[Federal Register Volume 67, Number 237 (Tuesday, December 10, 2002)]
[Rules and Regulations]
[Pages 75809-75812]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-30685]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-31-AD; Amendment 39-12973; AD 2002-24-08]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Models SR20 
and SR22 Airplanes

AGENCY: Federal Aviation Administration, DOT

ACTION: Final rule.

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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 2002-
05-05, which currently applies to certain Cirrus Design Corporation 
(Cirrus) Models SR20 and SR22 airplanes. AD 2002-05-05 currently 
requires you to incorporate temporary operating limitations into the 
Limitation Section of the airplane flight manual (AFM) for certain 
affected airplanes and install a cable clamp external to the cone 
adapter on the Cirrus Airplane Parachute System (CAPS) activation cable 
for all affected airplanes. AD 2002-05-05 resulted from a report from 
the manufacturer that certain CAPS may not activate in an emergency 
situation. This AD is the result of the manufacturer redesigning the 
CAPS activation system. This AD requires you to modify the CAPS 
activation system. The actions specified by this AD are intended to 
prevent failure of the CAPS activation system in an emergency 
situation. Failure of this system could result in occupant injury and/
or loss of life and loss of aircraft.

DATES: This AD becomes effective on January 24, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
January 24, 2003.

ADDRESSES: You may get the service information referenced in this AD 
from Cirrus Design Corporation, 4515 Taylor Circle, Duluth, MN 55811; 
telephone: (218) 727-2737. You may view this information at the Federal 
Aviation Administration (FAA), Central Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-CE-31-AD, 901 Locust, Room 
506, Kansas City, Missouri 64106; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Aerospace 
Engineer, FAA, Chicago ACO, 2300 East Devon Avenue, Des Plaines, IL 
60018; telephone: (847) 294-7135; facsimile: (847) 294-7834.

SUPPLEMENTARY INFORMATION: 

Discussion

    Has FAA taken any action to this point? The FAA received a report 
from the type certificate holder that a condition exists that could 
cause the Cirrus Airplane Parachute System (CAPS) installed on certain 
Cirrus Design Corporation (Cirrus) Model SR20 and SR22 airplanes not to 
activate in the event of an emergency. Ballistic Recovery Systems 
(BRS), the supplier of the CAPS, discovered the condition during a 
supplemental type certificate (STC) certification test of the same unit 
on another airplane.
    Investigation revealed that the rocket cone could allow for 
variance in the internal diameter at the threaded end of the rocket 
cone. This variance could result in the retaining nut internal to the 
cone adapter not being fully secured on the affected parachutes. When 
the igniter end of the cable housing is unsecured, the cable will not 
pull the igniter pin free to release the parachute.
    Section 23.221 of the Federal Aviation Regulations (14 CFR 23.221) 
requires that single-engine, normal category airplanes demonstrate 
compliance with either the one-turn spin recovery or the spin-resistant 
requirements. The airplane, for spin recovery compliance, must recover 
from a one-turn spin or a three-second spin, whichever takes longer, in 
not more than one additional turn after the controls have been applied 
for recovery. The Cirrus SR20/SR22 are not certificated to meet the 
spin recovery requirements or spin resistant requirements of 14 CFR 
23.221. Instead, Cirrus installed Cirrus Airplane

[[Page 75810]]

Parachute System (CAPS) that was FAA-approved as part of the SR20/SR22 
type design.
    Possible failure of the CAPS activation system in an emergency 
situation caused us to issue AD 2002-05-05, Amendment 39-12673 (67 FR 
11220, March 13, 2002). AD 2002-05-05 requires the following:

--Incorporating temporary operating limitations into the Limitation 
Section of the airplane flight manual (AFM) for the airplanes with a 
CAPS that incorporates the process change; and
--Installing a cable clamp external to the cone adapter on the CAPS 
activation cable (as terminating action for the AFM requirements).

    What has happened since AD 2002-05-05 to initiate this action? 
After further testing, Cirrus has made design changes to the whole CAPS 
activation system that now eliminate possible failure of the CAP 
activation system. Incorporation of the design changes eliminates the 
need for the actions of AD 2002-05-05.
    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 Models SR20 and SR22 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on August 29, 2002 (67 FR 55357). 
The NPRM proposed to supersede AD 2002-05-05 with a new AD that would 
require you to replace the CAPS handle access cover, replace the CAPS 
activation handle bracket, and replace the CAPS activation cable.
    Was the public invited to comment? The FAA encouraged interested 
persons to participate in the making of this amendment. We did not 
receive any comments on the proposed rule or on our determination of 
the cost to the public.

FAA's Determination

    What is FAA's final determination on this issue? After careful 
review of all available information related to the subject presented 
above, we have determined that air safety and the public interest 
require the adoption of the rule as proposed except for minor editorial 
corrections. We have determined that these minor corrections:

--Provide 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.

Cost Impact

    How many airplanes does this AD impact? We estimate that this AD 
affects 391 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to accomplish the 
replacement of the CAPS handle access cover:

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                                                          Total cost
                Labor cost                  Parts cost   per airplane         Total cost on U.S. operators
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1 workhour x $60 per hour = $60..........          $19           $79   $79 x 391 = $30,889.
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    We estimate the following costs to accomplish the replacement of 
the CAPS activation handle bracket:

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                                                          Total cost
                Labor cost                  Parts cost   per airplane         Total cost on U.S. operators
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2 workhours x $60 per hour = $120........           $7          $127   $127 x 391 = $49,657.
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    We estimate the following costs to accomplish the replacement of 
the CAPS activation cable:

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                                                          Total cost
                Labor cost                  Parts cost   per airplane         Total cost on U.S. operators
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3 workhours x $60 per hour = $180........         $320          $500   $500 x 391 = $195,500.
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    We summarize the following estimated costs to accomplish the 
modification to the CAPS activation system:

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                                            Total parts   Total cost
             Total labor cost                  cost      per airplane         Total cost on U.S. operators
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6 workhours x $60 per hour = $360........         $346          $706   $706 x 391 = $276,046.
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    The manufacturer will provide warranty credit for labor and parts 
to the extent noted under WARRANTY INFORMATION in each previously-
referenced service bulletin.

Compliance Time of This AD

    What is the compliance time of this AD? The compliance time of this 
AD is ``within 90 days after the effective date of this AD, unless 
already accomplished.''
    Why is the compliance time presented in calendar time instead of 
hours time-in-service (TIS)? Failure of the CAPS is only unsafe during 
airplane operation; this unsafe condition is not a result of the number 
of times the airplane is operated. The chance of this situation 
occurring is the same for an airplane with 10 hours time-in-service 
(TIS) as it is for an airplane with 500 hours TIS. For this reason, the 
FAA has determined that a compliance based on calendar time will be 
utilized in this AD in order to assure that the unsafe condition is 
addressed on all airplanes in a reasonable time period.

Regulatory Impact

    Does this AD impact various entities? The regulations adopted 
herein 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. Therefore, it is determined that this final rule does not 
have federalism implications under Executive Order 13132.
    Does this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this

[[Page 75811]]

action (1) is not a ``significant regulatory action'' under Executive 
Order 12866; (2) is not a ``significant rule'' under 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. A copy of the final evaluation prepared for 
this action is contained in the Rules Docket. A copy of it may be 
obtained by contacting the Rules Docket at the location provided under 
the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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

    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]

    2. FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2002-05-05, Amendment 39-12673 (67 FR March 13, 2002), and by adding a 
new AD to read as follows:

2002-24-08 Cirrus Design Corporation: Amendment 39-12973; Docket No. 
2002-CE-31-AD.
    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

------------------------------------------------------------------------
                Model                            Serial numbers
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SR20.................................  1005 through 1195.
SR22.................................  0002 through 0209.
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    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent failure of the Cirrus Airplane 
Parachute System (CAPS) activation system in an emergency situation. 
Failure of this system could result in occupant injury and/or loss 
of life and loss of aircraft.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
             Actions                  Compliance          Procedures
------------------------------------------------------------------------
Modify the Cirrus Airplane        Within the next 90  In accordance with
 Parachute System (CAPS) by        days after          the service
 replacing the CAPS handle         January 24, 2003    information
 access cover, the CAPS            (the effective      specified in
 activation handle bracket, and    date of this AD),   paragraph (e) of
 the CAPS activation cable with    unless already      this AD.
 parts of improved design.         accomplished.
------------------------------------------------------------------------

    (e) What service information should I use to accomplish the 
actions required in paragraph (d) of this AD: Use the service 
bulletins specified below, as applicable:
    (1) Cirrus Service Bulletin SB 20-95-03, Issued: June 10, 2002;
    (2) Cirrus Service Bulletin SB 20-95-04, Issued: July 10, 2002;
    (3) Cirrus Service Bulletin SB 20-95-05, Issued: July 10, 2002; 
or Cirrus Service Bulletin SB 20-95-05, Rev 1: dated August 14, 
2002;
    (4) Cirrus Service Bulletin SB 22-95-03, Issued: June 10, 2002;
    (5) Cirrus Service Bulletin SB 22-95-04, Issued: July 10, 2002; 
and
    (6) Cirrus Service Bulletin SB 22-95-05, Issued: July 10, 2002; 
or Cirrus Service Bulletin SB 22-95-05, Rev 1: dated August 14, 
2002.
    Note 1: Cirrus Service Bulletin SB 20-95-03, Issued: June 10, 
2002, on page 2 of 2, includes an incorrect reference to SB 22-95-03 
in step 4. The correct reference should be to SB 20-95-03.
    Note 2: Cirrus Service Bulletin SB 20-95-05, Issued: July 10, 
2002, on page 9 of 16, includes an incorrect reference to SB 22-95-
05 in step 15. The correct reference should be to SB 20-95-05.
    (f) Can I comply with this AD in any other way?
    (1) You may use an alternative method of compliance or adjust 
the compliance time if:
    (i) Your alternative method of compliance provides an equivalent 
level of safety; and
    (ii) The Manager, Chicago Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Chicago ACO.
    (2) Alternative methods of compliance approved in accordance 
with AD 2002-05-05, which is superseded by this AD, are not approved 
as alternative methods of compliance with this AD.
    Note 3: This AD applies to each airplane identified in paragraph 
(a) of this AD, regardless of whether it has been modified, altered, 
or repaired in the area subject to the requirements of this AD. For 
airplanes that have been modified, altered, or repaired so that the 
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of 
compliance in accordance with paragraph (f) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if you have not eliminated the unsafe condition, specific 
actions you propose to address it.
    (g) Where can I get information about any already-approved 
alternative methods of compliance? Contact Gregory J. Michalik, 
Aerospace Engineer, FAA, Chicago ACO, 2300 East Devon Avenue, Des 
Plaines, IL 60018; telephone: (847) 294-7135; facsimile: (847) 294-
7834.
    (h) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (i) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Cirrus Service Bulletin SB 20-95-03, Issued: June 10, 2002; 
Cirrus Service Bulletin SB 20-95-04, Issued: July 10, 2002; Cirrus 
Service Bulletin SB 20-95-05, Issued: July 10, 2002; Cirrus Service 
Bulletin SB 20-95-05, Rev 1: dated August 14, 2002; Cirrus Service 
Bulletin SB 22-95-03, Issued: June 10, 2002; Cirrus Service Bulletin 
SB 22-95-04, Issued: July 10, 2002; Cirrus Service Bulletin SB 22-
95-05, Issued: July 10, 2002; and Cirrus Service Bulletin SB 22-95-
05, Rev 1: dated August 14, 2002. The Director of the Federal 
Register approved this incorporation by reference under 5 U.S.C. 
552(a) and 1 CFR part 51. You may get copies from Cirrus Design

[[Page 75812]]

Corporation, 4515 Taylor Circle, Duluth, MN 55811; telephone: (218) 
727-2737. You may view copies at the FAA, Central Region, Office of 
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., Suite 700, Washington, DC.
    (j) Does this AD action affect any existing AD actions? This 
amendment supersedes AD 2002-05-05, Amendment 39-12673.
    (k) When does this amendment become effective? This amendment 
becomes effective on January 24, 2003.

    Issued in Kansas City, Missouri, on November 26, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-30685 Filed 12-9-02; 8:45 am]
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