AD 64-14-05
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
Fatigue cracks in the main landing gear actuator support fittings (Lockheed P/N 800618) could jam the main landing gear.
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Required Actions
Inspect the aft end of the main landing gear actuator support fittings for fatigue cracks in accordance with Lockheed 88 Alert Service Bulletin No. 599A, Section 2.A through 2.C or an FAA approved equivalent. Replace cracked fittings before further flight per Section 2.E(1) through 2.E(10) of 88/SB-599A and Section 2 of SB-538 or equivalent. Repair spar cap and plank cracks as per Lockheed Structural Repair Manual or equivalent before further flight, except for ferry flights under CAR 1.76.
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Compliance Time
Within 225 landings or 225 hours' time in service after the effective date (June 26, 1964), depending on whether operators maintain landing records. Inspections must occur at intervals not exceeding 1,000 landings or 1,000 hours' time in service. Adjusted intervals if replacement parts installed.
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Affected Aircraft
Lockheed Models 188A and 188C Series aircraft with Main Landing Gear Actuator Support Fitting P/N 800618 that has accumulated more than 5,000 hours' time in service.
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Federal Register Abstract
Main Landing Gear Support Fitting
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-14-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-14-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Series Aircraft Subject: Main Landing Gear Support Fitting Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/26/1964 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Lockheed Martin Corporation Model: 188A | 188C Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-14-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-14-05 SUBJECT HEADING: LOCKHEED Models 188A and 188C Series Aircraft ACTION: SUMMARY: DATES: Effective June 26, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-14-05 LOCKHEED: Amdt. 738 Part 507 Federal Register May 26, 1964. Applies to All Models 188A and 188C Series Aircraft on Which The Main Landing Gear Actuator Support Fitting, Lockheed P/N 800618, Has Accumulated More Than 5,000 Hours' Time in Service. Compliance required as indicated. To eliminate the possibility of jamming the main landing gear, accomplish the following: (a) For operators maintaining records of landings, within 225 landings after the effective date of this AD unless already accomplished within the last 775 landings, and thereafter at intervals not to exceed 1,000 landings, comply with (c). If a fitting is replaced in accordance with (d), the next inspection in accordance with (c) shall be accomplished within 5,225 landings from that time and at periodic intervals thereafter not to exceed 1,000 landings. Where past records of landings are unavailable, the number of landings prior to the effective date of this AD may be obtained by substituting one landing for each hour of time in service prior to the effective date of this AD. (b) For operators not maintaining records of landings, within 225 hours' time in service after the effective date of this AD, unless already accomplished within the last 775 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service, comply with (c). If a fitting is replaced in accordance with (d), the next inspection in accordance with (c) shall be accomplished within 5,225 hours' time in service from that time and at periodic intervals thereafter not to exceed 1,000 hours' time in service. (c) Inspect the aft end of the main landing gear actuator support fittings for fatigue cracks in accordance with Lockheed 88 Alert Service Bulletin No. 599A, Section 2.A through 2.C or an FAA approved equivalent. (d) Replace cracked actuator support fittings detected during the accomplishment of (c) before further flight in accordance with Section 2.E(1) through 2.E(10) of Lockheed 88 Alert Service Bulletin No. 599A and Section 2 of Lockheed Service Bulletin No. 538 or equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (e) Spar cap cracks and plank cracks detected during compliance with Section 2.E(4) of 88/SB-599A shall be repaired in accordance with the Lockheed Structural Repair Manual or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, 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. (f) The periodic inspections described in (a) and (b) may be discontinued when P/N 800618-3 is replaced by P/N 841275-101 and P/N 800618-4 is replaced by P/N 841275-102. (g) 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 Service Bulletin Nos. 88/SB-599A and 88/SB-538 cover this same subject.) This directive effective June 26, 1964. FOOTER:
Document Text
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AD Final Rules - DRS_64-14-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-14-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Series Aircraft Subject: Main Landing Gear Support Fitting Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/26/1964 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: 64-14-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 64-14-05 SUBJECT HEADING: LOCKHEED Models 188A and 188C Series Aircraft ACTION: SUMMARY: DATES: Effective June 26, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-14-05 LOCKHEED: Amdt. 738 Part 507 Federal Register May 26, 1964. Applies to All Models 188A and 188C Series Aircraft on Which The Main Landing Gear Actuator Support Fitting, Lockheed P/N 800618, Has Accumulated More Than 5,000 Hours' Time in Service. Compliance required as indicated. To eliminate the possibility of jamming the main landing gear, accomplish the following: (a) For operators maintaining records of landings, within 225 landings after the effective date of this AD unless already accomplished within the last 775 landings, and thereafter at intervals not to exceed 1,000 landings, comply with (c). If a fitting is replaced in accordance with (d), the next inspection in accordance with (c) shall be accomplished within 5,225 landings from that time and at periodic intervals thereafter not to exceed 1,000 landings. Where past records of landings are unavailable, the number of landings prior to the effective date of this AD may be obtained by substituting one landing for each hour of time in service prior to the effective date of this AD. (b) For operators not maintaining records of landings, within 225 hours' time in service after the effective date of this AD, unless already accomplished within the last 775 hours' time in service and thereafter at intervals not to exceed 1,000 hours' time in service, comply with (c). If a fitting is replaced in accordance with (d), the next inspection in accordance with (c) shall be accomplished within 5,225 hours' time in service from that time and at periodic intervals thereafter not to exceed 1,000 hours' time in service. (c) Inspect the aft end of the main landing gear actuator support fittings for fatigue cracks in accordance with Lockheed 88 Alert Service Bulletin No. 599A, Section 2.A through 2.C or an FAA approved equivalent. (d) Replace cracked actuator support fittings detected during the accomplishment of (c) before further flight in accordance with Section 2.E(1) through 2.E(10) of Lockheed 88 Alert Service Bulletin No. 599A and Section 2 of Lockheed Service Bulletin No. 538 or equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (e) Spar cap cracks and plank cracks detected during compliance with Section 2.E(4) of 88/SB-599A shall be repaired in accordance with the Lockheed Structural Repair Manual or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, 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. (f) The periodic inspections described in (a) and (b) may be discontinued when P/N 800618-3 is replaced by P/N 841275-101 and P/N 800618-4 is replaced by P/N 841275-102. (g) 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 Service Bulletin Nos. 88/SB-599A and 88/SB-538 cover this same subject.) This directive effective June 26, 1964. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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