Airworthiness Directives; Bombardier, Inc. Airplanes, 13483-13486 [2015-05735]
Download as PDF
<![CDATA[
Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations
Rmajette on DSK2VPTVN1PROD with RULES
airworthy upper skin. Repeat the inspection
of the longeron assembly at intervals not to
exceed 50 hours TIS.
(ii) If there is a crack, corrosion, or other
damage in the longeron assembly, before
further flight:
(A) Repair the longeron assembly or
replace it with an airworthy longeron
assembly, part number (P/N) 206–031–314–
237B, and reinstall the upper skin or replace
it with an airworthy upper skin.
(B) Install three external strap doublers in
accordance with Part III, paragraphs 5
through10 of Bell Helicopter Alert Service
Bulletin 407–11–95, Revision C, dated April
20, 2012 (ASB).
(C) Repeat the inspection of the longeron
assembly at intervals not to exceed 50 hours
TIS.
(2) If there is no crack in the upper skin,
within 10 hours TIS, visually inspect the
longeron assembly using a 10X or higher
power magnifying glass for a crack,
corrosion, or other damage.
(i) If there is a crack, corrosion, or other
damage in the longeron assembly, before
further flight:
(A) Repair the longeron assembly or
replace it with an airworthy longeron
assembly, P/N 206–031–314–237B.
(B) Install three external strap doublers in
accordance with Part III, paragraphs 5
through 10 of the ASB.
(C) Repeat the inspection of the upper skin
and longeron assembly at intervals not to
exceed 50 hours TIS.
(ii) If there are no cracks, corrosion, or
other damage in the longeron assembly,
repeat the inspection of the upper skin and
longeron assembly at intervals not to exceed
50 hours TIS.
(3) Replacing the longeron assembly with
longeron assembly, P/N 206–031–314–237B,
and installing three external strap doublers
constitutes terminating action for this AD.
(4) If there is no crack in the upper skin
and there is no crack, corrosion, or other
damage in the longeron assembly, you may
install three external strap doublers in
accordance with Part III, paragraphs 5
through 10 of the ASB. This option extends
the recurring 50 hours TIS inspection
interval to 150 hours TIS.
No. CF–2011–42, dated November 9, 2011.
You may view the TCCA AD on the Internet
at https://www.regulations.gov in Docket No.
FAA–2014–0070.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Sharon Miles,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
sharon.y.miles@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
DEPARTMENT OF TRANSPORTATION
(g) Additional Information
The subject of this AD is addressed in
Transport Canada Civil Aviation (TCCA) AD
VerDate Sep<11>2014
14:05 Mar 13, 2015
Jkt 235001
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 5313, Fuselage Main, Longeron/
Stringer.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bell Helicopter Alert Service Bulletin
407–11–95, Revision C, dated April 20, 2012.
(ii) Reserved.
(3) For BHTC service information
identified in this AD, contact Bell Helicopter
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4; telephone
(450) 437–2862 or (800) 363–8023; fax (450)
433–0272; or at
https://www.bellcustomer .com/files/.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this 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/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on March 3,
2015.
Bruce E. Cain,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2015–05571 Filed 3–13–15; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0491; Directorate
Identifier 2015–NM–019–AD; Amendment
39–18117; AD 2015–05–07]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–02–
SUMMARY:
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
13483
06 for certain Bombardier, Inc. Model
CL–600–2B16 (CL–604 Variant)
airplanes. AD 2015–02–06 required a
revision to the airplane flight manual, a
revision to the maintenance or
inspection program, as applicable, and
replacement of horizontal stabilizer trim
actuators (HSTAs) having certain part
numbers. This new AD continues to
require those actions and corrects
certain typographical errors. This AD
was prompted by the discovery of three
typographical errors in AD 2015–02–06.
We are issuing this AD to detect and
correct loose spur gear bolts on the
HSTA, which, if combined with the
failure of the primary load path, could
lead to failure of the HSTA and
subsequent loss of the airplane.
DATES: This AD becomes effective
March 16, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 6, 2015 (80 FR 5017,
January 30, 2015).
We must receive comments on this
AD by April 30, 2015
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–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, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
• For service information identified
in this AD, contact Bombardier, Inc.,
ˆ
400 Cote Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone
514–855–5000; fax 514–855–7401; email
thd.crj@aero.bombardier.com; Internet
https://www.bombardier.com. You may
view this referenced service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0491; or in person at the Docket
Operations office between 9 a.m. and
5 p.m., Monday through Friday, except
E:\FR\FM\16MRR1.SGM
16MRR1
13484
Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations
Rmajette on DSK2VPTVN1PROD with RULES
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 in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Ricardo Garcia, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7331; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
On January 11, 2015, we issued AD
2015–02–06, Amendment 39–18073 (80
FR 5017, January 30, 2015). AD 2015–
02–06 applied to certain Bombardier,
Inc. Model CL–600–2B16 (CL–604
Variant) airplanes. AD 2015–02–06 was
prompted by reports of loose, broken, or
backed-out spur gear bolts on the HSTA.
AD 2015–02–06 required a revision to
the airplane flight manual, a revision to
the maintenance or inspection program,
as applicable, and replacement of
HSTAs having certain part numbers. We
issued AD 2015–02–06 to detect and
correct loose spur gear bolts on the
HSTA, which, if combined with the
failure of the primary load path, could
lead to failure of the HSTA and
subsequent loss of the airplane.
Since we issued AD 2015–02–06,
Amendment 39–18073 (80 FR 5017,
January 30, 2015), three typographical
errors were discovered in AD 2015–02–
06.
As published, a digit was missing
from the engineer’s phone number in
the FOR FURTHER INFORMATION CONTACT
section of the preamble of AD 2015–02–
06, Amendment 39–18073 (80 FR 5017,
January 30, 2015). The correct phone
number is ‘‘516–228–7331.’’
As published, the AD number of AD
2015–02–06, Amendment 39–18073 (80
FR 5017, January 30, 2015), appears as
‘‘2014–02–06’’ in the Product
Identification line of the regulatory text
of the AD. The correct AD number is
‘‘2015–02–06.’’ The AD number is
referenced correctly throughout the
remainder of that document.
As published, a vendor part number
in paragraph (j) of AD 2015–02–06,
Amendment 39–18073 (80 FR 5017,
January 30, 2015), was incorrectly
identified as ‘‘845401.’’ The correct
vendor part number is ‘‘8454–1.’’
Since this new AD replaces AD 2015–
02–06, Amendment 39–18073 (80 FR
5017, January 30, 2015), there are no
additional changes in this new AD.
VerDate Sep<11>2014
14:05 Mar 13, 2015
Jkt 235001
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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because of the urgency to correct
the part number and AD number errors
to avoid non-compliance. Therefore, we
determined that notice and opportunity
for public comment before issuing this
AD are impracticable and that good
cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2015–0491;
Directorate Identifier 2015–NM–019–
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.
Costs of Compliance
We estimate that this AD affects 125
airplanes of U.S. registry.
The actions required by AD 2015–02–
06, Amendment 39–18073 (80 FR 5017,
January 30, 2015), and retained in this
AD take about 21 work-hours per
product, at an average labor rate of $85
per work-hour. Required parts cost
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
about $0 per product. Based on these
figures, the estimated cost of the actions
that are required by AD 2015–02–06 is
$1,785 per product.
The new requirements of this AD add
no additional economic burden.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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 that 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);
3. Will not affect intrastate aviation in
Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
E:\FR\FM\16MRR1.SGM
16MRR1
Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations
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 airworthiness directive (AD)
2015–02–06, Amendment 39–18073 (80
FR 5017, January 30, 2015), and adding
the following new AD:
■
2015–05–07 Bombardier, Inc.: Amendment
39–18117. Docket No. FAA–2015–0491;
Directorate Identifier 2015–NM–019–AD.
(a) Effective Date
This AD becomes effective March 16, 2015.
(b) Affected ADs
This AD replaces AD 2015–02–06,
Amendment 39–18073 (80 FR 5017, January
30, 2015).
(c) Applicability
This AD applies to Bombardier, Inc. Model
CL–600–2B16 (CL–604 Variant) airplanes,
certificated in any category, serial numbers
5301 and subsequent, equipped with
horizontal stabilizer trim actuator (HSTA)
part number (P/N) 604–92305–3 (vendor P/N
8454–1) or P/N 604–92305–5 (vendor P/N
8454–2).
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight Controls.
(e) Reason
This AD was prompted by the discovery of
three typographical errors in AD 2015–02–06.
We are issuing this AD to detect and correct
loose spur gear bolts on the HSTA, which, if
combined with the failure of the primary
load path, could lead to failure of the HSTA
and subsequent loss of the airplane.
Rmajette on DSK2VPTVN1PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Airplane Flight Manual (AFM)
Revision, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2015–02–06,
Amendment 39–18073 (80 FR 5017, January
30, 2015), with no changes. Within 30 days
after March 6, 2015 (the effective date of AD
2015–02–06: Revise the Normal Procedures
section of the applicable Bombardier AFM to
include the information in the applicable
temporary revision (TR) specified in
paragraph (g)(1) or (g)(2) of this AD. The TRs
introduce revised procedures for the
stabilizer trim system check. Operate the
airplane according to the limitations and
VerDate Sep<11>2014
14:05 Mar 13, 2015
Jkt 235001
procedures in the applicable TR. The
revision may be done by inserting a copy of
the applicable TR specified in paragraph
(g)(1) or (g)(2) of this AD into the AFM. When
the TR has been included in the general
revisions of the AFM, the general revisions
may be inserted into the AFM, provided the
relevant information in the general revision
is identical to that in the applicable TR, and
the TR may be removed.
(1) Bombardier Temporary Revision (TR)
604/37, dated May 21, 2013, to the
Bombardier Challenger CL–604 Airplane
Flight Manual, PSP 604–1.
(2) Bombardier TR 605/18, dated May 21,
2013, to the Bombardier Challenger CL–605
Airplane Flight Manual, PSP 605–1.
(h) Retained Maintenance or Inspection
Program Revision, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2015–02–06,
Amendment 39–18073 (80 FR 5017, January
30, 2015), with no changes. Within 30 days
after March 6, 2015 (the effective date of AD
2015–02–06): Revise the maintenance or
inspection program, as applicable, by
incorporating procedures for an Operational
Test (BITE) of the Horizontal Stabilizer Trim
Controls System (HSTCS), in accordance
with a method approved by the Manager,
New York Aircraft Certification Office (ACO),
ANE–170, FAA; or Transport Canada Civil
Aviation (TCCA); or Bombardier, Inc.’s TCCA
Design Approval Organization (DAO). The
initial compliance time for the operational
test is within 100 flight hours after March 6,
2015 (the effective date of AD 2015–02–06).
Note 1 to paragraph (h) of this AD:
Bombardier Task 27–41–00–101, Operational
Test (BITE) of the Horizontal Stabilizer Trim
Controls System (HSTCS), provides guidance
for the operational test specified in paragraph
(h) of this AD. Bombardier Task 27–41–00–
101 is included in the Bombardier Challenger
604 Time Limits/Maintenance Checks
(TLMC) Manual; and in the Bombardier
Challenger 605 TLMC Manual.
(i) Retained No Alternative Actions or
Intervals, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2015–02–06, Amendment
39–18073 (80 FR 5017, January 30, 2015),
with no changes. After the maintenance or
inspection program has been revised, as
required by paragraph (h) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (m)(1) of this AD.
(j) Retained HSTA Replacement, With
Corrected Vendor Part Number
This paragraph restates the requirements of
paragraph (j) of AD 2015–02–06, Amendment
39–18073 (80 FR 5017, January 30, 2015),
with a corrected vendor part number. For
airplanes equipped with a HSTA having
P/N 604–92305–3 (vendor P/N 8454–1) or
P/N 604–92305–5 (vendor P/N 8454–2):
Within 3,000 flight hours or 26 months after
March 6, 2015 (the effective date of AD 2015–
02–06), whichever occurs first, replace any
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
13485
HSTA having P/N 604–92305–3 (vendor P/N
8454–1) or P/N 604–92305–5 (vendor P/N
8454–2) with a HSTA having P/N 604–
92305–7 (vendor P/N 8454–3), in accordance
with the Accomplishment Instructions of
Bombardier Service Bulletin 604–27–032,
Revision 02, dated April 22, 2014; or
Bombardier Service Bulletin 605–27–002,
Revision 02, dated April 22, 2014; as
applicable.
(k) Retained Credit for Previous Actions,
With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2015–02–06,
Amendment 39–18073 (80 FR 5017, January
30, 2015), with no changes. This paragraph
provides credit for the actions required by
paragraph (j) of this AD if those actions were
performed before March 6, 2015 (the effective
date of AD 2015–02–06) using the service
information identified in paragraphs (k)(1)
through (k)(4) of this AD, as applicable. This
service information is not incorporated by
reference in this AD.
(1) Bombardier Service Bulletin 604–27–
032, dated September 10, 2012.
(2) Bombardier Service Bulletin 604–27–
032, Revision 01, dated April 29, 2013.
(3) Bombardier Service Bulletin 605–27–
002, dated September 10, 2012.
(4) Bombardier Service Bulletin 605–27–
002, Revision 01, April 29, 2013.
(l) Retained Parts Installation Prohibition,
With No Changes
This paragraph restates the requirements of
paragraph (l) of AD 2015–02–06, Amendment
39–18073 (80 FR 5017, January 30, 2015),
with no changes. As of March 6, 2015 (the
effective date of AD 2015–02–06), no person
may install any HSTA having P/N 604–
92305–3 (vendor P/N 8454–1) or 604–92305–
5 (vendor P/N 8454–2) on any airplane.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO,
ANE–170, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
FAA, New York ACO, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. Before
using any approved AMOC, notify your
appropriate principal inspector, or lacking a
principal inspector, the manager of the local
flight standards district office/certificate
holding district office. The AMOC approval
letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170;
or TCCA; or Bombardier, Inc.’s TCCA DAO.
If approved by the DAO, the approval must
include the DAO-authorized signature.
E:\FR\FM\16MRR1.SGM
16MRR1
13486
Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations
(n) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2013–18 dated
July 16, 2013, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2015–0491.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (o)(4) and (o)(5) of this AD.
Rmajette on DSK2VPTVN1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on March 6, 2015 (80 FR
5017, January 30, 2015).
(i) Bombardier Service Bulletin 604–27–
032, Revision 02, dated April 22, 2014.
(ii) Bombardier Service Bulletin 605–27–
002, Revision 02, dated April 22, 2014.
(iii) Bombardier Temporary Revision 604/
37, dated May 21, 2013, to the Bombardier
Challenger CL–604 Airplane Flight Manual,
PSP 604–1.
(iv) Bombardier Temporary Revision 605/
18, dated May 21, 2013, to the Bombardier
Challenger CL–605 Airplane Flight Manual,
PSP 605–1.
(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; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(5) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(6) You may view this 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/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 5,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
BILLING CODE 4910–13–P
VerDate Sep<11>2014
14:05 Mar 13, 2015
Jkt 235001
14 CFR Part 39
[Docket No. FAA–2008–0561; Directorate
Identifier 2007–NM–223–AD; Amendment
39–18111; AD 2015–05–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
(o) Material Incorporated by Reference
[FR Doc. 2015–05735 Filed 3–13–15; 8:45 am]
Federal Aviation Administration
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757–200,
–200PF, –200CB, and –300 series
airplanes; and Model 767–200, –300,
–300F, and –400ER series airplanes.
This AD was prompted by reports
indicating that the counterweights in
some hub assemblies of the ram air
turbine (RAT) could be understrength
and fracture when the RAT is rotating,
and that some RAT hub assemblies were
delivered with balance washer retention
screws that were incorrectly heattreated, and therefore, susceptible to
fracture and cracking. This AD requires
a part number and serial number
inspection to determine if certain RAT
hub assemblies are installed; and, for
affected RAT hub assemblies, doing an
inspection for missing and fractured
balance washer screws, and replacement
or rework if necessary. We are issuing
this AD to prevent an inoperative RAT,
which, following a dual engine
shutdown in flight, will cause loss of all
hydraulic power to the primary flight
controls, resulting in subsequent loss of
control of the airplane.
DATES: This AD is effective April 20,
2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 20, 2015.
ADDRESSES: For Boeing service
information identified in this AD,
contact Boeing Commercial Airplanes,
Attention: Data & Services Management,
P.O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; email
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. For
Hamilton Sundstrand service
information identified in this AD,
contact Hamilton Sundstrand, Technical
Publications, Mail Stop 302–9, 4747
Harrison Avenue, P.O. Box 7002,
Rockford, IL 61125–7002; phone: 860–
654–3575; fax: 860–998–4564; email:
SUMMARY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
tech.solutions@hs.utc.com; Internet:
https://www.hamiltonsundstrand.com.
You may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2008–
0561.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2008–
0561; 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 address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Douglas Tsuji, Senior Aerospace
Engineer, Systems and Equipment
Branch, ANM–130S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–917–6546; fax: 425–
917–6590; Douglas.Tsuji@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to all The Boeing
Company Model 757–200, –200PF,
–200CB, and –300 series airplanes; and
Model 767–200, –300, –300F, and
–400ER series airplanes. The SNPRM
published in the Federal Register on
April 24, 2014 (79 FR 22777). We
preceded the SNPRM with a notice of
proposed rulemaking (NPRM) that
published in the Federal Register on
May 20, 2008 (73 FR 29087). The NPRM
proposed to require doing an inspection
to determine the part number and serial
number of the RAT hub assembly, and
replacing the RAT hub assembly with a
new, serviceable, or reworked and reidentified RAT hub assembly if
necessary. The NPRM was prompted by
reports indicating that the
counterweights in some hub assemblies
of the RATs could be understrength and
fracture when the RAT is rotating. The
E:\FR\FM\16MRR1.SGM
16MRR1
]]>Agencies
[Federal Register Volume 80, Number 50 (Monday, March 16, 2015)]
[Rules and Regulations]
[Pages 13483-13486]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-05735]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0491; Directorate Identifier 2015-NM-019-AD;
Amendment 39-18117; AD 2015-05-07]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-06 for
certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes.
AD 2015-02-06 required a revision to the airplane flight manual, a
revision to the maintenance or inspection program, as applicable, and
replacement of horizontal stabilizer trim actuators (HSTAs) having
certain part numbers. This new AD continues to require those actions
and corrects certain typographical errors. This AD was prompted by the
discovery of three typographical errors in AD 2015-02-06. We are
issuing this AD to detect and correct loose spur gear bolts on the
HSTA, which, if combined with the failure of the primary load path,
could lead to failure of the HSTA and subsequent loss of the airplane.
DATES: This AD becomes effective March 16, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 6, 2015
(80 FR 5017, January 30, 2015).
We must receive comments on this AD by April 30, 2015
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-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, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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; email
thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You
may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0491; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
[[Page 13484]]
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 in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7331; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
On January 11, 2015, we issued AD 2015-02-06, Amendment 39-18073
(80 FR 5017, January 30, 2015). AD 2015-02-06 applied to certain
Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. AD 2015-
02-06 was prompted by reports of loose, broken, or backed-out spur gear
bolts on the HSTA. AD 2015-02-06 required a revision to the airplane
flight manual, a revision to the maintenance or inspection program, as
applicable, and replacement of HSTAs having certain part numbers. We
issued AD 2015-02-06 to detect and correct loose spur gear bolts on the
HSTA, which, if combined with the failure of the primary load path,
could lead to failure of the HSTA and subsequent loss of the airplane.
Since we issued AD 2015-02-06, Amendment 39-18073 (80 FR 5017,
January 30, 2015), three typographical errors were discovered in AD
2015-02-06.
As published, a digit was missing from the engineer's phone number
in the FOR FURTHER INFORMATION CONTACT section of the preamble of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015). The
correct phone number is ``516-228-7331.''
As published, the AD number of AD 2015-02-06, Amendment 39-18073
(80 FR 5017, January 30, 2015), appears as ``2014-02-06'' in the
Product Identification line of the regulatory text of the AD. The
correct AD number is ``2015-02-06.'' The AD number is referenced
correctly throughout the remainder of that document.
As published, a vendor part number in paragraph (j) of AD 2015-02-
06, Amendment 39-18073 (80 FR 5017, January 30, 2015), was incorrectly
identified as ``845401.'' The correct vendor part number is ``8454-1.''
Since this new AD replaces AD 2015-02-06, Amendment 39-18073 (80 FR
5017, January 30, 2015), there are no additional changes in this new
AD.
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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because of
the urgency to correct the part number and AD number errors to avoid
non-compliance. Therefore, we determined that notice and opportunity
for public comment before issuing this AD are impracticable and that
good cause exists for making this amendment effective in fewer than 30
days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2015-0491; Directorate
Identifier 2015-NM-019-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.
Costs of Compliance
We estimate that this AD affects 125 airplanes of U.S. registry.
The actions required by AD 2015-02-06, Amendment 39-18073 (80 FR
5017, January 30, 2015), and retained in this AD take about 21 work-
hours 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 actions that are required by AD 2015-02-06 is
$1,785 per product.
The new requirements of this AD add no additional economic burden.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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 that 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);
3. Will not affect intrastate aviation in Alaska; and
4. 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 13485]]
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
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 airworthiness directive (AD)
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), and
adding the following new AD:
2015-05-07 Bombardier, Inc.: Amendment 39-18117. Docket No. FAA-
2015-0491; Directorate Identifier 2015-NM-019-AD.
(a) Effective Date
This AD becomes effective March 16, 2015.
(b) Affected ADs
This AD replaces AD 2015-02-06, Amendment 39-18073 (80 FR 5017,
January 30, 2015).
(c) Applicability
This AD applies to Bombardier, Inc. Model CL-600-2B16 (CL-604
Variant) airplanes, certificated in any category, serial numbers
5301 and subsequent, equipped with horizontal stabilizer trim
actuator (HSTA) part number (P/N) 604-92305-3 (vendor P/N 8454-1) or
P/N 604-92305-5 (vendor P/N 8454-2).
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
Controls.
(e) Reason
This AD was prompted by the discovery of three typographical
errors in AD 2015-02-06. We are issuing this AD to detect and
correct loose spur gear bolts on the HSTA, which, if combined with
the failure of the primary load path, could lead to failure of the
HSTA and subsequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Airplane Flight Manual (AFM) Revision, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
no changes. Within 30 days after March 6, 2015 (the effective date
of AD 2015-02-06: Revise the Normal Procedures section of the
applicable Bombardier AFM to include the information in the
applicable temporary revision (TR) specified in paragraph (g)(1) or
(g)(2) of this AD. The TRs introduce revised procedures for the
stabilizer trim system check. Operate the airplane according to the
limitations and procedures in the applicable TR. The revision may be
done by inserting a copy of the applicable TR specified in paragraph
(g)(1) or (g)(2) of this AD into the AFM. When the TR has been
included in the general revisions of the AFM, the general revisions
may be inserted into the AFM, provided the relevant information in
the general revision is identical to that in the applicable TR, and
the TR may be removed.
(1) Bombardier Temporary Revision (TR) 604/37, dated May 21,
2013, to the Bombardier Challenger CL-604 Airplane Flight Manual,
PSP 604-1.
(2) Bombardier TR 605/18, dated May 21, 2013, to the Bombardier
Challenger CL-605 Airplane Flight Manual, PSP 605-1.
(h) Retained Maintenance or Inspection Program Revision, With No
Changes
This paragraph restates the requirements of paragraph (h) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
no changes. Within 30 days after March 6, 2015 (the effective date
of AD 2015-02-06): Revise the maintenance or inspection program, as
applicable, by incorporating procedures for an Operational Test
(BITE) of the Horizontal Stabilizer Trim Controls System (HSTCS), in
accordance with a method approved by the Manager, New York Aircraft
Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil
Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval
Organization (DAO). The initial compliance time for the operational
test is within 100 flight hours after March 6, 2015 (the effective
date of AD 2015-02-06).
Note 1 to paragraph (h) of this AD: Bombardier Task 27-41-00-
101, Operational Test (BITE) of the Horizontal Stabilizer Trim
Controls System (HSTCS), provides guidance for the operational test
specified in paragraph (h) of this AD. Bombardier Task 27-41-00-101
is included in the Bombardier Challenger 604 Time Limits/Maintenance
Checks (TLMC) Manual; and in the Bombardier Challenger 605 TLMC
Manual.
(i) Retained No Alternative Actions or Intervals, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
no changes. After the maintenance or inspection program has been
revised, as required by paragraph (h) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (m)(1) of this AD.
(j) Retained HSTA Replacement, With Corrected Vendor Part Number
This paragraph restates the requirements of paragraph (j) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
a corrected vendor part number. For airplanes equipped with a HSTA
having P/N 604-92305-3 (vendor P/N 8454-1) or P/N 604-92305-5
(vendor P/N 8454-2): Within 3,000 flight hours or 26 months after
March 6, 2015 (the effective date of AD 2015-02-06), whichever
occurs first, replace any HSTA having P/N 604-92305-3 (vendor P/N
8454-1) or P/N 604-92305-5 (vendor P/N 8454-2) with a HSTA having P/
N 604-92305-7 (vendor P/N 8454-3), in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 604-27-
032, Revision 02, dated April 22, 2014; or Bombardier Service
Bulletin 605-27-002, Revision 02, dated April 22, 2014; as
applicable.
(k) Retained Credit for Previous Actions, With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
no changes. This paragraph provides credit for the actions required
by paragraph (j) of this AD if those actions were performed before
March 6, 2015 (the effective date of AD 2015-02-06) using the
service information identified in paragraphs (k)(1) through (k)(4)
of this AD, as applicable. This service information is not
incorporated by reference in this AD.
(1) Bombardier Service Bulletin 604-27-032, dated September 10,
2012.
(2) Bombardier Service Bulletin 604-27-032, Revision 01, dated
April 29, 2013.
(3) Bombardier Service Bulletin 605-27-002, dated September 10,
2012.
(4) Bombardier Service Bulletin 605-27-002, Revision 01, April
29, 2013.
(l) Retained Parts Installation Prohibition, With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2015-02-06, Amendment 39-18073 (80 FR 5017, January 30, 2015), with
no changes. As of March 6, 2015 (the effective date of AD 2015-02-
06), no person may install any HSTA having P/N 604-92305-3 (vendor
P/N 8454-1) or 604-92305-5 (vendor P/N 8454-2) on any airplane.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York ACO, ANE-170, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the ACO, send it to ATTN: Program
Manager, Continuing Operational Safety, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7300; fax 516-794-5531. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the
DAO, the approval must include the DAO-authorized signature.
[[Page 13486]]
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2013-18 dated July 16,
2013, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-0491.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(4) and (o)(5) of this AD.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
March 6, 2015 (80 FR 5017, January 30, 2015).
(i) Bombardier Service Bulletin 604-27-032, Revision 02, dated
April 22, 2014.
(ii) Bombardier Service Bulletin 605-27-002, Revision 02, dated
April 22, 2014.
(iii) Bombardier Temporary Revision 604/37, dated May 21, 2013,
to the Bombardier Challenger CL-604 Airplane Flight Manual, PSP 604-
1.
(iv) Bombardier Temporary Revision 605/18, dated May 21, 2013,
to the Bombardier Challenger CL-605 Airplane Flight Manual, PSP 605-
1.
(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; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(5) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(6) You may view this 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on March 5, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-05735 Filed 3-13-15; 8:45 am]
BILLING CODE 4910-13-P
