Airworthiness Directives; Airbus SAS Airplanes, 51819-51823 [2018-21963]
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Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations
of airworthiness; or within 7,500 flight hours
or 36 months, whichever occurs first, after
the most recent inspection was performed as
specified in AWL No. 28–AWL–101;
whichever is later.
(h) Additional Acceptable Wire Types and
Sleeving
As an option, when accomplishing the
actions required by paragraph (g) of this AD,
the changes specified in paragraphs (h)(1)
and (h)(2) of this AD are acceptable.
(1) Where AWL No. 28–AWL–05 identifies
wire types BMS 13–48, BMS 13–58, and BMS
13–60, the following wire types are
acceptable: MIL–W–22759/16, SAE
AS22759/16 (M22759/16), MIL–W–22759/32,
SAE AS22759/32 (M22759/32), MIL–W–
22759/34, SAE AS22759/34 (M22759/34),
MIL–W–22759/41, SAE AS22759/41
(M22759/41), MIL–W–22759/86, SAE
AS22759/86 (M22759/86), MIL–W–22759/87,
SAE AS22759/87 (M22759/87), MIL–W–
22759/92, and SAE AS22759/92 (M22759/
92); and MIL–C–27500 and NEMA WC 27500
cables constructed from these military or
SAE specification wire types, as applicable.
(2) Where AWL No. 28–AWL–05 identifies
TFE–2X Standard wall for wire sleeving, the
following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP,
or HM.
(i) No Alternative Actions, Intervals, and
Critical Design Configuration Control
Limitations (CDCCLs)
Except as provided in paragraph (h) of this
AD, after the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections),
intervals, and CDCCLs may be used unless
the actions, intervals, and CDCCLs are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (k) of this
AD.
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(j) Terminating Actions for Certain AD
Requirements
Accomplishment of the revision required
by paragraph (g) of this AD terminates the
requirements specified in paragraphs (j)(1)
through (j)(5) of this AD for that airplane:
(1) The revision required by paragraphs (h)
and (h)(1) of AD 2008–06–03.
(2) All requirements of AD 2008–10–10 R1.
(3) The revision required by paragraph (g)
of AD 2008–17–15.
(4) The revision required by paragraph (k)
of AD 2011–18–03.
(5) All requirements of AD 2013–15–17.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (l) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
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(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
Branch, 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.
(l) Related Information
For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3553;
email: takahisa.kobayashi@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 737–600/700/700C/800/900/
900ER Special Compliance Items/
Airworthiness Limitations, D626A001–9–04,
Revision January 2017.
(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 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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 Des Moines, Washington, on
September 19, 2018.
John P. Piccola,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–21971 Filed 10–12–18; 8:45 am]
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51819
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0358; Product
Identifier 2017–NM–142–AD; Amendment
39–19463; AD 2018–21–05]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A319–131, A319–
132, A319–133, A320–231, A320–232,
A320–233, A321–131, A321–231, and
A321–232 airplanes. This AD was
prompted by reports of fan cowl door
(FCD) losses during take-off. This AD
requires modification and reidentification, or replacement, of certain
FCDs, and installation of a placard in
the flight deck. We are issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective November
19, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 19, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EIAS, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; internet https://
www.airbus.com. You may view this
service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0358.
SUMMARY:
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–2018–
0358; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
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information. The address for Docket
Operations (phone: 800–647–5527) is
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:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
A319–131, A319–132, A319–133, A320–
231, A320–232, A320–233, A321–131,
A321–231, and A321–232 airplanes.
The NPRM published in the Federal
Register on May 4, 2018 (83 FR 19648).
The NPRM was prompted by reports of
FCD losses during take-off. The NPRM
proposed to require modification and reidentification, or replacement, of certain
FCDs, and installation of a placard in
the flight deck.
We are issuing this AD to address inflight loss of an FCD, which could result
in damage to the airplane and injury to
persons on the ground.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0178,
dated September 15, 2017 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A319–
131, A319–132, A319–133, A320–231,
A320–232, A320–233, A321–131, A321–
231, and A321–232 airplanes. The
MCAI states:
Fan Cowl Door (FCD) losses during take-off
were reported on Airbus A320 family
aeroplanes equipped with IAE [International
Aero Engines] V2500 engines. Investigations
confirmed that in all cases, the FCD were
opened prior to the flight and were not
correctly re-secured. During the pre-flight
inspection, it was not detected that the FCD
were not properly latched.
This condition, if not corrected, could lead
to in-flight loss of an FCD, possibly resulting
in damage to the aeroplane and/or injury to
persons on the ground.
EASA issued AD 2016–0053 [which
corresponds to FAA AD 2017–13–10,
Amendment 39–18940 (82 FR 29371, June
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29, 2017) (‘‘AD 2017–13–10’’)], requiring
modification of the FCD installed on affected
aeroplanes, and installation of a placard in
the cockpit, in accordance with the
instructions of Airbus Service Bulletin (SB)
A320–71–1069 (which in turns refers to
Goodrich SB V2500–NAC–71–0331 for FCD
modification and re-identification).
The monolithic FCDs, installed on
aeroplanes embodying Short Brothers
supplemental type certificate (STC)
10029547, are also affected by this potential
unsafe condition. Consequently, the STC
Holder, trading as Bombardier Short
Brothers, developed a modification, similar
to the one designed by Airbus, and issued SB
V25MFC–71–1003. The modification consists
of a new FCD front latch and keeper
assembly, having a specific key necessary to
un-latch the FCD. This key cannot be
removed unless the FCD front latch is safely
closed. The key, after removal, must be
stowed in the flight deck at a specific
location, as instructed in the applicable
Aircraft Maintenance Manual. The applicable
Flight Crew Operating Manual has been
amended accordingly. After modification, the
FCD is identified with a different Part
Number (P/N).
Mixed FCD installation can be found on
aeroplanes embodying [EASA] STC 10029547
(i.e., Monolithic FCD and standard
production non-Monolithic FCD). For
standard production non-Monolithic FCD,
Bombardier Short Brothers SB V25MFC–71–
1003 specifies to accomplish the instructions
of Goodrich SB V2500–NAC–71–0331, as
applicable.
For the reasons described above, this
[EASA] AD requires modification and reidentification of FCD, and installation of a
placard in the cockpit.
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–2018–
0358.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
The Air Line Pilots Association,
International (ALPA) supported the
NPRM.
Request To Extend Compliance Time
United Airlines (UAL) requested that
the compliance time stated in the
proposed AD be extended from 18
months to 36 months to match the
compliance time stated in AD 2017–13–
10. UAL noted that both the proposed
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AD and AD 2017–13–10 address the
same unsafe condition, but on different
FCDs. UAL added that it has a mixture
of FCD configurations, which will be
subject to different compliance times.
We disagree with the commenter’s
request to extend the compliance time
to 36 months. We based the compliance
time for this AD on the compliance time
required by the EASA MCAI, which was
determined by considering the urgency
associated with the unsafe condition,
the availability of required parts, and
the practical aspect of accomplishing
the required modification within a
timeframe that corresponds to the
normal scheduled maintenance for most
affected operators. In addition, the
manufacturer recommended that the
service bulletin be accomplished no
later than March 28, 2019. We have not
changed this AD in this regard.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this
final rule as proposed with the changes
described previously and minor
editorial changes. We have determined
that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
Bombardier Short Brothers, PLC has
issued Service Bulletin V25MFC–71–
1003, dated September 28, 2016. The
service information describes
procedures for installing modified
latches on the left and right engine
FCDs, and re-identifying the FCDs. 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 557
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
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51821
ESTIMATED COSTS
Action
Labor cost
Modification and re-identification (or replacement), and placard installation.
8 work-hours × $85 per hour = $680 .............
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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
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Regulatory Findings
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
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Parts cost
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:
■
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):
■
2018–21–05 Airbus SAS: Amendment 39–
19463; Docket No. FAA–2018–0358;
Product Identifier 2017–NM–142–AD.
(a) Effective Date
This AD is effective November 19, 2018.
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$1,500
Cost per
product
$2,180
Cost on U.S.
operators
$1,214,260
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model
A319–131, A319–132, A319–133, A320–231,
A320–232, A320–233, A321–131, A321–231,
and A321–232 airplanes, certificated in any
category, if modified by Bombardier Short
Brothers, PLC Supplemental Type Certificate
(STC) ST03076NY.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of fan
cowl door (FCD) losses during takeoff. We are
issuing this AD to prevent in-flight loss of an
FCD, which could result in damage to the
airplane and injury to persons on the ground.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Modification and Re-Identification of
FCDs
Within 18 months after the effective date
of this AD: Do the modification and reidentification specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Modify each left-hand (LH) and righthand (RH) FCD having a part number listed
as ‘‘Old Part Number’’ in table 1 to
paragraphs (g), (h), and (l) of this AD, in
accordance with the Accomplishment
Instructions of Bombardier Short Brothers
Service Bulletin V25MFC–71–1003, dated
September 28, 2016.
(2) Re-identify each modified FCD with the
part number listed as ‘‘New Part Number’’ in
table 1 to paragraphs (g), (h), and (l) of this
AD, in accordance with the Accomplishment
Instructions of Bombardier Short Brothers
Service Bulletin V25MFC–71–1003, dated
September 28, 2016.
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(h) Optional Compliance by Replacement or
Installation
(1) Replacement of the FCDs having a part
number listed as ‘‘Old Part Number’’ in table
1 to paragraphs (g), (h), and (l) of this AD,
with the FCDs having the corresponding part
number listed as ‘‘New Part Number’’ in table
1 to paragraphs (g), (h), and (l) of this AD,
is acceptable for compliance with the
requirements of paragraph (g) of this AD.
(2) Installation on an engine of a LH and
RH FCD having a part number approved after
the effective date of this AD is acceptable for
compliance with the requirements of
paragraph (g) of this AD for that engine only,
provided the conditions specified in
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD
are met.
(i) The part number is approved using a
method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Bombardier Short
Brothers, PLC’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(ii) The installation is accomplished using
a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Bombardier Short
Brothers, PLC’s EASA DOA. If approved by
the DOA, the approval must include the
DOA-authorized signature.
(i) Placard Installation
For airplanes on which Airbus SAS
modification 157718 has not been embodied
in production: Within 18 months after the
effective date of this AD, install a placard
that specifies the FCD keys stowage location
in the flight deck on the box located at the
bottom of the 120VU panel, or at the bottom
of the coat stowage, as applicable to airplane
configuration, using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Bombardier Short Brothers, PLC’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(j) Missing FCD Keys or Placard
Flights with one or both FCD keys missing
from the stowage location in the fight deck,
or with the placard (that specifies the FCD
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keys stowage location) missing or damaged,
are permitted for a period not to exceed 10
calendar days from the date of discovery.
(k) Alternate Location of FCD Keys and
Placard
As an option to paragraph (i) of this AD,
an alternate location for the key stowage in
the flight deck and installation of a placard
for identification of that stowage location are
permitted as specified in the operator’s FAAaccepted maintenance or inspection program,
provided the keys can be retrieved from that
flight deck location when needed and the
placard installation is done within 18 months
after the effective date of this AD.
(l) Parts Installation Prohibition
No person may install on any airplane an
FCD with a part number identified as ‘‘Old
Part Number’’ in table 1 to paragraphs (g), (h),
and (l) of this AD, after the time specified in
paragraph (l)(1) or (l)(2) of this AD, as
applicable.
(1) For any airplane with an installed FCD
having a part number identified as ‘‘Old Part
Number’’ in table 1 to paragraphs (g), (h), and
(l) of this AD: After modification of that
airplane as required by paragraph (g) of this
AD or as specified in paragraph (h) of this
AD.
(2) For any airplane without an installed
FCD having a part number identified as ‘‘Old
Part Number’’ in table 1 to paragraphs (g), (h),
and (l) of this AD: After the effective date of
this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
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principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Bombardier Short Brothers, PLC’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0178, dated September 15, 2017, 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–2018–0358.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Short Brothers Service
Bulletin V25MFC–71–1003, dated September
28, 2016.
(ii) Reserved.
(3) For service information identified in
this AD, contact Bombardier Short Brothers,
PLC, Airworthiness, P.O. Box 241, Airport
Road, Belfast, BT3 9DZ Northern Ireland;
telephone +44(0)2890–462469; fax
+44(0)2890–468444; email
michael.mulholland@aero.bombardier.com;
internet https://www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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(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 Des Moines, Washington, on
September 20, 2018.
John P. Piccola,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–21963 Filed 10–12–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0546; Product
Identifier 2017–NM–171–AD; Amendment
39–19461; AD 2018–21–03]
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 BD–700–1A10
and BD–700–1A11 airplanes. This AD
was prompted by reports of multiple inflight departures of the aft belly fairing
access panels. This AD requires
modification of the aft belly fairing
access panels. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective November
19, 2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 19, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Bombardier, Inc., 400 Coˆte Vertu Road
West, Dorval, Que´bec H4S 1Y9, Canada;
telephone 514–855–5000; fax 514 855–
7401; email thd.crj@
aero.bombardier.com; internet https://
www.bombardier.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0546.
khammond on DSK30JT082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:29 Oct 12, 2018
Jkt 247001
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–2018–
0546; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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:
Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA,
New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7330; fax
516–794–5531; email 9-avs-nyaco-cos@
faa.gov.
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
BD–700–1A10 and BD–700–1A11
airplanes. The NPRM published in the
Federal Register on June 20, 2018 (83
FR 28553). The NPRM was prompted by
reports of multiple in-flight departures
of the aft belly fairing access panels. The
NPRM proposed to require modification
of the aft belly fairing access panels.
We are issuing this AD to address inflight departures of the aft belly fairing
access panels, which could result in
runway hazards or hazards to people on
the ground.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian AD
CF–2017–31, dated September 22, 2017
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Bombardier, Inc.,
Model BD–700–1A10 and BD–700–
1A11 airplanes. The MCAI states:
There have been multiple in-service
occurrences where operators reported inflight departure of the aft belly fairing access
panels, 185CL and/or 186CR. There has been
no damage reported to the affected aircraft to
date, however departure of the panels in any
phase of flight could create runway hazards
or a hazard to persons and property on the
ground.
Bombardier Inc. has issued Service
Bulletins (SBs) to incorporate new selflocking nutplates with associated hardware
(retaining rings and studs) to improve
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
51823
fastener engagement. A bracket has also been
added to provide two additional panel
attachment points.
This [Canadian] AD requires the
incorporation of these design changes to
prevent departure of the two aft belly fairing
access panels in flight and the associated risk
on the ground.
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–2018–
0546.
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comment
received on the NPRM and the FAA’s
response to that comment.
Request To Include Additional
Document in Credit for Previous
Actions Paragraph
Bombardier requested that paragraph
(h) of the proposed AD, ‘‘Credit for
Previous Actions,’’ be revised to include
Bombardier Service Request for Product
Support Action 124026 (‘‘SRPSA
124026’’). The requester noted that
Canadian AD CF–2017–31, dated
September 22, 2017, included a
statement that incorporation of the
actions described in Bombardier SRPSA
124026 on an airplane satisfies the
intent of the Canadian AD. The
commenter also noted that Bombardier
SRPSA 124026 was utilized on a U.S.registered airplane having number
N211PB and serial number 9378.
We agree with the commenter’s
request for the reasons provided by the
commenter. We have added paragraph
(h)(2) to this AD to provide credit for
airplanes on which Bombardier SRPSA
124026 has been incorporated.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
previously, and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
E:\FR\FM\15OCR1.SGM
15OCR1
]]>Agencies
[Federal Register Volume 83, Number 199 (Monday, October 15, 2018)]
[Rules and Regulations]
[Pages 51819-51823]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-21963]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0358; Product Identifier 2017-NM-142-AD; Amendment
39-19463; AD 2018-21-05]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus SAS Model A319-131, A319-132, A319-133, A320-231, A320-232,
A320-233, A321-131, A321-231, and A321-232 airplanes. This AD was
prompted by reports of fan cowl door (FCD) losses during take-off. This
AD requires modification and re-identification, or replacement, of
certain FCDs, and installation of a placard in the flight deck. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective November 19, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 19,
2018.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet https://www.airbus.com. You may view this service information
at the FAA, Transport Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0358.
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-2018-
0358; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other
[[Page 51820]]
information. The address for Docket Operations (phone: 800-647-5527) is
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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
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 Airbus SAS Model
A319-131, A319-132, A319-133, A320-231, A320-232, A320-233, A321-131,
A321-231, and A321-232 airplanes. The NPRM published in the Federal
Register on May 4, 2018 (83 FR 19648). The NPRM was prompted by reports
of FCD losses during take-off. The NPRM proposed to require
modification and re-identification, or replacement, of certain FCDs,
and installation of a placard in the flight deck.
We are issuing this AD to address in-flight loss of an FCD, which
could result in damage to the airplane and injury to persons on the
ground.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0178, dated September 15, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus SAS Model A319-131,
A319-132, A319-133, A320-231, A320-232, A320-233, A321-131, A321-231,
and A321-232 airplanes. The MCAI states:
Fan Cowl Door (FCD) losses during take-off were reported on
Airbus A320 family aeroplanes equipped with IAE [International Aero
Engines] V2500 engines. Investigations confirmed that in all cases,
the FCD were opened prior to the flight and were not correctly re-
secured. During the pre-flight inspection, it was not detected that
the FCD were not properly latched.
This condition, if not corrected, could lead to in-flight loss
of an FCD, possibly resulting in damage to the aeroplane and/or
injury to persons on the ground.
EASA issued AD 2016-0053 [which corresponds to FAA AD 2017-13-
10, Amendment 39-18940 (82 FR 29371, June 29, 2017) (``AD 2017-13-
10'')], requiring modification of the FCD installed on affected
aeroplanes, and installation of a placard in the cockpit, in
accordance with the instructions of Airbus Service Bulletin (SB)
A320-71-1069 (which in turns refers to Goodrich SB V2500-NAC-71-0331
for FCD modification and re-identification).
The monolithic FCDs, installed on aeroplanes embodying Short
Brothers supplemental type certificate (STC) 10029547, are also
affected by this potential unsafe condition. Consequently, the STC
Holder, trading as Bombardier Short Brothers, developed a
modification, similar to the one designed by Airbus, and issued SB
V25MFC-71-1003. The modification consists of a new FCD front latch
and keeper assembly, having a specific key necessary to un-latch the
FCD. This key cannot be removed unless the FCD front latch is safely
closed. The key, after removal, must be stowed in the flight deck at
a specific location, as instructed in the applicable Aircraft
Maintenance Manual. The applicable Flight Crew Operating Manual has
been amended accordingly. After modification, the FCD is identified
with a different Part Number (P/N).
Mixed FCD installation can be found on aeroplanes embodying
[EASA] STC 10029547 (i.e., Monolithic FCD and standard production
non-Monolithic FCD). For standard production non-Monolithic FCD,
Bombardier Short Brothers SB V25MFC-71-1003 specifies to accomplish
the instructions of Goodrich SB V2500-NAC-71-0331, as applicable.
For the reasons described above, this [EASA] AD requires
modification and re-identification of FCD, and installation of a
placard in the cockpit.
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-2018-
0358.
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Support for the NPRM
The Air Line Pilots Association, International (ALPA) supported the
NPRM.
Request To Extend Compliance Time
United Airlines (UAL) requested that the compliance time stated in
the proposed AD be extended from 18 months to 36 months to match the
compliance time stated in AD 2017-13-10. UAL noted that both the
proposed AD and AD 2017-13-10 address the same unsafe condition, but on
different FCDs. UAL added that it has a mixture of FCD configurations,
which will be subject to different compliance times.
We disagree with the commenter's request to extend the compliance
time to 36 months. We based the compliance time for this AD on the
compliance time required by the EASA MCAI, which was determined by
considering the urgency associated with the unsafe condition, the
availability of required parts, and the practical aspect of
accomplishing the required modification within a timeframe that
corresponds to the normal scheduled maintenance for most affected
operators. In addition, the manufacturer recommended that the service
bulletin be accomplished no later than March 28, 2019. We have not
changed this AD in this regard.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this final rule as proposed with
the changes described previously and minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Bombardier Short Brothers, PLC has issued Service Bulletin V25MFC-
71-1003, dated September 28, 2016. The service information describes
procedures for installing modified latches on the left and right engine
FCDs, and re-identifying the FCDs. 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 557 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
[[Page 51821]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification (or 8 work-hours x $85 per $1,500 $2,180 $1,214,260
replacement), and placard hour = $680.
installation.
----------------------------------------------------------------------------------------------------------------
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.
Regulatory Findings
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 adding the following new airworthiness
directive (AD):
2018-21-05 Airbus SAS: Amendment 39-19463; Docket No. FAA-2018-0358;
Product Identifier 2017-NM-142-AD.
(a) Effective Date
This AD is effective November 19, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model A319-131, A319-132, A319-
133, A320-231, A320-232, A320-233, A321-131, A321-231, and A321-232
airplanes, certificated in any category, if modified by Bombardier
Short Brothers, PLC Supplemental Type Certificate (STC) ST03076NY.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of fan cowl door (FCD) losses
during takeoff. We are issuing this AD to prevent in-flight loss of
an FCD, which could result in damage to the airplane and injury to
persons on the ground.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification and Re-Identification of FCDs
Within 18 months after the effective date of this AD: Do the
modification and re-identification specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Modify each left-hand (LH) and right-hand (RH) FCD having a
part number listed as ``Old Part Number'' in table 1 to paragraphs
(g), (h), and (l) of this AD, in accordance with the Accomplishment
Instructions of Bombardier Short Brothers Service Bulletin V25MFC-
71-1003, dated September 28, 2016.
(2) Re-identify each modified FCD with the part number listed as
``New Part Number'' in table 1 to paragraphs (g), (h), and (l) of
this AD, in accordance with the Accomplishment Instructions of
Bombardier Short Brothers Service Bulletin V25MFC-71-1003, dated
September 28, 2016.
[[Page 51822]]
[GRAPHIC] [TIFF OMITTED] TR15OC18.000
(h) Optional Compliance by Replacement or Installation
(1) Replacement of the FCDs having a part number listed as ``Old
Part Number'' in table 1 to paragraphs (g), (h), and (l) of this AD,
with the FCDs having the corresponding part number listed as ``New
Part Number'' in table 1 to paragraphs (g), (h), and (l) of this AD,
is acceptable for compliance with the requirements of paragraph (g)
of this AD.
(2) Installation on an engine of a LH and RH FCD having a part
number approved after the effective date of this AD is acceptable
for compliance with the requirements of paragraph (g) of this AD for
that engine only, provided the conditions specified in paragraphs
(h)(2)(i) and (h)(2)(ii) of this AD are met.
(i) The part number is approved using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
the European Aviation Safety Agency (EASA); or Bombardier Short
Brothers, PLC's EASA Design Organization Approval (DOA). If approved
by the DOA, the approval must include the DOA-authorized signature.
(ii) The installation is accomplished using a method approved by
the Manager, International Section, Transport Standards Branch, FAA;
or EASA; or Bombardier Short Brothers, PLC's EASA DOA. If approved
by the DOA, the approval must include the DOA-authorized signature.
(i) Placard Installation
For airplanes on which Airbus SAS modification 157718 has not
been embodied in production: Within 18 months after the effective
date of this AD, install a placard that specifies the FCD keys
stowage location in the flight deck on the box located at the bottom
of the 120VU panel, or at the bottom of the coat stowage, as
applicable to airplane configuration, using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Bombardier Short Brothers, PLC's EASA DOA. If approved by
the DOA, the approval must include the DOA-authorized signature.
(j) Missing FCD Keys or Placard
Flights with one or both FCD keys missing from the stowage
location in the fight deck, or with the placard (that specifies the
FCD keys stowage location) missing or damaged, are permitted for a
period not to exceed 10 calendar days from the date of discovery.
(k) Alternate Location of FCD Keys and Placard
As an option to paragraph (i) of this AD, an alternate location
for the key stowage in the flight deck and installation of a placard
for identification of that stowage location are permitted as
specified in the operator's FAA-accepted maintenance or inspection
program, provided the keys can be retrieved from that flight deck
location when needed and the placard installation is done within 18
months after the effective date of this AD.
(l) Parts Installation Prohibition
No person may install on any airplane an FCD with a part number
identified as ``Old Part Number'' in table 1 to paragraphs (g), (h),
and (l) of this AD, after the time specified in paragraph (l)(1) or
(l)(2) of this AD, as applicable.
(1) For any airplane with an installed FCD having a part number
identified as ``Old Part Number'' in table 1 to paragraphs (g), (h),
and (l) of this AD: After modification of that airplane as required
by paragraph (g) of this AD or as specified in paragraph (h) of this
AD.
(2) For any airplane without an installed FCD having a part
number identified as ``Old Part Number'' in table 1 to paragraphs
(g), (h), and (l) of this AD: After the effective date of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (n)(2) of this AD. Information
may be emailed to: [email protected]. 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Bombardier
Short Brothers, PLC's EASA DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0178, dated September 15, 2017, 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-2018-0358.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Bombardier Short Brothers Service Bulletin V25MFC-71-1003,
dated September 28, 2016.
(ii) Reserved.
(3) For service information identified in this AD, contact
Bombardier Short Brothers, PLC, Airworthiness, P.O. Box 241, Airport
Road, Belfast, BT3 9DZ Northern Ireland; telephone +44(0)2890-
462469; fax +44(0)2890-468444; email
[email protected]; internet https://www.bombardier.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
[[Page 51823]]
(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 Des Moines, Washington, on September 20, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-21963 Filed 10-12-18; 8:45 am]
BILLING CODE 4910-13-P
