Airworthiness Directives; British Aerospace Regional Aircraft Airplanes, 78726-78729 [2014-30631]
Download as PDF
<![CDATA[
78726
Proposed Rules
Federal Register
Vol. 79, No. 250
Wednesday, December 31, 2014
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1093; Directorate
Identifier 2014–CE–035–AD]
RIN 2120–AA64
Airworthiness Directives; British
Aerospace Regional Aircraft Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for British
Aerospace Regional Aircraft Model
Jetstream Series 3101 and Jetstream
Model 3201 airplanes that would
supersede AD 2014–06–03. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as stress corrosion
cracking of the main landing gear spigot
housing. We are issuing this proposed
AD to require actions to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by February 17, 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 20590, between 9 a.m.
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:21 Dec 30, 2014
Jkt 235001
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact BAE Systems
(Operations) Ltd, Customer Information
Department, Prestwick International
Airport, Ayrshire, KA9 2RW, Scotland,
United Kingdom; phone: +44 1292
675207, fax: +44 1292 675704; email:
RApublications@baesystems.com;
Internet: https://
www.jetstreamcentral.com. You may
review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
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–2014–
1093; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the 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:
Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4138; fax: (816) 329–4090; email:
taylor.martin@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–1093; Directorate Identifier
2014–CE–035–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
We will post all comments we
receive, without change, to https://
regulations.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On March 14, 2014, we issued AD
2014–06–03, Amendment 39–17807 (79
FR 17395; March 28, 2014) (‘‘AD 2014–
06–03’’). That AD required actions
intended to address an unsafe condition
on British Aerospace Regional Aircraft
Model Jetstream Series 3101 and
Jetstream Model 3201 airplanes and was
based on mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country.
Since we issued AD 2014–06–03,
corrosion was found on an airplane at
the top outer edge of the forward spigot
housing and extended along the top of
the spigot housing. BAE Systems
(Operations) Limited issued new service
information to ensure the spigot cap is
positioned correctly and to include
inspection instructions for movement of
the special washer and instructions for
addressing any corrosion that may be
found.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD No.
2014–0239, dated November 3, 2014
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Several cases of stress corrosion cracking of
DTD 5094 standard Main Landing Gear
(MLG) cylinders have been reported on
Jetstream Series 3200 and 3100 aeroplanes.
Prompted by these findings, The United
Kingdom (UK) Civil Aviation Authority
(CAA) issued AD 003–01–86 to require visual
and non-destructive testing (NDT)
inspections of the MLG assembly cylinder
attachment spigot housing in accordance
with BAE Systems (Operations) Ltd SB 32–
A–JA851226. In 2012 an additional
occurrence of Jetstream 3100 MLG failure
after landing was reported, the subsequent
investigation revealed stress corrosion
cracking of the yoke pintle housing as a root
cause of the MLG failure. Consequently
EASA issued EASA AD 2013–0208 to require
inspection of the MLG in accordance with
BAE Systems (Operations) Ltd SB 32–A–
JA851226 Revision 5 or later approved
revisions to detect any crack, however, SB
32–A–JA851226 did not apply to aeroplanes
E:\FR\FM\31DEP1.SGM
31DEP1
Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules
equipped with MLG cylinders manufactured
from L161 material, since that is not
susceptible to stress corrosion, BAE Systems
(Operations) Ltd issued SB 32–JM7862 to
address degradation of the surface protection
by placing a special washer over the forward
face of the MLG spigot housing, which
rotates with the spigot housing. EASA issued
AD 2013–0206 to require modification of the
left (LH) and right hand (RH) MLG in
accordance with this SB.
In 2014 a further event was reported, where
the LH MLG of a Jetstream 3100 aeroplane
collapsed during landing, this resulted in the
aeroplane departing from the runway. The
accident is still under investigation by the
UK Air Accident Investigation Branch.
Preliminary results of the investigation
determined that cracking, which caused the
MLG collapse, was initiated from a corrosion
pit at the top outer edge of the forward spigot
housing and extended along the top of the
spigot housing. The spigot housing material
was DTD 5094. The affected LH MLG had
been modified in accordance with BAE
Systems (Operations) Ltd SB 32–JM7862
Revision 1. Further investigation discovered
that the instructions provided in BAE
Systems (Operations) Ltd SB 32–JM7862
Revision 1 did not effectively prevent stress
corrosion cracking because, under certain
circumstances, it allows the rotation of the
special washer and consequent damage of the
end face of the spigot housing.
This condition, if not corrected, could lead
to structural failure of the MLG, possibly
resulting in loss of control of the aeroplane
during take-off or landing runs.
To address this potential unsafe condition,
BAE Systems (Operations) Ltd issued SB 32–
JM7862 Revision 2 to clarify the orientation
of the spigot bearing cap, later revised to SB
32–JM7862 Revision 3 to ensure the spigot
bearing cap is correctly positioned.
Additionally, BAE Systems (Operations) Ltd
issued SB 32–A–JA140940 to provide
inspection instructions to detect migration of
the special washer and any potential
corrosion resulting from that unwanted
migration for MLG installations modified
earlier in accordance with BAE Systems
(Operations) Ltd SB 32–JM7862 up to
Revision 2.
For the reasons described above, this AD
partially retains the requirements of EASA
AD 2013–0206, which is superseded, and
requires a one-time inspection of pre-SB 32–
JM7862 Revision 3 MLG installations and,
depending on findings, applicable corrective
action(s).
tkelley on DSK3SPTVN1PROD with PROPOSALS
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–1093.
Relevant Service Information
British Aerospace Regional Aircraft
has issued British Aerospace Jetstream
Series 3100 and 3200 Service Bulletin
No. 32–JM7862, Revision 3, dated
October 3, 2014; and British Aerospace
Jetstream Series 3100 and 3200 Service
Bulletin No. 32–A–JA140940, Original
Issue, dated October 3, 2014. The
VerDate Sep<11>2014
16:21 Dec 30, 2014
Jkt 235001
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of the Proposed 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 this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
will affect 44 products of U.S. registry.
We also estimate that it would take
about 2 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $170 per
product.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $14,960, or $340 per
product.
We accept modification of the MLG,
if done before the effective date of this
proposed AD, using earlier versions of
the service information. However, the
earlier versions of the service
information require additional
inspections with possible corrective
actions.
In addition, we estimate that any
necessary follow-on actions that may be
required if using an earlier version of
the service information would take
about 1 work-hour to inspect for special
washer migration and corrosion damage
and require parts costing $100 for
replacement of the special washer and
application of witness paint, if
necessary, for a cost of $185 per
product. We have no way of
determining the number of products
that may need these actions.
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,
PO 00000
Frm 00002
Fmt 4702
Sfmt 4702
78727
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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–17806 (79 FR
17395; March 28, 2014), and adding the
following new AD:
■
British Aerospace Regional Aircraft: Docket
No. FAA–2014–1093; Directorate
Identifier 2014–CE–035–AD.
E:\FR\FM\31DEP1.SGM
31DEP1
78728
Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules
(a) Comments Due Date
We must receive comments by February
17, 2015.
(b) Affected ADs
This AD supersedes AD 2014–06–03,
Amendment 39–17806 (79 FR 17395; March
28, 2014).
(c) Applicability
This AD applies to British Aerospace
Regional Aircraft Jetstream Series 3101 and
Jetstream Model 3201 airplanes, all serial
numbers, certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing Gear.
tkelley on DSK3SPTVN1PROD with PROPOSALS
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as stress
corrosion cracking of the main landing gear
(MLG) spigot housing. We are issuing this AD
to prevent corrosion cracking of the MLG
spigot housing. This condition, if not
corrected, could cause structural failure of
the MLG resulting in loss of control of the
airplane during take-off or landing.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) through (f)(11),
including all subparagraphs, as applicable.
(1) At the next scheduled MLG removal,
modify the installation of the left hand (LH)
and right hand (RH) MLG at the forward
spigot following British Aerospace Jetstream
Series 3100 and 3200 Service Bulletin No.
32–JM7862, Revision 3, dated October 3,
2014.
Note to paragraph (f)(1) of this AD: The
next scheduled MLG removal may be for
non-destructive testing or overhaul, as
applicable.
(2) If done before the effective date of this
AD, we will accept modification of the LH or
RG MLG following British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
SB 32–JM7862, Revision 2, dated June 13,
2014; or British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–JM7862,
Revision 1, dated May 7, 2013, for
compliance with paragraph (f)(1) of this AD.
(3) For airplanes that, before the effective
date of this AD, have been modified
following British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–JM7862,
Revision 2, dated June 13, 2014, visually
inspect the LH and RH MLG to detect
migration of a special washer following the
instructions in Part 1 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA140940, Original Issue, dated
October 3, 2014, at the compliance time
listed in paragraph (f)(3)(i) or (f)(3)(ii) of this
AD, as applicable.
(i) For MLG configuration equipped with
DTD5094 cylinder: Within the next 200 flight
cycles after the effective date of this AD or
within the next 2 months after the effective
date of this AD, whichever occurs first.
VerDate Sep<11>2014
16:21 Dec 30, 2014
Jkt 235001
(ii) For MLG configuration equipped with
L161 cylinder: Within the next 600 flight
cycles after the effective date of this AD or
within the next 6 months after the effective
date of this AD, whichever occurs first.
(4) If evidence of migration of the special
washer was detected during the inspection
required in paragraph (f)(3) of this AD,
within the applicable compliance time
specified in paragraph (f)(3)(i) or (f)(3)(ii) of
this AD, do the corrective actions on the LH
or RH MLG, as applicable, following Part 2
of British Aerospace Jetstream Series 3100 &
3200 Service Bulletin 32–A–JA140940,
Original Issue, dated October 3, 2014.
(5) If no evidence of migration of the
special washer was detected during the
inspection required in paragraph (f)(3) of this
AD, before further flight, apply a witness
paint over the special washer tab and onto
the MLG spigot housing (LH and RH MLG)
following Part 1 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA140940, Original Issue, dated
October 3, 2014.
(6) For airplanes that, before the effective
date of this AD, have been modified
following British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–JM7862,
Revision 1, dated May 7, 2013, do all of the
actions on the MLG cylinder (LH and/or RH,
as applicable) following the instructions in
Part 2 of British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–A–
JA140940, Original Issue, dated October 3,
2014, at the compliance time listed in
paragraph (f)(6)(i) or (f)(6)(ii), as applicable.
(i) For MLG configuration equipped with
DTD5094 cylinder: Within the next 200 flight
cycles after the effective date of this AD or
within the next 2 months after the effective
date of this AD, whichever occurs first.
(ii) For MLG configuration equipped with
L161 cylinder: Within the next 600 flight
cycles after the effective date of this AD or
within the next 6 months after the effective
date of this AD, whichever occurs first.
(7) If any wear, corrosion, or damage is
detected during the inspection required in
either paragraph (f)(3) or (f)(6), as applicable,
of this AD, before further flight, do all of the
corrective actions (including application of
the a witness paint) following the
instructions in Part 2 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA140940, Original Issue, dated
October 3, 2014.
(8) Between 30 and 45 days after doing the
action required in either paragraph (f)(3) or
(f)(6) of this AD or between the next 20 to
30 flight cycles after doing the action
required in either paragraph (f)(3) or (f)(6) of
this AD, whichever occurs first, inspect the
witness paint applied as required in either
paragraph (f)(5) or (f)(7) of this AD following
the instructions in Part 3 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA140940, Original Issue, dated
October 3, 2014.
(9) If any damaged paint is detected during
the inspection required in paragraph (f)(8) of
this AD, before further flight, contact British
Aerospace Regional Aircraft to obtain FAAapproved repair instructions approved
specifically for this AD and incorporate those
instructions. You may find the contact
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
information for British Aerospace Regional
Aircraft in paragraph (h) of this AD.
(10) As of the effective date of this AD, do
not install a LH or RH MLG on any of the
applicable airplanes unless it has passed all
of the inspections required by this AD.
(11) For all airplanes: The compliance
times for paragraphs (f)(3)(i), (f)(3)(ii),
(f)(6)(i), (f)(6)(ii), and (f)(8) of this AD are
presented in flight cycles (landings). If the
total flight cycles have not been kept,
multiply the total number of airplane hours
time-in-service (TIS) by 0.75 to calculate the
cycles. You may use the following as an
example for this AD:
(i) 200 hours TIS × .75 = 150 cycles; or
(ii) 600 hours TIS × .75 = 450 cycles.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
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: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4138; fax: (816) 329–
4090; email: taylor.martin@faa.gov. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the European
Community, AD No. 2014–0239, dated
November 3, 2014; and British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
SB 32–JA851226, Revision 5, dated April 30,
2013; British Aerospace Jetstream and British
Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32–JM7862, Revision 1,
dated May 7, 2013, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2014–1093.
For service information related to this AD,
contact BAE Systems (Operations) Ltd,
Customer Information Department, Prestwick
International Airport, Ayrshire, KA9 2RW,
Scotland, United Kingdom; phone: +44 1292
675207, fax: +44 1292 675704; email:
RApublications@baesystems.com; Internet:
https://www.jetstreamcentral.com. You may
review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
(816) 329–4148.
E:\FR\FM\31DEP1.SGM
31DEP1
Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules
Issued in Kansas City, Missouri, on
December 22, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–30631 Filed 12–30–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–1083; Directorate
Identifier 2014–CE–036–AD]
RIN 2120–AA64
Airworthiness Directives; Various
Aircraft Equipped With Wing Lift Struts
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 99–01–05
R1, which applies to certain aircraft
equipped with wing lift struts. AD 99–
01–05 R1 currently requires repetitively
inspecting the wing lift struts for
corrosion; repetitively inspecting the
wing lift strut forks for cracks; replacing
any corroded wing lift strut; replacing
any cracked wing lift strut fork; and
repetitively replacing the wing lift strut
forks at a specified time for certain
airplanes. Since we issued AD 99–01–05
R1, we have determined that additional
airplane models should be added to the
Applicability section. This proposed AD
would retain all requirements of the
existing AD. We are proposing this AD
to correct the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by February 17, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Piper
Aircraft, Inc., Customer Services, 2926
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:21 Dec 30, 2014
Jkt 235001
Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567–4361; Internet:
www.piper.com. Copies of the
instructions to the F. Atlee Dodge
supplemental type certificate (STC) and
information about the Jensen Aircraft
STCs may be obtained from F. Atlee
Dodge, Aircraft Services, LLC., 6672
Wes Way, Anchorage, Alaska 99518–
0409, Internet: www.fadodge.com. You
may review copies of the referenced
service information at the FAA, Small
Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–
4148.
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–2014–
1083; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
For Piper Aircraft, Inc. airplanes,
contact: Gregory ‘‘Keith’’ Noles,
Aerospace Engineer, FAA, Atlanta
Aircraft Certification Office (ACO), 1701
Columbia Avenue, College Park, Georgia
30337; phone: (404) 474–5551; fax: (404)
474–5606; email: gregory.noles@faa.gov.
For FS 2000 Corp, FS 2001 Corp, FS
2002 Corporation, and FS 2003
Corporation airplanes, contact: Jeff
Morfitt, Aerospace Engineer, FAA,
Seattle ACO, 1601 Lind Avenue SW.,
Renton, Washington 98057; phone:
(425) 917–6405; fax: (245) 917–6590;
email: jeff.morfitt@faa.gov.
For LAVIA ARGENTINA S.A.
(LAVIASA) airplanes, contact: S.M.
Nagarajan, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4145; fax: (816)
329–4090; email: sarjapur.nagarajan@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–1083; Directorate Identifier
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
78729
2014–CE–036–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On November 22, 2013, we issued AD
99–01–05 R1, Amendment 39–17688 (78
FR 73997, December 10, 2013) and later
issued on December 18, 2013 (78 FR
79599, December 31, 2013) as a
correction, (‘‘AD 99–01–05 R1’’), for
certain aircraft equipped with wing lift
struts. AD 99–01–05 R1 resulted from
the need to clarify the intent that if a
sealed wing lift strut assembly is
installed as a replacement part, the
repetitive inspection requirement is
terminated only if the seal is never
improperly broken. If the seal is
improperly broken, then that wing lift
strut becomes subject to continued
repetitive inspections. We did not
intend to promote drilling holes into or
otherwise unsealing a sealed strut.
We issued AD 99–01–05 R1 to detect
and correct corrosion and cracking on
the front and rear wing lift struts and
forks, which could cause the wing lift
strut to fail. This failure could result in
the wing separating from the airplane.
Actions Since AD 99–01–05 R1 Was
Issued
Since AD 99–01–05 R1 was issued,
we have been informed that Piper
Aircraft, Inc. (Piper) Models J–3, J3C–65
(Army L–4A), J3P, J4B, and J4F
airplanes should be added to the
Applicability section. We have also
been informed that there is a serial
number overlap between Piper Model
PA–18s listed in AD 99–01–05 R1 and
Piper Model PA–19 (Army L–18C).
Certain serial numbers listed for Model
PA–18s should also be listed under
Model PA–19 (Army L–18C).
On December 22, 1998, we issued AD
99–01–05, Amendment 39–10972 (63
FR 72132, December 31, 1998), to
supersede AD 93–10–06, Amendment
39–8586 (58 FR 29965, May 25, 1993),
which previously included Piper
Models J–3, J3P, J4B, and J4F airplanes
in the Applicability section, in order to
clarify certain requirements of AD 93–
10–06, eliminate the lift strut fork
E:\FR\FM\31DEP1.SGM
31DEP1
]]>Agencies
[Federal Register Volume 79, Number 250 (Wednesday, December 31, 2014)]
[Proposed Rules]
[Pages 78726-78729]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30631]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 /
Proposed Rules
[[Page 78726]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-1093; Directorate Identifier 2014-CE-035-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Regional Aircraft
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
British Aerospace Regional Aircraft Model Jetstream Series 3101 and
Jetstream Model 3201 airplanes that would supersede AD 2014-06-03. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated by an aviation authority of another country to
identify and correct an unsafe condition on an aviation product. The
MCAI describes the unsafe condition as stress corrosion cracking of the
main landing gear spigot housing. We are issuing this proposed AD to
require actions to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by February 17,
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 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact BAE
Systems (Operations) Ltd, Customer Information Department, Prestwick
International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom;
phone: +44 1292 675207, fax: +44 1292 675704; email:
RApublications@baesystems.com; Internet: https://www.jetstreamcentral.com. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information on the availability of
this material at the FAA, call (816) 329-4148.
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-2014-
1093; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the 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: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090; email:
taylor.martin@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-1093;
Directorate Identifier 2014-CE-035-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 14, 2014, we issued AD 2014-06-03, Amendment 39-17807 (79
FR 17395; March 28, 2014) (``AD 2014-06-03''). That AD required actions
intended to address an unsafe condition on British Aerospace Regional
Aircraft Model Jetstream Series 3101 and Jetstream Model 3201 airplanes
and was based on mandatory continuing airworthiness information (MCAI)
originated by an aviation authority of another country.
Since we issued AD 2014-06-03, corrosion was found on an airplane
at the top outer edge of the forward spigot housing and extended along
the top of the spigot housing. BAE Systems (Operations) Limited issued
new service information to ensure the spigot cap is positioned
correctly and to include inspection instructions for movement of the
special washer and instructions for addressing any corrosion that may
be found.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD No. 2014-0239, dated November 3, 2014 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Several cases of stress corrosion cracking of DTD 5094 standard Main
Landing Gear (MLG) cylinders have been reported on Jetstream Series
3200 and 3100 aeroplanes.
Prompted by these findings, The United Kingdom (UK) Civil Aviation
Authority (CAA) issued AD 003-01-86 to require visual and non-
destructive testing (NDT) inspections of the MLG assembly cylinder
attachment spigot housing in accordance with BAE Systems
(Operations) Ltd SB 32-A-JA851226. In 2012 an additional occurrence
of Jetstream 3100 MLG failure after landing was reported, the
subsequent investigation revealed stress corrosion cracking of the
yoke pintle housing as a root cause of the MLG failure. Consequently
EASA issued EASA AD 2013-0208 to require inspection of the MLG in
accordance with BAE Systems (Operations) Ltd SB 32-A-JA851226
Revision 5 or later approved revisions to detect any crack, however,
SB 32-A-JA851226 did not apply to aeroplanes
[[Page 78727]]
equipped with MLG cylinders manufactured from L161 material, since
that is not susceptible to stress corrosion, BAE Systems
(Operations) Ltd issued SB 32-JM7862 to address degradation of the
surface protection by placing a special washer over the forward face
of the MLG spigot housing, which rotates with the spigot housing.
EASA issued AD 2013-0206 to require modification of the left (LH)
and right hand (RH) MLG in accordance with this SB.
In 2014 a further event was reported, where the LH MLG of a
Jetstream 3100 aeroplane collapsed during landing, this resulted in
the aeroplane departing from the runway. The accident is still under
investigation by the UK Air Accident Investigation Branch.
Preliminary results of the investigation determined that cracking,
which caused the MLG collapse, was initiated from a corrosion pit at
the top outer edge of the forward spigot housing and extended along
the top of the spigot housing. The spigot housing material was DTD
5094. The affected LH MLG had been modified in accordance with BAE
Systems (Operations) Ltd SB 32-JM7862 Revision 1. Further
investigation discovered that the instructions provided in BAE
Systems (Operations) Ltd SB 32-JM7862 Revision 1 did not effectively
prevent stress corrosion cracking because, under certain
circumstances, it allows the rotation of the special washer and
consequent damage of the end face of the spigot housing.
This condition, if not corrected, could lead to structural failure
of the MLG, possibly resulting in loss of control of the aeroplane
during take-off or landing runs.
To address this potential unsafe condition, BAE Systems (Operations)
Ltd issued SB 32-JM7862 Revision 2 to clarify the orientation of the
spigot bearing cap, later revised to SB 32-JM7862 Revision 3 to
ensure the spigot bearing cap is correctly positioned. Additionally,
BAE Systems (Operations) Ltd issued SB 32-A-JA140940 to provide
inspection instructions to detect migration of the special washer
and any potential corrosion resulting from that unwanted migration
for MLG installations modified earlier in accordance with BAE
Systems (Operations) Ltd SB 32-JM7862 up to Revision 2.
For the reasons described above, this AD partially retains the
requirements of EASA AD 2013-0206, which is superseded, and requires
a one-time inspection of pre-SB 32-JM7862 Revision 3 MLG
installations and, depending on findings, applicable corrective
action(s).
You may examine the MCAI on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2014-1093.
Relevant Service Information
British Aerospace Regional Aircraft has issued British Aerospace
Jetstream Series 3100 and 3200 Service Bulletin No. 32-JM7862, Revision
3, dated October 3, 2014; and British Aerospace Jetstream Series 3100
and 3200 Service Bulletin No. 32-A-JA140940, Original Issue, dated
October 3, 2014. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed 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 this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Costs of Compliance
We estimate that this proposed AD will affect 44 products of U.S.
registry. We also estimate that it would take about 2 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour. Required parts would cost
about $170 per product.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $14,960, or $340 per product.
We accept modification of the MLG, if done before the effective
date of this proposed AD, using earlier versions of the service
information. However, the earlier versions of the service information
require additional inspections with possible corrective actions.
In addition, we estimate that any necessary follow-on actions that
may be required if using an earlier version of the service information
would take about 1 work-hour to inspect for special washer migration
and corrosion damage and require parts costing $100 for replacement of
the special washer and application of witness paint, if necessary, for
a cost of $185 per product. We have no way of determining the number of
products that may need these actions.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-17806 (79 FR
17395; March 28, 2014), and adding the following new AD:
British Aerospace Regional Aircraft: Docket No. FAA-2014-1093;
Directorate Identifier 2014-CE-035-AD.
[[Page 78728]]
(a) Comments Due Date
We must receive comments by February 17, 2015.
(b) Affected ADs
This AD supersedes AD 2014-06-03, Amendment 39-17806 (79 FR
17395; March 28, 2014).
(c) Applicability
This AD applies to British Aerospace Regional Aircraft Jetstream
Series 3101 and Jetstream Model 3201 airplanes, all serial numbers,
certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 32: Landing
Gear.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as stress corrosion
cracking of the main landing gear (MLG) spigot housing. We are
issuing this AD to prevent corrosion cracking of the MLG spigot
housing. This condition, if not corrected, could cause structural
failure of the MLG resulting in loss of control of the airplane
during take-off or landing.
(f) Actions and Compliance
Unless already done, do the following actions in paragraphs
(f)(1) through (f)(11), including all subparagraphs, as applicable.
(1) At the next scheduled MLG removal, modify the installation
of the left hand (LH) and right hand (RH) MLG at the forward spigot
following British Aerospace Jetstream Series 3100 and 3200 Service
Bulletin No. 32-JM7862, Revision 3, dated October 3, 2014.
Note to paragraph (f)(1) of this AD: The next scheduled MLG
removal may be for non-destructive testing or overhaul, as
applicable.
(2) If done before the effective date of this AD, we will accept
modification of the LH or RG MLG following British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin SB 32-JM7862, Revision
2, dated June 13, 2014; or British Aerospace Jetstream Series 3100 &
3200 Service Bulletin 32-JM7862, Revision 1, dated May 7, 2013, for
compliance with paragraph (f)(1) of this AD.
(3) For airplanes that, before the effective date of this AD,
have been modified following British Aerospace Jetstream Series 3100
& 3200 Service Bulletin 32-JM7862, Revision 2, dated June 13, 2014,
visually inspect the LH and RH MLG to detect migration of a special
washer following the instructions in Part 1 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin 32-A-JA140940,
Original Issue, dated October 3, 2014, at the compliance time listed
in paragraph (f)(3)(i) or (f)(3)(ii) of this AD, as applicable.
(i) For MLG configuration equipped with DTD5094 cylinder: Within
the next 200 flight cycles after the effective date of this AD or
within the next 2 months after the effective date of this AD,
whichever occurs first.
(ii) For MLG configuration equipped with L161 cylinder: Within
the next 600 flight cycles after the effective date of this AD or
within the next 6 months after the effective date of this AD,
whichever occurs first.
(4) If evidence of migration of the special washer was detected
during the inspection required in paragraph (f)(3) of this AD,
within the applicable compliance time specified in paragraph
(f)(3)(i) or (f)(3)(ii) of this AD, do the corrective actions on the
LH or RH MLG, as applicable, following Part 2 of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin 32-A-JA140940,
Original Issue, dated October 3, 2014.
(5) If no evidence of migration of the special washer was
detected during the inspection required in paragraph (f)(3) of this
AD, before further flight, apply a witness paint over the special
washer tab and onto the MLG spigot housing (LH and RH MLG) following
Part 1 of British Aerospace Jetstream Series 3100 & 3200 Service
Bulletin 32-A-JA140940, Original Issue, dated October 3, 2014.
(6) For airplanes that, before the effective date of this AD,
have been modified following British Aerospace Jetstream Series 3100
& 3200 Service Bulletin 32-JM7862, Revision 1, dated May 7, 2013, do
all of the actions on the MLG cylinder (LH and/or RH, as applicable)
following the instructions in Part 2 of British Aerospace Jetstream
Series 3100 & 3200 Service Bulletin 32-A-JA140940, Original Issue,
dated October 3, 2014, at the compliance time listed in paragraph
(f)(6)(i) or (f)(6)(ii), as applicable.
(i) For MLG configuration equipped with DTD5094 cylinder: Within
the next 200 flight cycles after the effective date of this AD or
within the next 2 months after the effective date of this AD,
whichever occurs first.
(ii) For MLG configuration equipped with L161 cylinder: Within
the next 600 flight cycles after the effective date of this AD or
within the next 6 months after the effective date of this AD,
whichever occurs first.
(7) If any wear, corrosion, or damage is detected during the
inspection required in either paragraph (f)(3) or (f)(6), as
applicable, of this AD, before further flight, do all of the
corrective actions (including application of the a witness paint)
following the instructions in Part 2 of British Aerospace Jetstream
Series 3100 & 3200 Service Bulletin 32-A-JA140940, Original Issue,
dated October 3, 2014.
(8) Between 30 and 45 days after doing the action required in
either paragraph (f)(3) or (f)(6) of this AD or between the next 20
to 30 flight cycles after doing the action required in either
paragraph (f)(3) or (f)(6) of this AD, whichever occurs first,
inspect the witness paint applied as required in either paragraph
(f)(5) or (f)(7) of this AD following the instructions in Part 3 of
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-
A-JA140940, Original Issue, dated October 3, 2014.
(9) If any damaged paint is detected during the inspection
required in paragraph (f)(8) of this AD, before further flight,
contact British Aerospace Regional Aircraft to obtain FAA-approved
repair instructions approved specifically for this AD and
incorporate those instructions. You may find the contact information
for British Aerospace Regional Aircraft in paragraph (h) of this AD.
(10) As of the effective date of this AD, do not install a LH or
RH MLG on any of the applicable airplanes unless it has passed all
of the inspections required by this AD.
(11) For all airplanes: The compliance times for paragraphs
(f)(3)(i), (f)(3)(ii), (f)(6)(i), (f)(6)(ii), and (f)(8) of this AD
are presented in flight cycles (landings). If the total flight
cycles have not been kept, multiply the total number of airplane
hours time-in-service (TIS) by 0.75 to calculate the cycles. You may
use the following as an example for this AD:
(i) 200 hours TIS x .75 = 150 cycles; or
(ii) 600 hours TIS x .75 = 450 cycles.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, 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: Taylor Martin, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4138; fax: (816) 329-4090; email:
taylor.martin@faa.gov. 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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(h) Related Information
Refer to MCAI European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Community,
AD No. 2014-0239, dated November 3, 2014; and British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin SB 32-JA851226,
Revision 5, dated April 30, 2013; British Aerospace Jetstream and
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-
JM7862, Revision 1, dated May 7, 2013, for related information. You
may examine the MCAI on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2014-1093. For service
information related to this AD, contact BAE Systems (Operations)
Ltd, Customer Information Department, Prestwick International
Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44
1292 675207, fax: +44 1292 675704; email:
RApublications@baesystems.com; Internet: https://www.jetstreamcentral.com. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.
[[Page 78729]]
Issued in Kansas City, Missouri, on December 22, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-30631 Filed 12-30-14; 8:45 am]
BILLING CODE 4910-13-P
