FINAL_Amendment_1_AG-024B-S-15-9007LFS_Solicitation_5-28-15.pdf

National Exclusive Use Large Fire Support Helicopter Services

AG-024B-S-15-9007

Table of Changes

Section Page Description

B B-3 71 & 72 Corrected Item #’s in both tables

B B-12 74 VHF-FM Programming Port – changed language

B B-12 74 Gated Powerfill Bucket – changed language

C C-4 82 Paragraph (d) (17) (i) – added language to paragraph C C-4 83 Paragraph (d) (18) (iii) (C) – changed language

C C-7 97 Paragraph (b) (4) (iii) (D) – added contact person to paragraph

Solicitation No. AG-024B-S-15-9007 US Forest Service National Exclusive Use Large Fire Support Helicopter Services National Office

SECTION B

SUPPLIES OR SERVICES AND PRICES

71 Amendment 1

(C) Following any major repair or major alteration or change to the equipment list, which significantly affects the center of gravity of the aircraft.

(iv) Helicopter(s) under this solicitation shall:

(A) Remain at or below the contracted helicopter equipped weight as proposed in the base year of the contract. When there is a difference in the aircraft's weight between different sets of scales, scales shall be allowed a maintenance tolerance of .2 % (two tenths of a percent) of the scale reading for each set of scales. For example, a helicopter that weighed 6000 lbs on one scale set would be allowed a 12 lb tolerance on each scale set when compared. (Ref. NIST Handbook 44, Table 6).

(B) Be allowed a total of 1% above the contracted helicopter equipped weight as proposed during the combined contract option periods.

(v) Cowlings, doors and fairings shall not be removed to meet contract equipped weight for performance.

(vi) If the government requires additional equipment after contract award, no penalty will be assessed.

(2) After proposal evaluations and prior to or post award all Exclusive Use aircraft weighing shall be witnessed and validated by Agency Aircraft Inspector(s). If aircraft must be weighed post award it will be at the option of the Government. The objective of the second and separate weighing is to validate the contractor’s proposed weight as configured to comply with the solicitation requirements. Contractors are responsible for the costs associated with weighing the aircraft excluding Agency Aircraft Inspector costs.

All aircraft shall be weighed prior to start of the base year Mandatory Availability Period

(MAP).

Applicable Performance Specifications for the Following Items:

Item 4 (Grangeville) Item 6 (Oskoda/Ely/Jeffco)

Item 7 (Rifle) Item 9 (Sierra Vista)

Item 10 (Silver City) Item 11 (Cedar City) Item 15 (McCall) Item 16 (Minden)

Item 17 (Salmon Item 20 (Fresno) Item 21 (Hemet) Item 22 (Lancaster)

Item 24 (Porterville) Item 26 and 27 (San Bernardino 1 and 2) Item 32 (LaGrande)

Note: See schedule of items for tank or bucket requirements.

CAPABILITY OF:

Hovering out of ground effect (HOGE)

At 8,000 feet pressure altitude and 25° C with non-jettisonable jettisonable

72 Amendment 1

Payload of 5000 pounds, as determined by Exhibit 13, Standard Interagency Load Calculation form, using a standard pilot weight of 200 pounds and fuel for one hour and 30 minutes (01+30) as determined by Exhibit 12, Hourly Flight Rates, Fuel Consumption, and Weight Reduction Chart. For Computed Gross Weight use Exhibit 22 for load calculation.

Applicable Performance Specifications for the Following Items:

Item 1 (Bozeman) Item 2 (Hamilton) Item 3 (Helena) Item 5 (Libby)

Item 8 (Custer) Item 12 (Lucky Peak) Item 13 (Mt. Green) Item 14 (Pocatello)

Item 18 (Bishop) Item 19 (Chester) Item 23 (Pollock Pines) Item 25 (Casitas)

Item 28 (Weed) Item 29 (Truckee) Item 30 (Grants Pass) Item 31 (John Day)

Item 33 (Prineville) Item 34 (Wenatchee)

Note: See schedule of items for tank or bucket requirements.

CAPABILITY OF:

Hovering out of ground effect (HOGE)

At 7,000 feet pressure altitude and 20 °C with non-jettisonable jettisonable

Payload of 3300 pounds, as determined by Exhibit 13, Standard Interagency Load Calculation form, using a standard pilot weight of 200 pounds and fuel for one hour and 30 minutes (01+30) as determined by Exhibit 12, Hourly Flight Rates, Fuel Consumption, and Weight Reduction Chart. For Computed Gross Weight use Exhibit 22 for load calculation.

B-4 ENGINE REQUIREMENTS

Turbine engine(s)

B-5 CREW COVERAGE

The number of persons required will be the minimum complement of personnel while operating under this contract, additional positions may be offered to staff and support the helicopters.

One Pilot Crew or Two Pilot crew or Three Pilot crew

And

With Relief Pilot(s) Without Relief Pilot(s)

6-Day Coverage (See Chart Below)

7-Day Coverage (See Chart Below) A B OR C

74 Amendment 1

B-11 OPERATIONS IN ALASKA, CARIBBEAN, CANADA, OR MEXICO (Contractor to check all that apply).

Contractor has authorization as indicated in FAA Operation Specifications for operations in the following locations. Reference Exhibit 3

ALASKA CARIBBEAN CANADA MEXICO

B-12 CONTRACTOR FURNISHED SPECIAL REQUIREMENTS (Note that exceptions may apply)

Note: Anything checked will have an Exhibit that applies, to a C clause applicable, or CFR Reference.

Additional VHF-AM Radios: Total A/C Qty: 2 (See C-7 (b) (1) (i)) All Items

Additional VHF-FM Radios: Total A/C Qty: 2 (See C-7 (b) (1) (ii)) All Items

VHF-FM Programming Port (See C-7 (b) (5) (iv))

External PA with Siren capability (See Exhibit 7.b)

Internal PA with Siren capability for Heavy helicopters (See Exhibit 7.c)

GPS with moving map display (See Exhibit 7.d)

GPS Data connector (See Exhibit 7.e)

Additional GPS Antenna (See Exhibit 7.f)

Traffic Advisory System (TAS) (See Exhibit 7.g)

Intercommunication System for all passenger positions (See Exhibit 7.h)

Aft Cabin Audio Control System (Use Exhibit 17 Avionics section for 3rd audio control system requirements.)

P-25 Digital VHF-FM Mobile Radio for Fuel Servicing Vehicle (See Exhibit 8.g)

Rappel Capability (See Exhibit 17)

Extended Height landing gear (See C-4)

Litter Kit Provisions with Litter w/o Litter (See Exhibit 25). List Item Number(s)

FAA Over Water Kit (See Exhibit 24)

Fixed Suppressant/Retardant Delivery Tank (As required or when offered See B-1 Schedule of Items and Exhibit 5.)

PART 27--Airworthiness Standards: Normal Category Rotorcraft Only (See CFR Part 27)

Certificated For Full Time Left Seat Operations (135 and 133) (C-4 (e) (4))

STC’d For Left Seat Vertical Reference (See Section C-4 (d) (10))

Gated Powerfill Bucket (Required as primary bucket on all bucket offers, see C-4 (18) (iii).)

SECTION C

DESCRIPTION/SPECIFICATIONS/EXHIBITS

82 Amendment 1

(15) One or more independently switched white strobe light(s) mounted on top of the helicopter or otherwise visible from above. An LED aviation red strobe installed by the OEM or Supplemental Type Certificate will also fulfill this requirement. In order to meet contract specifications, Contractors shall obtain FAA approval (FAA Form 337) to alter the aircraft, if applicable.

Each anti-collision light shall be aviation red and shall meet the applicable requirements of 14 CFR Part 27.1401 or Part 29.1401.

(16) High visibility markings on main rotor blades (Exhibit 6, High Visibility Markings on Main Rotor Blades).

(17) Remote and Cargo Hook

(i) Cargo Hook

(A) One keeperless cargo hook that is capable of being loaded and locked in a single motion with one hand, and is rated at the maximum lifting capacity of the aircraft. Note: Keeperless hook required for Type II helicopters only.

(B) As a minimum, the cargo hook shall be completely disassembled and inspected with repairs made as required, lubricated, and a full-load operational check in accordance with manufacturers recommendations.

(ii) Remote Hook/Long line

(A) One remote cargo hook and a minimum of 150 feet of long line. Long line may consist of multiple segments and none shorter than 50 feet as per Exhibit 5.

(B) For Power requirements see Exhibit 5

(18) Variable capacity collapsible bucket(s) (Required for all bucket helicopters and type II and III tanked helicopters)

(i) All Buckets

(A) One (1) collapsible, variable capacity water/retardant buckets shall be furnished under this Contract. Bucket must be capable of being transported in cabin or baggage compartment or external basket of the helicopter.

(B) The bucket, at 100 percent of manufacturers rated capacity (+/ -5%) shall be commensurate with the maximum OGE lifting capability of the helicopter at 5000 PA and 30 degrees C with a 200 pound pilot(s) and 1 1/2 hours of total fuel or the manufacturer recommended size/model bucket by helicopter make and model shall be used. The bucket shall be capable of being operated with all increments of the long-line.

83 Amendment 1

(C) An Operations Manual for the type bucket(s) provided shall be available on site.(D) Environmental operating conditions may dictate the need for more than one size bucket.

(E) Shall be leak free (1 gallon or less per minute)

(ii) Non-Gated buckets and non-powerfill buckets

(A) A second variable capacity water/retardant is required. At 100% capacity, the second bucket shall be no more than 10% greater than the minimum capacity of the primary bucket.

(B) Bucket capacity at each position or adjustment level shall be marked on the bucket. Collapsible buckets with cinch straps shall only be adjusted to marked graduations (i.e., 90%, 80%, and 70%). Intermediate graduations or capacities below the manufacturer’s minimum graduation (by tying knots, etc.) are prohibited.

(C) Either the weight of the bucket or capacity at each adjustment level shall be marked on the bucket or the operator shall have a written statement of the maximum capacity (weight) at each adjustment point.

(iii) Gated Buckets and Powerfill buckets

(A) Requires electronic hook load measuring system that provides cockpit readout of the actual weight.

(B) Either the weight of the bucket or capacity shall be marked on the bucket or the operator shall have a written statement of the maximum capacity (weight).

(C) If powerfill equipped, bucket must fill to maximum capacity in no more than 90 seconds.

(19) Reserved

(20) Reserved

(21) Fuel Servicing Vehicle (See Exhibit 8 Fuel Servicing Equipment Requirements) (Not required for Alaska).

(22) FAA Approved Extended Height /High Skid Landing Gear (if available by STC or aircraft manufacturer).

(23) FAA approved high visibility, pulsating, forward facing, conspicuity lighting.

(24) FAA approved locking cap(s) on all fuel filler ports. Single point refueling port dust caps need not have an FAA approved locking device.

(25) FAA approved Wire Cutters, if available, or Standard Category personnel transport helicopters only.

97 Amendment 1

(iii) Additional Telemetry Unit (ATU)

(A) Additional Telemetry Units shall be powered by the aircraft’s electrical system and operational in all phases of flight.

(B) The ATU must report tank door open, gallons dropped, and tank door close events with GPS data (Date, Time, Latitude, Longitude, Altitude, Speed and Heading) following the same data format as the AFF requirement. Depending on the tank system, additional data may be requested such as pump on/off and coverage level after ground speed adjustment.

(C) The ATU data must be available to the government in near real time.

A subscription service shall be maintained through the AFF equipment provider allowing AFF position reporting and ATU drop event data via the Government AFF program.

(D) Contact Bob Roth, the AFF Program Manager, at either rroth@fs.fed.us or (406) 829-6712 for a list of systems known to meet the ATU requirements.

(iv) Transponders

Transponder systems shall meet the requirements of 14 CFR 91.215(a). Part

135 aircraft shall meet the “Mode S” requirements of 14 CFR 135.143(c).

Transponder systems shall be tested and inspected every 24 calendar months as specified by 14 CFR 91.413.

(v) Altimeter and Automatic Pressure Altitude Reporting systems

Altimeter, static pressure, and automatic pressure altitude reporting systems shall be installed and maintained in accordance with the IFR requirements of 14

CFR Part 91. These systems shall be tested and inspected every 24 calendar months as specified by 14 CFR 91.411.

(vi) Traffic Advisory Systems (TAS)

Traffic advisory systems shall be TSO approved, use active interrogation, graphically display traffic relative to the aircraft’s horizontal position, and provide alert audio to the PICs audio control system. The display shall be within view of the PIC and SIC/observer. The system shall provide coverage in all directions above and below the aircraft with a maximum range of at least 10 nautical miles.

The display shall allow range selection of 2 miles or less.

mailto:rroth@fs.fed.us