AD 60-11-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Model 188 Series Aircraft |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Model 188 Series Aircraft |
Unsafe Condition
Loose attachments and cracked quick engine change upper cowl panel longerons.
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Required Actions
Inspect top cowl panel upper longerons and attachments at rear fittings for cracks or loose attachments every 300 hours' time in service. Replace loose attachments with specified fasteners (e.g., oversize Hi-Lok pins, NAS screws) and repair or replace cracked longerons before next flight. Discontinue inspections after incorporating Lockheed Service Bulletin 88/SB-500.
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Compliance Time
Prior to dispatch from a terminal with inspection facilities unless accomplished within last 300 hours' time in service, and thereafter every 300 hours' time in service.
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Affected Aircraft
Lockheed Model 188A and 188C aircraft, all serial numbers.
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Federal Register Abstract
Cowl Longerons
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_60-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 188 Series Aircraft Subject: Cowl Longerons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 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Lockheed Martin Corporation Model: 188A | 188C Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 60-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-11-03 SUBJECT HEADING: LOCKHEED Model 188 Series Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961. FOOTER:
Document Text
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AD Final Rules - DRS_60-11-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-11-03 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 188 Series Aircraft Subject: Cowl Longerons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 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: 60-11-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-11-03 SUBJECT HEADING: LOCKHEED Model 188 Series Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-11-03 LOCKHEED: Amdt. 159 Part 507 Federal Register May 24, 1960. Applies to All 188 Series Aircraft. Compliance required as indicated. Due to loose attachments and cracked quick engine change upper cowl panel longerons the following inspections are required. Prior to dispatch from a terminal where inspection facilities are available, unless already accomplished within the last 300 hours' time in service, and thereafter at every 300 hours' time in service, inspect the top cowl panel upper longerons and the attachments at the rear fittings for cracks or loose attachments. (a) Replace loose attachments in the longeron fittings. Acceptable replacements are: (1) One-sixty-fourths-inch diameter oversize Hi-Lok (P/N HL 56-6 pin, P/N HL 64-6-5 pin, P/N HL 85-6 collar). (2) Thirteen-sixty-fourths-inch diameter NAS type close tolerance screw, minimum heat treat 160,000 p.s.i. Ream to oversize hole limits of 0.212-0.2192-inch diameter. (3) Seven-thirty-seconds-inch diameter NAS type close tolerance screws; minimum heat treat 160,000 p.s.i.; minimum edge distance, 1 1/2 diameters. Ream to oversize hole limits of 0.2181-0.2192-inch diameter. (4) It is satisfactory to mix Huck bolts and Hi-Lok fasteners, but it is not acceptable to mix NAS type screws with Huck bolts or Hi-Lok fasteners. (b) Cracked longerons must be replaced or an FAA approved repair incorporated before next flight. The preceding inspections may be discontinued after the incorporation of the modifications contained in Lockheed Service Bulletin 88/SB-500. (Lockheed Alert Service Bulletin No. 467 covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 29, 1960. Revised September 29, 1960. Revised May 13, 1961. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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