AD 80-10-05

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AD Number:
80-10-05
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED-CALIFORNIA COMPANY Model 188A and 188C Series Airplanes
Subject:
Wing Front Spar Caps
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/23/1980
Make:
Lockheed Martin Corporation
Model:
188A | 188C
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Superseded AD: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Superseded By: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: 80-10-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3771

AD NUMBER:   80-10-05

SUBJECT HEADING:   LOCKHEED-CALIFORNIA COMPANY Model 188A and 188C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 23, 1980.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
80-10-05 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3771. Applies to all Model 188A and 188C series airplanes certificated in all categories.

To prevent loss of strength capability of the wing due to fatigue cracking accomplish the following; unless previously accomplished:

(a) Before accumulating 30,000 hours' time in service or within the next 100 hours' time in service on those airplanes with 30,000 or more hours' time in service, unless accomplished within last 400 hours:

(1) Inspect the wing front spar lower cap per paragraph (d) of this AD; and

(2) Reinspect per paragraph (d) prior to accumulating 500 hours' time in service since the last inspection required by paragraph (a)(1).

(b) Within 400 hours' time in service since inspection required in (a)(2) and thereafter at intervals not to exceed 2,000 hours' time in service, inspect per paragraph (e) of this AD.

(c) Inspections per paragraph (e) of this AD (including the 2,000 hour repetitive inspection) may be substituted for the inspections required by paragraph (a)(1) and (a)(2) of this AD.

(d) Inspect wing front spar lower cap per paragraph 1.D.(1) of Lockheed Alert Service Bulletin 88/SB-699B dated July 13, 1979, hereinafter referred to as Lockheed ASB 88/SB- 699B.

(e) Inspect spar cap adjacent structure per paragraph 1.D.(2), 1.D.(3), 1.D.(4), 1.D.(5), 1.D.(6), 1.D.(7), and 1.D.(8) of Lockheed ASB 88/SB-699B.

(f) Repair any detected cracks prior to further flight per Lockheed ASB 88/SB-699B.

(g) Incorporation of the modifications/repairs defined by the drawings listed below terminates the inspection requirements of this AD for the listed paragraphs in ASB 88/SB-699B.

(1) Drawing Numbers 842174 and 842181 for paragraphs 1.D.1, 1.D.3, 1.D.4 (spar cap only), 1.D.5 (spar cap at Station 203), 1.D.7 (spar cap at Stations 159 and 167).

(2) Drawing Numbers 842185 and 842186 for paragraphs 1.D.2 and 1.D.6.

(3) Drawing Number 842222 for paragraph 1.D.4 (spar web and cap at Station 203 only).

(4) Drawing Number 842217 for paragraph 1.D.4 (spar web at Station 216).

(5) Drawing Number 841738 (spar web at Station 160).

(h) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.

This amendment supersedes Amendment 39-3204 (43 FR 19210) AD 78-09-06.

This amendment becomes effective June 23, 1980.

FOOTER: