AD 73-07-01

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AD Number:
73-07-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; GENERAL DYNAMICS Model 340, 440 and C-131E Airplanes
Subject:
Wing Front Spar Lower Cap Cracks
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/26/1973
Make:
Kelowna Flightcraft R & D Ltd.
Model:
340 | 440 | Military C-131E
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 73-07-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1608

AD NUMBER:   73-07-01

SUBJECT HEADING:   Airworthiness Directives; GENERAL DYNAMICS Model 340, 440 and C-131E Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 26, 1973.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   73-07-01 GENERAL DYNAMICS: Amdt. 39-1608. Applies to Model 340, 440 and C- 131E and all such model airplanes converted to turbopropeller power in accordance with STC SA1096WE and SA4-1100 known as Model 640 and Model 580, respectively, certificated in all categories.

Compliance as indicated required on all airplanes with 30,000 hours or more total time in service unless already accomplished.

To detect cracks in the wing front spar lower caps, accomplish the following:

(1) As soon as practicable, but not to exceed 10 hours' time in service following the effective date of this AD, if the airplane is to be flown, visually inspect, on a daily basis, from the exterior of the wing, both left and right wing front spar lower caps in areas adjacent to each side of main landing gear drag strut attachment fittings for cracks until inspection in (2) below is accomplished.

(2) Within the next 100 hours' time in service after the effective date of this A.D., unless already accomplished within the last 500 hours' time in service, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, accomplish the following:

(a) Gain access to the wing interior in the area described in (1) above by removal of lower wing skin access cover.

(b) Perform inspection described in (1) above from the interior of the wing.

(3) If cracks are found as the result of the inspections described in (1) or (2) above, repair before further flight in a manner approved by the Chief, Aircraft Engineering Division FAA Western Region.

This amendment becomes effective March 26, 1973.

FOOTER: