CONCORDE LANDING REQUIREMENT EVALUATION TESTS

Tests of two late model jet transports, a Lockheed L-1011 and a Boeing 737 ADV., were conducted at Roswell, N.M. during the period of October 12-26, 1973, for the purpose of evaluating the Concorde SST Special Condition Landing Requirement. Flight path angle during approach landing weight, approach speed, sink rate at touchdown were all varied. Landings were made on both a wet and dry surface and up to five ground friction measurement vehicles were evaluated along with the aircraft. The landing requirement was shown to be feasible. Two minor changes to the requirement, both relaxatory, are indicated. One, change the reference approach flight path angle from 2.5 degrees to 3 degrees and two, revise the touchdown rate-of-sink requirement from a 3 ft./sec. maximum to a 3 ft./sec. mean with the maximum test data point not to exceed 5 ft/sec. The procedure for relating aircraft effective braking friction coefficient to the aircraft and the Diagonal-braked vehicle wet-to-dry stopping distance ratio (SDR) is shown to be adequate to establish Flight Manual data. (Author)

  • Corporate Authors:

    Federal Aviation Administration

    Flight Standards Service, 800 Independence Avenue, SW
    Washington, DC  USA  20591
  • Authors:
    • Merritt, L R
  • Publication Date: 1974-8

Media Info

  • Pagination: 218 p.

Filing Info

  • Accession Number: 00080449
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: FAA-FS-160-74-2 Final Rpt.
  • Files: NTIS, USDOT
  • Created Date: Feb 11 1975 12:00AM