Airworthiness Directives; BAE Systems (Operations) Limited Airplanes, 3350-3353 [2016-01088]
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules
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 adding
the following new airworthiness
directive (AD):
■
Beechcraft Corporation (Type Certificate
Previously Held by Hawker Beechcraft
Corporation; Raytheon Aircraft
Company): Docket No. FAA–2016–0460;
Directorate Identifier 2015–NM–078–AD.
(a) Comments Due Date
We must receive comments by March 7,
2016.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(b) Affected ADs
None.
(c) Applicability
This AD applies to Beechcraft Corporation
(type certificate previously held by Hawker
Beechcraft Corporation; Raytheon Aircraft
Company) airplanes, certificated in any
category, as identified in paragraphs (c)(1)
and (c)(2) of this AD.
(1) Model BAe.125 series 1000A and 1000B
airplanes, serial numbers 258151, 258159,
and 259004 through 259042 inclusive.
(2) Model Hawker 1000 airplanes, serial
numbers 259003 and 259043 through 259052
inclusive.
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(d) Subject
Air Transport Association (ATA) of
America Code 78, Exhaust.
(e) Unsafe Condition
This AD was prompted by reports of
inadvertent stowage of the thrust reversers,
which can result in high forward engine
thrust even though the throttle is
commanding reverse thrust. We are issuing
this AD to prevent inadvertent stowage of the
thrust reversers, which could cause a runway
overrun during a rejected takeoff or landing,
and consequent structural failure and
possible injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
https://pubs.beechcraft.com. You may view
this referenced service information at FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on January
8, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–00951 Filed 1–20–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(g) Installation
Within 600 flight hours or 12 months after
the effective date of this AD, whichever
occurs first: Install kits having part numbers
140–9005 and 140–9006, in accordance with
the Accomplishment Instructions of
Beechcraft Mandatory Service Bulletin 78–
4133, dated May 2015, except as specified in
paragraph (h) of this AD.
14 CFR Part 39
(h) Exception to Service Information
A note in the Accomplishment Instructions
of Beechcraft Mandatory Service Bulletin 78–
4133, dated May 2015, instructs operators to
contact Beechcraft Corporation if any
difficulty is encountered in accomplishing
the service bulletin. However, any deviation
from the actions required by paragraph (g) of
this AD must be approved as an alternative
method of compliance (AMOC) under
paragraph (i)(1) of this AD.
AGENCY:
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j)(1) of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
(1) For more information about this AD,
contact Jeffrey Englert, Aerospace Engineer,
Mechanical Systems and Propulsion Branch,
ACE–116W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road,
Room 100, Dwight D. Eisenhower National
Airport, Wichita, KS 67209; phone: 316–946–
4167; fax: 316–946–4107; email:
jeffrey.englert@faa.gov.
(2) For service information identified in
this AD, contact Beechcraft Corporation,
TMDC, P.O. Box 85, Wichita, KS 67201–
0085; telephone 316–676–8238; fax 316–671–
2540; email tmdc@beechcraft.com; Internet
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[Docket No. FAA–2016–0457; Directorate
Identifier 2015–NM–084–AD]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
We propose to supersede
Airworthiness Directive (AD) 2012–11–
15, for all BAE Systems (Operations)
Limited Model 4101 airplanes. AD
2012–11–15 currently requires a onetime detailed inspection for cracks,
corrosion, and other defects of the rear
face of the wing rear spar, and repair if
necessary. Since we issued AD 2012–
11–15, we received new reports of
cracking found in the wing rear spar and
technical analysis results confirmed that
the crack initiation and propagation are
due to fatigue, with no indication of any
other crack initiation mechanism (e.g.
stress corrosion). This proposed AD
would require repetitive detailed
inspections, and repair if necessary. We
are proposing this AD to detect and
correct cracking in the wing rear spar,
which could propagate to a critical
length, possibly affecting the structural
integrity of the area and resulting in a
fuel tank rupture, with consequent
damage to the airplane and possible
injury to its occupants.
DATES: We must receive comments on
this proposed AD by March 7, 2016.
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–
SUMMARY:
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30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact BAE Systems
(Operations) Limited, Customer
Information Department, Prestwick
International Airport, Ayrshire, KA9
2RW, Scotland, United Kingdom;
telephone +44 1292 675207; fax +44
1292 675704; email RApublications@
baesystems.com; Internet https://
www.baesystems.com/Businesses/
RegionalAircraft/index.htm. You may
view this referenced service information
at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
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–2016–
0457; 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 Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1175;
fax 425–227–1149.
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–2016–0457; Directorate Identifier
2015–NM–084–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 based on those comments.
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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 March 31, 2012, we issued AD
2012–11–15, Amendment 39–17079 (77
FR 36127, June 18, 2012). AD 2012–11–
15 requires actions intended to address
an unsafe condition on BAE Systems
(Operations) Limited Model 4101
airplanes.
Since we issued AD 2012–11–15,
Amendment 39–17079 (77 FR 36127,
June 18, 2012), we received new reports
of cracking found in the wing rear spar
and technical analysis results confirmed
that the crack initiation and propagation
are due to fatigue, with no indication of
any other crack initiation mechanism
(e.g. stress corrosion).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0100, dated June 3, 2015
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all BAE Systems
(Operations) Limited Model 4101
airplanes. The MCAI states:
During an investigation of a fuel leak on
the rear spar of a Jetstream 4100 aeroplane,
4 cracks were found between Ribs 6 and 7
(immediately inboard of the inboard engine
rib). The cracks initiated at adjacent fastener
bores in the rear spar upper boom, and
progressed downwards, diagonally, into the
rear spar web.
These cracks, if not detected and corrected,
could propagate to a critical length, affecting
the structural integrity of the area, possibly
resulting in a fuel tank rupture with
consequent damage to the aeroplane and
injury to its occupants.
Prompted by these findings, EASA issued
[EASA] AD 2011–0096 [which corresponds
to FAA AD 2012–11–15, Amendment 39–
17079 (77 FR 36127, June 18, 2012)] to
require a one-time [detailed] inspection [for
cracks, corrosion, and other defects] of the
rear face of the wing rear spar and the
accomplishment of applicable corrective
actions [i.e., repair], depending on findings.
Initial analysis of the event did not lead to
the conclusion that the cracking was fatigue
related, therefore [EASA] AD 2011–0096 did
not require repetitive inspections.
Since that [EASA] AD [2011–0096] was
issued, the results of the technical analysis
confirmed that the cracks were due to fatigue,
with no indication of any other crack
initiation mechanism (e.g. stress corrosion).
In addition, further similar in-service events
have been reported. During investigation of
those events, further metallurgical analysis
indicated that the crack initiation and
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3351
propagation are indeed fatigue driven and
occur at the same location.
To address this unsafe condition, a review
of the inspection interval was undertaken
based on the cracks from both aeroplanes and
BAE Systems (Operations) Ltd issued Service
Bulletin (SB) J41–A57–029 Revision 3 in
order to reduce the inspection interval of the
wing rear spar from 2,000 flight cycles (FC)
to 1,600 FC.
For the reasons described above, this
[EASA] AD supersedes AD 2011–0096,
without retaining its requirements,
introduces repetitive inspections and,
depending on findings, requires the
accomplishments of applicable corrective
action(s) [i.e., repair].
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0457.
Related Service Information Under 1
CFR Part 51
BAE Systems (Operations) Limited
has issued Alert Service Bulletin J41–
A57–029, Revision 3, dated April 8,
2014. The service information describes
detailed inspections for cracks,
corrosion, and other defects of the rear
face of the wing rear spars.
BAE Systems (Operations) Limited
also has issued Subject 57–00–00,
Wings General, of Chapter 57, Wings, of
the Jetstream Series 4100 Structural
Repair Manual, Volume 1, Revision 32,
dated October 15, 2014. The service
information describes procedures for
doing certain wing repairs.
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.
FAA’s Determination and Requirements
of This 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 the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD
affects 15 airplanes of U.S. registry.
We also estimate that it would take up
to 25 work-hours per product to comply
with the basic requirements of this
proposed AD. The average labor rate is
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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules
$85 per work-hour. Based on these
figures, we estimate the cost of this
proposed AD on U.S. operators to be up
to $31,875, or up to $2,125 per product.
We have received no definitive data
that would enable us to provide a cost
estimates for the on-condition actions
(repairing cracks, corrosion, and defects)
specified in this AD.
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.
Authority for This Rulemaking
§ 39.13
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
jstallworth on DSK7TPTVN1PROD with PROPOSALS
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,
VerDate Sep<11>2014
15:09 Jan 20, 2016
Jkt 238001
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–11–15, Amendment 39–17079 (77
FR 36127, June 18, 2012), and adding
the following new AD:
BAE Systems (Operations) Limited: Docket
No. FAA–2016–0457; Directorate
Identifier 2015–NM–084–AD.
(a) Comments Due Date
We must receive comments by March 7,
2016.
(b) Affected ADs
This AD replaces AD 2012–11–15,
Amendment 39–17079 (77 FR 36127, June
18, 2012).
(c) Applicability
This AD applies to BAE (Operations)
Limited Model 4101 airplanes, certificated in
any category, all models, and all serial
numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by new reports of
cracking found in the wing rear spar and
technical analysis results confirmed that the
crack initiation and propagation are due to
fatigue, with no indication of any other crack
initiation mechanism (e.g., stress corrosion).
We are issuing this AD to detect and correct
cracking in the wing rear spar, which could
propagate to a critical length, possibly
affecting the structural integrity of the area
and resulting in a fuel tank rupture, with
consequent damage to the airplane and
possible injury to its occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Repair
Within 30 days after the effective date of
this AD, or within 1,600 flight cycles since
the most recent detailed inspection was done
as specified in BAE Systems Alert Service
Bulletin J41–A57–029, whichever occurs
later: Do a detailed inspection for cracks,
corrosion, and other defects (defects include
scratches, dents, holes, damage to fastener
holes, or damage to surface protection and
finish) of the rear face of the wing rear spars,
in accordance with the Accomplishment
Instructions of BAE Systems Alert Service
Bulletin J41–A57–029, Revision 3, dated
April 8, 2014. Repeat the inspection
thereafter at intervals not to exceed 1,600
flight cycles.
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(1) If any cracking, corrosion, or other
defect is found within the criteria defined in
Subject 57–00–00, Wings General, of Chapter
57, Wings, of the Jetstream Series 4100
Structural Repair Manual, Volume 1,
Revision 32, dated October 15, 2014: Before
further flight, repair the affected area, in
accordance with the repair instructions of
Subject 57–00–00, Wings General, of Chapter
57, Wings, of the Jetstream Series 4100
Structural Repair Manual, Volume 1,
Revision 32, dated October 15, 2014.
(2) If any cracking, corrosion, or other
defect is found exceeding the criteria defined
in Subject 57–00–00, Wings General, of
Chapter 57, Wings, of the Jetstream Series
4100 Structural Repair Manual, Volume 1,
Revision 32, dated October 15, 2014: Before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or BAE Systems
(Operations) Limited’s EASA Design
Organization Approval (DOA).
(h) Repair Does Not Constitute Terminating
Action Except for Certain Repairs
Accomplishment of a repair as required by
paragraphs (g)(1) and (g)(2) of this AD, does
not constitute terminating action for the
repetitive inspections required by paragraph
(g) of this AD, unless the approved repair
required by paragraph (g)(2) of this AD states
otherwise (e.g., the approved repair states the
repair terminates the inspections for the
repaired area only).
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1175; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or BAE Systems (Operations)
Limited’s EASA Design Organization
Approval (DOA). If approved by the DOA,
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the approval must include the DOAauthorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0100, dated
June 3, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–0457.
(2) For service information identified in
this AD, contact BAE Systems (Operations)
Limited, Customer Information Department,
Prestwick International Airport, Ayrshire,
KA9 2RW, Scotland, United Kingdom;
telephone +44 1292 675207; fax +44 1292
675704; email RApublications@
baesystems.com; Internet https://
www.baesystems.com/Businesses/
RegionalAircraft/index.htm. You may view
this service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
Issued in Renton, Washington, on January
13, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–01088 Filed 1–20–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 73
[Docket No. FAA–2015–2776; Airspace
Docket No. 15–AEA–5]
RIN 2120–AA66
Proposed Amendment and
Establishment of Restricted Areas;
Chincoteague Inlet, VA
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM); reopening of comment period.
AGENCY:
This action reopens the
comment period for the NPRM
published September 10, 2015,
proposing to expand the restricted
airspace at Chincoteague Inlet, VA. This
reopening of the comment period is
necessary because a chart depicting the
proposed airspace was not available
prior to the original comment period
closing date. This action will ensure
that interested persons have the
opportunity to view the chart and
submit comments regarding the
proposal.
DATES: The comment period for the
NPRM published September 10, 2015
(80 FR 54444) closed on October 26,
jstallworth on DSK7TPTVN1PROD with PROPOSALS
SUMMARY:
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2015, and reopened until February 22,
2016.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, 1200 New Jersey Avenue SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001; telephone:
(202) 366–9826. You must identify FAA
Docket No. FAA–2015–2776 and
Airspace Docket No. 15–AEA–5, at the
beginning of your comments. You may
also submit comments through the
Internet at
https://www.regulations.gov. Comments
on environmental and land use aspects
to should be directed to: NASA Wallops
Flight Facility, Attn: Ms. Shari Silbert,
Wallops Island, VA 23337; telephone:
(757) 824–2327.
FOR FURTHER INFORMATION CONTACT: Paul
Gallant, Airspace Policy Group, Office
of Airspace Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2015–2776 and Airspace Docket No. 15–
AEA–5) and be submitted in triplicate to
the Docket Management System (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at https://
www.regulations.gov.
Persons wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2015–2776 and
Airspace Docket No. 15–AEA–5.’’ The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
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3353
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of NPRM’s
An electronic copy of this document
may be downloaded through the
internet at https://www.regulations.gov.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person at the Dockets Office (see
ADDRESSES section for address and
phone number) between 9:00 a.m. and
5:00 p.m., Monday through Friday,
except Federal holidays. An informal
docket may also be examined during
normal business hours at the office of
the Operations Support Group, Eastern
Service Center, Federal Aviation
Administration, 1701 Columbia Ave.,
College Park, GA 30337.
Persons interested in being placed on
a mailing list for future NPRM’s should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A.
Background
On September 10, 2015, the FAA
published a notice of proposed
rulemaking (NPRM) proposing the
amendment and establishment of
restricted areas at Chincoteague Inlet,
VA (80 FR 54444), Docket No. FAA–
2015–2776, Airspace Docket No. 15–
AEA–5. The NPRM included a
statement that a color chart of the
proposed airspace would be available
for viewing on the www.regulations.gov
Web site. However, the chart was not
posted until after the comment closing
date. One commenter responded that it
is difficult to understand the proposed
changes because the chart was
unavailable.
A color chart showing the location of
the proposed restricted areas is now
posted on the internet at https://
www.regulations.gov. Search docket no.
FAA–2015–2776 and click on ‘‘open
docket folder’’ to view the chart.
To give the public an opportunity to
view the chart prior to submitting
comments, the FAA is reopening the
comment period for 30 days. All
comments submitted during the new
comment period, as well as all
comments previously received, will be
considered before any final action is
taken on the proposal. No other
proposal information as published in
the NPRM has been changed.
E:\FR\FM\21JAP1.SGM
21JAP1
]]>Agencies
[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Proposed Rules]
[Pages 3350-3353]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01088]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-0457; Directorate Identifier 2015-NM-084-AD]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-11-
15, for all BAE Systems (Operations) Limited Model 4101 airplanes. AD
2012-11-15 currently requires a one-time detailed inspection for
cracks, corrosion, and other defects of the rear face of the wing rear
spar, and repair if necessary. Since we issued AD 2012-11-15, we
received new reports of cracking found in the wing rear spar and
technical analysis results confirmed that the crack initiation and
propagation are due to fatigue, with no indication of any other crack
initiation mechanism (e.g. stress corrosion). This proposed AD would
require repetitive detailed inspections, and repair if necessary. We
are proposing this AD to detect and correct cracking in the wing rear
spar, which could propagate to a critical length, possibly affecting
the structural integrity of the area and resulting in a fuel tank
rupture, with consequent damage to the airplane and possible injury to
its occupants.
DATES: We must receive comments on this proposed AD by March 7, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-
[[Page 3351]]
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact BAE
Systems (Operations) Limited, Customer Information Department,
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email
RApublications@baesystems.com; Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm. You may view this referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0457; 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
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1175;
fax 425-227-1149.
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-2016-0457;
Directorate Identifier 2015-NM-084-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 based on 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 March 31, 2012, we issued AD 2012-11-15, Amendment 39-17079 (77
FR 36127, June 18, 2012). AD 2012-11-15 requires actions intended to
address an unsafe condition on BAE Systems (Operations) Limited Model
4101 airplanes.
Since we issued AD 2012-11-15, Amendment 39-17079 (77 FR 36127,
June 18, 2012), we received new reports of cracking found in the wing
rear spar and technical analysis results confirmed that the crack
initiation and propagation are due to fatigue, with no indication of
any other crack initiation mechanism (e.g. stress corrosion).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0100, dated June 3, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all BAE Systems
(Operations) Limited Model 4101 airplanes. The MCAI states:
During an investigation of a fuel leak on the rear spar of a
Jetstream 4100 aeroplane, 4 cracks were found between Ribs 6 and 7
(immediately inboard of the inboard engine rib). The cracks
initiated at adjacent fastener bores in the rear spar upper boom,
and progressed downwards, diagonally, into the rear spar web.
These cracks, if not detected and corrected, could propagate to
a critical length, affecting the structural integrity of the area,
possibly resulting in a fuel tank rupture with consequent damage to
the aeroplane and injury to its occupants.
Prompted by these findings, EASA issued [EASA] AD 2011-0096
[which corresponds to FAA AD 2012-11-15, Amendment 39-17079 (77 FR
36127, June 18, 2012)] to require a one-time [detailed] inspection
[for cracks, corrosion, and other defects] of the rear face of the
wing rear spar and the accomplishment of applicable corrective
actions [i.e., repair], depending on findings. Initial analysis of
the event did not lead to the conclusion that the cracking was
fatigue related, therefore [EASA] AD 2011-0096 did not require
repetitive inspections.
Since that [EASA] AD [2011-0096] was issued, the results of the
technical analysis confirmed that the cracks were due to fatigue,
with no indication of any other crack initiation mechanism (e.g.
stress corrosion). In addition, further similar in-service events
have been reported. During investigation of those events, further
metallurgical analysis indicated that the crack initiation and
propagation are indeed fatigue driven and occur at the same
location.
To address this unsafe condition, a review of the inspection
interval was undertaken based on the cracks from both aeroplanes and
BAE Systems (Operations) Ltd issued Service Bulletin (SB) J41-A57-
029 Revision 3 in order to reduce the inspection interval of the
wing rear spar from 2,000 flight cycles (FC) to 1,600 FC.
For the reasons described above, this [EASA] AD supersedes AD
2011-0096, without retaining its requirements, introduces repetitive
inspections and, depending on findings, requires the accomplishments
of applicable corrective action(s) [i.e., repair].
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
0457.
Related Service Information Under 1 CFR Part 51
BAE Systems (Operations) Limited has issued Alert Service Bulletin
J41-A57-029, Revision 3, dated April 8, 2014. The service information
describes detailed inspections for cracks, corrosion, and other defects
of the rear face of the wing rear spars.
BAE Systems (Operations) Limited also has issued Subject 57-00-00,
Wings General, of Chapter 57, Wings, of the Jetstream Series 4100
Structural Repair Manual, Volume 1, Revision 32, dated October 15,
2014. The service information describes procedures for doing certain
wing repairs.
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.
FAA's Determination and Requirements of This 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 the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 15 airplanes of U.S.
registry.
We also estimate that it would take up to 25 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is
[[Page 3352]]
$85 per work-hour. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be up to $31,875, or up to $2,125 per
product.
We have received no definitive data that would enable us to provide
a cost estimates for the on-condition actions (repairing cracks,
corrosion, and defects) specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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 Airworthiness Directive (AD)
2012-11-15, Amendment 39-17079 (77 FR 36127, June 18, 2012), and adding
the following new AD:
BAE Systems (Operations) Limited: Docket No. FAA-2016-0457;
Directorate Identifier 2015-NM-084-AD.
(a) Comments Due Date
We must receive comments by March 7, 2016.
(b) Affected ADs
This AD replaces AD 2012-11-15, Amendment 39-17079 (77 FR 36127,
June 18, 2012).
(c) Applicability
This AD applies to BAE (Operations) Limited Model 4101
airplanes, certificated in any category, all models, and all serial
numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by new reports of cracking found in the
wing rear spar and technical analysis results confirmed that the
crack initiation and propagation are due to fatigue, with no
indication of any other crack initiation mechanism (e.g., stress
corrosion). We are issuing this AD to detect and correct cracking in
the wing rear spar, which could propagate to a critical length,
possibly affecting the structural integrity of the area and
resulting in a fuel tank rupture, with consequent damage to the
airplane and possible injury to its occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Repair
Within 30 days after the effective date of this AD, or within
1,600 flight cycles since the most recent detailed inspection was
done as specified in BAE Systems Alert Service Bulletin J41-A57-029,
whichever occurs later: Do a detailed inspection for cracks,
corrosion, and other defects (defects include scratches, dents,
holes, damage to fastener holes, or damage to surface protection and
finish) of the rear face of the wing rear spars, in accordance with
the Accomplishment Instructions of BAE Systems Alert Service
Bulletin J41-A57-029, Revision 3, dated April 8, 2014. Repeat the
inspection thereafter at intervals not to exceed 1,600 flight
cycles.
(1) If any cracking, corrosion, or other defect is found within
the criteria defined in Subject 57-00-00, Wings General, of Chapter
57, Wings, of the Jetstream Series 4100 Structural Repair Manual,
Volume 1, Revision 32, dated October 15, 2014: Before further
flight, repair the affected area, in accordance with the repair
instructions of Subject 57-00-00, Wings General, of Chapter 57,
Wings, of the Jetstream Series 4100 Structural Repair Manual, Volume
1, Revision 32, dated October 15, 2014.
(2) If any cracking, corrosion, or other defect is found
exceeding the criteria defined in Subject 57-00-00, Wings General,
of Chapter 57, Wings, of the Jetstream Series 4100 Structural Repair
Manual, Volume 1, Revision 32, dated October 15, 2014: Before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA); or BAE Systems
(Operations) Limited's EASA Design Organization Approval (DOA).
(h) Repair Does Not Constitute Terminating Action Except for Certain
Repairs
Accomplishment of a repair as required by paragraphs (g)(1) and
(g)(2) of this AD, does not constitute terminating action for the
repetitive inspections required by paragraph (g) of this AD, unless
the approved repair required by paragraph (g)(2) of this AD states
otherwise (e.g., the approved repair states the repair terminates
the inspections for the repaired area only).
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1175; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or BAE Systems (Operations) Limited's EASA Design
Organization Approval (DOA). If approved by the DOA,
[[Page 3353]]
the approval must include the DOA-authorized signature.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0100, dated June 3, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-0457.
(2) For service information identified in this AD, contact BAE
Systems (Operations) Limited, Customer Information Department,
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email
RApublications@baesystems.com; Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on January 13, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-01088 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P
