Free Reply to Response to Motion - District Court of Colorado - Colorado

Case 1:01-cv-02056-JLK

Document 135-2

Filed 02/05/2007

Page 1 of 2

Subject: FLIGHT TEST GUIDE FOR CERTIFICATION OF PART 23 AIRPLANES

Date: 8/14/03 Initiated By: ACE-100

AC No: 23-8B Change:

1.

PURPOSE. a. This advisory circular (AC) sets forth an acceptable means, but not the only means, of showing compliance with Title 14 Code of Federal Regulations (14 CFR) Part 23 concerning flight tests and pilot judgements. Material in this AC is neither mandatory nor regulatory in nature and does not constitute a regulation. b. This AC is one method being utilized to achieve national standardization in normal, utility, acrobatic, and commuter category airplanes. This AC applies to Subpart B and various sections under Subparts A, D, E, F and G from § 23.1 through § 23.1589. This AC consolidates existing policy documents, and certain AC's that cover specific paragraphs of the regulations, into a single document. c. This material is intended as a ready reference for Part 23 airplane manufacturers, modifiers, Federal Aviation Administration (FAA) design evaluation engineers, flight test engineers, and engineering flight test pilots, including Delegation Option Authorization (DOA), Designated Alteration Station (DAS), and Designated Engineering Representative (DER) personnel.

2.

CANCELLATION. The following AC is cancelled: AC 23-8A, Flight Test Guide for Certification of Part 23 Airplanes. GENERAL. This AC covers flight test items of interest during type certification. Other engineering disciplines, such as airframes, systems and equipment, and propulsion are addressed as they pertain to flight test criteria. BACKGROUND. a. AC 23-8, Flight Test Guide for Certification of Normal, Utility, and Acrobatic Category Airplanes, was published to replace FAA Order 8110.7, Engineering Flight Test Guide for Small Airplanes, dated June 20, 1972, and to consolidate existing flight test policy. AC 23-8 did not cover commuter category airplanes. AC 23-8A updated the original 23-8 by adding information and guidance for commuter airplanes. AC 23-8B again updates the Flight Test Guide to

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4.

Exhibit H

Case 1:01-cv-02056-JLK
AC 23-8B

Document 135-2

Filed 02/05/2007

Page 2 of 2
8/14/03

(3) Engine Operation with Automatic Propeller Control System Installed. (i) When an automatic control system for simultaneous r.p.m. control of all propellers is installed, it should be shown that no single failure or malfunction in this system or in the engine controlling this system will cause the following: (A) The allowable engine overspeed for this condition to be exceeded at any time; and (B) A loss of thrust that will cause the airplane to fail to meet the requirements of §§ 23.51 through 23.77 if such system is certificated for use during takeoff and climb. This should be shown for all weights and altitudes for which certification is desired. A period of 5 seconds should be allowed from the time the malfunction occurs to the initial motion of the cockpit control for corrective action taken by the crew. (ii) Compliance with this policy may be shown by analysis, flight demonstration, or a combination thereof.
c. Restart Envelope.

(1) Explanation. The applicant should propose a practicable airstart envelope wherein satisfactory inflight engine restarts may be accomplished as required by the code. Airstarts should be accomplished satisfactorily at critical combinations of airspeed and altitude. During these tests, normally, time history data showing airspeed, altitude, r.p.m., exhaust temperature, and so forth, are obtained for inclusion in the Type Inspection Report. The airstart envelope should be included in the limitations section of the AFM, and the procedures used to restart the engine(s) should be contained in the emergency or abnormal procedures section of the AFM. Results of restart tests completed by the engine manufacturer on the same type of engine in an altitude test facility or flying test bed, if available. The experience accumulated in other aircraft with the same engine and engine installation, may be taken into account if justified. (2) Procedures. To establish the required envelope of altitude and airspeed, sufficient flight tests should be made as follows: (i) From sea-level to the maximum declared restarting altitude in all appropriate configurations likely to affect restarting, including the emergency descent configuration; (ii) From the minimum to the maximum declared airspeed at all altitudes up to the maximum declared engine restarting altitude. The airspeed range of the declared restart envelope normally should cover at least 30 kts, but should be adapted to the type of airplane. The tests should include the effect on engine restarting performance of delay periods between engine shutdown and restarting as follows: (iii) Up to two minutes; and (iv) At least until the engine oil temperature is stabilized at its approximate cold soak value.

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Exhibit H