AD 68-15-03

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AD Number:
68-15-03
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Models 744 and 745D Airplanes
Subject:
Horizontal Stabilizer Top Fitting
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/15/1968
Make:
Vickers-Armstrongs (Aircraft Limited)
Model:
Viscount 744 | Viscount 745D
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Superseded AD: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Superseded By: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: 68-15-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-621

AD NUMBER:   68-15-03

SUBJECT HEADING:   Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Models 744 and 745D Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 15, 1968.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
68-15-03 BRITISH AIRCRAFT CORPORATION: Amendment 39-621. Applies to Viscount 744 and 745D airplanes.

Compliance required as indicated, unless already accomplished.

To prevent fatigue damage to the horizontal stabilizer top spar root joint fittings, P/N 70118-231/232 (Pre Mod. D. 3190) and P/N 70118-671/672 (Post Mod. D. 3190), accomplish the following:

(a) Inspect the horizontal stabilizer top spar root joint fittings for cracks in accordance with British Aircraft Corporation PTL No. 264, Issue 2, dated February 12, 1968 (700 Series) or later ARB-approved issue, or an FAA-approved equivalent, as follows:

(1) For fittings which have been involved in 11,500 or more landings on the effective date of this AD, within the next 500 landings, unless already accomplished within the last 2,500 landings, and thereafter at intervals not to exceed 3,000 landings for the last inspection.

(2) For fittings which have been involved in less than 11,500 landings on the effective date of this AD, prior to the accumulation of 12,000 landings and thereafter at intervals not to exceed 3,000 landings from the last inspection.

(b) After each inspection under paragraph (a), replace all cracked fittings with new fittings of the same part number before further flight.

(c) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type.

This superseded Amendment 39-371 (32 F.R. 4306), AD 67-9-5.

This amendment becomes effective August 15, 1968.

FOOTER: