Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 12901-12905 [E8-4769]
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12901
Proposed Rules
Federal Register
Vol. 73, No. 48
Tuesday, March 11, 2008
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.
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
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AGENCY:
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
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• 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 https://
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 https://
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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
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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.
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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
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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
Requirement in AD 2003–
11–11
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(a) ......................
(b) ......................
(c) ......................
(d) ......................
(e) ......................
(f) .......................
(g) ......................
(h) ......................
(i) .......................
(j) .......................
(k) ......................
(l) .......................
Corresponding
requirement in
this proposed
AD
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(f).
(g).
(h).
(i).
(j).
(k).
(l).
(m).
(n).
(o).
(p).
(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.
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ESTIMATED COSTS
Action
Work hours
Detailed inspection (required
by AD 2003–11–11).
Eddy current inspection (required by AD 2003–11–11).
Fluorescent penetrant inspection (required by AD
2003–11–11).
Inspection and servicing of
shock struts (required by
AD 2003–11–11).
Replacement (new proposed
action).
Parts
1
None ...........................
1
None ...........................
1
None ...........................
2
56
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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
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Cost per airplane
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Number of
U.S.-registered
airplanes
Fleet cost
$80, per inspection
cycle.
$80, per inspection
cycle.
$80, per inspection
cycle.
618
None ...........................
$160, per inspection
cycle.
618
$98,880, per inspection
cycle
Up to $35,000 ............
Up to $39,480 ............
618
$24,398,640
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:
618
618
$49,440, per inspection
cycle
$49,440, per inspection
cycle
$49,440, per inspection
cycle
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
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 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
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(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
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(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.
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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
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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.’’
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(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 SheetFacsimile 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.
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Credit for AD 2007–01–07
DEPARTMENT OF TRANSPORTATION
(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.
Federal Aviation Administration
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]
sroberts on PROD1PC70 with PROPOSALS
BILLING CODE 4910–13–P
VerDate Aug<31>2005
17:20 Mar 10, 2008
Jkt 214001
14 CFR Part 39
[Docket No. FAA–2008–0268; Directorate
Identifier 2008–NM–050–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702), CL–600–2D15
(Regional Jet Series 705), and CL–600–
2D24 (Regional Jet Series 900)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Bombardier Aerospace has completed a
system safety review of the aircraft fuel
system against fuel tank safety standards
introduced in Chapter 525 of the
Airworthiness Manual through Notice of
Proposed Amendment (NPA) 2002–043. The
identified non-compliances were then
assessed using Transport Canada Policy
Letter No. 525–001, to determine if
mandatory corrective action is required.
The assessment showed that it is necessary
to introduce Critical Design Configuration
Control Limitations (CDCCL), in order to
preserve critical fuel tank system ignition
source prevention features during
configuration changes such as modifications
and repairs, or during maintenance actions.
Failure to preserve critical fuel tank system
ignition source prevention features could
result in a fuel tank explosion. * * *
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
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
https://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–
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
12905
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations
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:
Mazdak Hobbi, 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) 228–7330; 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–2008–0268; Directorate Identifier
2008–NM–050–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 based on those comments.
We will post all comments we
receive, without change, to https://
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
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2008–07,
dated January 25, 2008 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Bombardier Aerospace has completed a
system safety review of the aircraft fuel
system against fuel tank safety standards
introduced in Chapter 525 of the
Airworthiness Manual through Notice of
Proposed Amendment (NPA) 2002–043. The
E:\FR\FM\11MRP1.SGM
11MRP1
]]>Agencies
[Federal Register Volume 73, Number 48 (Tuesday, March 11, 2008)]
[Proposed Rules]
[Pages 12901-12905]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4769]
========================================================================
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.
========================================================================
Federal Register / Vol. 73, No. 48 / Tuesday, March 11, 2008 /
Proposed Rules
[[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 https://
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 https://
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 https://
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
