Airworthiness Directives; British Aerospace Regional Aircraft Airplanes, 10973-10976 [2017-02771]
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Federal Register / Vol. 82, No. 32 / Friday, February 17, 2017 / Proposed Rules
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 adding
the following new airworthiness
directive (AD):
■
Romtex Anjou Aeronautique (Romtex) Torso
Restraint Systems: Docket No. FAA–
2017–0068; Directorate Identifier 2014–
SW–076–AD.
(a) Applicability
This AD applies to Romtex torso restraint
systems (restraint systems) with a rotary
buckle sub-assembly (buckle assembly) with
a part number and serial number as listed in
the Effectivity, paragraph 1.2, of Romtex
Service Bulletin No. 358SB–14–101, Revision
1, dated December 12, 2014. These restraint
systems are installed on, but not limited to,
Airbus Helicopters Model AS350B2,
AS350B3, EC130B4, EC130T2, and AS355NP
helicopters, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
broken buckle knob. This condition could
result in a restraint system strap failing to
release from the buckle, preventing
occupants from exiting the helicopter during
an emergency.
(c) Comments Due Date
We must receive comments by April 18,
2017.
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(e) Required Actions
(1) Within 30 hours time-in-service (TIS),
inspect each restraint system for correct
operation.
(i) If the straps do not release from the
buckle assembly, placard the seat as
inoperative. Within 180 hours TIS, replace
the buckle assembly with a buckle assembly
not identified in paragraph (a) of this AD.
(ii) If the straps release, within 180 hours
TIS, replace the buckle assembly with a
buckle assembly not identified in paragraph
(a) of this AD.
(2) Do not install a restraint system with a
buckle assembly identified in paragraph (a)
of this AD on any helicopter.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: David Hatfield,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 76177;
telephone (817) 222–5116; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
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(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2014–0279, dated December 19, 2014.
You may view the EASA AD on the Internet
at https://www.regulations.gov in the AD
Docket.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 2500 Cabin Equipment/Furnishings.
Issued in Fort Worth, Texas, on January 24,
2017.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2017–02858 Filed 2–16–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0053; Directorate
Identifier 2016–CE–037–AD]
RIN 2120–AA64
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
VerDate Sep<11>2014
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.
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 HP
137 Jetstream MK1, Jetstream Series
200, and Jetstream Series 3101 airplanes
that would supersede AD 2014–07–07.
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
cracking of the forward main landing
gear yoke pintle resulting from
corrosion pits leading to stress corrosion
cracking. 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 April 3, 2017.
ADDRESSES: You may send comments by
any of the following methods:
SUMMARY:
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• 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
view this 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–2017–
0053; 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:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@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–2017–0053; Directorate Identifier
2016–CE–037–AD’’ at the beginning of
your comments. We specifically invite
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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.
mstockstill on DSK3G9T082PROD with PROPOSALS
Discussion
On April 4, 2014, we issued AD 2014–
07–07, Amendment 39–17821 (79 FR
23897; April 29, 2014) (‘‘2014–07–07’’).
That AD required actions intended to
address an unsafe condition on British
Aerospace Regional Aircraft Model HP
137 Jetstream MK1, Jetstream Series
200, and Jetstream Series 3101 airplanes
and was based on mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country.
Since we issued AD 2014–07–07,
additional stress corrosion cracking in
the pintle housing has been found that
may not be detected during the current
inspection procedures.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD No.:
2016–0224, dated November 9, 2016
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Prompted by occurrences of the main
landing gear (MLG) yoke pintle housing
cracking, the Civil Aviation Authority (CAA)
UK issued AD 003–01–86 to require
repetitive inspections to detect cracks in the
yoke pintle housing on MLG fitted to
Jetstream 3100 aeroplanes in accordance with
BAE Systems (Operations) Ltd Service
Bulletin (SB) 32–A–JA851226, and,
depending on findings, corrective action.
After that AD was issued, an occurrence was
reported of Jetstream 3100 MLG failure after
landing. The subsequent investigation
revealed stress corrosion cracking of the MLG
yoke pintle housing to have caused this MLG
failure. Furthermore, the investigation report
recommended a review of the effectiveness of
CAA UK AD 003–01–86 in finding cracks in
the yoke pintle housing on MLG fitted to
Jetstream 3100 aeroplanes.
Degradation of the surface protection by
abrasion can occur when the forward face of
the yoke pintle rotates against the pintle
bearing, which introduces corrosion pits and,
consequently, stress corrosion cracking. This
condition, if not detected and 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 provide protection of the affected area
of the MLG assembly spigot housing, BAE
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Systems (Operations) Ltd issued SB 32–
JM7862 to provide instructions for
installation of a protective washer, fitted at
the forward spigot on both left hand and right
hand MLG. Consequently, BAE Systems
(Operations) Ltd issued SB 32–A–JA851226
Revision 05 to provide additional
accomplishment instructions for a Nondestructive testing (NDT) inspection of MLG
equipped with the protective washer
installed in accordance with BAE Systems
(Operations) Ltd SB 32–JM7862.
Consequently, EASA issued AD 2013–
0208, retaining the requirements of CAA UK
AD 003–01–86, which was superseded, and
required implementation of revised
inspection requirements, and, depending on
findings, accomplishment of applicable
corrective action(s). That AD also introduced
an optional modification, which constituted
terminating action for the inspections
required by that AD.
Since that AD was issued, BAE Systems
(Operations) Ltd has determined that the
existing inspection procedure may not be
effective in identifying stress corrosion
cracking in the pintle housing. Consequently
BAE Systems (Operations) Ltd has published
an improved inspection procedure in SB 32–
A–JA851226 Revision 07. This improved
inspection procedure has the ability to detect
smaller corrosion pits and cracks that are
proximate in size to those that will initiate
stress corrosion.
For the reasons described above, this AD
retains the requirements of EASA AD 2013–
0208, which is superseded, and requires
MLG inspections in accordance with the
improved procedure.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2017–0053.
Related Service Information Under 1
CFR Part 51
British Aerospace Regional Aircraft
has issued British Aerospace Jetstream
Series 3100 & 3200 Service Bulletin 32–
A–JA851226, Revision 7, dated May 25,
2015. The service information describes
procedures for nondestructive testing
(NDT) and visual inspections of the
main landing gear spigot housing for
cracks and repair if necessary. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this NPRM.
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
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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 26 products of U.S. registry.
We also estimate that it would take
about 14 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour.
Based on these figures, we estimate
the cost of the proposed AD on U.S.
operators to be $30,940, or $1,190 per
product.
In addition, we estimate that any
necessary follow-on actions would take
about 2 work-hours and require parts
costing $5,000, for a cost of $5,170 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
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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 39–17821 (82 FR
23897; April 29, 2014), and adding the
following new AD:
■
British Aerospace Regional Aircraft: Docket
No. FAA–2017–0053; Directorate
Identifier 2016–CE–037–AD.
(a) Comments Due Date
We must receive comments by April 3,
2017.
(b) Affected ADs
This AD replaces AD 2014–07–07,
Amendment 39–17821 (79 FR 23897; April
29, 2014) (‘‘2014–07–07’’).
(c) Applicability
This AD applies to British Aerospace
(Operations) Limited Model HP.137 Jetstream
Mk.1, Jetstream Series 200, and Jetstream
Series 3101 airplanes, all serial numbers,
certificated in any category.
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(d) Subject
Air Transport Association of America
(ATA) Code 32: Landing Gear.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as cracking of
the forward main landing gear yoke pintle
resulting from corrosion pits which can cause
stress corrosion cracking resulting in loss of
control during take-off or landing. We are
issuing this AD to revise the inspection
procedure to detect smaller corrosion pits
and cracks that could initiate stress corrosion
cracking.
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16:56 Feb 16, 2017
Jkt 241001
(f) Actions and Compliance
Unless already done, do the following
actions specified in paragraphs (f)(1) through
(11) of this AD:
(1) For all airplanes: Before or at the next
inspection that would have been required by
AD 2014–07–07 or within the next 30 days
after the effective date of this AD, whichever
occurs later, and repetitively thereafter at
intervals not to exceed 12 months or 1,200
main landing gear (MLG) flight cycles (FC),
whichever occurs first, do a nondestructive
testing (NDT) inspection of each MLG
assembly cylinder attachment spigot housing
following the Accomplishment Instructions
in paragraph 2.B. Part A of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA851226, Revision 7, dated May 25,
2015.
(2) For all airplanes: Within 300 landings
after a heavy or abnormal landing or 3
months after a heavy or abnormal landing,
whichever occurs first, do a NDT inspection
of each MLG assembly cylinder attachment
spigot housing following the accomplishment
instructions in paragraph 2.B. Part A of
British Aerospace Jetstream Series 3100 &
3200 Service Bulletin 32–A–JA851226,
Revision 7, dated May 25, 2015.
(3) For all airplanes: Within 3 months after
accomplishment of the the latest NDT
inspection required by paragraph (f)(1) of this
AD or 300 MLG FC after accomplishment of
the latest NDT inspection required by
paragraph (f)(1) of this AD, whichever occurs
first, and repetitively thereafter at intervals
not to exceed 3 months or 300 MLG FC,
whichever occurs first, do a visual inspection
of each MLG following the accomplishment
instructions in paragraph 2.B. Part B of
British Aerospace Jetstream Series 3100 &
3200 Service Bulletin 32–A–JA851226,
Revision 7, dated May 25, 2015. These
inspections start over after every repetitive
NDT inspection required by paragraph
(f)(1)of this AD.
(4) For all airplanes with a MLG
incorporating a microswitch hole: Within the
next 10,600 MLG FC since new and
repetitively thereafter at intervals not to
exceed 1,200 MLG flight cycles, do a NDT
inspection of each MLG microswitch hole
following the accomplishment instructions in
paragraph 2.B. Part C of British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin
32–A–JA851226, Revision 7, dated May 25,
2015.
(5) For all airplanes: If any discrepancy is
found during any NDT inspection required in
paragraphs (f)(1), (2), or (4) of this AD, before
further flight, take all necessary corrective
actions following the instructions in British
Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32–A–JA851226, Revision 7,
dated May 25, 2015.
(6) For all airplanes: If any discrepancy is
found during any visual inspection required
in paragraph (f)(3) of this AD, before further
flight, take all necessary corrective actions
following the instructions in British
Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32–A–JA851226, Revision 7,
dated May 25, 2015.
(7) For all airplanes: Doing all necessary
corrective actions required in paragraphs
(f)(5) or (6) of this AD does not constitute
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10975
terminating action for the inspections
required by this AD.
(8) For all airplanes: Modification of each
MLG cylinder following BAE Systems
(Operations) Ltd. Service Bulletin 32–
JA880340 original issue, dated January 6,
1989, constitutes terminating action for the
inspections required by this AD for that
MLG.
(9) For all airplanes: The compliance times
in paragraphs (f)(1), (2), (3), and (4) 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. For the purposes of this AD:
(i) 100 hours TIS × .75 = 75 cycles; and
(ii) 1,000 hours TIS × .75 = 750 cycles.
(g) Credit for Actions Done in Accordance
With Previous Service Information
(1) This AD allows credit for the initial
inspection required in paragraph (f)(1) of this
AD if done before June 3, 2014 (the effective
date retained from AD 2014–07–07)
following British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–A–
JA851226, Revision 5, dated April 30, 2013.
(2) This AD allows credit for the initial
inspection required in paragraph (f)(4) of this
AD if done before June 3, 2014 (the effective
date retained from AD 2014–07–07)
following APPH Ltd. Service Bulletin 32–40,
at Initial Issue dated June 21, 1989.
(h) 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: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@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.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
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including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(i) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2016–0224, dated
November 9, 2016 for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–0053.
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.
Issued in Kansas City, Missouri, on January
19, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–02771 Filed 2–16–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0078; Directorate
Identifier 2015–SW–026–AD]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Limited
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for Bell
Helicopter Textron Canada Limited
(Bell) Model 429 helicopters. This
proposed AD would require adding an
identification number to life-limited rod
ends that do not have a serial number
(S/N). The proposed actions are
intended to address an unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by April 18, 2017.
mstockstill on DSK3G9T082PROD with PROPOSALS
SUMMARY:
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16:56 Feb 16, 2017
Jkt 241001
You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
ADDRESSES:
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–2017–
0078 or in person at the Docket
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this proposed AD, the
Transport Canada AD, the economic
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 service information identified in
this proposed rule, 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/.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177.
FOR FURTHER INFORMATION CONTACT: Matt
Fuller, Senior Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 10101 Hillwood
Pkwy, Fort Worth, TX 76177; telephone
(817) 222–5110; email matthew.fuller@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
Discussion
Transport Canada, which is the
aviation authority for Canada, has
issued AD No. CF–2015–15, dated June
25, 2015, to correct an unsafe condition
for Bell Model 429 helicopters, S/Ns
57001 through 57260. Transport Canada
advises that, per its regulations, lifelimited parts must be marked with their
part number (P/N) and S/N. Transport
Canada further states that the pylon
restraint spring assembly (spring
assembly) rod end P/N 427–010–210–
105 has a life limit of 5,000 hours;
however, it is not serialized, causing
difficulties in tracking its accumulated
air time. According to Transport
Canada, this condition could result in a
rod end remaining in service beyond its
life limit. Therefore, the Transport
Canada AD requires adding
identification markings on each spring
assembly rod end.
FAA’s Determination
These helicopters have been approved
by the aviation authority of Canada and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with Canada, Transport
Canada, its technical representative, has
notified us of the unsafe condition
described in its AD. We are proposing
this AD because we evaluated all known
relevant information and determined
that an unsafe condition is likely to
exist or develop on other products of the
same type design.
Related Service Information Under 1
CFR Part 51
Bell Helicopter has issued Alert
Service Bulletin 429–15–19, dated
February 26, 2015. This service
information specifies procedures for
permanently marking each forward and
aft rod end with the S/N of the spring
assembly. This service information
E:\FR\FM\17FEP1.SGM
17FEP1
]]>Agencies
[Federal Register Volume 82, Number 32 (Friday, February 17, 2017)]
[Proposed Rules]
[Pages 10973-10976]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-02771]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0053; Directorate Identifier 2016-CE-037-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 HP 137 Jetstream MK1,
Jetstream Series 200, and Jetstream Series 3101 airplanes that would
supersede AD 2014-07-07. 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 cracking of the forward main landing gear yoke pintle
resulting from corrosion pits leading to stress corrosion cracking. 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 April 3, 2017.
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 view this 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-2017-
0053; 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: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@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-2017-0053;
Directorate Identifier 2016-CE-037-AD'' at the beginning of your
comments. We specifically invite
[[Page 10974]]
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 April 4, 2014, we issued AD 2014-07-07, Amendment 39-17821 (79
FR 23897; April 29, 2014) (``2014-07-07''). That AD required actions
intended to address an unsafe condition on British Aerospace Regional
Aircraft Model HP 137 Jetstream MK1, Jetstream Series 200, and
Jetstream Series 3101 airplanes and was based on mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country.
Since we issued AD 2014-07-07, additional stress corrosion cracking
in the pintle housing has been found that may not be detected during
the current inspection procedures.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD No.: 2016-0224, dated November 9, 2016 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Prompted by occurrences of the main landing gear (MLG) yoke
pintle housing cracking, the Civil Aviation Authority (CAA) UK
issued AD 003-01-86 to require repetitive inspections to detect
cracks in the yoke pintle housing on MLG fitted to Jetstream 3100
aeroplanes in accordance with BAE Systems (Operations) Ltd Service
Bulletin (SB) 32-A-JA851226, and, depending on findings, corrective
action. After that AD was issued, an occurrence was reported of
Jetstream 3100 MLG failure after landing. The subsequent
investigation revealed stress corrosion cracking of the MLG yoke
pintle housing to have caused this MLG failure. Furthermore, the
investigation report recommended a review of the effectiveness of
CAA UK AD 003-01-86 in finding cracks in the yoke pintle housing on
MLG fitted to Jetstream 3100 aeroplanes.
Degradation of the surface protection by abrasion can occur when
the forward face of the yoke pintle rotates against the pintle
bearing, which introduces corrosion pits and, consequently, stress
corrosion cracking. This condition, if not detected and 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 provide protection of the affected area of the MLG assembly
spigot housing, BAE Systems (Operations) Ltd issued SB 32-JM7862 to
provide instructions for installation of a protective washer, fitted
at the forward spigot on both left hand and right hand MLG.
Consequently, BAE Systems (Operations) Ltd issued SB 32-A-JA851226
Revision 05 to provide additional accomplishment instructions for a
Non-destructive testing (NDT) inspection of MLG equipped with the
protective washer installed in accordance with BAE Systems
(Operations) Ltd SB 32-JM7862.
Consequently, EASA issued AD 2013-0208, retaining the
requirements of CAA UK AD 003-01-86, which was superseded, and
required implementation of revised inspection requirements, and,
depending on findings, accomplishment of applicable corrective
action(s). That AD also introduced an optional modification, which
constituted terminating action for the inspections required by that
AD.
Since that AD was issued, BAE Systems (Operations) Ltd has
determined that the existing inspection procedure may not be
effective in identifying stress corrosion cracking in the pintle
housing. Consequently BAE Systems (Operations) Ltd has published an
improved inspection procedure in SB 32-A-JA851226 Revision 07. This
improved inspection procedure has the ability to detect smaller
corrosion pits and cracks that are proximate in size to those that
will initiate stress corrosion.
For the reasons described above, this AD retains the
requirements of EASA AD 2013-0208, which is superseded, and requires
MLG inspections in accordance with the improved procedure.
You may examine the MCAI on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2017-0053.
Related Service Information Under 1 CFR Part 51
British Aerospace Regional Aircraft has issued British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin 32-A-JA851226, Revision
7, dated May 25, 2015. The service information describes procedures for
nondestructive testing (NDT) and visual inspections of the main landing
gear spigot housing for cracks and repair if necessary. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section of this NPRM.
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 26 products of U.S.
registry. We also estimate that it would take about 14 work-hours per
product to comply with the basic requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of the proposed AD on
U.S. operators to be $30,940, or $1,190 per product.
In addition, we estimate that any necessary follow-on actions would
take about 2 work-hours and require parts costing $5,000, for a cost of
$5,170 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
[[Page 10975]]
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 39-17821 (82 FR
23897; April 29, 2014), and adding the following new AD:
British Aerospace Regional Aircraft: Docket No. FAA-2017-0053;
Directorate Identifier 2016-CE-037-AD.
(a) Comments Due Date
We must receive comments by April 3, 2017.
(b) Affected ADs
This AD replaces AD 2014-07-07, Amendment 39-17821 (79 FR 23897;
April 29, 2014) (``2014-07-07'').
(c) Applicability
This AD applies to British Aerospace (Operations) Limited Model
HP.137 Jetstream Mk.1, Jetstream Series 200, and Jetstream Series
3101 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) issued by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as cracking of the
forward main landing gear yoke pintle resulting from corrosion pits
which can cause stress corrosion cracking resulting in loss of
control during take-off or landing. We are issuing this AD to revise
the inspection procedure to detect smaller corrosion pits and cracks
that could initiate stress corrosion cracking.
(f) Actions and Compliance
Unless already done, do the following actions specified in
paragraphs (f)(1) through (11) of this AD:
(1) For all airplanes: Before or at the next inspection that
would have been required by AD 2014-07-07 or within the next 30 days
after the effective date of this AD, whichever occurs later, and
repetitively thereafter at intervals not to exceed 12 months or
1,200 main landing gear (MLG) flight cycles (FC), whichever occurs
first, do a nondestructive testing (NDT) inspection of each MLG
assembly cylinder attachment spigot housing following the
Accomplishment Instructions in paragraph 2.B. Part A of British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 7, dated May 25, 2015.
(2) For all airplanes: Within 300 landings after a heavy or
abnormal landing or 3 months after a heavy or abnormal landing,
whichever occurs first, do a NDT inspection of each MLG assembly
cylinder attachment spigot housing following the accomplishment
instructions in paragraph 2.B. Part A of British Aerospace Jetstream
Series 3100 & 3200 Service Bulletin 32-A-JA851226, Revision 7, dated
May 25, 2015.
(3) For all airplanes: Within 3 months after accomplishment of
the the latest NDT inspection required by paragraph (f)(1) of this
AD or 300 MLG FC after accomplishment of the latest NDT inspection
required by paragraph (f)(1) of this AD, whichever occurs first, and
repetitively thereafter at intervals not to exceed 3 months or 300
MLG FC, whichever occurs first, do a visual inspection of each MLG
following the accomplishment instructions in paragraph 2.B. Part B
of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin
32-A-JA851226, Revision 7, dated May 25, 2015. These inspections
start over after every repetitive NDT inspection required by
paragraph (f)(1)of this AD.
(4) For all airplanes with a MLG incorporating a microswitch
hole: Within the next 10,600 MLG FC since new and repetitively
thereafter at intervals not to exceed 1,200 MLG flight cycles, do a
NDT inspection of each MLG microswitch hole following the
accomplishment instructions in paragraph 2.B. Part C of British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 7, dated May 25, 2015.
(5) For all airplanes: If any discrepancy is found during any
NDT inspection required in paragraphs (f)(1), (2), or (4) of this
AD, before further flight, take all necessary corrective actions
following the instructions in British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32-A-JA851226, Revision 7, dated May
25, 2015.
(6) For all airplanes: If any discrepancy is found during any
visual inspection required in paragraph (f)(3) of this AD, before
further flight, take all necessary corrective actions following the
instructions in British Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32-A-JA851226, Revision 7, dated May 25, 2015.
(7) For all airplanes: Doing all necessary corrective actions
required in paragraphs (f)(5) or (6) of this AD does not constitute
terminating action for the inspections required by this AD.
(8) For all airplanes: Modification of each MLG cylinder
following BAE Systems (Operations) Ltd. Service Bulletin 32-JA880340
original issue, dated January 6, 1989, constitutes terminating
action for the inspections required by this AD for that MLG.
(9) For all airplanes: The compliance times in paragraphs
(f)(1), (2), (3), and (4) 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. For the purposes of this AD:
(i) 100 hours TIS x .75 = 75 cycles; and
(ii) 1,000 hours TIS x .75 = 750 cycles.
(g) Credit for Actions Done in Accordance With Previous Service
Information
(1) This AD allows credit for the initial inspection required in
paragraph (f)(1) of this AD if done before June 3, 2014 (the
effective date retained from AD 2014-07-07) following British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-A-
JA851226, Revision 5, dated April 30, 2013.
(2) This AD allows credit for the initial inspection required in
paragraph (f)(4) of this AD if done before June 3, 2014 (the
effective date retained from AD 2014-07-07) following APPH Ltd.
Service Bulletin 32-40, at Initial Issue dated June 21, 1989.
(h) 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: Doug Rudolph, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@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.
(3) Reporting Requirements: For any reporting requirement in
this AD, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response,
[[Page 10976]]
including the time for reviewing instructions, completing and
reviewing the collection of information. All responses to this
collection of information are mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden
should be directed to the FAA at: 800 Independence Ave. SW.,
Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(i) Related Information
Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2016-0224, dated November 9, 2016 for related information. You may
examine the MCAI on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0053. 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.
Issued in Kansas City, Missouri, on January 19, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-02771 Filed 2-16-17; 8:45 am]
BILLING CODE 4910-13-P
