Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) Airplanes, Model CL-600-2D15 (Regional Jet Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900) Airplanes, 11335-11341 [06-2159]
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Empresa Brasileira de Aeronautica S.A.
(EMBRAER): Docket No. FAA–2006–
24076; Directorate Identifier 2006–NM–
015–AD.
(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.
Related Information
(i) Brazilian airworthiness directive 2005–
12–03 , effective January 19, 2006, also
addresses the subject of this AD.
Issued in Renton, Washington, on February
22, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2158 Filed 3–6–06; 8:45 am]
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Comments Due Date
(a) The FAA must receive comments on
this AD action by April 6, 2006.
DEPARTMENT OF TRANSPORTATION
Affected ADs
(b) None.
14 CFR Part 39
Federal Aviation Administration
Applicability
(c) This AD applies to EMBRAER Model
EMB–120, –120ER, –120FC, –120QC, and
–120RT airplanes as identified in EMBRAER
Service Bulletin 120–36–0016, Revision 01,
dated October 4, 2004; certificated in any
category.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are proposing this AD to prevent a potential
source of ignition near a fuel tank, which, in
combination with flammable fuel vapors,
could result in a fuel tank explosion and
consequent loss of the airplane.
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.
Replacing the Shut-Off and Crossbleed
Valves
(f) Within 5,000 flight hours after the
effective date of this AD, replace the shut-off
and crossbleed valves of the bleed air system
with new shut-off and crossbleed valves
having hermetically sealed switches, in
accordance with EMBRAER Service Bulletin
120–36–0016, Revision 01, dated October 4,
2004.
sroberts on PROD1PC70 with PROPOSALS
Parts Installation
(g) As of the effective date of this AD, no
person may install any shut-off or crossbleed
valve of the bleed air system with any shutoff or crossbleed valve that does not have
hermetically sealed switches.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
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[Docket No. FAA–2006–24074; Directorate
Identifier 2005–NM–213–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2C10 (Regional Jet
Series 700, 701, & 702) Airplanes,
Model CL–600–2D15 (Regional Jet
Series 705) Airplanes, and Model CL–
600–2D24 (Regional Jet Series 900)
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–600–2C10
(Regional Jet Series 700 & 701) and CL–
600–2D24 (Regional Jet Series 900)
series airplanes. The existing AD
currently requires repetitive detailed
inspections for cracking or deformation,
or pulled or missing fasteners, on the
lower panel of the left- and right-hand
main landing gear (MLG) doors, as
applicable, and corrective actions if
necessary. This proposed AD would
reduce the repetitive inspection interval
for certain airplanes. This proposed AD
also adds airplanes to the applicability.
This proposed AD results from a report
of a MLG door departing from an
airplane. We are proposing this AD to
prevent failure of the lower panel of the
MLG door, the lower panel’s departure
from the airplane, and consequent
damage to airplane structure, which
could adversely affect the airplane’s
continued safe flight and landing.
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We must receive comments on
this proposed AD by April 6, 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:
DATES:
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 in the
ADDRESSES section. Include the docket
number ‘‘Docket No. FAA–2006–24074;
Directorate Identifier 2005–NM–213–
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 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 that 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,
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may 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 receives them.
sroberts on PROD1PC70 with PROPOSALS
Discussion
On October 23, 2003, we issued AD
2003–19–51, amendment 39–13353 (68
FR 61615, October 29, 2003), for certain
Bombardier Model CL–600–2C10
(Regional Jet Series 700 & 701) and CL–
600–2D24 (Regional Jet Series 900)
series airplanes (originally issued
September 17, 2003, as an emergency
airworthiness directive). That AD
requires repetitive detailed inspections
for cracking or deformation, or pulled or
missing fasteners, on the lower panel of
the left- and right-hand main landing
gear (MLG) doors, as applicable, and
corrective actions if necessary. That AD
resulted from a report of a lower panel
of the door of the right-hand MLG of a
Model CL–600–2C10 series airplane
departing the airplane during landing.
We issued that AD to prevent failure of
the lower panel of the MLG door, the
lower panel’s departure from the
airplane, and consequent damage to
airplane structure, which could
adversely affect the airplane’s continued
safe flight and landing.
Actions Since Existing AD Was Issued
Since we issued AD 2003–19–51,
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
inboard MLG door departed from an
airplane affected by the existing AD.
The airplane was operating under an
alternative means of compliance
(AMOC) to the TCCA airworthiness
directive that allowed extension of the
repetitive interval when certain repairs
or modifications where done. The TCCA
determined that the inspection intervals
should be reduced for those airplanes.
The TCCA also determined that
inspections are needed for additional
airplanes affected by the identified
unsafe condition.
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16:19 Mar 06, 2006
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Relevant Service Information
Bombardier has issued Alert Service
Bulletin A670BA–32–016, Revision A,
dated June 7, 2005, including
Appendices A and B, dated June 2,
2005. The service bulletin describes
procedures for doing repetitive
inspections of the left- and right-hand
inboard MLG doors for damage, and
corrective actions if necessary. The
inspections include doing a general
visual inspection of the skin for damage
such as loose, pulled, or missing
fasteners, missing paint, or scratches
around the rivet heads; and a detailed
inspection of the inboard MLG door for
cracking or deformation. The corrective
actions include replacing the MLG door
with a new or repaired MLG door.
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–2003–23R2,
dated July 27, 2005, to ensure the
continued airworthiness of these
airplanes in Canada.
FAA’s Determination and Requirements
of the Proposed AD
These airplane models 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 2003–19–51. This proposed AD
would retain certain requirements of AD
2003–19–51 and would require
accomplishing the actions specified in
the service bulletin described
previously, except as discussed under
‘‘Differences Between the Proposed AD
and the Service Bulletin/Canadian
Airworthiness Directive.’’
Differences Among the Proposed AD
and the Service Bulletin/Canadian
Airworthiness Directive
Although Bombardier Alert Service
Bulletin A670BA–32–016, Revision A,
dated June 7, 2005, and the Canadian
airworthiness directive specify to
submit certain information to the
manufacturer, this proposed AD does
not include that requirement.
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Bombardier Alert Service Bulletin
A670BA–32–016, Revision A, dated
June 7, 2005, includes a note in the
Accomplishment Instructions to inform
operators to contact Bombardier if no
accurate generic repair engineering
order is available when accomplishing
the repair. However, this proposed AD
would require doing the repair using a
method that we or TCCA (or its
delegated agent) approve. In light of the
type of repair that would be required to
address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair we or TCCA (or its delegated
agent) approve would be acceptable for
compliance with this proposed AD. The
Canadian airworthiness directive
references the limitations specified in
the configuration deviation list (CDL)
for airplanes that remove damaged
inboard MLG doors. The information in
the CDL has been revised since we
issued AD 2003–19–51. For airplanes on
which the door(s) have been removed in
accordance with AD 2003–19–51, we
would require revising the CDL to the
latest revision.
Change to Existing AD
This proposed AD would retain
certain requirements of AD 2003–19–51.
Since AD 2003–19–51 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 2003–19–51
paragraph
paragraph
paragraph
paragraph
(a)
(b)
(c)
(d)
............
............
............
............
Corresponding
requirement in this
proposed AD
paragraph
paragraph
paragraph
paragraph
(f).
(g).
(h).
(i).
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Explanation of Change to Applicability
We have revised the applicability of
the existing AD to identify model
designations as published in the most
recent type certificate data sheet for the
affected models.
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Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
Interim Action
identified, we may consider further
rulemaking then.
We consider this proposed AD
interim action. If final action is later
11337
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
Work
hours
Action
Average
labor rate
per hour
Number of
U.S.-registered
airplanes
Cost per
airplane
Inspections (required by AD 2003–19–
51).
Inspections (new proposed action) ......
1
$65
$65, per inspection cycle ....................
83
1
65
$65, per inspection cycle ....................
213
Revision (new proposed action) ..........
1
65
$65, if necessary .................................
213
sroberts on PROD1PC70 with PROPOSALS
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
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Jkt 208001
Fleet cost
$5,395, per inspection
cycle.
$13,854, per inspection
cycle.
Up to $13,854.
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
airplane, and consequent damage to airplane
structure, which could adversely affect the
airplane’s continued safe flight and landing.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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.
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–13353 (68
FR 61615, October 29, 2003) and adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly Canadair):
Docket No. FAA–2006–24074;
Directorate Identifier 2005–NM–213–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 6, 2006.
Affected ADs
(b) This AD supersedes AD 2003–19–51.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2C10 (Regional Jet Series 700, 701,
& 702) airplanes, serial numbers (S/Ns) 10003
and subsequent; and Model CL–600–2D15
(Regional Jet Series 705) airplanes, and
Model CL–600–2D24 (Regional Jet Series
900) airplanes, S/Ns 15001 and subsequent;
certificated in any category.
Unsafe Condition
(d) This AD results from a report of a main
landing gear (MLG) door departing from an
airplane. We are issuing this AD to prevent
failure of the lower panel of the MLG door,
the lower panel’s departure from the
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Restatement of Requirements of AD 2003–
19–51
Initial Compliance Time
(f) For Model CL–600–2C10 (Regional Jet
series 700 & 701) series airplanes, S/Ns 10003
through 10999 inclusive; and Model CL–600–
2D24 (Regional Jet series 900) series
airplanes, S/Ns 15002 through 15990
inclusive: Perform the initial inspection
specified in paragraph (g) of this AD at the
applicable time specified in paragraph (f)(1)
or (f)(2) of this AD.
(1) For airplanes with fewer than 1,500
total flight cycles as of November 3, 2003,
(the effective date of AD 2003–19–51): Do the
inspections before the accumulation of 1,050
total flight cycles, or within 50 flight cycles
after the effective date of this AD, whichever
is later.
(2) For airplanes with 1,500 or more total
flight cycles as of November 3, 2003: Do the
inspections within 10 flight cycles after the
effective date of this AD.
Inspections
(g) For Model CL–600–2C10 (Regional Jet
series 700 & 701) series airplanes, S/Ns 10003
through 10999 inclusive; and Model CL–600–
2D24 (Regional Jet series 900) series
airplanes, S/Ns 15002 through 15990
inclusive: At the applicable time specified in
paragraph (f) of this AD, perform detailed
inspections of the lower panel, part number
(P/N) CC670–10520, of the left- and righthand MLG doors for the conditions and in
the areas specified in paragraphs (g)(1), (g)(2),
(g)(3), and (g)(4) of this AD; and Figures 1,
2, and 3 of this AD.
Note 1: 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,
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magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
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(1) Inspect the cross member, P/N CC670–
10572, of the MLG door lower panel for
cracking or deformation, in accordance with
Figure 2 of this AD.
(2) Inspect the inner skin, P/N CC670–
10577, of the MLG door lower panel at the
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Jkt 208001
cross member (P/N CC670–10572) for
cracking or deformation, or pulled or missing
fasteners, in accordance with Figure 2 of this
AD.
(3) Inspect the outer skin, P/N CC670–
10574, of the MLG door lower panel at the
cross member (P/N CC670–10572) for
cracking or deformation, or pulled or missing
PO 00000
fasteners, in accordance with Figure 2 of this
AD.
(4) Inspect the forward member, P/N
CC670–10570, and aft member, P/N CC670–
10571, of the MLG door lower panel, for
cracking or deformation, or pulled or missing
fasteners, in accordance with Figure 3 of this
AD. Figures 1 through 3 of this AD follow.
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11338
thereafter at intervals not to exceed 100 flight
cycles.
Repetitive Inspections
(h) If no cracking or deformation, or pulled
or missing fastener, as applicable, is found
during any inspection required by paragraph
(g) or (h) of this AD, repeat the inspections
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Corrective Actions
(i) If any cracking or deformation, or pulled
or missing fastener, as applicable, is found
during any inspection done in accordance
with paragraph (g) or (h) of this AD: Before
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further flight, accomplish paragraph (i)(1),
(i)(2), or (i)(3) of this AD.
(1) Repair the damage in accordance with
a method approved by either the Manager,
New York Aircraft Certification Office (ACO),
FAA; or Transport Canada Civil Aviation (or
its delegated agent); and accomplish
repetitive inspections in accordance with a
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EP07MR06.001</GPH>
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method and at a repetitive interval approved
by same.
(2) Replace the lower panel assembly, P/N
CC670–10520, of the affected MLG door with
a new or serviceable lower panel assembly
having the same P/N, in accordance with
Task Cards 32–12–01–000–801–A01 and 32–
12–01–400–801–A01 of the CRJ 700/900
Series Regional Jet Aircraft Maintenance
Manual; and repeat the inspections specified
in paragraph (g) of this AD at intervals not
to exceed 100 flight cycles.
(3) Remove the lower panel assembly, P/N
CC670–10520, of the affected MLG door, and
accomplish paragraph (i)(3)(i) or (i)(3)(ii), as
applicable.
(i) For Model CL600–2C10 (Regional Jet
series 700 & 701) series airplanes: Revise the
Configuration Deviation List (CDL),
Appendix 1, of the airplane flight manual
(AFM), to include the following limitations.
This may be accomplished by inserting a
copy of this AD into the CDL of the AFM.
‘‘For Model CL600–2C10 series airplanes:
If one or both door panel assemblies, part
number CC670–10520, is missing:
(1) Take-off Weight is reduced by 202.5 kg/
door, or 450 lb/door
(2) Enroute Climb Weight is reduced by
445.5 kg/door, or 990 lb/door
(3) Landing Weight is reduced by 202.5 kg/
door, or 450 lb/door
(4) Fuel Consumption is increased by
+3.42% on fuel used/door
(5) Cruise Airspeed is limited to not more
than 0.78 Mach.’’
(ii) For Model CL–600–2D24 (Regional Jet
series 900) series airplanes: Revise the CDL,
Appendix 1, of the AFM, to include the
following limitations. This may be
accomplished by inserting a copy of this AD
into the CDL of the AFM.
‘‘For Model CL600–2D24 series airplanes:
If one or both door panel assemblies, part
number CC670–10520, is missing:
(1) Take-off Weight is reduced by 245 kg/
door, or 540 lb/door
(2) Enroute Climb Weight is reduced by
551 kg/door, or 1,215 lb/door
(3) Landing Weight is reduced by 245 kg/
door, or 540 lb/door
(4) Fuel Consumption is increased by
+3.42% on fuel used/door
(5)Cruise Airspeed is limited to not more
than 0.78 Mach.’’
sroberts on PROD1PC70 with PROPOSALS
New Requirements of This AD
Inboard MLG Door Inspections
(j) For all airplanes on which an inspection
has not been done in accordance with
paragraph (g) of this AD on or before the
effective date of this AD: At the applicable
time specified in paragraph (j)(1) or (j)(2) of
this AD, do the inspections of the left- and
right-hand inboard MLG doors for damage in
accordance with Part A of the
Accomplishment Instructions of the
Bombardier Alert Service Bulletin A670BA–
32–016, Revision A, dated June 7, 2005,
including Appendix B, dated June 2, 2005,
excluding Appendix A, dated June 2, 2005.
Doing the inspections required by this
paragraph terminates the actions required by
paragraphs (f) through (i) of this AD.
(1) For airplanes that have accumulated
fewer than 1,500 total flight cycles as of the
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effective date of this AD: Before the
accumulation of 1,000 total flight cycles or
within 50 flight cycles after the effective date
of this AD, whichever occurs later.
(2) For airplanes that have accumulated
1,500 flight cycles or more as of the effective
date of this AD: Within 10 flight cycles after
the effective date of this AD.
(k) For all airplanes on which an
inspection has been done in accordance with
paragraph (g) of this AD on or before the
effective date of this AD and on which both
doors have not been removed in accordance
with paragraph (i)(3) of this AD: At the
applicable time specified in paragraph (k)(1)
or (k)(2) of this AD, do the inspections
specified in paragraph (j) of this AD; except
for airplanes on which one door has been
removed in accordance with paragraph (i)(3)
of this AD, do the inspections specified in
paragraph (j) of this AD for the door that has
not been removed. Doing the inspections
required by this paragraph terminates the
actions required by paragraphs (f) through (i)
of this AD.
(1) For airplanes that are not subject to an
approved alternative method of compliance
(AMOC) that extends the inspection interval
to 450 flight cycles: Within 100 flight cycles
since the last inspection done in accordance
with paragraph (g) of this AD.
(2) For airplanes that are subject to an
approved AMOC that extends the inspection
interval to 450 flight cycles: At the earlier of
the times specified in paragraph (k)(2)(i) and
(k)(2)(ii) of this AD:
(i) Within 450 flight cycles since the last
inspection done in accordance with
paragraph (g) of this AD.
(ii) Within 100 flight cycles since the last
inspection done in accordance with
paragraph (g) of this AD or within 50 cycles
after the effective date of this AD, whichever
occurs later.
(l) If no damage is found during any
inspection done in accordance with
paragraph (j) of this AD, repeat the
inspections specified in paragraph (j) of this
AD thereafter at intervals not to exceed 100
flight cycles.
Corrective Action—Replace or Remove MLG
Door
(m) If any damage is found during any
inspection done in accordance with
paragraph (j) of this AD, before further flight,
do the actions in paragraph (m)(1) or (m)(2)
of this AD. Repeat the inspections specified
in paragraph (j) of this AD thereafter at
intervals not to exceed 100 flight cycles.
(1) Replace the inboard MLG door with a
new or repaired door in accordance with Part
B of the Accomplishment Instructions of the
Bombardier Alert Service Bulletin A670BA–
32–016, Revision A, dated June 7, 2005,
including Appendix B, dated June 2, 2005,
excluding Appendix A, dated June 2, 2005;
except where the service bulletin specifies to
contact the manufacturer for repair if no
generic repair engineering order (REO) is
available, before further flight, repair using a
method approved by either the Manager,
New York Aircraft Certification Office (ACO),
FAA; or the Transport Canada Civil Aviation
(TCCA) (or its delegated agent).
(2) Remove the inboard MLG door in
accordance with Part B of the
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
Accomplishment Instructions of the
Bombardier Alert Service Bulletin A670BA–
32–016, Revision A, dated June 7, 2005,
including Appendix B, dated June 2, 2005,
excluding Appendix A, dated June 2, 2005;
and accomplish paragraph (m)(2)(i) or
(m)(2)(ii), as applicable.
(i) For Model CL–600–2C10 (Regional Jet
Series 700, 701, & 702) airplanes and Model
CL–600–2D15 (Regional Jet Series 705)
airplanes: Revise the Configuration Deviation
List (CDL), Appendix 1, of the airplane flight
manual (AFM), to include the following
limitations. This may be accomplished by
inserting a copy of this AD into the CDL of
the AFM. Remove any existing CDL
limitation required by paragraph (i)(3)(i) of
this AD from the AFM.
‘‘For Model CL–600–2C10 (Regional Jet
Series 700, 701, & 702) airplanes and Model
CL–600–2D15 (Regional Jet Series 705)
airplanes: If one or both door panel
assemblies, part number CC670–10520, is
missing:
(1) Take-off Weight is reduced by 202.5 kg/
door, or 450 lb/door
(2) Enroute Climb Weight is reduced by
445.5 kg/door, or 990 lb/door
(3) Landing Weight is reduced by 202.5 kg/
door, or 450 lb/door
(4) Fuel Consumption is increased by
+2.5% on fuel used/door
(5) Cruise Airspeed is limited to not more
than 0.78 Mach
(6) The climb ceiling obtained from the
Flight Planning and Cruise Control Manual
(FPCCM) must be reduced by 1,000 ft/door.’’
Note 2: When a statement with the
information specified in paragraph (m)(2)(i)
of this AD has been included in the general
revisions of the AFM, the general revisions
may be inserted into the AFM, and the copy
of this AD may be removed from the AFM.
(ii) For Model CL–600–2D24 (Regional Jet
Series 900) airplanes: Revise the CDL,
Appendix 1, of the AFM, to include the
following limitations. This may be
accomplished by inserting a copy of this AD
into the CDL of the AFM. Remove any
existing CDL limitation required by
paragraph (i)(3)(ii) of this AD from the AFM.
‘‘For Model CL–600–2D24 (Regional Jet
Series 900) airplanes: If one or both door
panel assemblies, part number CC670–10520,
is missing:
(1) Take-off Weight is reduced by 245 kg/
door, or 540 lb/door
(2) Enroute Climb Weight is reduced by
551 kg/door, or 1,215 lb/door
(3) Landing Weight is reduced by 245 kg/
door, or 540 lb/door
(4) Fuel Consumption is increased by
+2.5% on fuel used/door
(5)Cruise Airspeed is limited to not more
than 0.78 Mach
(6)The climb ceiling obtained from the
Flight Planning and Cruise Control Manual
(FPCCM) must be reduced by 1,000 ft/door.’’
Note 3: When a statement with the
information specified in paragraph (m)(2)(ii)
of this AD has been included in the general
revisions of the AFM, the general revisions
may be inserted into the AFM, and the copy
of this AD may be removed from the AFM.
E:\FR\FM\07MRP1.SGM
07MRP1
Federal Register / Vol. 71, No. 44 / Tuesday, March 7, 2006 / Proposed Rules
Revise CDL
(n) For airplanes on which the door(s) have
been removed in accordance with paragraph
(i)(3) of this AD: Within 30 days after the
effective date of this AD, do the revision
specified in paragraph (m)(2)(i) or (m)(2)(ii)
of this AD, as applicable, and remove any
revision required by paragraph (i)(3)(i) or
(i)(3)(ii) of this AD.
Notice of proposed rulemaking
(NPRM).
ACTION:
[Docket No. FAA–2006–24072; Directorate
Identifier 2006–NM–016–AD]
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Empresa Brasileira de Aeronautica S.A.
(EMBRAER) EMB–120( ) airplane
models in operation. This proposed AD
would require replacing the de-icing
system ejector flow control valves with
new, improved control valves having
hermetically sealed switches; and
rewiring applicable connectors. This
proposed AD results from a fuel system
review conducted by the manufacturer.
We are proposing this AD to prevent a
potential source of ignition near a fuel
tank, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane.
DATES: We must receive comments on
this proposed AD by April 6, 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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
Comments Invited
No Reporting Required
(o) Although Bombardier Alert Service
Bulletin A670BA–32–016, Revision A, dated
June 7, 2005, specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
Actions Accomplished According to Previous
Issue of Service Bulletin
(p) Actions accomplished before the
effective date of this AD according to
Bombardier Alert Service Bulletin A670BA–
32–016, dated June 2, 2005, are considered
acceptable for compliance with the
corresponding action specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(q)(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 § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 2003–19–51 are not
approved as AMOCs with this AD.
Related Information
(r) Canadian airworthiness directive CF–
2003–23R2, dated July 27, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on February
22, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–2159 Filed 3–6–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
sroberts on PROD1PC70 with PROPOSALS
14 CFR Part 39
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) EMB–120( ) Airplane
Models in Operation
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
VerDate Aug<31>2005
16:19 Mar 06, 2006
Jkt 208001
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2006–24072; Directorate
Identifier 2006–NM–016–AD’’ at the
beginning of your comments. We
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
11341
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 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 that 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 may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may 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 receives them.
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (67 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
E:\FR\FM\07MRP1.SGM
07MRP1
]]>Agencies
[Federal Register Volume 71, Number 44 (Tuesday, March 7, 2006)]
[Proposed Rules]
[Pages 11335-11341]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2159]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24074; Directorate Identifier 2005-NM-213-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2C10 (Regional
Jet Series 700, 701, & 702) Airplanes, Model CL-600-2D15 (Regional Jet
Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900)
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-600-2C10
(Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet Series
900) series airplanes. The existing AD currently requires repetitive
detailed inspections for cracking or deformation, or pulled or missing
fasteners, on the lower panel of the left- and right-hand main landing
gear (MLG) doors, as applicable, and corrective actions if necessary.
This proposed AD would reduce the repetitive inspection interval for
certain airplanes. This proposed AD also adds airplanes to the
applicability. This proposed AD results from a report of a MLG door
departing from an airplane. We are proposing this AD to prevent failure
of the lower panel of the MLG door, the lower panel's departure from
the airplane, and consequent damage to airplane structure, which could
adversely affect the airplane's continued safe flight and landing.
DATES: We must receive comments on this proposed AD by April 6, 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 in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-24074; Directorate Identifier 2005-NM-213-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 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
that 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,
[[Page 11336]]
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78), or you may visit https://dms.dot.gov.
Examining the Docket
You may 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
receives them.
Discussion
On October 23, 2003, we issued AD 2003-19-51, amendment 39-13353
(68 FR 61615, October 29, 2003), for certain Bombardier Model CL-600-
2C10 (Regional Jet Series 700 & 701) and CL-600-2D24 (Regional Jet
Series 900) series airplanes (originally issued September 17, 2003, as
an emergency airworthiness directive). That AD requires repetitive
detailed inspections for cracking or deformation, or pulled or missing
fasteners, on the lower panel of the left- and right-hand main landing
gear (MLG) doors, as applicable, and corrective actions if necessary.
That AD resulted from a report of a lower panel of the door of the
right-hand MLG of a Model CL-600-2C10 series airplane departing the
airplane during landing. We issued that AD to prevent failure of the
lower panel of the MLG door, the lower panel's departure from the
airplane, and consequent damage to airplane structure, which could
adversely affect the airplane's continued safe flight and landing.
Actions Since Existing AD Was Issued
Since we issued AD 2003-19-51, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, notified us
that an inboard MLG door departed from an airplane affected by the
existing AD. The airplane was operating under an alternative means of
compliance (AMOC) to the TCCA airworthiness directive that allowed
extension of the repetitive interval when certain repairs or
modifications where done. The TCCA determined that the inspection
intervals should be reduced for those airplanes. The TCCA also
determined that inspections are needed for additional airplanes
affected by the identified unsafe condition.
Relevant Service Information
Bombardier has issued Alert Service Bulletin A670BA-32-016,
Revision A, dated June 7, 2005, including Appendices A and B, dated
June 2, 2005. The service bulletin describes procedures for doing
repetitive inspections of the left- and right-hand inboard MLG doors
for damage, and corrective actions if necessary. The inspections
include doing a general visual inspection of the skin for damage such
as loose, pulled, or missing fasteners, missing paint, or scratches
around the rivet heads; and a detailed inspection of the inboard MLG
door for cracking or deformation. The corrective actions include
replacing the MLG door with a new or repaired MLG door. 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-2003-23R2,
dated July 27, 2005, to ensure the continued airworthiness of these
airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplane models 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 2003-19-51. This proposed AD
would retain certain requirements of AD 2003-19-51 and would require
accomplishing the actions specified in the service bulletin described
previously, except as discussed under ``Differences Between the
Proposed AD and the Service Bulletin/Canadian Airworthiness
Directive.''
Differences Among the Proposed AD and the Service Bulletin/Canadian
Airworthiness Directive
Although Bombardier Alert Service Bulletin A670BA-32-016, Revision
A, dated June 7, 2005, and the Canadian airworthiness directive specify
to submit certain information to the manufacturer, this proposed AD
does not include that requirement.
Bombardier Alert Service Bulletin A670BA-32-016, Revision A, dated
June 7, 2005, includes a note in the Accomplishment Instructions to
inform operators to contact Bombardier if no accurate generic repair
engineering order is available when accomplishing the repair. However,
this proposed AD would require doing the repair using a method that we
or TCCA (or its delegated agent) approve. In light of the type of
repair that would be required to address the unsafe condition, and
consistent with existing bilateral airworthiness agreements, we have
determined that, for this proposed AD, a repair we or TCCA (or its
delegated agent) approve would be acceptable for compliance with this
proposed AD. The Canadian airworthiness directive references the
limitations specified in the configuration deviation list (CDL) for
airplanes that remove damaged inboard MLG doors. The information in the
CDL has been revised since we issued AD 2003-19-51. For airplanes on
which the door(s) have been removed in accordance with AD 2003-19-51,
we would require revising the CDL to the latest revision.
Change to Existing AD
This proposed AD would retain certain requirements of AD 2003-19-
51. Since AD 2003-19-51 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
Requirement in AD 2003-19-51 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
paragraph (d)............................. paragraph (i).
------------------------------------------------------------------------
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
[[Page 11337]]
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we may consider further rulemaking then.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Work labor Cost per Number of U.S.-
Action hours rate per airplane registered Fleet cost
hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 1 $65 $65, per 83 $5,395, per inspection
2003-19-51). inspection cycle.
cycle.
Inspections (new proposed 1 65 $65, per 213 $13,854, per inspection
action). inspection cycle.
cycle.
Revision (new proposed 1 65 $65, if 213 Up to $13,854.
action). necessary.
----------------------------------------------------------------------------------------------------------------
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 39-13353 (68 FR 61615, October 29, 2003) and adding
the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2006-24074;
Directorate Identifier 2005-NM-213-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 6,
2006.
Affected ADs
(b) This AD supersedes AD 2003-19-51.
Applicability
(c) This AD applies to Bombardier Model CL-600-2C10 (Regional
Jet Series 700, 701, & 702) airplanes, serial numbers (S/Ns) 10003
and subsequent; and Model CL-600-2D15 (Regional Jet Series 705)
airplanes, and Model CL-600-2D24 (Regional Jet Series 900)
airplanes, S/Ns 15001 and subsequent; certificated in any category.
Unsafe Condition
(d) This AD results from a report of a main landing gear (MLG)
door departing from an airplane. We are issuing this AD to prevent
failure of the lower panel of the MLG door, the lower panel's
departure from the airplane, and consequent damage to airplane
structure, which could adversely affect the airplane's continued
safe flight and 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.
Restatement of Requirements of AD 2003-19-51
Initial Compliance Time
(f) For Model CL-600-2C10 (Regional Jet series 700 & 701) series
airplanes, S/Ns 10003 through 10999 inclusive; and Model CL-600-2D24
(Regional Jet series 900) series airplanes, S/Ns 15002 through 15990
inclusive: Perform the initial inspection specified in paragraph (g)
of this AD at the applicable time specified in paragraph (f)(1) or
(f)(2) of this AD.
(1) For airplanes with fewer than 1,500 total flight cycles as
of November 3, 2003, (the effective date of AD 2003-19-51): Do the
inspections before the accumulation of 1,050 total flight cycles, or
within 50 flight cycles after the effective date of this AD,
whichever is later.
(2) For airplanes with 1,500 or more total flight cycles as of
November 3, 2003: Do the inspections within 10 flight cycles after
the effective date of this AD.
Inspections
(g) For Model CL-600-2C10 (Regional Jet series 700 & 701) series
airplanes, S/Ns 10003 through 10999 inclusive; and Model CL-600-2D24
(Regional Jet series 900) series airplanes, S/Ns 15002 through 15990
inclusive: At the applicable time specified in paragraph (f) of this
AD, perform detailed inspections of the lower panel, part number (P/
N) CC670-10520, of the left- and right-hand MLG doors for the
conditions and in the areas specified in paragraphs (g)(1), (g)(2),
(g)(3), and (g)(4) of this AD; and Figures 1, 2, and 3 of this AD.
Note 1: 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,
[[Page 11338]]
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(1) Inspect the cross member, P/N CC670-10572, of the MLG door
lower panel for cracking or deformation, in accordance with Figure 2
of this AD.
(2) Inspect the inner skin, P/N CC670-10577, of the MLG door
lower panel at the cross member (P/N CC670-10572) for cracking or
deformation, or pulled or missing fasteners, in accordance with
Figure 2 of this AD.
(3) Inspect the outer skin, P/N CC670-10574, of the MLG door
lower panel at the cross member (P/N CC670-10572) for cracking or
deformation, or pulled or missing fasteners, in accordance with
Figure 2 of this AD.
(4) Inspect the forward member, P/N CC670-10570, and aft member,
P/N CC670-10571, of the MLG door lower panel, for cracking or
deformation, or pulled or missing fasteners, in accordance with
Figure 3 of this AD. Figures 1 through 3 of this AD follow.
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BILLING CODE 4910-13-C
Repetitive Inspections
(h) If no cracking or deformation, or pulled or missing
fastener, as applicable, is found during any inspection required by
paragraph (g) or (h) of this AD, repeat the inspections thereafter
at intervals not to exceed 100 flight cycles.
Corrective Actions
(i) If any cracking or deformation, or pulled or missing
fastener, as applicable, is found during any inspection done in
accordance with paragraph (g) or (h) of this AD: Before further
flight, accomplish paragraph (i)(1), (i)(2), or (i)(3) of this AD.
(1) Repair the damage in accordance with a method approved by
either the Manager, New York Aircraft Certification Office (ACO),
FAA; or Transport Canada Civil Aviation (or its delegated agent);
and accomplish repetitive inspections in accordance with a
[[Page 11340]]
method and at a repetitive interval approved by same.
(2) Replace the lower panel assembly, P/N CC670-10520, of the
affected MLG door with a new or serviceable lower panel assembly
having the same P/N, in accordance with Task Cards 32-12-01-000-801-
A01 and 32-12-01-400-801-A01 of the CRJ 700/900 Series Regional Jet
Aircraft Maintenance Manual; and repeat the inspections specified in
paragraph (g) of this AD at intervals not to exceed 100 flight
cycles.
(3) Remove the lower panel assembly, P/N CC670-10520, of the
affected MLG door, and accomplish paragraph (i)(3)(i) or (i)(3)(ii),
as applicable.
(i) For Model CL600-2C10 (Regional Jet series 700 & 701) series
airplanes: Revise the Configuration Deviation List (CDL), Appendix
1, of the airplane flight manual (AFM), to include the following
limitations. This may be accomplished by inserting a copy of this AD
into the CDL of the AFM.
``For Model CL600-2C10 series airplanes: If one or both door
panel assemblies, part number CC670-10520, is missing:
(1) Take-off Weight is reduced by 202.5 kg/door, or 450 lb/door
(2) Enroute Climb Weight is reduced by 445.5 kg/door, or 990 lb/
door
(3) Landing Weight is reduced by 202.5 kg/door, or 450 lb/door
(4) Fuel Consumption is increased by +3.42% on fuel used/door
(5) Cruise Airspeed is limited to not more than 0.78 Mach.''
(ii) For Model CL-600-2D24 (Regional Jet series 900) series
airplanes: Revise the CDL, Appendix 1, of the AFM, to include the
following limitations. This may be accomplished by inserting a copy
of this AD into the CDL of the AFM.
``For Model CL600-2D24 series airplanes: If one or both door
panel assemblies, part number CC670-10520, is missing:
(1) Take-off Weight is reduced by 245 kg/door, or 540 lb/door
(2) Enroute Climb Weight is reduced by 551 kg/door, or 1,215 lb/
door
(3) Landing Weight is reduced by 245 kg/door, or 540 lb/door
(4) Fuel Consumption is increased by +3.42% on fuel used/door
(5)Cruise Airspeed is limited to not more than 0.78 Mach.''
New Requirements of This AD
Inboard MLG Door Inspections
(j) For all airplanes on which an inspection has not been done
in accordance with paragraph (g) of this AD on or before the
effective date of this AD: At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD, do the inspections of the
left- and right-hand inboard MLG doors for damage in accordance with
Part A of the Accomplishment Instructions of the Bombardier Alert
Service Bulletin A670BA-32-016, Revision A, dated June 7, 2005,
including Appendix B, dated June 2, 2005, excluding Appendix A,
dated June 2, 2005. Doing the inspections required by this paragraph
terminates the actions required by paragraphs (f) through (i) of
this AD.
(1) For airplanes that have accumulated fewer than 1,500 total
flight cycles as of the effective date of this AD: Before the
accumulation of 1,000 total flight cycles or within 50 flight cycles
after the effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 1,500 flight cycles or
more as of the effective date of this AD: Within 10 flight cycles
after the effective date of this AD.
(k) For all airplanes on which an inspection has been done in
accordance with paragraph (g) of this AD on or before the effective
date of this AD and on which both doors have not been removed in
accordance with paragraph (i)(3) of this AD: At the applicable time
specified in paragraph (k)(1) or (k)(2) of this AD, do the
inspections specified in paragraph (j) of this AD; except for
airplanes on which one door has been removed in accordance with
paragraph (i)(3) of this AD, do the inspections specified in
paragraph (j) of this AD for the door that has not been removed.
Doing the inspections required by this paragraph terminates the
actions required by paragraphs (f) through (i) of this AD.
(1) For airplanes that are not subject to an approved
alternative method of compliance (AMOC) that extends the inspection
interval to 450 flight cycles: Within 100 flight cycles since the
last inspection done in accordance with paragraph (g) of this AD.
(2) For airplanes that are subject to an approved AMOC that
extends the inspection interval to 450 flight cycles: At the earlier
of the times specified in paragraph (k)(2)(i) and (k)(2)(ii) of this
AD:
(i) Within 450 flight cycles since the last inspection done in
accordance with paragraph (g) of this AD.
(ii) Within 100 flight cycles since the last inspection done in
accordance with paragraph (g) of this AD or within 50 cycles after
the effective date of this AD, whichever occurs later.
(l) If no damage is found during any inspection done in
accordance with paragraph (j) of this AD, repeat the inspections
specified in paragraph (j) of this AD thereafter at intervals not to
exceed 100 flight cycles.
Corrective Action--Replace or Remove MLG Door
(m) If any damage is found during any inspection done in
accordance with paragraph (j) of this AD, before further flight, do
the actions in paragraph (m)(1) or (m)(2) of this AD. Repeat the
inspections specified in paragraph (j) of this AD thereafter at
intervals not to exceed 100 flight cycles.
(1) Replace the inboard MLG door with a new or repaired door in
accordance with Part B of the Accomplishment Instructions of the
Bombardier Alert Service Bulletin A670BA-32-016, Revision A, dated
June 7, 2005, including Appendix B, dated June 2, 2005, excluding
Appendix A, dated June 2, 2005; except where the service bulletin
specifies to contact the manufacturer for repair if no generic
repair engineering order (REO) is available, before further flight,
repair using a method approved by either the Manager, New York
Aircraft Certification Office (ACO), FAA; or the Transport Canada
Civil Aviation (TCCA) (or its delegated agent).
(2) Remove the inboard MLG door in accordance with Part B of the
Accomplishment Instructions of the Bombardier Alert Service Bulletin
A670BA-32-016, Revision A, dated June 7, 2005, including Appendix B,
dated June 2, 2005, excluding Appendix A, dated June 2, 2005; and
accomplish paragraph (m)(2)(i) or (m)(2)(ii), as applicable.
(i) For Model CL-600-2C10 (Regional Jet Series 700, 701, & 702)
airplanes and Model CL-600-2D15 (Regional Jet Series 705) airplanes:
Revise the Configuration Deviation List (CDL), Appendix 1, of the
airplane flight manual (AFM), to include the following limitations.
This may be accomplished by inserting a copy of this AD into the CDL
of the AFM. Remove any existing CDL limitation required by paragraph
(i)(3)(i) of this AD from the AFM.
``For Model CL-600-2C10 (Regional Jet Series 700, 701, & 702)
airplanes and Model CL-600-2D15 (Regional Jet Series 705) airplanes:
If one or both door panel assemblies, part number CC670-10520, is
missing:
(1) Take-off Weight is reduced by 202.5 kg/door, or 450 lb/door
(2) Enroute Climb Weight is reduced by 445.5 kg/door, or 990 lb/
door
(3) Landing Weight is reduced by 202.5 kg/door, or 450 lb/door
(4) Fuel Consumption is increased by +2.5% on fuel used/door
(5) Cruise Airspeed is limited to not more than 0.78 Mach
(6) The climb ceiling obtained from the Flight Planning and
Cruise Control Manual (FPCCM) must be reduced by 1,000 ft/door.''
Note 2: When a statement with the information specified in
paragraph (m)(2)(i) of this AD has been included in the general
revisions of the AFM, the general revisions may be inserted into the
AFM, and the copy of this AD may be removed from the AFM.
(ii) For Model CL-600-2D24 (Regional Jet Series 900) airplanes:
Revise the CDL, Appendix 1, of the AFM, to include the following
limitations. This may be accomplished by inserting a copy of this AD
into the CDL of the AFM. Remove any existing CDL limitation required
by paragraph (i)(3)(ii) of this AD from the AFM.
``For Model CL-600-2D24 (Regional Jet Series 900) airplanes: If
one or both door panel assemblies, part number CC670-10520, is
missing:
(1) Take-off Weight is reduced by 245 kg/door, or 540 lb/door
(2) Enroute Climb Weight is reduced by 551 kg/door, or 1,215 lb/
door
(3) Landing Weight is reduced by 245 kg/door, or 540 lb/door
(4) Fuel Consumption is increased by +2.5% on fuel used/door
(5)Cruise Airspeed is limited to not more than 0.78 Mach
(6)The climb ceiling obtained from the Flight Planning and
Cruise Control Manual (FPCCM) must be reduced by 1,000 ft/door.''
Note 3: When a statement with the information specified in
paragraph (m)(2)(ii) of this AD has been included in the general
revisions of the AFM, the general revisions may be inserted into the
AFM, and the copy of this AD may be removed from the AFM.
[[Page 11341]]
Revise CDL
(n) For airplanes on which the door(s) have been removed in
accordance with paragraph (i)(3) of this AD: Within 30 days after
the effective date of this AD, do the revision specified in
paragraph (m)(2)(i) or (m)(2)(ii) of this AD, as applicable, and
remove any revision required by paragraph (i)(3)(i) or (i)(3)(ii) of
this AD.
No Reporting Required
(o) Although Bombardier Alert Service Bulletin A670BA-32-016,
Revision A, dated June 7, 2005, specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.
Actions Accomplished According to Previous Issue of Service
Bulletin
(p) Actions accomplished before the effective date of this AD
according to Bombardier Alert Service Bulletin A670BA-32-016, dated
June 2, 2005, are considered acceptable for compliance with the
corresponding action specified in this AD.
Alternative Methods of Compliance (AMOCs)
(q)(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.
(3) AMOCs approved previously in accordance with AD 2003-19-51
are not approved as AMOCs with this AD.
Related Information
(r) Canadian airworthiness directive CF-2003-23R2, dated July
27, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on February 22, 2006.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-2159 Filed 3-6-06; 8:45 am]
BILLING CODE 4910-13-P
