Airworthiness Directives; Bombardier, Inc. Model DHC-8-400, -401, and -402 Airplanes, 39798-39801 [2010-16434]
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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Aircraft Industries, a.s., Na
´
Zahonech 1177, 686 04 Kunovice, Czech
Republic; phone: +420 572 817 660; fax: +420
572 816 112; Internet: https://www.let.cz/; email: ots@let.cz.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Kansas City, Missouri, on June
28, 2010.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–16382 Filed 7–12–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0382; Directorate
Identifier 2009–NM–211–AD; Amendment
39–16361; AD 2010–14–16]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model DHC–8–400, –401, and –402
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Several cases have been reported where a
loss of fluid in the No.2 hydraulic system has
caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations
and increased fluid flow within the No. 1
hydraulic system. In one case, the hydraulic
system control logic did not shut down the
PTU and the overspeed condition persisted,
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resulting in the illumination of the No.1 HYD
FLUID HOT caution light.
*
*
*
*
*
The unsafe condition is possible loss of
both the No. 1 and No. 2 hydraulic
systems, resulting in the potential loss
of several functions essential for safe
flight and landing of the airplane. We
are issuing this AD to require actions to
correct the unsafe condition on these
products.
DATES: This AD becomes effective
August 17, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 17, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 2, 2008 (73 FR 47818,
August 15, 2008).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of July 10, 2007 (72 FR
30968, June 5, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Fabio Buttitta, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7303; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on April 21, 2010 (75 FR
20787), and proposed to supersede AD
2008–17–06, Amendment 39–15644 (73
FR 47818, August 15, 2008). That NPRM
proposed to correct an unsafe condition
for the specified products. The MCAI
states:
Since we issued AD 2008–17–06, a
modification of the power transfer unit
(PTU) control logic, including the
provision of automatic PTU shutdown
in the event of loss of fluid in the No.
2 hydraulic system, has been developed.
The modification addresses the
identified unsafe condition. In addition,
the applicability has been revised to
remove airplanes having serial number
PO 00000
Frm 00012
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Sfmt 4700
4185 and subsequent, since an
equivalent modification has been
installed in production on these
airplanes. Transport Canada Civil
Aviation (TCCA), which is the aviation
authority for Canada, has issued
Canadian Airworthiness Directive CF–
2006–08R1, dated August 31, 2009
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Several cases have been reported where a
loss of fluid in the No.2 hydraulic system has
caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations
and increased fluid flow within the No. 1
hydraulic system. In one case, the hydraulic
system control logic did not shut down the
PTU and the overspeed condition persisted,
resulting in the illumination of the No. 1
HYD FLUID HOT caution light.
As an interim action to avoid possible loss
of both the No. 1 and No. 2 hydraulic
systems, the Airplane Flight Manual (AFM)
has been revised to include pulling the HYD
PWR XFER circuit breaker in the event of the
loss of all hydraulic fluid in the No. 2
hydraulic system.
Insertion of the resultant Temporary
Amendment (TA) No. 13 into the AFM was
mandated in the original issue of this
[Canadian] directive. This instruction * * *
remains in effect until * * * this [revised]
directive is accomplished.
Revision 1 of this directive * * *
mandates modification of the PTU control
logic, including the provision of automatic
PTU shutdown in the event of loss of fluid
in the No. 2 hydraulic system. In addition,
the applicability of the [Canadian] directive
has been revised to remove aircraft Serial
Number (SN) 4185 and subsequent, since an
equivalent modification has been installed in
production on these aircraft.
The unsafe condition is possible loss of
both the No. 1 and No. 2 hydraulic
systems, resulting in the potential loss
of several functions essential for safe
flight and landing of the airplane. You
may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
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different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
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Costs of Compliance
We estimate that this AD will affect
about 42 products of U.S. registry.
The actions that are required by AD
2008–17–06 and retained in this AD
take about 1 work-hour per product, at
an average labor rate of $85 per work
hour. Required parts cost about $0 per
product. Based on these figures, the
estimated cost of the currently required
actions is $85 per product.
We estimate that it will take about 165
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Required parts will cost about
$10,982 per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$1,050,294, or $25,007 per product.
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 determined that this AD will not
have federalism implications under
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Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 FAA amends § 39.13 by
removing Amendment 39–39–15644 (73
FR 47818, August 15, 2008) and adding
the following new AD:
■
2010–14–16 Bombardier, Inc.: Amendment
39–16361. Docket No. FAA–2010–0382;
Directorate Identifier 2009–NM–211–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 17, 2010.
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
39799
Affected ADs
(b) This AD supersedes AD 2008–17–06,
Amendment 39–15644.
Applicability
(c) This AD applies to Bombardier, Inc.
Model DHC–8–400, –401, and –402
airplanes, certificated in any category; serial
numbers 4001, 4003, 4004, 4006, and 4008
through 4184 inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 29: Hydraulic power.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Several cases have been reported where a
loss of fluid in the No.2 hydraulic system has
caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations
and increased fluid flow within the No. 1
hydraulic system. In one case, the hydraulic
system control logic did not shut down the
PTU and the overspeed condition persisted,
resulting in the illumination of the No. 1
HYD FLUID HOT caution light.
As an interim action to avoid possible loss
of both the No. 1 and No. 2 hydraulic
systems, the Airplane Flight Manual (AFM)
has been revised to include pulling the HYD
PWR XFER circuit breaker in the event of the
loss of all hydraulic fluid in the No. 2
hydraulic system.
Insertion of the resultant Temporary
Amendment (TA) No. 13 into the AFM was
mandated in the original issue of this
[Canadian] directive. This instruction * * *
remains in effect until * * * this [revised]
directive is accomplished.
Revision 1 of this directive * * *
mandates modification of the PTU control
logic, including the provision of automatic
PTU shutdown in the event of loss of fluid
in the No. 2 hydraulic system. In addition,
the applicability of the [Canadian] directive
has been revised to remove aircraft Serial
Number (SN) 4185 and subsequent, since an
equivalent modification has been installed in
production on these aircraft.
The unsafe condition is possible loss of both
the No. 1 and No. 2 hydraulic systems,
resulting in the potential loss of several
functions essential for safe flight and landing
of the airplane.
Compliance
(f) 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 2007–12–03 AIRPLANE FLIGHT
MANUAL (AFM) REVISION
(g) Within 14 days after July 10, 2007 (the
effective date of AD 2007–12–03,
Amendment 39–15081, which was
superseded by AD 2008–17–06), revise the
Limitations section of the applicable AFM to
include the information in the applicable
Bombardier temporary amendment specified
in Table 1 of this AD, as specified in the
temporary amendment. These temporary
amendments introduce procedures for
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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations
pulling the ‘‘HYD PWR XFER’’ circuit breaker
in the event of the loss of all hydraulic fluid
in the No. 1 or No. 2 hydraulic system.
Operate the airplane according to the
limitations and procedures in the applicable
temporary amendment.
TABLE 1—AFM TEMPORARY AMENDMENTS
Use Bombardier
temporary
amendment—
For model—
DHC–8–400 airplanes ......................................................
DHC–8–401 airplanes ......................................................
DHC–8–402 airplanes ......................................................
Note 1: This may be done by inserting a
copy of the applicable temporary amendment
into the applicable AFM. When the
applicable temporary amendment has been
included in general revisions of the AFM, the
general revisions may be inserted into the
AFM, provided the relevant information in
the general revisions is identical to that in
the temporary amendment.
Dated—
Issue—
13
13
13
1
1
1
To Bombardier Dash
8 Q400 Airplane
Flight Manual—
July 14, 2005 .............
July 14, 2005 .............
July 14, 2005 .............
PSM 1–84–1A.
PSM 1–84–1A.
PSM 1–84–1A.
Restatement of Requirements of AD 2008–
17–06: AFM Revision
amendment. These temporary amendments
introduce additional procedures for ensuring
that the ‘‘PTU CNTRL’’ switch is Normal, the
‘‘PTU CNTRL ON’’ advisory light is out, and
the ‘‘HYD PWR XFER’’ circuit breaker is
pulled in the event of the illumination of the
‘‘#2 HYD ISO VALVE’’ caution light. After
accomplishing the AFM revision, the AFM
limitation required by paragraph (g) in this
AD may be removed from the AFM.
(h) Within 14 days after September 2, 2008
(the effective date of AD 2008–17–06), revise
the applicable AFM Normal and Abnormal
Procedures section to include the
information in the applicable Bombardier
temporary amendment specified in Table 2 of
this AD, as specified in the temporary
TABLE 2—AFM TEMPORARY AMENDMENTS
Use Bombardier
temporary
amendment—
For model—
DHC–8–400 airplanes ......................................................
DHC–8–401 airplanes ......................................................
DHC–8–402 airplanes ......................................................
New Requirements of This AD: Actions
(i) Within 6,000 flight hours after the
effective date of this AD, modify the PTU
control logic, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 84–29–22, Revision A, dated
February 24, 2009. Doing this modification
terminates the requirements of paragraphs (g)
and (h) of this AD, and after the modification
has been done, the AFM limitation required
by paragraphs (g) and (h) of this AD may be
removed from the AFM.
(j) Modifying the PTU control logic is also
acceptable for compliance with the
requirements of paragraph (i) of this AD if
done before the effective date of this AD, in
accordance with Bombardier Service Bulletin
84–29–22, dated December 5, 2008.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(k) The following provisions also apply to
this AD:
Dated—
Issue—
13
13
13
3
3
3
To Bombardier Dash
8 Q400 Airplane
Flight Manual—
June 9, 2008 .............
June 9, 2008 .............
June 9, 2008 .............
PSM 1–84–1A.
PSM 1–84–1A.
PSM 1–84–1A.
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone 516–228–7300; fax 516–
794–5531. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(l) Refer to MCAI Canadian Airworthiness
Directive CF–2006–08R1, dated August 31,
2009; the Bombardier temporary
amendments specified in Tables 1 and 2; and
Bombardier Service Bulletin 84–29–22,
Revision A, dated February 24, 2009; for
related information.
Material Incorporated by Reference
(m) You must use Bombardier Service
Bulletin 84–29–22, Revision A, dated
February 24, 2009, and the applicable
temporary amendment identified in Table 3
of this AD; as applicable; to do the actions
required by this AD, unless the AD specifies
otherwise.
TABLE 3—ALL TEMPORARY AMENDMENTS INCORPORATED BY REFERENCE
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Bombardier temporary amendment—
13
13
13
13
13
13
Issue—
...............................................................
...............................................................
...............................................................
...............................................................
...............................................................
...............................................................
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Dated—
1
1
1
3
3
3
PO 00000
July 14, 2005
July 14, 2005
July 14, 2005
June 9, 2008
June 9, 2008
June 9, 2008
Frm 00014
Fmt 4700
To Bombardier Dash 8 Q400 Airplane Flight Manual—
.............
.............
.............
.............
.............
.............
Sfmt 4700
Model
Model
Model
Model
Model
Model
400
401
402
400
401
402
PSM
PSM
PSM
PSM
PSM
PSM
1–84–1A.
1–84–1A.
1–84–1A.
1–84–1A.
1–84–1A.
1–84–1A.
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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations
(1) The Director of the Federal Register
approved the incorporation by reference of
Bombardier Service Bulletin 84–29–22,
Revision A, dated February 24, 2009, under
5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
39801
reference of the service information
contained in Table 4 of this AD on September
2, 2008 (73 FR 47818, August 15, 2008).
TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2008–17–06
Bombardier temporary amendment—
Dated—
Issue—
13 ...............................................................
13 ...............................................................
13 ...............................................................
3
3
3
(3) On July 10, 2007 (72 FR 30968, June 5,
2007), the Director of the Federal Register
approved the incorporation by reference of
To Bombardier Dash 8 Q400
Airplane Flight Manual—
June 9, 2008 .............
June 9, 2008 .............
June 9, 2008 .............
Model 400 PSM 1–84–1A.
Model 401 PSM 1–84–1A.
Model 402 PSM 1–84–1A.
the temporary amendments identified in
Table 5 of this AD.
TABLE 5—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2007–12–03
Bombardier temporary amendment—
13 ...............................................................
13 ...............................................................
13 ...............................................................
1
1
1
(4) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(5) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(6) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 25,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–16434 Filed 7–12–10; 8:45 am]
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Dated—
Issue—
To Bombardier Dash 8 Q400
Airplane Flight Manual—
July 14, 2005 .............
July 14, 2005 .............
July 14, 2005 .............
Model 400 PSM 1–84–1A.
Model 401 PSM 1–84–1A.
Model 402 PSM 1–84–1A.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29176; Directorate
Identifier 2007–NE–38–AD; Amendment 39–
16365; AD 2010–14–20]
RIN 2120–AA64
Airworthiness Directives; McCauley
Propeller Systems Model 4HFR34C653/
L106FA Propellers
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
McCauley Propeller Systems model
4HFR34C653/L106FA propellers. This
AD requires a onetime fluorescent
penetrant inspection (FPI) and eddy
current inspection (ECI) of the propeller
hub for cracks. This AD results from
reports of 10 hubs found cracked during
propeller overhaul. We are issuing this
AD to prevent failure of the propeller
hub, which could cause blade
separation, damage to the airplane, and
loss of control of the airplane.
DATES: This AD becomes effective
August 17, 2010. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of August 17, 2010.
ADDRESSES: You can get the service
information identified in this AD from
McCauley Propeller Systems, P.O. Box
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
7704, Wichita, KS 67277–7704;
telephone (800) 621–7767.
The Docket Operations office is
located at Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
FOR FURTHER INFORMATION CONTACT: Jeff
Janusz, Aerospace Engineer, Wichita
Aircraft Certification Office, FAA, Small
Airplane Directorate, 1801 Airport
Road, Wichita, KS 67209; e-mail:
jeff.janusz@faa.gov; telephone (316)
946–4148; fax (316) 946–4107.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to McCauley Propeller Systems
model 4HFR34C653/L106FA propellers.
We published the proposed AD in the
Federal Register on September 28, 2007
(72 FR 55120). We also published a
supplemental proposed AD in the
Federal Register on April 13, 2010 (75
FR 18774). Those actions proposed to
require a onetime FPI and ECI of the
propeller hub for cracks.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is provided in the
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]]>Agencies
[Federal Register Volume 75, Number 133 (Tuesday, July 13, 2010)]
[Rules and Regulations]
[Pages 39798-39801]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-16434]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0382; Directorate Identifier 2009-NM-211-AD;
Amendment 39-16361; AD 2010-14-16]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model DHC-8-400, -401,
and -402 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Several cases have been reported where a loss of fluid in the
No.2 hydraulic system has caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations and increased fluid
flow within the No. 1 hydraulic system. In one case, the hydraulic
system control logic did not shut down the PTU and the overspeed
condition persisted, resulting in the illumination of the No.1 HYD
FLUID HOT caution light.
* * * * *
The unsafe condition is possible loss of both the No. 1 and No. 2
hydraulic systems, resulting in the potential loss of several functions
essential for safe flight and landing of the airplane. We are issuing
this AD to require actions to correct the unsafe condition on these
products.
DATES: This AD becomes effective August 17, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 17,
2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 2,
2008 (73 FR 47818, August 15, 2008).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of July
10, 2007 (72 FR 30968, June 5, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7303; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on April 21, 2010 (75
FR 20787), and proposed to supersede AD 2008-17-06, Amendment 39-15644
(73 FR 47818, August 15, 2008). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Since we issued AD 2008-17-06, a modification of the power transfer
unit (PTU) control logic, including the provision of automatic PTU
shutdown in the event of loss of fluid in the No. 2 hydraulic system,
has been developed. The modification addresses the identified unsafe
condition. In addition, the applicability has been revised to remove
airplanes having serial number 4185 and subsequent, since an equivalent
modification has been installed in production on these airplanes.
Transport Canada Civil Aviation (TCCA), which is the aviation authority
for Canada, has issued Canadian Airworthiness Directive CF-2006-08R1,
dated August 31, 2009 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
Several cases have been reported where a loss of fluid in the
No.2 hydraulic system has caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations and increased fluid
flow within the No. 1 hydraulic system. In one case, the hydraulic
system control logic did not shut down the PTU and the overspeed
condition persisted, resulting in the illumination of the No. 1 HYD
FLUID HOT caution light.
As an interim action to avoid possible loss of both the No. 1
and No. 2 hydraulic systems, the Airplane Flight Manual (AFM) has
been revised to include pulling the HYD PWR XFER circuit breaker in
the event of the loss of all hydraulic fluid in the No. 2 hydraulic
system.
Insertion of the resultant Temporary Amendment (TA) No. 13 into
the AFM was mandated in the original issue of this [Canadian]
directive. This instruction * * * remains in effect until * * * this
[revised] directive is accomplished.
Revision 1 of this directive * * * mandates modification of the
PTU control logic, including the provision of automatic PTU shutdown
in the event of loss of fluid in the No. 2 hydraulic system. In
addition, the applicability of the [Canadian] directive has been
revised to remove aircraft Serial Number (SN) 4185 and subsequent,
since an equivalent modification has been installed in production on
these aircraft.
The unsafe condition is possible loss of both the No. 1 and No. 2
hydraulic systems, resulting in the potential loss of several functions
essential for safe flight and landing of the airplane. You may obtain
further information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use
[[Page 39799]]
different words from those in the MCAI to ensure the AD is clear for
U.S. operators and is enforceable. In making these changes, we do not
intend to differ substantively from the information provided in the
MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 42 products of U.S.
registry.
The actions that are required by AD 2008-17-06 and retained in this
AD take about 1 work-hour per product, at an average labor rate of $85
per work hour. Required parts cost about $0 per product. Based on these
figures, the estimated cost of the currently required actions is $85
per product.
We estimate that it will take about 165 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $10,982 per
product. Where the service information lists required parts costs that
are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $1,050,294, or $25,007 per product.
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 determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-39-15644 (73 FR
47818, August 15, 2008) and adding the following new AD:
2010-14-16 Bombardier, Inc.: Amendment 39-16361. Docket No. FAA-
2010-0382; Directorate Identifier 2009-NM-211-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
17, 2010.
Affected ADs
(b) This AD supersedes AD 2008-17-06, Amendment 39-15644.
Applicability
(c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401,
and -402 airplanes, certificated in any category; serial numbers
4001, 4003, 4004, 4006, and 4008 through 4184 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 29:
Hydraulic power.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Several cases have been reported where a loss of fluid in the
No.2 hydraulic system has caused the power transfer unit (PTU) to
overspeed, resulting in pressure fluctuations and increased fluid
flow within the No. 1 hydraulic system. In one case, the hydraulic
system control logic did not shut down the PTU and the overspeed
condition persisted, resulting in the illumination of the No. 1 HYD
FLUID HOT caution light.
As an interim action to avoid possible loss of both the No. 1
and No. 2 hydraulic systems, the Airplane Flight Manual (AFM) has
been revised to include pulling the HYD PWR XFER circuit breaker in
the event of the loss of all hydraulic fluid in the No. 2 hydraulic
system.
Insertion of the resultant Temporary Amendment (TA) No. 13 into
the AFM was mandated in the original issue of this [Canadian]
directive. This instruction * * * remains in effect until * * * this
[revised] directive is accomplished.
Revision 1 of this directive * * * mandates modification of the
PTU control logic, including the provision of automatic PTU shutdown
in the event of loss of fluid in the No. 2 hydraulic system. In
addition, the applicability of the [Canadian] directive has been
revised to remove aircraft Serial Number (SN) 4185 and subsequent,
since an equivalent modification has been installed in production on
these aircraft.
The unsafe condition is possible loss of both the No. 1 and No. 2
hydraulic systems, resulting in the potential loss of several
functions essential for safe flight and landing of the airplane.
Compliance
(f) 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 2007-12-03 AIRPLANE FLIGHT MANUAL
(AFM) REVISION
(g) Within 14 days after July 10, 2007 (the effective date of AD
2007-12-03, Amendment 39-15081, which was superseded by AD 2008-17-
06), revise the Limitations section of the applicable AFM to include
the information in the applicable Bombardier temporary amendment
specified in Table 1 of this AD, as specified in the temporary
amendment. These temporary amendments introduce procedures for
[[Page 39800]]
pulling the ``HYD PWR XFER'' circuit breaker in the event of the
loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system.
Operate the airplane according to the limitations and procedures in
the applicable temporary amendment.
Table 1--AFM Temporary Amendments
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Use Bombardier
For model-- temporary Issue-- Dated-- To Bombardier Dash 8 Q400 Airplane
amendment-- Flight Manual--
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DHC-8-400 airplanes.................... 13 1 July 14, 2005........................ PSM 1-84-1A.
DHC-8-401 airplanes.................... 13 1 July 14, 2005........................ PSM 1-84-1A.
DHC-8-402 airplanes.................... 13 1 July 14, 2005........................ PSM 1-84-1A.
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Note 1: This may be done by inserting a copy of the applicable
temporary amendment into the applicable AFM. When the applicable
temporary amendment has been included in general revisions of the
AFM, the general revisions may be inserted into the AFM, provided
the relevant information in the general revisions is identical to
that in the temporary amendment.
Restatement of Requirements of AD 2008-17-06: AFM Revision
(h) Within 14 days after September 2, 2008 (the effective date
of AD 2008-17-06), revise the applicable AFM Normal and Abnormal
Procedures section to include the information in the applicable
Bombardier temporary amendment specified in Table 2 of this AD, as
specified in the temporary amendment. These temporary amendments
introduce additional procedures for ensuring that the ``PTU CNTRL''
switch is Normal, the ``PTU CNTRL ON'' advisory light is out, and
the ``HYD PWR XFER'' circuit breaker is pulled in the event of the
illumination of the ``2 HYD ISO VALVE'' caution light.
After accomplishing the AFM revision, the AFM limitation required by
paragraph (g) in this AD may be removed from the AFM.
Table 2--AFM Temporary Amendments
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Use Bombardier
For model-- temporary Issue-- Dated-- To Bombardier Dash 8 Q400 Airplane
amendment-- Flight Manual--
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DHC-8-400 airplanes.................... 13 3 June 9, 2008......................... PSM 1-84-1A.
DHC-8-401 airplanes.................... 13 3 June 9, 2008......................... PSM 1-84-1A.
DHC-8-402 airplanes.................... 13 3 June 9, 2008......................... PSM 1-84-1A.
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New Requirements of This AD: Actions
(i) Within 6,000 flight hours after the effective date of this
AD, modify the PTU control logic, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-29-22,
Revision A, dated February 24, 2009. Doing this modification
terminates the requirements of paragraphs (g) and (h) of this AD,
and after the modification has been done, the AFM limitation
required by paragraphs (g) and (h) of this AD may be removed from
the AFM.
(j) Modifying the PTU control logic is also acceptable for
compliance with the requirements of paragraph (i) of this AD if done
before the effective date of this AD, in accordance with Bombardier
Service Bulletin 84-29-22, dated December 5, 2008.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(k) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Program
Manager, Continuing Operational Safety, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516-
228-7300; fax 516-794-5531. Before using any approved AMOC on any
airplane to which the AMOC applies, notify your principal
maintenance inspector (PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal inspector, your local Flight
Standards District Office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(l) Refer to MCAI Canadian Airworthiness Directive CF-2006-08R1,
dated August 31, 2009; the Bombardier temporary amendments specified
in Tables 1 and 2; and Bombardier Service Bulletin 84-29-22,
Revision A, dated February 24, 2009; for related information.
Material Incorporated by Reference
(m) You must use Bombardier Service Bulletin 84-29-22, Revision
A, dated February 24, 2009, and the applicable temporary amendment
identified in Table 3 of this AD; as applicable; to do the actions
required by this AD, unless the AD specifies otherwise.
Table 3--All Temporary Amendments Incorporated by Reference
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To Bombardier Dash 8
Bombardier temporary amendment-- Issue-- Dated-- Q400 Airplane Flight
Manual--
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13.................................... 1 July 14, 2005...................... Model 400 PSM 1-84-1A.
13.................................... 1 July 14, 2005...................... Model 401 PSM 1-84-1A.
13.................................... 1 July 14, 2005...................... Model 402 PSM 1-84-1A.
13.................................... 3 June 9, 2008....................... Model 400 PSM 1-84-1A.
13.................................... 3 June 9, 2008....................... Model 401 PSM 1-84-1A.
13.................................... 3 June 9, 2008....................... Model 402 PSM 1-84-1A.
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[[Page 39801]]
(1) The Director of the Federal Register approved the
incorporation by reference of Bombardier Service Bulletin 84-29-22,
Revision A, dated February 24, 2009, under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of the service information contained in
Table 4 of this AD on September 2, 2008 (73 FR 47818, August 15,
2008).
Table 4--Material Previously Incorporated by Reference in AD 2008-17-06
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To Bombardier Dash 8
Bombardier temporary amendment-- Issue-- Dated-- Q400 Airplane Flight
Manual--
----------------------------------------------------------------------------------------------------------------
13.................................... 3 June 9, 2008....................... Model 400 PSM 1-84-1A.
13.................................... 3 June 9, 2008....................... Model 401 PSM 1-84-1A.
13.................................... 3 June 9, 2008....................... Model 402 PSM 1-84-1A.
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(3) On July 10, 2007 (72 FR 30968, June 5, 2007), the Director
of the Federal Register approved the incorporation by reference of
the temporary amendments identified in Table 5 of this AD.
Table 5--Material Previously Incorporated by Reference in AD 2007-12-03
----------------------------------------------------------------------------------------------------------------
To Bombardier Dash 8
Bombardier temporary amendment-- Issue-- Dated-- Q400 Airplane Flight
Manual--
----------------------------------------------------------------------------------------------------------------
13.................................... 1 July 14, 2005...................... Model 400 PSM 1-84-1A.
13.................................... 1 July 14, 2005...................... Model 401 PSM 1-84-1A.
13.................................... 1 July 14, 2005...................... Model 402 PSM 1-84-1A.
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(4) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.qseries@aero.bombardier.com; Internet https://www.bombardier.com.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(6) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on June 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-16434 Filed 7-12-10; 8:45 am]
BILLING CODE 4910-13-P
