Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 47818-47822 [E8-18683]
Download as PDF
<![CDATA[
47818
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations
Authority: 12 U.S.C. 4001–4010, 12 U.S.C.
5001–5018.
2. The Fourth District routing symbol
list in appendix A is revised to read as
follows:
I
Appendix A to Part 229—Routing
Number Guide to Next-Day Availability
Checks and Local Checks
*
*
*
*
*
Fourth Federal Reserve District
[Federal Reserve Bank of Cleveland]
Head Office
0220 2220
0223 2223
0410 2410
0412 2412
0420 2420
0421 2421
0422 2422
0423 2423
0430 2430
0432 2432
0433 2433
0434 2434
0440 2440
0441 2441
0442 2442
0515 2515
0519 2519
0720 2720
0724 2724
0740 2740
0749 2749
0813 2813
0830 2830
0839 2839
0863 2863
*
*
*
SUPPLEMENTARY INFORMATION:
Background
On November 8, 2007, the FAA
published a final rule to establish part
26 in the Code of Federal Regulations
(72 FR 63364). The heading for subpart
B of that part contained the phrase
‘‘aging systems’’ instead of the intended
‘‘airplane systems.’’ This final rule
corrects that error.
Justification for Immediate Adoption
Because this action corrects merely a
typographical error, the FAA finds that
notice and public comment under 5
U.S.C. 553(b) is unnecessary. For the
same reason, the FAA finds that good
cause exists under 5 U.S.C. 553(d) for
making this rule effective upon
publication.
List of Subjects in 14 CFR Part 26
*
*
By order of the Board of Governors of the
Federal Reserve System, acting through the
Secretary of the Board under delegated
authority, August 11, 2008.
Robert deV. Frierson,
Deputy Secretary of the Board.
[FR Doc. E8–18850 Filed 8–14–08; 8:45 am]
BILLING CODE 6210–01–P
DEPARTMENT OF TRANSPORTATION
14 CFR Part 26
[Docket No. FAA–2004–18379; Amendment
No. 26–0]
PART 26—CONTINUED
AIRWORTHINESS AND SAFETY
IMPROVEMENTS FOR TRANSPORT
CATEGORY AIRPLANES
1. The authority citation for part 26
continues to read as follows:
I
Subpart B—Enhanced Airworthiness
Program for Airplane Systems
2. The heading for subpart B is revised
to read as set forth above.
I
RIN 2120–AI31
sroberts on PROD1PC70 with PROPOSALS
Aircraft, Aviation safety, Continued
airworthiness.
I In consideration of the foregoing, the
Federal Aviation Administration
amends Chapter I of Title 14, Code of
Federal Regulations part 26 as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702 and 44704.
Federal Aviation Administration
Enhanced Airworthiness Program for
Airplane Systems/Fuel Tank Safety
(EAPAS/FTS); Technical Correction
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; technical correction.
AGENCY:
VerDate Aug<31>2005
SUMMARY: This final rule corrects a
subpart heading in the Code of Federal
Regulations. The heading was
inadvertently misstated when the FAA
published the rule in November 2007.
EFFECTIVE DATE: This final rule is
effective August 15, 2008.
FOR FURTHER INFORMATION CONTACT:
Annette K. Kovite, ANM–113,
Standardization Branch, Federal
Aviation Administration, 1601 Lind
Avenue, SW., Renton, WA 98057,
telephone: 425–227–1262, facsimile:
425–227–1320, e-mail:
Annette.Kovite@faa.gov.
17:44 Aug 14, 2008
Jkt 214001
Issued in Washington, DC, on August 11,
2008.
Pamela Hamilton-Powell,
Director, Office of Rulemaking, Aviation
Safety.
[FR Doc. E8–18859 Filed 8–14–08; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0864; Directorate
Identifier 2008–NM–120–AD; Amendment
39–15644; AD 2008–17–06]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Bombardier
Model DHC–8–400 series airplanes. The
existing AD currently requires revising
the Limitations section of the airplane
flight manual (AFM) to include
procedures for 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. This AD
requires a revision to the AFM to
include 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. This
AD resulted from low No. 2 hydraulic
pressure in-flight, which caused the
power transfer unit to overspeed, and
the fluid flow within the No. 1
hydraulic system to increase. We are
issuing this AD to prevent 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.
DATES: This AD becomes effective
September 2, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 2, 2008.
On July 10, 2007 (72 FR 30968, June
5, 2007), the Director of the Federal
Register approved the incorporation by
reference of certain other publications.
We must receive any comments on
this AD by September 15, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
E:\FR\FM\15AUR1.SGM
15AUR1
47819
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Bombardier, Inc.,
Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview,
Ontario M3K 1Y5, Canada.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Fabio Buttitta, 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) 228–7303; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
On May 25, 2007, the FAA issued AD
2007–12–03, amendment 39–15081 (72
FR 30968, June 5, 2007). That AD
applies to certain Bombardier Model
DHC–8–400 series airplanes. That AD
requires revising the airplane flight
manual (AFM) to include procedures for
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. That AD resulted
from low No. 2 hydraulic pressure inflight, which caused the power transfer
unit (PTU) to overspeed, and the fluid
flow within the No. 1 hydraulic system
to increase. The actions specified in that
AD are intended to prevent 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.
Actions Since AD Was Issued
Since we issued AD 2007–12–03,
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, advises that it has
received an additional report of loss of
the No. 2 hydraulic system on a Model
DHC–8–402 airplane, causing the PTU
to overspeed, increasing the fluid flow
within the No. 1 hydraulic system.
Investigation revealed that, after the
caution light for the No. 2 hydraulic
system had illuminated, the PTU was
left in the ‘‘ON’’ position. The
flightcrew had followed AFM
procedures, as specified in the AFM
revision required by AD 2007–12–03,
and did not pull the circuit breaker
because the hydraulic fluid from the No.
2 system was not completely depleted.
Therefore, we find that the AFM
revision required by AD 2007–12–03
does not adequately prevent 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. The hydraulic power
transfer system on the Model DHC–8–
400 and DHC–8–401 airplanes are
similar to those on the affected Model
DHC–8–402 airplanes. Therefore, all of
the models are subject to the same
unsafe condition.
Relevant Service Information
Bombardier has issued the temporary
amendments specified in the following
table (AD 2007–12–03 refers to Issue 1
of Bombardier Temporary Amendments
13, all dated July 14, 2005, as
appropriate sources of service
information for accomplishing the
required AFM revision).
REVISED AFM TEMPORARY AMENDMENTS
Use
Bombardier
temporary
amendment—
For model—
sroberts on PROD1PC70 with PROPOSALS
DHC–8–400 airplanes ................................
DHC–8–401 airplanes ................................
DHC–8–402 airplanes ................................
VerDate Aug<31>2005
17:44 Aug 14, 2008
Jkt 214001
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.
Issue—
13
13
13
The procedures specified in Issue 3
for addressing the loss of all hydraulic
fluid in the No. 1 and No. 2 hydraulic
systems are identical to those specified
in Issue 1. Issue 3 has been revised to
include procedures for ensuring that the
PTU is disabled when the fluid level in
the No. 2 hydraulic system falls to a
value where the PTU becomes a hazard
to the No. 1 hydraulic system. This is
achieved by 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. TCCA previously mandated Issue
1 (‘‘or later’’) of the service information
and issued Canadian airworthiness
directive CF–2006–08, dated April 26,
Dated—
3
3
3
2006 (referred to after this as ‘‘the
MCAI’’), to ensure the continued
airworthiness of these airplanes in
Canada.
FAA’s Determination and Requirements
of this AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
develop on other products of the same
type design.
Therefore, we are issuing this AD to
supersede AD 2007–12–03. This new
AD retains the requirements of the
existing AD. This AD also requires a
revision to the Normal and Abnormal
Procedures section of the AFM to
include 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.
In addition, AD 2007–12–03 specifies
to revise the Limitations section of the
AFM; however, this AD specifies to
revise the Normal and Abnormal
Procedures section.
E:\FR\FM\15AUR1.SGM
15AUR1
47820
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations
Interim Action
Authority for This Rulemaking
We consider this AD interim action.
The manufacturer is currently
developing a modification that will
address the unsafe condition identified
in this AD. Once this modification is
developed, approved, and available, we
might consider additional 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.
FAA’s Justification and Determination
of the Effective Date
Fluid loss in the No. 2 hydraulic
system causing a PTU overspeed and
increased fluid flow in the No. 1
hydraulic system could cause the loss of
several functions essential for safe flight
and landing of the airplane. Because of
our requirement to promote safe flight of
civil aircraft, and thus the critical need
to ensure the proper functioning of the
No.1 and No. 2 hydraulic systems and
the short compliance time involved
with this action, this AD must be issued
immediately.
Because an unsafe condition exists
that requires the immediate adoption of
this AD, we find that notice and
opportunity for prior public comment
hereon are impracticable and that good
cause exists for making this amendment
effective in less than 30 days.
sroberts on PROD1PC70 with PROPOSALS
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2008–0864; Directorate Identifier 2008–
NM–120–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
VerDate Aug<31>2005
17:44 Aug 14, 2008
Jkt 214001
Regulatory Findings
We have 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 that the 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 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, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
I
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Aviation Regulations (14 CFR part 39) as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–15081 (72
FR 30968, June 5, 2007) and adding the
following new AD:
I
2008–17–06 Bombardier, Inc. (Formerly de
Havilland, Inc.): Docket No. FAA–2008–
0864; Directorate Identifier 2008–NM–
120–AD; Amendment 39–15644.
Effective Date
(a) This AD becomes effective September 2,
2008.
Affected ADs
(b) This AD supersedes AD 2007–12–03.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400, DHC–8–401, and DHC–8–402
airplanes, certificated in any category; serial
numbers 4001 and 4003 and subsequent.
Unsafe Condition
(d) This AD results from low No. 2
hydraulic pressure in-flight, which caused
the power transfer unit to overspeed, and the
fluid flow within the No. 1 hydraulic system
to increase. We are issuing this AD to prevent
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
(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.
Requirements of AD 2007–12–03
Airplane Flight Manual (AFM) Revision
(f) Within 14 days after July 10, 2007 (the
effective date of AD 2007–12–03), 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
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.
E:\FR\FM\15AUR1.SGM
15AUR1
47821
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations
TABLE 1—AFM TEMPORARY AMENDMENTS
Use Bombardier
temporary
amendment—
For model—
DHC–8–400 airplanes ................................
DHC–8–401 airplanes ................................
DHC–8–402 airplanes ................................
Dated—
Issue—
13
13
13
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.
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.
New Requirements of This AD
AFM Revision
(g) Within 14 days after the effective date
of this AD, 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 (f) in this AD may be removed
from the AFM.
TABLE 2—AFM TEMPORARY AMENDMENTS
Use
Bombardier
temporary
amendment—
For model—
DHC–8–400 airplanes ................................
DHC–8–401 airplanes ................................
DHC–8–402 airplanes ................................
Dated—
Issue—
13
13
13
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, New York Aircraft
Certification Office, 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: Fabio
Buttitta, Aerospace Engineer, Systems and
Flight Test Branch, ANE–172, FAA, New
York Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury, New
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.
York 11590; telephone (516) 228–7303; fax
(516) 794–5531. Before using any approved
AMOC on any airplane to which the AMOC
applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your
local FSDO.
Related Information
(i) Canadian airworthiness directive CF–
2006–08, dated April 26, 2006, also addresses
the subject of this AD.
Material Incorporated by Reference
(j) You must use the applicable temporary
amendment identified in Table 3 of this AD
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
(Only the last pages of the temporary
amendments identified in Table 4 of this AD
contain the issue date, no other pages of
those documents are dated.)
TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE
Bombardier temporary amendment—
13
13
13
13
13
13
Dated—
Issue—
.....................................................................
.....................................................................
.....................................................................
.....................................................................
.....................................................................
.....................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the temporary amendments identified in
1
1
1
3
3
3
To Bombardier Dash 8
Q400 airplane flight manual—
July 14, 2005 ...................................................
July 14, 2005 ...................................................
July 14, 2005 ...................................................
June 9, 2008 ....................................................
June 9, 2008 ....................................................
June 9, 2008 ....................................................
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.
Table 4 of this AD in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
sroberts on PROD1PC70 with PROPOSALS
TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE
Bombardier temporary amendment—
13 .....................................................................
13 .....................................................................
VerDate Aug<31>2005
17:44 Aug 14, 2008
Jkt 214001
Dated—
Issue—
PO 00000
3
3
Frm 00005
To Bombardier Dash 8
Q400 airplane flight manual—
June 9, 2008 ....................................................
June 9, 2008 ....................................................
Model 400 PSM 1–84–1A.
Model 401 PSM 1–84–1A.
Fmt 4700
Sfmt 4700
E:\FR\FM\15AUR1.SGM
15AUR1
47822
Federal Register / Vol. 73, No. 159 / Friday, August 15, 2008 / Rules and Regulations
TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE
Bombardier temporary amendment—
Dated—
Issue—
13 .....................................................................
(2) On July 10, 2007 (72 FR 30968, June 5,
2007), the Director of the Federal Register
approved the incorporation by reference of
3
To Bombardier Dash 8
Q400 airplane flight manual—
June 9, 2008 ....................................................
Model 402 PSM 1–84–1A.
the temporary amendments identified in
Table 5 of this AD.
TABLE 5—PREVIOUSLY APPROVED MATERIAL INCORPORATED BY REFERENCE
Bombardier temporary amendment—
13 .....................................................................
13 .....................................................................
13 .....................................................................
(3) Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 31,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18683 Filed 8–14–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0844; Directorate
Identifier 2007–SW–23–AD; Amendment 39–
15635; AD 2008–16–17]
RIN 2120–AA64
Airworthiness Directives; PZL Swidnik
S. A. Model W–3A Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
sroberts on PROD1PC70 with PROPOSALS
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the PZL
Swidnik S. A. (PZL) Model W–3A
helicopters. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by the
VerDate Aug<31>2005
17:44 Aug 14, 2008
Jkt 214001
Dated—
Issue—
1
1
1
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.
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community. The MCAI states: ‘‘In PZL
W–3A helicopter S/N 37.07.05, and
previously also in the PZL W–3AS
model helicopters, leakage was found in
the pipe 37.59.006.00.00 installed in the
pressure line of hydraulic system 2, in
the part between the hydraulic block
and the ground hydraulic unit panel.
The hydraulic system in the part
between hydraulic blocks and the
ground hydraulic unit panel is used
only during periodical inspections, for
the performance of which it is required
to use the hydraulic power unit. This
condition, if not corrected, could result
in a fire hazard.’’ The actions specified
in this AD are intended to prevent this
unsafe condition.
DATES: This AD becomes effective on
September 2, 2008.
The Director of the Federal Register
approved the incorporation by reference
´
of ‘‘PZL-Swidnik’’ S.A. Mandatory
Bulletin No. BO–37–07–192, dated
´
January 12, 2007, and ‘‘PZL-Swidnik’’
Technical Bulletin No. BT–37–07–196,
dated April 24, 2007, as of September 2,
2008.
We must receive comments on this
AD by October 14, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting your
comments electronically.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
You may get the service information
identified in this AD from WSK ‘‘PZL´
´
Swidnik’’ S.A., Al. Lotnikow Polskich 1,
´
21–045 Swidnik, Poland, telephone
(+48 81) 468 09 01, 751 20 71, or fax
(+48 81) 468 09 19, 751 21 73, e-mail:
hem@pzl.swidnik.pl.
Examining the 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, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is stated in the
ADDRESSES section of this AD.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Uday Garadi, Aerospace Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, Fort Worth,
Texas 76193–0110, telephone (817)
222–5123, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: The
EASA, which is the Technical Agent for
the Member States of the European
Community, has issued EASA
Emergency AD No. 2007–0072R1, dated
July 6, 2007 (referred to after this as ‘‘the
MCAI’’), to correct an unsafe condition
for the PZL Model W–3A helicopters.
The MCAI states: ‘‘In PZL W–3A
helicopter S/N 37.07.05, and previously
also in the PZL W–3AS model
helicopters, leakage was found in the
E:\FR\FM\15AUR1.SGM
15AUR1
]]>Agencies
[Federal Register Volume 73, Number 159 (Friday, August 15, 2008)]
[Rules and Regulations]
[Pages 47818-47822]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18683]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0864; Directorate Identifier 2008-NM-120-AD;
Amendment 39-15644; AD 2008-17-06]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to certain Bombardier Model DHC-8-400 series
airplanes. The existing AD currently requires revising the Limitations
section of the airplane flight manual (AFM) to include procedures for
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. This AD
requires a revision to the AFM to include 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. This AD resulted from low No. 2 hydraulic
pressure in-flight, which caused the power transfer unit to overspeed,
and the fluid flow within the No. 1 hydraulic system to increase. We
are issuing this AD to prevent 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.
DATES: This AD becomes effective September 2, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 2,
2008.
On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the
Federal Register approved the incorporation by reference of certain
other publications.
We must receive any comments on this AD by September 15, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-
[[Page 47819]]
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue,
SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Bombardier,
Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, 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) 228-7303; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
On May 25, 2007, the FAA issued AD 2007-12-03, amendment 39-15081
(72 FR 30968, June 5, 2007). That AD applies to certain Bombardier
Model DHC-8-400 series airplanes. That AD requires revising the
airplane flight manual (AFM) to include procedures for 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. That AD
resulted from low No. 2 hydraulic pressure in-flight, which caused the
power transfer unit (PTU) to overspeed, and the fluid flow within the
No. 1 hydraulic system to increase. The actions specified in that AD
are intended to prevent 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.
Actions Since AD Was Issued
Since we issued AD 2007-12-03, Transport Canada Civil Aviation
(TCCA), which is the airworthiness authority for Canada, advises that
it has received an additional report of loss of the No. 2 hydraulic
system on a Model DHC-8-402 airplane, causing the PTU to overspeed,
increasing the fluid flow within the No. 1 hydraulic system.
Investigation revealed that, after the caution light for the No. 2
hydraulic system had illuminated, the PTU was left in the ``ON''
position. The flightcrew had followed AFM procedures, as specified in
the AFM revision required by AD 2007-12-03, and did not pull the
circuit breaker because the hydraulic fluid from the No. 2 system was
not completely depleted.
Therefore, we find that the AFM revision required by AD 2007-12-03
does not adequately prevent 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. The hydraulic
power transfer system on the Model DHC-8-400 and DHC-8-401 airplanes
are similar to those on the affected Model DHC-8-402 airplanes.
Therefore, all of the models are subject to the same unsafe condition.
Relevant Service Information
Bombardier has issued the temporary amendments specified in the
following table (AD 2007-12-03 refers to Issue 1 of Bombardier
Temporary Amendments 13, all dated July 14, 2005, as appropriate
sources of service information for accomplishing the required AFM
revision).
Revised AFM Temporary Amendments
----------------------------------------------------------------------------------------------------------------
Use Bombardier To Bombardier Dash 8
For model-- temporary Issue-- Dated-- Q400 airplane flight
amendment-- manual--
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
The procedures specified in Issue 3 for addressing the loss of all
hydraulic fluid in the No. 1 and No. 2 hydraulic systems are identical
to those specified in Issue 1. Issue 3 has been revised to include
procedures for ensuring that the PTU is disabled when the fluid level
in the No. 2 hydraulic system falls to a value where the PTU becomes a
hazard to the No. 1 hydraulic system. This is achieved by 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.
TCCA previously mandated Issue 1 (``or later'') of the service
information and issued Canadian airworthiness directive CF-2006-08,
dated April 26, 2006 (referred to after this as ``the MCAI''), to
ensure the continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of this AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Therefore, we are issuing this AD to supersede AD 2007-12-03. This
new AD retains the requirements of the existing AD. This AD also
requires a revision to the Normal and Abnormal Procedures section of
the AFM to include 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.
In addition, AD 2007-12-03 specifies to revise the Limitations
section of the AFM; however, this AD specifies to revise the Normal and
Abnormal Procedures section.
[[Page 47820]]
Interim Action
We consider this AD interim action. The manufacturer is currently
developing a modification that will address the unsafe condition
identified in this AD. Once this modification is developed, approved,
and available, we might consider additional rulemaking.
FAA's Justification and Determination of the Effective Date
Fluid loss in the No. 2 hydraulic system causing a PTU overspeed
and increased fluid flow in the No. 1 hydraulic system could cause the
loss of several functions essential for safe flight and landing of the
airplane. Because of our requirement to promote safe flight of civil
aircraft, and thus the critical need to ensure the proper functioning
of the No.1 and No. 2 hydraulic systems and the short compliance time
involved with this action, this AD must be issued immediately.
Because an unsafe condition exists that requires the immediate
adoption of this AD, we find that notice and opportunity for prior
public comment hereon are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2008-0864; Directorate Identifier 2008-NM-120-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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 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 that the 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 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends part 39 of the Federal Aviation Regulations (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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-15081 (72 FR 30968, June 5, 2007) and adding the
following new AD:
2008-17-06 Bombardier, Inc. (Formerly de Havilland, Inc.): Docket
No. FAA-2008-0864; Directorate Identifier 2008-NM-120-AD; Amendment
39-15644.
Effective Date
(a) This AD becomes effective September 2, 2008.
Affected ADs
(b) This AD supersedes AD 2007-12-03.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401,
and DHC-8-402 airplanes, certificated in any category; serial
numbers 4001 and 4003 and subsequent.
Unsafe Condition
(d) This AD results from low No. 2 hydraulic pressure in-flight,
which caused the power transfer unit to overspeed, and the fluid
flow within the No. 1 hydraulic system to increase. We are issuing
this AD to prevent 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
(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.
Requirements of AD 2007-12-03
Airplane Flight Manual (AFM) Revision
(f) Within 14 days after July 10, 2007 (the effective date of AD
2007-12-03), 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 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.
[[Page 47821]]
Table 1--AFM Temporary Amendments
----------------------------------------------------------------------------------------------------------------
Use Bombardier To Bombardier Dash 8
For model-- temporary Issue-- Dated-- Q400 airplane flight
amendment-- manual--
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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.
New Requirements of This AD
AFM Revision
(g) Within 14 days after the effective date of this AD, 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 (f) in this
AD may be removed from the AFM.
Table 2--AFM Temporary Amendments
----------------------------------------------------------------------------------------------------------------
Use Bombardier To Bombardier Dash 8
For model-- temporary Issue-- Dated-- Q400 airplane flight
amendment-- manual--
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(h) The Manager, New York Aircraft Certification Office, 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: Fabio Buttitta, 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) 228-7303; fax (516) 794-5531. Before using any
approved AMOC on any airplane to which the AMOC applies, notify your
appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(i) Canadian airworthiness directive CF-2006-08, dated April 26,
2006, also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use the applicable temporary amendment identified
in Table 3 of this AD to perform the actions that are required by
this AD, unless the AD specifies otherwise. (Only the last pages of
the temporary amendments identified in Table 4 of this AD contain
the issue date, no other pages of those documents are dated.)
Table 3--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
To Bombardier Dash 8 Q400 airplane
Bombardier temporary amendment-- Issue-- Dated-- 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.
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.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the temporary amendments identified in
Table 4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part
51.
Table 4--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
To Bombardier Dash 8 Q400 airplane
Bombardier temporary amendment-- Issue-- Dated-- flight manual--
----------------------------------------------------------------------------------------------------------------
13............................... 3 June 9, 2008........ Model 400 PSM 1-84-1A.
13............................... 3 June 9, 2008........ Model 401 PSM 1-84-1A.
[[Page 47822]]
13............................... 3 June 9, 2008........ Model 402 PSM 1-84-1A.
----------------------------------------------------------------------------------------------------------------
(2) 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--Previously Approved Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
To Bombardier Dash 8 Q400 airplane
Bombardier temporary amendment-- Issue-- Dated-- 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.
----------------------------------------------------------------------------------------------------------------
(3) Contact Bombardier, Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada,
for a copy of this service information. You may review copies at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 31, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18683 Filed 8-14-08; 8:45 am]
BILLING CODE 4910-13-P
