1964

A) Inflight Motion Picture System provisions in accordance with Lockheed Report 2580, Rev. 7, dated October 1964 and Electro Magnetic Compatibility, Lockheed Report 2573, Rev. 2, dated October 1964. (Report 2580 Rev. 7 dated October 1963 is equivalent to EM 1800 Section Report 2580 Rev. 20 dated November 1964). (B) Inflight Motion Picture System provision in 3 Class DC-8 in accordance with EM 1801 Section of Lockheed Report 2580 Rev. 30, December 1964 and Electro Magnetic Compatibility Lockheed Report 2573, Rev. 9, dated November 1964. This installation must be accomplished on aircraft with STC SA759WE installed. (Report 2580 Rev. dated December 30, 1964, same as Rev. dated December 10, 1964, with E.O. 19472, 19473, 19474, 19475, 19487). ( See Continuation on Page 3).

Aircraft: DC-8-12, DC-8-21, DC-8-51, DC-8-52

Interior modifications for two 85 occupant configurations and rework of seats to provide removable arm rests as described on United Air Lines Approved Drawing List Nos. COA 6-3023 dated October 14, 1963, COA 6-3036 dated October 28, 1963, and COA 6-3053, Revision B, dated August 21, 1964.

Aircraft: DC-6B

Interior configuration - 120 passenger single class 5-abreast seating per United Air Lines approved drawing lists: COA 2-2083 (Sheet #1 Revision February 17, 1964, Sheet #2 dated December 4, 1963, Sheet #3 Revision dated February 27, 1964 and, COA 2-2099 Revision dated December 17, 1963).

Aircraft: DC-8-11, DC-8-12, DC-8-21, DC-8-31 +23 more

Approval of 200 lb. increase in Maximum gross weight for takeoff and landing when equipped with the following Flight Extenders Inc. Tip tank Installation: 15 gal (RB2-100B) or 14.7 gal (RBI-IOOG, RBI-IDOL) Fiberglass wing tip fuel tanks (ref STC SA3OEA, Configuration 2 or 3) and Type II or III Kit transfer fuel system. This system eligible with Beech 20 gal wing aux. tanks or baggage compartment tanks, but not both. This STC also places the above aircraft in the Normal and Utility categories, using the Normal Category as the basic category for purposes of placarding and marking. Flight Extenders, Inc. Installation Manual FEI-35 (4A) Rev. C dated February 15, 1964 is required.

Aircraft: H35, J35, K35, M35 +7 more

Approval of 200 lb. increase in Maximum gross weight for takeoff and landing when equipped with the following Flight Extenders Inc. Tip tank Installation: 15 gal (RB2-100B) or 14.7 gal (RBI-IOOG, RBI-IDOL) Fiberglass wing Solenoid Fuel System (ref STC SAl-303 dated February 20, 1959). No wing or baggage compartment auxiliary tanks are permitted with this system. This STC also places the above aircraft in the Normal and Utility categories, using the Normal Category as the basic category for purposes of placarding and marking. Flight Extenders, Inc. Installation Manual FEI-35 (4A) Rev. D dated February 15, 1964 is required.

Aircraft: H35, A35, B35, C35 +4 more

Installation of Lycoming O-360-A1D engine and McCauley 2D36C14/78KM-4 or Hartzell HC-C2YK-1A/7666-2 propeller in accordance with Doyn Aircraft Drawing List for Model 1700 conversion dated May 6, 1964; for Cessna Model 175B: Atlas Aviation Oil Cooler Installation dated September 12, 1967, is required.

Aircraft: 175, 175A, 175B

Installation of Lycoming IO-360-B1A engines and Hartzell HC-C2YK-2RA/7666A-2 propellers. Gross weight increase to 4000 lbs. Data required: Eight photographs for Doyn 180 HP Piper Apache Fuel Injection dated May 20, 1964. Doyn dwg. 1800, Rev. C dated 3/23/62, except for propeller specified and fuel system (dwg. 1807). Hartzell Type Certification Data Sheet P-920-5 for propeller installation.

Aircraft: PA-23-160

Modification of flush type fuel caps for installation of a locking cylinder and keeper. (1964 and subsequent)

Aircraft: PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P) +280 more