AD 60-01-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 188A | LOCKHEED Models 188A and 188C Aircraft |
| aircraft | Lockheed Martin Corporation | 188C | LOCKHEED Models 188A and 188C Aircraft |
Unsafe Condition
The design of the propeller deicing power transfer relay (Lockheed P/N 613649-1, Leach P/N 9202-4516) allows plastic relay body cold flowing, which prevents terminals from remaining properly tightened over time.
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Required Actions
Deactivate the propeller deicing system by pulling the control circuit breaker at the forward load center and placarding it inoperative. Disconnect 8-gauge power wires from the priority buses, type and stow them. Reapply Icex compound (B.F. Goodrich Adhesive Depressant No. 6) to propeller blade fairing heater boots and spinners every 6 hours of precipitation exposure or 50 hours elapsed time, whichever comes first. To reactive the system, replace the original relay with a new Hartman B124-GL (Lockheed P/N 613422-17) per approved installation.
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Compliance Time
On arrival at the next station with maintenance personnel and at main base
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Affected Aircraft
Lockheed Models 188A and 188C Aircraft, all serial numbers
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Federal Register Abstract
Propeller Deicing
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_60-01-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-01-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Aircraft Subject: Propeller Deicing 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Lockheed Martin Corporation Model: 188A | 188C Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 60-01-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-01-05 SUBJECT HEADING: LOCKHEED Models 188A and 188C Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-01-05 LOCKHEED: Amdt. 74 Part 507 Federal Register January 6, 1960. Applies to all 188A and 188C Aircraft. Compliance required as indicated. Continuing investigation of the propeller deicing power transfer relay has shown the design of the relay is such that properly tightened terminals cannot be assured for a practical interval of time due to cold flowing of plastic relay body. Upon arrival at the next station where maintenance personnel are available, deactivate the propeller deicing system by pulling the control circuit breaker on the main and essential direct current bus at the forward load center. Placard the propeller deicing system inoperative. On arrival at main base disconnect 8-gage power wires from the priority A and B bus to the propeller deicing power relay. Type and stow at priority bus end. With the propeller deicing system deactivated, aircraft may be dispatched into known icing conditions if Icex compound (B. F. Goodrich Company Adhesive Depressant No. 6) is applied to all propeller blade fairing heater boots and spinners under the following conditions: After initial application, Icex compound shall be reapplied after cumulative exposure to not more than six hours precipitation during flight or after 50 hours elapsed time, whichever occurs first. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27, 1959, covers this same subject.) The propeller electrical deicing system may be returned to operative status when the original propeller ice control relay (Lockheed P/N 613649-1, Leach P/N 9202-4516) has been removed and a new relay (Lockheed P/N 613422-17, Hartman B124-GL) has been installed in the circuit and physically located in the main transfer relay box in a manner approved by an authorized representative of the Administrator. When the propeller electrical deicing system has been reactivated in this manner, Icex compound will no longer be required for aircraft dispatching into known icing conditions. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27 covers the deactivation of the original Leach relay and the use of Icex compound. Lockheed 188 Service Bulletin No. 403, effective December 15, 1959, describes a satisfactory and approved means of installing the replacement Hartman relay.) This airworthiness directive sent by telegram to all operators of Lockheed 188A and 188C aircraft on December 8, 1959. FOOTER:
Document Text
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AD Final Rules - DRS_60-01-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 60-01-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Models 188A and 188C Aircraft Subject: Propeller Deicing 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: 60-01-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 60-01-05 SUBJECT HEADING: LOCKHEED Models 188A and 188C Aircraft ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 60-01-05 LOCKHEED: Amdt. 74 Part 507 Federal Register January 6, 1960. Applies to all 188A and 188C Aircraft. Compliance required as indicated. Continuing investigation of the propeller deicing power transfer relay has shown the design of the relay is such that properly tightened terminals cannot be assured for a practical interval of time due to cold flowing of plastic relay body. Upon arrival at the next station where maintenance personnel are available, deactivate the propeller deicing system by pulling the control circuit breaker on the main and essential direct current bus at the forward load center. Placard the propeller deicing system inoperative. On arrival at main base disconnect 8-gage power wires from the priority A and B bus to the propeller deicing power relay. Type and stow at priority bus end. With the propeller deicing system deactivated, aircraft may be dispatched into known icing conditions if Icex compound (B. F. Goodrich Company Adhesive Depressant No. 6) is applied to all propeller blade fairing heater boots and spinners under the following conditions: After initial application, Icex compound shall be reapplied after cumulative exposure to not more than six hours precipitation during flight or after 50 hours elapsed time, whichever occurs first. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27, 1959, covers this same subject.) The propeller electrical deicing system may be returned to operative status when the original propeller ice control relay (Lockheed P/N 613649-1, Leach P/N 9202-4516) has been removed and a new relay (Lockheed P/N 613422-17, Hartman B124-GL) has been installed in the circuit and physically located in the main transfer relay box in a manner approved by an authorized representative of the Administrator. When the propeller electrical deicing system has been reactivated in this manner, Icex compound will no longer be required for aircraft dispatching into known icing conditions. (Lockheed Alert Bulletin No. 403 wired to all operators on November 27 covers the deactivation of the original Leach relay and the use of Icex compound. Lockheed 188 Service Bulletin No. 403, effective December 15, 1959, describes a satisfactory and approved means of installing the replacement Hartman relay.) This airworthiness directive sent by telegram to all operators of Lockheed 188A and 188C aircraft on December 8, 1959. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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