Airworthiness Directives; Bombardier Model CL-600-2B16 (CL-604) Airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 67502-67506 [E6-19798]
Download as PDF
<![CDATA[
67502
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26378; Directorate
Identifier 2006–NM–230–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B16 (CL–604)
Airplanes and Model CL–600–2B19
(Regional Jet Series 100 & 440)
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
jlentini on PROD1PC65 with PROPOSAL
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to certain
Bombardier Model CL–600–2B16 (CL–
604) airplanes and Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. These models may be referred
to by their marketing designations as
RJ100, RJ200, RJ440, CRJ100, CRJ200,
CRJ440, and CL–65. The existing AD
currently requires revising the
Emergency Procedures section of the
airplane flight manual (AFM) to advise
the flightcrew of additional procedures
to follow in the event of stabilizer trim
runaway. The existing AD also requires
revising the Abnormal Procedures
section of the AFM to advise the
flightcrew of procedures to follow in the
event of MACH TRIM, STAB TRIM, and
horizontal stabilizer trim malfunctions.
The existing AD also requires revising
the Normal section of the AFM to
require a review of the location of
certain circuit breakers and a functional
check of the stabilizer trim system. The
existing AD also requires installing
circuit breaker identification collars and
provides an optional terminating action
for the requirements of the AD. This
proposed AD would require doing the
previously optional terminating action
(installation of a new horizontal
stabilizer trim control unit). This
proposed AD results from a
determination that the terminating
action is necessary to address
uncommanded horizontal stabilizer trim
motion. We are proposing this AD to
prevent horizontal stabilizer trim
uncommanded motion, which could
result in reduced controllability of the
airplane.
We must receive comments on
this proposed AD by December 22,
2006.
DATES:
VerDate Aug<31>2005
16:20 Nov 21, 2006
Jkt 211001
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:
Daniel Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE–
172, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7305; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
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–2006–26378;
Directorate Identifier 2006–NM–230–
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,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
PO 00000
Frm 00036
Fmt 4702
Sfmt 4702
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 13, 2006, we issued AD
2006–22–06, amendment 39–14803 (71
FR 63219, October 30, 2006), for certain
Bombardier Model CL–600–2B16 (CL–
604) airplanes and Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. That AD requires revising the
Emergency Procedures section of the
airplane flight manual (AFM) to advise
the flightcrew of additional procedures
to follow in the event of stabilizer trim
runaway. That AD also requires revising
the Abnormal Procedures section of the
AFM to advise the flightcrew of
procedures to follow in the event of
MACH TRIM, STAB TRIM, and
horizontal stabilizer trim malfunctions.
That AD also requires revising the
Normal section of the AFM to require a
review of the location of certain circuit
breakers and a functional check of the
stabilizer trim system. That AD also
requires installing circuit breaker
identification collars and provides an
optional terminating action for the
requirements of the AD. That AD
resulted from reports of uncommanded
horizontal stabilizer trim motion. We
issued that AD to ensure that the
flightcrew is advised of appropriate
procedures to follow in the event of
uncommanded movement or stabilizer
trim runaway. Failure to follow these
procedures could result in excessive
uncommanded movement of the
horizontal stabilizer trim actuator
(HSTA) and loss of ability to use trim
switches to override uncommanded
movement or yoke disconnect switches
to disconnect the HSTA, which could
result in reduction of or loss of pitch
control and consequent reduced
controllability of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006–22–06
explains that we consider the
requirements of that AD ‘‘interim
E:\FR\FM\22NOP1.SGM
22NOP1
67503
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules
action’’ and that we were considering
further rulemaking. We now have
determined that further rulemaking is
indeed necessary, and this proposed AD
follows from that determination. The
optional terminating action specified in
AD 2006–22–06 (installation of a new,
improved horizontal stabilizer trim
control unit (HSTCU)) is necessary to
address the identified unsafe condition.
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, mandated the
terminating action and issued Canadian
airworthiness directives CF–2006–20R1,
dated October 4, 2006, and CF–2006–
21R1, dated October 3, 2006, 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 2006–22–06 and would continue to
require revising the Emergency, Normal,
and Abnormal Procedures sections of
the AFM and installing circuit breaker
identification collars. This proposed AD
would also require doing the
terminating action (installation of a new
HSTCU).
Difference Between Canadian
Airworthiness Directives and Proposed
AD
Although Canadian airworthiness
directives CF–2006–20R1 and CF–2006–
21R1 recommend accomplishing the
terminating action within 12 months,
this proposed AD would require
accomplishment within 9 months in
order to match the date the actions
required by the Canadian airworthiness
directives must be completed. We find
that 9 months is an appropriate
compliance time to complete the
terminating action. This has been
coordinated with TCCA.
Change to Existing AD
This proposed AD would retain only
certain requirements of AD 2006–22–06.
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
2006–22–06
Corresponding requirement in this proposed
AD
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(h) ........
(i) .........
(j) .........
(k) ........
(l) .........
(m) .......
(n) ........
(o) ........
(f).
(g).
(h).
(i).
(j).
(l).
(m).
(k).
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD. The
average labor rate per hour is $80.
ESTIMATED COSTS
Work
hours
Action
AFM Revisions and Installation of Circuit Breaker Collars (required by AD
2006–22–06).
Installation of HSTCU (new proposed
action).
2
11
jlentini on PROD1PC65 with PROPOSAL
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.
VerDate Aug<31>2005
16:20 Nov 21, 2006
Jkt 211001
Number of
U.S.-registered
airplanes
Parts
Cost per airplane
$3 ...........................
$163 .......................
875
$142,625.
Between $2,530
and $3,995.
Between $3,410
and $4,875.
875
Between $2,983,750 and
$4,265,625.
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
PO 00000
Frm 00037
Fmt 4702
Sfmt 4702
Fleet cost
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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
E:\FR\FM\22NOP1.SGM
22NOP1
67504
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules
by removing amendment 39–14803 (71
FR 63219, October 30, 2006) and adding
the following new airworthiness
directive (AD):
Bombardier, Inc. (Formerly Canadair):
Docket No. FAA–2006–26378;
Directorate Identifier 2006–NM–230–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by December 22, 2006.
Affected ADs
(b) This AD supersedes AD 2006–22–06.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2B16 (CL–604) airplanes, serial
numbers 5301 through 5665 inclusive; and
Model CL–600–2B19 (Regional Jet Series 100
& 440) airplanes, serial numbers 7003
through 7990 inclusive and 8000 through
8066 inclusive; certificated in any category.
Note 1: The Model CL–600–2B19 (Regional
Jet Series 100 & 440) airplanes may be
referred to by their marketing designations as
RJ100, RJ200, RJ440, CRJ100, CRJ200,
CRJ440, and CL–65.
Unsafe Condition
(d) This AD results from reports of
uncommanded horizontal stabilizer trim
motion. We are issuing this AD to prevent
horizontal stabilizer trim uncommanded
motion, which could result in reduced
controllability 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.
Restatement of Certain Requirements of AD
2006–22–06
Airplane Flight Manual (AFM) Revisions
(f) Within 14 days after November 14, 2006
(the effective date of AD 2006–22–06), make
the applicable AFM revisions specified in
paragraph (f)(1) or (f)(2) of this AD by
incorporating the applicable Canadair
(Bombardier) temporary revisions (TRs)
identified in Table 1 of this AD into the
applicable AFM.
(1) For Model CL–600–2B16 (CL–604)
airplanes: Revise the Emergency and
Abnormal Procedures sections of the AFM to
advise the flightcrew of additional
procedures to follow in the event of stabilizer
trim runaway and to advise the flightcrew of
revised procedures to follow in the event of
MACH TRIM, STAB TRIM, and horizontal
stabilizer trim malfunctions.
(2) For Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes: Revise the
Emergency and Abnormal Procedures
sections of the AFM to advise the flightcrew
of revised procedures to follow in the event
of stabilizer trim runaway and in the event
of MACH TRIM, STAB TRIM, and horizontal
stabilizer trim malfunctions.
TABLE 1.—TRS
For Bombardier Model—
Use—
Dated—
To the—
CL–600–2B16 (CL–604) airplanes ..............
Canadair Challenger TR
604/21–1.
Canadair Regional Jet
TR RJ/152–5.
October 3, 2006 ..............
Canadair Challenger CL–604 AFM, PSP
604–1.
Canadair Regional Jet AFM, CSP A–012.
CL–600–2B19 (Regional Jet Series 100 &
440) airplanes.
jlentini on PROD1PC65 with PROPOSAL
(g) When the applicable TR specified in
paragraph (f) of this AD has been included
in the general revisions of the applicable
AFM, those general revisions may be inserted
into the AFM and the applicable TR may be
removed, provided the relevant information
in the general revisions is identical to that in
the TR.
VerDate Aug<31>2005
16:20 Nov 21, 2006
Jkt 211001
October 3, 2006 ..............
Installation of Circuit Breaker Identification
Collars
(h) Within 14 days after November 14,
2006, install circuit breaker identification
collars in accordance with Bombardier
Modification Summary Package
IS601R27410051, Revision C, dated
September 29, 2006 (for Model CL–600–2B19
(Regional Jet Series 100 & 440) airplanes); or
the Accomplishment Instructions of
Bombardier Alert Service Bulletin A604–27–
029, dated September 28, 2006 (for Model
PO 00000
Frm 00038
Fmt 4702
Sfmt 4702
CL–600–2B16 (CL–604) airplanes); as
applicable.
Additional AFM Revision
(i) For Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes: Within 14 days
after November 14, 2006, revise the Normal
section of the Canadair Regional Jet AFM,
CSP A–012, to include the statement
specified in Figure 1 of this AD. This may be
done by inserting a copy of Figure 1 of this
AD into the AFM.
E:\FR\FM\22NOP1.SGM
22NOP1
Note 2: When a statement identical to that
in paragraph (i) of this AD has been included
in the general revisions of the applicable
AFM, those general revisions may be inserted
into the AFM, and the copy of this AD may
be removed from the AFM.
(j) For Model CL–600–2B16 (CL–604)
airplanes: Within 14 days after November 14,
2006, revise the Normal section of the
Canadair Challenger CL–604 AFM, PSP 604–
1, to include the following statement. This
may be done by inserting a copy of this AD
into the AFM.
‘‘Prior to the flightcrew’s first flight of the
day, do the following actions:
VerDate Aug<31>2005
16:20 Nov 21, 2006
Jkt 211001
1. Review the location of the STAB CH1
HSTCU and STAB CH2 HSTCU circuit
breakers.
2. Check the stabilizer trim system as
detailed in CL–604 AFM ’Normal Procedures’
section titled ‘Flight Controls Trim Systems,
Before Flight—First Flight of the Day.’ ’’
Note 3: When a statement identical to that
in paragraph (j) of this AD has been included
in the general revisions of the applicable
AFM, those general revisions may be inserted
into the AFM, and the copy of this AD may
be removed from the AFM.
PO 00000
Frm 00039
Fmt 4702
Sfmt 4702
67505
Previous Actions Accomplished According to
Modification Summary Package
(k) Actions accomplished before November
14, 2006, in accordance with Bombardier
Modification Summary Package
IS601R27410051, Revision A, dated
September 18, 2006; or Revision B, dated
September 27, 2006; are considered
acceptable for compliance with the action
specified in paragraph (h) of this AD,
provided that the circuit breaker collars meet
the color requirements of Bombardier
Modification Summary Package
IS601R27410051, Revision C, dated
September 29, 2006.
E:\FR\FM\22NOP1.SGM
22NOP1
EP22NO06.011</GPH>
jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules
67506
Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Proposed Rules
New Requirements of This AD
DEPARTMENT OF TRANSPORTATION
Terminating Action—Installation of New,
Improved Part
Federal Aviation Administration
(l) Within 9 months after the effective date
of this AD, install horizontal stabilizer trim
control unit (HSTCU), part number (P/N)
601R92301–15 (vendor P/N 7060–10) or
higher dash number, in accordance with the
Accomplishment Instructions of Bombardier
Alert Service Bulletin A604–27–029, dated
September 28, 2006 (for Model CL–600–2B16
(CL–604) airplanes); or Bombardier Service
Bulletin 601R–27–147, dated September 28,
2006 (for Model CL–600–2B19 (Regional Jet
Series 100 & 440) airplanes); as applicable.
After doing the installation, the AFM
revisions required by paragraph (f) of this AD
may be removed from the applicable AFM,
and the circuit breaker identification collars
required by paragraph (h) of this AD may be
removed. After doing the installation, the
AFM revision required by paragraphs (i) and
(j) of this AD may also be removed from the
AFM but operators should note that the
functional check of the stabilizer trim system
on the airplane’s first flight of the day, as
described in the AFM, must still be done.
Note 4: Bombardier Service Bulletin 601R–
27–147, dated September 28, 2006, refers to
Sagem Service Bulletin HSTCU–27–011,
dated September 22, 2006, as an additional
source of service information for
accomplishment of the installation.
14 CFR Part 39
Service Bulletin Exception
(m) Although Bombardier Alert Service
Bulletin A604–27–029, dated September 28,
2006, specifies to return certain parts to the
manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, New York Aircraft
Certification Office, 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.
Related Information
jlentini on PROD1PC65 with PROPOSAL
(o) Canadian airworthiness directives CF–
2006–20R1, dated October 4, 2006, and CF–
2006–21R1, dated October 3, 2006, also
address the subject of this AD.
Issued in Renton, Washington, on
November 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–19798 Filed 11–21–06; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
16:20 Nov 21, 2006
Jkt 211001
[Docket No. FAA–2006–26236; Directorate
Identifier 2006–CE–66–AD]
RIN 2120–AA64
Airworthiness Directives; SOCATA—
Groupe AEROSPATIALE Models TB 20
and TB 21 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as reports of interference
between the wing spar lower boom and
the wheel fairing attaching screw. The
proposed AD would require actions that
are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by December 22,
2006.
You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
PO 00000
Frm 00040
Fmt 4702
Sfmt 4702
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. The streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This proposed AD references the
MCAI and related service information
that we considered in forming the
engineering basis to correct the unsafe
condition. The proposed AD contains
text copied from the MCAI and for this
reason might not follow our plain
language principles.
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–26236; Directorate Identifier
2006–CE–66–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No.: 2006–
0123, dated May 16, 2006 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
E:\FR\FM\22NOP1.SGM
22NOP1
]]>Agencies
[Federal Register Volume 71, Number 225 (Wednesday, November 22, 2006)]
[Proposed Rules]
[Pages 67502-67506]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19798]
[[Page 67502]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26378; Directorate Identifier 2006-NM-230-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B16 (CL-604)
Airplanes and 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-600-2B16
(CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 &
440) airplanes. These models may be referred to by their marketing
designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65.
The existing AD currently requires revising the Emergency Procedures
section of the airplane flight manual (AFM) to advise the flightcrew of
additional procedures to follow in the event of stabilizer trim
runaway. The existing AD also requires revising the Abnormal Procedures
section of the AFM to advise the flightcrew of procedures to follow in
the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim
malfunctions. The existing AD also requires revising the Normal section
of the AFM to require a review of the location of certain circuit
breakers and a functional check of the stabilizer trim system. The
existing AD also requires installing circuit breaker identification
collars and provides an optional terminating action for the
requirements of the AD. This proposed AD would require doing the
previously optional terminating action (installation of a new
horizontal stabilizer trim control unit). This proposed AD results from
a determination that the terminating action is necessary to address
uncommanded horizontal stabilizer trim motion. We are proposing this AD
to prevent horizontal stabilizer trim uncommanded motion, which could
result in reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by December 22,
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: Daniel Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York 11590; telephone (516) 228-7305; 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-2006-26378; Directorate Identifier 2006-NM-230-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, 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 13, 2006, we issued AD 2006-22-06, amendment 39-14803
(71 FR 63219, October 30, 2006), for certain Bombardier Model CL-600-
2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100
& 440) airplanes. That AD requires revising the Emergency Procedures
section of the airplane flight manual (AFM) to advise the flightcrew of
additional procedures to follow in the event of stabilizer trim
runaway. That AD also requires revising the Abnormal Procedures section
of the AFM to advise the flightcrew of procedures to follow in the
event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim
malfunctions. That AD also requires revising the Normal section of the
AFM to require a review of the location of certain circuit breakers and
a functional check of the stabilizer trim system. That AD also requires
installing circuit breaker identification collars and provides an
optional terminating action for the requirements of the AD. That AD
resulted from reports of uncommanded horizontal stabilizer trim motion.
We issued that AD to ensure that the flightcrew is advised of
appropriate procedures to follow in the event of uncommanded movement
or stabilizer trim runaway. Failure to follow these procedures could
result in excessive uncommanded movement of the horizontal stabilizer
trim actuator (HSTA) and loss of ability to use trim switches to
override uncommanded movement or yoke disconnect switches to disconnect
the HSTA, which could result in reduction of or loss of pitch control
and consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2006-22-06 explains that we consider the
requirements of that AD ``interim
[[Page 67503]]
action'' and that we were considering further rulemaking. We now have
determined that further rulemaking is indeed necessary, and this
proposed AD follows from that determination. The optional terminating
action specified in AD 2006-22-06 (installation of a new, improved
horizontal stabilizer trim control unit (HSTCU)) is necessary to
address the identified unsafe condition.
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, mandated the terminating action and issued
Canadian airworthiness directives CF-2006-20R1, dated October 4, 2006,
and CF-2006-21R1, dated October 3, 2006, 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 2006-22-06 and would continue
to require revising the Emergency, Normal, and Abnormal Procedures
sections of the AFM and installing circuit breaker identification
collars. This proposed AD would also require doing the terminating
action (installation of a new HSTCU).
Difference Between Canadian Airworthiness Directives and Proposed AD
Although Canadian airworthiness directives CF-2006-20R1 and CF-
2006-21R1 recommend accomplishing the terminating action within 12
months, this proposed AD would require accomplishment within 9 months
in order to match the date the actions required by the Canadian
airworthiness directives must be completed. We find that 9 months is an
appropriate compliance time to complete the terminating action. This
has been coordinated with TCCA.
Change to Existing AD
This proposed AD would retain only certain requirements of AD 2006-
22-06. As a result, the corresponding paragraph identifiers have
changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2006-22-06 this proposed AD
------------------------------------------------------------------------
Paragraph (h).......................... Paragraph (f).
Paragraph (i).......................... Paragraph (g).
Paragraph (j).......................... Paragraph (h).
Paragraph (k).......................... Paragraph (i).
Paragraph (l).......................... Paragraph (j).
Paragraph (m).......................... Paragraph (l).
Paragraph (n).......................... Paragraph (m).
Paragraph (o).......................... Paragraph (k).
------------------------------------------------------------------------
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD. The average labor rate per hour is
$80.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work Parts Cost per airplane registered Fleet cost
hours airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM Revisions and Installation of 2 $3.................... $163.................. 875 $142,625.
Circuit Breaker Collars (required
by AD 2006-22-06).
Installation of HSTCU (new proposed 11 Between $2,530 and Between $3,410 and 875 Between $2,983,750 and $4,265,625.
action). $3,995. $4,875.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
[[Page 67504]]
by removing amendment 39-14803 (71 FR 63219, October 30, 2006) and
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2006-26378;
Directorate Identifier 2006-NM-230-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
22, 2006.
Affected ADs
(b) This AD supersedes AD 2006-22-06.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B16 (CL-604)
airplanes, serial numbers 5301 through 5665 inclusive; and Model CL-
600-2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers
7003 through 7990 inclusive and 8000 through 8066 inclusive;
certificated in any category.
Note 1: The Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes may be referred to by their marketing designations as
RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65.
Unsafe Condition
(d) This AD results from reports of uncommanded horizontal
stabilizer trim motion. We are issuing this AD to prevent horizontal
stabilizer trim uncommanded motion, which could result in reduced
controllability 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.
Restatement of Certain Requirements of AD 2006-22-06
Airplane Flight Manual (AFM) Revisions
(f) Within 14 days after November 14, 2006 (the effective date
of AD 2006-22-06), make the applicable AFM revisions specified in
paragraph (f)(1) or (f)(2) of this AD by incorporating the
applicable Canadair (Bombardier) temporary revisions (TRs)
identified in Table 1 of this AD into the applicable AFM.
(1) For Model CL-600-2B16 (CL-604) airplanes: Revise the
Emergency and Abnormal Procedures sections of the AFM to advise the
flightcrew of additional procedures to follow in the event of
stabilizer trim runaway and to advise the flightcrew of revised
procedures to follow in the event of MACH TRIM, STAB TRIM, and
horizontal stabilizer trim malfunctions.
(2) For Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes: Revise the Emergency and Abnormal Procedures sections of
the AFM to advise the flightcrew of revised procedures to follow in
the event of stabilizer trim runaway and in the event of MACH TRIM,
STAB TRIM, and horizontal stabilizer trim malfunctions.
Table 1.--TRs
----------------------------------------------------------------------------------------------------------------
For Bombardier Model-- Use-- Dated-- To the--
----------------------------------------------------------------------------------------------------------------
CL-600-2B16 (CL-604) airplanes....... Canadair Challenger TR October 3, 2006........ Canadair Challenger CL-
604/21-1. 604 AFM, PSP 604-1.
CL-600-2B19 (Regional Jet Series 100 Canadair Regional Jet October 3, 2006........ Canadair Regional Jet
& 440) airplanes. TR RJ/152-5. AFM, CSP A-012.
----------------------------------------------------------------------------------------------------------------
(g) When the applicable TR specified in paragraph (f) of this AD
has been included in the general revisions of the applicable AFM,
those general revisions may be inserted into the AFM and the
applicable TR may be removed, provided the relevant information in
the general revisions is identical to that in the TR.
Installation of Circuit Breaker Identification Collars
(h) Within 14 days after November 14, 2006, install circuit
breaker identification collars in accordance with Bombardier
Modification Summary Package IS601R27410051, Revision C, dated
September 29, 2006 (for Model CL-600-2B19 (Regional Jet Series 100 &
440) airplanes); or the Accomplishment Instructions of Bombardier
Alert Service Bulletin A604-27-029, dated September 28, 2006 (for
Model CL-600-2B16 (CL-604) airplanes); as applicable.
Additional AFM Revision
(i) For Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes: Within 14 days after November 14, 2006, revise the Normal
section of the Canadair Regional Jet AFM, CSP A-012, to include the
statement specified in Figure 1 of this AD. This may be done by
inserting a copy of Figure 1 of this AD into the AFM.
[[Page 67505]]
[GRAPHIC] [TIFF OMITTED] TP22NO06.011
Note 2: When a statement identical to that in paragraph (i) of
this AD has been included in the general revisions of the applicable
AFM, those general revisions may be inserted into the AFM, and the
copy of this AD may be removed from the AFM.
(j) For Model CL-600-2B16 (CL-604) airplanes: Within 14 days
after November 14, 2006, revise the Normal section of the Canadair
Challenger CL-604 AFM, PSP 604-1, to include the following
statement. This may be done by inserting a copy of this AD into the
AFM.
``Prior to the flightcrew's first flight of the day, do the
following actions:
1. Review the location of the STAB CH1 HSTCU and STAB CH2 HSTCU
circuit breakers.
2. Check the stabilizer trim system as detailed in CL-604 AFM
'Normal Procedures' section titled `Flight Controls Trim Systems,
Before Flight--First Flight of the Day.' ''
Note 3: When a statement identical to that in paragraph (j) of
this AD has been included in the general revisions of the applicable
AFM, those general revisions may be inserted into the AFM, and the
copy of this AD may be removed from the AFM.
Previous Actions Accomplished According to Modification Summary
Package
(k) Actions accomplished before November 14, 2006, in accordance
with Bombardier Modification Summary Package IS601R27410051,
Revision A, dated September 18, 2006; or Revision B, dated September
27, 2006; are considered acceptable for compliance with the action
specified in paragraph (h) of this AD, provided that the circuit
breaker collars meet the color requirements of Bombardier
Modification Summary Package IS601R27410051, Revision C, dated
September 29, 2006.
[[Page 67506]]
New Requirements of This AD
Terminating Action--Installation of New, Improved Part
(l) Within 9 months after the effective date of this AD, install
horizontal stabilizer trim control unit (HSTCU), part number (P/N)
601R92301-15 (vendor P/N 7060-10) or higher dash number, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A604-27-029, dated September 28, 2006 (for Model
CL-600-2B16 (CL-604) airplanes); or Bombardier Service Bulletin
601R-27-147, dated September 28, 2006 (for Model CL-600-2B19
(Regional Jet Series 100 & 440) airplanes); as applicable. After
doing the installation, the AFM revisions required by paragraph (f)
of this AD may be removed from the applicable AFM, and the circuit
breaker identification collars required by paragraph (h) of this AD
may be removed. After doing the installation, the AFM revision
required by paragraphs (i) and (j) of this AD may also be removed
from the AFM but operators should note that the functional check of
the stabilizer trim system on the airplane's first flight of the
day, as described in the AFM, must still be done.
Note 4: Bombardier Service Bulletin 601R-27-147, dated September
28, 2006, refers to Sagem Service Bulletin HSTCU-27-011, dated
September 22, 2006, as an additional source of service information
for accomplishment of the installation.
Service Bulletin Exception
(m) Although Bombardier Alert Service Bulletin A604-27-029,
dated September 28, 2006, specifies to return certain parts to the
manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, New York Aircraft Certification Office, 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
(o) Canadian airworthiness directives CF-2006-20R1, dated
October 4, 2006, and CF-2006-21R1, dated October 3, 2006, also
address the subject of this AD.
Issued in Renton, Washington, on November 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-19798 Filed 11-21-06; 8:45 am]
BILLING CODE 4910-13-P
