Airworthiness Directives; BAE Systems (Operations) Limited Airplanes, 7-10 [2016-30412]
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Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Rules and Regulations
(h) Corrective Actions
If any defect (e.g., rifling, gouging, nicks, or
burrs, or excessive surface roughness) is
found in any fastener hole (other than
normally produced during a typical reaming
operation), during accomplishment of any
inspection (related investigative actions)
required by this AD, and Boeing Alert
Service Bulletin 767–53A0267, Revision 1,
dated August 4, 2016, specifies to contact
Boeing for repair instructions: Before further
flight, repair in accordance with the
procedures specified in paragraph (k) of this
AD.
(i) Exception to the Service Information
Where Boeing Alert Service Bulletin 767–
53A0267, Revision 1, dated August 4, 2016,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified time after the effective date of this
AD.
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(j) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 767–53A0267,
dated August 13, 2015; which is not
incorporated by reference in this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 (l) of this AD. Information may be
emailed to: 9–ANM-Seattle-ACO-AMOCRequests@faa.gov.
(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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or sub-step is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
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sub-step. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6447; fax: 425–
917–6590; email: wayne.lockett@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 767–
53A0267, Revision 1, dated August 4, 2016.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
November 25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–29678 Filed 12–30–16; 8:45 am]
BILLING CODE 4910–13–P
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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; Amendment
39–18751; AD 2016–25–25]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–11–
15 for all BAE Systems (Operations)
Limited Model 4101 airplanes. AD
2012–11–15 required a one-time
detailed inspection for cracks,
corrosion, and other defects of the rear
face of the wing rear spar, and repair if
necessary. This new AD requires
repetitive detailed inspections, and
repair if necessary. This AD was
prompted by new reports of cracking
found in the wing rear spar and
technical analysis results, which
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 address the unsafe
condition on these products.
DATES: This AD is effective February 7,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 7, 2017.
ADDRESSES: For service information
identified in this final rule, 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
0457.
SUMMARY:
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Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Rules and Regulations
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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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–11–15,
Amendment 39–17079 (77 FR 36127,
June 18, 2012) (‘‘AD 2012–11–15’’). AD
2012–11–15 applied to all BAE Systems
(Operations) Limited Model 4101
airplanes. The NPRM published in the
Federal Register on January 21, 2016
(81 FR 3350) (‘‘the NPRM’’). The NPRM
was prompted by new reports of
cracking found in the wing rear spar and
technical analysis results, which
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
NPRM proposed to require a one-time
detailed inspection for cracks,
corrosion, and other defects of the rear
face of the wing rear spar, and repair if
necessary. The NPRM also proposed to
require repetitive detailed inspections,
and repair if necessary. 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.
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
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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 occupants.
Prompted by these findings, EASA issued
AD 2011–0096 [which corresponds to FAA
AD 2012–11–15, Amendment 39–17079 (77
FR 36127, June 18, 2012)] to require a onetime [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 [EASA] 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.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Explanation of Change in This AD
The NPRM incorrectly referred to
Subject 57–00–00, Wings General, of
Chapter 57, Wings, of the BAE Systems
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(Operations) Limited Jetstream Series
4100 Structural Repair Manual (SRM),
Volume 1, Revision 32, dated October
15, 2014, for damage criteria and repair
instructions. We have revised this final
rule to refer to Chapter 57 of the SRM
instead of Subject 57–00–00.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed, except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
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 Chapter 57, Wings, of
the Jetstream Series 4100 SRM, Volume
1, Publication Ref. No. (Transmittal No.)
SA 4–4100/SRM/400, Revision 32,
dated October 15, 2014. Among other
actions, Chapter 57 describes damage
criteria and procedures for repairing the
wing structure.
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.
Costs of Compliance
We estimate that this AD affects 15
airplanes of U.S. registry.
We also estimate that it takes up to 25
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this 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 enables us to provide a cost
estimate 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:
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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.
2016–25–25 Bombardier: Amendment 39–
18751; Docket No. FAA–2016–0457;
Directorate Identifier 2015–NM–084–AD.
Regulatory Findings
(e) Reason
This AD was prompted by new reports of
cracking found in the wing rear spar and
technical analysis results, which 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.
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
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■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[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:
■
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(a) Effective Date
This AD is effective February 7, 2017.
(b) Affected ADs
This AD replaces AD 2012–11–15,
Amendment 39–17079 (77 FR 36127, June
18, 2012) (‘‘AD 2012–11–15’’).
(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.
(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
Chapter 57, Wings, of the Jetstream Series
4100 Structural Repair Manual (SRM),
Volume 1, Publication Ref. No. (Transmittal
No.) SA 4–4100/SRM/400, Revision 32, dated
October 15, 2014 (‘‘Chapter 57 of the SRM’’):
Before further flight, repair the affected area,
in accordance with the repair instructions of
Chapter 57 of the SRM.
(2) If any cracking, corrosion, or other
defect is found exceeding the criteria defined
in Chapter 57 of the SRM: 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).
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9
(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 EASA; or BAE Systems (Operations)
Limited’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(j) Related Information
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.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) BAE Systems Alert Service Bulletin J41–
A57–029, Revision 3, dated April 8, 2014.
(ii) Chapter 57, Wings, of the BAE Systems
(Operations) Limited Jetstream Series 4100
Structural Repair Manual, Volume 1,
Publication Ref. No. (Transmittal No.) SA 4–
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4100/SRM/400, Revision 32, dated October
15, 2014.
(3) 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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 6, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–30412 Filed 12–30–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8180; Directorate
Identifier 2016–NM–083–AD; Amendment
39–18760; AD 2016–26–02]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, Model CL–600–2D15
(Regional Jet Series 705) airplanes,
Model CL–600–2D24 (Regional Jet
Series 900) airplanes, and Model CL–
600–2E25 (Regional Jet Series 1000)
airplanes. This AD was prompted by a
determination that the protective
polyurethane tapes applied to the upper
surfaces of the aluminum and titanium
floor structural members may overhang
the profiles of the floor structural parts
and may allow fire propagation below
the floor structure. This AD requires an
inspection of the polyurethane
protective tapes installed on the floor
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SUMMARY:
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structure for excess tape or incorrect
tape installation, and corrective actions
if necessary. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective February 7,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 7, 2017.
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
Widebody Customer Response Center
North America toll-free telephone 1–
866–538–1247 or direct-dial telephone:
1–514–855–2999; fax: 514–855–7401;
email: ac.yul@aero.bombardier.com;
Internet: https://www.bombardier.com.
You may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
8180.
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–
8180; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone: 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Fabio Buttitta, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone: 516–228–7303;
fax: 516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc. Model
CL–600–2C10 (Regional Jet Series 700,
701, & 702) airplanes, Model CL–600–
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
2D15 (Regional Jet Series 705) airplanes,
Model CL–600–2D24 (Regional Jet
Series 900) airplanes, and Model CL–
600–2E25 (Regional Jet Series 1000)
airplanes. The NPRM published in the
Federal Register on July 28, 2016 (81 FR
49577) (‘‘the NPRM’’). The NPRM was
prompted by a determination that the
protective polyurethane tapes applied to
the upper surfaces of the aluminum and
titanium floor structural members may
not be trimmed properly, and on some
places may overhang the profiles of the
floor structural parts. Subsequent tests
revealed that the overhanging pieces of
tapes that are not bonded to the
structure do not meet the flammability
requirements and may allow fire
propagation below the floor structure.
The NPRM proposed to require an
inspection of the polyurethane
protective tapes installed on the floor
structure for excess tape or incorrect
tape installation, and corrective actions
if necessary. We are issuing this AD to
detect and correct overhanging pieces of
protective polyurethane tapes, which
are not bonded to the structure and do
not meet the flammability requirements;
this condition may allow fire
propagation below the floor structure.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2016–14, dated May 18, 2016
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.
Model CL–600–2C10 (Regional Jet
Series 700, 701, & 702) airplanes, Model
CL–600–2D15 (Regional Jet Series 705)
airplanes, Model CL–600–2D24
(Regional Jet Series 900) airplanes, and
Model CL–600–2E25 (Regional Jet Series
1000) airplanes. The MCAI states:
An inspection revealed that the protective
polyurethane tapes applied to the upper
surfaces of the aluminum and titanium floor
structural members installed on CRJ 700/900/
1000 aeroplanes may not be trimmed
properly and on some places may overhang
the profiles of the floor structural parts.
Subsequent tests revealed that the
overhanging pieces of tapes which are not
bonded to the structure, do not meet the
flammability requirements. If not corrected,
this condition may allow fire propagation
below the floor structure.
This [Canadian] AD was issued to mandate
the [detailed] inspection and removal of any
excessive pieces of overhanging tape [or
replacing incorrectly installed tape] found on
the floor structure.
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–
8180.
E:\FR\FM\03JAR1.SGM
03JAR1
]]>Agencies
[Federal Register Volume 82, Number 1 (Tuesday, January 3, 2017)]
[Rules and Regulations]
[Pages 7-10]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30412]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-0457; Directorate Identifier 2015-NM-084-AD;
Amendment 39-18751; AD 2016-25-25]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-11-15 for
all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2012-11-
15 required a one-time detailed inspection for cracks, corrosion, and
other defects of the rear face of the wing rear spar, and repair if
necessary. This new AD requires repetitive detailed inspections, and
repair if necessary. This AD was prompted by new reports of cracking
found in the wing rear spar and technical analysis results, which
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 address the unsafe
condition on these products.
DATES: This AD is effective February 7, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 7,
2017.
ADDRESSES: For service information identified in this final rule,
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. It is also
available on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2016-0457.
[[Page 8]]
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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-11-15, Amendment 39-17079 (77 FR 36127,
June 18, 2012) (``AD 2012-11-15''). AD 2012-11-15 applied to all BAE
Systems (Operations) Limited Model 4101 airplanes. The NPRM published
in the Federal Register on January 21, 2016 (81 FR 3350) (``the
NPRM''). The NPRM was prompted by new reports of cracking found in the
wing rear spar and technical analysis results, which 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
NPRM proposed to require a one-time detailed inspection for cracks,
corrosion, and other defects of the rear face of the wing rear spar,
and repair if necessary. The NPRM also proposed to require repetitive
detailed inspections, and repair if necessary. 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.
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 occupants.
Prompted by these findings, EASA issued 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
[EASA] 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Explanation of Change in This AD
The NPRM incorrectly referred to Subject 57-00-00, Wings General,
of Chapter 57, Wings, of the BAE Systems (Operations) Limited Jetstream
Series 4100 Structural Repair Manual (SRM), Volume 1, Revision 32,
dated October 15, 2014, for damage criteria and repair instructions. We
have revised this final rule to refer to Chapter 57 of the SRM instead
of Subject 57-00-00.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed, except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
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 Chapter 57, Wings,
of the Jetstream Series 4100 SRM, Volume 1, Publication Ref. No.
(Transmittal No.) SA 4-4100/SRM/400, Revision 32, dated October 15,
2014. Among other actions, Chapter 57 describes damage criteria and
procedures for repairing the wing structure.
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.
Costs of Compliance
We estimate that this AD affects 15 airplanes of U.S. registry.
We also estimate that it takes up to 25 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this 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 enables us to provide a
cost estimate 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:
[[Page 9]]
Aviation Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-11-15, Amendment 39-17079 (77 FR 36127, June 18, 2012), and adding
the following new AD:
2016-25-25 Bombardier: Amendment 39-18751; Docket No. FAA-2016-0457;
Directorate Identifier 2015-NM-084-AD.
(a) Effective Date
This AD is effective February 7, 2017.
(b) Affected ADs
This AD replaces AD 2012-11-15, Amendment 39-17079 (77 FR 36127,
June 18, 2012) (``AD 2012-11-15'').
(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, which 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 Chapter 57, Wings, of the Jetstream Series
4100 Structural Repair Manual (SRM), Volume 1, Publication Ref. No.
(Transmittal No.) SA 4-4100/SRM/400, Revision 32, dated October 15,
2014 (``Chapter 57 of the SRM''): Before further flight, repair the
affected area, in accordance with the repair instructions of Chapter
57 of the SRM.
(2) If any cracking, corrosion, or other defect is found
exceeding the criteria defined in Chapter 57 of the SRM: 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 EASA; or BAE Systems (Operations)
Limited's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(j) Related Information
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.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) BAE Systems Alert Service Bulletin J41-A57-029, Revision 3,
dated April 8, 2014.
(ii) Chapter 57, Wings, of the BAE Systems (Operations) Limited
Jetstream Series 4100 Structural Repair Manual, Volume 1,
Publication Ref. No. (Transmittal No.) SA 4-
[[Page 10]]
4100/SRM/400, Revision 32, dated October 15, 2014.
(3) 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 6, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30412 Filed 12-30-16; 8:45 am]
BILLING CODE 4910-13-P
