AD 78-12-03

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AD Number:
78-12-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model BAC 1-11 400 Series Airplanes
Subject:
Nose Landing Gear
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/10/1978
Make:
Airbus SAS
Model:
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Superseded AD: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Superseded By: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: 78-12-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3231

AD NUMBER:   78-12-03

SUBJECT HEADING:   Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model BAC 1-11 400 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 10, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-12-03 BRITISH AIRCRAFT CORPORATION: Amendment 39-3231. Applies to Model BAC 1-11 400 Series Airplanes, certificated in all categories.

Compliance required as indicated.

To detect cracks in the nose landing gear sustaining ram P/N AK44 A103 or P/N AK 44 A853, as applicable, accomplish the following:

(a) For airplanes on which nose landing gear sustaining ram P/N AK 44 A103 is installed, prior to accumlating 4500 landings on the ram or within 500 landings after the effective date of this AD, whichever occurs later, unless accomplished within the last 500 landings, and thereafter at intervals not to exceed 1000 landings from the last inspection, inspect in accordance with paragraph (c) of this AD.

(b) For airplanes on which nose landing gear sustaining ram P/N AK44 A853 is installed, prior to accumulating 4500 landings or within 500 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1000 landings from the last inspection, inspect in accordance with paragraph (c) of this AD.

(c) Inspect nose landing gear sustaining ram, P/N AK44 A103 or AK44 A853, as applicable, for cracks using a permanent magnet and detection ink in accordance with the procedure outlined in sections 2.1.1 and 4.1 of British Aircraft Corporation Alert Service Bulletin No. 32-A-PM3509, issue 5, dated March 23, 1977, (service bulletin) or an FAA-approved equivalent.

(d) If during the inspection required by paragraph (c) of this AD, cracks are found which exceed 2-1/2 inches in length around the circumference of the ram, before further flight, replace the ram P/N AK44 A103 or AK44 A853 with a serviceable part of the same part number, or with P/N AK44 A987 in accordance with Modification PM5227 referred to in the service bulletin. If P/N AK44 A103 or AK44 A853 rams are used as replacements, inspect the replacement rams in accordance with paragraph (c) prior to accumulating 4500 landings on the part and thereafter at intervals not to exceed 1000 landings from the last inspection.

(e) If, during the inspection required by paragraph (c) of this AD, cracks are found which do not exceed 2-1/2 inches in length around the circumference of the ram, such cracks may be blended out in accordance with and within the limitations of section 2.1.4 of the service bulletin or an FAA-approved equivalent. Sustaining rams reworked in this manner must be shot peened and reprotected in accordance with section 2.1.5 of the service bulletin or an FAA-approved equivalent, and the ram must continue to be inspected in accordance with paragraph (c) of this AD at intervals not to exceed 1000 landings. If the cracks cannot be blended out within the specified material limitations, the ram must be replaced before further flight in accordance with paragraph (d) of this AD.

(f) The repetitive inspections of the nose landing gear sustaining ram as specified in this AD may be terminated upon embodiment of BAC Modification PM5227 which introduces ram P/N AK44 A987 or an FAA-approved equivalent.

(g) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, where the number of landings has not been recorded for the parts affected by this AD, the number of landings may be determined by dividing the number of flight hours time in service since installation of the part by the operator's fleet average time from takeoff to landing for the airplane type.

This supersedes Amendment 39-697 (33 FR 18695), AD-68-26-04.

This amendment becomes effective July 10, 1978.

FOOTER: