Exemption No. 11092 UNITED STATES OF AMERICA D E PARTM ENT OF TRANSPORTATION F E DERAL AVIATION ADMINISTRA TlON WAS HINGTO N , D C 2 0591

In the matter of the petiti o n of CIRRUS DESIGN CORPORAT ION for an exemption from 

### § 23 .177(b) of Ti tl e 14 , Code of Federal R eg ulation s Regulatory Docket No. FAA 2014-0533

GRANT OF EXEMPTION By letter da t e d Jul y 23 , 2 014 , Mr. Tom E nge lm ann, Certification Eng ineer, Ci rru s De s ign Corporation ( C irru s), 451 5 Tay lor C ircl e, Duluth , MN 55811 petitioned the Federal Aviation Administration (FAA) on b e half of Cirrus for an exemp tion from 

### § 23.177(b) of Title 14 , Co de of Federal Regulation s ( 14 CFR)

. The propo se d exempti o n , if granted , would allow type certification of the Cirru s Mode l SFSO without a Rudder-Aileron Interconnect (RAJ). The petitioner requests relief from the following regulation: Section 23 .177 (b) , i n pertinent part , s tate s:

" (b)(1) T he s tatic lateral s tabilit y, as shown by the tendency to rai se the low wing in a s ides lip with the ai leron controls free , may not be negative for any landing gea r and flap position appropriate to the takeoff , climb , c ru ise , approac h , and landing configurations. Thi s mu s t be shown with symmetrical power from idle up to 75 p e rcent of maximum continuous powe r at speeds from 1.2 V s 1 in the takeoff configuration(s) and at s peeds from 1 .3 V s 1 in oth er configurations , up to the maximum allowab l e airs peed for th e configurat ion being inve s tigated (V F E, Y LE, Y No, YFc/ M Fc, w hi chever is appropriate) in the takeoff , climb, crui se, de s cent , and approach configurations. Fo r the landin g co nfigurati on, the pow e r mu s t b e that necessary to maintain a 3-degree angl e of desc ent in coo rdinated flight. (2) The static lateral stability m ay not be negative at 1. 2 Y s 1 in th e takeoff configuration , or at 1.3 Vs 1 in other configurations.

ACE-14-40 9- E2 (3) The angle of sides lip for these tests must be app ropriate to the type of a irplane, but in no case may the constant heading s ideslip ang le be less than that obtainable with a I 0 degree bank or, if less, the m ax imum bank angle obtainable with full rudder deflection or 1 50 pound rudder force. " The petitioner supports its request with the fo ll owing information: The petitioner states on the SR20 and SR22 the rudder ai l eron interconnect introdu ced a higher l evel of comp lex ity into the flight control system and was the subj ect of several Ser vice Bulletins as well as an Airwort hine ss Directive (AD) on the previous C irru s Models SR20 and SR22. To avoid si milar i ssues with the SF50, Cirrus is requesting an exemp tion to simplify maintainability witho ut detrimental effect on operational safety. The FAA has determined that good cause exists for waiving the requirement for Federal Register publication because th e exemption , if granted , would not set a prec edent , and any delay in acting on this petition would be detrimental to Cirrus. The FAA 's ana lysis is as fo ll ows: The FAA recognizes relief granted in another similar circumstance as presented in your petition. Exemption No. 10923 granted re lieffr om § 23.177(b) to the SR20/22 C irru s model ser ie s. T hi s exemption yielded no comments when it was published in the Federal Re g i ster (75 FR 73919). T he FAA has reviewed your reasons for requesting an exemp tion and frnds that

1. Flight test results show the level ofsafety provided by§ 23.177(b) remains sati sfactory. Cirrus h as demonstrated the use of the electric roll trim control system , as part of the app ro ved type design, for lateral control in the eve nt the primary roll controls system b eco mes disconnected; 2. Flight test s how that with the RAI removed, all other subpart B rules remain comp li ant; 3. The reasons sta ted by th e FAA for granting the previous relief (Exemption l 0923) a l so applies to this Cirrus design; and 4. A grant of exemption is in the public interest. The FAA's Decision 

### In consideration of the foregoing , I find that a grant of exemption i s in the public interest. Therefore , pursuant to the authori ty co nta ined in 49 U.S.C. §§ 1 06(f) , 40113 and 44701 , delegated to me by the Administrator , Cirrus Design Corporation is granted an exemption from 14 CFR 23 .177(b) to the extent necessary to a llow Cirrus to remove the Rudder-Ail e ron

### 3 int erconnect (RAI) from the Cirrus SF50 a irplane , s ubj ect to the cond ition s and limitation s li ste d below. 

### Co nditions and Limitations 1

. The Airplane Flight Manua l (AFM) Limitati ons mu st s how that the electric roll trim syste m mu st be operatio n al for fli g ht. Issued 

### in Kansas City , MO , on October 23 , 2014

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# ld~ Earl Lawrence Manager, Small Airplane Directorate Aircraft Certification Service