Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 39237-39241 [E6-10913]
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Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules
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of safety embodied in the existing
regulations.
Hydrophobic windshield coatings
may depend to some degree on airflow
directly over the windshield to maintain
a clear vision area. The heavy rain and
high-speed conditions specified in the
current rule do not necessarily represent
the limiting conditions for this new
technology. For example, airflow over
the windshield, which may be necessary
to remove moisture from the
windshield, may not be adequate to
maintain a sufficiently clear area of the
windshield in low speed flight or during
ground operations. Alternatively,
airflow over the windshield may be
disturbed during such critical times as
the approach to land, where the airplane
is at a higher than normal pitch attitude.
In these cases, areas of airflow
disturbance or separation on the
windshield could cause failure to
maintain a clear vision area on the
windshield.
In addition to potentially depending
on airflow to function effectively,
hydrophobic coatings may also be
dependent on water droplet size for
effective precipitation removal. For
example, precipitation in the form of a
light mist may not be sufficient for the
coating’s properties to result in
maintaining a clear area of vision.
In summary, the current regulations
identify speed and precipitation rate
requirements that represent limiting
conditions for windshield wipers and
blowers, but not for hydrophobic
coatings, so it is necessary to issue
special conditions to maintain the level
of safety represented by the current
regulations.
These special conditions provide an
appropriate safety standard for the
hydrophobic coating technology as the
means to maintain a clear area of vision
by requiring it to be effective at low
speeds and precipitation rates as well as
the higher speeds and precipitation
rates identified in the current
regulation. These are the only new or
changed requirements relative to those
in § 25.773(b)(1) at Amendment 25–108.
Applicability
As discussed above, these special
conditions are applicable to the Model
Falcon 7X. Should Dassault Aviation
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
unusual design feature, the special
conditions would apply to that model as
well.
Conclusion
This action affects only certain novel
or unusual design features on one model
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of airplane. It is not a rule of general
applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for Dassault
Aviation Model Falcon 7X airplanes.
Pilot Compartment View—Hydrophobic
Coatings in Lieu of Windshield Wipers
The airplane must have a means to
maintain a clear portion of the
windshield, during precipitation
conditions, enough for both pilots to
have a sufficiently extensive view along
the flight path in normal flight attitudes
of the airplane. This means must be
designed to function, without
continuous attention on the part of the
crew, in conditions from light misting
precipitation to heavy rain at speeds
from fully stopped in still air, to 1.5
VSR1 with lift and drag devices retracted.
Issued in Renton, Washington, on July 3,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–10894 Filed 7–11–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22559; Directorate
Identifier 2005–NM–076–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. The existing AD currently
requires repetitive inspections for
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39237
cracks, sealant damage, and corrosion of
the main fittings of the main landing
gear (MLG), and corrective actions if
necessary. This proposed AD would
reduce the compliance times for
inspecting certain low-utilization
airplanes, and provide a terminating
action for the repetitive inspections.
This proposed AD results from a report
of a cracked main fitting of the MLG. We
are proposing this AD to detect and
correct fatigue cracking of the main
fitting of the MLG and consequent
failure of the main fitting, which could
result in the collapse of the MLG.
DATES: We must receive comments on
this proposed AD by August 11, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Richard Beckwith, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7302; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–22559; Directorate Identifier
2005–NM–076–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
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proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System (DMS) receives
them.
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Discussion
On September 27, 2004, we issued AD
2004–20–09, amendment 39–13814 (69
FR 59790, October 6, 2004), for certain
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. That AD requires repetitive
inspections for cracks, sealant damage,
and corrosion of the main fittings of the
main landing gear (MLG), and corrective
actions if necessary. That AD resulted
from a report of a cracked main fitting
of the MLG. We issued that AD to detect
and correct fatigue cracking of the main
fitting of the MLG and consequent
failure of the main fitting, which could
result in the collapse of the MLG.
Actions Since Existing AD Was Issued
Since we issued AD 2004–20–09,
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has revised its
parallel airworthiness directive, and
issued Canadian airworthiness directive
CF–2004–18R1, dated September 21,
2005. (Canadian emergency
airworthiness directive CF–2004–18,
dated September 16, 2004, was
referenced as the parallel airworthiness
directive in AD 2004–20–09.) This
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revision to the Canadian airworthiness
directive specifies the revised
inspection intervals in Revision B of
Bombardier Alert Service Bulletin
A601R–32–099, dated June 16, 2005.
(Alert Service Bulletin A601R–32–099,
dated September 15, 2004, was
referenced in AD 2004–20–09 as the
appropriate source of service
information for accomplishing the
required actions.) The revised
inspection intervals apply only to
certain low-utilization airplanes, and
specify that these airplanes comply with
the actions in AD 2004–20–09 sooner
than currently required by that AD. This
revision to the Canadian airworthiness
directive also specifies replacement of
the main fittings of the MLG with new
fittings, which terminates the repetitive
inspections.
In addition, the preamble to AD 2004–
20–09 explains that we consider the
requirements of AD 2004–20–09 to be
‘‘interim action’’ and that we are
considering further rulemaking. We now
have determined that further
rulemaking is indeed necessary, and
this proposed AD follows from that
determination.
Other Relevant Rulemaking
On November 16, 2001, we issued AD
2001–22–09 (amendment 39–12488, 66
FR 58931, November 26, 2001), for
certain Bombardier Model CL–600–
2B19 series airplanes. That AD requires
repetitive eddy current inspections for
cracking of the MLG main fittings, and
replacement with a new or serviceable
MLG if necessary. That AD also requires
servicing the MLG shock struts;
inspecting the MLG shock struts for
nitrogen pressure, visible chrome
dimension, and oil leakage; and
performing corrective actions if
necessary. That AD was prompted by
reports of premature failure of the MLG
main fitting. We issued that AD to
prevent failure of the MLG main fitting,
which could result in collapse of the
MLG upon landing.
On June 30, 2004, we issued AD
2004–14–16 (amendment 39–13725, 69
FR 41421, July 9, 2004), for certain
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. That AD requires repetitive
detailed and eddy current inspections
on the main fittings of the MLGs to
detect discrepancies, and related
investigative/corrective actions if
necessary. That AD also requires
servicing the shock strut of the MLGs;
inspecting the shock strut of the MLGs
for nitrogen pressure, visible chrome
dimension, and oil leakage; and
servicing any discrepant strut. That AD
resulted from results of a stress analysis
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that revealed that certain main fittings
of the MLGs are susceptible to
premature cracking, starting in the
radius of the upper lug. We issued that
AD to detect and correct premature
cracking of the main fittings of the
MLGs, which could result in failure of
the fittings and consequent collapse of
the MLGs during landing.
Relevant Service Information
Bombardier has issued Alert Service
Bulletin A601R–32–099, Revision B,
dated June 16, 2005, including
Appendices A through D, Revision A,
dated December 13, 2004. The
procedures in this service bulletin are
essentially the same as the procedures
in the original issue of Bombardier Alert
Service Bulletin A601R–32–099,
including Appendices A through D,
dated September 15, 2004, which was
cited as the appropriate source of
service information in AD 2004–20–09.
Bombardier has also issued Service
Bulletin 601R–32–093, Revision B,
dated July 14, 2005. This service
bulletin describes procedures for
replacing the main fitting of the MLG
with a new main fitting having a new
part number.
TCCA mandated the service
information and issued Canadian
airworthiness directive CF–2004–18R1,
dated September 21, 2005, to ensure the
continued airworthiness of these
airplanes in Canada. TCCA considers
Bombardier Service Bulletin 601R–32–
093 to be terminating action for the
repetitive inspections in Bombardier
Alert Service Bulletin A601R–32–099.
Bombardier Service Bulletin 601R–
32–093, Revision B, refers to MessierDowty Service Bulletin M–DT
SB17002–32–24, dated October 9, 2003;
and Messier-Dowty Service Bulletin M–
DT SB17002–32–25, Revision 1, dated
October 17, 2003; as additional sources
of service information for replacing the
MLG main fitting. Operators should
note that P/Ns 601R85001–81/82
(Messier-Dowty P/Ns 17064–105/106),
as specified in Bombardier Service
Bulletin 601R–32–093, Revision B, and
Messier-Dowty Service Bulletin M–DT
SB17002–32–25, Revision 1, require
different inspections in accordance with
AD 2004–14–16. We are considering
additional rulemaking to supersede that
AD to require replacement of the noted
part numbers at a different compliance
time.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in Canada and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
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Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
TCCA has kept the FAA informed of the
situation described above. We have
examined TCCA’s findings, evaluated
all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would supersede
AD 2004–20–09. This proposed AD
would continue to require repetitive
inspections for cracks, sealant damage,
and corrosion of the main fittings of the
MLG, and corrective actions if
necessary. This proposed AD also
would reduce the compliance times for
inspecting certain affected airplanes,
and require that operators do the actions
in accordance with a new revision of the
service bulletin, described previously,
except as discussed under ‘‘Difference
Between the Proposed AD and
Bombardier Alert Service Bulletin
A601R–32–099.’’
Difference Between the Proposed AD
and Bombardier Alert Service Bulletin
A601R–32–099
Although the Accomplishment
Instructions of the Bombardier Alert
Service Bulletin A601R–32–099,
Revision B, describe procedures for
reporting crack indications, returning
cracked parts to Messier-Dowty, and
submitting a comment sheet related to
service bulletin quality and a sheet
recording compliance with the service
bulletin, this AD, like Canadian
airworthiness directive CF–2004–18R1,
would not require those actions.
Difference Between the Proposed AD
and the Canadian Airworthiness
Directive
Canadian airworthiness directive CF–
2004–18R1, recommends replacing the
main fitting of the MLG with a new
main fitting having a new part number
by June 2007, which is 27 months after
the effective date of the Canadian
airworthiness directive. We find that a
compliance time of within 15 months
after the effective date of this proposed
AD would allow us to come close to the
compliance date of June 2007, and
represents an appropriate interval of
time for affected airplanes to continue to
operate without compromising safety.
This difference has been coordinated
with TCCA.
Clarification of Inspection Language
Bombardier Alert Service Bulletin
A601R–32–099, Revision B, specifies
that operators should do a visual
inspection for cracks of the inboard and
outboard sides of the main fitting of the
MLG; and a visual inspection for sealant
damage or corrosion around the forward
bushing of the left and right main
fittings of the MLG. The Canadian
airworthiness directive refers to this
inspection as a ‘‘detailed visual
inspection.’’ In this proposed AD we
refer to this inspection as a ‘‘detailed
inspection.’’ Note 1 of this proposed AD
defines this inspection.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD. There
are approximately 201 U.S.-registered
airplanes. The average labor rate is $80
per hour.
ESTIMATED COSTS
Work
hours
Action
Detailed inspection for cracks of the main fitting (required by AD 2004–20–09).
Detailed inspection for sealant damage of the bushing
(required by AD 2004–20–09).
Ultrasonic inspection for cracks of the main fittings (required by AD 2004–20–09).
Replacement (new proposed action) ..............................
Parts
Cost per airplane
1
N/A
$80, per inspection cycle ...
1
N/A
$80, per inspection cycle ...
1
N/A
$80, per inspection cycle ...
56
$105,732
$110,212 ............................
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Authority for This Rulemaking
Regulatory Findings
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.
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.
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Fleet cost
$16,080, per inspection
cycle.
$16,080, per inspection
cycle.
$16,080, per inspection
cycle.
$22,152,612.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
Federal Register / Vol. 71, No. 133 / Wednesday, July 12, 2006 / Proposed Rules
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–13814 (69 FR
59790, October 6, 2004) and adding the
following new airworthiness directive
(AD):
Bombardier, Inc. (Formerly Canadair):
Docket No. FAA–2005–22559;
Directorate Identifier 2005–NM–076–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
August 11, 2006.
main landing gear (MLG) main fittings,
having part number (P/N) 601R85001–3 or –4
(Messier-Dowty P/N 17064–101, –102, –103,
or –104).
Unsafe Condition
(d) This AD results from a report of a
cracked main fitting of the MLG. We are
issuing this AD to detect and correct fatigue
cracking of the main fitting of the MLG and
consequent failure of the main fitting, which
could result in the collapse of the MLG.
Affected ADs
(b) This AD supersedes AD 2004–20–09.
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.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2B19 (Regional Jet Series 100 & 440)
airplanes, certificated in any category; serial
numbers 7003 through 7067 inclusive, and
7069 through 8999 inclusive; equipped with
Service Bulletin
(f) Unless otherwise specified in this AD,
the term ‘‘service bulletin,’’ as used in this
AD, means the Accomplishment Instructions
of Bombardier Alert Service Bulletin A601R–
32–099, including Appendices A, B, and D,
and excluding Appendix C, dated September
15, 2004; or Bombardier Alert Service
Bulletin A601R–32–099, Revision A,
including Appendices A, B, and D, and
excluding Appendix C, dated December 13,
2004; or Bombardier Alert Service Bulletin
A601R–32–099, Revision B, dated June 16,
2005, including Appendices A, B, and D, and
excluding Appendix C, Revision A, dated
December 13, 2004.
(1) After the effective date of this AD, only
Revision B of the service bulletin may be
used.
(2) Although the service bulletin specifies
to submit certain information to the airplane
manufacturer and to return cracked main
fittings to the supplier, this AD does not
include those requirements.
Restatement of the Requirements of AD
2004–20–09
Initial Inspections at New Reduced
Compliance Times
(g) Do the actions in Table 1 of this AD.
TABLE 1.—INITIAL INSPECTION THRESHOLDS AT NEW REDUCED COMPLIANCE TIMES
Do the following in Column 1—
At the earlier of the times specified in Column 2 or Column 3—
Column 1—
Column 2—The latest of—
Column 3—The latest of—
(1) A detailed inspection for cracks of the inboard and outboard sides of the main fitting
of the MLG between the pintle pin trunnion
and the radius of the shock strut lug, in accordance with Part A of the service bulletin.
(i)(A) Before the accumulation of 8,000 total
flight cycles since the main fitting of the
MLG was new.
(B) Within 8,000 flight cycles since the last
overhaul of the MLG done before the effective date of this AD.
(C) Within 50 flight cycles after October 21,
2004 (the effective date of AD 2004–20–09).
(i)(A) Before the accumulation of 8,000 total
flight cycles since the main fitting of the
MLG was new.
(B) Within 8,000 flight cycles since the last
overhaul of the MLG done before the effective date of this AD.
(C) Within 500 flight cycles after October 21,
2004.
(i)(A) Before the accumulation of 8,000 total
flight cycles since the main fitting of the
MLG was new.
(B) Within 8,000 flight cycles, since the last
overhaul of the MLG done before the effective date of this AD.
(C) Within 500 flight cycles after October 21,
2004.
(ii)(A) Within 48 months since the main fitting
of the MLG was new.
(B) Within 48 months since the last overhaul
of the MLG done before the effective date
of this AD.
(C) Within 50 flight cycles after the effective
date of this AD.
(2) A detailed inspection for sealant damage or
corrosion around the forward bushing of the
left and right main fittings of the MLG, in accordance with Part B of the service bulletin.
(3) An ultrasonic inspection for cracks of the left
and right main fittings of the MLG, in accordance with Part C of the service bulletin.
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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 mirror, magnifying
lenses, etc., may be necessary. Surface
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cleaning and elaborate procedures may be
required.’’
Repetitive Inspections
(h) Repeat the inspections in paragraph (g)
of this AD thereafter at the applicable
interval in paragraph (h)(1) or (h)(2) of this
AD, until the terminating action required by
paragraph (l) of this AD is accomplished.
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(ii)(A) Within 48 months since the main fitting
of the MLG was new.
(B) Within 48 months since the last overhaul
of the MLG done before the effective date
of this AD.
(C) Within 500 flight cycles or 6 months after
the effective date of this AD, whichever occurs first.
(ii)(A) Within 48 months since the main fitting
of the MLG was new.
(B) Within 48 months since the last overhaul
of the MLG done before the effective date
of this AD.
(C) Within 500 flight cycles or 6 months after
the effective date of this AD, whichever occurs first.
(1) For airplanes on which the applicable
initial inspection in paragraph (g) of this AD
has been done before the effective date of this
AD, do the next inspection at the applicable
interval in Table 2 of this AD.
(2) For airplanes on which the applicable
initial inspection in paragraph (g) of this AD
has not been done before the effective date
of this AD, repeat the inspection at the
applicable interval in Table 2 of this AD.
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TABLE 2.—REPETITIVE INSPECTIONS AT NEW INTERVALS
For the inspection required by—
Repeat at intervals not to
exceed—
Until the action required by—
(3) Paragraph (g)(1) of this AD ..........................
5 days ..............................................................
(4) Paragraph (g)(2) of this AD ..........................
500 flight cycles or 6 months, whichever occurs first.
5,000 flight cycles or 30 months, whichever
occurs first, except as required by paragraph (j)(2) of this AD.
Paragraph (g)(3) of this AD is done, unless
required by paragraph (j) of this AD.
Paragraph (j)(2) of this AD is done.
(5) Paragraph (g)(3) of this AD ..........................
Corrective Actions
(i) If there is an indication of a crack during
any inspection required by paragraph (g)(1),
(h)(3), or (j)(1) of this AD, before further
flight, do the actions specified in paragraph
(i)(1) or (i)(2) of this AD in accordance with
Part A of the service bulletin; or do the
terminating action required by paragraph (l)
of this AD.
(1) Replace the cracked main fitting of the
MLG with a new or serviceable main fitting.
(2) Do an eddy current inspection to verify
whether there is a crack. If there is a crack,
replace the cracked main fitting of the MLG
with a new or serviceable main fitting.
(None).
(j) If any sealant damage or corrosion is
found during any inspection required by
either paragraph (g)(2) or (h)(4) of this AD, do
the actions specified in Table 3 of this AD
in accordance with Part B of the service
bulletin, until the terminating action required
by paragraph (l) of this AD is accomplished.
TABLE 3.—CORRECTIVE ACTIONS FOR SEALANT DAMAGE OR CORROSION
Do the inspection specified in—
Within—
Repeat at intervals not to
exceed—
Until the action specified in—
(1) Paragraph (g)(1) of this AD .......
5 days after doing the inspection
required by (g)(2) or (h)(4) of
this AD, as applicable.
500 flight cycles after doing the
inspection required by paragraph (g)(2) or (h)(4) of this
AD, as applicable.
5 days ...........................................
Paragraph (j)(2) or (l) of this AD
is done.
500 flight cycles ...........................
Paragraph (l) of this AD is done.
(2) Paragraph (g)(3) of this AD .......
(k) If there is an indication of a crack
during any inspection required by paragraph
(g)(3) or (h)(5) of this AD, before further
flight, replace the cracked main fitting of the
MLG with a new or serviceable main fitting
in accordance with Part C of the service
bulletin; or do the terminating action
required by paragraph (l) of this AD.
New Requirement of This AD
Terminating Action—Replacement
(l) Within 15 months after the effective
date of this AD, replace both main fittings of
the MLG with new main fittings having new
part numbers, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 601R–32–093, Revision B,
dated July 14, 2005. Doing this replacement
terminates all requirements of paragraphs (g),
(h), (i), (j), and (k) of this AD.
Note 2: Bombardier Service Bulletin 601R–
32–093, Revision B, refers to Messier-Dowty
Service Bulletin M–DT SB17002–32–24,
dated October 9, 2003; and Messier-Dowty
Service Bulletin M–DT SB17002–32–25,
Revision 1, dated October 17, 2003; as
additional sources of service information for
replacing the MLG main fitting.
Actions Accomplished in Accordance With
Earlier Issues of Service Bulletin
(m) Actions done before the effective date
of this AD in accordance with the service
bulletins listed in Table 4 of this AD are
acceptable for compliance with the
corresponding action specified in this AD.
TABLE 4.—EARLIER ISSUES OF SERVICE BULLETINS
Revision
level
Bombardier Service Bulletin 601R–32–093 ............................................................................................
Bombardier Service Bulletin 601R–32–093 ............................................................................................
wwhite on PROD1PC61 with PROPOSALS
Service bulletin
Original ........
A ..................
Parts Installation
(n) As of the effective date of this AD, no
person may install a main fitting of the MLG,
Bombardier P/N 601R85001–3 or
601R85001–4; also referred to as MessierDowty P/N 17064–101, 17064–102, 17064–
103, or 17064–104; on any airplane.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, New York Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
VerDate Aug<31>2005
18:09 Jul 11, 2006
Jkt 208001
Date
October 17, 2003.
September 21, 2004.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on July 6,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–10913 Filed 7–11–06; 8:45 am]
Related Information
BILLING CODE 4910–13–P
(p) Canadian airworthiness directive CF–
2004–18R1, dated September 21, 2005, also
addresses the subject of this AD.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
E:\FR\FM\12JYP1.SGM
12JYP1
]]>Agencies
[Federal Register Volume 71, Number 133 (Wednesday, July 12, 2006)]
[Proposed Rules]
[Pages 39237-39241]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-10913]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22559; Directorate Identifier 2005-NM-076-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. The existing AD currently
requires repetitive inspections for cracks, sealant damage, and
corrosion of the main fittings of the main landing gear (MLG), and
corrective actions if necessary. This proposed AD would reduce the
compliance times for inspecting certain low-utilization airplanes, and
provide a terminating action for the repetitive inspections. This
proposed AD results from a report of a cracked main fitting of the MLG.
We are proposing this AD to detect and correct fatigue cracking of the
main fitting of the MLG and consequent failure of the main fitting,
which could result in the collapse of the MLG.
DATES: We must receive comments on this proposed AD by August 11, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7302; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22559;
Directorate Identifier 2005-NM-076-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
[[Page 39238]]
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
(DMS) receives them.
Discussion
On September 27, 2004, we issued AD 2004-20-09, amendment 39-13814
(69 FR 59790, October 6, 2004), for certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes. That AD requires
repetitive inspections for cracks, sealant damage, and corrosion of the
main fittings of the main landing gear (MLG), and corrective actions if
necessary. That AD resulted from a report of a cracked main fitting of
the MLG. We issued that AD to detect and correct fatigue cracking of
the main fitting of the MLG and consequent failure of the main fitting,
which could result in the collapse of the MLG.
Actions Since Existing AD Was Issued
Since we issued AD 2004-20-09, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, has revised
its parallel airworthiness directive, and issued Canadian airworthiness
directive CF-2004-18R1, dated September 21, 2005. (Canadian emergency
airworthiness directive CF-2004-18, dated September 16, 2004, was
referenced as the parallel airworthiness directive in AD 2004-20-09.)
This revision to the Canadian airworthiness directive specifies the
revised inspection intervals in Revision B of Bombardier Alert Service
Bulletin A601R-32-099, dated June 16, 2005. (Alert Service Bulletin
A601R-32-099, dated September 15, 2004, was referenced in AD 2004-20-09
as the appropriate source of service information for accomplishing the
required actions.) The revised inspection intervals apply only to
certain low-utilization airplanes, and specify that these airplanes
comply with the actions in AD 2004-20-09 sooner than currently required
by that AD. This revision to the Canadian airworthiness directive also
specifies replacement of the main fittings of the MLG with new
fittings, which terminates the repetitive inspections.
In addition, the preamble to AD 2004-20-09 explains that we
consider the requirements of AD 2004-20-09 to be ``interim action'' and
that we are considering further rulemaking. We now have determined that
further rulemaking is indeed necessary, and this proposed AD follows
from that determination.
Other Relevant Rulemaking
On November 16, 2001, we issued AD 2001-22-09 (amendment 39-12488,
66 FR 58931, November 26, 2001), for certain Bombardier Model CL-600-
2B19 series airplanes. That AD requires repetitive eddy current
inspections for cracking of the MLG main fittings, and replacement with
a new or serviceable MLG if necessary. That AD also requires servicing
the MLG shock struts; inspecting the MLG shock struts for nitrogen
pressure, visible chrome dimension, and oil leakage; and performing
corrective actions if necessary. That AD was prompted by reports of
premature failure of the MLG main fitting. We issued that AD to prevent
failure of the MLG main fitting, which could result in collapse of the
MLG upon landing.
On June 30, 2004, we issued AD 2004-14-16 (amendment 39-13725, 69
FR 41421, July 9, 2004), for certain Bombardier Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes. That AD requires repetitive
detailed and eddy current inspections on the main fittings of the MLGs
to detect discrepancies, and related investigative/corrective actions
if necessary. That AD also requires servicing the shock strut of the
MLGs; inspecting the shock strut of the MLGs for nitrogen pressure,
visible chrome dimension, and oil leakage; and servicing any discrepant
strut. That AD resulted from results of a stress analysis that revealed
that certain main fittings of the MLGs are susceptible to premature
cracking, starting in the radius of the upper lug. We issued that AD to
detect and correct premature cracking of the main fittings of the MLGs,
which could result in failure of the fittings and consequent collapse
of the MLGs during landing.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A601R-32-099, Revision
B, dated June 16, 2005, including Appendices A through D, Revision A,
dated December 13, 2004. The procedures in this service bulletin are
essentially the same as the procedures in the original issue of
Bombardier Alert Service Bulletin A601R-32-099, including Appendices A
through D, dated September 15, 2004, which was cited as the appropriate
source of service information in AD 2004-20-09.
Bombardier has also issued Service Bulletin 601R-32-093, Revision
B, dated July 14, 2005. This service bulletin describes procedures for
replacing the main fitting of the MLG with a new main fitting having a
new part number.
TCCA mandated the service information and issued Canadian
airworthiness directive CF-2004-18R1, dated September 21, 2005, to
ensure the continued airworthiness of these airplanes in Canada. TCCA
considers Bombardier Service Bulletin 601R-32-093 to be terminating
action for the repetitive inspections in Bombardier Alert Service
Bulletin A601R-32-099.
Bombardier Service Bulletin 601R-32-093, Revision B, refers to
Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated October 9,
2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-25, Revision
1, dated October 17, 2003; as additional sources of service information
for replacing the MLG main fitting. Operators should note that P/Ns
601R85001-81/82 (Messier-Dowty P/Ns 17064-105/106), as specified in
Bombardier Service Bulletin 601R-32-093, Revision B, and Messier-Dowty
Service Bulletin M-DT SB17002-32-25, Revision 1, require different
inspections in accordance with AD 2004-14-16. We are considering
additional rulemaking to supersede that AD to require replacement of
the noted part numbers at a different compliance time.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the
[[Page 39239]]
Federal Aviation Regulations (14 CFR 21.29) and the applicable
bilateral airworthiness agreement. Pursuant to this bilateral
airworthiness agreement, TCCA has kept the FAA informed of the
situation described above. We have examined TCCA's findings, evaluated
all pertinent information, and determined that AD action is necessary
for airplanes of this type design that are certificated for operation
in the United States.
This proposed AD would supersede AD 2004-20-09. This proposed AD
would continue to require repetitive inspections for cracks, sealant
damage, and corrosion of the main fittings of the MLG, and corrective
actions if necessary. This proposed AD also would reduce the compliance
times for inspecting certain affected airplanes, and require that
operators do the actions in accordance with a new revision of the
service bulletin, described previously, except as discussed under
``Difference Between the Proposed AD and Bombardier Alert Service
Bulletin A601R-32-099.''
Difference Between the Proposed AD and Bombardier Alert Service
Bulletin A601R-32-099
Although the Accomplishment Instructions of the Bombardier Alert
Service Bulletin A601R-32-099, Revision B, describe procedures for
reporting crack indications, returning cracked parts to Messier-Dowty,
and submitting a comment sheet related to service bulletin quality and
a sheet recording compliance with the service bulletin, this AD, like
Canadian airworthiness directive CF-2004-18R1, would not require those
actions.
Difference Between the Proposed AD and the Canadian Airworthiness
Directive
Canadian airworthiness directive CF-2004-18R1, recommends replacing
the main fitting of the MLG with a new main fitting having a new part
number by June 2007, which is 27 months after the effective date of the
Canadian airworthiness directive. We find that a compliance time of
within 15 months after the effective date of this proposed AD would
allow us to come close to the compliance date of June 2007, and
represents an appropriate interval of time for affected airplanes to
continue to operate without compromising safety. This difference has
been coordinated with TCCA.
Clarification of Inspection Language
Bombardier Alert Service Bulletin A601R-32-099, Revision B,
specifies that operators should do a visual inspection for cracks of
the inboard and outboard sides of the main fitting of the MLG; and a
visual inspection for sealant damage or corrosion around the forward
bushing of the left and right main fittings of the MLG. The Canadian
airworthiness directive refers to this inspection as a ``detailed
visual inspection.'' In this proposed AD we refer to this inspection as
a ``detailed inspection.'' Note 1 of this proposed AD defines this
inspection.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD. There are approximately 201 U.S.-
registered airplanes. The average labor rate is $80 per hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Detailed inspection for cracks of 1 N/A $80, per inspection $16,080, per
the main fitting (required by AD cycle. inspection cycle.
2004-20-09).
Detailed inspection for sealant 1 N/A $80, per inspection $16,080, per
damage of the bushing (required by cycle. inspection cycle.
AD 2004-20-09).
Ultrasonic inspection for cracks of 1 N/A $80, per inspection $16,080, per
the main fittings (required by AD cycle. inspection cycle.
2004-20-09).
Replacement (new proposed action)... 56 $105,732 $110,212............... $22,152,612.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 39240]]
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-13814 (69 FR
59790, October 6, 2004) and adding the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2005-22559;
Directorate Identifier 2005-NM-076-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by August 11, 2006.
Affected ADs
(b) This AD supersedes AD 2004-20-09.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category;
serial numbers 7003 through 7067 inclusive, and 7069 through 8999
inclusive; equipped with main landing gear (MLG) main fittings,
having part number (P/N) 601R85001-3 or -4 (Messier-Dowty P/N 17064-
101, -102, -103, or -104).
Unsafe Condition
(d) This AD results from a report of a cracked main fitting of
the MLG. We are issuing this AD to detect and correct fatigue
cracking of the main fitting of the MLG and consequent failure of
the main fitting, which could result in the collapse of the MLG.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin
(f) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in this AD, means the Accomplishment
Instructions of Bombardier Alert Service Bulletin A601R-32-099,
including Appendices A, B, and D, and excluding Appendix C, dated
September 15, 2004; or Bombardier Alert Service Bulletin A601R-32-
099, Revision A, including Appendices A, B, and D, and excluding
Appendix C, dated December 13, 2004; or Bombardier Alert Service
Bulletin A601R-32-099, Revision B, dated June 16, 2005, including
Appendices A, B, and D, and excluding Appendix C, Revision A, dated
December 13, 2004.
(1) After the effective date of this AD, only Revision B of the
service bulletin may be used.
(2) Although the service bulletin specifies to submit certain
information to the airplane manufacturer and to return cracked main
fittings to the supplier, this AD does not include those
requirements.
Restatement of the Requirements of AD 2004-20-09
Initial Inspections at New Reduced Compliance Times
(g) Do the actions in Table 1 of this AD.
Table 1.--Initial Inspection Thresholds at New Reduced Compliance Times
------------------------------------------------------------------------
Do the following in Column At the earlier of the times specified in
1-- Column 2 or Column 3--
------------------------------------------------------------------------
Column 2--The latest Column 3--The latest
Column 1-- of-- of--
------------------------------------------------------------------------
(1) A detailed inspection (i)(A) Before the (ii)(A) Within 48
for cracks of the inboard accumulation of months since the
and outboard sides of the 8,000 total flight main fitting of the
main fitting of the MLG cycles since the MLG was new.
between the pintle pin main fitting of the (B) Within 48 months
trunnion and the radius of MLG was new. since the last
the shock strut lug, in (B) Within 8,000 overhaul of the MLG
accordance with Part A of flight cycles since done before the
the service bulletin. the last overhaul effective date of
of the MLG done this AD.
before the (C) Within 50 flight
effective date of cycles after the
this AD. effective date of
(C) Within 50 flight this AD.
cycles after
October 21, 2004
(the effective date
of AD 2004-20-09).
(2) A detailed inspection (i)(A) Before the (ii)(A) Within 48
for sealant damage or accumulation of months since the
corrosion around the 8,000 total flight main fitting of the
forward bushing of the left cycles since the MLG was new.
and right main fittings of main fitting of the (B) Within 48 months
the MLG, in accordance with MLG was new. since the last
Part B of the service (B) Within 8,000 overhaul of the MLG
bulletin. flight cycles since done before the
the last overhaul effective date of
of the MLG done this AD.
before the (C) Within 500
effective date of flight cycles or 6
this AD. months after the
(C) Within 500 effective date of
flight cycles after this AD, whichever
October 21, 2004. occurs first.
(3) An ultrasonic inspection (i)(A) Before the (ii)(A) Within 48
for cracks of the left and accumulation of months since the
right main fittings of the 8,000 total flight main fitting of the
MLG, in accordance with cycles since the MLG was new.
Part C of the service main fitting of the (B) Within 48 months
bulletin. MLG was new. since the last
(B) Within 8,000 overhaul of the MLG
flight cycles, done before the
since the last effective date of
overhaul of the MLG this AD.
done before the (C) Within 500
effective date of flight cycles or 6
this AD. months after the
(C) Within 500 effective date of
flight cycles after this AD, whichever
October 21, 2004. occurs first.
------------------------------------------------------------------------
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(h) Repeat the inspections in paragraph (g) of this AD
thereafter at the applicable interval in paragraph (h)(1) or (h)(2)
of this AD, until the terminating action required by paragraph (l)
of this AD is accomplished.
(1) For airplanes on which the applicable initial inspection in
paragraph (g) of this AD has been done before the effective date of
this AD, do the next inspection at the applicable interval in Table
2 of this AD.
(2) For airplanes on which the applicable initial inspection in
paragraph (g) of this AD has not been done before the effective date
of this AD, repeat the inspection at the applicable interval in
Table 2 of this AD.
[[Page 39241]]
Table 2.--Repetitive Inspections at New Intervals
------------------------------------------------------------------------
For the inspection required Repeat at intervals Until the action
by-- not to exceed-- required by--
------------------------------------------------------------------------
(3) Paragraph (g)(1) of this 5 days.............. Paragraph (g)(3) of
AD. this AD is done,
unless required by
paragraph (j) of
this AD.
(4) Paragraph (g)(2) of this 500 flight cycles or Paragraph (j)(2) of
AD. 6 months, whichever this AD is done.
occurs first.
(5) Paragraph (g)(3) of this 5,000 flight cycles (None).
AD. or 30 months,
whichever occurs
first, except as
required by
paragraph (j)(2) of
this AD.
------------------------------------------------------------------------
Corrective Actions
(i) If there is an indication of a crack during any inspection
required by paragraph (g)(1), (h)(3), or (j)(1) of this AD, before
further flight, do the actions specified in paragraph (i)(1) or
(i)(2) of this AD in accordance with Part A of the service bulletin;
or do the terminating action required by paragraph (l) of this AD.
(1) Replace the cracked main fitting of the MLG with a new or
serviceable main fitting.
(2) Do an eddy current inspection to verify whether there is a
crack. If there is a crack, replace the cracked main fitting of the
MLG with a new or serviceable main fitting.
(j) If any sealant damage or corrosion is found during any
inspection required by either paragraph (g)(2) or (h)(4) of this AD,
do the actions specified in Table 3 of this AD in accordance with
Part B of the service bulletin, until the terminating action
required by paragraph (l) of this AD is accomplished.
Table 3.--Corrective Actions for Sealant Damage or Corrosion
----------------------------------------------------------------------------------------------------------------
Repeat at intervals not Until the action
Do the inspection specified in-- Within-- to exceed-- specified in--
----------------------------------------------------------------------------------------------------------------
(1) Paragraph (g)(1) of this AD.. 5 days after doing the 5 days.................. Paragraph (j)(2) or (l)
inspection required by of this AD is done.
(g)(2) or (h)(4) of this
AD, as applicable.
(2) Paragraph (g)(3) of this AD.. 500 flight cycles after 500 flight cycles....... Paragraph (l) of this AD
doing the inspection is done.
required by paragraph
(g)(2) or (h)(4) of this
AD, as applicable.
----------------------------------------------------------------------------------------------------------------
(k) If there is an indication of a crack during any inspection
required by paragraph (g)(3) or (h)(5) of this AD, before further
flight, replace the cracked main fitting of the MLG with a new or
serviceable main fitting in accordance with Part C of the service
bulletin; or do the terminating action required by paragraph (l) of
this AD.
New Requirement of This AD
Terminating Action--Replacement
(l) Within 15 months after the effective date of this AD,
replace both main fittings of the MLG with new main fittings having
new part numbers, in accordance with the Accomplishment Instructions
of Bombardier Service Bulletin 601R-32-093, Revision B, dated July
14, 2005. Doing this replacement terminates all requirements of
paragraphs (g), (h), (i), (j), and (k) of this AD.
Note 2: Bombardier Service Bulletin 601R-32-093, Revision B,
refers to Messier-Dowty Service Bulletin M-DT SB17002-32-24, dated
October 9, 2003; and Messier-Dowty Service Bulletin M-DT SB17002-32-
25, Revision 1, dated October 17, 2003; as additional sources of
service information for replacing the MLG main fitting.
Actions Accomplished in Accordance With Earlier Issues of Service
Bulletin
(m) Actions done before the effective date of this AD in
accordance with the service bulletins listed in Table 4 of this AD
are acceptable for compliance with the corresponding action
specified in this AD.
Table 4.--Earlier Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Service Bulletin 601R-32-093 Original................... October 17, 2003.
Bombardier Service Bulletin 601R-32-093 A.......................... September 21, 2004.
----------------------------------------------------------------------------------------------------------------
Parts Installation
(n) As of the effective date of this AD, no person may install a
main fitting of the MLG, Bombardier P/N 601R85001-3 or 601R85001-4;
also referred to as Messier-Dowty P/N 17064-101, 17064-102, 17064-
103, or 17064-104; on any airplane.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, New York Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(p) Canadian airworthiness directive CF-2004-18R1, dated
September 21, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on July 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-10913 Filed 7-11-06; 8:45 am]
BILLING CODE 4910-13-P
