
[Federal Register: March 11, 2008 (Volume 73, Number 48)]
[Proposed Rules]               
[Page 12901-12905]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11mr08-17]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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[[Page 12901]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0265; Directorate Identifier 2007-NM-349-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).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Bombardier Model CL-600-2B19 
airplanes. The existing AD currently requires repetitive eddy current 
inspections for cracking of the main landing gear (MLG) main fittings, 
and replacement with new or serviceable MLG main fittings if necessary. 
The existing AD also currently 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. This proposed AD would require replacement of the MLG main 
fittings with new improved MLG main fittings, which would terminate the 
repetitive inspections of the MLG main fittings and inspection and 
servicing of the MLG shock struts. This proposed AD results from 
premature failure of the MLG main fittings. We are proposing this AD to 
prevent failure of the MLG main fittings, which could result in 
collapse of the MLG upon landing.

DATES: We must receive comments on this proposed AD by April 10, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Bombardier, 
Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, 
Montreal, Quebec H3C 3G9, Canada.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Pong K. Lee, 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) 228-7324; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0265; 
Directorate Identifier 2007-NM-349-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 20, 2003, we issued AD 2003-11-11, amendment 39-13170 (68 FR 
31956, May 29, 2003), for certain Bombardier Model CL-600-2B19 
airplanes. That AD requires repetitive eddy current inspections for 
cracking of the main landing gear (MLG) main fittings, and replacement 
with new or serviceable MLG main fittings 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 
resulted from issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. We issued that 
AD to prevent failure of the MLG main fittings, which could result in 
collapse of the MLG upon landing.

Actions Since Existing AD Was Issued

    Since we issued AD 2003-11-11, Transport Canada Civil Aviation 
(TCCA), which is the airworthiness authority for Canada, notified us 
that it has certified a new design of the MLG main fitting. 
Installation of the new improved MLG main fittings would eliminate the 
need for the repetitive inspections of the MLG main fittings and the 
inspection and servicing of the MLG shock struts.
    The preamble to AD 2003-11-11 explains that we consider the 
requirements ``interim action'' and were considering further 
rulemaking. We now have determined that further rulemaking is indeed 
necessary, and this proposed AD follows from that determination.

Other Related Rulemaking

    On December 21, 2006, we issued AD 2007-01-07, amendment 39-14879 
(72 FR 1430, January 12, 2007), for Model CL-600-2B19 (Regional Jet 
Series 100 & 440) airplanes having serial numbers (S/Ns) 7003 through 
7067 inclusive and S/Ns 7069 through 8999 inclusive, equipped with MLG 
main fittings having part number (P/N) 601R85001-3 or -4 (Messier-Dowty 
P/N 17064-101, -102, -103, or -104). That AD requires

[[Page 12902]]

repetitive inspections for cracks, sealant damage, and corrosion of the 
main fittings of the MLG, and corrective actions if necessary. That AD 
also requires replacement of both main fittings of the MLG with new 
main fittings, which terminates the repetitive inspections. 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. For certain airplanes, accomplishing the 
replacements in accordance with paragraph (l) of AD 2007-01-07 is 
considered acceptable for compliance with the replacement specified in 
this proposed AD.
    On January 29, 2007, we issued AD 2007-03-19, amendment 39-14930 
(72 FR 5925, February 8, 2007), for certain Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes having S/Ns 7003 and subsequent, 
equipped with MLG main fittings having P/N 601R85001-81 and -82 
(Messier-Dowty P/N 17064-105 and -106). That AD requires repetitive 
detailed and eddy current inspections of 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 also requires installing a new improved MLG main 
fitting, which terminates the repetitive inspections and servicing 
requirements. That AD resulted from stress analyses that showed certain 
main fittings of the MLG 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. The requirements of AD 2007-03-19 do not affect 
the actions specified in this proposed AD, since AD 2007-03-19 is 
applicable to airplanes equipped with different MLG main fittings.

Relevant Service Information

    Bombardier has issued Service Bulletin 601R-32-093, Revision B, 
dated July 14, 2005. The service bulletin describes procedures for 
replacing the MLG main fittings with new improved MLG main fittings 
having P/Ns 601R85001-83 and -84 (Messier-Dowty P/Ns 17064-107 and -
108). Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. TCCA mandated the 
service information and issued Canadian airworthiness directive CF-
1999-32R3, dated September 21, 2005, to ensure the continued 
airworthiness of these airplanes in Canada.

FAA's Determination and Requirements of the Proposed AD

    These airplanes are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the 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 2003-11-11 and would retain the 
requirements of the existing AD. This proposed AD would also require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Difference Between 
the Proposed AD and Canadian Airworthiness Directive.''

Difference Between the Proposed AD and Canadian Airworthiness Directive

    Canadian airworthiness directive CF-1999-32R3 specifies replacing 
the MLG main fittings by June 30, 2007, which is a compliance time of 
about 21 months after issuance of Canadian airworthiness directive CF-
1999-32R3. This proposed AD, however, would require replacing the MLG 
main fittings within 6 months after the effective date of the AD. In 
developing an appropriate compliance time for this proposed AD, we 
considered not only the manufacturer's recommendation, but the degree 
of urgency associated with addressing the subject unsafe condition, the 
average utilization of the affected fleet, and the time necessary to 
perform the replacements. In light of all of these factors, we find a 
compliance time of 6 months for completing the required actions to be 
warranted, in that it represents an appropriate interval of time for 
affected airplanes to continue to operate without compromising safety. 
This difference has been coordinated with TCCA.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2003-11-11. 
Since AD 2003-11-11 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
      Requirement in AD 2003-11-11               this proposed  AD
------------------------------------------------------------------------
Paragraph (a)...........................  Paragraph (f).
Paragraph (b)...........................  Paragraph (g).
Paragraph (c)...........................  Paragraph (h).
Paragraph (d)...........................  Paragraph (i).
Paragraph (e)...........................  Paragraph (j).
Paragraph (f)...........................  Paragraph (k).
Paragraph (g)...........................  Paragraph (l).
Paragraph (h)...........................  Paragraph (m).
Paragraph (i)...........................  Paragraph (n).
Paragraph (j)...........................  Paragraph (o).
Paragraph (k)...........................  Paragraph (p).
Paragraph (l)...........................  Paragraph (q).
------------------------------------------------------------------------

Costs of Compliance

    The following table provides the estimated costs, at an average 
labor rate of $80 per work hour, for U.S. operators to comply with this 
proposed AD. Due to other existing ADs, the proposed actions have 
already been accomplished on the majority of affected U.S.-registered 
airplanes; therefore, the estimated costs will be significantly less 
than those specified in the table.

[[Page 12903]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                 Number of U.S.-
            Action               Work hours         Parts           Cost per       registered       Fleet cost
                                                                    airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Detailed inspection (required               1  None...........  $80, per                    618  $49,440, per
 by AD 2003-11-11).                                              inspection                       inspection
                                                                 cycle.                           cycle
Eddy current inspection                     1  None...........  $80, per                    618  $49,440, per
 (required by AD 2003-11-11).                                    inspection                       inspection
                                                                 cycle.                           cycle
Fluorescent penetrant                       1  None...........  $80, per                    618  $49,440, per
 inspection (required by AD                                      inspection                       inspection
 2003-11-11).                                                    cycle.                           cycle
Inspection and servicing of                 2  None...........  $160, per                   618  $98,880, per
 shock struts (required by AD                                    inspection                       inspection
 2003-11-11).                                                    cycle.                           cycle
Replacement (new proposed                  56  Up to $35,000..  Up to $39,480..             618  $24,398,640
 action).
----------------------------------------------------------------------------------------------------------------

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 and placed it in the AD docket. 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.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13170 (68 FR 31956, May 29, 2003) and adding the 
following new airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2008-0265; 
Directorate Identifier 2007-NM-349-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 10, 
2008.

Affected ADs

    (b) This AD supersedes AD 2003-11-11.

Applicability

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

Unsafe Condition

    (d) This AD results from premature failure of the MLG main 
fittings. We are issuing this AD to prevent failure of the MLG main 
fittings, which could result in collapse of the MLG upon landing.

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.

    Note 1: Where there are differences between the referenced 
service bulletin and the AD, the AD prevails.

Restatement of Requirements of AD 2003-11-11

Service Bulletin References

    (f) Accomplishment of the inspections and servicing, as applicable, 
specified in paragraphs (h), (l), (m), and (n) of this AD, per 
Bombardier Alert Service Bulletin A601R-32-079, dated December 3, 1999; 
Revision `A,' dated January 7, 2000; Revision `B,' dated June 1, 2000; 
Revision `C,' dated October 26, 2000; or Revision `D,' dated December 
1, 2000; prior to June 13, 2003 (the effective date of AD 2003-11-11), 
is considered acceptable for compliance with the requirements of 
paragraphs (h), (l), (m), and (n) of this AD.
    (g) The term ``service bulletin,'' as used in paragraphs (h) 
through (q) of this AD, means the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A601R-32-079, Revision `E,' dated 
September 12, 2002; including Appendix 1, Revision D, dated September 
12, 2002; including Appendices 2 and 3, dated September 12, 2002.

Initial Eddy Current Inspection

    (h) Perform an eddy current inspection to detect cracking of the 
MLG main fittings, per PART B of the service bulletin, at the earlier 
of the times specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) Prior to the accumulation of 1,500 total flight cycles on the 
MLG, or within 150 flight cycles after December 4, 2001

[[Page 12904]]

(the effective date of AD 2001-22-09, amendment 39-12488, which was 
superseded by AD 2003-11-11), whichever occurs later.
    (2) Prior to the accumulation of 1,000 total flight cycles on the 
MLG, or within 150 flight cycles after June 13, 2003, whichever occurs 
later.

Repetitive Eddy Current Inspections

    (i) Repeat the eddy current inspection specified in paragraph (h) 
of this AD at the time specified in paragraph (i)(1), (i)(2), or 
(i)(3), as applicable, except as provided by paragraph (i)(4) of this 
AD, per PART B of the service bulletin.
    (1) For airplanes on which the eddy current inspection required by 
paragraph (g) of this AD is accomplished after June 13, 2003: Repeat 
the inspection at intervals not to exceed 500 flight cycles.
    (2) For airplanes on which the repetitive eddy current inspection 
required by AD 2001-22-09 has been accomplished, and on which the 
repetitive intervals have been increased per paragraph (j) of AD 2001-
22-09 before June 13, 2003: Repeat the inspection within 500 flight 
cycles after June 13, 2003, or within 1,000 flight cycles since the 
last eddy current inspection, whichever occurs first, and thereafter at 
intervals not to exceed 500 flight cycles.
    (3) For airplanes on which the repetitive eddy current inspection 
required by AD 2001-22-09 has been accomplished, and on which the 
repetitive intervals have not been increased per paragraph (j) of AD 
2001-22-09 before June 13, 2003: Repeat the eddy current inspection at 
intervals not to exceed 500 flight cycles.
    (4) For airplanes on which an eddy current inspection has been 
accomplished to confirm the detailed inspection required by paragraph 
(o) of this AD: The next eddy current inspection must be done within 
500 flight cycles following the last detailed inspection required by 
paragraph (o) of this AD, and thereafter at intervals not to exceed 500 
flight cycles.

Corrective Actions

    (j) If no cracking of the MLG main fittings is suspected during the 
next eddy current inspection required by paragraph (h) or (i) of this 
AD, but the paint has been removed: Prior to further flight, apply a 
new finish and install the harness clamp on the brake line with the 
bolt, washers, nut, and cotter pin; per PART B of the service bulletin.
    (k) If any cracking of the MLG main fittings is found during any 
eddy current inspection required by paragraph (h) or (i) of this AD: 
Prior to further flight, replace any cracked MLG main fitting with a 
new or serviceable part per the service bulletin.

Servicing the Shock Struts

    (l) Prior to the accumulation of 1,500 total flight cycles on the 
MLG shock struts, or within 500 flight cycles after December 4, 2001, 
whichever occurs later: Service (Oil and Nitrogen) the left and right 
MLG shock struts per PART C (for airplanes on the ground) or PART D 
(for airplanes on jacks) of the service bulletin.

Other Inspections

    (m) Within 500 flight cycles after completing the actions required 
by paragraph (l) of this AD: Inspect the MLG left and right shock 
struts for nitrogen pressure, visible chrome dimension, and oil 
leakage, in accordance with PART E of the service bulletin. Thereafter, 
repeat the inspection at intervals not to exceed 500 flight cycles.

Corrective Actions for Certain Inspections

    (n) If the chrome extension dimension of the shock strut pressure 
reading is outside the limits specified in the Airplane Maintenance 
Manual, Task 32-11-05-220-801, or any oil leakage is found during any 
inspection required by paragraph (m) of this AD: Prior to further 
flight, service the MLG shock strut in accordance with PART C (for 
airplanes on the ground) or PART D (for airplanes on jacks) of the 
service bulletin.

Detailed and Follow-On Inspections and Corrective Action

    (o) Prior to the accumulation of 1,000 total flight cycles on the 
MLG, or within 250 flight cycles after June 13, 2003, whichever occurs 
later: Accomplish a detailed inspection of the MLG main fittings to 
detect signs of cracking (including linear paint cracks along the 
circumference of the main fitting tube, lack of paint (paint peeling) 
or other paint damage, lack of adhesion or paint bulging, and signs of 
corrosion), per PART A of the service bulletin. Repeat the inspection 
thereafter at intervals not to exceed 100 flight cycles.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (p) If any linear paint crack along the circumference of the main 
fitting tube, lack of paint (paint peeling) or other paint damage, 
evidence of paint bulging due to lack of adhesion, or evidence of 
corrosion is found during any inspection required by paragraph (o) of 
this AD: Prior to further flight, accomplish either an eddy current 
inspection to detect cracking, per PART B of the service bulletin; or a 
fluorescent penetrant inspection to detect cracking, per PART F of the 
service bulletin.
    (1) If no cracking of the MLG main fittings is found during any 
inspection required by paragraph (p) of this AD: Prior to further 
flight, repaint and/or repair/rework any paint damage per PART B of the 
service bulletin.
    (2) If any cracking of the MLG main fittings is found during any 
inspection required by paragraph (p) of this AD: Prior to further 
flight, replace any cracked MLG main fitting with a new or serviceable 
part per the service bulletin.

Reporting Requirement

    (q) Within 30 days after each inspection and servicing required by 
paragraphs (h), (i), (l), (m), (o), and (p) of this AD, report all 
findings, positive or negative, to: Bombardier Aerospace, In-Service 
Engineering, fax number 514-855-8501. Although the service bulletin 
references completion of a ``Service Bulletin Comment Sheet-Facsimile 
Reply Sheet,'' this AD does not require that action. Information 
collection requirements contained in this regulation have been approved 
by the Office of Management and Budget (OMB) under the provisions of 
the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have 
been assigned OMB Control Number 2120-0056.

New Requirements of This AD

Replacement

    (r) Within 6 months after the effective date of this AD, replace 
the MLG main fittings with new improved MLG main fittings, in 
accordance with Bombardier Service Bulletin 601R-32-093, Revision B, 
dated July 14, 2005. Replacing the MLG main fittings terminates the 
requirements of paragraphs (h) through (q) of this AD.

Credit for Actions Done According to Previous Issues of the Service 
Bulletin

    (s) Replacements done before the effective date of this AD in 
accordance with Bombardier Service Bulletin 601R-32-093, dated October 
17, 2003; or Revision A, dated September 21, 2004; are acceptable for 
compliance with the requirements of paragraph (r) of this AD.

[[Page 12905]]

Credit for AD 2007-01-07

    (t) For airplanes having S/Ns 7003 through 7067 inclusive and S/Ns 
7069 through 8999 inclusive, equipped with MLG main fittings having P/N 
601R85001-3 or -4 (Messier-Dowty P/N 17064-101, -102, -103, or -104): 
Accomplishing the replacements required by paragraph (l) of AD 2007-01-
07, amendment 39-14879, is acceptable for compliance with the 
requirements of paragraph (r) of this AD.

Alternative Methods of Compliance (AMOCs)

    (u)(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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) AMOCs issued to allow escalation of the repetitive intervals 
for the eddy current inspections from 500 to 1,000 flight cycles in 
accordance with paragraph (e) of AD 2001-22-09 are not approved as 
AMOCs with this AD.

    Note 3: Information concerning the existence of AMOCs with this 
AD, if any, may be obtained from the New York ACO.

Related Information

    (v) Canadian airworthiness directive CF-1999-32R3, dated September 
21, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-4769 Filed 3-10-08; 8:45 am]

BILLING CODE 4910-13-P
