[Federal Register Volume 70, Number 102 (Friday, May 27, 2005)]
[Rules and Regulations]
[Pages 30621-30624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-10536]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21315; Directorate Identifier 2005-NM-090-AD; 
Amendment 39-14106; AD 2005-11-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) Airplanes Modified by Supplemental Type Certificate (STC) SA4900SW

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), 
and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes modified 
by STC SA4900SW. This AD requires revising the airplane flight manual 
(AFM) to require repetitive visual checks of the microphone jack 
assemblies on both control columns to detect damage that may interfere 
with movement of the control column. This AD also requires modification 
of the microphone jack assembly, related investigative actions, and 
corrective actions if necessary, which allows the AFM revision to be 
removed from the AFM. This AD is prompted by a report of a rejected 
take-off and subsequent runway overrun due to restricted movement of 
the co-pilot's control column, which resulted in collapse of the nose 
landing gear and consequent damage of the forward fuselage. We are 
issuing this AD to prevent a damaged microphone jack assembly from 
interfering with movement of the control column, which could result in 
loss of control of the airplane.

DATES: Effective May 27, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of May 
27, 2005.
    We must receive comments on this AD by July 26, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Raytheon 
Aircraft Company, P.O. Box 3356, Little Rock, Arkansas 72203; or 
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station 
Centre-ville, Montreal, Quebec H3C 3G9, Canada.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21315; the directorate identifier for this docket is 
2005-NM-090-AD.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
(DMS) receives them.

FOR FURTHER INFORMATION CONTACT: John Hardie, Aerospace Engineer, 
Special Certification Office, ASW-190, 2601 Meacham Blvd., Fort Worth, 
Texas 76137-4298; telephone (817) 222-5194; fax (817) 222-5785.

SUPPLEMENTARY INFORMATION: We have received a report indicating that a 
Bombardier Model CL-600-1A11 (CL-600) airplane experienced a rejected 
take-off and subsequently overran the runway. The nose landing gear 
collapsed, and the forward fuselage was damaged as a result of the 
incident. The

[[Page 30622]]

flightcrew reported that, when they attempted to take off, the control 
column would not move aft beyond the neutral position. Investigation 
revealed that the microphone jack assembly installed on the co-pilot's 
control column was bent downward, which restricted the aft movement of 
the control column. This condition, if not corrected, could result in 
loss of control of the airplane.
    The microphone jack assembly on the affected airplane was installed 
incidental to Supplemental Type Certificate (STC) SA4900SW. Therefore, 
we find that all Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 
(CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) airplanes 
modified by that STC may be subject to the same unsafe condition.

Relevant Service Information

    Raytheon has issued Service Bulletin SB 23-3727, dated May 2005. 
The service bulletin describes procedures for modifying the microphone 
jack assembly, and performing related investigative actions and 
corrective actions if necessary. The related investigative actions 
include performing a general visual inspection of the cover of the 
pilot's and co-pilot's control columns for cracking around the existing 
fastener holes for the microphone bracket assembly; a Non-Destructive 
Test (NDT) of the microphone jack assembly for any damage, including 
cracks; and a measurement of the distance between existing fastener 
holes and the location of the new fastener holes. (The service bulletin 
specifies various alternatives for performing the NDT including dye-
penetrant, ultrasonic, and eddy current methods.) The service bulletin 
specifies to contact Raytheon if any cracking or damage is found, or if 
the minimum distance between existing and new fastener holes is below a 
certain limit. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.
    Bombardier Advisory Wire AW600-00-2247, Revision 2, dated March 24, 
2005, also addresses the subject of this AD. Section 3.0, Action, of 
the Advisory Wire recommends a repetitive inspection to ``verify the 
security of the installation of the [microphone jack] receptacle.'' The 
intent of this inspection is identical to that of the repetitive visual 
checks specified in the airplane flight manual (AFM) revision required 
by paragraph (f) of this AD.

FAA's Determination and Requirements of This AD

    These airplane models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
Sec.  21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. We have evaluated all 
pertinent information, and determined that we need to issue an AD for 
products of this type design that are modified by STC SA4900SW and 
certificated for operation in the United States.
    Therefore, we are issuing this AD to prevent a damaged microphone 
jack assembly from interfering with movement of the control column, 
which could result in loss of control of the airplane. This AD requires 
revising the AFM to require repetitive visual checks of the microphone 
jack assemblies on both control columns to detect damage that may 
interfere with movement of the control column. We have determined that 
the checks specified in the AFM revision must be performed by the 
flightcrew because of the possibility that damage to the microphone 
jack assembly may occur between the time an inspection is performed by 
maintenance personnel and the time the flightcrew enters the flight 
deck to prepare for the flight. (For example, a member of the 
flightcrew may inadvertently step on the microphone jack assembly, 
causing it to bend.) We have determined that it is possible for the 
flightcrew to perform the visual checks because the checks do not 
require tools, precision measuring equipment, training, or pilot 
logbook endorsements, or the use of or reference to technical data that 
are not contained in the body of the AD.
    This AD also requires accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the AD and Service Information,'' after which the 
AFM revision may be removed from the AFM.

Differences Between the AD and Service Information

    Although the Raytheon service bulletin specifies that operators may 
contact the manufacturer for disposition of certain repair conditions, 
this proposed AD would require operators to repair those conditions 
according to a method approved by the FAA.
    The Raytheon service bulletin recommends that the modification of 
the microphone jack assembly be accomplished before the next flight or 
within 15 days from receipt of the service bulletin, whichever is 
first. This AD specifies a compliance time for the modification of 15 
flight hours or 15 days after the effective date of the AD, whichever 
is first. In developing an appropriate compliance time for this AD, we 
considered the manufacturer's recommendation, the degree of urgency 
associated with the subject unsafe condition, and the average 
utilization of the affected fleet. We also considered the 
recommendation for repetitive inspections in Bombardier Advisory Wire 
AW600-00-2247, Revision 2. (These repetitive inspections are similar to 
the repetitive visual checks specified in the AFM revision required by 
this AD.) In light of all of these factors, we find that, for the 
modification, a compliance time of 15 flight hours or 15 days, 
whichever is earlier, represents an appropriate interval of time for 
affected airplanes to continue to operate without compromising safety, 
provided that the microphone jack assembly is checked for damage before 
every flight. We find that this compliance time should provide an 
opportunity for affected operators to accomplish the modification 
without unnecessarily grounding airplanes. This difference has been 
coordinated with Raytheon.
    Although the Accomplishment Instructions of the referenced service 
bulletin describe procedures for reporting accomplishment of the 
service bulletin, this AD does not require that action. We do not need 
this information from operators.

Clarification of Service Bulletin Note

    The Raytheon service bulletin includes a note in the Accomplishment 
Instructions to inform operators to contact Raytheon ``should any 
difficulty be encountered'' in accomplishing the service bulletin. We 
have included Note 3 in this proposed AD to clarify that any deviation 
from the instructions provided in the service bulletin must be approved 
as an alternative method of compliance under paragraph (i) of this 
proposed AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment;

[[Page 30623]]

however, we invite you to submit any relevant written data, views, or 
arguments regarding this AD. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2005-21315; Directorate 
Identifier 2005-NM-090-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the AD. We will consider all 
comments received by the closing date and may amend the AD in light of 
those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of our docket 
web site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You can review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you can visit 
http://dms.dot.gov.

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 
rulemaking action.

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 the regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

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 FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-11-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-14106. 
Docket No. FAA-2005-21315; Directorate Identifier 2005-NM-090-AD.

Effective Date

    (a) This AD becomes effective May 27, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Bombardier Model CL-600-1A11 (CL-600), 
CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-
604) airplanes; certificated in any category; modified by STC 
SA4900SW; excluding serial number (S/N) 3025; and including but not 
limited to the serial numbers listed in Table 1 of this AD.

                      Table 1.--Known Affected S/Ns
------------------------------------------------------------------------
                 Model                              Known S/Ns
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CL-600-1A11 (CL-600)...................  1054, 1059, 1069, 1071, 1080
CL-600-2A12 (CL-601)...................  3012, 3013, 3034, 3045, 3050,
                                          3051, 3061, 3065
CL-600-2B16 (CL-601-3A, CL-601-3R, and   5012, 5046, 5060
 CL-604).
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by a report of a rejected take-off and 
subsequent runway overrun due to restricted movement of the control 
column, which resulted in collapse of the nose landing gear and 
consequent damage of the forward fuselage. The FAA is issuing this 
AD to prevent a damaged microphone jack assembly from interfering 
with movement of the control column, which could result in loss of 
control of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Airplane Flight Manual (AFM) Revision

    (f) Within 5 days after the effective date of this AD, revise 
the Limitations and Normal Procedures section of the AFM to contain 
the following information. This may be done by inserting a copy of 
this AD in the AFM.

``Before every flight, perform a visual check of the microphone jack 
assembly on the pilot's and co-pilot's control column to detect 
damage that may interfere with movement of the control column, 
including downward bending of the receptacle. This check must be 
performed by the flightcrew. Any damage that may interfere with the 
movement of the control column must be repaired before further 
flight.''


    Note 1: Bombardier Advisory Wire AW600-00-2247, Revision 2, 
dated March 24, 2005, provides additional information on damaged 
microphone jack assemblies and interference of damaged assemblies 
with movement of the control column.

Modification

    (g) At the applicable compliance time specified in paragraph 
(g)(1) or (g)(2) of this AD, modify the microphone jack assembly and 
do all related investigative actions and applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Raytheon Service Bulletin SB 23-3727, dated May 2005, except as 
provided by paragraph (h) of this AD. Once this modification is 
complete, the AFM revision required by

[[Page 30624]]

paragraph (f) of this AD may be removed from the AFM. Although the 
service bulletin specifies reporting accomplishment of the service 
bulletin to the manufacturer, this AD does not require that action.
    (1) If damage that may interfere with the movement of the 
control column is found during any visual check performed in 
accordance with the AFM revision required by paragraph (f) of this 
AD: Before further flight.
    (2) If no damage that may interfere with the movement of the 
control column is found during any visual check performed in 
accordance with the AFM revision required by paragraph (f) of this 
AD: Within 15 days or 15 flight hours after the effective date of 
this AD, whichever is first.

Repairs

    (h) If any cracking is found during any inspection required by 
this AD, or if the distance between existing and new fastener holes 
is less than the limit specified in Raytheon Service Bulletin SB 23-
3727, dated May 2005, and the service bulletin specifies contacting 
Raytheon for appropriate action: Before further flight, repair the 
cracking or do other applicable corrective actions according to a 
method approved by the Manager, Special Certification Office, ASW-
190, FAA. For a repair or corrective action method to be approved by 
the Manager, Special Certification Office, as required by this 
paragraph, the Manager's approval letter must specifically refer to 
this AD.

    Note 2: A note in the Accomplishment Instructions of the 
Raytheon service bulletin instructs operators to contact Raytheon if 
any difficulty is encountered in accomplishing the service bulletin. 
However, any deviation from the instructions provided in the service 
bulletin must be approved as an alternative method of compliance 
(AMOC) under paragraph (i) of this AD.

AMOCs

    (i) The Manager, Special Certification Office, ASW-190, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (j) Bombardier Advisory Wire AW600-00-2247, Revision 2, dated 
March 24, 2005, addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use Raytheon Service Bulletin SB 23-3727, dated May 
2005, to perform the actions that are required by this AD, unless 
the AD specifies otherwise. The Director of the Federal Register 
approves the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
the service information, contact Raytheon Aircraft Company, P.O. Box 
3356, Little Rock, Arkansas 72203; or Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, 
Quebec H3C 3G9, Canada. To view the AD docket, go to the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street SW, room PL-401, Nassif Building, Washington, DC. To review 
copies of the service information, go to the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 20, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-10536 Filed 5-26-05; 8:45 am]
BILLING CODE 4910-13-P