Amendment_0006__SAH.doc

SECTION SF 30 BLOCK 14 CONTINUATION PAGE

SUMMARY OF CHANGES

SECTION SF 30 - BLOCK 14 CONTINUATION PAGE

The following have been added by full text:

AMENDMENT 0006

1. Clause 52.222-60, Paycheck Transparency (Executive Order 13673)(OCT 2016), is hereby incorporated as shown below in Section I.

2. The following are questions received by this Agency and our answers:

Question 1: Within 4.2.28 and 4.2.29 of the Specification it mentioned the test methods are "MIL-STD-810, Method 510.6, Procedure I and II" - looking at MIL-STD-810 there's no "Method 510.6" mentioned, is this supposed to be Method 510.5?

Answer: The reference to Method 510.6 is correct, the current version of the MIL-STD is MIL-STD-810G with Change 1 dated 15 April 2014.

Question 2: Confirm that DEPOT level repairable components will be identified in the LPD records but will NOT include further breakdown that may occur at the organic depot repair facility.

Answer: The above statement is correct.

Question 3: Confirm that vendor COTS manuals, instructional pamphlets, specification sheets and drawing packages will be considered acceptable to serve as Depot Repair Instructions for identified DEPOT repairable components.

Answer: The above statement is correct.

Question 4: SAH-REQ-0140 (3.2.7.2.f) states that the fuel tank capacity shall be sized to accommodate 48 aircraft moves. Is there an average idle runtime per aircraft move that has been factored into fuel tank capacity? If not, how much idle runtime should be factored in addition to each aircraft move?

Answer: While there will be idle runtime during actual aircraft moves the requirement for fuel tank capacity is defined correctly in Performance specification paragraph 3.2.7.2.f. The method to verify fuel tank capacity is defined in Performance Specification paragraph 4.2.17 and was revised in Amendment 0002.

Question 5:

Section 3.2.1.3.e.2 states “The SAH with a 17,300 lb. lifted load shall withstand the side forces associated with an instantaneous 90 degree turn while towing a 66,000 lb. aircraft at maximum towing speed.”

Section 3.2.1.4.a.2 states “The SAH, with 66,000 lbs. in tow and 17,300 lbs. carried by the lift mechanism shall have a top speed of 2.5 (+/-0.5) MPH.”

Section 3.2.1.5.a states “Towed Load Braking Requirement [SAH-REQ-0009] The SAH, while towing a 66,000 lb. load (with 17,300 lbs. carried by the lift arms) at top speed, shall come to a complete stop within 2.0 feet when the operator controls are release or the E-stop button is pushed.”

Please confirm the total towed load (aircraft weight) is 66,000 pounds of which 17,300 pounds will be carried by the pickup system as specified in Sections 3.2.1.3.e.2 and 3.2.1.5.a and not a load of 66,000 pounds plus 17,300 pounds for a total of 83,300 pounds that could be inferred by Section 3.2.1.4.a.2.

Answer: The total towed load (aircraft weight) is 66,000 lbs of which 17,300 lbs is carried by the lift mechanism.

Question 6:

Section 3.2.4.b states “Ground Clearance [SAH-REQ-0036] The SAH with a 17,300 lb. load on the lifting arms shall have a ground clearance greater than 1.5 inches.”

Section 3.2.4.d states “Approach and Departure Angle [SAH-REQ-0038] the unloaded SAH shall be capable of traversing the ramp identified in Figure 3:” which requires a four inch ground clearance.

Section 3.2.1.3.b.6 states “The lifting/attaching mechanism shall be able to lift the landing gear a minimum of 18 inches off the deck. If using pins engaged to the landing gear axles, the engagement centerline heights vary from 4.5 inches to 31 inches off the deck (this range includes the total lift height requirement).”

To comply with the 4.5 inch pin height required in Section 3.2.1.3.b.6, the pickup arms will rest below the four inch ramp clearance requirement when full down. The pickup arms will need to be raised slightly to traverse the four inch ramp shown in Figure 3. Please confirm this is acceptable.

Answer: Raising the lift mechanism while traversing the ramp depicted in Performance Specification paragraph 3.2.4.d is acceptable.

Question 7:

Where can we access the dimensions for nose/tail wheel profiles for all required aircraft?

Answer: All available dimensions are included in the Aircraft Landing Gear Summary Table (Jan 2017) which is attached to this Amendment. The range provided in the Performance Specification paragraph 3.2.1.3.b accommodates lifting all aircraft by their axles.

SECTION I - CONTRACT CLAUSES

The following have been added by reference:

52.222-60

(End of Summary of Changes)