Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters, 12838-12841 [2016-05368]
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12838
Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
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 proposed 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus Helicopters: Docket No. FAA–2015–
6033; Directorate Identifier 2015–SW–
019–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS 365 N3 helicopters, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as
missing or incorrectly located information for
exiting a helicopter. This condition could
result in failure to jettison cabin doors during
an emergency, resulting in death or injury of
helicopter occupants.
(c) Comments Due Date
We must receive comments by May 10,
2016.
AS365–11.00.02, Revision 2, dated April 23,
2015.
(f) Credit for Previously Completed Actions
Actions accomplished before the effective
date of this AD in accordance with Airbus
Helicopters Modification (MOD) 0711B68 for
helicopters without external life rafts or MOD
0711B68 and MOD 0711B67 for helicopters
with external life rafts are considered
acceptable for compliance with this AD.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: David Hatfield,
Aviation Safety Engineer, Safety Management
Group, Rotorcraft Directorate, FAA, 10101
Hillwood Pkwy, Fort Worth, TX 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.
(h) Additional Information
The subject of this AD is addressed in the
European Aviation Safety Agency (EASA) AD
No. 2015–0068–E, dated April 29, 2015. You
may view the EASA AD on the Internet at
https://www.regulations.gov by searching for
and locating it in Docket No. FAA–2015–
6033.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 1100, Placards and Markings.
Issued in Fort Worth, Texas, on February
29, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–05369 Filed 3–10–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(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.
14 CFR Part 39
(e) Required Actions
Within 50 hours time-in-service:
(1) Inspect the cabin and cockpit for labels,
placards, and markings that provide jettison
procedure instructions for cabin doors.
(2) For the left and right side, remove any
existing label, placard, and marking and
install placards in accordance with the
Accomplishment Instructions, paragraph
3.B.2 and Figures 1 through 6, of Airbus
Helicopters Alert Service Bulletin No.
Airworthiness Directives;
AgustaWestland S.p.A. (Agusta)
Helicopters
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Jkt 238001
[Docket No. FAA–2016–4278; Directorate
Identifier 2012–SW–022–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
SUMMARY:
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Agusta Model AB139 and AW139
helicopters. This proposed AD would
require performing operational checks
of both hydraulic systems. This
proposed AD is prompted by an
assessment of the hydraulic systems of
the helicopter following an accident.
The proposed actions are intended to
prevent loss of hydraulic power to the
flight controls and subsequent loss of
control of the helicopter.
DATES: We must receive comments on
this proposed AD by May 10, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket number 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 proposed AD, the
European Aviation Safety Agency
(EASA) AD, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
For service information identified in
this proposed 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
Parkway, Fort Worth, Texas 76177.
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.
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Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
SUPPLEMENTARY INFORMATION:
FAA’s Determination
Comments Invited
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 its
AD. We are proposing this AD because
we evaluated all known relevant
information and determined that an
unsafe condition is likely to exist or
develop on other products of the same
type design.
We invite you to participate in this
rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that might result
from adopting the proposals in this
document. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit only one time.
We will file in the docket all
comments that we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning this proposed rulemaking.
Before acting on this proposal, we will
consider all comments we receive on or
before the closing date for comments.
We will consider comments filed after
the comment period has closed if it is
possible to do so without incurring
expense or delay. We may change this
proposal in light of the comments we
receive.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD No. 2011–
0207, dated October 20, 2011 (EASA
2011–0207), to correct an unsafe
condition for certain serial-numbered
Agusta Model AB139 and AW139
helicopters. 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.
Investigation following the accident
resulted in an assessment of the
helicopter’s hydraulic systems.
According to EASA, this assessment
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 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.
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Related Service Information Under 1
CFR Part 51
We reviewed Agusta Bollettino
Tecnico No. 139–269, dated September
30, 2011 (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.
Proposed AD Requirements
This proposed AD would 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 the
operational checks, this proposed AD
would 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.
Differences Between This Proposed AD
and the EASA AD
The EASA AD requires reporting the
results of the operational checks to
Agusta, while the proposed AD does
not. The EASA AD also requires
compliance within 50 flight-hours or 2
months, while the proposed AD requires
compliance within 50 hours TIS.
Costs of Compliance
We estimate that this proposed AD
would 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 proposed
AD.
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12839
Performing the operational checks of
the hydraulic systems would require
about 2 work-hours for a total cost per
helicopter of $170 and a total cost to
U.S. operators of $17,340.
Replacing a PCM would require about
3 work-hours and required parts would
cost about $87,136, for a cost per
helicopter of $87,391.
Replacing a tail or flight control shutoff valve would require about 2 workhours, and required parts would cost
about $7,512, for a cost per helicopter of
$7,682.
Replacing the number 2 hydraulic
control panel would require about 2
work-hours, and required parts would
cost about $8,165, for a cost per
helicopter of $8,335.
Replacing the number 1 hydraulic
module would require about 4 workhours, and required parts would cost
about $87,137, for a cost per helicopter
of $87,477.
Replacing a PCM pressure switch
would require about 2 work-hours, and
required parts would cost about $6,974,
for a cost per helicopter of $7,144.
Repairing the electrical wiring would
require about 2 work-hours, and
required parts would 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
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
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12840
Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
For the reasons discussed, I certify
this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska 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 proposed 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Agustawestland S.P.A. (Agusta): 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.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(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) Comments Due Date
We must receive comments by May 10,
2016.
(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
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Jkt 238001
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:
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(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;
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Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
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.
DEPARTMENT OF TRANSPORTATION
We must receive comments on
this proposed AD by May 10, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Rolls-Royce
Deutschland Ltd & Co KG, Eschenweg
11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49–0–33–
7086–1064; fax: 49–0–33–7086–3276.
You may view this service information
at the FAA, Engine & Propeller
Directorate, 1200 District Avenue,
Burlington, MA. For information on the
availability of this material at the FAA,
call 781–238–7125.
Federal Aviation Administration
Examining the AD Docket
(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.
Issued in Fort Worth, Texas, on March 3,
2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2016–05368 Filed 3–10–16; 8:45 am]
BILLING CODE 4910–13–P
14 CFR Part 39
[Docket No. FAA–2006–25513; Directorate
Identifier 99–NE–61–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2006–18–
14 that applies to all Rolls-Royce
Deutschland Ltd & Co KG (RRD) Tay
650–15 and Tay 651–54 turbofan
engines. AD 2006–18–14 requires
calculating and re-establishing the
cyclic life of stage 1 high-pressure
turbine (HPT) disks, part number (P/N)
JR32013 and P/N JR33838, and stage 1
low-pressure turbine (LPT) disk, P/N
JR32318A. This proposed AD would
require re-calculating the cyclic life, and
would impose a reduced cyclic life, of
stage 1 HPT disk, P/N JR32013. We are
proposing this AD to prevent failure of
stage 1 HPT disks, P/N JR32013 and P/
N JR33838, and stage 1 LPT disk, P/N
JR32318A, which could result in an
uncontained engine failure and damage
to the airplane.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
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Jkt 238001
DATES:
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2006–
25513; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
mandatory continuing airworthiness
information, regulatory evaluation, any
comments received, and other
information. The address for the Docket
Office (phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7770; fax: 781–238–7199;
email: philip.haberlen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–25513; Directorate Identifier
99–NE–61–AD’’ at the beginning of your
comments. We specifically invite
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12841
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On August 30, 2006, we issued AD
2006–18–14, Amendment 39–14753 (71
FR 52988, September 8, 2006), for all
RRD Tay 650–15 and Tay 651–54
turbofan engines. AD 2006–18–14
requires calculating and re-establishing
the cyclic life of stage 1 HPT disks, P/
N JR32013 and P/N JR33838, and stage
1 LPT disk, P/N JR32318A, that have
been exposed to different engine flight
plan profiles. AD 2006–18–14 also
requires removing from service, using a
drawdown schedule, those stage 1 HPT
disks and stage 1 LPT disks operated
under Tay 650–15 engine flight plan
profiles A, B, C, or D; or operated under
the Tay 651–54 engine datum flight
profile, at reduced cyclic life limits. AD
2006–18–14 resulted from RRD
updating their low-cycle-fatigue
analysis for stage 1 HPT disks and stage
1 LPT disks and reducing their cyclic
life limits. We issued AD 2006–18–14 to
prevent cracks leading to turbine disk
failure, which could result in an
uncontained engine failure and damage
to the airplane.
Actions Since AD 2006–18–14 Was
Issued
Since we issued AD 2006–18–14, RRD
reviewed the cyclic life limit of parts
affected by AD 2006–18–14; RRD
concluded that the stage 1 HPT disk, P/
N JR32013, requires further cyclic life
limit reduction. RRD did not further
reduce the cyclic life limit of stage 1
HPT disk, P/N JR33838, or stage 1 LPT
disk, P/N JR32318A. Accordingly, the
cyclic life limits of stage 1 HPT disk, P/
N JR33838, and stage 1 LPT disk, P/N
JR32318A, as imposed by AD 2006–18–
14, remain unchanged in this proposed
AD.
Since AD 2006–18–14 was issued, the
European Aviation Safety Agency
(EASA) issued AD 2015–0056, dated
March 31, 2015 to reduce the cyclic life
limits of the stage 1 HPT disk, P/N
JR32013.
E:\FR\FM\11MRP1.SGM
11MRP1
]]>Agencies
[Federal Register Volume 81, Number 48 (Friday, March 11, 2016)]
[Proposed Rules]
[Pages 12838-12841]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05368]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-4278; Directorate Identifier 2012-SW-022-AD]
RIN 2120-AA64
Airworthiness Directives; AgustaWestland S.p.A. (Agusta)
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Agusta Model AB139 and AW139 helicopters. This proposed AD
would require performing operational checks of both hydraulic systems.
This proposed AD is prompted by an assessment of the hydraulic systems
of the helicopter following an accident. The proposed actions are
intended to prevent loss of hydraulic power to the flight controls and
subsequent loss of control of the helicopter.
DATES: We must receive comments on this proposed AD by May 10, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket number 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 proposed AD, the European Aviation Safety Agency
(EASA) AD, the economic evaluation, any comments received, and other
information. The street address for the Docket Operations Office
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
For service information identified in this proposed 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 Parkway, Fort Worth, Texas 76177.
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.
[[Page 12839]]
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD No. 2011-0207, dated October 20,
2011 (EASA 2011-0207), to correct an unsafe condition for certain
serial-numbered Agusta Model AB139 and AW139 helicopters. 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. Investigation
following the accident resulted in an assessment of the helicopter's
hydraulic systems. According to EASA, this assessment 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 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.
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 its AD. We are
proposing this AD because we evaluated all known relevant information
and determined that an unsafe condition is likely to exist or develop
on other products of the same type design.
Related Service Information Under 1 CFR Part 51
We reviewed Agusta Bollettino Tecnico No. 139-269, dated September
30, 2011 (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.
Proposed AD Requirements
This proposed AD would 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 the operational checks, this proposed
AD would 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.
Differences Between This Proposed AD and the EASA AD
The EASA AD requires reporting the results of the operational
checks to Agusta, while the proposed AD does not. The EASA AD also
requires compliance within 50 flight-hours or 2 months, while the
proposed AD requires compliance within 50 hours TIS.
Costs of Compliance
We estimate that this proposed AD would 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 proposed AD.
Performing the operational checks of the hydraulic systems would
require about 2 work-hours for a total cost per helicopter of $170 and
a total cost to U.S. operators of $17,340.
Replacing a PCM would require about 3 work-hours and required parts
would cost about $87,136, for a cost per helicopter of $87,391.
Replacing a tail or flight control shut-off valve would require
about 2 work-hours, and required parts would cost about $7,512, for a
cost per helicopter of $7,682.
Replacing the number 2 hydraulic control panel would require about
2 work-hours, and required parts would cost about $8,165, for a cost
per helicopter of $8,335.
Replacing the number 1 hydraulic module would require about 4 work-
hours, and required parts would cost about $87,137, for a cost per
helicopter of $87,477.
Replacing a PCM pressure switch would require about 2 work-hours,
and required parts would cost about $6,974, for a cost per helicopter
of $7,144.
Repairing the electrical wiring would require about 2 work-hours,
and required parts would 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 products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
[[Page 12840]]
For the reasons discussed, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska 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 proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Agustawestland S.P.A. (Agusta): 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) Comments Due Date
We must receive comments by May 10, 2016.
(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;
[[Page 12841]]
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.
Issued in Fort Worth, Texas, on March 3, 2016.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-05368 Filed 3-10-16; 8:45 am]
BILLING CODE 4910-13-P
