81 FR 12838 - Airworthiness Directives; AgustaWestland S.p.A. (Agusta) Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 48 (March 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 48 (March 11, 2016)
| Page Range | 12838-12841 | |
| FR Document | 2016-05368 |
[Federal Register Volume 81, Number 48 (Friday, March 11, 2016)] [Proposed Rules] [Pages 12838-12841] From the Federal Register Online [www.thefederalregister.org] [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 http://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 http://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 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 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 [email protected]. [[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 [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. 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
![12838 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
3. Will not affect intrastate aviation in AS365–11.00.02, Revision 2, dated April 23, Agusta Model AB139 and AW139
Alaska to the extent that it justifies 2015. helicopters. This proposed AD would
making a regulatory distinction; and (f) Credit for Previously Completed Actions require performing operational checks
4. Will not have a significant of both hydraulic systems. This
Actions accomplished before the effective
economic impact, positive or negative, date of this AD in accordance with Airbus proposed AD is prompted by an
on a substantial number of small entities Helicopters Modification (MOD) 0711B68 for assessment of the hydraulic systems of
under the criteria of the Regulatory helicopters without external life rafts or MOD the helicopter following an accident.
Flexibility Act. 0711B68 and MOD 0711B67 for helicopters The proposed actions are intended to
We prepared an economic evaluation with external life rafts are considered prevent loss of hydraulic power to the
of the estimated costs to comply with acceptable for compliance with this AD. flight controls and subsequent loss of
this proposed AD and placed it in the (g) Alternative Methods of Compliance control of the helicopter.
AD docket. (AMOCs) DATES: We must receive comments on
List of Subjects in 14 CFR Part 39 (1) The Manager, Safety Management this proposed AD by May 10, 2016.
Group, FAA, may approve AMOCs for this ADDRESSES: You may send comments by
Air transportation, Aircraft, Aviation AD. Send your proposal to: David Hatfield, any of the following methods:
safety, Incorporation by reference, Aviation Safety Engineer, Safety Management • Federal eRulemaking Docket: Go to
Safety. Group, Rotorcraft Directorate, FAA, 10101 http://www.regulations.gov. Follow the
The Proposed Amendment Hillwood Pkwy, Fort Worth, TX 76177; online instructions for sending your
telephone (817) 222–5110; email 9–ASW– comments electronically.
Accordingly, under the authority FTW–AMOC-Requests@faa.gov. • Fax: 202–493–2251.
delegated to me by the Administrator, (2) For operations conducted under a 14 • Mail: Send comments to the U.S.
the FAA proposes to amend 14 CFR part CFR part 119 operating certificate or under
Department of Transportation, Docket
39 as follows: 14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or Operations, M–30, West Building
lacking a principal inspector, the manager of Ground Floor, Room W12–140, 1200
PART 39—AIRWORTHINESS
the local flight standards district office or New Jersey Avenue SE., Washington,
DIRECTIVES
certificate holding district office before DC 20590–0001.
■ 1. The authority citation for part 39 operating any aircraft complying with this • Hand Delivery: Deliver to the
continues to read as follows: AD through an AMOC. ‘‘Mail’’ address between 9 a.m. and 5
(h) Additional Information
p.m., Monday through Friday, except
Authority: 49 U.S.C. 106(g), 40113, 44701. Federal holidays.
The subject of this AD is addressed in the
§ 39.13 [Amended] European Aviation Safety Agency (EASA) AD Examining the AD Docket
■ 2. The FAA amends § 39.13 by adding No. 2015–0068–E, dated April 29, 2015. You You may examine the AD docket on
the following new airworthiness may view the EASA AD on the Internet at
http://www.regulations.gov by searching for
the Internet at http://
directive (AD): www.regulations.gov by searching for
and locating it in Docket No. FAA–2015–
Airbus Helicopters: Docket No. FAA–2015– 6033. and locating Docket number FAA–
6033; Directorate Identifier 2015–SW– 2016–4278 or in person at the Docket
019–AD. (i) Subject Operations Office between 9 a.m. and 5
(a) Applicability Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except
Code: 1100, Placards and Markings. Federal holidays. The AD docket
This AD applies to Airbus Helicopters
Model AS 365 N3 helicopters, certificated in Issued in Fort Worth, Texas, on February contains this proposed AD, the
any category. 29, 2016. European Aviation Safety Agency
Scott A. Horn, (EASA) AD, the economic evaluation,
(b) Unsafe Condition any comments received, and other
Acting Manager, Rotorcraft Directorate,
This AD defines the unsafe condition as Aircraft Certification Service. information. The street address for the
missing or incorrectly located information for Docket Operations Office (telephone
[FR Doc. 2016–05369 Filed 3–10–16; 8:45 am]
exiting a helicopter. This condition could 800–647–5527) is in the ADDRESSES
result in failure to jettison cabin doors during BILLING CODE 4910–13–P
section. Comments will be available in
an emergency, resulting in death or injury of
helicopter occupants. the AD docket shortly after receipt.
DEPARTMENT OF TRANSPORTATION For service information identified in
(c) Comments Due Date this proposed rule, contact
We must receive comments by May 10, Federal Aviation Administration AgustaWestland, Product Support
2016. Engineering, Via del Gregge, 100, 21015
(d) Compliance 14 CFR Part 39 Lonate Pozzolo (VA) Italy, ATTN:
Maurizio D’Angelo; telephone 39–0331–
You are responsible for performing each [Docket No. FAA–2016–4278; Directorate
664757; fax 39 0331–664680; or at
action required by this AD within the Identifier 2012–SW–022–AD]
specified compliance time unless it has
http://www.agustawestland.com/
already been accomplished prior to that time. RIN 2120–AA64 technical-bulletins. You may review the
referenced service information at the
(e) Required Actions Airworthiness Directives; FAA, Office of the Regional Counsel,
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Within 50 hours time-in-service: AgustaWestland S.p.A. (Agusta) Southwest Region, 10101 Hillwood
(1) Inspect the cabin and cockpit for labels, Helicopters Parkway, Fort Worth, Texas 76177.
placards, and markings that provide jettison FOR FURTHER INFORMATION CONTACT: Matt
procedure instructions for cabin doors. AGENCY: Federal Aviation
Administration (FAA), DOT. Wilbanks, Aviation Safety Engineer,
(2) For the left and right side, remove any
existing label, placard, and marking and ACTION: Notice of proposed rulemaking Safety Management Group, Rotorcraft
install placards in accordance with the (NPRM). Directorate, FAA, 10101 Hillwood
Accomplishment Instructions, paragraph Parkway, Fort Worth, Texas 76177;
3.B.2 and Figures 1 through 6, of Airbus SUMMARY: We propose to adopt a new telephone (817) 222–5110; email
Helicopters Alert Service Bulletin No. airworthiness directive (AD) for certain matt.wilbanks@faa.gov.
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![12840 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules
For the reasons discussed, I certify module (PCM). If the fluid level in the (A) On the hydraulic control panel, lift the
this proposed regulation: reservoir changes more than 5mm (0.196 in) guard of the SOV1/SOV2 switch and set it to
1. Is not a ‘‘significant regulatory in an hour, replace the affected PCM. SOV1 (closed position). Make sure that the 1
action’’ under Executive Order 12866; (2) Perform an operational test of each tail HYD PRESS caution message and the HYD 1
2. Is not a ‘‘significant rule’’ under the shut-off valve. If the 2 SERVO caution PRESS warning light on the hydraulic control
message is not illuminated and the UTIL panel are illuminated.
DOT Regulatory Policies and Procedures SOV2 and TR SOV indications are in the (B) Reset the SOV1/SOV2 switch to the
(44 FR 11034, February 26, 1979); open position: open position. If the 1 HYD PRESS and 1
3. Will not affect intrastate aviation in (i) Disconnect the Tail Shutoff valve SERVO caution messages remain
Alaska to the extent that it justifies connector, HP4P1. illuminated:
making a regulatory distinction; and (ii) Disconnect the PCM2 connectors, (1) Disconnect the PL14P1 and PL14P2
4. Will not have a significant A44P3 and A44P12. connectors from the hydraulic control panel.
economic impact, positive or negative, (iii) Disconnect the TB38 terminal board (2) Disconnect the A1–1P4 connector from
on a substantial number of small entities connector, TB38P1. the MAU1.
under the criteria of the Regulatory (iv) Perform a continuity test from HP4P1– (3) Disconnect the A2–1P3 connector from
1 to A44P12–16, from HP4P1–2 to TB38P1– the MAU2.
Flexibility Act. D, and from HP4P1–4 to A44P3–6. (4) Disconnect the A45P3 connector from
We prepared an economic evaluation (v) If there is no continuity, repair or the Number 1 PCM.
of the estimated costs to comply with replace the defective wiring. (5) Disconnect the PL1P3 connector from
this proposed AD and placed it in the (vi) If there is continuity, release the test the circuit breaker panel.
AD docket. lever of the PCM2 to the DOWN NORM (6) Perform a continuity test from PL14P1–
position. J to A1–1P4–18, from PL14P1–E to A45P3–
List of Subjects in 14 CFR Part 39 (vii) If the TRSVO indication stays in the 5, from PL14P1–D to PL1P3-q, and from
Air transportation, Aircraft, Aviation closed position, replace the tail shutoff valve. PL14P2–T to A2–1P3–34. If there is no
safety, Incorporation by reference, (3) Perform an operational test of the PCM continuity, repair or replace the defective
Safety. 2 flight control shut-off valve as described in wiring.
the Compliance Instructions, paragraphs 5.1. (7) If the HYD PRESS and 1 SERVO caution
The Proposed Amendment through 5.5., of Agusta Bollettino Tecnico messages remain illuminated, replace the
Accordingly, under the authority No. 139–269, dated September 30, 2011 (BT Number 1 hydraulic control panel.
139–269). (ii) If the 1 HYD PRESS caution message
delegated to me by the Administrator,
(i) If the 2 SERVO caution message is is illuminated, the HYD 1 pressure indication
the FAA proposes to amend 14 CFR part illuminated: is more than 190 bar (2,755 lbf/sq in), and the
39 as follows: (A) On the hydraulic control panel, lift the SOV1 shutoff valve is in the open position,
guard of the SOV1/SOV2 switch and set it to replace the pressure switch on the Number
PART 39—AIRWORTHINESS SOV2 (closed position). Make sure that the 2 1 PCM.
DIRECTIVES HYD PRESS caution message and the HYD 2 (iii) If the closure of SOV 1 is indicated on
PRESS warning light on the hydraulic control the MFD hydraulic synoptic page, before
■ 1. The authority citation for part 39 panel are illuminated. further flight, replace the Number 1 PCM.
continues to read as follows: (B) Reset the SOV1/SOV2 switch to the (4) Perform an operational test of the
Authority: 49 U.S.C. 106(g), 40113, 44701. open position. emergency landing gear shutoff valve as
(C) If the 2 HYD PRESS and 2 SERVO described in the Compliance Instructions,
§ 39.13 [Amended] 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
the MAU1. in), and the UTIL SOV1 (LDG GEAR EMER)
Agustawestland S.P.A. (Agusta): Docket No. (3) Disconnect the A2–1P3 connector from shutoff valve is in the open position, replace
FAA–2016–4278; Directorate Identifier the MAU2. the pressure switch on the Number 1 PCM.
2012–SW–022–AD. (4) Disconnect the A44P3 connector from (ii) If the 1 HYD MIN caution message is
(a) Applicability the Number 2 PCM. illuminated, inspect the fluid level on the
(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-q, and ADD marks, or if there are no hydraulic
31301, 31303, 31313, and 31329, certificated 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
(b) Unsafe Condition continuity, repair or replace the defective message is illuminated, replace the Number
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
(c) Comments Due Date is illuminated, the HYD 2 pressure indication remains illuminated, perform an operational
We must receive comments by May 10, is more than 190 bar (2,755 lbf/sq in), and the test of the level switches.
2016. SOV2 shutoff valve is in the open position, (3) If the 1 HYD MIN caution message
replace the pressure switch on the Number remains illuminated, replace the Number 1
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(d) Compliance 2 PCM. PCM.
You are responsible for performing each (iii) If the closure of SOV 2 is indicated on
the MFD hydraulic synoptic page, before (f) Alternative Methods of Compliance
action required by this AD within the
further flight, replace the Number 2 PCM. (AMOCs)
specified compliance time unless it has
already been accomplished prior to that time. (4) Perform an operational test of the PCM (1) The Manager, Safety Management
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,
Within 50 hours time-in service: through 6.4., of BT 139–269. Aviation Safety Engineer, Safety Management
(1) Perform an operational test of each (i) If the 1 SERVO caution message is Group, Rotorcraft Directorate, FAA, 10101
Number 1 and Number 2 power control illuminated: Hillwood Parkway, Fort Worth, Texas 76177;
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![Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12841
telephone (817) 222–5110; email 9-ASW- DATES: We must receive comments on comments on the overall regulatory,
FTW-AMOC-Requests@faa.gov. this proposed AD by May 10, 2016. economic, environmental, and energy
(2) For operations conducted under a 14 aspects of this proposed AD. We will
CFR part 119 operating certificate or under ADDRESSES: You may send comments,
14 CFR part 91, subpart K, we suggest that using the procedures found in 14 CFR consider all comments received by the
you notify your principal inspector, or 11.43 and 11.45, by any of the following closing date and may amend this
lacking a principal inspector, the manager of methods: proposed AD because of those
the local flight standards district office or • Federal eRulemaking Portal: Go to comments.
certificate holding district office before http://www.regulations.gov. Follow the
operating any aircraft complying with this We will post all comments we
instructions for submitting comments. receive, without change, to http://
AD through an AMOC.
• Fax: 202–493–2251. www.regulations.gov, including any
(g) Additional Information • Mail: U.S. Department of personal information you provide. We
The subject of this AD is addressed in Transportation, Docket Operations, M– will also post a report summarizing each
European Aviation Safety Agency (EASA) AD 30, West Building Ground Floor, Room substantive verbal contact we receive
No. 2011–0207, dated October 20, 2011. You W12–140, 1200 New Jersey Avenue SE.,
may view the EASA AD on the Internet at about this proposed AD.
Washington, DC 20590.
http://www.regulations.gov in Docket No. • Hand Delivery: Deliver to Mail Discussion
FAA-2016–4278.
address above between 9 a.m. and 5
(h) Subject p.m., Monday through Friday, except On August 30, 2006, we issued AD
Joint Aircraft Service Component (JASC) Federal holidays. 2006–18–14, Amendment 39–14753 (71
Code: 2900: Hydraulic Power. For service information identified in FR 52988, September 8, 2006), for all
this proposed AD, contact Rolls-Royce RRD Tay 650–15 and Tay 651–54
Issued in Fort Worth, Texas, on March 3, turbofan engines. AD 2006–18–14
2016. Deutschland Ltd & Co KG, Eschenweg
11, Dahlewitz, 15827 Blankenfelde- requires calculating and re-establishing
Scott A. Horn,
Mahlow, Germany; phone: 49–0–33– the cyclic life of stage 1 HPT disks, P/
Acting Manager, Rotorcraft Directorate, N JR32013 and P/N JR33838, and stage
Aircraft Certification Service.
7086–1064; fax: 49–0–33–7086–3276.
You may view this service information 1 LPT disk, P/N JR32318A, that have
[FR Doc. 2016–05368 Filed 3–10–16; 8:45 am] at the FAA, Engine & Propeller been exposed to different engine flight
BILLING CODE 4910–13–P Directorate, 1200 District Avenue, plan profiles. AD 2006–18–14 also
Burlington, MA. For information on the requires removing from service, using a
availability of this material at the FAA, drawdown schedule, those stage 1 HPT
DEPARTMENT OF TRANSPORTATION call 781–238–7125. disks and stage 1 LPT disks operated
Federal Aviation Administration Examining the AD Docket under Tay 650–15 engine flight plan
profiles A, B, C, or D; or operated under
You may examine the AD docket on the Tay 651–54 engine datum flight
14 CFR Part 39
the Internet at http:// profile, at reduced cyclic life limits. AD
[Docket No. FAA–2006–25513; Directorate www.regulations.gov by searching for 2006–18–14 resulted from RRD
Identifier 99–NE–61–AD] and locating Docket No. FAA–2006– updating their low-cycle-fatigue
RIN 2120–AA64 25513; or in person at the Docket analysis for stage 1 HPT disks and stage
Management Facility between 9 a.m. 1 LPT disks and reducing their cyclic
Airworthiness Directives; Rolls-Royce and 5 p.m., Monday through Friday, life limits. We issued AD 2006–18–14 to
Deutschland Ltd & Co KG Turbofan except Federal holidays. The AD docket prevent cracks leading to turbine disk
Engines contains this proposed AD, the failure, which could result in an
mandatory continuing airworthiness uncontained engine failure and damage
AGENCY: Federal Aviation
information, regulatory evaluation, any to the airplane.
Administration (FAA), DOT.
comments received, and other
ACTION: Notice of proposed rulemaking information. The address for the Docket Actions Since AD 2006–18–14 Was
(NPRM). Office (phone: 800–647–5527) is in the Issued
SUMMARY: We propose to supersede ADDRESSES section. Comments will be
available in the AD docket shortly after Since we issued AD 2006–18–14, RRD
airworthiness directive (AD) 2006–18–
receipt. reviewed the cyclic life limit of parts
14 that applies to all Rolls-Royce
FOR FURTHER INFORMATION CONTACT:
affected by AD 2006–18–14; RRD
Deutschland Ltd & Co KG (RRD) Tay
Philip Haberlen, Aerospace Engineer, concluded that the stage 1 HPT disk, P/
650–15 and Tay 651–54 turbofan
Engine Certification Office, FAA, Engine N JR32013, requires further cyclic life
engines. AD 2006–18–14 requires
& Propeller Directorate, 1200 District limit reduction. RRD did not further
calculating and re-establishing the
Avenue, Burlington, MA 01803; phone: reduce the cyclic life limit of stage 1
cyclic life of stage 1 high-pressure
turbine (HPT) disks, part number (P/N) 781–238–7770; fax: 781–238–7199; HPT disk, P/N JR33838, or stage 1 LPT
JR32013 and P/N JR33838, and stage 1 email: philip.haberlen@faa.gov. disk, P/N JR32318A. Accordingly, the
low-pressure turbine (LPT) disk, P/N cyclic life limits of stage 1 HPT disk, P/
SUPPLEMENTARY INFORMATION:
JR32318A. This proposed AD would N JR33838, and stage 1 LPT disk, P/N
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
require re-calculating the cyclic life, and Comments Invited JR32318A, as imposed by AD 2006–18–
would impose a reduced cyclic life, of We invite you to send any written 14, remain unchanged in this proposed
stage 1 HPT disk, P/N JR32013. We are relevant data, views, or arguments about AD.
proposing this AD to prevent failure of this proposed AD. Send your comments Since AD 2006–18–14 was issued, the
stage 1 HPT disks, P/N JR32013 and P/ to an address listed under the European Aviation Safety Agency
N JR33838, and stage 1 LPT disk, P/N ADDRESSES section. Include ‘‘Docket No. (EASA) issued AD 2015–0056, dated
JR32318A, which could result in an FAA–2006–25513; Directorate Identifier March 31, 2015 to reduce the cyclic life
uncontained engine failure and damage 99–NE–61–AD’’ at the beginning of your limits of the stage 1 HPT disk, P/N
to the airplane. comments. We specifically invite JR32013.
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Document Created: 2016-03-11 01:50:52
Document Modified: 2016-03-11 01:50:52
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 10, 2016. | |
| 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 12838 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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