18626 Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0363; Directorate 

Identifier 2013–NM–031–AD; Amendment 

39–17769; AD 2014–04–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200, –300 and –200 

Freighter series airplanes; and Model 

A340–200, –300, –500, and –600 series 

airplanes. This AD was prompted by a 

report that an airplane equipped with 

Angle of Attack (AOA) sensors installed 

with conic plates recently experienced 

blockage of all sensors during climb, 

leading to autopilot disconnection and 

activation of the alpha protection 

(Alpha Prot) when Mach number was 

increased. This AD requires, for certain 

airplanes, revising the airplane flight 

manual (AFM) to advise the flightcrew 

of emergency procedures for addressing 

AOA sensor blockage. This AD also 

requires replacing the AOA sensor conic 

plates with AOA sensor flat plates, 

which is a terminating action for the 

AFM revision. We are issuing this AD 

to prevent reduced control of the 

airplane. 

DATES: This AD becomes effective May 

8, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 8, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0363; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–227–1138; fax: 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to all Airbus Model 

A330–200, –300 and –200 Freighter 

series airplanes; and Model A340–200, 

–300, –500, and –600 series airplanes. 

The SNPRM published in the Federal 

Register on October 2, 2013 (78 FR 

60798). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM), which published in the 

Federal Register on May 3, 2013 (78 FR 

25902). The SNPRM was prompted by a 

report that an airplane equipped with 

AOA sensors installed with conic plates 

recently experienced blockage of all 

sensors during climb, leading to 

autopilot disconnection and activation 

of the alpha protection (Alpha Prot) 

when Mach number was increased. The 

NPRM and the SNPRM both proposed to 

revise the airplane flight manual (AFM) 

to advise the flightcrew of emergency 

procedures for addressing AOA sensor 

blockage, for certain airplanes. The 

NPRM and the SNPRM also proposed to 

require replacing the AOA sensor conic 

plates with AOA sensor flat plates, 

which is a terminating action for the 

AFM revision. We are issuing this AD 

to prevent reduced control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0023, 

dated February 1, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

An A330 aeroplane experienced a blockage 

of all Angle of Attack (AOA) probes during 

climb leading to Autopilot (AP) 

disconnection and activation of the alpha 

protection (Alpha Prot) when Mach number 

increased. 

Analysis showed that this aeroplane was 

equipped with AOA probes having conic 

plates, and it is suspected that these plates 

might have contributed to the event. 

Investigations are on-going to determine the 

root cause of this AOA probes blockage. The 

AOA conic plates can also be installed on 

A340 aeroplanes. 

These AOA conic plates could have been 

installed in production through Airbus 

modification (mod.) 201609, associated to 

Thales Avionics AOA probes Part Number 

(P/N) C16291AA and P/N C16291AB, or 

mod. 201610, associated to Goodrich AOA 

probes P/N 0861ED, or in service through 

Airbus Service Bulletin (SB) A330–34–3255 

or SB A340–34–4250 or SB A340–34–5081. 

The blockage of two or three AOA probes 

of the same angle may cause the Alpha Prot 

of the normal law to activate. 

Under normal flight conditions (in normal 

law), if the Alpha Prot activates and Mach 

number increases, the flight control laws 

order a pitch down of the aeroplane that the 

flight crew may not be able to counteract 

with a sidestick deflection, even in the full 

backward position. 

This condition, if not corrected, could 

result in reduced control of the aeroplane. 

To address this condition, Airbus 

developed a ‘‘Blocked AOA probes’’ 

emergency procedure included in Airbus 

Airplane Flight Manual (AFM) A330 

Temporary Revision (TR) TR293 issue 1 and 

Airbus AFM A340 TR294 issue 1. 

Consequently, EASA issued Emergency AD 

2012–0258–E to require amendment of the 

AFM to ensure that flight crews, in case of 

AOA probe blockage, apply the applicable 

emergency procedure. 

Since that [EASA] AD was issued, Airbus 

published approved instructions to re-install 

AOA probe flat plates on A330/A340 family 

aeroplanes. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

[Emergency] AD 2012–0258–E which is 

superseded, and requires installation of AOA 

probe flat plates, after which the AFM 

operational procedure must be removed. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0363- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The following presents the comment 

received on the proposal (78 FR 60798, 

October 2, 2013) and the FAA’s 

response to each comment. 

Request To Reduce Compliance Times 

Airbus asked that we reduce the 

compliance time of 5 months, as 

specified in paragraphs (h) and (i) of the 

SNPRM (78 FR 60798, October 2, 2013), 

to 10 weeks. Airbus stated that, taking 

into account that this AD was delayed 

due to issuance of an SNPRM, and that 

the terminating action required by 

EASA AD 2013–0023, dated February 1, 

2013 (http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0363- 

0002), was already completed, it 


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Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 18627 

recommends a 10-week compliance 

time for the actions in those paragraphs. 

We acknowledge the commenter’s 

recommendation to reduce the 

compliance time specified in the 

SNPRM (78 FR 60798, October 2, 2013) 

to 10 weeks. While there might be merit 

to reducing the compliance time in this 

AD, the suggested reduction would 

make the actions currently required by 

this AD more restrictive, so additional 

rulemaking would be necessary. We 

find that further delaying this action 

would be inappropriate in light of the 

identified unsafe condition. Therefore, 

we have not changed this final rule in 

this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

60798, October 2, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 60798, 

October 2, 2013). 

Costs of Compliance 

We estimate that this AD affects 64 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

AFM revision ................................................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $5,440 

Replacement of certain AOA sensor conic 

plates.

7 work-hours × $85 per hour = $595 ............. 0 595 38,080 

Modification of installations of certain AOA 

sensor flat plates.

5 work-hours × $85 per hour = $425 ............. 0 425 27,200 

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 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0363; 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 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. 

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 

■ 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 AD: 

2014–04–10 Airbus: Amendment 39–17769. 

Docket No. FAA–2013–0363; Directorate 

Identifier 2013–NM–031–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 8, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

all manufacturer serial numbers. 

(2) Model A340–211, –212, –213, –311, 

–312, –313, –541, and –642 airplanes, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34: Navigation. 

(e) Reason 

This AD was prompted by a report that an 

airplane equipped with Angle of Attack 

(AOA) sensors installed with conic plates 

recently experienced blockage of all sensors 

during climb, leading to autopilot 

disconnection and activation of the alpha 

protection (Alpha Prot) when Mach number 

was increased. We are issuing this AD to 

prevent reduced control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 


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18628 Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 

(g) Airplane Flight Manual Revision 

For airplanes identified in paragraphs 

(g)(1) and (g)(2) of this AD, except as 

provided by paragraph (j) of this AD: Within 

10 days after the effective date of this AD, 

revise the Emergency Procedures of the 

Airbus A330 and A340 Airplane Flight 

Manuals (AFMs), by incorporating Airbus 

A330 Temporary Revision TR293, Issue 1.0, 

dated December 4, 2012; or Airbus A340 

Temporary Revision TR294, Issue 1.0, dated 

December 4, 2012; as applicable; to advise 

the flightcrew of emergency procedures for 

addressing AOA sensor blockage. This can be 

done by inserting Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; 

into the applicable AFM. When the 

information in Airbus A330 Temporary 

Revision TR293, Issue 1.0, dated December 4, 

2012; or Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012; is 

included in the general revisions of the 

applicable AFM, the general revisions may be 

incorporated into the AFM, and the 

temporary revisions may be removed. 

(1) Model A330–201, –202, –203, –223, 

223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes, 

all manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A330–34–3255 has 

been embodied in service. 

(2) Model A340–211, –212, –213, –311, 

–312, –313, –541, and –642 airplanes, all 

manufacturer serial numbers, on which 

Airbus modification 201609 or 201610 has 

been embodied in production; or on which 

Airbus Service Bulletin A340–34–4250 or 

A340–34–5081 has been embodied in service. 

(h) Replacement 

Except as provided by paragraph (j) of this 

AD: Within 5 months after the effective date 

of this AD, replace all AOA sensor conic 

plates having part number (P/N) 

F3411060200000 or P/N F3411060900000 

with an applicable AOA sensor flat plate 

identified in paragraph (h)(1) or (h)(2) of this 

AD. Performing this replacement constitutes 

terminating action for the AFM revision 

required by paragraph (g) of this AD; and 

Airbus A330 Temporary Revision TR293, 

Issue 1.0, dated December 4, 2012, and 

Airbus A340 Temporary Revision TR294, 

Issue 1.0, dated December 4, 2012, to the 

Airbus A330 and A340 AFMs, as applicable, 

must be removed from the AFM before 

further flight after doing the replacement. 

(1) Replace with a flat plate having P/N 

F3411007920200 or P/N F3411007920300, as 

applicable, in accordance with the applicable 

service information specified in paragraph 

(h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A330–34–3293, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(ii) Airbus Mandatory Service Bulletin 

A340–34–4273, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(iii) Airbus Mandatory Service Bulletin 

A340–34–5093, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(2) Replace with a flat plate having P/N 

F3411007920000 or P/N F3411007920100, in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) or its delegated agent. 

(i) Modification of Installation 

For airplanes on which any AOA sensor 

conic plate has been replaced with an AOA 

sensor flat plate, in accordance with the 

applicable service information specified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD: 

Within 5 months after the effective date of 

this AD, modify the installation of the AOA 

sensor flat plates so that the plates are flush 

with the fuselage, in accordance with the 

applicable service information identified in 

paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of 

this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–34–3293, including Appendix 01, 

dated January 31, 2013. 

(2) Airbus Mandatory Service Bulletin 

A340–34–4273, including Appendix 01, 

dated January 30, 2013. 

(3) Airbus Mandatory Service Bulletin 

A340–34–5093, including Appendix 01, 

dated January 30, 2013. 

(j) Exception to the Requirements of 

Paragraphs (g) and (h) of this AD 

For airplanes on which Airbus 

modification 203285 (improved AOA flat 

plate protection treatment) has been 

embodied in production: The actions 

specified in paragraphs (g) and (h) of this AD 

are not required, provided that, since first 

flight, no AOA probe conic plate having P/ 

N F3411060200000 or P/N F3411060900000 

has been installed. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, an AOA 

sensor conic plate having P/N 

F3411060200000 or P/N F3411060900000 or 

an AOA protection cover having P/N 

98D34203003000. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2013–0023, dated 

February 1, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0363-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) 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) Airbus A330 Temporary Revision 

TR293, Issue 1.0, dated December 4, 2012, to 

the Airbus A330 Airplane Flight Manual 

(AFM). 

(ii) Airbus A340 Temporary Revision 

TR294, Issue 1.0, dated December 4, 2012, to 

the Airbus A340 Airplane Flight Manual 

(AFM). 

(iii) Airbus Mandatory Service Bulletin 

A330–34–3293, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(iv) Airbus Mandatory Service Bulletin 

A340–34–4273, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(v) Airbus Mandatory Service Bulletin 

A340–34–5093, Revision 01, including 

Appendix 01, dated June 12, 2013. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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/ibrlocations.html. 


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Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 18629 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–07235 Filed 4–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1202; Directorate 

Identifier 2012–NE–38–AD; Amendment 39– 

17816; AD 2014–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2012–26– 

14 for all Rolls-Royce Deutschland Ltd 

& Co KG (RRD) BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1– 

30 turbofan engines. AD 2012–26–14 

required removal from service of certain 

high-pressure (HP) compressor stages 1 

to 6 rotor disc assemblies before 

exceeding certain thresholds. This AD 

requires removal from service at those 

same thresholds but restricts the 

applicability to engines exposed to 

silver-plated nuts, and removes the 

terminating action statement required 

by AD 2012–26–14. This AD was 

prompted by RRD development of a new 

silver-free nut that, if installed with a 

new HP compressor stages 1 to 6 rotor 

disc assembly, would correct the unsafe 

condition identified in AD 2012–26–14. 

We are issuing this AD to prevent 

failure of the HP compressor stages 1 to 

6 rotor disc assembly, which could lead 

to an uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective May 8, 2014. 

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–2012– 

1202; 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 AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7154; fax: (781) 238– 

7199; email: robert.c.morlath@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–26–14, 

Amendment 39–17309 (78 FR 2195, 

January 10, 2013), (‘‘AD 2012–26–14’’). 

AD 2012–26–14 applied to the specified 

products. The NPRM published in the 

Federal Register on November 19, 2013 

(78 FR 69316). The NPRM proposed to 

continue to require removal from 

service of certain HP compressor stages 

1 to 6 rotor disc assemblies before 

exceeding certain thresholds. The 

NPRM also proposed to restrict the 

applicability to engines exposed to 

silver-plated nuts, and to remove the 

terminating action statement required 

by AD 2012–26–14. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Include a Mandatory 

Terminating Action 

RRD requested that we include the 

installation of a new HP compressor 

stages 1 to 6 rotor disc assembly with 

silver-free nuts, part number (P/N) 

U755872, as a necessary terminating 

action to the parts removal requirements 

of this AD, because this would eliminate 

the unsafe condition caused by silver 

nut corrosion. 

We disagree. The flight cycle limits 

imposed by this AD on engines 

operating with silver-plated nuts 

provide an acceptable level of safety. 

Requiring operators to purchase a new 

HP compressor stages 1 to 6 rotor disc 

assembly and new silver-free nuts 

would be an undue economic burden. If 

an operator chooses to install a new HP 

compressor stages 1 to 6 rotor disc 

assembly and silver-free nuts, P/N 

U755872, this AD would no longer 

apply to that engine. We did not change 

this AD. 

Request To Require the Replacement of 

Affected P/Ns at Listed Intervals 

RRD requested that instead of 

requiring a one-time replacement of the 

HP compressor stages 1 to 6 rotor disc 

assembly installed with silver-plated 

nuts, we require replacement of the 

P/Ns at intervals published in European 

Aviation Safety Agency (EASA) AD 

2012–0230, Initial Issue, dated October 

30, 2012. 

We disagree. Our proposed AD did 

not require a one-time replacement. 

This AD requires, for any HP 

compressor stages 1 to 6 rotor disc 

assembly that has ever been installed 

with silver-plated nuts, replacement at 

the cyclic limits stated in paragraphs 

(e)(1) and (e)(2) of this AD, which are 

equivalent to the cyclic limits stated in 

EASA AD 2012–0230, Initial Issue, 

dated October 30, 2012. We did not 

change this AD. 

Request To Update Service Information 

References to the Most Recent Versions 

RRD requested that we update 

references to service bulletins (SBs) to 

the most recent versions. 

We disagree. We do not reference any 

SBs in this AD. We did not change this 

AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 255 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 20 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Prorated parts life 

will cost about $13,500 per engine. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$3,876,000. 

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 


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