[Federal Register Volume 71, Number 133 (Wednesday, July 12, 2006)]
[Proposed Rules]
[Pages 39237-39241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-10913]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22559; Directorate Identifier 2005-NM-076-AD]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Bombardier Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes. The existing AD currently 
requires repetitive inspections for cracks, sealant damage, and 
corrosion of the main fittings of the main landing gear (MLG), and 
corrective actions if necessary. This proposed AD would reduce the 
compliance times for inspecting certain low-utilization airplanes, and 
provide a terminating action for the repetitive inspections. This 
proposed AD results from a report of a cracked main fitting of the MLG. 
We are proposing this AD to detect and correct fatigue cracking of the 
main fitting of the MLG and consequent failure of the main fitting, 
which could result in the collapse of the MLG.

DATES: We must receive comments on this proposed AD by August 11, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed 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.
    Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, 
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7302; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-22559; 
Directorate Identifier 2005-NM-076-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the

[[Page 39238]]

proposed 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 proposed 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.

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.

Discussion

    On September 27, 2004, we issued AD 2004-20-09, amendment 39-13814 
(69 FR 59790, October 6, 2004), for certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. That AD requires 
repetitive inspections for cracks, sealant damage, and corrosion of the 
main fittings of the main landing gear (MLG), and corrective actions if 
necessary. That AD resulted from a report of a cracked main fitting of 
the MLG. We issued that AD to detect and correct fatigue cracking of 
the main fitting of the MLG and consequent failure of the main fitting, 
which could result in the collapse of the MLG.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-20-09, Transport Canada Civil Aviation 
(TCCA), which is the airworthiness authority for Canada, has revised 
its parallel airworthiness directive, and issued Canadian airworthiness 
directive CF-2004-18R1, dated September 21, 2005. (Canadian emergency 
airworthiness directive CF-2004-18, dated September 16, 2004, was 
referenced as the parallel airworthiness directive in AD 2004-20-09.) 
This revision to the Canadian airworthiness directive specifies the 
revised inspection intervals in Revision B of Bombardier Alert Service 
Bulletin A601R-32-099, dated June 16, 2005. (Alert Service Bulletin 
A601R-32-099, dated September 15, 2004, was referenced in AD 2004-20-09 
as the appropriate source of service information for accomplishing the 
required actions.) The revised inspection intervals apply only to 
certain low-utilization airplanes, and specify that these airplanes 
comply with the actions in AD 2004-20-09 sooner than currently required 
by that AD. This revision to the Canadian airworthiness directive also 
specifies replacement of the main fittings of the MLG with new 
fittings, which terminates the repetitive inspections.
    In addition, the preamble to AD 2004-20-09 explains that we 
consider the requirements of AD 2004-20-09 to be ``interim action'' and 
that we are considering further rulemaking. We now have determined that 
further rulemaking is indeed necessary, and this proposed AD follows 
from that determination.

Other Relevant Rulemaking

    On November 16, 2001, we issued AD 2001-22-09 (amendment 39-12488, 
66 FR 58931, November 26, 2001), for certain Bombardier Model CL-600-
2B19 series airplanes. That AD requires repetitive eddy current 
inspections for cracking of the MLG main fittings, and replacement with 
a new or serviceable MLG if necessary. That AD also requires servicing 
the MLG shock struts; inspecting the MLG shock struts for nitrogen 
pressure, visible chrome dimension, and oil leakage; and performing 
corrective actions if necessary. That AD was prompted by reports of 
premature failure of the MLG main fitting. We issued that AD to prevent 
failure of the MLG main fitting, which could result in collapse of the 
MLG upon landing.
    On June 30, 2004, we issued AD 2004-14-16 (amendment 39-13725, 69 
FR 41421, July 9, 2004), for certain Bombardier Model CL-600-2B19 
(Regional Jet Series 100 & 440) airplanes. That AD requires repetitive 
detailed and eddy current inspections on the main fittings of the MLGs 
to detect discrepancies, and related investigative/corrective actions 
if necessary. That AD also requires servicing the shock strut of the 
MLGs; inspecting the shock strut of the MLGs for nitrogen pressure, 
visible chrome dimension, and oil leakage; and servicing any discrepant 
strut. That AD resulted from results of a stress analysis that revealed 
that certain main fittings of the MLGs are susceptible to premature 
cracking, starting in the radius of the upper lug. We issued that AD to 
detect and correct premature cracking of the main fittings of the MLGs, 
which could result in failure of the fittings and consequent collapse 
of the MLGs during landing.

Relevant Service Information

    Bombardier has issued Alert Service Bulletin A601R-32-099, Revision 
B, dated June 16, 2005, including Appendices A through D, Revision A, 
dated December 13, 2004. The procedures in this service bulletin are 
essentially the same as the procedures in the original issue of 
Bombardier Alert Service Bulletin A601R-32-099, including Appendices A 
through D, dated September 15, 2004, which was cited as the appropriate 
source of service information in AD 2004-20-09.
    Bombardier has also issued Service Bulletin 601R-32-093, Revision 
B, dated July 14, 2005. This service bulletin describes procedures for 
replacing the main fitting of the MLG with a new main fitting having a 
new part number.
    TCCA mandated the service information and issued Canadian 
airworthiness directive CF-2004-18R1, dated September 21, 2005, to 
ensure the continued airworthiness of these airplanes in Canada. TCCA 
considers Bombardier Service Bulletin 601R-32-093 to be terminating 
action for the repetitive inspections in Bombardier Alert Service 
Bulletin A601R-32-099.
    Bombardier Service Bulletin 601R-32-093, Revision B, refers to 
Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated October 9, 
2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-25, Revision 
1, dated October 17, 2003; as additional sources of service information 
for replacing the MLG main fitting. Operators should note that P/Ns 
601R85001-81/82 (Messier-Dowty P/Ns 17064-105/106), as specified in 
Bombardier Service Bulletin 601R-32-093, Revision B, and Messier-Dowty 
Service Bulletin M-DT SB17002-32-25, Revision 1, require different 
inspections in accordance with AD 2004-14-16. We are considering 
additional rulemaking to supersede that AD to require replacement of 
the noted part numbers at a different compliance time.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in Canada and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the

[[Page 39239]]

Federal Aviation Regulations (14 CFR 21.29) and the applicable 
bilateral airworthiness agreement. Pursuant to this bilateral 
airworthiness agreement, TCCA has kept the FAA informed of the 
situation described above. We have examined TCCA's findings, evaluated 
all pertinent information, and determined that AD action is necessary 
for airplanes of this type design that are certificated for operation 
in the United States.
    This proposed AD would supersede AD 2004-20-09. This proposed AD 
would continue to require repetitive inspections for cracks, sealant 
damage, and corrosion of the main fittings of the MLG, and corrective 
actions if necessary. This proposed AD also would reduce the compliance 
times for inspecting certain affected airplanes, and require that 
operators do the actions in accordance with a new revision of the 
service bulletin, described previously, except as discussed under 
``Difference Between the Proposed AD and Bombardier Alert Service 
Bulletin A601R-32-099.''

Difference Between the Proposed AD and Bombardier Alert Service 
Bulletin A601R-32-099

    Although the Accomplishment Instructions of the Bombardier Alert 
Service Bulletin A601R-32-099, Revision B, describe procedures for 
reporting crack indications, returning cracked parts to Messier-Dowty, 
and submitting a comment sheet related to service bulletin quality and 
a sheet recording compliance with the service bulletin, this AD, like 
Canadian airworthiness directive CF-2004-18R1, would not require those 
actions.

Difference Between the Proposed AD and the Canadian Airworthiness 
Directive

    Canadian airworthiness directive CF-2004-18R1, recommends replacing 
the main fitting of the MLG with a new main fitting having a new part 
number by June 2007, which is 27 months after the effective date of the 
Canadian airworthiness directive. We find that a compliance time of 
within 15 months after the effective date of this proposed AD would 
allow us to come close to the compliance date of June 2007, and 
represents an appropriate interval of time for affected airplanes to 
continue to operate without compromising safety. This difference has 
been coordinated with TCCA.

Clarification of Inspection Language

    Bombardier Alert Service Bulletin A601R-32-099, Revision B, 
specifies that operators should do a visual inspection for cracks of 
the inboard and outboard sides of the main fitting of the MLG; and a 
visual inspection for sealant damage or corrosion around the forward 
bushing of the left and right main fittings of the MLG. The Canadian 
airworthiness directive refers to this inspection as a ``detailed 
visual inspection.'' In this proposed AD we refer to this inspection as 
a ``detailed inspection.'' Note 1 of this proposed AD defines this 
inspection.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. There are approximately 201 U.S.-
registered airplanes. The average labor rate is $80 per hour.

                                                 Estimated Costs
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                                         Work
               Action                   hours         Parts         Cost per airplane           Fleet cost
----------------------------------------------------------------------------------------------------------------
Detailed inspection for cracks of             1             N/A  $80, per inspection      $16,080, per
 the main fitting (required by AD                                 cycle.                   inspection cycle.
 2004-20-09).
Detailed inspection for sealant               1             N/A  $80, per inspection      $16,080, per
 damage of the bushing (required by                               cycle.                   inspection cycle.
 AD 2004-20-09).
Ultrasonic inspection for cracks of           1             N/A  $80, per inspection      $16,080, per
 the main fittings (required by AD                                cycle.                   inspection cycle.
 2004-20-09).
Replacement (new proposed action)...         56        $105,732  $110,212...............  $22,152,612.
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.

[[Page 39240]]

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-13814 (69 FR 
59790, October 6, 2004) and adding the following new airworthiness 
directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2005-22559; 
Directorate Identifier 2005-NM-076-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by August 11, 2006.

Affected ADs

    (b) This AD supersedes AD 2004-20-09.

Applicability

    (c) This AD applies to Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category; 
serial numbers 7003 through 7067 inclusive, and 7069 through 8999 
inclusive; equipped with main landing gear (MLG) main fittings, 
having part number (P/N) 601R85001-3 or -4 (Messier-Dowty P/N 17064-
101, -102, -103, or -104).

Unsafe Condition

    (d) This AD results from a report of a cracked main fitting of 
the MLG. We are issuing this AD to detect and correct fatigue 
cracking of the main fitting of the MLG and consequent failure of 
the main fitting, which could result in the collapse of the MLG.

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.

Service Bulletin

    (f) Unless otherwise specified in this AD, the term ``service 
bulletin,'' as used in this AD, means the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A601R-32-099, 
including Appendices A, B, and D, and excluding Appendix C, dated 
September 15, 2004; or Bombardier Alert Service Bulletin A601R-32-
099, Revision A, including Appendices A, B, and D, and excluding 
Appendix C, dated December 13, 2004; or Bombardier Alert Service 
Bulletin A601R-32-099, Revision B, dated June 16, 2005, including 
Appendices A, B, and D, and excluding Appendix C, Revision A, dated 
December 13, 2004.
    (1) After the effective date of this AD, only Revision B of the 
service bulletin may be used.
    (2) Although the service bulletin specifies to submit certain 
information to the airplane manufacturer and to return cracked main 
fittings to the supplier, this AD does not include those 
requirements.

Restatement of the Requirements of AD 2004-20-09

Initial Inspections at New Reduced Compliance Times

    (g) Do the actions in Table 1 of this AD.

 Table 1.--Initial Inspection Thresholds at New Reduced Compliance Times
------------------------------------------------------------------------
 Do the following in Column    At the earlier of the times specified in
             1--                        Column 2 or Column 3--
------------------------------------------------------------------------
                              Column 2--The latest  Column 3--The latest
         Column 1--                   of--                  of--
------------------------------------------------------------------------
(1) A detailed inspection     (i)(A) Before the     (ii)(A) Within 48
 for cracks of the inboard     accumulation of       months since the
 and outboard sides of the     8,000 total flight    main fitting of the
 main fitting of the MLG       cycles since the      MLG was new.
 between the pintle pin        main fitting of the  (B) Within 48 months
 trunnion and the radius of    MLG was new.          since the last
 the shock strut lug, in      (B) Within 8,000       overhaul of the MLG
 accordance with Part A of     flight cycles since   done before the
 the service bulletin.         the last overhaul     effective date of
                               of the MLG done       this AD.
                               before the           (C) Within 50 flight
                               effective date of     cycles after the
                               this AD.              effective date of
                              (C) Within 50 flight   this AD.
                               cycles after
                               October 21, 2004
                               (the effective date
                               of AD 2004-20-09).
(2) A detailed inspection     (i)(A) Before the     (ii)(A) Within 48
 for sealant damage or         accumulation of       months since the
 corrosion around the          8,000 total flight    main fitting of the
 forward bushing of the left   cycles since the      MLG was new.
 and right main fittings of    main fitting of the  (B) Within 48 months
 the MLG, in accordance with   MLG was new.          since the last
 Part B of the service        (B) Within 8,000       overhaul of the MLG
 bulletin.                     flight cycles since   done before the
                               the last overhaul     effective date of
                               of the MLG done       this AD.
                               before the           (C) Within 500
                               effective date of     flight cycles or 6
                               this AD.              months after the
                              (C) Within 500         effective date of
                               flight cycles after   this AD, whichever
                               October 21, 2004.     occurs first.
(3) An ultrasonic inspection  (i)(A) Before the     (ii)(A) Within 48
 for cracks of the left and    accumulation of       months since the
 right main fittings of the    8,000 total flight    main fitting of the
 MLG, in accordance with       cycles since the      MLG was new.
 Part C of the service         main fitting of the  (B) Within 48 months
 bulletin.                     MLG was new.          since the last
                              (B) Within 8,000       overhaul of the MLG
                               flight cycles,        done before the
                               since the last        effective date of
                               overhaul of the MLG   this AD.
                               done before the      (C) Within 500
                               effective date of     flight cycles or 6
                               this AD.              months after the
                              (C) Within 500         effective date of
                               flight cycles after   this AD, whichever
                               October 21, 2004.     occurs first.
------------------------------------------------------------------------


    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repetitive Inspections

    (h) Repeat the inspections in paragraph (g) of this AD 
thereafter at the applicable interval in paragraph (h)(1) or (h)(2) 
of this AD, until the terminating action required by paragraph (l) 
of this AD is accomplished.
    (1) For airplanes on which the applicable initial inspection in 
paragraph (g) of this AD has been done before the effective date of 
this AD, do the next inspection at the applicable interval in Table 
2 of this AD.
    (2) For airplanes on which the applicable initial inspection in 
paragraph (g) of this AD has not been done before the effective date 
of this AD, repeat the inspection at the applicable interval in 
Table 2 of this AD.

[[Page 39241]]



            Table 2.--Repetitive Inspections at New Intervals
------------------------------------------------------------------------
 For the inspection required   Repeat at intervals    Until the action
            by--                not to  exceed--        required by--
------------------------------------------------------------------------
(3) Paragraph (g)(1) of this  5 days..............  Paragraph (g)(3) of
 AD.                                                 this AD is done,
                                                     unless required by
                                                     paragraph (j) of
                                                     this AD.
(4) Paragraph (g)(2) of this  500 flight cycles or  Paragraph (j)(2) of
 AD.                           6 months, whichever   this AD is done.
                               occurs first.
(5) Paragraph (g)(3) of this  5,000 flight cycles   (None).
 AD.                           or 30 months,
                               whichever occurs
                               first, except as
                               required by
                               paragraph (j)(2) of
                               this AD.
------------------------------------------------------------------------

Corrective Actions

    (i) If there is an indication of a crack during any inspection 
required by paragraph (g)(1), (h)(3), or (j)(1) of this AD, before 
further flight, do the actions specified in paragraph (i)(1) or 
(i)(2) of this AD in accordance with Part A of the service bulletin; 
or do the terminating action required by paragraph (l) of this AD.
    (1) Replace the cracked main fitting of the MLG with a new or 
serviceable main fitting.
    (2) Do an eddy current inspection to verify whether there is a 
crack. If there is a crack, replace the cracked main fitting of the 
MLG with a new or serviceable main fitting.
    (j) If any sealant damage or corrosion is found during any 
inspection required by either paragraph (g)(2) or (h)(4) of this AD, 
do the actions specified in Table 3 of this AD in accordance with 
Part B of the service bulletin, until the terminating action 
required by paragraph (l) of this AD is accomplished.

                          Table 3.--Corrective Actions for Sealant Damage or Corrosion
----------------------------------------------------------------------------------------------------------------
                                                               Repeat at intervals not      Until the action
 Do the inspection specified in--           Within--                to  exceed--             specified in--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph (g)(1) of this AD..  5 days after doing the     5 days..................  Paragraph (j)(2) or (l)
                                    inspection required by                               of this AD is done.
                                    (g)(2) or (h)(4) of this
                                    AD, as applicable.
(2) Paragraph (g)(3) of this AD..  500 flight cycles after    500 flight cycles.......  Paragraph (l) of this AD
                                    doing the inspection                                 is done.
                                    required by paragraph
                                    (g)(2) or (h)(4) of this
                                    AD, as applicable.
----------------------------------------------------------------------------------------------------------------

    (k) If there is an indication of a crack during any inspection 
required by paragraph (g)(3) or (h)(5) of this AD, before further 
flight, replace the cracked main fitting of the MLG with a new or 
serviceable main fitting in accordance with Part C of the service 
bulletin; or do the terminating action required by paragraph (l) of 
this AD.

New Requirement of This AD

Terminating Action--Replacement

    (l) Within 15 months after the effective date of this AD, 
replace both main fittings of the MLG with new main fittings having 
new part numbers, in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 601R-32-093, Revision B, dated July 
14, 2005. Doing this replacement terminates all requirements of 
paragraphs (g), (h), (i), (j), and (k) of this AD.


    Note 2: Bombardier Service Bulletin 601R-32-093, Revision B, 
refers to Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated 
October 9, 2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-
25, Revision 1, dated October 17, 2003; as additional sources of 
service information for replacing the MLG main fitting.

Actions Accomplished in Accordance With Earlier Issues of Service 
Bulletin

    (m) Actions done before the effective date of this AD in 
accordance with the service bulletins listed in Table 4 of this AD 
are acceptable for compliance with the corresponding action 
specified in this AD.

                                  Table 4.--Earlier Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
            Service bulletin                    Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Bombardier Service Bulletin 601R-32-093  Original...................  October 17, 2003.
Bombardier Service Bulletin 601R-32-093  A..........................  September 21, 2004.
----------------------------------------------------------------------------------------------------------------

Parts Installation

    (n) As of the effective date of this AD, no person may install a 
main fitting of the MLG, Bombardier P/N 601R85001-3 or 601R85001-4; 
also referred to as Messier-Dowty P/N 17064-101, 17064-102, 17064-
103, or 17064-104; on any airplane.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, New York Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (p) Canadian airworthiness directive CF-2004-18R1, dated 
September 21, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on July 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-10913 Filed 7-11-06; 8:45 am]
BILLING CODE 4910-13-P