8134 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

14 ‘‘Interagency Guidance Regarding Unfair or 

Deceptive Credit Practices’’ (Aug. 22, 2014). 

http://www.federalreserve.gov/newsevents/press/

bcreg/bcreg20140822a2.pdf. 

15One state chartered bank commenter did not 

address the proposed repeal, but objected to 

examiners’ citations of banks for unfair or deceptive 

practices in the supervisory process. Two 

individual commenters did not address the 

proposed repeal of Regulation AA. 

16https://www.federalreserveconsumerhelp.gov/. 

17 5 U.S.C. 601 et seq. 

18See section 1092(2) of the Dodd-Frank Act. 

Currency in issuing interagency 

guidance stating that, depending on the 

facts and circumstances, a depository 

institution might violate the prohibition 

against unfair or deceptive practices in 

the FTC Act and the Dodd-Frank Act if 

it engages in the practices prohibited by 

the former credit practices rules.14

II. Discussion 

Fourteen commenters responded to 

the proposed repeal of Regulation AA. 

Three individual commenters stated 

that Regulation AA was a necessary and 

helpful regulation; two of these 

commenters stated that the Board’s 

reasons for repealing the regulation 

were unclear. A comment letter received 

from seven consumer advocate 

organizations acknowledged that the 

Board’s repeal of Regulation AA was 

required by the Dodd-Frank Act. In their 

letter, these commenters also provided 

recommendations to the Bureau 

regarding acts or practices that the 

Bureau now has to authority to regulate 

if it finds they are unfair or deceptive.15

Eight commenters addressed the 

interagency guidance that was issued 

simultaneously with the proposed 

repeal of Regulation AA. One individual 

commenter believed the guidance 

would discourage banks from engaging 

in unfair or deceptive acts or practices, 

but seven consumer advocate 

commenters recommended 

strengthening the guidance language. 

The consumer advocate commenters 

also recommended that the Board issue 

additional guidance regarding other acts 

or practices that the commenters believe 

should be declared unfair or deceptive 

acts or practices. 

The Board is finalizing the repeal of 

Regulation AA as proposed. As the 

Board discussed in the Proposed Rule, 

the Dodd-Frank Act eliminated the 

Board’s rule writing authority under the 

FTC Act, which nullified the regulation. 

The Board will continue to monitor 

developments with respect to unfair or 

deceptive acts or practices and assess 

whether to issue additional supervisory 

guidance. 

The repeal of Regulation AA also 

eliminates Subpart A of the regulation, 

which generally describes the internal 

procedures used by the Board in 

handling consumer complaints. The 

Board did not receive comment on the 

removal of these internal procedures 

from the Code of Federal Regulations. 

Information about how the Board 

processes consumer complaints is 

provided on the Board’s public Web 

site.16

III. Final Regulatory Flexibility 

Analysis 

The Regulatory Flexibility Act 17

(RFA) generally requires an agency to 

perform an assessment of the impact a 

rule is expected to have on small 

entities. Based on its analysis, and for 

the reasons stated below, the Board 

believes that this final rule will not have 

a significant economic impact on a 

substantial number of small entities. 

1. Statement of the need for, and 

objectives of, the final rule. Regulation 

AA was issued pursuant to section 

18(f)(1) of the FTC Act. As noted above, 

the Dodd-Frank Act repealed this 

provision of the FTC Act.18

Accordingly, the Board is repealing its 

Regulation AA. 

2. Summary of issues raised by 

comments in response to the initial 

regulatory flexibility analysis. The 

Board did not receive any comments on 

the initial regulatory flexibility analysis. 

3. Small entities affected by the final 

rule. The final rule repeals Regulation 

AA, which was issued pursuant to 

section 18(f)(1) of the FTC. As a result 

of the FTC Act amendments made by 

the Dodd-Frank Act, the Board no 

longer has rule writing authority under 

section 18(f)(1). The legislative repeal of 

the Board’s rulemaking authority 

nullified the provisions in Regulation 

AA that were issued pursuant to that 

authority. Consequently, the Board’s 

repeal of the regulation, which no 

longer has legal effect, will not affect 

any entity, including any small entity. 

The repeal of Regulation AA will also 

remove information about how the 

Board processes consumer complaints 

from the Code of Federal Regulations. 

This is not expected to have an effect on 

small entities because that information 

is provided on the Board’s public Web 

site. 

4. Recordkeeping, reporting, and 

compliance requirements. The final rule 

repeals Regulation AA and therefore 

does not impose any recordkeeping, 

reporting, or compliance requirements 

on any entities. 

5. Significant alternatives to the final 

revisions. Because the repeal of 

Regulation AA will have no impact, 

there are no alternatives that would 

further minimize the economic impact 

of the final rule on small entities. 

IV. Paperwork Reduction Act 

In accordance with the Paperwork 

Reduction Act (PRA) of 1995 (44 U.S.C. 

3506; 5 CFR 1320 Appendix A.1), the 

Board reviewed the rule under the 

authority delegated to the Federal 

Reserve by the Office of Management 

and Budget (OMB). The final rule 

contains no requirements subject to the 

PRA. 

List of Subjects in 12 CFR Part 227 

Banks, Banking, Consumer protection, 

Credit, Federal Reserve System, 

Finance. 

Authority and Issuance 

For the reasons set forth in the 

preamble, and under the authority of 

section 1092(2) of Public Law 111–203, 

124 Stat. 1376 (Jul. 21, 2010), the Board 

amends 12 CFR chapter II by removing 

part 227. 

PART 227—[REMOVED] 

By order of the Board of Governors of the 

Federal Reserve System, February 11, 2016. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2016–03228 Filed 2–17–16; 8:45 am] 

BILLING CODE–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0467; Directorate 

Identifier 2016–NM–008–AD; Amendment 

39–18395; AD 2016–04–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–26– 

02 for all Airbus Model A330–200, 

A330–200 Freighter, and A330–300 

series airplanes; and Airbus Model 

A340–200, A340–300, A340–500, and 

A340–600 series airplanes. AD 2015– 

26–02 required, for certain airplanes, 

identification of the part number, serial 

number, and standard of the ram air 

turbine (RAT) pump, RAT module, RAT 

actuator, and RAT lower gearbox 

assembly; replacement of the balance 


wgreen on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 8135 

weight screw, modification of the 

actuator coil spring, modification of the 

actuator, an inspection of the anti-stall 

valve for correct installation in the RAT 

pump housing; and corrective actions if 

necessary. For certain other airplanes, 

AD 2015–26–02 required reidentification or replacement of the RAT 

module. This new AD requires the same 

actions as AD 2015–26–02. This new 

AD was prompted by a report of a 

typographical error in the regulatory 

text of AD 2015–26–02. We are issuing 

this AD to prevent loss of the impeller 

function and RAT pump pressurization 

capability, which, if preceded by a total 

engine flame-out, could result in loss of 

control of the airplane. 

DATES: This AD becomes effective 

March 4, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 2, 2016 (80 FR 81174, 

December 29, 2015). 

We must receive comments on this 

AD by April 4, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this final rule, 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.A330A340@

airbus.com; Internet http://

www.airbus.com. 

For Hamilton Sundstrand service 

information identified in this final rule, 

contact Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 

Harrison Avenue, P.O. Box 7002, 

Rockford, IL 61125–7002; telephone 

860–654–3575; fax 860–998–4564; email 

tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0467. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0467; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the 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. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 9, 2015, we issued AD 

2015–26–02, Amendment 39–18350 (80 

FR 81174, December 29, 2015) (‘‘AD 

2015–26–02’’). AD 2015–26–02 applied 

to all Airbus Model A330–200, A330– 

200 Freighter, and A330–300 series 

airplanes; and Airbus Model A340–200, 

A340–300, A340–500, and A340–600 

series airplanes. AD 2015–26–02 was 

prompted by a report indicating that, 

during a production flight test, the RAT 

did not pressurize the green hydraulic 

system. AD 2015–26–02 required for 

certain airplanes, identification of the 

part number, serial number, and 

standard of the RAT pump, RAT 

module, RAT actuator, and RAT lower 

gearbox assembly; replacement of the 

balance weight screw, modification of 

the actuator coil spring, modification of 

the actuator, an inspection of the antistall valve for correct installation in the 

RAT pump housing; and corrective 

actions if necessary. For certain other 

airplanes, AD 2015–26–02 required reidentification or replacement of the RAT 

module. We issued AD 2015–26–02 to 

prevent loss of the impeller function 

and RAT pump pressurization 

capability, which, if preceded by a total 

engine flame-out, could result in loss of 

control of the airplane. 

Since we issued AD 2015–26–02, we 

received a report of a typographical 

error in the regulatory text of AD 2015– 

26–02. Paragraph (m) of AD 2015–26–02 

inadvertently referred to paragraph (n) 

and should have referred to paragraph 

(o), ‘‘Parts Installation Prohibition.’’ 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0274, dated November 

15, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes; and 

Airbus Model A340–200, A340–300, 

A340–500, and A340–600 series 

airplanes. The MCAI states: 

During a production flight test of an A330– 

300 aeroplane, the Ram Air Turbine (RAT) 

did not pressurize the green hydraulic 

system. Investigation revealed that the 

impeller drive (hex) shaft had a reduced 

length of engagement with the pump drive 

shaft. This caused the impeller drive shaft to 

disengage from the pump and disconnect the 

impeller. It was determined that the 

disconnection was the result of internal hex 

dimensions on the pump impeller shaft, 

which had been changed in a manufacturing 

drawing. From the investigation analysis, it 

was possible to identify a list of affected 

parts. 

This condition, if not detected and 

corrected, could lead to the loss of impeller 

function and RAT pump pressurization 

capability, possibly resulting, in case of total 

engine flame out, to the loss of control of the 

aeroplane. 

To address this unsafe condition, a new 

design RAT pump shaft has been developed 

with a decreased hexagonal shaft housing 

depth, which increases the hexagonal drive 

shaft engagement in the impeller shaft to 

carry the impeller torque. Airbus issued 

Service Bulletin (SB) A330–29–3122, SB 

A340–29–4093 and SB A340–29–5021 to 

provide instructions for in-service 

replacement of the affected RAT hydraulic 

pumps, or re-identification of the RAT pump 

and complete RAT module, as applicable. 

For the reasons described above, this 

[EASA] AD requires identification and 

replacement [modification] or reidentification of all affected RAT hydraulic 

pumps on A330 and A340–200/300 

aeroplanes, and replacement [modification] 

of all affected RAT modules on A340–500/ 

–600 aeroplanes. 

For affected pumps, the required 

actions also include concurrent actions, 

as applicable, including replacement of 

the balance weight screw, modification 

of the actuator coil spring, modification 

of the actuator, an inspection of the antistall valve for correct installation in the 

RAT pump housing and re-installation 

if necessary. For affected pumps, 

corrective actions include replacement 

of the RAT hydraulic pump, and reidentification of the part number of the 


wgreen on DSK2VPTVN1PROD with RULES
8136 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

RAT module. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0467. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012. 

• Airbus Service Bulletin A340–29– 

4093, dated October 25, 2012. 

This service information describes 

procedures for identifying the part 

number, serial number, and standard of 

the RAT pump, RAT module, RAT 

actuator, and RAT lower gearbox 

assembly; replacing the balance weight 

screw, modifying the actuator coil 

spring, modifying the actuator, and 

doing an inspection of the anti-stall 

valve for correct installation; and reidentifying the part numbers of the RAT 

hydraulic pump and RAT module. 

Airbus also issued Service Bulletin 

A330–29–3126, dated June 12, 2014; 

and Service Bulletin A340–29–4097, 

dated June 12, 2014, which describe 

procedures for identifying the part 

number and serial number of the RAT 

actuator; modifying the RAT actuators; 

and re-identifying the part numbers of 

the RAT module. 

In addition, Airbus issued Service 

Bulletin A340–29–5021, dated October 

2, 2012; and Service Bulletin A340–29– 

5025, dated June 16, 2014, which 

describe procedures for replacing 

(modifying) the RAT module. 

Hamilton Sundstrand has issued 

Service Bulletin ERPS06M–29–19, dated 

August 6, 2012, which identifies the 

serial numbers of the suspect hydraulic 

pump. 

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. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

FAA’s Determination of the Effective 

Date 

We are superseding AD 2015–26–02 

to correct a typographical error in the 

regulatory text. No other changes have 

been made to AD 2015–26–02. 

Therefore, we determined that notice 

and opportunity for prior public 

comment are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2016–0467; 

Directorate Identifier 2016–NM–008– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 66 

airplanes of U.S. registry. 

We also estimate that it will take 

about 14 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $78,540, or $1,190 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 18 work-hours and require parts 

costing up to $427,301, for a cost of 

$428,831 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

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. 

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 

removing airworthiness directive (AD) 

2015–26–02, Amendment 39–18350 (80 

FR 81174, December 29, 2015), and 

adding the following new AD: 

2016–04–01 Airbus: Amendment 39–18395; 

Docket No. FAA–2016–0467; Directorate 

Identifier 2016–NM–008–AD. 

(a) Effective Date 

This AD becomes effective March 4, 2016. 


wgreen on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 8137 

(b) Affected ADs 

(1) This AD replaces AD 2015–26–02, 

Amendment 39–18350 (80 FR 81174, 

December 29, 2015). 

(2) This AD affects AD 2012–21–19, 

Amendment 39–17235 (77 FR 65812, October 

31, 2012); and AD 2012–21–20, Amendment 

39–17236 (77 FR 65799, October 31, 2012). 

(c) Applicability 

This AD applies to all Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD, all 

manufacturer serial numbers. 

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

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

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

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

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Reason 

This AD was prompted by a report 

indicating that, during a production flight 

test, the ram air turbine (RAT) did not 

pressurize the green hydraulic system. We 

are issuing this AD to prevent loss of the 

impeller function and RAT pump 

pressurization capability, which, if preceded 

by a total engine flame-out, could result in 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of RAT Components 

For Airbus Model A330–201, –202, –203, 

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

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes: Except as 

provided by paragraph (i) of this AD, within 

36 months after the effective date of this AD, 

identify the part number, serial number, and 

standard (through the mod-dots) of the RAT 

pump, RAT module, RAT actuator, and RAT 

lower gearbox assembly, in accordance with 

the Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (g)(1) and (g)(2) of 

this AD. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number, serial 

number, and standard can be conclusively 

determined from that review. 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes: Airbus Service Bulletin A330–29– 

3122, dated October 25, 2012. 

(2) For Airbus Model A340–211, –212, 

–213, –311, –312, and –313 airplanes: Airbus 

Service Bulletin A340–29–4093, dated 

October 25, 2012. 

(h) Corrective and Concurrent Actions 

If the serial number of the RAT hydraulic 

pump is included in table 7, ‘‘Suspect 

Hydraulic Pump Serial Numbers,’’ of 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012: 

Within 36 months after the effective date of 

this AD, do all applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD. Prior to or concurrently 

with doing the corrective actions required by 

this paragraph, do the actions specified in 

paragraphs (h)(1) through (h)(4) of this AD, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3122, dated October 25, 2012 (for Model 

A330–200, –200 Freighter, and –300 series 

airplanes); or Airbus Service Bulletin A340– 

29–4093, dated October 25, 2012 (for Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes). 

(1) Replace the balance weight screw. 

(2) Modify the actuator coil spring. 

(3) Modify the actuator. 

(4) Do a general visual inspection of the 

anti-stall valve for correct installation in the 

RAT pump housing, and if any incorrect 

installation is found, before further flight, 

correctly install the anti-stall valve. 

(i) Exception to Service Information 

Specifications 

Airbus Service Bulletin A330–29–3122, 

dated October 25, 2012 (for Model A330–200, 

–200 Freighter, and –300 series airplanes), 

refers to Hamilton Sundstrand Service 

Bulletin ‘‘EPRPS06M–29–13’’ as an 

additional source of guidance for doing 

certain actions required by paragraph (h) of 

this AD. The first ‘‘P’’ in the citation should 

have been omitted; the correct reference is to 

Hamilton Sundstrand Service Bulletin 

‘‘ERPS06M–29–13.’’ 

(j) Re-Identification of Part Numbers 

If the serial number of the RAT hydraulic 

pump is not included in table 7, ‘‘Suspect 

Hydraulic Pump Serial Numbers,’’ of 

Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012: 

Within 36 months after the effective date of 

this AD, re-identify the part numbers of the 

RAT hydraulic pump and RAT module, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1) 

and (g)(2) of this AD. 

(k) Service Information for Optional Actions 

Accomplishment of the actions required by 

paragraphs (g), (h), and (j) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

29–3126, dated June 12, 2014; or Airbus 

Service Bulletin A340–29–4097, dated June 

12, 2014, as applicable, constitutes 

compliance with the requirements of 

paragraphs (g), (h), and (j) of this AD. 

(l) RAT Module Replacement (Modification) 

For Airbus Model A340–541 and –642 

airplanes having RAT module part number 

(P/N) 772722D, 772722E, 772722F, or 

772722G: Within 36 months after the 

effective date of this AD, replace (modify) the 

RAT module, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–29–5021, dated 

October 2, 2012. As an option, 

accomplishment of the RAT module 

replacement (modification), in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A340–29–5025, 

dated June 16, 2014, constitutes compliance 

with the requirement of this paragraph. 

(m) Exception to Paragraphs (g), (h), and (j) 

of This AD 

The actions required by paragraphs (g), (h), 

and (j) of this AD are not required for 

airplanes on which Airbus Modification 

202537 was embodied in production, 

provided it can be determined that, since the 

airplane’s first flight, no RAT hydraulic 

pump or RAT module having a part number 

identified in paragraph (o) of this AD is 

installed on that airplane. 

(n) Terminating Action for Certain 

Requirements of Other ADs 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes: 

Accomplishment of the actions required by 

paragraphs (g), (h), and (j) of this AD 

constitutes compliance with the 

requirements of paragraphs (g)(1) and (g)(2) 

of AD 2012–21–19, Amendment 39–17235 

(77 FR 65812, October 31, 2012); and 

paragraphs (g)(1) and (g)(2) of AD 2012–21– 

20, Amendment 39–17236 (77 FR 65799, 

October 31, 2012). 

(2) For Airbus Model A340–541 and –642 

airplanes: Accomplishment of the actions 

required by paragraph (l) of this AD 

constitutes compliance with the 

requirements of paragraphs (h)(1) and (h)(2) 

of AD 2012–21–20, Amendment 39–17236 

(77 FR 65799, October 31, 2012). 

(o) Parts Installation Prohibition 

(1) For Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and A340–211, –212, –213, –311, 

–312, and –313 airplanes: After modification 

of the RAT module as required by paragraph 

(h) of this AD, no person may install any 

complete RAT module having a part number 

identified in paragraph (o)(1)(i) of this AD, or 

any RAT hydraulic pump having the part 

number identified in paragraph (o)(1)(ii) of 

this AD, on any airplane. 

(i) RAT module P/N 766351, 768084, 

770379, 770952, 770952A, 770952B, 

1702934, 1702934A, or 1702934B. 

(ii) RAT hydraulic pump P/N 5909522 

(Parker P/N 4207902). 

(2) For Airbus Model A340–541 and –642 

airplanes: After modification of the RAT 

module as required by paragraph (l) of this 

AD, no person may install any complete RAT 

module having P/N 772722D, 772722E, 

772722F, or 772722G, on any airplane. 

(p) 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 


wgreen on DSK2VPTVN1PROD with RULES
8138 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0274, dated 

November 15, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2016–0467. 

(r) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on February 2, 2016 (80 FR 

81174, December 29, 2015). 

(i) Airbus Service Bulletin A330–29–3122, 

dated October 25, 2012. 

(ii) Airbus Service Bulletin A330–29–3126, 

dated June 12, 2014. 

(iii) Airbus Service Bulletin A340–29– 

4093, dated October 25, 2012. 

(iv) Airbus Service Bulletin A340–29– 

4097, dated June 12, 2014. 

(v) Airbus Service Bulletin A340–29–5021, 

dated October 2, 2012. 

(vi) Airbus Service Bulletin A340–29– 

5025, dated June 16, 2014. 

(vii) Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012. 

(4) For Airbus 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. 

(5) For Hamilton Sundstrand service 

information identified in this AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, IL 61125– 

7002; telephone 860–654–3575; fax 860–998– 

4564; email tech.solutions@hs.utc.com; 

Internet http://

www.hamiltonsundstrand.com. 

(6) 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. 

(7) 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. 

Issued in Renton, Washington, on February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03215 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3630; Directorate 

Identifier 2014–NM–253–AD; Amendment 

39–18397; AD 2016–04–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 747–400F 

series airplanes. This AD was prompted 

by an analysis of the production 

methods used to increase fatigue 

resistance of the upper closure fittings at 

the nose cargo door portal’s C–3 frame, 

which showed that cracking could start 

too early to be caught in a timely 

manner by the inspection or 

maintenance program. This AD requires 

inspections of the upper closure fitting 

and connected strap and doubler at the 

nose cargo door portal for cracking, and 

related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct such cracking, 

which could result in sudden 

decompression and loss of the airplane’s 

structural integrity. 

DATES: This AD is effective March 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3630. 

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–2015– 

3630; 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 address for the 

Docket Office (phone: 800–647–5527) is 

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 20590. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

747–400F series airplanes. The NPRM 

published in the Federal Register on 

September 15, 2015 (80 FR 55273) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report indicating that an analysis of 

the production methods used to 

increase fatigue resistance of the upper 

closure fittings at the nose cargo door 

portal’s C–3 frame showed that cracking 

could start too early to be caught in a 

timely manner by the inspection or 

maintenance program. The upper 

closure fittings used in the nose cargo 

door portal C–3 frame were shot peened 

to increase fatigue resistance. However, 

an analysis showed that the increase in 


wgreen on DSK2VPTVN1PROD with RULES