[Federal Register Volume 71, Number 181 (Tuesday, September 19, 2006)]
[Rules and Regulations]
[Pages 54755-54757]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-15432]



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  Federal Register / Vol. 71, No. 181 / Tuesday, September 19, 2006 / 
Rules and Regulations  

[[Page 54755]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24254; Directorate Identifier 2006-CE-24-AD; 
Amendment 39-14767; AD 2006-19-10]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Models SR20 
and SR22 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) that 
supersedes AD 2005-17-19, which applies to certain Cirrus Design 
Corporation (CDC) Models SR20 and SR22 airplanes. AD 2005-17-19 
currently requires you to measure and adjust the crew seat break-over 
bolts and to replace the crew seat recline locks on both crew seats. 
Since we issued AD 2005-17-19, CDC developed new crew seat break-over 
pins to replace the old crew seat break-over bolts. Consequently, this 
AD retains the action from AD 2005-17-19 of replacing the crew seat 
recline locks on both seats and adds the action of replacing the crew 
seat break-over bolts with the new crew seat break-over pins on both 
seats. 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 24, 2006.
    As of October 24, 2006 the Director of the Federal Register 
approved the incorporation by reference of Cirrus Design Corporation 
Service Bulletin SB 2X-25-17 R1, Issued: December 15, 2005, Revised: 
January 20, 2006.
    As of October 13, 2005 (70 FR 51999, September 1, 2005), the 
Director of the Federal Register previously approved the incorporation 
by reference of Cirrus Design Corporation Service Bulletin SB 2X-25-06 
R4, Issued: August 13, 2004; Revised: May 5, 2005.

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 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-24254; Directorate 
Identifier 2006-CE-24-AD.

FOR FURTHER INFORMATION CONTACT:
     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; e-mail: [email protected]; 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: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On April 25, 2006, 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 CDC Models SR20 and SR22 airplanes. This 
proposal was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on May 2, 2006 (71 FR 25785). The NPRM proposed to 
supersede AD 2005-17-19, Amendment 39-14240 (70 FR 51999, September 1, 
2005), retain the action of replacing the crew seat recline locks on 
both seats, and add the action of replacing the crew seat break-over 
bolts with the new crew seat break-over pins on both seats.

Comments

    We provided the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and FAA's response to each comment:

Comment Issue

    We received one comment from Jenna Deutschmann. The commenter 
supports the AD but believes the manufacturer should be liable to 
correct and pay for the problem since it involves a malfunction on 
their part.
    The FAA issues ADs to correct unsafe conditions. We do not identify 
who will pay for the parts or labor. In this case, CDC will provide 
warranty credit to the extent noted in Service Bulletins SB 2X-25-17 
R1, Issued: December 15, 2005, Revised: January 20, 2006; and SB 2X-25-
06 R4, Issued: August 13, 2004, Revised: May 5, 2005.
    We are not changing the AD as a result of this comment.

Conclusion

    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.

Costs of Compliance

    We estimate that this AD affects 2,230 airplanes in the U.S. 
registry.
    We estimate the following costs to do the required replacements:

[[Page 54756]]



----------------------------------------------------------------------------------------------------------------
                                         Model number and serial                  Total cost per   Total cost on
              Labor cost                         number             Parts cost       airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Replacement of the recline locks: 1     Model SR20, serial                   $83            $163         $41,565
 work-hour x $80 per hour = $80.         numbers (S/N) 1148
                                         through 1152 and 1206
                                         through 1455.
Replacement of the recline locks: 1     Model SR20, S/N 1005                 165             245          48,020
 work-hour x $80 per hour = $80.         through 1147 and 1153
                                         through 1205.
Replacement of the recline locks: 1     Model SR22, S/N 0002                  89             169         176,267
 work-hour x $80 per hour = $80.         through 1044.
Replacement of the crew seat break-     Model SR20, S/N 1005                  33             113         262,273
 over pins: 1 work-hour x $80 per hour   through 1600 and Model
 = $80.                                  SR22, S/N 0002 through
                                         1727.
----------------------------------------------------------------------------------------------------------------


    Note: CDC will provide warranty credit to the extent noted in 
Service Bulletins SB 2X-25-17 R1, Issued: December 15, 2005, 
Revised: January 20, 2006; and SB 2X-25-06 R4, Issued: August 13, 
2004, Revised: May 5, 2005.

Authority for This Rulemaking

    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 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

    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.
    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 Evaluation) 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-2006-24254; Directorate Identifier 2006-CE-24-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 removing Airworthiness Directive (AD) 
2005-17-19, Amendment 39-14240 (70 FR 51999, September 1, 2005), and by 
adding the following new AD:

2006-19-10 Cirrus Design Corporation: Amendment 39-14767; Docket No. 
FAA-2006-24254; Directorate Identifier 2006-CE-24-AD.

Effective Date

    (a) This AD becomes effective on October 24, 2006.

Affected ADs

    (b) This AD supersedes AD 2005-17-19, Amendment 39-14240.

Applicability

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

------------------------------------------------------------------------
             Model                  Serial Nos.
--------------------------------------------------
(1) SR20.......................  1005 through
                                  1600.
(2) SR22.......................  0002 through
                                  1727.
------------------------------------------------------------------------

Unsafe Condition

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

Compliance

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

----------------------------------------------------------------------------------------------------------------
               Actions                             Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(1) For Model SR20, serial numbers    Within 50 hours time-in-service       Follow Cirrus Design Corporation
 (S/Ns) 1005 through 1600, and Model   (TIS) or within 180 days, whichever   Service Bulletin SB 2X-25-17 R1,
 SR22, S/Ns 0002 through 1727, do      occurs first, after October 24,       Issued: December 15, 2005, Revised:
 the following actions:                2006 (the effective date of this      January 20, 2006.
(i) At the lower back of the crew      AD), unless already done.
 seat, release the reclosable
 fasteners to expose the lower seat
 frame.
(ii) Replace the crew seat break-
 over bolt with the new crew seat
 break-over pin, part number 17063-
 002.
(iii) Recover the seat frame,
 refastening the reclosable
 fasteners.
(iv) Inspect the crew seat.
(v) Repeat the above actions for the
 opposite crew seat.

[[Page 54757]]

 
(2) For Models SR20, S/Ns 1005        Within 50 hours TIS or within 180     Follow Cirrus Design Corporation
 through 1455, and SR22, S/Ns 0002     days, whichever occurs first after    Service Bulletin SB 2X-25-06 R4,
 through 1044, do the following        October 13, 2005 (the effective       Issued: August 13, 2004, Revised:
 actions:                              date of AD 2005-17-19), unless        May 5, 2005.
(i) Identify whether the recline       already done.
 lock is secured with two bolts or
 three bolts.
    (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.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Chicago Aircraft Certification Office, FAA, 
ATTN: 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; e-mail: [email protected]; 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: [email protected], have the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19.

Related Information

    (g) None.

Material Incorporated by Reference

    (h) You must do the actions required by this AD following the 
instructions in Cirrus Design Corporation Service Bulletins SB 2X-
25-17 R1, Issued: December 15, 2005, Revised: January 20, 2006; and 
SB 2X-25-06 R4, Issued: August 13, 2004; Revised: May 5, 2005.
    (1) As of October 24, 2006, the Director of the Federal Register 
approved the incorporation by reference of Cirrus Design Corporation 
Service Bulletin SB 2X-25-17 R1, Issued: December 15, 2005, Revised: 
January 20, 2006 under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On October 13, 2005 (70 FR 51999, September 1, 2005), the 
Director of the Federal Register previously approved the 
incorporation by reference of Cirrus Design Corporation Service 
Bulletin SB 2X-25-06 R4, Issued: August 13, 2004, Revised: May 5, 
2005.
    (3) 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 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-24254; Directorate 
Identifier 2006-CE-24-AD.

    Issued in Kansas City, Missouri, on September 8, 2006.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-15432 Filed 9-18-06; 8:45 am]
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