AD 61-22-06
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Air Trading Corporation | Lockheed Aircraft Corporation | Army B-34 | LOCKHEED Model PV-1, B-34, and 18 Series Aircraft |
| aircraft | Air Trading Corporation | Lockheed Aircraft Corporation | Navy PV-1 | LOCKHEED Model PV-1, B-34, and 18 Series Aircraft |
| aircraft | Air Trading Corporation | Lockheed Aircraft Corporation | 18 | LOCKHEED Model PV-1, B-34, and 18 Series Aircraft |
Unsafe Condition
Cracks in the elevator control mast assembly castings P/N 11467 or 56045 in the attach bolt lugs, which could lead to failure of the elevator control system.
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Required Actions
Inspect elevator control mast assembly castings for cracks using dye penetrant methods; replace cracked castings. Install AN 5-16A bolts with lockplate, torque bolts to specified ranges, and install shim with specific dimensions between castings.
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Compliance Time
within the next 100 hours' time in service after effective date
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Affected Aircraft
Lockheed Model PV-1, B-34, and 18 Series Aircraft with elevator control mast assembly castings P/N 11467 or 56045
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Federal Register Abstract
Elevator Control Mast Castings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_61-22-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-22-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model PV-1, B-34, and 18 Series Aircraft Subject: Elevator Control Mast Castings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/21/1961 Make: Air Trading Corporation | Lockheed Aircraft Corporation Model: Army B-34 | Navy PV-1 | 18 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 61-22-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-22-06 SUBJECT HEADING: LOCKHEED Model PV-1, B-34, and 18 Series Aircraft ACTION: SUMMARY: DATES: Effective November 21, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-22-06 LOCKHEED: Amdt. 351 Part 507 Federal Register October 21, 1961. Applies to All PV-1, B-34, and 18 Series Aircraft Having Elevator Control Mast Assembly Castings P/N 11467 or 56045. Compliance required within the next 100 hours' time in service after effective date. As a result of reported cracks in the elevator control mast assembly castings, the following inspections and installation procedures are required unless already accomplished: (a) Inspect the elevator control mast assembly casting prior to removal, for mating marks to insure correct assembly. If none exist, determine the proper position of the cap on the mast and mark the assembly with a paint stripe or equivalent to insure future correct assembly of parts. (b) Remove the elevator control mast assembly casting and inspect both the control mast and the cap castings for cracks in the attach bolt lugs using dye penetrant methods or equivalent. If any cracks are found, the casting must be replaced prior to further flight. (c) Install the four AN 5-16A bolts in the casting in place on the aircraft, with the lockplate between the cast cap and the casting on the aft side, and with the mating marks matched. Torque the two bolts which go through the lockplate to 50-70 inch-pounds, then the other two bolts to the same range of torque values. Measure the gap between the forward side of the castings. Fabricate an aluminum alloy shim, +0.002 to +0.005-inch greater than the measured gap. Remove the forward bolts, install the shim, replace the bolts, and torque all bolts to 100-140 inch-pounds. Ensure that the shim does not contact the surrounding structure. This directive effective November 21, 1961. FOOTER:
Document Text
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AD Final Rules - DRS_61-22-06.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 61-22-06 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model PV-1, B-34, and 18 Series Aircraft Subject: Elevator Control Mast Castings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 11/21/1961 Make: Air Trading Corporation | Lockheed Aircraft Corporation Model: Army B-34 | Navy PV-1 | 18 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: 61-22-06 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 61-22-06 SUBJECT HEADING: LOCKHEED Model PV-1, B-34, and 18 Series Aircraft ACTION: SUMMARY: DATES: Effective November 21, 1961. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 61-22-06 LOCKHEED: Amdt. 351 Part 507 Federal Register October 21, 1961. Applies to All PV-1, B-34, and 18 Series Aircraft Having Elevator Control Mast Assembly Castings P/N 11467 or 56045. Compliance required within the next 100 hours' time in service after effective date. As a result of reported cracks in the elevator control mast assembly castings, the following inspections and installation procedures are required unless already accomplished: (a) Inspect the elevator control mast assembly casting prior to removal, for mating marks to insure correct assembly. If none exist, determine the proper position of the cap on the mast and mark the assembly with a paint stripe or equivalent to insure future correct assembly of parts. (b) Remove the elevator control mast assembly casting and inspect both the control mast and the cap castings for cracks in the attach bolt lugs using dye penetrant methods or equivalent. If any cracks are found, the casting must be replaced prior to further flight. (c) Install the four AN 5-16A bolts in the casting in place on the aircraft, with the lockplate between the cast cap and the casting on the aft side, and with the mating marks matched. Torque the two bolts which go through the lockplate to 50-70 inch-pounds, then the other two bolts to the same range of torque values. Measure the gap between the forward side of the castings. Fabricate an aluminum alloy shim, +0.002 to +0.005-inch greater than the measured gap. Remove the forward bolts, install the shim, replace the bolts, and torque all bolts to 100-140 inch-pounds. Ensure that the shim does not contact the surrounding structure. This directive effective November 21, 1961. FOOTER:
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Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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