AD 64-08-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Aeronautics Company | 1649A-98 | LOCKHEED Model 1649A Series Aircraft |
Unsafe Condition
Cracks in the wing upper milled skin panel (second plank aft of the front spar) aft of Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to skin lap joints.
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Required Actions
Inspect for cracks using ultrasonic shear wave inspection technique (within 350 hours' time in service after effective date, then every 5,500 hours). Visually inspect for cracks (within 1,400 hours' time in service after effective date, then every 1,050 hours). Repair cracks per Lockheed Report 11885 or FAA-approved equivalent before further flight. Ferrying allowed under Section 1.76 of CAR Part 1 pending repair.
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Compliance Time
Within 350 hours' time in service after May 11, 1964, and within each 5,500 hours' time in service thereafter for ultrasonic inspections; within 1,400 hours' time in service after May 11, 1964, and thereafter at intervals not exceeding 1,050 hours' time in service for visual inspections.
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Affected Aircraft
Lockheed Model 1649A Series Aircraft (all serial numbers)
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Federal Register Abstract
Wing Upper Milled Skin Panel
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_64-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-08-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 1649A Series Aircraft Subject: Wing Upper Milled Skin Panel Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/11/1964 Make: Lockheed Martin Aeronautics Company Model: 1649A-98 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 64-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-711 AD NUMBER: 64-08-02 SUBJECT HEADING: LOCKHEED Model 1649A Series Aircraft ACTION: SUMMARY: DATES: Effective May 11, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-08-02 LOCKHEED: Amdt. 711 Part 507 Federal Register April 8, 1964. Applies to All Model 1649A Series Aircraft. Compliance required as indicated. (a) Within 350 hours' time in service after the effective date of this AD, unless already accomplished, and within each 5,500 hours' time in service thereafter following the initial inspection, inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to the skin lap joints using the ultrasonic shear wave inspection technique described in Lockheed Letter FS/267105-L or an FAA approved equivalent. (b) Within 1,400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,050 hours' time in service, visually inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aft-most risers adjacent to skin lap joints. (c) Any cracks found during the inspections specified in (a) and (b) shall be repaired in accordance with Lockheed Report 11885 (Structural Repair Manual), Figure 2-10 or an FAA approved equivalent before further flight, except that the aircraft may be ferried in accordance with the provisions of Section 1.76 of CAR Part 1 to a base where the repairs are to be accomplished. (d) 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 Letter FS/267105-L dated August 30, 1963, covers this same subject.) This directive effective May 11, 1964. FOOTER:
Document Text
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AD Final Rules - DRS_64-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 64-08-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 1649A Series Aircraft Subject: Wing Upper Milled Skin Panel Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/11/1964 Make: Lockheed Martin Aeronautics Company Model: 1649A-98 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: 64-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-711 AD NUMBER: 64-08-02 SUBJECT HEADING: LOCKHEED Model 1649A Series Aircraft ACTION: SUMMARY: DATES: Effective May 11, 1964. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 64-08-02 LOCKHEED: Amdt. 711 Part 507 Federal Register April 8, 1964. Applies to All Model 1649A Series Aircraft. Compliance required as indicated. (a) Within 350 hours' time in service after the effective date of this AD, unless already accomplished, and within each 5,500 hours' time in service thereafter following the initial inspection, inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aftmost risers adjacent to the skin lap joints using the ultrasonic shear wave inspection technique described in Lockheed Letter FS/267105-L or an FAA approved equivalent. (b) Within 1,400 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 1,050 hours' time in service, visually inspect for cracks in the right and left hand wing upper milled skin panel (second plank aft of the front spar) in the area aft of the Nos. 2 and 3 nacelles between W.S. 175 and W.S. 283.5 at the forward and aft-most risers adjacent to skin lap joints. (c) Any cracks found during the inspections specified in (a) and (b) shall be repaired in accordance with Lockheed Report 11885 (Structural Repair Manual), Figure 2-10 or an FAA approved equivalent before further flight, except that the aircraft may be ferried in accordance with the provisions of Section 1.76 of CAR Part 1 to a base where the repairs are to be accomplished. (d) 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 Letter FS/267105-L dated August 30, 1963, covers this same subject.) This directive effective May 11, 1964. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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