83648 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

(h) Dispute resolution. A requester 

seeking to engage in dispute resolution 

may make a request to the FOIA Public 

Liaison and/or OGIS by following the 

procedures set forth online in the FDIC’s 

FOIA Service Center at http://

www.fdic.gov. 

(i) * * * 

(2) A person whose initial request for 

records under this section, or whose 

request for a waiver of fees under 

paragraph (f)(1)(x) of this section, has 

been denied, either in part or in whole, 

has the right to appeal the denial to the 

FDIC’s General Counsel (or designee) 

within 90 calendar days after receipt of 

notification of the denial. Appeals of 

denials of initial requests or for a waiver 

of fees must be in writing and include 

any additional information relevant to 

consideration of the appeal. 

* * * * * 

Dated at Washington, DC, this 15th day of 

November, 2016. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Valerie J. Best, 

Assistant Executive Secretary. 

[FR Doc. 2016–27961 Filed 11–21–16; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3701; Directorate 

Identifier 2015–NM–015–AD; Amendment 

39–18689; AD 2016–21–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–25– 

08 for all Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. AD 2013–25–08 required a 

repetitive inspection program on certain 

check valves in the hydraulic systems 

that includes, among other things, 

inspections for lock wire presence and 

integrity, traces of seepage or black 

deposits, proper torque, alignment of 

the check valve and manifold, 

installation of new lock wire, and 

corrective actions if needed. This new 

AD removes airplanes from the 

applicability, and requires modifying 

the green, blue, and yellow high 

pressure hydraulic manifolds by 

replacing certain check valves with 

improved check valves, which 

terminates the repetitive inspections 

required by this AD. This AD was 

prompted by multiple reports of 

hydraulic line check valves loosening. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective December 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 31, 2014 (78 FR 

78694, December 27, 2013). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of December 14, 2009 (74 FR 

62208, November 27, 2009). 

ADDRESSES: For 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.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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2016–3701. 

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– 

3701; 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 (telephone 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: 

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 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013) (‘‘AD 2013–25– 

08’’). AD 2013–25–08 applied to all 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on February 25, 2016 

(81 FR 9374) (‘‘the NPRM’’). The NPRM 

was prompted by multiple reports of 

hydraulic line check valves loosening. 

The NPRM proposed to continue to 

require a repetitive inspection program 

on certain check valves in the hydraulic 

systems that includes, among other 

things, inspections for lock wire 

presence and integrity, traces of seepage 

or black deposits, proper torque, 

alignment of the check valve and 

manifold, installation of new lock wire, 

and corrective actions if needed. The 

NPRM also proposed to add airplanes to 

the applicability, and require modifying 

the green, blue, and yellow high 

pressure hydraulic manifolds by 

replacing certain check valves with 

improved check valves, which would 

terminate the repetitive inspections 

required by the proposed AD. We are 

issuing this AD to detect and correct 

hydraulic check valve loosening; 

loosened valves could result in 

hydraulic leaks, possibly leading to the 

loss of all three hydraulic systems and 

consequent loss of control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0009, dated January 16, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

An A330 operator experienced a Yellow 

hydraulic circuit low level due to a loose 

check valve, Part Number (P/N) CAR401. 

During the inspection on the other two 

hydraulic systems, the other three check 

valves P/N CAR401 were also found to be 

loose with their lock wire broken in two 

instances. Airbus A340 aeroplanes are also 

equipped with P/N CAR401 high pressure 

manifold check valves. 

Additional cases of P/N CAR401 check 

valve loosening have been reported on 

aeroplanes having accumulated more than 

1,000 flight cycles (FC). The check valve 

fitted on the Yellow hydraulic system is more 


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affected, due to additional system cycles 

induced by cargo door operation. 

This condition, if not detected and 

corrected, could result in hydraulic leaks, 

possibly leading to the loss of all three 

hydraulic systems and consequent loss of 

control of the aeroplane. 

To address this unsafe condition, EASA 

issued Emergency AD 2009–0223–E [which 

corresponds to FAA AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009)] to require an inspection 

programme to detect any check valve 

loosening and, if necessary, to apply the 

applicable corrective actions. 

EASA AD 2010–0145, which superseded 

EASA EAD 2009–0223–E retaining its 

requirements, was issued to expand the 

applicability to the newly certified models 

A330–223F and A330–243F. 

Prompted by further reported in-service 

events of check valve P/N CAR401 loosening 

before reaching the threshold of 700 FC, 

EASA AD 2011–0139, which superseded 

EASA AD 2010–0145, retaining its 

requirements, was issued to: 

—Extend the requirement to identify the P/ 

N CAR401 check valves to all aeroplanes, 

and 

—reduce the inspection threshold for 

aeroplanes fitted with check valve P/N 

CAR401, either installed in production 

through Airbus modification 54491, or 

installed in service through Airbus Service 

Bulletin (SB) A330–29–3101 or Airbus SB 

A340–29–4078. 

EASA AD 2012–0070, which superseded 

EASA AD 2011–0139, retaining its 

requirements, was issued to require an 

increased torque value of the check valve 

tightening and High Pressure (HP) manifold 

re-identification. 

Since EASA AD 2012–0070 was issued, 

additional in-service events have been 

reported on aeroplanes fitted with check 

valves on which the increased torque value 

had been applied. Based on those events, it 

has been concluded that the action to retorque the check valves with an increased 

value is not a satisfactory terminating action 

for addressing the issue of those check 

valves. 

To address that, EASA issued AD 2012– 

0244, which partially retained the 

requirements of EASA AD 2012–0070, which 

was superseded. Additionally, for aeroplanes 

equipped with P/N CAR401 on which the 

increased torque value had been applied, 

EASA AD 2012–0244 required repetitive 

inspections of the check valves and HP 

manifolds. Finally, EASA AD 2012–0244 also 

required application of a lower torque value 

when a check valve P/N CAR401 is installed 

on an aeroplane. 

Note: The reporting and the torque value 

increase requirements for check valves P/N 

CAR401 of EASA AD 2012–0070 were no 

longer part of EASA AD 2012–0244. 

EASA AD was revised to clarify which 

actions are required for P/N CAR401 check 

valves, depending on applied (or not) torque 

value. 

Since EASA AD 2012–0244R1 was issued, 

Airbus developed an improved check valve 

P/N CAR402, which is embodied in 

production through Airbus modification 

203972, and in service through associated 

Airbus SB A330–29–3125, or Airbus SB 

A340–29–4096, as applicable to aeroplane 

type. In addition, these SBs provide 

instructions about the torque value (between 

230 and 250 Nm) and re-identification of HP 

manifolds after check valve P/N CAR402 

installation. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0244R1, which is superseded, and 

requires the installation of check valves P/N 

CAR402 as terminating action to the 

repetitive inspections [and removes airplanes 

on which Airbus modification 203972 has 

been embodied from the applicability]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3701. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Support for the NPRM 

American Airlines (AAL) stated that it 

operates 24 airplanes that will be 

affected by the NPRM, and that it agrees 

with the need to accomplish Airbus 

Service Bulletin A330–29–3125 on these 

airplanes. 

Request To Reference Revised Service 

Information 

AAL requested that we revise the 

NPRM to reference Airbus Service 

Bulletin A330–29–3125, Revision 02, 

including Appendixes 01 and 02, dated 

January 21, 2016. AAL pointed out that 

this revision includes several 

corrections in the Accomplishment 

Instructions. 

We agree to reference the latest 

service information in this final rule. 

Since we issued the NPRM, Airbus has 

issued Airbus Service Bulletin A330– 

29–3125, Revision 03, including 

Appendixes 01 and 02, dated April 8, 

2016; and Service Bulletin A340–29– 

4096, Revision 02, including 

Appendixes 01 and 02, dated April 8, 

2016. This service information states 

that no additional work is required by 

these revisions for airplanes modified 

by any previous issue. We have revised 

paragraph (p) of this AD to reference 

this revised service information as 

appropriate sources of service 

information for accomplishing the 

actions required by that paragraph. We 

have also revised paragraph (s) of this 

AD by adding credit for actions required 

by paragraph (p) of this AD, if those 

actions were performed before the 

effective date of this AD using Airbus 

Service Bulletin A330–29–3125, 

Revision 02, including Appendixes 01 

and 02, dated January 21, 2016; or 

Airbus Service Bulletin A330–29–3125, 

Revision 01, including Appendixes 01 

and 02, dated July 30, 2015; or Airbus 

Service Bulletin A340–29–4096, 

Revision 01, including Appendixes 01 

and 02, dated July 30, 2015; as 

applicable. Additionally, we have 

reformatted paragraph (s) of this AD to 

improve readability; this change does 

not affect the intent or requirements of 

that paragraph. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A330–29–3125, Revision 03, including 

Appendixes 01 and 02, dated April 8, 

2016; and Service Bulletin A340–29– 

4096, Revision 02, including 

Appendixes 01 and 02, dated April 8, 

2016. This service information describes 

procedures for modifying the green, 

blue, and yellow high pressure 

hydraulic manifolds by replacing each 

check valve having P/N CAR401 with an 

improved check valve having P/N 

CAR402. These documents are distinct 

since they apply to different airplane 

models. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 88 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

The actions required by AD 2013–25– 

08, and retained in this AD take about 

10 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Based on these figures, the estimated 

cost of the actions that were required by 

AD 2013–25–08 is $850 per product. 

We also estimate that it would take 

about 32 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 


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per work-hour. Based on these figures, 

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

operators to be $239,360, or $2,720 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. We have no way 

of determining the number of aircraft 

that might need these actions. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all available costs in our 

cost estimate. 

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) 

2013–25–08, Amendment 39–17704 (78 

FR 78694, December 27, 2013), and 

adding the following new AD: 

2016–21–08 Airbus: Amendment 39–18689; 

Docket No. FAA–2016–3701; Directorate 

Identifier 2015–NM–015–AD. 

(a) Effective Date 

This AD is effective December 27, 2016. 

(b) Affected ADs 

This AD replaces AD 2013–25–08, 

Amendment 39–17704 (78 FR 78694, 

December 27, 2013) (‘‘AD 2013–25–08’’). 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, as 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 except those 

on which Airbus modification 203972 has 

been embodied in production. 

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

–312, and –313 airplanes, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic power. 

(e) Reason 

This AD was prompted by multiple reports 

of hydraulic line check valves loosening. We 

are issuing this AD to detect and correct 

hydraulic check valve loosening; loosened 

valves could result in hydraulic leaks, 

possibly leading to the loss of all three 

hydraulic systems and consequent loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–25–08, with no 

changes. Except for Model A330–223F and 

A330–243F airplanes: Do the actions 

required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) For airplanes that do not have Airbus 

Modification 54491 embodied in production, 

or Airbus Service Bulletin A330–29–3101 or 

Airbus Service Bulletin A340–29–4078 

embodied in service: Within 100 flight cycles 

or 28 days after December 14, 2009 (the 

effective date of AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009) (‘‘AD 2009–24–09’’)), 

whichever occurs first, inspect the check 

valves on the blue, green, and yellow 

hydraulic systems to identify their part 

numbers (P/Ns), in accordance with the 

instructions of Airbus All Operators Telex 

(AOT) A330–29A3111, Revision 1, dated 

October 8, 2009 (for Model A330–200 and 

–300 series airplanes); or Airbus AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Accomplishment of the inspection 

required by paragraph (h) of this AD 

terminates the requirements of this 

paragraph. 

(i) If check valves having P/N CAR401 are 

installed on all three hydraulic systems, 

before further flight, do the actions specified 

in paragraph (g)(2)(i) of this AD. After 

accomplishing the actions required by 

paragraph (g)(2)(i) of this AD, do the actions 

specified in paragraphs (g)(2)(ii) and 

(g)(2)(iii) of this AD at the applicable 

compliance times specified in those 

paragraphs. Accomplishment of the 

inspection required by paragraph (i) of this 

AD terminates the requirements of this 

paragraph. 

(ii) If check valves having P/N CAR401 are 

not installed on all three hydraulic systems, 

no further action is required by this 

paragraph until any check valve having P/N 

CAR400 is replaced with a check valve 

having P/N CAR401. If any check valve 

having P/N CAR400 is replaced by a check 

valve having P/N CAR401, before further 

flight, do the inspection specified in 

paragraph (g)(1) of this AD to determine if all 

three hydraulic systems are equipped with 

check valves having P/N CAR401. 

Accomplishment of the inspection required 

by paragraph (h) of this AD terminates the 

requirements of this paragraph. 

(2) For airplanes on which Airbus 

Modification 54491 was embodied in 

production, or Airbus Service Bulletin A330– 

29–3101; or Airbus Service Bulletin A340– 

29–4078 was embodied in service, do the 

actions specified in paragraphs (g)(2)(i), 

(g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Except as required by paragraph (g)(1)(i) 

of this AD, at the applicable times specified 

in paragraphs (g)(2)(i)(A) and (g)(2)(i)(B) of 

this AD, as applicable: Do the inspection 

program (detailed inspection of the lock wire 

for presence and integrity, a detailed 

inspection for traces of seepage or black 

deposits, and an inspection for proper 

torque) on yellow and blue high pressure 

manifolds, install new lock wires, and do all 

applicable corrective actions, in accordance 

with the instructions of paragraph 4.1.1 of 

Airbus AOT A330–29A3111, Revision 1, 

dated October 8, 2009 (for Model A330–200 

and –300 series airplanes); or Airbus AOT 

A340–29A4086, Revision 1, dated October 8, 


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2009 (for Airbus Model A340–200 and –300 

series airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection required by paragraph (h)(1) 

of this AD terminates the requirements of this 

paragraph. 

(A) For airplanes on which Airbus 

Modification 54491 has been embodied in 

production: At the later of the times specified 

in paragraphs (g)(2)(i)(A)(1) and (g)(2)(i)(A)(2) 

of this AD. 

(1) Before the accumulation of 1,000 total 

flight cycles since first flight but no earlier 

than the accumulation of 700 total flight 

cycles since first flight. 

(2) Within 100 flight cycles or 28 days after 

December 14, 2009 (the effective date of AD 

2009–24–09), whichever occurs first. 

(B) For airplanes on which Airbus Service 

Bulletin A330–29–3101 or Airbus Service 

Bulletin A340–29–4078 was embodied in 

service: At the later of the times specified in 

paragraphs (g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of 

this AD. 

(1) Within 1,000 flight cycles since the 

embodiment of Airbus Service Bulletin 

A330–29–3101 or Airbus Service Bulletin 

A340–29–4078 but no earlier than 700 flight 

cycles after the embodiment of Airbus 

Service Bulletin A330–29–3101 or Airbus 

Service Bulletin A340–29–4078. 

(2) Within 100 flight cycles or 28 days after 

December 14, 2009 (the effective date of AD 

2009–24–09), whichever occurs first. 

(ii) Within 900 flight hours after 

accomplishment of paragraph (g)(2)(i) of this 

AD, do the inspection program (detailed 

inspection of the lock wire for presence and 

integrity, a detailed inspection for traces of 

seepage or black deposits, and an inspection 

for proper torque) and install a new lock wire 

on the green high pressure manifold; and do 

an inspection (detailed inspection for traces 

of seepage or black deposits, and detailed 

inspection to determine alignment of the 

check valve and manifold) on the yellow and 

blue high pressure manifolds, and do all 

applicable corrective actions; in accordance 

with the instructions of paragraph 4.1.2 of 

Airbus AOT A330–29A3111, Revision 1, 

dated October 8, 2009 (for Model A330–200 

and –300 series airplanes); or Airbus AOT 

A340–29A4086, Revision 1, dated October 8, 

2009 (for Model A340–200 and –300 series 

airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection program required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

(iii) Within 900 flight hours after 

accomplishment of paragraph (g)(2)(ii) of this 

AD, and thereafter at intervals not to exceed 

900 flight hours, do the inspection program 

(detailed inspection for traces of seepage or 

black deposits, and detailed inspection to 

determine alignment of the check valve and 

manifold) on the green, yellow, and blue high 

pressure manifolds, and do all applicable 

corrective actions, in accordance with the 

instructions of paragraph 4.1.3 of Airbus 

AOT A330–29A3111, Revision 1, dated 

October 8, 2009 (for Model A330–200 and 

–300 series airplanes); or Airbus AOT A340– 

29A4086, Revision 1, dated October 8, 2009 

(for Model A340–200 and –300 series 

airplanes). Do all applicable corrective 

actions before further flight. Accomplishment 

of the inspection program required by 

paragraph (i) of this AD terminates the 

requirements of this paragraph. 

(h) Retained Inspection, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–25–08, with no 

changes. For airplanes equipped with check 

valves having P/N CAR400; and for airplanes 

equipped with check valves having P/N 

CAR401, except for airplanes on which 

Airbus Modification 201384 has been 

embodied during production, or on which 

Airbus Service Bulletin A330–29–3119 (for 

Model A330–200, –200F, and –300 series 

airplanes) or Airbus Service Bulletin A340– 

29–4091 (for Model A340–200 and –300 

series airplanes) has been embodied in 

service: Within 900 flight hours after January 

31, 2014 (the effective date of AD 2013–25– 

08), inspect the check valves on the blue, 

green, and yellow hydraulic systems to 

identify their part numbers, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–29– 

3111, Revision 02, dated June 23, 2011 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–29–4086, Revision 02, dated 

June 23, 2011 (for Model A340–200 and –300 

series airplanes). Accomplishment of the 

actions required by this paragraph terminates 

the requirements specified in paragraphs 

(g)(1) and (g)(1)(ii) of this AD. 

(1) If check valves having P/N CAR401 are 

installed on all three hydraulic systems: 

Before further flight, do the inspection 

program (detailed inspection for red mark 

presence and alignment integrity of the check 

valve and manifold, a detailed inspection for 

traces of seepage or black deposits, and an 

inspection for proper torque) on yellow and 

blue high pressure manifolds, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–29– 

3111, Revision 02, dated June 23, 2011 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–29–4086, Revision 02, dated 

June 23, 2011 (for Model A340–200 and –300 

series airplanes). Accomplishment of the 

actions required by this paragraph terminates 

the requirements specified in paragraph 

(g)(2)(i) of this AD. 

(2) If check valves having P/N CAR401 are 

not installed on all three hydraulic systems, 

no further action is required by this 

paragraph until any check valve having P/N 

CAR400 is replaced with a check valve 

having P/N CAR401. If any check valve 

having P/N CAR400 is replaced by a check 

valve having P/N CAR401: Before further 

flight after such replacement, do the actions 

specified in paragraph (h) of this AD, to 

determine if all three hydraulic systems are 

equipped with check valves having P/N 

CAR401. If check valves having P/N CAR401 

are installed on all three hydraulic systems: 

Before further flight, do the actions specified 

in paragraphs (h)(1) and (i) of this AD. 

(i) Retained Repetitive Inspection Program 

and Corrective Actions, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2013–25–08, with no 

changes. Within 900 flight hours after 

accomplishment of paragraph (h)(1) of this 

AD, do the inspection program (detailed 

inspection for red mark presence and 

alignment integrity of the check valve and 

manifold, a detailed inspection for traces of 

seepage or black deposits, and an inspection 

for proper torque) on the green, yellow, and 

blue system check valves, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–29– 

3111, Revision 02, dated June 23, 2011 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A340–29–4086, Revision 02, dated 

June 23, 2011 (for Model A340–200 and –300 

series airplanes). Do all applicable corrective 

actions before further flight. Repeat the 

inspection program thereafter at intervals not 

to exceed 900 flight hours. Accomplishment 

of the actions required by this paragraph 

terminates the requirements specified in 

paragraphs (g)(1)(i), (g)(2)(ii), and (g)(2)(iii) of 

this AD. 

(j) Retained Repetitive Inspection for Certain 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2013–25–08, with no 

changes. For airplanes equipped with check 

valves having P/N CAR401 and on which 

Airbus Modification 201384 has been 

embodied during production, or on which 

Airbus Service Bulletin A330–29–3119 (for 

Model A330–200, –200F, and –300 series 

airplanes); or Airbus Service Bulletin A340– 

29–4091 (for Model A340–200 and –300 

series airplanes) has been embodied in 

service: Within 1,000 flight hours after 

January 31, 2014 (the effective date of AD 

2013–25–08), do a general visual inspection 

of the green, yellow, and blue high pressure 

manifolds and check valves having P/N 

CAR401 for any sign of rotation of the check 

valve head, and for any signs of hydraulic 

fluid leakage or seepage (including black 

deposits), in accordance with the instructions 

of Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. Repeat 

the inspection thereafter at interval not to 

exceed 900 flight hours. 

(k) Retained Corrective Action for Certain 

Airplanes, With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2013–25–08, with no 

changes. If, during any inspection required 

by paragraph (j) of this AD, any sign of 

rotation of the check valve head is found, or 

any sign of hydraulic fluid leakage or seepage 

(including black deposits) is found: Before 

further flight, do all applicable corrective 

actions, in accordance with the instructions 

of Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(l) Retained Provisions Regarding 

Terminating Action, With No Changes 

This paragraph restates the provisions of 

paragraph (l) of AD 2013–25–08, with no 

changes. Accomplishment of the corrective 

actions required by this AD does not 

constitute terminating action for the 

repetitive inspections required by this AD. 


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83652 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 

(m) Retained Replacement Check Valve 

Torque Value, With No Changes 

This paragraph restates the requirements of 

paragraph (m) of AD 2013–25–08, with no 

changes. As of January 31, 2014 (the effective 

date of AD 2013–25–08), at each replacement 

of a check valve with a check valve having 

P/N CAR401, apply a torque of 141 to 143 

newton meters (N.m) (103.98 to 105.45 

pounds-foot (lbf.ft)) during installation. 

(n) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the provisions of 

paragraph (n) of AD 2013–25–08, with no 

changes. 

(1) This paragraph provides credit for 

actions required by paragraph (g)(2)(i) of this 

AD, if those actions were performed before 

December 14, 2009 (the effective date of AD 

2009–24–09), using the applicable service 

information specified in paragraphs (n)(1)(i) 

and (n)(1)(ii) of this AD. 

(i) Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(ii) Airbus AOT A340–29A4086, dated 

September 2, 2009 (for Model A340–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before 

January 31, 2014 (the effective date of AD 

2013–25–08), using the applicable service 

information specified in paragraphs (n)(2)(i) 

through (n)(2)(iv) of this AD. 

(i) Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(ii) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009 (for Model A330– 

200 and –300 series airplanes), which is 

incorporated by reference in this AD. 

(iii) Airbus AOT A340–29A4086, dated 

September 2, 2009 (for Model A340–200 and 

–300 series airplanes), which is not 

incorporated by reference in this AD. 

(iv) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009 (for Model A340– 

200 and –300 series airplanes), which is 

incorporated by reference in this AD. 

(o) Retained Provisions for Reporting, With 

No Changes 

This paragraph restates the provisions of 

paragraph (o) of AD 2013–25–08, with no 

changes. Although the service information 

specified in paragraphs (o)(1) through (o)(5) 

of this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(1) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(2) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(3) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(4) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009. 

(5) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009. 

(p) New Requirement of This AD: Modify 

Hydraulic Systems 

Within 36 months after the effective date 

of this AD, modify the green, blue, and 

yellow high pressure hydraulic manifolds by 

replacing each check valve having P/N 

CAR401 with an improved check valve 

having P/N CAR402, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–29–3125, Revision 03, 

including Appendixes 01 and 02, dated April 

8, 2016; or Airbus Service Bulletin A340–29– 

4096, Revision 02, including Appendixes 01 

and 02, dated April 8, 2016; as applicable. 

(q) New Provision of This AD: Terminating 

Action for Repetitive Inspections 

Modification of an airplane, as required by 

paragraph (p) of this AD, constitutes 

terminating action for the repetitive 

inspections required by this AD. 

(r) New Requirement of This AD: Parts 

Installation Limitations 

(1) For an airplane that, as of the effective 

date of this AD, has a check valve having P/ 

N CAR401 installed, after modification as 

required by paragraph (p) of this AD, no 

person may install a check valve having P/ 

N CAR401, on that airplane. 

(2) For an airplane that does not have a 

check valve having P/N CAR401 installed, as 

of the effective date of this AD, no person 

may install a check valve having P/N 

CAR401, on that airplane. 

(s) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (p) of this AD, if those 

actions were performed before the effective 

date of this AD using the applicable service 

information specified in paragraphs (s)(1) 

through (s)(5) of this AD, which are not 

incorporated by reference in this AD. 

(1) Airbus Service Bulletin A330–29–3125, 

dated August 8, 2014. 

(2) Airbus Service Bulletin A330–29–3125, 

Revision 01, including Appendixes 01 and 

02, dated July 30, 2015. 

(3) Airbus Service Bulletin A330–29–3125, 

Revision 02, including Appendixes 01 and 

02, dated January 21, 2016. 

(4) Airbus Service Bulletin A340–29–4096, 

dated August 8, 2014. 

(5) Airbus Service Bulletin A340–29–4096, 

Revision 01, including Appendixes 01 and 

02, dated July 30, 2015. 

(t) 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. 

(i) 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. 

(ii) AMOC ANM–116–14–180 R1, dated 

February 21, 2014, is approved as an AMOC 

for the corresponding provisions of this AD. 

(iii) AMOC ANM–116–14–429, dated 

September 25, 2014, is not approved as an 

AMOC for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(u) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0009, dated 

January 16, 2015, 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–2016–3701. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (v)(6) and (v)(7) of this AD. 

(v) 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 December 27, 2016. 

(i) Airbus Service Bulletin A330–29–3125, 

Revision 03, including Appendixes 01 and 

02, dated April 8, 2016. 

(ii) Airbus Service Bulletin A340–29–4096, 

Revision 02, including Appendixes 01 and 

02, dated April 8, 2016. 


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Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations 83653 

(4) The following service information was 

approved for IBR on January 31, 2014 (78 FR 

78694, December 27, 2013). 

(i) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(5) The following service information was 

approved for IBR on December 14, 2009 (74 

FR 62208, November 27, 2009). 

(i) Airbus Alert Operators Telex A330– 

29A3111, Revision 1, dated October 8, 2009. 

Only the first page of this document contains 

the document number, revision level, and 

date; no other pages of this document contain 

this information. 

(ii) Airbus Alert Operators Telex A340– 

29A4086, Revision 1, dated October 8, 2009. 

Only the first page of this document contains 

the document number, revision level, and 

date; no other pages of this document contain 

this information. 

(6) 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. 

(7) 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. 

(8) 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 October 

12, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–25745 Filed 11–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–7421; Directorate 

Identifier 2015–NM–145–AD; Amendment 

39–18705; AD 2016–22–16] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, and 702), 

CL–600–2D15 (Regional Jet Series 705), 

CL–600–2D24 (Regional Jet Series 900), 

and CL–600–2E25 (Regional Jet Series 

1000) airplanes. This AD was prompted 

by a determination that wear and 

possible leakage of the high-pressure 

seal in the cylinder of the No. 3 

hydraulic system reservoir could occur 

and cause high hydraulic fluid 

temperature and/or prevent the system 

from reaching normal operating 

pressure. This AD requires repetitive 

operational checks for wear and leakage 

of the high-pressure seal in the cylinder 

of the reservoir of the No. 3 hydraulic 

system, and corrective actions if 

necessary. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective December 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 400 Coˆte Vertu Road 

West, Dorval, Que ́bec H4S 1Y9, Canada; 

Widebody Customer Response Center 

North America toll-free telephone 1– 

866–538–1247 or direct-dial telephone 

1–514–855–2999; fax 514–855–7401; 

email ac.yul@aero.bombardier.com; 

Internet http://www.bombardier.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– 

7421. 

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– 

7421; 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 Office (telephone 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

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 certain Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 

701, and 702), CL–600–2D15 (Regional 

Jet Series 705), CL–600–2D24 (Regional 

Jet Series 900), and CL–600–2E25 

(Regional Jet Series 1000) airplanes. The 

NPRM published in the Federal 

Register on July 1, 2016 (81 FR 43122) 

(‘‘the NPRM’’). The NPRM was 

prompted by a determination that wear 

and possible leakage of the highpressure seal in the cylinder of the No. 

3 hydraulic system reservoir could 

occur and cause high hydraulic fluid 

temperature and/or prevent the system 

from reaching normal operating 

pressure. The NPRM proposed to 

require repetitive operational checks for 

wear and leakage of the high-pressure 

seal in the cylinder of the reservoir of 

the No. 3 hydraulic system, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

wear and leakage of the high-pressure 

seal in the cylinder of the reservoir of 

the No. 3 hydraulic system, which can 

result in high hydraulic fluid 

temperature. High hydraulic fluid 

temperature combined with a 

temperature transducer malfunction 

could result in un-annunciated 

overheating of the hydraulic system and 

consequent ignition sources inside the 

fuel tank, which, combined with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2015–27, 

dated September 14, 2015 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2C10 (Regional Jet Series 700, 701, 

and 702), CL–600–2D15 (Regional Jet 

Series 705), CL–600–2D24 (Regional Jet 

Series 900), and CL–600–2E25 (Regional 

Jet Series 1000) airplanes. The MCAI 

states: 


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