 R1

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AD Number:
82-01-02 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes
Subject:
Doors Inner Operating Handles
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/19/1984
Make:
Airbus SAS
Model:
BAC 1-11 200 Series | BAC 1-11 400 Series
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Superseded AD: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Superseded By: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: 82-01-02 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4824

AD NUMBER:   82-01-02 R1

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 19, 1984.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   82-01-02 R1 BRITISH AEROSPACE, AIRCRAFT GROUP (formerly British Aircraft Corporation): Amendment 39-4285 as amended by Amendment 39-4824. Applies to Model BAC 1-11 200 and 400 series airplanes, certificated in all categories, which have not incorporated British Aerospace Modification PM 5703.

Compliance required as indicated.

To detect cracking and prevent possible failures of the passenger and service door inner operating handles and endfittings, accomplish the following:

(a) On airplanes which have not incorporated British Aerospace Modification PM 5176, within the next 600 hours time in service after the effective date of this AD, unless already accomplished, remove the passenger door inner handle and inspect the handle tube and reinforcing liners and handle for cracks in accordance with paragraph 2.1, "ACCOMPLISHMENT INSTRUCTIONS," of British Aerospace Alert Service Bulletin 52-A-PM5703, Issue 1, dated September 3, 1979 (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent.

(b) On airplanes which incorporate British Aerospace Modification PM 5176, prior to the accumulation of 10,000 hours time in service since the incorporation of this modification, or within the next 600 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished, remove the passenger door inner handle and inspect the handle tube and reinforcing liners in accordance with paragraph 2.2, "ACCOMPLISHMENT INSTRUCTIONS," of the Service Bulletin, or an FAA-approved equivalent.

(c) On airplanes which have not incorporated British Aerospace Modification PM5703, prior to the accumulation of 10,000 hours time in service, or within the next 600 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished, remove and inspect the endfitting, P/N AB24-4269, for cracks in accordance with paragraph 2.3, "ACCOMPLISHMENT INSTRUCTIONS," of the Service Bulletin, or an FAA- approved equivalent.

(d) If no cracks are found during the inspections required by paragraph (a), (b), or (c) of this AD, repeat these inspections at intervals not to exceed 1800 hours time in service from the last inspection.

(e) If, during the inspection required by paragraph (a) or (b) of this AD, no cracks are found in the handle tube on either side of the reinforcing liner, but cracks are found in the reinforcing liners which are 0.10 inches in length or less, return the handle assembly to service and continue the inspection required by paragraph (a) or (b) of this AD at intervals not to exceed 300 hours time in service from the last inspection.

(f) If, during the inspection required by paragraph (a) or (b) of this AD, cracks are found in the reinforcing liner with any crack exceeding 0.10 inches in length, or any cracks are found in the handle tube on either side of the reinforcing liner, before further flight, either -

(1) Replace the handle and reinforcing liner assembly with a serviceable assembly and continue the inspection required by paragraph (a) or (b) of this AD at intervals not to exceed 1800 hours time in service from the last inspection; or

(2) Perform temporary repairs to the handle and reinforcing liner assembly in accordance with paragraph (i) of this AD and continue the inspections required by paragraph (a) or (b) of this AD at intervals not to exceed 300 hours time in service from the last inspection.

(g) If, during the inspection required by paragraph (c) of this AD, cracks are found in the endfitting running inboard or outboard from the taper pin hole, with the length of each crack 0.30 inches or less, either -

(1) Replace the endfitting with a serviceable part and continue the inspection required by paragraph (c) of this AD at intervals not to exceed 1800 hours time in service from the last inspection; or

(2) The endfitting may remain in service if the cracks are stop-drilled and inspected in accordance with paragraph 2.3.1, "ACCOMPLISHMENT INSTRUCTIONS," of the Service Bulletin, or an FAA-approved equivalent, at intervals not to exceed 300 hours time in service from the last inspection.

(h) If, during the inspection required by paragraph (c) of this AD, cracks are found in the endfitting running outboard or inboard from the taper pin hole, with the length of any crack greater than 0.30 inches, before further flight, either -

(1) Replace the endfitting with a serviceable part and continue the inspection required by paragraph (c) of this AD at intervals not to exceed 1800 hours time in service from the last inspection; or

(2) Perform temporary repairs to the endfitting in accordance with paragraph (i) of this AD and continue the inspections required by paragraph (c) of this AD at intervals not to exceed 300 hours time in service from the last inspection.

(i) If serviceable spares are not available, temporary repairs of inner handles or endfittings may be made in accordance with paragraph 2.1.4., 2.2.3., or 2.3.4., "ACCOMPLISHMENT INSTRUCTIONS," of the Service Bulletin, or an FAA-approved equivalent.

(j) Upon incorporation of British Aerospace Modification PM5703, compliance with this AD is no longer required.

(k) For the purpose of complying with paragraphs (f) and (h) of this AD, the airplane may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the inspection, repair, or replacement can be performed.

(l) If an equivalent means of compliance is used in complying with this AD, that equivalent means must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at FAA Headquarters, Room 916, 800 Independence Avenue, SW., Washington, D.C. 20591.

Amendment 39-4285 became effective January 20, 1982.

This Amendment 39-4824 becomes effective March 19, 1984.

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