[Federal Register: October 6, 2004 (Volume 69, Number 193)]
[Rules and Regulations]
[Page 59790-59793]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06oc04-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19229; Directorate Identifier 2004-NM-195-AD;
Amendment 39-13814; AD 2004-20-09]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) Airplanes
AGENCY: Federal Aviation Administration (FAA), 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-600-2B19 (Regional Jet Series 100 & 440)
airplanes. This 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. This AD is prompted by 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.
DATES: Effective October 21, 2004.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of
October 21, 2004.
We must receive comments on this AD by December 6, 2004.
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 Bombardier,
Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville,
Montreal, Quebec H3C 3G9, Canada. You can examine this information at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call (202)
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
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.
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
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 DMS receives them.
FOR FURTHER INFORMATION CONTACT:
Technical information: Serge Napoleon, 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) 228-7312; fax (516) 794-5531.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION: Transport Canada Civil Aviation (TCCA),
which is the airworthiness authority for Canada, notified the FAA that
an unsafe condition may exist on certain Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. TCCA advises that it has
received a report of a cracked main fitting of the main landing gear
(MLG) at the section between the forward face of the main fitting on
the trunnion side and the area just above the upper attach lug radius
of the shock strut. Laboratory examination has found that the fatigue
crack was initiated from a corrosion pit located on the chamfer of the
inner bore of the pintle pin socket of the main fitting of the MLG.
This condition, if not detected and corrected in a timely manner, could
cause failure of the main fitting of the MLG, which could result in the
collapse of the MLG.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A601R-32-099,
including Appendices A through D, dated September 15, 2004. The service
bulletin describes the following procedures:
Repetitive detailed inspections for cracks of the inboard
and outboard sides
[[Page 59791]]
of the main fitting of the MLG between the pintle pin trunnion and the
radius of the shock strut lug;
Repetitive detailed inspections for sealant damage or
corrosion around the forward bushing of the left and right main
fittings of the MLG;
Repetitive ultrasonic inspections for cracks of the left
and right main fittings of MLG; and
Corrective actions if necessary. The corrective actions
include replacing any cracked main fitting of the MLG with a new or
serviceable main fitting; doing an eddy current inspection to verify
that there is a crack on the fitting if necessary; and repeating
certain inspections described previously at reduced intervals; as
applicable.
TCCA mandated the service bulletin and issued Canadian
airworthiness directive CF-2004-18, dated September 16, 2004, to ensure
the continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of This 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 Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCAA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, 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. This AD
requires accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the AD and Referenced Service Bulletin/Canadian Airworthiness
Directive.''
Differences Between the AD and Referenced Service Bulletin/Canadian
Airworthiness Directive
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletin 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-2004-18, will not require those
actions. We do not need this information from operators.
In addition, if there is evidence of sealant damage or corrosion,
the referenced service bulletin describes procedures for accomplishing
only the ultrasonic inspection at intervals not to exceed 500 flight
cycles. This AD, as well as the Canadian airworthiness directive,
requires repeating the detailed inspection of the main fitting lateral
surface within 5 days following the visual inspection of the sealant,
and every 5 days thereafter, in addition to the ultrasonic inspections
of the main fittings within 500 flight cycles.
Canadian airworthiness directive CF-2004-18 specifies that the
required actions must be done in accordance with Bombardier Alert
Service Bulletin A601R-32-099, dated September 15, 2004, or ``later
revisions approved by the Chief, Continuing Airworthiness, Aircraft
Certification, Transport Canada.'' We cannot use the phrase, ``or later
FAA-approved revisions,'' in an AD when referring to the service
document because doing so violates Office of the Federal Register (OFR)
regulations for approval of materials ``incorporated by reference'' in
rules. In general terms, we are required by these OFR regulations to
either publish the service document contents as part of the actual AD
language; or submit the service document to the OFR for approval as
``referenced'' material, in which case we may only refer to such
material in the text of an AD. The AD may refer to the service document
only if the OFR approved it for ``incorporation by reference.'' To
allow operators to use later revisions of the referenced document
(issued after publication of the AD), either we must revise the AD to
reference specific later revisions, or operators must request approval
to use later revisions as an alternative method of compliance with this
AD under the provisions of paragraph (m) of this AD.
Interim Action
This is considered to be interim action until final action is
identified, at which time we may consider further rulemaking.
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; 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-2004-19229;
Directorate Identifier 2004-NM-195-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.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You can get more information about plain
language at http://www/faa.gov/language and http://www.plainlanguage.gov.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
[[Page 59792]]
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):
2004-20-09 Bombardier, Inc. (Formerly Canadair): Amendment 39-13814.
Docket No. FAA-2004-19229; Directorate Identifier 2004-NM-195-AD.
Effective Date
(a) This AD becomes effective October 21, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, serial numbers 7003 through 7067
inclusive and 7069 through 8999 inclusive, certificated in any
category; equipped with main landing gear (MLG) main fittings, part
number (P/N) 601R85001-3 or -4 (Messier Dowty P/N 17064-101, -102, -
103, or -104).
Unsafe Condition
(d) This AD was prompted by a report of a cracked main fitting
of the MLG. The FAA is 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) 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.
Initial Inspections
(g) Do the actions specified in Table 1 of this AD.
Table 1.--Initial Inspections
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Do-- At the latest of--
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(1) A detailed inspection for cracks of the (i) Before the
inboard and outboard sides of the main accumulation of 8,000
fitting of the MLG between the pintle pin total flight cycles
trunnion and the radius of the shock strut since the main fitting
lug, in accordance with Part A of the of the MLG was new.
service bulletin. (ii) Within 8,000 flight
cycles since the last
overhaul of the MLG.
(iii) Within 50 flight
cycles after the
effective date of this
AD.
(2) A detailed inspection for sealant damage (i) Before the
or corrosion around the forward bushing of accumulation of 8,000
the left and right main fittings of the MLG, total flight cycles
in accordance with Part B of the service since the main fitting
bulletin. of the MLG was new.
(ii) Within 8,000 flight
cycles since the last
overhaul of the MLG.
(iii) Within 500 flight
cycles after the
effective date of this
AD.
(3) An ultrasonic inspection for cracks of (i) Before the
the left and right main fittings of the MLG, accumulation of 8,000
in accordance with Part C of the service total flight cycles
bulletin. since the main fitting
of the MLG was new.
(ii) Within 8,000 flight
cycles since the last
overhaul of the MLG.
(iii) Within 500 flight
cycles after the
effective date of this
AD.
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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
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(h) Repeat the inspections required by paragraph (g) of this AD
at the time specified in Table 2 of this AD.
Table 2.--Repetitive Inspection Interval
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Repeat at
For the inspection required by-- intervals not to Until the action
exceed-- required by--
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(1) Paragraph (g)(1) of this AD. 5 days............ Paragraph (g)(3)
of the AD is
done, unless
required by
paragraph (j) of
this AD.
(2) Paragraph (g)(2) of this AD. 500 flight cycles. Paragraph (j)(2)
of this AD is
done.
(3) Paragraph (g)(3) of this AD. 5,000 flight (None).
cycles, except as
required by
paragraph (j)(2)
of this AD.
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[[Page 59793]]
Corrective Actions
(i) If there is an indication of a crack during any inspection
required by paragraph (g)(1), (h)(1), or (j)(1) of this AD, before
further flight, do the actions specified in paragraphs (i)(1) or
(i)(2) of this AD in accordance with Part A of the service bulletin.
(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)(2) of this AD,
do the actions specified in Table 3 of this AD in accordance with
Part B of the service bulletin.
Table 3.--Corrective Actions for Sealant Damage or Corrosion
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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) of
inspection required by this AD is done.
paragraph (g)(2) or
(h)(2) of this AD, as
aplicable.
(2) Paragraph (g)(3) of this AD...... 500 flight cycles after 500 flight cycles...... (None).
doing the inspection
required by paragraph
(g)(2) or (h)(2) of
this AD, as applicable.
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(k) If there is an indication of a crack during any inspection
required by paragraph (g)(3), (h)(3), or (j)(2) 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.
No Reporting or Returning of Parts
(l) Although the service bulletin referenced in this AD
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.
Alternative Methods of Compliance (AMOCs)
(m) 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.
Related Information
(n) Canadian airworthiness directive CF-2004-18, dated September
16, 2004, also addresses the subject of this AD.
Material Incorporated by Reference
(o) You must use Bombardier Alert Service Bulletin A601R-32-099,
including Appendices A, B, and D, and excluding Appendix C, dated
September 15, 2004, 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. For copies of the
service information, contact Bombardier, Inc., Canadair, Aerospace
Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C
3G9, Canada. You can review copies at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street SW,
room PL-401, Nassif Building, Washington, DC; or at the National
Archives and Records Administration (NARA). For information on the
availability of this material at 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 September 27, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service
[FR Doc. 04-22266 Filed 10-5-04; 8:45 am]
BILLING CODE 4910-13-P