Airworthiness Directives; Airbus Helicopters, 2039-2042 [2018-00478]
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Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations
Issued in Renton, Washington, on January
9, 2018.
Victor Wicklund,
Manager, Transport Standards Branch, Policy
and Innovation Division, Aircraft
Certification Service.
telephone 425–227–2432; facsimile
425–227–1149.
SUPPLEMENTARY INFORMATION:
Background
On April 22, 2016, the Federal
Register published a document
designated as Docket No. FAA–2015–
4279, Final Special Conditions No. 25–
612–SC (81 FR 23573). The document
issued special conditions pertaining to
the installation of non-rechargeable
lithium batteries in Gulfstream GVI
airplanes. As published, the document
contained an error in a title 14, Code of
Federal Regulations (14 CFR) section
citation in two locations in the final
special conditions document. These
citations inadvertently referred to the
wrong amendment level for the
certification basis of the various
Gulfstream GVI airplanes. Therefore, we
have corrected these special conditions
to include the correct citations and
amendment levels that apply to
certification bases applicable to
airplanes with non-rechargeable
lithium-ion battery installations.
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Correction
In the final special conditions
document (FR Doc. 2016–09311 Filed
4–21–16; 8:45 a.m.), published on April
22, 2016 (81 FR 23573), make the
following corrections.
1. On page 23574, second column,
change the following paragraph:
These special conditions apply to all
non-rechargeable lithium battery
installations in lieu of § 25.1353(b)(1)
through (b)(4) at Amendment 25–113.
Sections 25.1353(b)(1) through (b)(4) at
Amendment 25–113 remain in effect for
other battery installations.
To read:
These special conditions apply to all
non-rechargeable lithium battery
installations in lieu of § 25.1353(b)(1)
through (4) at Amendment 25–123 or
§ 25.1353(c)(1) through (4) at earlier
amendments. Those regulations remain
in effect for other battery installations.
2. On page 23577, third column,
change the following paragraph:
In lieu of § 25.1353(b)(1) through
(b)(4) at Amendment 25–113, each nonrechargeable lithium battery installation
must:
To read:
In lieu of § 25.1353(b)(1) through (4)
at Amendment 25–123, or
§ 25.1353(c)(1) through (4) at earlier
amendments, each non-rechargeable
lithium battery installation must:
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[FR Doc. 2018–00547 Filed 1–12–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0826; Product
Identifier 2016–SW–084–AD; Amendment
39–19153; AD 2018–01–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2015–22–
53 for Airbus Helicopters Model
AS350B3 helicopters. AD 2015–22–53
required revising the rotorcraft flight
manual (RFM) to perform the yaw load
compensator check after rotor shutdown and to state that the yaw servo
hydraulic switch must be in the ‘‘ON’’
position before taking off. Since we
issued AD 2015–22–53, Airbus
Helicopters developed a modification of
the ACCU TST switch. This new AD
retains the requirements of AD 2015–
22–53 and requires modifying the yaw
servo hydraulic switch (collective
switch) and replacing the ACCU TST
button. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD is effective February 20,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 20, 2018.
ADDRESSES: For Airbus Helicopters
service information identified in this
final rule, contact Airbus Helicopters,
2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641–0000 or
(800) 232–0323; fax (972) 641–3775; or
at https://www.helicopters.airbus.com/
website/en/ref/Technical-Support_
73.html. You may view this referenced
service information at the FAA, Office
of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room
6N–321, Fort Worth, TX 76177. It is also
available on the internet at https://
www.regulations.gov by searching for
SUMMARY:
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2039
and locating Docket No. FAA–2017–
0826.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov in Docket No.
FAA–2017–0826; 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 European
Aviation Safety Agency (EASA) AD, any
incorporated-by-reference information,
the economic evaluation, any comments
received, and other information. The
address for the Docket Office (phone:
800–647–5527) is Document
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:
George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
george.schwab@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2015–22–53,
Amendment 39–18331 (80 FR 74982,
December 1, 2015) and add a new AD.
AD 2015–22–53 applied to Airbus
Helicopters Model AS350B3 helicopters
with a dual hydraulic system installed.
AD 2015–22–53 required revising the
pre-flight and post-flight procedures in
the RFM to perform the yaw load
compensator check (ACCU TST switch)
after rotor shut-down instead of during
preflight procedures and to state that the
yaw servo hydraulic switch (collective
switch) must be in the ‘‘ON’’ (forward)
position before taking off.
The NPRM published in the Federal
Register on September 8, 2017 (82 FR
42487). The NPRM was prompted by
AD No. 2016–0220, dated November 4,
2016, issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition for Airbus Helicopters
Model AS 350 B3 helicopters. EASA
advises that further analysis resulted in
the recognition that a pilot could forget
to activate a switch despite the RFM
changes and that altering the bistable
push button (push-on, push-off) ACCU
TST switch is necessary.
Accordingly, the NPRM proposed to
retain the requirements of AD 2015–22–
53 and also proposed to require, within
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Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations
350 hours time-in-service, installing a
timer relay for the yaw servo hydraulic
switch, installing an additional light on
the caution and warning panel, and
replacing the bistable ACCU TST button
with a monostable button. The proposed
requirements were intended to prevent
takeoff without hydraulic pressure in
the tail rotor (T/R) hydraulic system,
loss of T/R flight control, and
subsequent loss of control of the
helicopter.
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Comments
After our NPRM was published, we
received comments from two
commenters.
Requests
The National Transportation Safety
Board (NTSB) requested that the AD
address the need for an alert when there
is insufficient pressure in the T/R
hydraulic system, which results in
increased pedal loads. In support of this
request, the NTSB stated that, for at
least four events it investigated in which
the yaw servo hydraulic switch was
likely not returned to its correct position
before takeoff, a salient alert could have
cued the pilots of insufficient T/R
hydraulic pressure.
We partially agree. We agree that an
aural and visual alert to the pilot to
indicate loss of T/R hydraulic pressure
would address this unsafe condition.
However, Airbus Helicopters has not
developed an alteration that provides
such an alert. The FAA has determined
the requirements proposed by the
NPRM are appropriate to address this
unsafe condition at this time. Should an
aural and visual alert to the pilot to
indicate loss of T/R hydraulic pressure
be developed and approved, we might
consider additional rulemaking at that
time. We did not change the AD based
on this comment.
The NTSB also requested that we
eliminate the requirement to move the
yaw load compensator check (ACCU
TST switch) to post-flight procedures
instead of preflight procedures. In
support of this request, the NTSB stated
that performing this check post-flight
does not ensure the yaw load
compensator will remain functional for
the next flight.
We disagree. We determined that
requiring this check post-flight with the
RFM procedure to have the yaw servo
hydraulic switch in the ‘‘ON’’ position
before takeoff, along with the alterations
to the yaw servo hydraulic switch and
replacement of the ACCU TST button,
reduces the risk of takeoff with the
switch in the incorrect position to an
acceptable level. We did not change the
AD based on this comment.
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Eagle Copters requested we change
the AD to address helicopters that have
replaced the factory console with a
Geneva Aviation P122 or P132 electrical
console under Eagle Copters USA, Inc.
Supplemental Type Certificate No.
SH4747NM. In support of this request,
Eagle Copters noted that operators of
these helicopters will need to request an
Alternative Method of Compliance to
comply with the AD, because the Airbus
Helicopters service information required
for replacing the bistable ACCU TST
button does not apply to these
helicopters. Eagle Copters proposed
adding a requirement to the AD to
replace the HYD TEST/ACCU TEST
ESN–11 switch on the console from the
locking bistable toggle switch to a
locking momentary (monostable) toggle
switch part number (P/N) MS24658–
16F.
We agree. We revised the AD to
require helicopters with a P122 or P132
electrical console installed to replace
the bistable ACCU TEST switch (which
may be marked ‘‘HYD TEST’’) with
monostable toggle switch P/N
MS24658–16F.
FAA’s Determination
We have reviewed the relevant
information and determined that an
unsafe condition exists and is likely to
exist or develop on other helicopters of
the same type design and that air safety
and the public interest require adopting
the AD requirements as proposed with
the change previously described. This
change is consistent with the intent of
the proposals in the NPRM and will not
increase the economic burden on any
operator nor increase the scope of the
AD.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Helicopters
Service Bulletin (SB) No. AS350–
67.00.64, Revision 0, dated February 25,
2015. This service information specifies
procedures to install a timer relay and
an additional indicator light on the
caution and warning panel. This
modification provides an ‘‘OFF’’ status
indication of the yaw servo hydraulic
switch by flashing a newly installed
‘‘HYD2’’ indicator light on the caution
and warning panel. Airbus Helicopters
identifies performance of this SB as
modification 074622. This modification
was available when AD 2015–22–53 was
issued; however, it was determined
unnecessary to address the unsafe
condition at that time.
We also reviewed Airbus Helicopters
SB No. AS350–67.00.65, Revision 0,
dated August 25, 2016. This service
information specifies procedures to
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replace the bistable push button ACCU
TST switch with a monostable push
button switch. Airbus Helicopters
identifies performance of this SB as
modification 074719.
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.
Other Related Service Information
We reviewed Airbus Helicopters SB
No. AS350–67.00.66, Revision 1, dated
October 22, 2015. This service
information specifies inserting specific
pages of the SB into the rotorcraft flight
manual. These pages revise the preflight
and post-flight hydraulic checks by
moving the T/R yaw load compensator
check from preflight to post-flight.
These pages also revise terminology
within the flight manuals for the
different engine configurations.
Costs of Compliance
We estimate that this AD affects 86
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
Labor costs are estimated at $85 per
work-hour.
Revising an RFM would take about
0.5 work-hour for a cost of $43 per
helicopter and $3,698 for the U.S. fleet.
Installing a timer relay for the yaw servo
hydraulic switch and an indicator light
would take about 9 work-hours and
parts would cost about $2,224.
Replacing the ACCU TST button would
take about 1 work-hour and parts would
cost about $2,244.
Based on these figures, we estimate a
total cost of $5,361 per helicopter and
$461,046 for the U.S. fleet.
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
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Federal Register / Vol. 83, No. 10 / Tuesday, January 16, 2018 / Rules and Regulations
products identified in this rulemaking
action.
result in loss of T/R flight control and
subsequent loss of control of the helicopter.
Regulatory Findings
We have 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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska to the extent that a regulatory,
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.
(c) Affected ADs
This AD supersedes AD 2015–22–53,
Amendment 39–18331 (80 FR 74982,
December 1, 2015).
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
removing Airworthiness Directive (AD)
2015–22–53, Amendment 39–18331 (80
FR 74982, December 1, 2015), and
adding the following new AD:
■
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2018–01–12 Airbus Helicopters:
Amendment 39–19153; Docket No.
FAA–2017–0826; Product Identifier
2016–SW–084–AD.
(a) Applicability
This AD applies to Model AS350B3
helicopters with a dual hydraulic system
installed, certificated in any category.
Note 1 to paragraph (a) of this AD: The
dual hydraulic system for Model AS350B3
helicopters is referred to as Airbus
modification OP 3082 or OP 3346.
(b) Unsafe Condition
This AD defines the unsafe condition as
lack of hydraulic pressure in a tail rotor
(T/R) hydraulic system. This condition could
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(d) Effective Date
This AD becomes effective February 20,
2018.
(e) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(f) Required Actions
(1) Before further flight, insert a copy of
this AD into the rotorcraft flight manual,
Section 4 Normal Operating Procedures, or
make pen and ink changes to the preflight
and post-flight procedures as follows:
(i) Stop performing the yaw load
compensator check (ACCU TST switch)
during preflight procedures, and instead
perform the yaw load compensator check
during post-flight procedures after rotor shutdown.
(ii) The yaw servo hydraulic switch
(collective switch) must be in the ‘‘ON’’
(forward) position before takeoff.
Note 2 to paragraph (f)(1)(ii) of this AD:
The yaw servo hydraulic switch is also called
the hydraulic pressure switch or hydraulic
cut off switch in various Airbus Helicopters
rotorcraft flight manuals.
(2) Within 350 hours time-in-service:
(i) Install a timer relay for the yaw servo
hydraulic switch (collective switch) by
following the Accomplishment Instructions,
paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3,
3.B.2.b.4, 3.B.2.b.5, or 3.B.2.b.6, as applicable
to the configuration of your helicopter, of
Airbus Helicopters Service Bulletin (SB) No.
AS350–67.00.64, Revision 0, dated February
25, 2015 (AS350–67.00.64). If your helicopter
has an automatic pilot system, also comply
with paragraph 3.B.2.b.7 of AS350–67.00.64.
(ii) Install an indicator light on the caution
and warning panel by following the
Accomplishment Instructions, paragraph
3.B.2.c.1 or 3.B.2.c.2, as applicable to the
configuration of your helicopter, of AS350–
67.00.64.
(iii) For helicopters with a Geneva Aviation
P122 or P132 electrical console installed,
replace the ESN–11 HYD TEST (ACCU TST)
switch with a monostable toggle switch part
number MS24658–16F.
(iv) For helicopters without a Geneva
Aviation P122 or P132 electrical console
installed, replace the bistable ACCU TST
button on the control panel with a
monostable button as depicted in Figure 1 or
Figure 3, as applicable to the configuration of
your helicopter, of Airbus Helicopters SB No.
AS350–67.00.65, Revision 0, dated August
25, 2016.
(3) After the effective date of this AD, do
not install a bistable ACCU TST button on
any helicopter.
(g) Special Flight Permits
A special flight permit may be issued for
paragraph (f)(2) of this AD only.
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(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Section, Rotorcraft Standards Branch, FAA,
may approve AMOCs for this AD. Send your
proposal to: George Schwab, Aviation Safety
Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters SB No. AS350–
67.00.66, Revision 1, dated October 22, 2015,
which is not incorporated by reference,
contains additional information about the
subject of this AD. For service information
identified in this AD, contact Airbus
Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–0000
or (800) 232–0323; fax (972) 641–3775; or at
https://www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You may
view a copy of the service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2016–0220, dated November 4, 2016.
You may view the EASA AD on the internet
at https://www.regulations.gov in Docket No.
FAA–2017–0826.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 2910, Main Hydraulic System.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Airbus Helicopters Service Bulletin No.
AS350–67.00.64, Revision 0, dated February
25, 2015.
(ii) Airbus Helicopters Service Bulletin No.
AS350–67.00.65, Revision 0, dated August
25, 2016.
(3) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://www.helicopters.
airbus.com/website/en/ref/TechnicalSupport_73.html.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call (817) 222–5110.
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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 Fort Worth, Texas, on January 8,
2018.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2018–00478 Filed 1–12–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0514; Product
Identifier 2016–NM–206–AD; Amendment
39–19148; AD 2018–01–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 B4–600, B4–600R,
and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes) airplanes.
This AD was prompted by a revision of
certain airworthiness limitation item
(ALI) documents, which require more
restrictive maintenance requirements
and airworthiness limitations. This AD
requires revising the maintenance or
inspection program, as applicable, to
incorporate new maintenance
requirements and airworthiness
limitations. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective February 20,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 20, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAW, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@
airbus.com; internet https://
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DATES:
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www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 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–2017–
0514.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0514; 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: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW, Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–
1149.
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 all Airbus Model A300 B4–600,
B4–600R, and F4–600R series airplanes,
and Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). The NPRM
published in the Federal Register on
June 2, 2017 (82 FR 25552) (‘‘the
NPRM’’).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0218,
dated November 2, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes). The MCAI
states:
The airworthiness limitations for Airbus
A300–600 aeroplanes, which are approved by
EASA, are currently defined and published
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in the Airbus A300–600 Airworthiness
Limitations Section (ALS) document(s).
These instructions have been identified as
mandatory actions for continued
airworthiness.
Failure to accomplish these instructions
could result in an unsafe condition.
EASA previously issued [EASA] AD 2014–
0124 (later revised) [which includes actions
for Airbus A300–600 airplanes; those actions
are included in FAA AD 2013–13–13,
Amendment 39–17501 (79 FR 48957, August
19, 2014) (‘‘AD 2013–13–13’’)], requiring the
actions described in Airbus A300–600
Airworthiness Limitation Item (ALI)
Document at issue 13 and Temporary
Revision (TR) 13.1.
Since EASA AD 2014–0124R1 was issued,
Airbus replaced A300–600 ALI Document
issue 13, with A300–600 ALS Part 2 Revision
01 and then published the A300–600 ALS
Part 2 Variation 1.1 and Variation 1.2, to
introduce more restrictive maintenance
requirements and/or airworthiness
limitations.
A300–600 ALS Part 2 Variation 1.1 also
includes ALI 571067 and ALI 571068,
superseding Service Bulletin A300–53–6154,
which is referenced in EASA AD 2006–0257
[which corresponds to FAA AD 2007–22–05,
Amendment 39–15241 (72 FR 60236, October
24, 2007) (‘‘AD 2007–22–05’’)].
For the reasons described above, this
[EASA] AD retains part of the requirements
of EASA AD 2014–0124R1, which will be
superseded, and requires accomplishment of
the actions specified in Airbus A300–600
ALS Part 2 Revision 01, and ALS Part 2
Variation 1.1 and ALS Part 2 Variation 1.2
(hereafter collectively referred to as ‘the ALS’
in this [EASA] AD), and supersedes EASA
AD 2006–0257. The remaining requirements
of EASA AD 2014–0124R1 are retained in AD
2016–0217, applicable to A310 aeroplanes,
published at the same time as this [EASA]
AD.
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–2017–
0514.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response. FedEx generally supported the
NPRM.
Request To Provide an Additional
Compliance Time Grace Period
United Parcel Service (UPS) requested
that the compliance time specified in
paragraph (g) of the NPRM be revised to
add an additional grace period. UPS
pointed out that there are several new
or revised tasks with relatively low
compliance time thresholds that would
lead to short lead times on
accomplishing those tasks after the
effective date of the AD. UPS referenced
the compliance time required in AD
E:\FR\FM\16JAR1.SGM
16JAR1
]]>Agencies
[Federal Register Volume 83, Number 10 (Tuesday, January 16, 2018)]
[Rules and Regulations]
[Pages 2039-2042]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-00478]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0826; Product Identifier 2016-SW-084-AD; Amendment
39-19153; AD 2018-01-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2015-22-53 for
Airbus Helicopters Model AS350B3 helicopters. AD 2015-22-53 required
revising the rotorcraft flight manual (RFM) to perform the yaw load
compensator check after rotor shut-down and to state that the yaw servo
hydraulic switch must be in the ``ON'' position before taking off.
Since we issued AD 2015-22-53, Airbus Helicopters developed a
modification of the ACCU TST switch. This new AD retains the
requirements of AD 2015-22-53 and requires modifying the yaw servo
hydraulic switch (collective switch) and replacing the ACCU TST button.
The actions of this AD are intended to address an unsafe condition on
these products.
DATES: This AD is effective February 20, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 20,
2018.
ADDRESSES: For Airbus Helicopters service information identified in
this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may view this referenced service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. It is
also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2017-0826.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2017-0826; 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
European Aviation Safety Agency (EASA) AD, any incorporated-by-
reference information, the economic evaluation, any comments received,
and other information. The address for the Docket Office (phone: 800-
647-5527) is Document 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: George Schwab, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2015-22-53, Amendment 39-18331 (80 FR 74982,
December 1, 2015) and add a new AD. AD 2015-22-53 applied to Airbus
Helicopters Model AS350B3 helicopters with a dual hydraulic system
installed. AD 2015-22-53 required revising the pre-flight and post-
flight procedures in the RFM to perform the yaw load compensator check
(ACCU TST switch) after rotor shut-down instead of during preflight
procedures and to state that the yaw servo hydraulic switch (collective
switch) must be in the ``ON'' (forward) position before taking off.
The NPRM published in the Federal Register on September 8, 2017 (82
FR 42487). The NPRM was prompted by AD No. 2016-0220, dated November 4,
2016, issued by EASA, which is the Technical Agent for the Member
States of the European Union, to correct an unsafe condition for Airbus
Helicopters Model AS 350 B3 helicopters. EASA advises that further
analysis resulted in the recognition that a pilot could forget to
activate a switch despite the RFM changes and that altering the
bistable push button (push-on, push-off) ACCU TST switch is necessary.
Accordingly, the NPRM proposed to retain the requirements of AD
2015-22-53 and also proposed to require, within
[[Page 2040]]
350 hours time-in-service, installing a timer relay for the yaw servo
hydraulic switch, installing an additional light on the caution and
warning panel, and replacing the bistable ACCU TST button with a
monostable button. The proposed requirements were intended to prevent
takeoff without hydraulic pressure in the tail rotor (T/R) hydraulic
system, loss of T/R flight control, and subsequent loss of control of
the helicopter.
Comments
After our NPRM was published, we received comments from two
commenters.
Requests
The National Transportation Safety Board (NTSB) requested that the
AD address the need for an alert when there is insufficient pressure in
the T/R hydraulic system, which results in increased pedal loads. In
support of this request, the NTSB stated that, for at least four events
it investigated in which the yaw servo hydraulic switch was likely not
returned to its correct position before takeoff, a salient alert could
have cued the pilots of insufficient T/R hydraulic pressure.
We partially agree. We agree that an aural and visual alert to the
pilot to indicate loss of T/R hydraulic pressure would address this
unsafe condition. However, Airbus Helicopters has not developed an
alteration that provides such an alert. The FAA has determined the
requirements proposed by the NPRM are appropriate to address this
unsafe condition at this time. Should an aural and visual alert to the
pilot to indicate loss of T/R hydraulic pressure be developed and
approved, we might consider additional rulemaking at that time. We did
not change the AD based on this comment.
The NTSB also requested that we eliminate the requirement to move
the yaw load compensator check (ACCU TST switch) to post-flight
procedures instead of preflight procedures. In support of this request,
the NTSB stated that performing this check post-flight does not ensure
the yaw load compensator will remain functional for the next flight.
We disagree. We determined that requiring this check post-flight
with the RFM procedure to have the yaw servo hydraulic switch in the
``ON'' position before takeoff, along with the alterations to the yaw
servo hydraulic switch and replacement of the ACCU TST button, reduces
the risk of takeoff with the switch in the incorrect position to an
acceptable level. We did not change the AD based on this comment.
Eagle Copters requested we change the AD to address helicopters
that have replaced the factory console with a Geneva Aviation P122 or
P132 electrical console under Eagle Copters USA, Inc. Supplemental Type
Certificate No. SH4747NM. In support of this request, Eagle Copters
noted that operators of these helicopters will need to request an
Alternative Method of Compliance to comply with the AD, because the
Airbus Helicopters service information required for replacing the
bistable ACCU TST button does not apply to these helicopters. Eagle
Copters proposed adding a requirement to the AD to replace the HYD
TEST/ACCU TEST ESN-11 switch on the console from the locking bistable
toggle switch to a locking momentary (monostable) toggle switch part
number (P/N) MS24658-16F.
We agree. We revised the AD to require helicopters with a P122 or
P132 electrical console installed to replace the bistable ACCU TEST
switch (which may be marked ``HYD TEST'') with monostable toggle switch
P/N MS24658-16F.
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type design and that air safety and the public
interest require adopting the AD requirements as proposed with the
change previously described. This change is consistent with the intent
of the proposals in the NPRM and will not increase the economic burden
on any operator nor increase the scope of the AD.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Helicopters Service Bulletin (SB) No. AS350-
67.00.64, Revision 0, dated February 25, 2015. This service information
specifies procedures to install a timer relay and an additional
indicator light on the caution and warning panel. This modification
provides an ``OFF'' status indication of the yaw servo hydraulic switch
by flashing a newly installed ``HYD2'' indicator light on the caution
and warning panel. Airbus Helicopters identifies performance of this SB
as modification 074622. This modification was available when AD 2015-
22-53 was issued; however, it was determined unnecessary to address the
unsafe condition at that time.
We also reviewed Airbus Helicopters SB No. AS350-67.00.65, Revision
0, dated August 25, 2016. This service information specifies procedures
to replace the bistable push button ACCU TST switch with a monostable
push button switch. Airbus Helicopters identifies performance of this
SB as modification 074719.
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.
Other Related Service Information
We reviewed Airbus Helicopters SB No. AS350-67.00.66, Revision 1,
dated October 22, 2015. This service information specifies inserting
specific pages of the SB into the rotorcraft flight manual. These pages
revise the preflight and post-flight hydraulic checks by moving the T/R
yaw load compensator check from preflight to post-flight. These pages
also revise terminology within the flight manuals for the different
engine configurations.
Costs of Compliance
We estimate that this AD affects 86 helicopters of U.S. Registry.
We estimate that operators may incur the following costs in order to
comply with this AD. Labor costs are estimated at $85 per work-hour.
Revising an RFM would take about 0.5 work-hour for a cost of $43
per helicopter and $3,698 for the U.S. fleet. Installing a timer relay
for the yaw servo hydraulic switch and an indicator light would take
about 9 work-hours and parts would cost about $2,224. Replacing the
ACCU TST button would take about 1 work-hour and parts would cost about
$2,244.
Based on these figures, we estimate a total cost of $5,361 per
helicopter and $461,046 for the U.S. fleet.
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
[[Page 2041]]
products identified in this rulemaking action.
Regulatory Findings
We have 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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent
that a regulatory, 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)
2015-22-53, Amendment 39-18331 (80 FR 74982, December 1, 2015), and
adding the following new AD:
2018-01-12 Airbus Helicopters: Amendment 39-19153; Docket No. FAA-
2017-0826; Product Identifier 2016-SW-084-AD.
(a) Applicability
This AD applies to Model AS350B3 helicopters with a dual
hydraulic system installed, certificated in any category.
Note 1 to paragraph (a) of this AD: The dual hydraulic system
for Model AS350B3 helicopters is referred to as Airbus modification
OP 3082 or OP 3346.
(b) Unsafe Condition
This AD defines the unsafe condition as lack of hydraulic
pressure in a tail rotor (T/R) hydraulic system. This condition
could result in loss of T/R flight control and subsequent loss of
control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2015-22-53, Amendment 39-18331 (80 FR
74982, December 1, 2015).
(d) Effective Date
This AD becomes effective February 20, 2018.
(e) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(f) Required Actions
(1) Before further flight, insert a copy of this AD into the
rotorcraft flight manual, Section 4 Normal Operating Procedures, or
make pen and ink changes to the preflight and post-flight procedures
as follows:
(i) Stop performing the yaw load compensator check (ACCU TST
switch) during preflight procedures, and instead perform the yaw
load compensator check during post-flight procedures after rotor
shut-down.
(ii) The yaw servo hydraulic switch (collective switch) must be
in the ``ON'' (forward) position before takeoff.
Note 2 to paragraph (f)(1)(ii) of this AD: The yaw servo
hydraulic switch is also called the hydraulic pressure switch or
hydraulic cut off switch in various Airbus Helicopters rotorcraft
flight manuals.
(2) Within 350 hours time-in-service:
(i) Install a timer relay for the yaw servo hydraulic switch
(collective switch) by following the Accomplishment Instructions,
paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 3.B.2.b.4, 3.B.2.b.5, or
3.B.2.b.6, as applicable to the configuration of your helicopter, of
Airbus Helicopters Service Bulletin (SB) No. AS350-67.00.64,
Revision 0, dated February 25, 2015 (AS350-67.00.64). If your
helicopter has an automatic pilot system, also comply with paragraph
3.B.2.b.7 of AS350-67.00.64.
(ii) Install an indicator light on the caution and warning panel
by following the Accomplishment Instructions, paragraph 3.B.2.c.1 or
3.B.2.c.2, as applicable to the configuration of your helicopter, of
AS350-67.00.64.
(iii) For helicopters with a Geneva Aviation P122 or P132
electrical console installed, replace the ESN-11 HYD TEST (ACCU TST)
switch with a monostable toggle switch part number MS24658-16F.
(iv) For helicopters without a Geneva Aviation P122 or P132
electrical console installed, replace the bistable ACCU TST button
on the control panel with a monostable button as depicted in Figure
1 or Figure 3, as applicable to the configuration of your
helicopter, of Airbus Helicopters SB No. AS350-67.00.65, Revision 0,
dated August 25, 2016.
(3) After the effective date of this AD, do not install a
bistable ACCU TST button on any helicopter.
(g) Special Flight Permits
A special flight permit may be issued for paragraph (f)(2) of
this AD only.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
George Schwab, Aviation Safety Engineer, Safety Management Section,
Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth,
TX 76177; telephone (817) 222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(i) Additional Information
(1) Airbus Helicopters SB No. AS350-67.00.66, Revision 1, dated
October 22, 2015, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact Airbus Helicopters, 2701
N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or
(800) 232-0323; fax (972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
You may view a copy of the service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room
6N-321, Fort Worth, TX 76177.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2016-0220, dated November 4, 2016. You
may view the EASA AD on the internet at https://www.regulations.gov
in Docket No. FAA-2017-0826.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 2910, Main
Hydraulic System.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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) Airbus Helicopters Service Bulletin No. AS350-67.00.64,
Revision 0, dated February 25, 2015.
(ii) Airbus Helicopters Service Bulletin No. AS350-67.00.65,
Revision 0, dated August 25, 2016.
(3) For Airbus Helicopters service information identified in
this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972) 641-3775; or at https://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
[[Page 2042]]
(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 Fort Worth, Texas, on January 8, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2018-00478 Filed 1-12-18; 8:45 am]
BILLING CODE 4910-13-P
