TextPartly OCR
Some pages are OCR from a scan. OCR can misread letters and numbers.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'ef5cc414ef43bca88517a20aaece19341b4584568c5e3177230d3090f7508e81' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = 'ef5cc414ef43bca88517a20aaece19341b4584568c5e3177230d3090f7508e81' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
Page 1 of 19 A382J-53-004 THIS DOCUMENT CONTAINS COMMERCIAL PROPRIETARY TECHNICAL DATA OF LOCKHEED MARTIN CORPORATION AND OTHERS. USE, COPYING AND/OR DISCLOSURE OF THE TECHNICAL DATA CONTAINED HEREIN IS GOVERNED BY THE TERMS OF LOCKHEED MARTIN CORPORATION'S LM-100J SALES CONTRACT WITH THE CUSTOMER.
© 2023 LOCKHEED MARTIN CORPORATION.
EXPORT CONTROLLED INFORMATION WARNING - This document contains data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et seq.) as amended, or the Export Administration Act (Title 50, U.S.C., App 2401 et seq.) as amended. Violations of these export laws are subject to severe criminal and civil penalties.
March 27, 2023 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN FUSELAGE - INSPECTION OF 342986-13/-14/-19/-20 LONGERON FOR POTENTIAL OVERHEATING
1. PLANNING INFORMATION A. EFFECTIVITY
(1) This Service Bulletin is applicable to model 382J FAA Certificated Hercules aircraft. For this aircraft model, aircraft within the following serial range are affected: Lockheed Martin serial numbers 5854, 5889, 5894, and 5956.
(2) Spares - This Service Bulletin is applicable to all spare 342986-13/-14/-19/-20 Longerons held in stock.
B. REASON
(1) The 342986-13/-14/-19/-20 Longerons may have been exposed to excessive hot forming temperatures during manufacturing. Exposure to the higher temperatures will reduce the material strength properties of the longerons.
(2) Lockheed Martin Aeronautics Company recommends that this inspection be accomplished on each affected aircraft within 35 days after receipt of this Service Bulletin, and on any affected spare prior to installation on the aircraft.
C. DESCRIPTION This Service Bulletin provides instructions for a conductivity test and follow-on hardness test, if required, for 342986-13/-14/-19/-20 Longerons. Depending on aircraft serial number, 342986-13/-14 longerons fabricated from 7075 extrusion or 342986-19/-20 longerons fabricated from 7055 extrusion may be installed.
D. APPROVAL
(1) The aircraft owner/operator will make an appropriate entry in the aircraft log records upon completion of this Service Bulletin.
(2) When the work has been completed on each affected aircraft, please complete the attached Figure 4 and Figure 5 tables along with a Notice of Service Bulletin Compliance and e-mail to hercules.support@lmco.com.
E. MANPOWER The manpower estimates provided have not been validated and are estimates only. These estimates are provided only as a convenience for aircraft owner/operator planning purposes. The estimated man-hours listed include the following procedures: equipment preparation, gaining access to work location, inspection, closing work location, and updating aircraft log records, as applicable. It is estimated that approximately 20 man-hours (a crew of 2 qualified technicians) will be required to accomplish the work described herein on each affected aircraft. This will take approximately 10 hours elapsed time while the aircraft is out of service.
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN NOTE: This Service Bulletin is based upon the configuration of the aircraft as it was delivered from Lockheed Martin Aeronautics Company. Previous service bulletins issued by Lockheed Martin Aeronautics Company have been considered in the preparation of this Service Bulletin, but no consideration has been given to peculiar changes made to the aircraft by the owner/operator since its delivery.
F. MATERIAL - COST AND AVAILABILITY Refer to Paragraph 3 for a complete list of materials to inspect each aircraft.
Requirements for the materials are based upon inspection findings. Materials required to accomplish this Service Bulletin for each aircraft and affected spare will be provided by the aircraft owner/operator.
G. TOOLING - PRICE AND AVAILABILITY This test equipment will be furnished by the aircraft owner/operator.
H. WEIGHT AND BALANCE None.
I. REFERENCES J. OTHER PUBLICATIONS AFFECTED None.
Stock Number Part Number Nomenclature 6635-00-803-7596 6635-00-996-1417 Magnatest FM-110 or Magnatest ED-500 unit (or similar meeting ASTM E1004) Electrical Conductivity Meter 5305-01-053-6482 Wilson M-51 (or similar meeting ASTM E110) Portable Rockwell Hardness Tester Corrosion Prevention and Control Manual Data Module Control Number DMC-L382-A-20-10-04-00A-353A-A DMC-L382-A-52-00-03-00A-913A-A Job Guide
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
A382J-53-004March 27, 2023 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN
2. ACCOMPLISHMENT INSTRUCTIONS WARNING: ENSURE THAT ALL APPLICABLE SAFETY PRECAUTIONS ARE OBSERVED WHILE ACCOMPLISHING THE WORK PRESCRIBED IN THIS PUBLICATION.
CAUTION: FAILURE TO PERFORM TESTING BETWEEN TEMPERATURE RANGES OF 50 TO 95 °F WILL RESULT IN INCORRECT RESULTS.
NOTE: Some steps in the Accomplishment Instructions have been identified as Required for Compliance (RC).
If this Alert Service Bulletin is mandated by an Airworthiness Directive (AD) by the Federal Aviation Administration (FAA), the steps identified as RC must be done to comply with the AD. Steps not identified with RC are recommended and may be deviated from; done as a part of other actions; or done with accepted methods different from those given in the Service Bulletin if the steps can be done and the airplane returned to a serviceable condition.
These work instructions refer to methods, techniques, and practices described in other referenced documents. When the words "refer to" are used and there are other acceptable methods, techniques, and practices (including tools, equipment, and test equipment) those acceptable methods, techniques, and practices (including tools, equipment, and test equipment) may be used to complete the work. When the words "in accordance with" are included in the instruction, the methods, techniques, and practices specified (including tools, equipment, and test equipment) in the referenced document must be used.
If any of the below steps cannot be performed as written, contact Lockheed Martin Aeronautics Company for troubleshooting instructions.
A. Ensure 342986-13/-14/-19/-20 Longeron is not in direct sunlight and is not hot to the touch. If longeron is found to be hot to the touch, reposition the aircraft to be out of direct sunlight if possible or move aircraft into hangar and wait until temperature of the longeron stabilizes between 50 to 95 °F.
B. Prepare aircraft for maintenance in accordance with applicable Job Guide.
C. Open cargo ramp to ground position in accordance with DMC-L382-A-52-00-03-00A-913A-A.
D. RC - Perform conductivity check on 342986-13/-14/-19/-20 Longeron as follows:
WARNING: ISOPROPYL ALCOHOL IS FLAMMABLE AND TOXIC TO SKIN, EYES, AND RESPIRATORY TRACT. AVOID SKIN AND EYE CONTACT. GOOD GENERAL VENTILATION IS NORMALLY ADEQUATE. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY TO PERSONNEL.
(1) The surface of the longeron to be inspected shall be free of dirt, grease, oil, or other contaminants prior to performing any conductivity measurements. Clean area with ASTM D 770 Isopropyl Alcohol. Wipe surface dry. Do not allow alcohol to dry on surface.
CAUTION: FAILURE TO PERFORM CONDUCTIVITY TESTING BETWEEN TEMPERATURE RANGES OF 50 TO 95 °F WILL RESULT IN INCORRECT RESULTS.
(2) Place tape measure just aft of starting location of 342986-13/-14/-19/-20 Longeron (FS 737), at approximately FS 739. See Figure 1, Sheet 2. Extend tape measure along the length of the longeron past the location at which the ramp and door come together, approximately FS 869. See red circled area on Figure 1, Sheet 3. Keep tape measure taut by securing tape measure with adhesive tape along the length of the longeron.
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN CAUTION: ENSURE THAT THE 342986-13/-14/-19/-20 LONGERON, CONDUCTIVITY METER, AND CONDUCTIVITY STANDARDS ARE WITHIN 5 °F OF EACH OTHER. FAILURE TO PROPERLY
STANDARDIZE THE CONDUCTIVITY METER AND APPLY LIFT OFF COMPENSATION WILL RESULT IN AN INCORRECT CONDUCTIVITY READING.
(3) Standardize Magnatest FM-110 or Magnatest ED-500 unit in accordance with DMC-L382-A-20-10-04-00A-353A-A.
(4) Using standardized Magnatest FM-110 or Magnatest ED-500 unit, measure the conductivity in the 342986-13/-14/-19/-20 Longeron beginning at the curved end of the longeron, taking the first measurement 12 inches from FS 739 or whichever location is first accessible and not blocked by obstructions such as rivets or end fittings in accordance with DMC-L382-A-20-10-04-00A-353A-A. See Figure 2. Continue taking measurements every four inches along the vertical flange of the longeron, stopping eleven feet from FS 739. The first 0 to 2.5 feet of the longeron are not typically accessible, however conductivity measurements shall be taken where possible within this 2.5 foot section. If a measurement is not able to be taken at a test location, mark location on Figure 4 and Figure 5 as “no access” and continue to next text location. Record results in Figure 4 and Figure 5.
(5) Take three additional conductivity measurements in approximately four inch intervals, at the unformed end of the longeron which starts approximately eleven feet aft from FS 739. The exact location of these measurements is not critical, but the test shall be performed in the vertical flange of the longeron as shown in Figure 2, not near a large formed tang, and not blocked by obstructions such as rivets or end fittings. Record results in Figure 4 and Figure 5.
(6) If conductivity measurements at the unformed end recorded in Figure 4 or Figure 5 are less than or equal to 36% IACS then the longeron is most likely Part Number 342986-13 (left) and 342986-14 (right) 7075-T6511. In this case, if conductivity does not exceed 39.0% IACS along the entire accessible length, the sloping longeron has the properties needed to perform its function and does not require further testing. If conductivity exceeds 39.0% IACS at any location, hardness testing is required.
(7) If the conductivity measurements at the unformed end recorded in Figure 4 or Figure 5 is greater than 36% IACS then the longeron is 7055 Part Number 342986-19 (left) and 342986-20 (right) and may be either T74511 or T76511. In this case, if conductivity does not exceed 40.0% IACS along the entire accessible length, the sloping longeron has the properties needed to perform its function and does not require further testing. If conductivity exceeds 40.0% IACS at any location, hardness testing is required.
E. RC - If hardness testing was determined to be required in either Step 2.D.(6) or (7), perform a Rockwell Hardness Test as follows:
CAUTION: FAILURE TO PERFORM HARDNESS TESTING BETWEEN TEMPERATURE RANGES OF 50 TO 95 °F WILL RESULT IN INCORRECT RESULTS.
(1) For each location where a hardness testing was determined to be required in either Step 2.D.(6) or (7), mark the location as shown in Figure 3, Sheet 1, and remove the tape measure.
(2) For each marked location, ensure Wilson M-51 Portable Rockwell Hardness Tester, or similar portable hardness tester meeting ASTM E110, can be clamped in the desired measurement location as shown in Figure 3, Sheet 2. Some locations may be obstructed by rivets or other assemblies as shown in Figure 3, Sheet 3. Finishes should not be removed in obstructed locations. Mark obstructed locations on Figure 4 and Figure 5 as “no access”.
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
A382J-53-004March 27, 2023 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN WARNING: FINISHES CONTAIN HEXAVALENT CHROMIUM. HEXAVALENT CHROMIUM FINISHES ARE TOXIC TO SKIN, EYES, AND RESPIRATORY TRACT WHEN AIRBORNE. AVOID SKIN AND EYE CONTACT. FOLLOW LOCAL PROCEDURES FOR HEXAVALENT CHROMATED PPE. FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY TO PERSONNEL.
(3) Remove finishes in unobstructed locations down to bare metal in the area to be hardness tested in an area one inch in diameter. See Figure 3, Sheet 4.
(4) Standardize Wilson M-51 Portable Rockwell Hardness Tester, or similar portable hardness tester meeting ASTM E110 in accordance with manufacturer’s directions. This shall include performing a pre and post test verification and standardizing the tester by performing a hardness test on a calibrated test block that is within 15 Rockwell points of the material to be tested.
(5) Using standardized Wilson M-51 Portable Rockwell Hardness Tester, or similar portable hardness tester meeting ASTM E110, measure 342986-13/-14/-19/-20 Longeron hardness at each location at which finishes have been removed. When clamping the hardness tester, place a steel shim, 2 by 1 by 1/8 inch, underneath the longeron before the tester is installed to ensure compliant installation. See Figure 3, Sheet 5. Record results in Figure 4 and Figure 5. After testing is complete, there will be hardness test indentations as shown in Figure 3, Sheet 6.
(6) If all hardness readings are 80 Rockwell B or above, the 342986-13/-14/-19/-20 Longeron is acceptable and no further inspection is required, proceed to Step 2.E.(7). Otherwise, if any hardness reading is below 80 Rockwell B, Lockheed Martin Aeronautics Company must review results to determine further actions. Submit all conductivity and hardness inspection results as recorded on Left Hand and Right Hand Longeron Inspection Results Forms as shown in Figure 4 and Figure 5 as an attachment to the address below.
(7) Treat bare metal exposed in Step 2.E.(3) as follows:
WARNING: ISOPROPYL ALCOHOL, COLORED CHEMICAL CONVERSION COATING, EPOXY PRIMER, AND POLYURETHANE ARE FLAMMABLE AND TOXIC TO SKIN, EYES, AND RESPIRATORY TRACT.
AVOID SKIN AND EYE CONTACT. GOOD GENERAL VENTILATION IS NORMALLY ADEQUATE.
FAILURE TO COMPLY MAY RESULT IN SERIOUS INJURY TO PERSONNEL.
(a) Clean areas with ASTM D 770 Isopropyl Alcohol. Wipe surface dry. Do not allow alcohol to dry on surfaces.
(b) Apply MIL-DTL-81706 Colored Chemical Conversion Coating to areas in accordance with Corrosion Prevention and Control Manual.
(c) Touch up finish with two coats of MIL-PRF-23377, Type I, Class C2, Epoxy Primer, and two coats of MIL-PRF-85285, Type I, Polyurethane. Match color to aircraft.
F. If inspection results were not submitted in Step 2.E.(6), complete Figure 4 and Figure 5 Inspection Results (positive or negative) and return to the Customer Support Center at the address below.
G. Close cargo ramp in accordance with DMC-L382-A-52-00-03-00A-913A-A.
H. Restore aircraft to service in accordance with applicable Job Guide.
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN NOTE: If assistance is needed, contact your local Lockheed Martin Aeronautics Company representative, or the Customer Support Center in Marietta, Georgia, USA, as follows:
TELEPHONE: (770) 494-9131 FAX: (770) 494-9122 E-MAIL: hercules.support@lmco.com MAIL: Lockheed Martin Aeronautics Company 86 South Cobb Drive Dept. 3D3M00, Zone 0591 Marietta, GA 30063, USA
HERCULES Lockheed Martin Aeronautics Company Marietta, Georgia 30063
ALERT SERVICE BULLETIN FS 1023 FS 869- 342986-()
LONGERON (REF) FS 737 WL
140.0 1-5637-001 342986-13/-14/-19/-20 Longeron Location and Inspection Details Figure 1, Sheet 1 of 3 March 27, 2023 USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT. A382J-53-004 Page 7
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN 342986-13/-14/-19/-20 Longeron Location and Inspection Details Figure 1, Sheet 2 Start of Tape Measure Location
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
A382J-53-004March 27, 2023 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN 342986-13/-14/-19/-20 Longeron Location and Inspection Details Figure 1, Sheet 3 End of Tape Measure Location
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN Conductivity Test Probe Placement Figure 2
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
A382J-53-004March 27, 2023 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN Hardness Tester Placement and Testing Details Figure 3, Sheet 1 of 6 Marking Hardness Test Locations
USE, COPYING, AND/OR DISCLOSURE IS GOVERNED BY THE STATEMENT ON THE TITLE PAGE OF THIS DOCUMENT.
March 27, 2023A382J-53-004 HERCULES Lockheed Martin Aeronautics CompanyMarietta, Georgia 30063
ALERT SERVICE BULLETIN Hardness Tester Placement and Testing Details Figure 3, Sheet 2 Hardness Tester Clamped on Longeron