Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters, 94946-94949 [2016-30285]
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Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations
or the component history card or equivalent
record do not specify a life limit for the TT
strap, or if they specify a different life limit
than in paragraph (e)(1), do the following:
(i) Revise the Airworthiness Limitations
section of the applicable maintenance
manual or ICA by establishing a life limit of
25,000 flights or 10 years since date of
manufacture, whichever occurs first, for each
TT strap P/N 2604067 and P/N 117–14110 by
making pen-and-ink changes or by inserting
a copy of this AD into the Airworthiness
Limitations section of the maintenance
manual or the ICA. For purposes of this AD,
a flight would be counted anytime the
helicopter lifts off into the air and then lands
again regardless of the duration of the
landing and regardless of whether the engine
is shut down.
(ii) Create a component history card or
equivalent record for each TT strap P/N
2604067 and P/N 117–14110, if one does not
exist, and record a life limit of 25,000 flights
or 10 years since date of manufacture,
whichever occurs first.
(3) Remove from service each TT strap that
has reached or exceeded its life limit.
(f) Special Flight Permits
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller,
Senior Aviation Safety Engineer, Safety
Management Group, Rotorcraft Directorate,
FAA, 10101 Hillwood Pkwy, Fort Worth,
Texas 76177; telephone (817) 222–5110;
email 9-ASW-FTW-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.
asabaliauskas on DSK3SPTVN1PROD with RULES
(h) Additional Information
(1) Airbus Helicopters Alert Service
Bulletin ASB BO105LS–10A–013, Revision 0,
dated March 9, 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.airbushelicopters.com/techpub. You
may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101
Hillwood Pkwy, Room 6N–321, Fort Worth,
TX 76177.
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2015–0042, dated March 9, 2015. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2016–5247.
Jkt 241001
[FR Doc. 2016–30053 Filed 12–23–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–4278; Directorate
Identifier 2012–SW–022–AD; Amendment
39–18758; AD 2016–26–01]
RIN 2120–AA64
Airworthiness Directives;
AgustaWestland S.p.A. (Agusta)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
(g) Alternative Methods of Compliance
(AMOCs)
19:06 Dec 23, 2016
Issued in Fort Worth, Texas, on December
1, 2016.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
AGENCY:
Special flight permits are prohibited.
VerDate Sep<11>2014
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 6200 Main Rotor System.
We are adopting a new
airworthiness directive (AD) for certain
Agusta Model AB139 and AW139
helicopters. This AD requires
performing operational checks of both
hydraulic systems. This AD was
prompted by an assessment of the
hydraulic systems of the helicopter
following an accident. These actions are
intended to prevent the unsafe
condition on these products.
DATES: This AD is effective January 31,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of January 31, 2017.
ADDRESSES: For service information
identified in this final rule, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN:
Maurizio D’Angelo; telephone 39–0331–
664757; fax 39 0331–664680; or at
https://www.agustawestland.com/
technical-bulletins. You may review the
referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy, Room 6N–321, Fort Worth, TX
76177.
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–2016–
4278; or in person at the Docket
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Operations Office 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, the
economic evaluation, any incorporatedby-reference service information, any
comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Wilbanks, Aviation Safety Engineer,
Safety Management Group, Rotorcraft
Directorate, FAA, 10101 Hillwood
Parkway, Fort Worth, Texas 76177;
telephone (817) 222–5110; email
matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On March 11, 2016, at 81 FR 12838,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 by adding an AD that would apply
to certain serial-numbered Agusta
Model AB139 and AW139 helicopters.
The NPRM proposed to require, within
50 hours time-in-service (TIS),
performing operational tests of the
Number 1 and Number 2 hydraulic
systems power control modules (PCMs),
the tail shut-off valve, the PCM1 and
PCM2 flight control shut-off valves, and
the emergency landing gear shut-off
valve for correct functionality.
Depending on the results of the
operational checks, the NPRM proposed
to require replacing a PCM, the tail shutoff valve, a flight control shut-off valve,
the number 2 hydraulic control panel,
the number 1 hydraulic module, the
number 1 or number 2 PCM pressure
switch, or repairing the electrical
wiring. The proposed requirements
were intended to prevent loss of
hydraulic power to the flight controls
and subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
2011–0207, dated October 20, 2011 (AD
No. 2011–0207), issued by EASA, which
is the Technical Agent for the Member
States of the European Union, to correct
an unsafe condition for certain serialnumbered Agusta Model AB139 and
AW139 helicopters. EASA advises that
an accident involving a Model AW139
helicopter caused the tail rotor (T/R),
the T/R gearbox, and part of the fin to
detach from the aircraft, rupturing the
hydraulic lines and draining all of the
hydraulic fluid. According to EASA, an
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Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations
assessment of the helicopter’s hydraulic
systems following the accident revealed
that an operational check of the
hydraulic systems is necessary to ensure
its functionality. EASA advises that this
condition, if not corrected, could lead,
in the case of multiple failures, to loss
of hydraulic power and subsequent loss
of control of the helicopter. To address
this, EASA AD No. 2011–0207 requires,
within 50 flight hours or 2 months,
operational checks of the power control
modules and shutoff valves and
reporting the results to the
manufacturer.
Comments
After our NPRM (81 FR 12838, March
11, 2016) was published, we received
comments from one commenter.
Request
The commenter requested we not
adopt the proposed AD, as it is
unnecessary. The commenter stated that
following the release of EASA AD No.
2011–0207 and Agusta Bollettino
Tecnico No. 139–269, dated September
30, 2011 (BT 139–269), they already
have a 600 hour/12 month inspection
and operational check of the hydraulic
systems as part of their maintenance
program that covers all of the proposed
actions in the NPRM. Finally, the
commenter stated that the proposed AD
would not change any of their
maintenance procedures, but it would
add an additional burden of required
paper work for the same results.
We disagree. EASA AD No. 2011–
0207 is not mandatory for U.S.
operators. Additionally, while an
operator may incorporate the
procedures described in BT 139–269
into its maintenance program, not all
operators are required to do so. In order
for the corrective actions in BT 139–269
to become mandatory, and to correct the
unsafe condition identified in the
NPRM, the FAA must issue an AD.
asabaliauskas on DSK3SPTVN1PROD with RULES
FAA’s Determination
These helicopters have been approved
by the aviation authority of Italy and are
approved for operation in the United
States. Pursuant to our bilateral
agreement with Italy, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA, reviewed the
relevant information, considered the
comment received, and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
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19:06 Dec 23, 2016
Jkt 241001
adopting the AD requirements as
proposed.
Differences Between This AD and the
EASA AD
The EASA AD requires reporting the
results of the operational checks to
Agusta, while this AD does not. The
EASA AD also requires compliance
within 50 flight-hours or 2 months,
while this AD requires compliance
within 50 hours TIS.
Related Service Information Under 1
CFR Part 51
We reviewed BT 139–269 for Model
AB139 and AW139 helicopters. BT 139–
269 contains procedures for conducting
operational checks of both hydraulic
systems to confirm correct functionality.
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 this AD will affect 102
helicopters of U.S. Registry.
Based on an average labor rate of $85
per hour, we estimate that operators
may incur the following costs in order
to comply with this AD. Performing the
operational checks of the hydraulic
systems requires about 2 work-hours for
a total cost per helicopter of $170 and
a total cost to U.S. operators of $17,340.
If required, replacing a PCM will
require about 3 work-hours and required
parts will cost about $87,136, for a cost
per helicopter of $87,391.
If required, replacing a tail or flight
control shut-off valve will require about
2 work-hours, and required parts will
cost about $7,512, for a cost per
helicopter of $7,682. If required,
replacing the number 2 hydraulic
control panel will require about 2 workhours, and required parts will cost about
$8,165, for a cost per helicopter of
$8,335.
If required, replacing the number 1
hydraulic module will require about 4
work-hours, and required parts will cost
about $87,137, for a cost per helicopter
of $87,477.
If required, replacing a PCM pressure
switch will require about 2 work-hours,
and required parts will cost about
$6,974, for a cost per helicopter of
$7,144.
If required, repairing the electrical
wiring will require about 2 work-hours,
and required parts will cost about $45,
for a cost per helicopter of $215.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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94947
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
helicopters identified in this rulemaking
action.
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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.
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94948
§ 39.13
Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–26–01 AGUSTAWESTLAND S.P.A.
(AGUSTA): Amendment 39–18758;
Docket No. FAA–2016–4278; Directorate
Identifier 2012–SW–022–AD.
(a) Applicability
This AD applies to Agusta Model AB139
and AW139 helicopters, all serial numbers
except serial number 31007, 31094, 31293,
31301, 31303, 31313, and 31329, certificated
in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as an
inoperative hydraulic shut-off valve, which
could result in loss of hydraulic power and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective January 31,
2017.
asabaliauskas on DSK3SPTVN1PROD with RULES
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
Within 50 hours time-in service:
(1) Perform an operational test of each
Number 1 and Number 2 power control
module (PCM). If the fluid level in the
reservoir changes more than 5mm (0.196 in)
in an hour, replace the affected PCM.
(2) Perform an operational test of each tail
shut-off valve. If the 2 SERVO caution
message is not illuminated and the UTIL
SOV2 and TR SOV indications are in the
open position:
(i) Disconnect the Tail Shutoff valve
connector, HP4P1.
(ii) Disconnect the PCM2 connectors,
A44P3 and A44P12.
(iii) Disconnect the TB38 terminal board
connector, TB38P1.
(iv) Perform a continuity test from HP4P1–
1 to A44P12–16, from HP4P1–2 to TB38P1–
D, and from HP4P1–4 to A44P3–6.
(v) If there is no continuity, repair or
replace the defective wiring.
(vi) If there is continuity, release the test
lever of the PCM2 to the DOWN NORM
position.
(vii) If the TRSVO indication stays in the
closed position, replace the tail shutoff valve.
(3) Perform an operational test of the PCM
2 flight control shut-off valve as described in
the Compliance Instructions, paragraphs 5.1.
through 5.5., of Agusta Bollettino Tecnico
No. 139–269, dated September 30, 2011 (BT
139–269).
(i) If the 2 SERVO caution message is
illuminated:
(A) On the hydraulic control panel, lift the
guard of the SOV1/SOV2 switch and set it to
SOV2 (closed position). Make sure that the 2
HYD PRESS caution message and the HYD 2
PRESS warning light on the hydraulic control
panel are illuminated.
(B) Reset the SOV1/SOV2 switch to the
open position.
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19:06 Dec 23, 2016
Jkt 241001
(C) If the 2 HYD PRESS and 2 SERVO
caution messages remain illuminated:
(1) Disconnect the PL14P1 and PL14P2
connectors from the hydraulic control panel.
(2) Disconnect the A1–1P4 connector from
the MAU1.
(3) Disconnect the A2–1P3 connector from
the MAU2.
(4) Disconnect the A44P3 connector from
the Number 2 PCM.
(5) Disconnect the PL1P3 connector from
the circuit breaker panel.
(6) Perform a continuity test from PL14P1–
J to A1–1P4–18, from PL14P1–D to PL1P3–
q, from PL14P2–J to A44P3–5, and from
PL14P2–T to A2–1P3–34. If there is no
continuity, repair or replace the defective
wiring.
(7) If the HYD PRESS and 2 SERVO caution
messages remain illuminated, replace the
number 2 hydraulic power module.
(ii) If the 2 HYD PRESS caution message
is illuminated, the HYD 2 pressure indication
is more than 190 bar (2,755 lbf/sq in), and the
SOV2 shutoff valve is in the open position,
replace the pressure switch on the Number
2 PCM.
(iii) If the closure of SOV 2 is indicated on
the MFD hydraulic synoptic page, before
further flight, replace the Number 2 PCM.
(4) Perform an operational test of the PCM
1 flight control shut-off valve as described in
the Compliance Instructions, paragraphs 6.1.
through 6.4., of BT 139–269.
(i) If the 1 SERVO caution message is
illuminated:
(A) On the hydraulic control panel, lift the
guard of the SOV1/SOV2 switch and set it to
SOV1 (closed position). Make sure that the 1
HYD PRESS caution message and the HYD 1
PRESS warning light on the hydraulic control
panel are illuminated.
(B) Reset the SOV1/SOV2 switch to the
open position. If the 1 HYD PRESS and 1
SERVO caution messages remain
illuminated:
(1) Disconnect the PL14P1 and PL14P2
connectors from the hydraulic control panel.
(2) Disconnect the A1–1P4 connector from
the MAU1.
(3) Disconnect the A2–1P3 connector from
the MAU2.
(4) Disconnect the A45P3 connector from
the Number 1 PCM.
(5) Disconnect the PL1P3 connector from
the circuit breaker panel.
(6) Perform a continuity test from PL14P1–
J to A1–1P4–18, from PL14P1–E to A45P3–
5, from PL14P1–D to PL1P3-q, and from
PL14P2–T to A2–1P3–34. If there is no
continuity, repair or replace the defective
wiring.
(7) If the HYD PRESS and 1 SERVO caution
messages remain illuminated, replace the
Number 1 hydraulic control panel.
(ii) If the 1 HYD PRESS caution message
is illuminated, the HYD 1 pressure indication
is more than 190 bar (2,755 lbf/sq in), and the
SOV1 shutoff valve is in the open position,
replace the pressure switch on the Number
1 PCM.
(iii) If the closure of SOV 1 is indicated on
the MFD hydraulic synoptic page, before
further flight, replace the Number 1 PCM.
(4) Perform an operational test of the
emergency landing gear shutoff valve as
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described in the Compliance Instructions,
paragraphs 7.1. through 7.4., of BT 139–269.
(i) If the EMERG L/G PRESS caution
message is illuminated, the HYD 1 pressure
indication is more than 190 bar (2,755 lbf/sq
in), and the UTIL SOV1 (LDG GEAR EMER)
shutoff valve is in the open position, replace
the pressure switch on the Number 1 PCM.
(ii) If the 1 HYD MIN caution message is
illuminated, inspect the fluid level on the
Number 1 PCM and inspect the Number 1
main hydraulic system for leaks.
(A) If the fluid level is between the FULL
and ADD marks, or if there are no hydraulic
fluid leaks, perform an operational test of the
level switches. If the 1 HYD MIN caution
message is illuminated, replace the Number
1 PCM.
(B) If there is a hydraulic fluid leak:
(1) Replace all leaking parts and lines or
repair the leak.
(2) If the 1 HYD MIN caution message
remains illuminated, perform an operational
test of the level switches.
(3) If the 1 HYD MIN caution message
remains illuminated, replace the Number 1
PCM.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Wilbanks,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Parkway, Fort Worth, Texas 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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2011–0207, dated October 20, 2011. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA-2016–4278.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 2900: Hydraulic Power.
(i) 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) Agusta Bollettino Tecnico No. 139–269,
dated September 30, 2011.
(ii) Reserved.
(3) For Agusta service information
identified in this final rule, contact
AgustaWestland, Product Support
Engineering, Via del Gregge, 100, 21015
Lonate Pozzolo (VA) Italy, ATTN: Maurizio
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Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations
D’Angelo; telephone 39–0331–664757; fax 39
0331–664680; or at https://
www.agustawestland.com/technicalbulletins.
(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.
(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 December
9, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–30285 Filed 12–23–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–7525; Directorate
Identifier 2015–NM–064–AD; Amendment
39–18727; AD 2016–25–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 747–400,
747–400D, and 747–400F series
airplanes; Model 757 airplanes; and
Model 767–200, –300, –300F, and
–400ER series airplanes. This AD was
prompted by reports of uncommanded
autopilot engagement events resulting in
incorrect stabilizer trim adjustment
during takeoff. This AD requires,
depending on the model/configuration,
installing an on-ground stabilizer
autotrim inhibit system, relays and
related wiring to open and close the
flight control computer (FCC) analog
output, and new operational program
software (OPS) into the FCCs. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 31,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 31, 2017.
asabaliauskas on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
19:06 Dec 23, 2016
Jkt 241001
94949
ADDRESSES:
For service information
identified in this final rule, contact
Boeing Commercial Airplanes,
Attention: Data & Services Management,
P. O. Box 3707, MC 2H–65, Seattle, WA
98124–2207; telephone: 206–544–5000,
extension 1; fax: 206–766–5680; Internet
https://www.myboeingfleet.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
7525.
functional testing of the system, and
doing corrective actions if necessary; for
Model 757 airplanes and Model 767
airplanes, installing relays and related
wiring to open and close the FCC analog
output that controls the stabilizer trim
adjustment, doing routine functional
testing of the on-ground auto stabilizer
trim inhibit system, and doing
corrective actions if necessary; and for
Model 767–300, and –300F series
airplanes, installing new OPS into the
FCCs. We are issuing this AD to prevent
stabilizer mistrim, which could result in
a high-speed rejected takeoff and
runway overrun, or reduced
controllability of the airplane after
takeoff due to insufficient pitch control.
Examining the AD Docket
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 to each comment.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
7525; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 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: Fnu
Winarto, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification
Office (ACO), 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–
917–6659; fax: 425–917–6590; email:
fnu.winarto@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 The Boeing Company
Model 747–400, 747–400D, and 747–
400F series airplanes; Model 757
airplanes; and Model 767–200, –300,
–300F, and –400ER series airplanes. The
NPRM published in the Federal
Register on December 23, 2015 (80 FR
79735) (‘‘the NPRM’’). The NPRM was
prompted by reports of uncommanded
autopilot engagement events resulting in
incorrect stabilizer trim adjustment
during takeoff. The NPRM proposed to
require, depending on the model/
configuration for Model 747 airplanes,
installing an on-ground stabilizer
autotrim inhibit system, doing routine
PO 00000
Frm 00041
Fmt 4700
Sfmt 4700
Support for the NPRM
The Airline Pilots Association,
International stated that it fully supports
the intent of the NPRM.
Requests To Withdraw the NPRM
United Parcel Service (UPS) requested
that the NPRM be withdrawn until the
actual root cause of the unsafe condition
can be determined and a validated and
confirmed solution is developed.
FedEx Express (FedEx) requested that
we withdraw the NPRM. FedEx stated
that the burden of the actions proposed
in the NPRM is not justified based on
data presented in Boeing Fleet Team
Digest 757–FTD–22–12001 or its
operational experience. FedEx believes
this is an extremely isolated and
unlikely anomaly on the Model 757
fleet. FedEx stated that it operates over
100 Model 757 aircraft and has
completed over 210,000 flight cycles
with no reports of uncommanded
autopilot engagement.
We disagree with the commenters’
request to withdraw the NPRM. The
quantitative and qualitative risks
analyzed for this identified unsafe
condition present an unacceptable risk
that must be addressed on both
passenger and freighter models. The
manufacturer also considers the
condition a safety issue and has
developed an on-ground stabilizer
autotrim inhibit system that addresses
the unsafe condition. We have
determined that it is necessary to
proceed with issuance of this AD.
Requests To Clarify Root Cause
Boeing requested that we revise the
Discussion section of the NPRM. Boeing
E:\FR\FM\27DER1.SGM
27DER1
]]>Agencies
[Federal Register Volume 81, Number 248 (Tuesday, December 27, 2016)]
[Rules and Regulations]
[Pages 94946-94949]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30285]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-4278; Directorate Identifier 2012-SW-022-AD;
Amendment 39-18758; AD 2016-26-01]
RIN 2120-AA64
Airworthiness Directives; AgustaWestland S.p.A. (Agusta)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Agusta Model AB139 and AW139 helicopters. This AD requires performing
operational checks of both hydraulic systems. This AD was prompted by
an assessment of the hydraulic systems of the helicopter following an
accident. These actions are intended to prevent the unsafe condition on
these products.
DATES: This AD is effective January 31, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of January 31,
2017.
ADDRESSES: For service information identified in this final rule,
contact AgustaWestland, Product Support Engineering, Via del Gregge,
100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo;
telephone 39-0331-664757; fax 39 0331-664680; or at https://www.agustawestland.com/technical-bulletins. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort
Worth, TX 76177.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4278; or in person at the Docket Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the European Aviation Safety Agency (EASA) AD, the
economic evaluation, any incorporated-by-reference service information,
any comments received, and other information. The street address for
the Docket Operations Office (phone: 800-647-5527) is U.S. Department
of Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt Wilbanks, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101
Hillwood Parkway, Fort Worth, Texas 76177; telephone (817) 222-5110;
email matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On March 11, 2016, at 81 FR 12838, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 by adding an AD that would apply to certain serial-numbered
Agusta Model AB139 and AW139 helicopters. The NPRM proposed to require,
within 50 hours time-in-service (TIS), performing operational tests of
the Number 1 and Number 2 hydraulic systems power control modules
(PCMs), the tail shut-off valve, the PCM1 and PCM2 flight control shut-
off valves, and the emergency landing gear shut-off valve for correct
functionality. Depending on the results of the operational checks, the
NPRM proposed to require replacing a PCM, the tail shut-off valve, a
flight control shut-off valve, the number 2 hydraulic control panel,
the number 1 hydraulic module, the number 1 or number 2 PCM pressure
switch, or repairing the electrical wiring. The proposed requirements
were intended to prevent loss of hydraulic power to the flight controls
and subsequent loss of control of the helicopter.
The NPRM was prompted by AD No. 2011-0207, dated October 20, 2011
(AD No. 2011-0207), issued by EASA, which is the Technical Agent for
the Member States of the European Union, to correct an unsafe condition
for certain serial-numbered Agusta Model AB139 and AW139 helicopters.
EASA advises that an accident involving a Model AW139 helicopter caused
the tail rotor (T/R), the T/R gearbox, and part of the fin to detach
from the aircraft, rupturing the hydraulic lines and draining all of
the hydraulic fluid. According to EASA, an
[[Page 94947]]
assessment of the helicopter's hydraulic systems following the accident
revealed that an operational check of the hydraulic systems is
necessary to ensure its functionality. EASA advises that this
condition, if not corrected, could lead, in the case of multiple
failures, to loss of hydraulic power and subsequent loss of control of
the helicopter. To address this, EASA AD No. 2011-0207 requires, within
50 flight hours or 2 months, operational checks of the power control
modules and shutoff valves and reporting the results to the
manufacturer.
Comments
After our NPRM (81 FR 12838, March 11, 2016) was published, we
received comments from one commenter.
Request
The commenter requested we not adopt the proposed AD, as it is
unnecessary. The commenter stated that following the release of EASA AD
No. 2011-0207 and Agusta Bollettino Tecnico No. 139-269, dated
September 30, 2011 (BT 139-269), they already have a 600 hour/12 month
inspection and operational check of the hydraulic systems as part of
their maintenance program that covers all of the proposed actions in
the NPRM. Finally, the commenter stated that the proposed AD would not
change any of their maintenance procedures, but it would add an
additional burden of required paper work for the same results.
We disagree. EASA AD No. 2011-0207 is not mandatory for U.S.
operators. Additionally, while an operator may incorporate the
procedures described in BT 139-269 into its maintenance program, not
all operators are required to do so. In order for the corrective
actions in BT 139-269 to become mandatory, and to correct the unsafe
condition identified in the NPRM, the FAA must issue an AD.
FAA's Determination
These helicopters have been approved by the aviation authority of
Italy and are approved for operation in the United States. Pursuant to
our bilateral agreement with Italy, EASA, its technical representative,
has notified us of the unsafe condition described in the EASA AD. We
are issuing this AD because we evaluated all information provided by
EASA, reviewed the relevant information, considered the comment
received, and determined the unsafe condition exists and is likely to
exist or develop on other helicopters of these same type designs and
that air safety and the public interest require adopting the AD
requirements as proposed.
Differences Between This AD and the EASA AD
The EASA AD requires reporting the results of the operational
checks to Agusta, while this AD does not. The EASA AD also requires
compliance within 50 flight-hours or 2 months, while this AD requires
compliance within 50 hours TIS.
Related Service Information Under 1 CFR Part 51
We reviewed BT 139-269 for Model AB139 and AW139 helicopters. BT
139-269 contains procedures for conducting operational checks of both
hydraulic systems to confirm correct functionality.
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 this AD will affect 102 helicopters of U.S. Registry.
Based on an average labor rate of $85 per hour, we estimate that
operators may incur the following costs in order to comply with this
AD. Performing the operational checks of the hydraulic systems requires
about 2 work-hours for a total cost per helicopter of $170 and a total
cost to U.S. operators of $17,340.
If required, replacing a PCM will require about 3 work-hours and
required parts will cost about $87,136, for a cost per helicopter of
$87,391.
If required, replacing a tail or flight control shut-off valve will
require about 2 work-hours, and required parts will cost about $7,512,
for a cost per helicopter of $7,682. If required, replacing the number
2 hydraulic control panel will require about 2 work-hours, and required
parts will cost about $8,165, for a cost per helicopter of $8,335.
If required, replacing the number 1 hydraulic module will require
about 4 work-hours, and required parts will cost about $87,137, for a
cost per helicopter of $87,477.
If required, replacing a PCM pressure switch will require about 2
work-hours, and required parts will cost about $6,974, for a cost per
helicopter of $7,144.
If required, repairing the electrical wiring will require about 2
work-hours, and required parts will cost about $45, for a cost per
helicopter of $215.
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 helicopters identified in this
rulemaking action.
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
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.
[[Page 94948]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-26-01 AGUSTAWESTLAND S.P.A. (AGUSTA): Amendment 39-18758;
Docket No. FAA-2016-4278; Directorate Identifier 2012-SW-022-AD.
(a) Applicability
This AD applies to Agusta Model AB139 and AW139 helicopters, all
serial numbers except serial number 31007, 31094, 31293, 31301,
31303, 31313, and 31329, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as an inoperative hydraulic
shut-off valve, which could result in loss of hydraulic power and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective January 31, 2017.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
Within 50 hours time-in service:
(1) Perform an operational test of each Number 1 and Number 2
power control module (PCM). If the fluid level in the reservoir
changes more than 5mm (0.196 in) in an hour, replace the affected
PCM.
(2) Perform an operational test of each tail shut-off valve. If
the 2 SERVO caution message is not illuminated and the UTIL SOV2 and
TR SOV indications are in the open position:
(i) Disconnect the Tail Shutoff valve connector, HP4P1.
(ii) Disconnect the PCM2 connectors, A44P3 and A44P12.
(iii) Disconnect the TB38 terminal board connector, TB38P1.
(iv) Perform a continuity test from HP4P1-1 to A44P12-16, from
HP4P1-2 to TB38P1-D, and from HP4P1-4 to A44P3-6.
(v) If there is no continuity, repair or replace the defective
wiring.
(vi) If there is continuity, release the test lever of the PCM2
to the DOWN NORM position.
(vii) If the TRSVO indication stays in the closed position,
replace the tail shutoff valve.
(3) Perform an operational test of the PCM 2 flight control
shut-off valve as described in the Compliance Instructions,
paragraphs 5.1. through 5.5., of Agusta Bollettino Tecnico No. 139-
269, dated September 30, 2011 (BT 139-269).
(i) If the 2 SERVO caution message is illuminated:
(A) On the hydraulic control panel, lift the guard of the SOV1/
SOV2 switch and set it to SOV2 (closed position). Make sure that the
2 HYD PRESS caution message and the HYD 2 PRESS warning light on the
hydraulic control panel are illuminated.
(B) Reset the SOV1/SOV2 switch to the open position.
(C) If the 2 HYD PRESS and 2 SERVO caution messages remain
illuminated:
(1) Disconnect the PL14P1 and PL14P2 connectors from the
hydraulic control panel.
(2) Disconnect the A1-1P4 connector from the MAU1.
(3) Disconnect the A2-1P3 connector from the MAU2.
(4) Disconnect the A44P3 connector from the Number 2 PCM.
(5) Disconnect the PL1P3 connector from the circuit breaker
panel.
(6) Perform a continuity test from PL14P1-J to A1-1P4-18, from
PL14P1-D to PL1P3-q, from PL14P2-J to A44P3-5, and from PL14P2-T to
A2-1P3-34. If there is no continuity, repair or replace the
defective wiring.
(7) If the HYD PRESS and 2 SERVO caution messages remain
illuminated, replace the number 2 hydraulic power module.
(ii) If the 2 HYD PRESS caution message is illuminated, the HYD
2 pressure indication is more than 190 bar (2,755 lbf/sq in), and
the SOV2 shutoff valve is in the open position, replace the pressure
switch on the Number 2 PCM.
(iii) If the closure of SOV 2 is indicated on the MFD hydraulic
synoptic page, before further flight, replace the Number 2 PCM.
(4) Perform an operational test of the PCM 1 flight control
shut-off valve as described in the Compliance Instructions,
paragraphs 6.1. through 6.4., of BT 139-269.
(i) If the 1 SERVO caution message is illuminated:
(A) On the hydraulic control panel, lift the guard of the SOV1/
SOV2 switch and set it to SOV1 (closed position). Make sure that the
1 HYD PRESS caution message and the HYD 1 PRESS warning light on the
hydraulic control panel are illuminated.
(B) Reset the SOV1/SOV2 switch to the open position. If the 1
HYD PRESS and 1 SERVO caution messages remain illuminated:
(1) Disconnect the PL14P1 and PL14P2 connectors from the
hydraulic control panel.
(2) Disconnect the A1-1P4 connector from the MAU1.
(3) Disconnect the A2-1P3 connector from the MAU2.
(4) Disconnect the A45P3 connector from the Number 1 PCM.
(5) Disconnect the PL1P3 connector from the circuit breaker
panel.
(6) Perform a continuity test from PL14P1-J to A1-1P4-18, from
PL14P1-E to A45P3-5, from PL14P1-D to PL1P3-q, and from PL14P2-T to
A2-1P3-34. If there is no continuity, repair or replace the
defective wiring.
(7) If the HYD PRESS and 1 SERVO caution messages remain
illuminated, replace the Number 1 hydraulic control panel.
(ii) If the 1 HYD PRESS caution message is illuminated, the HYD
1 pressure indication is more than 190 bar (2,755 lbf/sq in), and
the SOV1 shutoff valve is in the open position, replace the pressure
switch on the Number 1 PCM.
(iii) If the closure of SOV 1 is indicated on the MFD hydraulic
synoptic page, before further flight, replace the Number 1 PCM.
(4) Perform an operational test of the emergency landing gear
shutoff valve as described in the Compliance Instructions,
paragraphs 7.1. through 7.4., of BT 139-269.
(i) If the EMERG L/G PRESS caution message is illuminated, the
HYD 1 pressure indication is more than 190 bar (2,755 lbf/sq in),
and the UTIL SOV1 (LDG GEAR EMER) shutoff valve is in the open
position, replace the pressure switch on the Number 1 PCM.
(ii) If the 1 HYD MIN caution message is illuminated, inspect
the fluid level on the Number 1 PCM and inspect the Number 1 main
hydraulic system for leaks.
(A) If the fluid level is between the FULL and ADD marks, or if
there are no hydraulic fluid leaks, perform an operational test of
the level switches. If the 1 HYD MIN caution message is illuminated,
replace the Number 1 PCM.
(B) If there is a hydraulic fluid leak:
(1) Replace all leaking parts and lines or repair the leak.
(2) If the 1 HYD MIN caution message remains illuminated,
perform an operational test of the level switches.
(3) If the 1 HYD MIN caution message remains illuminated,
replace the Number 1 PCM.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety
Engineer, Safety Management Group, Rotorcraft Directorate, FAA,
10101 Hillwood Parkway, Fort Worth, Texas 76177; telephone (817)
222-5110; email 9-ASW-FTW-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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2011-0207, dated October 20, 2011. You may view
the EASA AD on the Internet at https://www.regulations.gov in Docket
No. FAA[hyphen]2016-4278.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 2900: Hydraulic
Power.
(i) 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) Agusta Bollettino Tecnico No. 139-269, dated September 30,
2011.
(ii) Reserved.
(3) For Agusta service information identified in this final
rule, contact AgustaWestland, Product Support Engineering, Via del
Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio
[[Page 94949]]
D'Angelo; telephone 39-0331-664757; fax 39 0331-664680; or at https://www.agustawestland.com/technical-bulletins.
(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.
(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 December 9, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-30285 Filed 12-23-16; 8:45 am]
BILLING CODE 4910-13-P
