| AD Number | 66-11-02 | Status | Active |
| Effective Date | September 23, 1966 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-213 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Lockheed Martin Corporation |
| Model(s) | 188A 188C |
66-11-02 LOCKHEED: Amdt. 39-213 Part 39 Federal Register March 17, 1966. Applies to Model 188A and 188C Series Airplanes Except Those Modified in Accordance with Lockheed Drawing 841318A (including Notes 10 and 11), Lockheed Drawing 841318B (including Notes 11, 13, and 19), or an Equivalent Approved by the Chief, Aircraft Engineering Division, FAA Western Region.
Compliance required as indicated.
To detect spanwise cracks in the wing lower surface aft of the main gear fulcrum fitting and chordwise cracks in the wing lower surface plank, accomplish the following:
(a) Within the next 700 landings after the effective date of this AD, unless already accomplished within the last 700 landings before the effective date of this AD, and at intervals not to exceed 1,400 landings from the last inspection until repaired or modified in accordance with (b), accomplish the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region:
(1) Inspect for cracks in accordance with (i) or (ii) the wing plank riser radius (Item 7, Lockheed Service Bulletin 88/SB-620D, Figure 3) of riser number 29, plank 5 and riser number 36, plank 6 between Wing Stations 162 and 172 and between Wing Stations 204 and 214, of airplanes not modified in accordance with Lockheed Drawing 841318.
(i) Inspect externally, by the ultrasonic technique described in Lockheed Service Bulletin 88/SB-620D, Section 2.B.(5)(c), pages 25 through 31, or later FAA- approved revision. Test block design must be in accordance with Lockheed Service Bulletin 88/SB- 625B, Figure 2, or later FAA-approved revision. If indication of a crack is found, inspect before further flight in accordance with (ii).
(ii) Inspect internally, by dye penetrant method, as described in Lockheed Service Bulletin 88/SB-625B, Sections 2(A) through 2(F), or later FAA-approved revision.
(2) Inspect for cracks the internal plank area surrounding the bulkhead angle (P/N810970) at the Wing Station 211 attachment hole or holes, as applicable, located between the lower number 6 plank risers 37 and 38, by dye penetrant method, in accordance with Lockheed Service Bulletin 88 SB-625C, Section 2G, or later FAA-approved revision.
(b) Repair cracks found during the inspections required by this AD before further flight in accordance with Lockheed Drawing 841318A (including Notes 10 and 11) or Lockheed Drawing 841318B (including Notes 11, 13, and 19), as applicable, and the accomplishment instructions of Lockheed Service Bulletin 88/SB-625C or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. The airplane may be flown in accordance with FAR 21.197 to a base where the repair is to be performed. Seal all splice areas to be covered with repairs in accordance with Lockheed Service Bulletin 88/SB-620D or later FAA-approved revision.
NOTE: Regional approval required by (b) may be facilitated by obtaining prior approval of a Structural DER.
(c) The repetitive inspections required by (a)(2) may be discontinued if, during the inspections required by (a), no cracks are found, and before further flight the airplane is modified in accordance with Note 10 of Lockheed Drawing No. 841318A or Notes 13 and 19 of Lockheed Drawing No. 841318B, as applicable.
(d) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type.
(e) 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 that operator.
This directive effective April 16, 1966.
Revised April 15, 1966.
Revised September 23, 1966.