26716 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 

EC635 is not type-certificated in the 

U.S. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 246 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD. Modifying the 

injection tubes would require about 4.5 

work-hours at an average labor rate of 

$85 per hour and required parts would 

cost about $900, for a cost of $1,282 per 

helicopter and a total cost to U.S. 

operators of $315,372. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Eurocopter Deutschland GmbH: Docket No. 

FAA–2013–0398; Directorate Identifier 

2011–SW–065–AD. 

(a) Applicability 

This AD applies to Eurocopter Deutschland 

GmbH (ECD) Model EC135P1, EC135P2, 

EC135P2+, EC135T1, EC135T2, and 

EC135T2+ helicopters with a fire 

extinguishing system part number (P/N) 

L262M1808101, P/N L262M1812101, or P/N 

L262M1812102 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

deformation of the fire extinguishing system 

injection tubes during an engine fire, which 

could result in impaired distribution of the 

fire extinguishing agent, failure of the fire 

extinguishing system to contain a fire, and 

subsequent loss of control of the helicopter. 

(c) Comments Due Date 

We must receive comments by July 8, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 30 days, modify each fire 

extinguishing system injection tube by 

removing and replacing a section of the 

tubing in accordance with the 

Accomplishment Instructions, paragraph 

3.B., of Eurocopter EC135 Alert Service 

Bulletin No. EC135–26A–003, Revision 2, 

dated December 19, 2011. 

(2) Do not install an injection tube, P/N 

L262M1810101, P/N L262M1811801, or P/N 

L262M1809101, on any helicopter unless it 

has been modified as required by this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0172, dated September 7, 2011. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2620: Extinguishing System. 

Issued in Fort Worth, Texas, on April 26, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10911 Filed 5–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0365; Directorate 

Identifier 2012–NM–223–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Airbus Model A330– 

200 and –300 series airplanes, and 

Model A340–200 and –300 series 

airplanes. The existing AD currently 

requires 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, installing new lock wire, and 

corrective actions if needed. Since we 

issued that AD, additional in-service 

reports of check valves loosening at 

lower flight cycle thresholds than 

previously reported have been received. 

This proposed AD would expand the 

applicability, reduce the compliance 

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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 26717 

time, change torque values of the check 

valve tightening, and require a repetitive 

inspection program for certain check 

valves in the hydraulic systems on 

airplanes that have had a certain 

modification embodied during 

production or in-service. We are 

proposing this AD to detect and correct 

such check valve loosening, which 

could result in hydraulic leaks, possibly 

leading to the loss of all three hydraulic 

systems and consequent loss of control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 24, 2013. 

ADDRESSES: You may send comments 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 service information identified in 

this proposed 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 review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0365; Directorate Identifier 

2012–NM–223–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On November 16, 2009, we issued AD 

2009–24–09, Amendment 39–16068 (74 

FR 62208, November 27, 2009). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A330–200 and –300 series airplanes, 

and Model A340–200 and –300 series 

airplanes. 

Since we issued AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2012–0244R1, dated January 25, 2013 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. 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 [total] flight cycles (FC). The check 

valve fitted on the Yellow hydraulic system 

is more 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 to 

—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. 

For the reasons described above, this new 

[EASA] AD partially retains the requirements 

of EASA AD 2012–0070, which is 

superseded. Additionally, for aeroplanes 

equipped with P/N CAR401 on which the 

increased torque value has been applied, this 

new [EASA] AD requires repetitive 

inspections of the check valves and HP 

manifolds. Finally, this [EASA] AD also 

requires application of a lower torque value 

when a check valve P/N CAR401 is installed 

on an aeroplane. 

This [EASA] AD is considered to be an 

interim action and further AD action may 

follow. 

Note: the reporting and the torque value 

increase requirements for check valves P/N 

CAR401 of EASA AD 2012–0070 are no 

longer part of this new [EASA] AD. 

This proposed AD would expand the 

applicability to include Model A330– 

200 freighter series airplanes, reduce the 

compliance time for initial inspection, 

and change torque values of the check 

valve tightening. The corrective actions 

include replacing seal assemblies, retorquing the check valve, and replacing 

the lock wire. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

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26718 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 

Relevant Service Information 

Airbus has issued the following 

service information. 

• Airbus Alert Operators 

Transmission A29L001–12, dated 

October 11, 2012. 

• Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 

23, 2011. 

• Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 

23, 2011. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 67 products of U.S. registry. 

The actions that are required by AD 

2009–24–09, Amendment 39–16068 (74 

FR 62208, November 27, 2009), and 

retained in this proposed AD take about 

8 work-hours per product, at an average 

labor rate of $85 per work hour. Based 

on these figures, the estimated cost of 

the currently required actions is $680 

per product. 

We estimate that it would take about 

2 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$11,390, or $170 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2009–24–09, Amendment 39–16068 (74 

FR 62208, November 27, 2009), and 

adding the following new AD: 

Airbus: Docket No. FAA–2013–0365; 

Directorate Identifier 2012–NM–223–AD. 

(a) Comments Due Date 

We must receive comments by June 24, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009). 

(c) Applicability 

This AD applies to 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; certificated in any category; 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 such 

check valve loosening, which 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 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–24–09, 

Amendment 39–16068 (74 FR 62208, 

November 27, 2009). 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)), 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 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 

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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 26719 

(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 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 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, Amendment 39–16068 (74 FR 

62208, November 27, 2009)), whichever 

occurs first. 

(B) For airplanes on which Airbus Service 

Bulletin A330–29–3101 or 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 A340–29–4078 but no 

earlier than 700 flight cycles after the 

embodiment of Airbus Service Bulletin 

A330–29–3101 or A340–29–4078. 

(2) 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)), 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 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 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) New Inspection and Actions 

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 the 

effective date of this AD, 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) New Repetitive Inspection Program and 

Corrective Actions 

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). Repeat the inspection 

program thereafter at intervals not to exceed 

900 flight hours. Do all applicable corrective 

actions before further flight. 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) New Repetitive Inspection for Certain 

Airplanes 

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); 

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26720 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 

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 the effective 

date of this AD, 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) New Corrective Action for Certain 

Airplanes 

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) No Terminating Action 

Accomplishment of the corrective actions 

required by this AD does not constitute 

terminating action for the repetitive 

inspections required by this AD. 

(m) Replacement Check Valve Torque Value 

As of the effective date of this AD, at each 

replacement of a check valve with a check 

valve having P/N CAR401, apply a torque of 

141 to 143 newton metre (N.m) (103.98 to 

105.45 pounds-foot (lbf.ft)) during 

installation. 

(n) Credit for Previous Actions 

(1) This paragraph restates the credit 

specified in paragraph (g)(2)(iv) of AD 2009– 

24–09, Amendment 39–16068 (74 FR 62208, 

November 27, 2009). 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 

Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes); or AOT A340– 

29A4086, dated September 2, 2009 (for 

Model A340–200 and –300 series airplanes). 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus AOT 

A330–29A3111, dated September 2, 2009; or 

Revision 1, dated October 8, 2009 (for Model 

A330–200 and –300 series airplanes); or AOT 

A340–29A4086, dated September 2, 2009; or 

Revision 1, dated October 8, 2009 (for Model 

A340–200 and –300 series airplanes). After 

the effective date of this AD all inspections 

and corrective actions, as required by 

paragraph (i) of this AD, must be 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–29–3111, 

Revision 02, dated June 23, 2011, or Airbus 

Mandatory Service Bulletin A340–29–4086, 

Revision 02, dated June 23, 2011; as 

applicable. 

(o) No Reporting 

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) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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. AMOCs 

approved for AD 2009–24–09, Amendment 

39–16068 (74 FR 62208, November 27, 2009) 

are approved as AMOCs for the 

corresponding provisions of this AD, except 

AMOC ANM–116–11–172 is not approved as 

an AMOC for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0244R1, dated January 25, 

2013; and the following service information; 

for related information. 

(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. 

(iv) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009. 

(v) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009. 

(2) 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 

review copies of the 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. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10908 Filed 5–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0366; Directorate 

Identifier 2011–NM–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–300, 747–400, 747–400D, and 

747SR series airplanes. The existing AD 

requires, for certain airplanes, 

inspection to determine the material of 

a main entry door (MED) reveal; 

repetitive inspections of certain reveals 

for cracking; a detailed inspection of 

certain reveals for a sharp edge and 

cracking; and corrective action if 

necessary. That AD also allows a certain 

replacement as an optional action for 

certain inspections of certain airplanes. 

Since we issued that AD, an operator 

reported a crack found in a 6061 

machined aluminum one-piece corner 

reveal. This proposed AD would add, 

for certain airplanes, an inspection to 

determine material type of MED reveals, 

repetitive inspections for cracking of 

6061 machined aluminum one-piece 

corner reveals, and replacement with 

6061 machined aluminum two-piece 

corner reveals if necessary. This 

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