12838 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus Helicopters: Docket No. FAA–2015– 

6033; Directorate Identifier 2015–SW– 

019–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model AS 365 N3 helicopters, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

missing or incorrectly located information for 

exiting a helicopter. This condition could 

result in failure to jettison cabin doors during 

an emergency, resulting in death or injury of 

helicopter occupants. 

(c) Comments Due Date 

We must receive comments by May 10, 

2016. 

(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) Inspect the cabin and cockpit for labels, 

placards, and markings that provide jettison 

procedure instructions for cabin doors. 

(2) For the left and right side, remove any 

existing label, placard, and marking and 

install placards in accordance with the 

Accomplishment Instructions, paragraph 

3.B.2 and Figures 1 through 6, of Airbus 

Helicopters Alert Service Bulletin No. 

AS365–11.00.02, Revision 2, dated April 23, 

2015. 

(f) Credit for Previously Completed Actions 

Actions accomplished before the effective 

date of this AD in accordance with Airbus 

Helicopters Modification (MOD) 0711B68 for 

helicopters without external life rafts or MOD 

0711B68 and MOD 0711B67 for helicopters 

with external life rafts are considered 

acceptable for compliance with this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: David Hatfield, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9–ASW– 

FTW–AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2015–0068–E, dated April 29, 2015. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov by searching for 

and locating it in Docket No. FAA–2015– 

6033. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 1100, Placards and Markings. 

Issued in Fort Worth, Texas, on February 

29, 2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–05369 Filed 3–10–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

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 

matt.wilbanks@faa.gov. 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 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 shutoff valve would require about 2 workhours, and required parts would cost 

about $7,512, for a cost per helicopter of 

$7,682. 

Replacing the number 2 hydraulic 

control panel would require about 2 

work-hours, and required parts would 

cost about $8,165, for a cost per 

helicopter of $8,335. 

Replacing the number 1 hydraulic 

module would require about 4 workhours, and required parts would cost 

about $87,137, for a cost per helicopter 

of $87,477. 

Replacing a PCM pressure switch 

would require about 2 work-hours, and 

required parts would cost about $6,974, 

for a cost per helicopter of $7,144. 

Repairing the electrical wiring would 

require about 2 work-hours, and 

required parts would cost about $45, for 

a cost per helicopter of $215. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
12840 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Agustawestland S.P.A. (Agusta): Docket No. 

FAA–2016–4278; Directorate Identifier 

2012–SW–022–AD. 

(a) Applicability 

This AD applies to Agusta Model AB139 

and AW139 helicopters, all serial numbers 

except serial number 31007, 31094, 31293, 

31301, 31303, 31313, and 31329, certificated 

in any category. 

(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; 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12841 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(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-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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25513; Directorate 

Identifier 99–NE–61–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2006–18– 

14 that applies to all Rolls-Royce 

Deutschland Ltd & Co KG (RRD) Tay 

650–15 and Tay 651–54 turbofan 

engines. AD 2006–18–14 requires 

calculating and re-establishing the 

cyclic life of stage 1 high-pressure 

turbine (HPT) disks, part number (P/N) 

JR32013 and P/N JR33838, and stage 1 

low-pressure turbine (LPT) disk, P/N 

JR32318A. This proposed AD would 

require re-calculating the cyclic life, and 

would impose a reduced cyclic life, of 

stage 1 HPT disk, P/N JR32013. We are 

proposing this AD to prevent failure of 

stage 1 HPT disks, P/N JR32013 and P/ 

N JR33838, and stage 1 LPT disk, P/N 

JR32318A, which could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 10, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49–0–33– 

7086–1064; fax: 49–0–33–7086–3276. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 1200 District Avenue, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

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–2006– 

25513; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

mandatory continuing airworthiness 

information, regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–25513; Directorate Identifier 

99–NE–61–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 30, 2006, we issued AD 

2006–18–14, Amendment 39–14753 (71 

FR 52988, September 8, 2006), for all 

RRD Tay 650–15 and Tay 651–54 

turbofan engines. AD 2006–18–14 

requires calculating and re-establishing 

the cyclic life of stage 1 HPT disks, P/ 

N JR32013 and P/N JR33838, and stage 

1 LPT disk, P/N JR32318A, that have 

been exposed to different engine flight 

plan profiles. AD 2006–18–14 also 

requires removing from service, using a 

drawdown schedule, those stage 1 HPT 

disks and stage 1 LPT disks operated 

under Tay 650–15 engine flight plan 

profiles A, B, C, or D; or operated under 

the Tay 651–54 engine datum flight 

profile, at reduced cyclic life limits. AD 

2006–18–14 resulted from RRD 

updating their low-cycle-fatigue 

analysis for stage 1 HPT disks and stage 

1 LPT disks and reducing their cyclic 

life limits. We issued AD 2006–18–14 to 

prevent cracks leading to turbine disk 

failure, which could result in an 

uncontained engine failure and damage 

to the airplane. 

Actions Since AD 2006–18–14 Was 

Issued 

Since we issued AD 2006–18–14, RRD 

reviewed the cyclic life limit of parts 

affected by AD 2006–18–14; RRD 

concluded that the stage 1 HPT disk, P/ 

N JR32013, requires further cyclic life 

limit reduction. RRD did not further 

reduce the cyclic life limit of stage 1 

HPT disk, P/N JR33838, or stage 1 LPT 

disk, P/N JR32318A. Accordingly, the 

cyclic life limits of stage 1 HPT disk, P/ 

N JR33838, and stage 1 LPT disk, P/N 

JR32318A, as imposed by AD 2006–18– 

14, remain unchanged in this proposed 

AD. 

Since AD 2006–18–14 was issued, the 

European Aviation Safety Agency 

(EASA) issued AD 2015–0056, dated 

March 31, 2015 to reduce the cyclic life 

limits of the stage 1 HPT disk, P/N 

JR32013. 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS