[Federal Register Volume 70, Number 169 (Thursday, September 1, 2005)]
[Rules and Regulations]
[Pages 51999-52001]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-16980]



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Rules and Regulations
                                                Federal Register
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Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / 
Rules and Regulations

[[Page 51999]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19694; Directorate Identifier 2004-CE-41-AD; 
Amendment 39-14240; AD 2005-17-19]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Models SR20 
and SR22 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD 
requires you to measure and adjust the crew seat break-over bolts and 
to replace the crew seat recline locks on both crew seats. This AD 
results from CDC discovering that the crew seats, under emergency 
landing dynamic loads, may fold forward at less than the 26 g required 
by the regulations. We are issuing this AD to prevent the crew seats 
from folding forward during emergency landing dynamic loads with 
consequent occupant injury.

DATES: This AD becomes effective on October 13, 2005.
    As of October 13, 2005, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: To get the service information identified in this AD, 
contact Cirrus Design Corporation, 4515 Taylor Circle, Duluth, 
Minnesota 55811; telephone: (218) 727-2737; Internet address: http://www.cirrusdesign.com.
    To view the AD docket, go to the Docket Management Facility; U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19694; Directorate 
Identifier 2004-CE-41-AD.

FOR FURTHER INFORMATION CONTACT ONE OF THE FOLLOWING: 
--Wess Rouse, Small Airplane Project Manager, ACE-117C, Chicago 
Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des 
Plaines, Illinois 60018; telephone: 847-294-8113; facsimile: (847) 294-
7834; email: <a href="/cdn-cgi/l/email-protection#7b2c1e08085529140e081e3b1d1a1a551c140d"><span class="__cf_email__" data-cfemail="80d7e5f3f3aed2eff5f3e5c0e6e1e1aee7eff6">[email protected]</span></a>; or
--Angie Kostopoulos, Composite Technical Specialist, ACE-116C, Chicago 
Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des 
Plaines, Illinois 60018; telephone: (847) 294-7426; facsimile: (847) 
294-7834; e-mail: <a href="/cdn-cgi/l/email-protection#266350474841434a4f47086d495552495649534a49556660474708414950"><span class="__cf_email__" data-cfemail="397c4f58575e5c5550581772564a4d5649564c55564a797f5858175e564f">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    What events have caused this AD? The Cirrus Design Corporation 
(CDC) performed dynamic seat testing on Models SR20 and SR22 airplanes. 
CDC found that, under emergency landing dynamic loads, the crew seats 
may fold forward at less than the 26 g required by 14 CFR Section 
23.562(b)(2).
    What is the potential impact if FAA took no action? If not 
prevented, the crew seats folding forward during emergency landing 
dynamic loads could result in occupant injury.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to certain Cirrus Design Corporation 
(CDC) Models SR20 and SR22 airplanes. This proposal was published in 
the Federal Register as a notice of proposed rulemaking (NPRM) on 
January 13, 2005 (70 FR 2370). The NPRM proposed to measure and adjust 
the crew seat break-over bolts and to replace the crew seat recline 
locks on both crew seats. Since issuing the earlier NPRM, FAA received 
and evaluated new service information that increases the serial number 
effectivity of the earlier NPRM. Since the change imposed an additional 
burden over that proposed in the earlier NPRM, we reopened the comment 
period to allow the public additional time to comment on the proposed 
AD. The supplemental NPRM was published in the Federal Register on June 
9, 2005 (70 FR 33724).

Comments

    Was the public invited to comment? We again provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the supplemental NPRM or on the determination of the cost 
to the public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 1,501 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? CDC will provide warranty credit for service 
bulletins SB A2X-25-08, dated June 22, 2004, and SB 2X-25-06 R4, dated 
May 5, 2005. This AD will not have a labor or parts cost for the owner 
or operator.

Authority for This Rulemaking

    What authority does FAA have for issuing this rulemaking action? 
Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106 describes the 
authority of the FAA

[[Page 52000]]

Administrator. Subtitle VII, Aviation Programs, describes in more 
detail the scope of the agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this AD.

Regulatory Findings

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD will not have a substantial direct effect on the States, on the 
relationship between the national government and the States, or on the 
distribution of power and responsibilities among the various levels of 
government.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD (and 
other information as included in the Regulatory Impact) and placed it 
in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2004-19694; Directorate Identifier 2004-CE-41-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2005-17-19 Cirrus Design Corporation: Amendment 39-14240; Docket No. 
FAA-2004-19694; Directorate Identifier 2004-CE-41-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on October 13, 2005.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
(1) SR20...............................  1005 through 1455.
(2) SR22...............................  0002 through 1044.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of discovering that the crew seats, 
under emergency landing dynamic loads, may fold forward at less than 
26 g required by the regulations, 14 Code of Federal Regulations 
(CFR) Section 23.562(b)(2). The actions specified in this AD are 
intended to prevent the crew seats from folding forward during 
emergency landing dynamic loads with consequent occupant injury.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

 
------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
(1) For Models SR20, serial       Within 50 hours     Follow Cirrus
 numbers 1005 through 1423, and    time-in-service     Design
 SR22, serial numbers 0002         (TIS) or within     Corporation Alert
 through 0972, do the following    180 days,           Service Bulletin
 actions:                          whichever occurs    SB A2X-25-08,
(i) Move the lower portion of      first after         dated June 22,
 the crew seat upholstery upward   October 13, 2005    2004.
 to expose the seat frame and      (the effective
 locking mechanism. Measure the    date of this AD).
 clearance between the break-
 over bolt and the seat frame
 for a clearance that meets the
 requirements in the service
 bulletin.
(ii) If the clearance does not
 meet that specified in the
 service bulletin, do the crew
 seat break-over bolt adjustment
 and re-cover the crew seat
 frame and locking mechanism
 with the upholstery.
(iii) If the clearance does meet
 that specified in the service
 bulletin, re-cover the crew
 seat frame and locking
 mechanism.
(iv) Repeat the above actions
 for the opposite crew seat.

[[Page 52001]]

 
(2) For Models SR20, serial       Within 50 hours     Follow Cirrus
 numbers 1005 through 1455, and    TIS or within 180   Design
 SR22, serial numbers 0002         days, whichever     Corporation
 through 1044, do the following    occurs first        Service Bulletin
 actions:                          after October 13,   SB 2X-25-06 R4,
(i) Identify whether the recline   2005 (the           revised May 5,
 lock is secured with two bolts    effect9ve date of   2005.
 or three bolts.                   this AD).
(ii) If the recline locks are
 secured with two bolts, remove
 the existing recline locks and
 replace with the new recline
 locks kit, kit number 70084-001.
(iii) If the recline locks are
 secured with three bolts,
 remove existing recline locks
 and replace with the new
 recline locks kit, kit number
 70084-002.
(iv) Check break-over pin
 alignment and adjust as
 necessary.
(v) Check that the locks engage
 with the break-over bolts with
 the seat in the full recline
 position. If full seat recline
 is not possible or difficult to
 engage, grinding of the lower
 aft seat frame is necessary.
(vi) Repeat the above actions
 for the opposite crew seat.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Chicago Aircraft 
Certification Office, FAA. For information on any already approved 
alternative methods of compliance, please contact one of the 
following:
    (1) Wess Rouse, Small Airplane Project Manager, ACE-117C; 
Chicago Aircraft Certification Office, 2300 East Devon Avenue, Roon 
107, Des Plaines, Illinois 60018; telephone: (847) 294-8113; 
facsimile: (847) 294-7834; e-mail: <a href="/cdn-cgi/l/email-protection" class="__cf_email__" data-cfemail="1b4c7e68683549746e687e5b5d7a7a357c746d">[email protected]</a>; or
    (2) Angie Kostopoulos, Aerospace Engineer, ACE-116C, Chicago 
Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des 
Plaines, Illinois 60018; telephone: (847) 294-7426; facsimile: (847) 
294-7834; e-mail: <a href="/cdn-cgi/l/email-protection#064370676861636a6f67284d697572697669736a69754640676728616970"><span class="__cf_email__" data-cfemail="2d685b4c434a4841444c0366425e59425d425841425e6d6b4c4c034a425b">[email protected]</span></a>.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Cirrus Design Corporation Alert Service Bulletin SB 
A2X-25-08, dated June 22, 2004; and Service Bulletin SB 2X-25-06 R4, 
revised May 5, 2005. The Director of the Federal Register approved 
the incorporation by reference of these service bulletins in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of 
this service information, contact Cirrus Design Corporation, 4515 
Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727-2737; 
Internet address: http://www.cirrusdesign.com. To review copies of 
this service information, go to the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 
741-6030. To view the AD docket, go to the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on 
the Internet at http://dms.dot.gov. The docket number is FAA-2004-
19694; Directorate Identifier 2004-CE-41-AD.

    Issued in Kansas City, Missouri, on August 19, 2005.
Terry L. Chasteen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16980 Filed 8-31-05; 8:45 am]
BILLING CODE 4910-13-P


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