AD 67-11-04

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AD Number:
67-11-04
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
LOCKHEED Models 188A and 188C Series Airplanes
Subject:
Fuselage Main Frames Forging
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/09/1967
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Superseded AD: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Superseded By: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: 67-11-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-395

AD NUMBER:   67-11-04

SUBJECT HEADING:   LOCKHEED Models 188A and 188C Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 9, 1967.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-11-04 LOCKHEED: Amdt. 39-383 Part 39 Federal Register April 5, 1967, as Amended by Amdt. 39-395 Part 39 Federal Register April 13, 1967. Applies to Models 188A and 188C Series Airplanes.

Compliance required as indicated.

As a result of cracking of the fuselage main frame forging, P/Ns 801030-3 and -4 and P/Ns 801031-1 and -2, accomplish the following:

(a) For airplanes having fuselage main frame forgings, P/Ns 801030-1, 801030-2, 801030-3, 801030-4, 801031-1, or 801031-2, with 10,000 or more hours' time in service on the effective date of this AD, unless the rework specified in (d) has been performed, perform the inspection specified in (c) within the next 60 hours' time in service after the effective date of this AD unless already accomplished within the previous 940 hours' time in service, and thereafter within 1,000 hours' time in service from the last inspection.

(b) For airplanes having fuselage main frame forgings, P/Ns 801030-1, 801030-2, 801030-3, 801030-4, 801031-1, or 801031-2, with less than 10,000 hours' time in service on the effective date of this AD, unless the rework specified in (d) has been performed, perform the inspection specified in (c) prior to completing 10,060 hours' time in service and thereafter within periods of 1,000 hours' time in service from the last inspection.

(c) Inspect each forging for cracks at the areas above the floor line by the visual procedure in accordance with "2. Accomplishment Instruction," Part I, Paragraph A, Lockheed Service Bulletin 88/SB-644, or later FAA-approved revision, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. If a crack is found, comply with (i).

(d) Rework the intercostals described in Lockheed Drawing 811126 in accordance with Lockheed Wire FS/296808-W (reprinted in Lockheed Service Bulletin 88/SB-644), Lockheed Drawing 841474, or later FAA-approved revision (for forward intercostals attached to the forgings at F.S. 571) and Lockheed Drawing 841475 or later FAA-approved revision (for aft intercostals attached to the forgings at F.S. 695), or in either case by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 2,000 hours' time in service after the effective date of this AD unless already accomplished for those airplanes having fuselage main frame forgings with 10,000 or more hours time in service on that date, or prior to the completion of 12,000 hours' time in service unless already accomplished for airplanes having fuselage main frame forgings with less than 10,000 hours' time in service on that date. Thereafter, inspect in accordance with (c) within periods not to exceed 4,000 hours' time in service from the completion of the rework specified in this paragraph.

(e) For airplanes having fuselage main frame forgings, P/Ns 801030-1, 801030-2, 801030-3, 801030-4, 801031-1, or 801031-2, with 15,000 or more hours' time in service on the effective date of this AD, unless the rework specified in (h) has been performed, perform the inspection specified in (g) within the next 350 hours' time in service after the effective date of this AD unless already accomplished within the previous 650 hours' time in service and thereafter within periods not to exceed 1,000 hours' time in service from the last inspection.

(f) For airplanes having fuselage main frame forgings, P/Ns 801030-1, 801030-2, 801030-3, 801030-4, 801031-1, or 801031-2, with less than 15,000 hours' time in service on the effective date of this AD, unless the rework specified in (h) has been performed, perform the inspection specified in (g) prior to completing 15,350 hours' time in service and thereafter within periods not to exceed 1,000 hours' time in service from the last inspection.

(g) Visually inspect each forging for cracks at the areas below the floor line in accordance with "2. Accomplishment Instructions," Part I, Paragraph B, Lockheed Service Bulletin 88/SB-644, or later FAA-approved revision. If a crack is found, comply with (i).

(h) Rework the floor support structure at the location of the fuselage main frame forgings in accordance with "2. Accomplishment Instructions", Parts III and IV, Lockheed Service Bulletin 88/SB-644, or later FAA-approved revision, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region, within 4,000 hours' time in service after the effective date of this AD unless already accomplished for those airplanes having fuselage main frame forgings with 15,000 or more hours' time in service on that date, or prior to the completion of 19,000 hours' time in service unless already accomplished for those airplanes having fuselage main frame forgings with less than 15,000 hours on that date. Thereafter, inspect in accordance with (g) within periods not to exceed 4,000 hours' time in service from the completion of the rework specified in this paragraph.

(i) If a crack is detected during the inspections conducted in accordance with (c) or (g), repair or replace each forging found cracked before further flight (except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be accomplished) as follows:

(1) Accomplish a "special repair" or a "complete repair" in accordance with a method previously approved by the Chief, Aircraft Engineering Division, FAA Western Region; or

(2) Replace with a new forging of the same part number or with a "new design" forging, P/N 801030-101 (in place of P/N 801030-3), P/N 801030-102 (in place of P/N 801030-4), P/N 801031-101 (in place of P/N 801031-1), P/N 801031-102 (in place of P/N 801031-2), P/N 801030-101 (in place of P/N 801030-1), P/N 801030-102 (in place of P/N 801030-2), in accordance with "2. Accomplishment Instructions", Part V, Lockheed Service Bulletin 88/SB-644, or later FAA-approved revision, or in accordance with an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region.

(i) If a "special repair" is accomplished, visually inspect the repaired area for evidence of crack growth within 60 hours' time in service after the completion of the "special repair" and thereafter at intervals not to exceed 60 hours' time in service from the last inspection. If crack growth is detected during the repetitive inspections conducted under this paragraph, accomplish a "complete repair" of the affected forging or replace the affected forging with a new forging of the same part number or with a "new design" forging before further flight in accordance with paragraph (i). If crack growth is not detected during inspections under this paragraph, accomplish the "complete repair" of the affected forging or replace the affected forging with a new forging of the same part number or with a "new design" forging in accordance with paragraph (i) within 1250 hours' time in service after the completion of a "special repair."

(ii) If a "complete repair" is accomplished, the inspections specified in (c) and (g) and the rework specified in (d) and (h), unless previously accomplished, must be accomplished for that forging at the compliance times indicated in this AD.

(j) If a forging is replaced with a new forging of the same part number, the inspections specified in (c) and (g), and the rework specified in (d) and (h), unless previously accomplished, must be accomplished for that forging at the compliance times indicated in this AD.

(k) If a forging is replaced with a "new design" forging listed in (i) in accordance with "2. Accomplishment Instructions," Part V, Lockheed Service Bulletin 88/SB-644, or later FAA- approved revision, the inspections specified in (c) and (g) may be discontinued for that forging.

(l) For the purpose of complying with this AD, operators who have not kept records of hours' time in service of individual fuselage main frame forgings shall in lieu thereof substitute hours' time in service of the airplane in which the forgings are installed.

(m) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Regional director, 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.

This directive effective April 5, 1967, as amended by Amdt. 39-395, Federal Register April 13, 1967.

Revised May 6, 1967.

Revised June 9, 1967.

FOOTER: