81 FR 94946 - Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 248 (December 27, 2016)

Page Range		94946-94949
FR Document		2016-30285
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.
Federal Register, Volume 81 Issue 248 (Tuesday, December 27, 2016)
[Federal Register Volume 81, Number 248 (Tuesday, December 27, 2016)]
[Rules and Regulations]
[Pages 94946-94949]
From the Federal Register Online  [www.thefederalregister.org]
[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]
 BILLING CODE 4910-13-P
94946 Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations

or the component history card or equivalent (i) Subject Operations Office between 9 a.m. and 5
record do not specify a life limit for the TT Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except
strap, or if they specify a different life limit Code: 6200 Main Rotor System. Federal holidays. The AD docket
than in paragraph (e)(1), do the following: contains this AD, the European Aviation
(i) Revise the Airworthiness Limitations Issued in Fort Worth, Texas, on December
1, 2016. Safety Agency (EASA) AD, the
section of the applicable maintenance
Lance T. Gant, economic evaluation, any incorporated-
manual or ICA by establishing a life limit of
25,000 flights or 10 years since date of Manager, Rotorcraft Directorate, Aircraft
by-reference service information, any
manufacture, whichever occurs first, for each Certification Service. comments received, and other
TT strap P/N 2604067 and P/N 117–14110 by [FR Doc. 2016–30053 Filed 12–23–16; 8:45 am]
information. The street address for the
making pen-and-ink changes or by inserting Docket Operations Office (phone: 800–
BILLING CODE 4910–13–P
a copy of this AD into the Airworthiness 647–5527) is U.S. Department of
Limitations section of the maintenance Transportation, Docket Operations
manual or the ICA. For purposes of this AD, DEPARTMENT OF TRANSPORTATION Office, M–30, West Building Ground
a flight would be counted anytime the Floor, Room W12–140, 1200 New Jersey
helicopter lifts off into the air and then lands Federal Aviation Administration Avenue SE., Washington, DC 20590.
again regardless of the duration of the FOR FURTHER INFORMATION CONTACT: Matt
landing and regardless of whether the engine
14 CFR Part 39 Wilbanks, Aviation Safety Engineer,
is shut down.
(ii) Create a component history card or [Docket No. FAA–2016–4278; Directorate
Safety Management Group, Rotorcraft
equivalent record for each TT strap P/N Identifier 2012–SW–022–AD; Amendment Directorate, FAA, 10101 Hillwood
2604067 and P/N 117–14110, if one does not 39–18758; AD 2016–26–01] Parkway, Fort Worth, Texas 76177;
exist, and record a life limit of 25,000 flights telephone (817) 222–5110; email
RIN 2120–AA64 matt.wilbanks@faa.gov.
or 10 years since date of manufacture,
whichever occurs first. Airworthiness Directives; SUPPLEMENTARY INFORMATION:
(3) Remove from service each TT strap that
AgustaWestland S.p.A. (Agusta) Discussion
has reached or exceeded its life limit.
Helicopters
(f) Special Flight Permits On March 11, 2016, at 81 FR 12838,
AGENCY: Federal Aviation the Federal Register published our
Special flight permits are prohibited.
Administration (FAA), DOT. notice of proposed rulemaking (NPRM),
(g) Alternative Methods of Compliance ACTION: Final rule. which proposed to amend 14 CFR part
(AMOCs) 39 by adding an AD that would apply
(1) The Manager, Safety Management SUMMARY: We are adopting a new to certain serial-numbered Agusta
Group, FAA, may approve AMOCs for this airworthiness directive (AD) for certain Model AB139 and AW139 helicopters.
AD. Send your proposal to: Matt Fuller, Agusta Model AB139 and AW139 The NPRM proposed to require, within
Senior Aviation Safety Engineer, Safety helicopters. This AD requires 50 hours time-in-service (TIS),
Management Group, Rotorcraft Directorate, performing operational checks of both performing operational tests of the
FAA, 10101 Hillwood Pkwy, Fort Worth, hydraulic systems. This AD was Number 1 and Number 2 hydraulic
Texas 76177; telephone (817) 222–5110; prompted by an assessment of the systems power control modules (PCMs),
email 9-ASW-FTW-AMOC-Requests@faa.gov. hydraulic systems of the helicopter the tail shut-off valve, the PCM1 and
(2) For operations conducted under a 14 following an accident. These actions are PCM2 flight control shut-off valves, and
CFR part 119 operating certificate or under intended to prevent the unsafe
14 CFR part 91, subpart K, we suggest that the emergency landing gear shut-off
condition on these products. valve for correct functionality.
you notify your principal inspector, or
lacking a principal inspector, the manager of DATES: This AD is effective January 31, Depending on the results of the
the local flight standards district office or 2017. operational checks, the NPRM proposed
certificate holding district office, before The Director of the Federal Register to require replacing a PCM, the tail shut-
operating any aircraft complying with this approved the incorporation by reference off valve, a flight control shut-off valve,
AD through an AMOC. of a certain document listed in this AD the number 2 hydraulic control panel,
as of January 31, 2017. the number 1 hydraulic module, the
(h) Additional Information
ADDRESSES: For service information number 1 or number 2 PCM pressure
(1) Airbus Helicopters Alert Service switch, or repairing the electrical
identified in this final rule, contact
Bulletin ASB BO105LS–10A–013, Revision 0,
AgustaWestland, Product Support wiring. The proposed requirements
dated March 9, 2015, which is not
incorporated by reference, contains Engineering, Via del Gregge, 100, 21015 were intended to prevent loss of
additional information about the subject of Lonate Pozzolo (VA) Italy, ATTN: hydraulic power to the flight controls
this AD. For service information identified in Maurizio D’Angelo; telephone 39–0331– and subsequent loss of control of the
this AD, contact Airbus Helicopters, 2701 N. 664757; fax 39 0331–664680; or at helicopter.
Forum Drive, Grand Prairie, TX 75052; http://www.agustawestland.com/ The NPRM was prompted by AD No.
telephone (972) 641–0000 or (800) 232–0323; technical-bulletins. You may review the 2011–0207, dated October 20, 2011 (AD
fax (972) 641–3775; or at http:// referenced service information at the No. 2011–0207), issued by EASA, which
www.airbushelicopters.com/techpub. You FAA, Office of the Regional Counsel, is the Technical Agent for the Member
may review the referenced service Southwest Region, 10101 Hillwood States of the European Union, to correct
information at the FAA, Office of the Pkwy, Room 6N–321, Fort Worth, TX an unsafe condition for certain serial-
asabaliauskas on DSK3SPTVN1PROD with RULES

Regional Counsel, Southwest Region, 10101 numbered Agusta Model AB139 and
76177.
Hillwood Pkwy, Room 6N–321, Fort Worth,
AW139 helicopters. EASA advises that
TX 76177. Examining the AD Docket
(2) The subject of this AD is addressed in
an accident involving a Model AW139
European Aviation Safety Agency (EASA) AD You may examine the AD docket on helicopter caused the tail rotor (T/R),
No. 2015–0042, dated March 9, 2015. You the Internet at http:// the T/R gearbox, and part of the fin to
may view the EASA AD on the Internet at www.regulations.gov by searching for detach from the aircraft, rupturing the
http://www.regulations.gov in Docket No. and locating Docket No. FAA–2016– hydraulic lines and draining all of the
FAA–2016–5247. 4278; or in person at the Docket hydraulic fluid. According to EASA, an

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Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations 94947

assessment of the helicopter’s hydraulic adopting the AD requirements as rules on aviation safety. Subtitle I,
systems following the accident revealed proposed. section 106, describes the authority of
that an operational check of the the FAA Administrator. Subtitle VII:
Differences Between This AD and the
hydraulic systems is necessary to ensure Aviation Programs, describes in more
EASA AD
its functionality. EASA advises that this detail the scope of the Agency’s
condition, if not corrected, could lead, The EASA AD requires reporting the authority.
in the case of multiple failures, to loss results of the operational checks to We are issuing this rulemaking under
of hydraulic power and subsequent loss Agusta, while this AD does not. The the authority described in Subtitle VII,
of control of the helicopter. To address EASA AD also requires compliance Part A, Subpart III, Section 44701:
this, EASA AD No. 2011–0207 requires, within 50 flight-hours or 2 months, ‘‘General requirements.’’ Under that
within 50 flight hours or 2 months, while this AD requires compliance section, Congress charges the FAA with
operational checks of the power control within 50 hours TIS. promoting safe flight of civil aircraft in
modules and shutoff valves and Related Service Information Under 1 air commerce by prescribing regulations
reporting the results to the CFR Part 51 for practices, methods, and procedures
manufacturer. the Administrator finds necessary for
We reviewed BT 139–269 for Model safety in air commerce. This regulation
Comments AB139 and AW139 helicopters. BT 139– is within the scope of that authority
After our NPRM (81 FR 12838, March 269 contains procedures for conducting because it addresses an unsafe condition
11, 2016) was published, we received operational checks of both hydraulic that is likely to exist or develop on
comments from one commenter. systems to confirm correct functionality. helicopters identified in this rulemaking
This service information is reasonably action.
Request available because the interested parties
have access to it through their normal Regulatory Findings
The commenter requested we not
adopt the proposed AD, as it is course of business or by the means This AD will not have federalism
unnecessary. The commenter stated that identified in the ADDRESSES section. implications under Executive Order
following the release of EASA AD No. Costs of Compliance 13132. This AD will not have a
2011–0207 and Agusta Bollettino substantial direct effect on the States, on
We estimate this AD will affect 102
Tecnico No. 139–269, dated September the relationship between the national
helicopters of U.S. Registry.
30, 2011 (BT 139–269), they already government and the States, or on the
Based on an average labor rate of $85
have a 600 hour/12 month inspection distribution of power and
per hour, we estimate that operators
and operational check of the hydraulic responsibilities among the various
may incur the following costs in order
systems as part of their maintenance levels of government.
to comply with this AD. Performing the
program that covers all of the proposed operational checks of the hydraulic For the reasons discussed above, I
actions in the NPRM. Finally, the systems requires about 2 work-hours for certify that this AD:
commenter stated that the proposed AD a total cost per helicopter of $170 and (1) Is not a ‘‘significant regulatory
would not change any of their a total cost to U.S. operators of $17,340. action’’ under Executive Order 12866;
maintenance procedures, but it would If required, replacing a PCM will (2) Is not a ‘‘significant rule’’ under
add an additional burden of required require about 3 work-hours and required DOT Regulatory Policies and Procedures
paper work for the same results. parts will cost about $87,136, for a cost (44 FR 11034, February 26, 1979);
We disagree. EASA AD No. 2011– per helicopter of $87,391. (3) Will not affect intrastate aviation
0207 is not mandatory for U.S. If required, replacing a tail or flight in Alaska to the extent that it justifies
operators. Additionally, while an control shut-off valve will require about making a regulatory distinction; and
operator may incorporate the 2 work-hours, and required parts will (4) Will not have a significant
procedures described in BT 139–269 cost about $7,512, for a cost per economic impact, positive or negative,
into its maintenance program, not all helicopter of $7,682. If required, on a substantial number of small entities
operators are required to do so. In order replacing the number 2 hydraulic under the criteria of the Regulatory
for the corrective actions in BT 139–269 control panel will require about 2 work- Flexibility Act.
to become mandatory, and to correct the hours, and required parts will cost about We prepared an economic evaluation
unsafe condition identified in the $8,165, for a cost per helicopter of of the estimated costs to comply with
NPRM, the FAA must issue an AD. $8,335. this AD and placed it in the AD docket.
FAA’s Determination If required, replacing the number 1
List of Subjects in 14 CFR Part 39
hydraulic module will require about 4
These helicopters have been approved work-hours, and required parts will cost Air transportation, Aircraft, Aviation
by the aviation authority of Italy and are about $87,137, for a cost per helicopter safety, Incorporation by reference,
approved for operation in the United of $87,477. Safety.
States. Pursuant to our bilateral If required, replacing a PCM pressure
agreement with Italy, EASA, its Adoption of the Amendment
switch will require about 2 work-hours,
technical representative, has notified us and required parts will cost about Accordingly, under the authority
of the unsafe condition described in the $6,974, for a cost per helicopter of delegated to me by the Administrator,
EASA AD. We are issuing this AD $7,144. the FAA amends 14 CFR part 39 as
asabaliauskas on DSK3SPTVN1PROD with RULES

because we evaluated all information If required, repairing the electrical follows:
provided by EASA, reviewed the wiring will require about 2 work-hours,
relevant information, considered the and required parts will cost about $45, PART 39—AIRWORTHINESS
comment received, and determined the for a cost per helicopter of $215. DIRECTIVES
unsafe condition exists and is likely to
exist or develop on other helicopters of Authority for This Rulemaking ■ 1. The authority citation for part 39
these same type designs and that air Title 49 of the United States Code continues to read as follows:
safety and the public interest require specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701.

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94948 Federal Register / Vol. 81, No. 248 / Tuesday, December 27, 2016 / Rules and Regulations

§ 39.13 [Amended] (C) If the 2 HYD PRESS and 2 SERVO described in the Compliance Instructions,
caution messages remain illuminated: paragraphs 7.1. through 7.4., of BT 139–269.
■ 2. The FAA amends § 39.13 by adding (1) Disconnect the PL14P1 and PL14P2 (i) If the EMERG L/G PRESS caution
the following new airworthiness connectors from the hydraulic control panel. message is illuminated, the HYD 1 pressure
directive (AD): (2) Disconnect the A1–1P4 connector from indication is more than 190 bar (2,755 lbf/sq
2016–26–01 AGUSTAWESTLAND S.P.A. the MAU1. in), and the UTIL SOV1 (LDG GEAR EMER)
(AGUSTA): Amendment 39–18758; (3) Disconnect the A2–1P3 connector from shutoff valve is in the open position, replace
Docket No. FAA–2016–4278; Directorate the MAU2. the pressure switch on the Number 1 PCM.
Identifier 2012–SW–022–AD. (4) Disconnect the A44P3 connector from (ii) If the 1 HYD MIN caution message is
the Number 2 PCM. illuminated, inspect the fluid level on the
(a) Applicability (5) Disconnect the PL1P3 connector from Number 1 PCM and inspect the Number 1
This AD applies to Agusta Model AB139 the circuit breaker panel. main hydraulic system for leaks.
and AW139 helicopters, all serial numbers (6) Perform a continuity test from PL14P1– (A) If the fluid level is between the FULL
except serial number 31007, 31094, 31293, J to A1–1P4–18, from PL14P1–D to PL1P3– and ADD marks, or if there are no hydraulic
31301, 31303, 31313, and 31329, certificated q, from PL14P2–J to A44P3–5, and from fluid leaks, perform an operational test of the
in any category. PL14P2–T to A2–1P3–34. If there is no level switches. If the 1 HYD MIN caution
continuity, repair or replace the defective message is illuminated, replace the Number
(b) Unsafe Condition wiring. 1 PCM.
This AD defines the unsafe condition as an (7) If the HYD PRESS and 2 SERVO caution (B) If there is a hydraulic fluid leak:
inoperative hydraulic shut-off valve, which messages remain illuminated, replace the (1) Replace all leaking parts and lines or
could result in loss of hydraulic power and number 2 hydraulic power module. repair the leak.
subsequent loss of control of the helicopter. (ii) If the 2 HYD PRESS caution message (2) If the 1 HYD MIN caution message
is illuminated, the HYD 2 pressure indication remains illuminated, perform an operational
(c) Effective Date
is more than 190 bar (2,755 lbf/sq in), and the test of the level switches.
This AD becomes effective January 31, SOV2 shutoff valve is in the open position, (3) If the 1 HYD MIN caution message
2017. replace the pressure switch on the Number remains illuminated, replace the Number 1
(d) Compliance 2 PCM. PCM.
(iii) If the closure of SOV 2 is indicated on
You are responsible for performing each (f) Alternative Methods of Compliance
the MFD hydraulic synoptic page, before
action required by this AD within the (AMOCs)
further flight, replace the Number 2 PCM.
specified compliance time unless it has (4) Perform an operational test of the PCM (1) The Manager, Safety Management
already been accomplished prior to that time. 1 flight control shut-off valve as described in Group, FAA, may approve AMOCs for this
(e) Required Actions the Compliance Instructions, paragraphs 6.1. AD. Send your proposal to: Matt Wilbanks,
through 6.4., of BT 139–269. Aviation Safety Engineer, Safety Management
Within 50 hours time-in service: Group, Rotorcraft Directorate, FAA, 10101
(i) If the 1 SERVO caution message is
(1) Perform an operational test of each Hillwood Parkway, Fort Worth, Texas 76177;
illuminated:
Number 1 and Number 2 power control telephone (817) 222–5110; email 9-ASW-
(A) On the hydraulic control panel, lift the
module (PCM). If the fluid level in the FTW-AMOC-Requests@faa.gov.
guard of the SOV1/SOV2 switch and set it to
reservoir changes more than 5mm (0.196 in) (2) For operations conducted under a 14
in an hour, replace the affected PCM. SOV1 (closed position). Make sure that the 1
HYD PRESS caution message and the HYD 1 CFR part 119 operating certificate or under
(2) Perform an operational test of each tail 14 CFR part 91, subpart K, we suggest that
shut-off valve. If the 2 SERVO caution PRESS warning light on the hydraulic control
panel are illuminated. you notify your principal inspector, or
message is not illuminated and the UTIL lacking a principal inspector, the manager of
SOV2 and TR SOV indications are in the (B) Reset the SOV1/SOV2 switch to the
open position. If the 1 HYD PRESS and 1 the local flight standards district office or
open position: certificate holding district office, before
(i) Disconnect the Tail Shutoff valve SERVO caution messages remain
illuminated: operating any aircraft complying with this
connector, HP4P1. AD through an AMOC.
(ii) Disconnect the PCM2 connectors, (1) Disconnect the PL14P1 and PL14P2
A44P3 and A44P12. connectors from the hydraulic control panel. (g) Additional Information
(iii) Disconnect the TB38 terminal board (2) Disconnect the A1–1P4 connector from
The subject of this AD is addressed in
connector, TB38P1. the MAU1.
European Aviation Safety Agency (EASA) AD
(iv) Perform a continuity test from HP4P1– (3) Disconnect the A2–1P3 connector from
No. 2011–0207, dated October 20, 2011. You
1 to A44P12–16, from HP4P1–2 to TB38P1– the MAU2. may view the EASA AD on the Internet at
D, and from HP4P1–4 to A44P3–6. (4) Disconnect the A45P3 connector from http://www.regulations.gov in Docket No.
(v) If there is no continuity, repair or the Number 1 PCM. FAA-2016–4278.
replace the defective wiring. (5) Disconnect the PL1P3 connector from
(vi) If there is continuity, release the test the circuit breaker panel. (h) Subject
lever of the PCM2 to the DOWN NORM (6) Perform a continuity test from PL14P1– Joint Aircraft Service Component (JASC)
position. J to A1–1P4–18, from PL14P1–E to A45P3– Code: 2900: Hydraulic Power.
(vii) If the TRSVO indication stays in the 5, from PL14P1–D to PL1P3-q, and from
closed position, replace the tail shutoff valve. PL14P2–T to A2–1P3–34. If there is no (i) Material Incorporated by Reference
(3) Perform an operational test of the PCM continuity, repair or replace the defective (1) The Director of the Federal Register
2 flight control shut-off valve as described in wiring. approved the incorporation by reference of
the Compliance Instructions, paragraphs 5.1. (7) If the HYD PRESS and 1 SERVO caution the service information listed in this
through 5.5., of Agusta Bollettino Tecnico messages remain illuminated, replace the paragraph under 5 U.S.C. 552(a) and 1 CFR
No. 139–269, dated September 30, 2011 (BT Number 1 hydraulic control panel. part 51.
139–269). (ii) If the 1 HYD PRESS caution message (2) You must use this service information
(i) If the 2 SERVO caution message is is illuminated, the HYD 1 pressure indication as applicable to do the actions required by
asabaliauskas on DSK3SPTVN1PROD with RULES

illuminated: is more than 190 bar (2,755 lbf/sq in), and the this AD, unless the AD specifies otherwise.
(A) On the hydraulic control panel, lift the SOV1 shutoff valve is in the open position, (i) Agusta Bollettino Tecnico No. 139–269,
guard of the SOV1/SOV2 switch and set it to replace the pressure switch on the Number dated September 30, 2011.
SOV2 (closed position). Make sure that the 2 1 PCM. (ii) Reserved.
HYD PRESS caution message and the HYD 2 (iii) If the closure of SOV 1 is indicated on (3) For Agusta service information
PRESS warning light on the hydraulic control the MFD hydraulic synoptic page, before identified in this final rule, contact
panel are illuminated. further flight, replace the Number 1 PCM. AgustaWestland, Product Support
(B) Reset the SOV1/SOV2 switch to the (4) Perform an operational test of the Engineering, Via del Gregge, 100, 21015
open position. emergency landing gear shutoff valve as Lonate Pozzolo (VA) Italy, ATTN: Maurizio

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Document Created: 2018-02-14 09:13:33
Document Modified: 2018-02-14 09:13:33
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final rule.
Dates		This AD is effective January 31, 2017.
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]
FR Citation		81 FR 94946
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
81 FR 94946 - Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 248 (December 27, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
