[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]
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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.
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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 http://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 http://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 [email protected].
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 [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(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 http://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 http://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: http://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]
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