Att_A_-_1620-01-071-0534_-_13Jun11.docx

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ENGINEERING DATA REQUIREMENTS

(ATTACHMENT “A”)

NOTE: MILITARY SPECIFICATIONS STANDARDS WILL NOT BE FURNISHED IN THE BID SET.

1. THE FOLLOWING INSTRUCTIONS ARE FURNISHED FOR THE MANUFACTURE OF:

XXXXXXXXXXXXXXXX

2. PART NUMBER:

3. NATIONAL STOCK NUMBER:

1234-12-123-1234FG

4. THE FOLLOWING SPECIFICATIONS/STANDARDS, ETC, WILL BE USED IN LIEU OF THE DATA INDICATED. THE SUPERSEDED DATA WILL NOT BE FURNISHED UNLESS SO INDICATED.

(ATTACHMENT “A”)

NOTE: MILITARY SPECIFICATIONS / STANDARDS WILL NOT BE FURNISHED IN THE BID SET.

1. THE FOLLOWING INSTRUCTIONS ARE FURNISHED FOR THE MANUFACTURE OF:

CYLINDER ASSY, INNER - SHOCK STRUT, NLG (F-16)

2. PART NUMBER:

2006644-103

3. NATIONAL STOCK NUMBER:

1620-01-071-0534LE

4. The following specifications/standards, etc., will be used in lieu of the data indicated. The superseded data will not be furnished unless so indicated.

5. Material Review Board (MRB) disposition:

A. 417 SCMS/GUEA retains all rights to review and accept material review board (MRB) dispositions prior to shipment of discrepant item. All deviations, minor and major, from the engineering drawing package shall be submitted for MRB disposition.

B. Prior to contract award, the contractor shall certify to the government in writing full compliance with manuals, specifications, and standards called out and required for the manufacture of this contracted landing gear component/assembly. Contractor is responsible to completely search these manual, specifications, and standards and fully understand the requirements necessary to manufacture landing gear components. Any questions can be forwarded to 417 SCMS/GUEA.

6. Drawing 2006644-103 – Inner Shock Strut Cylinder Assembly, NLG

6.1. Material ref: use 4330 Steel per SAE AMS 6411 in lieu of AMS 6411.

6.2. Heat Treat to meet drawing requirements per SAE AMS-H-6875 in lieu of MIL-H-6875 and MM4995.

6.3. On parts Heat Treated 180 KSI and above, any surfaces ground/machined after heat treat will be inspected for burns per MIL-STD-867 in lieu of MM5512. No more than three successive inspections shall be performed without a waiver from 417 SCMS/GUEA. Grinding will be per MIL-STD-866 in lieu of MM5759.

6.4. Magnetic Particle Inspection per ASTM E 1444 in lieu of MIL-I-6868. Use fluorescent type, full wave direct current (FWDC), and wet continuous method. The following acceptance/rejection criteria may be used as an alternate to the original manufacturer criteria: NO RELEVANT INDICATIONS ALLOWED. The intent of NO RELEVANT INDICATIONS ALLOWED is that the inspection is conducted at the required sensitivity level and there shall be no defects allowed. The inspector performing the inspections shall be certified to Level II with the inspection procedure developed by a Level III as specified in the AIA/NAS-410.

6.5. Shot Peen per SAE AMS 2430 in lieu of MIL-S-13165. Shot peen size and intensity shall be as specified by the drawing. For steel parts heat treated to 200 KSI or above, use hard steel shot in the range 55-65 HRC (per SAE AMS 2431/2 or 2431/8), or ceramic shot with a hardness comparable to 57-63 HRC (per SAE AMS 2431/7). For nonferrous metals and steel parts heat treated to values below 200 KSI, use standard hardness steel shot (per SAE AMS 2431/1, 2431/3, OR 2431/4).

6.6. Chromium Plate per MIL-STD-1501, Type 1, Class 2, in lieu of QQ-C-320, Class 2.

6.7. Install bushings per the following in lieu of MM5743:

A. The bushing installations shall be accomplished in such a manner as to avoid damage to the finish on the I.D. of the housing into which the bushing is installed, or the finish of the O.D. of the bushing. Forced installation of sub-zero installations, such as the use of a press or hammer is not permitted, and is not acceptable. A small non-metallic hammer may be used to tap the bushing into alignment with the housing bore, or to seat the bushing.

B. Prior to bushing installation, the parts and housing bore shall be cleaned with cleaning solvent to remove all contamination.

C. Liquid Nitrogen shall be used for all sub-zero installations unless some other sub-zero coolant is specified, and approved by 417 SCMS/GUEA. The soak time of the bushing in the Liquid Nitrogen shall be sufficient to allow the bushing to reach the same temperature as the coolant.

D. The bushing shall be installed into the housing immediately upon removal from the coolant with an absolute minimum of lost time. Trial runs shall be accomplished as necessary to minimize installation time which should be in the order of about seven (7) seconds maximum.

E. It may occasionally be necessary to heat the housing into which the bushing is to be installed, in addition to sub-zero cooling of the bushing. Detail parts in process will not have paint or sealant or other organic material applied prior to heating; the parts shall be heated by the use of radiant heat techniques, such as thermal blankets, infrared lamps etc., to no more than a maximum temperature of 250 F. Temperature measuring devices shall be used to monitor heat and shall be located on areas of the part expected to reach maximum temperature. No scaling, oxidation, or corrosion shall be permitted

F. Cor-Ban 27L (Zip-Chem ZC-027L), hereafter referred to as Corrosion Inhibiting Compound, per BMS 3-38 (Boeing Cage 81205), manufactured by Zip-Chem Products, 400 Jarvis Dr., Morgan Hill, CA 95037 (Cage 8E913), shall be used as noted in paragraphs G and H.

G. Bushings without flanges shall be installed into housing bore which has received a light coat of Corrosion Inhibiting Compound. Corrosion Inhibiting Compound shall not obstruct grease zerk passages. Install shrunken bushing and wipe off any excess compound that may have extruded around the periphery of both ends of the bushings.

H. Bushing with flanges shall be installed in a similar manner as paragraph (G), except Corrosion-Inhibiting Compound shall also be applied to face of lug under flange. The compound shall be applied in such a manner as to ensure complete coverage of inside face of bushing flange when bushing is installed. Wipe off any excess compound around periphery of bushing flange forming a bead. Wipe any excess compound from other end of bushing also.

6.8. Apply one coat Epoxy Waterborne Primer to noted surfaces per MIL-PRF-85582, Type I, Class C2 or N in lieu of MIL-P-23377. (Alternate one coat of Epoxy Polyamide Primer per MIL-PRF-23377, Type I, Class C2 or N). Apply two topcoats Polyurethane to noted surfaces per MIL-PRF-85285 Type I, Class H, Color Number 17925 (White) per FED-STD-595 in lieu OF MIL-C-83286, Color Number 17875.

6.9. Cadmium Plate per MIL-STD-870, Type II, Class2, in lieu of QQ-P-416, MM4951 or MM5542. (Notes 16 and 18).

6.10. Threads per SAE AS8879 in lieu of MIL-S-8879.

6.11. Threads per SAE AS8879 in lieu of MIL-S-8879.

6.12. Dimensioning and tolerancing per ASME Y14.5 in lieu of ANSI Y14.5.

6.13. Unique Identification (UID) shall be applied to each part per MIL-STD-130 in lieu of TM 1040 IAW EO# 09A3045. Marking and identification shall be per MIL-STD-130 in lieu of TM 1040. Both part number and serial number shall be marked on the part in the location shown on the drawing. The serial number shall be limited to 16 alphanumeric characters including the vendor cage (FSCM) of the contractor named on the contract, date of manufacture in the format MMYY, and a unique 4-digit number starting with 0001 in numerical order of manufacture. The serial number shall appear as “SN 9874701040001”. The height of each alphanumeric character shall be a maximum of .125 inches. The method of marking shall be limited to electro-chemical etching, dot peen, or vibro peen. The depth of each mark shall be from .003 - .005 inches.

6.14. Surface roughness per ASME B46.1 in lieu of ASA B46.1.

6.15. This component has been identified as a Critical Safety Item (CSI). Critical characteristics have been identified as follows: Flag Notes 1, 2, 4, 8, 9, 13, 16 and 18.

7. Drawing 2006744 - Forging of Cylinder, Inner Shock Strut – NLG

7.1. Material ref: use 4330 Steel per SAE AMS 6411 in lieu of AMS 6411.

7.2. Heat Treat to meet drawing requirements per SAE AMS-H-6875 in lieu of MIL-H-6875 and MM4995.

7.3. Forge per SAE AMS 6400 in lieu of MIL-F-7190:

7.4. Magnetic Particle Inspection per ASTM E 1444 in lieu of MIL-I-6868. Use fluorescent type, full wave direct current (FWDC), and wet continuous method. The following acceptance/rejection criteria may be used as an alternate to the original manufacturer criteria: NO RELEVANT INDICATIONS ALLOWED. The intent of NO RELEVANT INDICATIONS ALLOWED is that the inspection is conducted at the required sensitivity level and there shall be no defects allowed. The inspector performing the inspections shall be certified to Level II with the inspection procedure developed by a Level III as specified in the AIA/NAS-410.

7.5. Chemical milling of metals per SAE AMS-C-81769 in lieu of MM5527.

7.6. Corrosion protection per MIL-PRF-16173 Class II, Grade 3 in lieu of MM5752.

7.7. The contractor may procure forgings from sources pre-approved by landing gear engineering per paragraph A, or may elect to develop sources per paragraph B.

A. If forging are procured from sources approved by 417 SCMS/GUEA landing gear engineering, original certified forging procedures and dies/tooling or equivalent (e.g., refurbished/resunk by approved forging source) shall be used. Prior to contract award, the detailed part bidder shall provide verification (e.g., forging quote) to the government that the certified dies and procedures are available for their use in the event they are the successful bidder.

B. If the forging source is listed as unknown or the contractor wishes to develop additional sources, the contractor shall advise the government in writing of their intent to procure new forging dies and the proposed forging source prior to contract award. The contractor shall not proceed to obtain new dies without the express consent of the government procuring agency (see 417 SCMS/GUEA landing gear engineering forging SQS for further information on forging tooling qualification requirements). The government shall have unlimited use of the dies developed under this contract. The contractor shall inform the forging house in writing, at the same time the order for the dies is placed, that the government has unlimited use right of the dies and forward a copy of this letter to the government contracting officer.

C. Forging source and the location of the dies:

1. Forging Drawing: 2006744-1

2. Die #: 10124

3. Location of Dies: SIFCO Industries Inc SIFCO Forge Group

4. POC: Marilyn Irvine

5. Phone: (216) 881-8600 Ex. 287

6. CAGE: 78226

D. Prior to production, forging lot qualification shall be accomplished as specified on the forging drawing and SAE AMS-F-7190 for steel forgings and SAE AMS-A-22771 for aluminum forgings. The detailed part contractor shall assure that this has been accomplished by the forging source and retain in their records for no less than 10 years. Landing Gear Engineering reserves the right to review this documentation as needed.

7.8. This component has been identified as a Critical Safety Item (CSI). Critical characteristics have been identified as follows: Flag Notes 5, 6, 8 and 10.

8. Drawing 2006404-247 and 2006404-249 – Bushing

8.1. Fluorescent Penetrant Inspection per ASTM E 1417, Type I, Method B, C, or D, Level 3 or 4 in lieu of MIL-I-6866. The following acceptance/rejection criteria may be used as an alternate to the original manufacturer criteria: NO RELEVANT INDICATIONS ALLOWED. The intent of NO RELEVANT INDICATIONS ALLOWED is that the inspection is conducted at the required sensitivity level and there shall be no defects allowed. The inspector performing the inspection shall be certified to Level II with the inspection procedure developed by a Level III as specified in AIA/NAS-410.

8.2. Part marking and identification shall be applied to each part per MIL-STD-130 in lieu of TM1040

8.3. Dimensioning and tolerancing per ASME Y14.5 in lieu of ANSI Y14.5.

8.4. Surface roughness per ASME B46.1 in lieu of ASA B46.1.

8.5. Material use AL Bronze per SAE AMS 4640 in lieu of SAE 4640 or SAE 4880.

8.6. Cadmium Plate per SAE AMS-QQ-P-416, Type II, Class 3, or MIL-STD-870, Type II, Class 3, in lieu of QQ-P-416, MM4951 or MM5542

PREPARED BY:

RICHARD TILTON

OFFICE SYMBOL:

GBMAF

DATE:

20080411

PREPARED BY:

Steve Thorne

OFFICE SYMBOL:

417 SCMS/GUEA

DATE:

13 June 2011

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