Document ID: FAA-2016-4278-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: AgustaWestland S.p.A. (Agusta) Helicopters
Posted Date: 2016-12-27T05:00Z

[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 matt.wilbanks@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 11, 2016, at 81 FR 12838, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to certain serial-numbered 
Agusta Model AB139 and AW139 helicopters. The NPRM proposed to require, 
within 50 hours time-in-service (TIS), performing operational tests of 
the Number 1 and Number 2 hydraulic systems power control modules 
(PCMs), the tail shut-off valve, the PCM1 and PCM2 flight control shut-
off valves, and the emergency landing gear shut-off valve for correct 
functionality. Depending on the results of the operational checks, the 
NPRM proposed to require replacing a PCM, the tail shut-off valve, a 
flight control shut-off valve, the number 2 hydraulic control panel, 
the number 1 hydraulic module, the number 1 or number 2 PCM pressure 
switch, or repairing the electrical wiring. The proposed requirements 
were intended to prevent loss of hydraulic power to the flight controls 
and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2011-0207, dated October 20, 2011 
(AD No. 2011-0207), issued by EASA, which is the Technical Agent for 
the Member States of the European Union, to correct an unsafe condition 
for certain serial-numbered Agusta Model AB139 and AW139 helicopters. 
EASA advises that an accident involving a Model AW139 helicopter caused 
the tail rotor (T/R), the T/R gearbox, and part of the fin to detach 
from the aircraft, rupturing the hydraulic lines and draining all of 
the hydraulic fluid. According to EASA, an

[[Page 94947]]

assessment of the helicopter's hydraulic systems following the accident 
revealed that an operational check of the hydraulic systems is 
necessary to ensure its functionality. EASA advises that this 
condition, if not corrected, could lead, in the case of multiple 
failures, to loss of hydraulic power and subsequent loss of control of 
the helicopter. To address this, EASA AD No. 2011-0207 requires, within 
50 flight hours or 2 months, operational checks of the power control 
modules and shutoff valves and reporting the results to the 
manufacturer.

Comments

    After our NPRM (81 FR 12838, March 11, 2016) was published, we 
received comments from one commenter.

Request

    The commenter requested we not adopt the proposed AD, as it is 
unnecessary. The commenter stated that following the release of EASA AD 
No. 2011-0207 and Agusta Bollettino Tecnico No. 139-269, dated 
September 30, 2011 (BT 139-269), they already have a 600 hour/12 month 
inspection and operational check of the hydraulic systems as part of 
their maintenance program that covers all of the proposed actions in 
the NPRM. Finally, the commenter stated that the proposed AD would not 
change any of their maintenance procedures, but it would add an 
additional burden of required paper work for the same results.
    We disagree. EASA AD No. 2011-0207 is not mandatory for U.S. 
operators. Additionally, while an operator may incorporate the 
procedures described in BT 139-269 into its maintenance program, not 
all operators are required to do so. In order for the corrective 
actions in BT 139-269 to become mandatory, and to correct the unsafe 
condition identified in the NPRM, the FAA must issue an AD.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Italy and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Italy, EASA, its technical representative, 
has notified us of the unsafe condition described in the EASA AD. We 
are issuing this AD because we evaluated all information provided by 
EASA, reviewed the relevant information, considered the comment 
received, and determined the unsafe condition exists and is likely to 
exist or develop on other helicopters of these same type designs and 
that air safety and the public interest require adopting the AD 
requirements as proposed.

Differences Between This AD and the EASA AD

    The EASA AD requires reporting the results of the operational 
checks to Agusta, while this AD does not. The EASA AD also requires 
compliance within 50 flight-hours or 2 months, while this AD requires 
compliance within 50 hours TIS.

Related Service Information Under 1 CFR Part 51

    We reviewed BT 139-269 for Model AB139 and AW139 helicopters. BT 
139-269 contains procedures for conducting operational checks of both 
hydraulic systems to confirm correct functionality.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate this AD will affect 102 helicopters of U.S. Registry.
    Based on an average labor rate of $85 per hour, we estimate that 
operators may incur the following costs in order to comply with this 
AD. Performing the operational checks of the hydraulic systems requires 
about 2 work-hours for a total cost per helicopter of $170 and a total 
cost to U.S. operators of $17,340.
    If required, replacing a PCM will require about 3 work-hours and 
required parts will cost about $87,136, for a cost per helicopter of 
$87,391.
    If required, replacing a tail or flight control shut-off valve will 
require about 2 work-hours, and required parts will cost about $7,512, 
for a cost per helicopter of $7,682. If required, replacing the number 
2 hydraulic control panel will require about 2 work-hours, and required 
parts will cost about $8,165, for a cost per helicopter of $8,335.
    If required, replacing the number 1 hydraulic module will require 
about 4 work-hours, and required parts will cost about $87,137, for a 
cost per helicopter of $87,477.
    If required, replacing a PCM pressure switch will require about 2 
work-hours, and required parts will cost about $6,974, for a cost per 
helicopter of $7,144.
    If required, repairing the electrical wiring will require about 2 
work-hours, and required parts will cost about $45, for a cost per 
helicopter of $215.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on helicopters identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction; and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 94948]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-26-01 AGUSTAWESTLAND S.P.A. (AGUSTA): Amendment 39-18758; 
Docket No. FAA-2016-4278; Directorate Identifier 2012-SW-022-AD.

(a) Applicability

    This AD applies to Agusta Model AB139 and AW139 helicopters, all 
serial numbers except serial number 31007, 31094, 31293, 31301, 
31303, 31313, and 31329, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as an inoperative hydraulic 
shut-off valve, which could result in loss of hydraulic power and 
subsequent loss of control of the helicopter.

 (c) Effective Date

    This AD becomes effective January 31, 2017.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    Within 50 hours time-in service:
    (1) Perform an operational test of each Number 1 and Number 2 
power control module (PCM). If the fluid level in the reservoir 
changes more than 5mm (0.196 in) in an hour, replace the affected 
PCM.
    (2) Perform an operational test of each tail shut-off valve. If 
the 2 SERVO caution message is not illuminated and the UTIL SOV2 and 
TR SOV indications are in the open position:
    (i) Disconnect the Tail Shutoff valve connector, HP4P1.
    (ii) Disconnect the PCM2 connectors, A44P3 and A44P12.
    (iii) Disconnect the TB38 terminal board connector, TB38P1.
    (iv) Perform a continuity test from HP4P1-1 to A44P12-16, from 
HP4P1-2 to TB38P1-D, and from HP4P1-4 to A44P3-6.
    (v) If there is no continuity, repair or replace the defective 
wiring.
    (vi) If there is continuity, release the test lever of the PCM2 
to the DOWN NORM position.
    (vii) If the TRSVO indication stays in the closed position, 
replace the tail shutoff valve.
    (3) Perform an operational test of the PCM 2 flight control 
shut-off valve as described in the Compliance Instructions, 
paragraphs 5.1. through 5.5., of Agusta Bollettino Tecnico No. 139-
269, dated September 30, 2011 (BT 139-269).
    (i) If the 2 SERVO caution message is illuminated:
    (A) On the hydraulic control panel, lift the guard of the SOV1/
SOV2 switch and set it to SOV2 (closed position). Make sure that the 
2 HYD PRESS caution message and the HYD 2 PRESS warning light on the 
hydraulic control panel are illuminated.
    (B) Reset the SOV1/SOV2 switch to the open position.
    (C) If the 2 HYD PRESS and 2 SERVO caution messages remain 
illuminated:
    (1) Disconnect the PL14P1 and PL14P2 connectors from the 
hydraulic control panel.
    (2) Disconnect the A1-1P4 connector from the MAU1.
    (3) Disconnect the A2-1P3 connector from the MAU2.
    (4) Disconnect the A44P3 connector from the Number 2 PCM.
    (5) Disconnect the PL1P3 connector from the circuit breaker 
panel.
    (6) Perform a continuity test from PL14P1-J to A1-1P4-18, from 
PL14P1-D to PL1P3-q, from PL14P2-J to A44P3-5, and from PL14P2-T to 
A2-1P3-34. If there is no continuity, repair or replace the 
defective wiring.
    (7) If the HYD PRESS and 2 SERVO caution messages remain 
illuminated, replace the number 2 hydraulic power module.
    (ii) If the 2 HYD PRESS caution message is illuminated, the HYD 
2 pressure indication is more than 190 bar (2,755 lbf/sq in), and 
the SOV2 shutoff valve is in the open position, replace the pressure 
switch on the Number 2 PCM.
    (iii) If the closure of SOV 2 is indicated on the MFD hydraulic 
synoptic page, before further flight, replace the Number 2 PCM.
    (4) Perform an operational test of the PCM 1 flight control 
shut-off valve as described in the Compliance Instructions, 
paragraphs 6.1. through 6.4., of BT 139-269.
    (i) If the 1 SERVO caution message is illuminated:
    (A) On the hydraulic control panel, lift the guard of the SOV1/
SOV2 switch and set it to SOV1 (closed position). Make sure that the 
1 HYD PRESS caution message and the HYD 1 PRESS warning light on the 
hydraulic control panel are illuminated.
    (B) Reset the SOV1/SOV2 switch to the open position. If the 1 
HYD PRESS and 1 SERVO caution messages remain illuminated:
    (1) Disconnect the PL14P1 and PL14P2 connectors from the 
hydraulic control panel.
    (2) Disconnect the A1-1P4 connector from the MAU1.
    (3) Disconnect the A2-1P3 connector from the MAU2.
    (4) Disconnect the A45P3 connector from the Number 1 PCM.
    (5) Disconnect the PL1P3 connector from the circuit breaker 
panel.
    (6) Perform a continuity test from PL14P1-J to A1-1P4-18, from 
PL14P1-E to A45P3-5, from PL14P1-D to PL1P3-q, and from PL14P2-T to 
A2-1P3-34. If there is no continuity, repair or replace the 
defective wiring.
    (7) If the HYD PRESS and 1 SERVO caution messages remain 
illuminated, replace the Number 1 hydraulic control panel.
    (ii) If the 1 HYD PRESS caution message is illuminated, the HYD 
1 pressure indication is more than 190 bar (2,755 lbf/sq in), and 
the SOV1 shutoff valve is in the open position, replace the pressure 
switch on the Number 1 PCM.
    (iii) If the closure of SOV 1 is indicated on the MFD hydraulic 
synoptic page, before further flight, replace the Number 1 PCM.
    (4) Perform an operational test of the emergency landing gear 
shutoff valve as described in the Compliance Instructions, 
paragraphs 7.1. through 7.4., of BT 139-269.
    (i) If the EMERG L/G PRESS caution message is illuminated, the 
HYD 1 pressure indication is more than 190 bar (2,755 lbf/sq in), 
and the UTIL SOV1 (LDG GEAR EMER) shutoff valve is in the open 
position, replace the pressure switch on the Number 1 PCM.
    (ii) If the 1 HYD MIN caution message is illuminated, inspect 
the fluid level on the Number 1 PCM and inspect the Number 1 main 
hydraulic system for leaks.
    (A) If the fluid level is between the FULL and ADD marks, or if 
there are no hydraulic fluid leaks, perform an operational test of 
the level switches. If the 1 HYD MIN caution message is illuminated, 
replace the Number 1 PCM.
    (B) If there is a hydraulic fluid leak:
    (1) Replace all leaking parts and lines or repair the leak.
    (2) If the 1 HYD MIN caution message remains illuminated, 
perform an operational test of the level switches.
    (3) If the 1 HYD MIN caution message remains illuminated, 
replace the Number 1 PCM.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 
10101 Hillwood Parkway, Fort Worth, Texas 76177; telephone (817) 
222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that you 
notify your principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office or 
certificate holding district office, before operating any aircraft 
complying with this AD through an AMOC.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2011-0207, dated October 20, 2011. You may view 
the EASA AD on the Internet at 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