AD 78-23-13

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AD Number:
78-23-13
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model 744, 745D, and 810 Series Airplanes
Subject:
MLG Shock Absorber Struts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/18/1978
Make:
Vickers-Armstrongs (Aircraft Limited)
Model:
Viscount 744 | Viscount 745D | Viscount 810
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Superseded AD: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Superseded By: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: 78-23-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3350

AD NUMBER:   78-23-13

SUBJECT HEADING:   Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model 744, 745D, and 810 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 18, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-23-13 BRITISH AIRCRAFT CORPORATION: Amendment 39-3350. Applies to Viscount Model 744, 745D, and 810 Series airplanes, certificated in all categories.

Compliance is required as indicated.

The following parts are affected by this AD:

	
700 Series
	800 Series
10" Oleos	14" Oleos	
Gland Nut	70050-317	72450-69	81050-69
Locking Plate		72450-71	81050-71
Locking Screw	70050-259	

To ensure the security of the gland nut and locking plate/locking screw combination and prevent detachment of the gland nut of the main landing gear shock absorber struts, accomplish the following:

(a) Within the next 25 landings after the effective date of this AD and thereafter at intervals not to exceed 25 landings from the last inspection until the inspection required by paragraph (c) of this AD is performed, visually inspect the gland nut and locking plate/locking screw combination as installed for security and satisfactory locking in accordance with paragraph 2.2 of the "Accomplishment Instructions" of British Aircraft Corporation Preliminary Technical Leaflet (PTL) No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA-approved equivalent.

(b) If, during any of the inspections required by paragraph (a) of this AD, the gland nut is found to be loose or not adequately locked, before further flight, remove the gland nut and inspect the thread form in accordance with paragraph (c) of this AD.

(c) Within 500 landings after the effective date of this AD, unless already accomplished within the last 2,500 landings, and thereafter at intervals not to exceed 3,000 landings, remove the gland nut and inspect the condition of the threads in accordance with the criteria established in paragraph 2.2.2 of British Aircraft Corporation PTL No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA- approved equivalent.

(d) If, during any inspection performed in accordance with paragraph (c) of this AD, the thread form of the gland nut is found unacceptable under the criteria referenced in paragraph (c) of this AD, before further flight, replace the gland nut with a serviceable part of the same part number found acceptable under those criteria.

(e) If, during any of the inspections required by this AD, a locking plate is found worn or fractured, before further flight, replace the locking plate with a serviceable part of the same part number. Replacement locking plates may be installed with the shock absorber strut intact by parting the plate as illustrated in Figure 1 of British Aircraft Corporation PTL No. 299 (700 Series) or PTL No. 168 (800 Series), as applicable, both at Revision 3, dated January 12, 1977, or an FAA-approved equivalent.

This amendment becomes effective December 18, 1978.

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