AD 64-11-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Models 188A and 188C Series Aircraft |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Models 188A and 188C Series Aircraft |
Unsafe Condition
Cracks have been detected in the upper wing planks on both the inboard and outboard sides of the nacelle where the inboard nacelle skate angles attach to the wing planks.
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Required Actions
Within 450 hours' time in service after the effective date, and every 450 hours thereafter, externally inspect the wing planks per Lockheed SB 88/SB-600 or FAA-approved equivalent. Within 900 hours' time in service after the effective date (or within 2,100 hours prior), and every 3,000 hours thereafter, internally inspect the wing planks by X-ray or visual means per the same service bulletin. Repair any cracks before further flight unless ferried under CAR 1.76.
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Compliance Time
Effective June 15, 1964
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Affected Aircraft
Lockheed Models 188A and 188C Series Aircraft
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Federal Register Abstract
Upper Wing Planks
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Series Aircraft Subject: Upper Wing Planks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/15/1964 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Lockheed Martin Corporation Model: 188A | 188C Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-11-03 SUBJECT HEADING: LOCKHEED Models 188A and 188C Series Aircraft ACTION: SUMMARY: DATES: Effective June 15, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-11-03 LOCKHEED: Amdt. 729 Part 507 Federal Register May 15, 1964. Applies to All Models 188A and 188C Series Aircraft. Compliance required as indicated. Cracks have been detected in the upper wing planks on both the inboard and outboard sides of the nacelle where the inboard nacelle skate angles attach to the wing planks. As a result of these cracks, accomplish the following: (a) Within the next 450 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 450 hours' time in service, externally inspect the wing planks in accordance with Section 2.A. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. The external inspections may be discontinued when the internal inspection program prescribed by (b) is initiated. (b) Within the next 900 hours' time in service after the effective date of this AD, unless accomplished within 2,100 hours' time in service prior to the effective date of this AD, and thereafter at intervals not to exceed 3,000 hours' time in service, internally inspect the wing planks by X-ray or visual means in accordance with Section 2.B. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. (c) Any cracks found during the accomplishment of (a) or (b) shall be repaired before further flight (except that the aircraft may be ferried in accordance with the provisions of CAR 1.76 to the base at which the repairs are to be accomplished) in accordance with the Lockheed Electra Structural Repair Manual, Section 57-2-1, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) The repetitive inspections of (b) may be discontinued for those aircraft which exhibit no signs of cracks 6,000 hours' time in service after the initial internal inspection is accomplished. (e) For aircraft on which cracks are detected and repaired in accordance with (c), the repetitive inspections of (b) may be discontinued if no cracks are detected 6,000 hours' time in service after the repair is accomplished. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Alert Bulletin 88/SB-600 dated June 24, 1963, covers this same subject.) This directive effective June 15, 1964. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_64-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Series Aircraft Subject: Upper Wing Planks Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/15/1964 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: 64-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-11-03 SUBJECT HEADING: LOCKHEED Models 188A and 188C Series Aircraft ACTION: SUMMARY: DATES: Effective June 15, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-11-03 LOCKHEED: Amdt. 729 Part 507 Federal Register May 15, 1964. Applies to All Models 188A and 188C Series Aircraft. Compliance required as indicated. Cracks have been detected in the upper wing planks on both the inboard and outboard sides of the nacelle where the inboard nacelle skate angles attach to the wing planks. As a result of these cracks, accomplish the following: (a) Within the next 450 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 450 hours' time in service, externally inspect the wing planks in accordance with Section 2.A. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. The external inspections may be discontinued when the internal inspection program prescribed by (b) is initiated. (b) Within the next 900 hours' time in service after the effective date of this AD, unless accomplished within 2,100 hours' time in service prior to the effective date of this AD, and thereafter at intervals not to exceed 3,000 hours' time in service, internally inspect the wing planks by X-ray or visual means in accordance with Section 2.B. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. (c) Any cracks found during the accomplishment of (a) or (b) shall be repaired before further flight (except that the aircraft may be ferried in accordance with the provisions of CAR 1.76 to the base at which the repairs are to be accomplished) in accordance with the Lockheed Electra Structural Repair Manual, Section 57-2-1, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) The repetitive inspections of (b) may be discontinued for those aircraft which exhibit no signs of cracks 6,000 hours' time in service after the initial internal inspection is accomplished. (e) For aircraft on which cracks are detected and repaired in accordance with (c), the repetitive inspections of (b) may be discontinued if no cracks are detected 6,000 hours' time in service after the repair is accomplished. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Alert Bulletin 88/SB-600 dated June 24, 1963, covers this same subject.) This directive effective June 15, 1964. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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