AD 62-19-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Aircraft Corporation | 149-46 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
| aircraft | Lockheed Aircraft Corporation | 49-46 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
| aircraft | Lockheed Aircraft Corporation | 649-79 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
| aircraft | Lockheed Aircraft Corporation | 649A-79 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
| aircraft | Lockheed Aircraft Corporation | 749-79 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
| aircraft | Lockheed Aircraft Corporation | 749A-79 | LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft |
Unsafe Condition
Cracks in the main landing gear pistons in the area immediately above the weld retaining the metering pin bulkhead, with some cases of complete fatigue failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect main landing gear pistons (Cleveland Pneumatic Tool Co., P/N 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D-4, 8298F-4) for cracks above the weld using dye penetrant, magnetic particle, or ultrasonic methods. Modify or repair cracked pistons exceeding 0.050 inch depth per Lockheed FS/256603L or FAA-approved equivalent. Repaired/modified pistons must be re-designated or marked with 'R'. Discontinue inspections if modified pistons are installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 800 hours' time in service after the effective date (September 24, 1962), and thereafter every 2,000 hours' time in service. Initial inspections within 1,200 hours prior to effective date may be used, with subsequent intervals starting within 2,000 hours from that date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Lockheed Aircraft Corporation models 149-46, 49-46, 649-79, 649A-79, 749-79, 749A-79 with Cleveland Pneumatic Tool Company main landing gear pistons P/N 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D-4, or 8298F-4.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Main Landing Gear Pistons
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_62-19-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-19-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft Subject: Main Landing Gear Pistons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/24/1962 Make: Lockheed Aircraft Corporation Model: 149-46 | 49-46 | 649-79 | 649A-79 | 749-79 | 749A-79 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: 62-19-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-19-02 SUBJECT HEADING: LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft ACTION: SUMMARY: DATES: Effective September 24, 1962. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-19-02 LOCKHEED: Amdt. 477 Part 507 Federal Register August 23, 1962. Applies to All Models 49, 149, 649, 749, and 749A Series Aircraft Incorporating Cleveland Pneumatic Tool Company Main Landing Gear Pistons, P/N's 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D- 4 or 8298F-4. Compliance required as indicated. As a result of one complete fatigue failure and subsequent cases of cracks in numerous pistons in the area immediately above the weld that retains the metering pin bulkhead, accomplish the following: (a) Within the next 800 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 2,000 hours' time in service, inspect the main landing gear pistons, Cleveland Pneumatic Tool Company, P/N's 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D-4, and 8298F-4, for cracks in the area immediately above the weld that retains the metering pin bulkhead. In those cases where an inspection in accordance with the procedures described in this AD has been accomplished within the last 1,200 hours' time in service as of the effective date of this AD, that inspection may be considered as the initial inspection, and the repetitive reinspection intervals shall then start no later than 2,000 hours' time in service from that date. This inspection may be made by dye penetrant, magnetic particle or ultrasonic methods. (1) Pistons with cracks which exceed a depth of 0.050 inch as measured from the piston inner wall surface shall be modified in accordance with paragraph 4(b) of Lockheed Field Service Letter No. FS/256603L, dated January 24, 1962, or an FAA approved equivalent in order to be eligible for further use. Pistons with this modification are redesignated Cleveland Pneumatic Tool Company P/N's 8298C-4B, 8298C-4C, 8298D-4A, 8298F-4A. (2) Pistons with cracks which do not exceed a depth of 0.050 inch as measured from the piston inner wall surface shall be repaired in accordance with paragraph 4(a) of Lockheed Field Service Letter No. FS/256603L, dated January 24, 1962, or an FAA approved equivalent in order to be eligible for further use. Repaired pistons shall be identified by stamping a letter "R" in front of the part number. (3) Pistons showing no evidence of cracks and pistons repaired in accordance with (a)(2) may be returned to service subject to the 2,000 hours' repetitive reinspection intervals. (b) When modified pistons, P/N's 8298C-4B, 8298C-4C, 8298D-4A, or 8298F-4A, or FAA approved equivalent are installed, the periodic reinspections of (a) may be discontinued. (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, 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 Field Service Letter No. FS/256603L dated January 24, 1962, covers this same subject.) This directive effective September 24, 1962. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_62-19-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 62-19-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft Subject: Main Landing Gear Pistons Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/24/1962 Make: Lockheed Aircraft Corporation Model: 149-46 | 49-46 | 649-79 | 649A-79 | 749-79 | 749A-79 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: 62-19-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 62-19-02 SUBJECT HEADING: LOCKHEED All Models 49, 149, 649, 749, and 749A Series Aircraft ACTION: SUMMARY: DATES: Effective September 24, 1962. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 62-19-02 LOCKHEED: Amdt. 477 Part 507 Federal Register August 23, 1962. Applies to All Models 49, 149, 649, 749, and 749A Series Aircraft Incorporating Cleveland Pneumatic Tool Company Main Landing Gear Pistons, P/N's 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D- 4 or 8298F-4. Compliance required as indicated. As a result of one complete fatigue failure and subsequent cases of cracks in numerous pistons in the area immediately above the weld that retains the metering pin bulkhead, accomplish the following: (a) Within the next 800 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 2,000 hours' time in service, inspect the main landing gear pistons, Cleveland Pneumatic Tool Company, P/N's 8298-4, 8298B-4, 8298C-4, 8298C-4A, 8298D-4, and 8298F-4, for cracks in the area immediately above the weld that retains the metering pin bulkhead. In those cases where an inspection in accordance with the procedures described in this AD has been accomplished within the last 1,200 hours' time in service as of the effective date of this AD, that inspection may be considered as the initial inspection, and the repetitive reinspection intervals shall then start no later than 2,000 hours' time in service from that date. This inspection may be made by dye penetrant, magnetic particle or ultrasonic methods. (1) Pistons with cracks which exceed a depth of 0.050 inch as measured from the piston inner wall surface shall be modified in accordance with paragraph 4(b) of Lockheed Field Service Letter No. FS/256603L, dated January 24, 1962, or an FAA approved equivalent in order to be eligible for further use. Pistons with this modification are redesignated Cleveland Pneumatic Tool Company P/N's 8298C-4B, 8298C-4C, 8298D-4A, 8298F-4A. (2) Pistons with cracks which do not exceed a depth of 0.050 inch as measured from the piston inner wall surface shall be repaired in accordance with paragraph 4(a) of Lockheed Field Service Letter No. FS/256603L, dated January 24, 1962, or an FAA approved equivalent in order to be eligible for further use. Repaired pistons shall be identified by stamping a letter "R" in front of the part number. (3) Pistons showing no evidence of cracks and pistons repaired in accordance with (a)(2) may be returned to service subject to the 2,000 hours' repetitive reinspection intervals. (b) When modified pistons, P/N's 8298C-4B, 8298C-4C, 8298D-4A, or 8298F-4A, or FAA approved equivalent are installed, the periodic reinspections of (a) may be discontinued. (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, 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 Field Service Letter No. FS/256603L dated January 24, 1962, covers this same subject.) This directive effective September 24, 1962. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
93-14-12
final ruleAirworthiness Directives; ESSEX PB&R CORPORATION (formerly E.I. DuPont de Nemours and Company \\nIncorporated) PELS Model 4566M37B Crewmember Protective Breathing Equipment (PBE) Units
Unsafe Condition: Leakage of the PBE neck seal could compromise the crew's ability to combat an aircraft fire.
71-07-02
final ruleLOCKHEED Models 49, 149, 649, 749, 1049, and 1649 Series Airplanes
Unsafe Condition: Failure to provide an acceptable obstacle clearance profile when computing the takeoff flight path.
64-13-03
final ruleLOCKHEED Models 49, 149, 649, 649A, 749, 749A, 1049-54, 1049C, 1049D, 1049E, 1049G, and 1049H Series Aircraft
Unsafe Condition: Cracks and failure in the nose landing gear retract cylinder rod terminal ends (P/N 404052 or 1005032) due to fatigue.
64-07-04
final ruleLOCKHEED Models 49, 149, 649, 649A, 749, 749A, 1049-54, 1049C, 1049D, 1049E, 1049G and 1049H Series Aircraft
Unsafe Condition: Loose or unsafetied bolts in the parallelogram linkages of the primary flight control boost systems could result in loss of flight control system integrity.
