Federal Register / Vol. 78, No. 27 / Friday, February 8, 2013 / Proposed Rules 9341 

facts within his or her personal 

knowledge, but, unless specifically 

authorized to do so by the Director, the 

employee must not: 

(1) Disclose confidential or privileged 

information; or 

(2) Testify as an expert or opinion 

witness with regard to any matter 

arising out of the employee’s official 

duties or FHFA’s mission or functions. 

This provision does not apply to 

requests from the United States for 

expert or opinion testimony. 

(d) The Director may assign FHFA 

Counsel to be present for an employee’s 

testimony. 

§ 1215.13 Restrictions That Apply to 

Records and Information. 

(a) The Director may impose 

conditions or restrictions on the release 

of records and information, including 

but not limited to requiring that parties 

to the legal proceeding obtain a 

protective order or execute a 

confidentiality agreement to limit access 

and further disclosure, or that parties 

take other appropriate steps to comply 

with applicable privacy requirements. 

The terms of a protective order or 

confidentiality agreement must be 

acceptable to the Director. In cases 

where protective orders or 

confidentiality agreements have already 

been executed, the Director may 

condition the release of records and 

information on an amendment to the 

existing protective order or 

confidentiality agreement. 

(b) If the Director so determines, 

original agency records may be 

presented for examination in response 

to a demand or request, but they are not 

to be presented as evidence or otherwise 

used in a manner by which they could 

lose their status as original records, nor 

are they to be marked or altered. In lieu 

of the original records, certified copies 

will be presented for evidentiary 

purposes. 

(c) The scope of permissible 

production is limited to that set forth in 

the prior, written authorization granted 

by the Director. 

(d) If records or information are 

produced in connection with a legal 

proceeding, the demanding or 

requesting party must: 

(1) Promptly notify all other parties to 

the legal proceeding that the records or 

information are FHFA records or 

information and are subject to this part 

and any applicable confidentiality 

agreement or protective order; 

(2) Provide copies of any 

confidentiality agreement or protective 

order to all other parties; and 

(3) Retrieve the records or information 

from the court or other competent 

authority’s file when the court or other 

competent authority no longer requires 

the records or information and certify 

that every party covered by a 

confidentiality agreement, protective 

order, or other privacy protection has 

destroyed all copies of the records or 

information. 

§ 1215.14 Procedure in the Event of an 

Adverse FHFA Determination. 

(a) Procedure for seeking 

reconsideration of FHFA’s 

determination. A demanding or 

requesting party seeking reconsideration 

of FHFA’s rejection of a demand or 

request, or of any restrictions on 

receiving records, information, or 

testimony, may seek reconsideration of 

the rejection or restrictions as follows— 

(1) Notice of Intention to Petition for 

Reconsideration. The aggrieved 

demanding or requesting party may seek 

reconsideration by filing a written 

Notice of Intention to Petition for 

Reconsideration (Notice) within 10 

business days of the date of FHFA’s 

determination. The Notice must identify 

the petitioner, the determination for 

which reconsideration is being 

petitioned, and any dates (such as 

deposition, hearing, or court dates) that 

are significant to petitioner. The Notice 

must be served in accordance with 

§ 1215.7. 

(2) Petition for Reconsideration. 

Within five business days of filing 

Notice, the petitioner must file a 

Petition for Reconsideration (Petition) in 

accordance with § 1215.7. The Petition 

must contain a clear and concise 

statement of the basis for the 

reconsideration with supporting 

authorities. Determinations about 

petitions for reconsideration are within 

the discretion of the FHFA Director, and 

are final. 

(b) Prerequisite to judicial review. 

Pursuant to section 704 of the 

Administrative Procedure Act, 5 U.S.C. 

704, a petition to FHFA for 

reconsideration of a final determination 

made under the authority of this part is 

a prerequisite to judicial review. 

§ 1215.15 Conflicting Court Order. 

Notwithstanding FHFA’s rejection of 

a demand for records, information, or 

testimony, if a court or other competent 

authority orders an FHFA employee to 

comply with the demand, the employee 

must promptly notify FHFA’s General 

Counsel of the order, and the employee 

must respectfully decline to comply, 

citing United States ex rel. Touhy v. 

Ragen, 340 U.S. 462 (1951). An 

employee’s failure to notify the General 

Counsel of a court or other authority’s 

order is grounds for discipline or other 

adverse action. 

§ 1215.16 Fees. 

(a) The Director may condition the 

production of records, information, or 

an employee’s appearance on advance 

payment of reasonable costs to FHFA, 

which may include but are not limited 

to those associated with employee 

search time, copying, computer usage, 

and certifications. 

(b) Witness fees will include fees, 

expenses, and allowances prescribed by 

the rules applicable to the particular 

legal proceeding. If no fees are 

prescribed, FHFA will base fees on the 

rule of the federal district court closest 

to the location where the witness will 

appear. Such fees may include but are 

not limited to time for preparation, 

travel, and attendance at the legal 

proceeding. 

Dated: February 2, 2013. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2013–02908 Filed 2–7–13; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0088; Directorate 

Identifier 2011–NM–233–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 A318, 

A319, A320, and A321 series airplanes. 

The existing AD currently requires 

repetitive inspections of the upper 

support of the nose landing gear (NLG), 

and related investigative and corrective 

actions if necessary; and also provides 

an optional terminating action for the 

repetitive inspections. Since we issued 

that AD, we have determined that 

previously allowed terminating actions 

no longer address the unsafe condition 

and that a new terminating action is 

necessary. This proposed AD would 

require installing a new enhanced 

manufacturing and maintainability 

(EMM) braking and steering control unit 

(BSCU) standard and adds airplanes to 


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9342 Federal Register / Vol. 78, No. 27 / Friday, February 8, 2013 / Proposed Rules 

the applicability. We are proposing this 

AD to prevent landings with the NLG 

turned 90 degrees from centerline, 

which could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 25, 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, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

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–2013–0088; Directorate Identifier 

2011–NM–233–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 August 17, 2007, we issued AD 

2007–18–09, Amendment 39–15189 (72 

FR 51164, September 6, 2007), which 

superseded AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007), The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2011–0201, dated October 13, 2011 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

In 2005, an A320 aeroplane experienced a 

landing with the Nose Landing Gear (NLG) 

wheels rotated at 90 degrees to the aeroplane 

centreline. 

Investigation showed that the upper 

support of the NLG shock absorber was 

damaged and the anti-rotation lugs were 

ruptured. This caused the nose wheels to lose 

their centred position reference. The affected 

Braking and Steering Control Unit (BSCU) 

had logged a steering system fault because 

hydraulic power was not available at the time 

of steering system checks, therefore the BSCU 

was not able to proceed with the re-centring 

of the wheels. Failure to centre the NLG 

wheels correctly may result in a failure of the 

NLG to retract. 

To prevent further landing incidents with 

NLG wheels rotated at 90 degrees, DGAC 

France issued AD F–2005–191 [which 

corresponds to FAA AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005)] to require the 

implementation of an operational procedure 

and the accomplishment of certain 

maintenance actions. 

EASA AD 2006–0174, [which corresponds 

to FAA AD 2007–18–09, Amendment 39– 

15189 (72 FR 51164, September 6, 2007)] 

which superseded AD F–2005–191, was 

issued to extend the applicability and to 

introduce repetitive boroscope inspections of 

the NLG upper support lugs and cylinder 

lugs which have been driven by EMM BSCU 

L4.1 (Part Number (P/N) E21327001) or L4.5 

(P/N E21327003) and, corrective actions, 

depending on findings. 

Since that AD was issued, Airbus has 

demonstrated the acceptability of installing 

EMM BSCU L4.9B (P/N E21327006 or P/N 

E21327106) or conventional BSCU std 10 (P/ 

N C202163392E34) or conventional BSCU std 

10.1 (P/N C202163392E35) as terminating 

action for the actions required by EASA AD 

2006–0174, for aeroplanes fitted with twin 

wheel Main Landing Gear (MLG) units. 

For the reasons described above, this AD 

retains some of the requirements of EASA AD 

2006–0174, which is superseded, extends the 

applicability to all A318, A319, A320 and 

A321 aeroplanes, requires the installation of 

BSCU L4.9B, or BSCU std 10, or BSCU std 

10.1 for in service aeroplanes fitted with twin 

wheel MLG, which constitutes terminating 

action for the repetitive inspections and 

checks required by this AD. 

Installation of a NLG with new upper 

support anti-rotation lugs and new cylinders 

lugs, or installation of a NLG for which it can 

be demonstrated that it was never driven by 

EMM BSCU L4.1 or L4.5, is no longer 

considered as terminating action for the 

requirements of this AD. 

The unsafe condition is the NLG turning 

90 degrees from centerline, which could 

result in reduced controllability of the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service bulletins. 

• Airbus Mandatory Service Bulletin 

A320–32–1310, Revision 01, dated June 

23, 2011. 

• Airbus Mandatory Service Bulletin 

A320–32–1336, Revision 01, dated 

January 10, 2008. 

• Airbus Service Bulletins A320–32– 

1350, dated July 31, 2008. 

• Airbus Service Bulletin A320–32– 

1360, dated March 18, 2009. 

• Airbus Service Bulletin A320–32– 

1369, Revision 01, dated March 31, 

2010. 

• Airbus Service Bulletin A320–32– 

1387, dated April 7, 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 


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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. 

Differences Between This AD and the 

MCAI or Service Information 

Airbus Mandatory Service Bulletin 

A320–32–1310, Revision 01, dated June 

23, 2011, specifies to use Airbus 

recommendations when restoring the 

NLG, but this proposed AD would 

require restoring the NLG in accordance 

with a method approved by the 

Manager, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

The MCAI permits accomplishment of 

MCAI paragraph 1.1 by inserting a copy 

of certain Airbus airplane flight manual 

(AFM) temporary revisions into the 

AFM. We have not included that 

provision in this proposed AD, since the 

temporary revisions have already been 

incorporated into the AFM. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 755 products of U.S. 

registry. 

The actions that are required by FAA 

AD 2007–18–09, Amendment 39–15189 

(72 FR 51164, September 6, 2007), and 

retained in this proposed AD take about 

3 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 $255 

per product. 

We estimate that it would take about 

35 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$2,246,125, or $2,975 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. We have 

no way of determining the number of 

products that may need these actions. 

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) 

2007–18–09, Amendment 39–15189 (72 

FR 51164, September 6, 2007), and 

adding the following new AD: 

Airbus: Docket No. FAA–2013–0088; 

Directorate Identifier 2011–NM–233–AD. 

(a) Comments Due Date 

We must receive comments by March 25, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). 

(c) Applicability 

This AD applies to the Airbus airplanes 

listed in paragraphs (c)(1), (c)(2), (c)(3), and 

(c)(4) of this AD; certificated in any category; 

all serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–111, –211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a report of an 

airplane landing with the nose landing gear 

(NLG) turned 90 degrees from centerline, and 

from additional reports of upper support 

anti-rotation lugs of the NLG rupturing in 

service. We are issuing this AD to prevent 

landings with the NLG turned 90 degrees 

from centerline, which could result in 

reduced controllability 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 Records Review 

This paragraph restates the requirements of 

paragraph (f) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007). 

Within 5 days after November 30, 2005 (the 

effective date of AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005)), perform a records 

review to determine whether the airplane is 

equipped with or has ever been equipped 

with an enhanced manufacturing and 

maintainability (EMM) braking and steering 

control unit (BSCU) part number (P/N) 

E21327001 (standard L4.1, installed by 

Airbus Modification 26965, or Airbus Service 

Bulletin A320–32–1912) or P/N E21327003 

(standard L4.5, installed by Airbus 

Modification 33376, or Airbus Service 

Bulletin A320–32–1261). Airbus Service 

Bulletin A320–32–1310, dated February 8, 

2006, is one approved method for doing the 

records review. 


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(h) Retained Statement of No Further Action 

Required 

This paragraph restates the requirements of 

paragraph (g) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes on which 

a records review required by paragraph (g) of 

this AD conclusively determines that the 

airplane is not and never has been equipped 

with a BSCU P/N E21327001 or P/N 

E21327003, no further action is required by 

paragraphs (i), (j), (k), (l), and (m) of this AD. 

(i) Retained Airplane Flight Manual (AFM) 

Revision 

This paragraph restates the requirements of 

paragraph (h) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes that are not 

specified in paragraph (h) of this AD and on 

which Airbus Modification 31152 has not 

been incorporated in production (i.e., 

applicable only to aircraft with steering 

powered by the green hydraulic system): 

Within 10 days after November 30, 2005 (the 

effective date of AD 2005–24–06, 

Amendment 39–14386 (70 FR 70715, 

November 23, 2005)), revise the Limitation 

Section of the Airbus A318/319/320/321 

Aircraft Flight Manual (AFM) to include the 

following information. This may be done by 

inserting a copy of this AD into the AFM: 

The ECAM message, in case of a nose 

wheel steering failure, will be worded as 

follows: 

—‘‘WHEEL N/W STRG FAULT’’ for aircraft 

with the FWC E3 and subsequent standards 

—‘‘WHEEL N.W. STEER FAULT’’ for aircraft 

with the FWC E2 Standard. 

› If the L/G SHOCK ABSORBER FAULT 

ECAM caution is triggered at any time in 

flight, and the WHEEL N/W STRG FAULT 

ECAM caution is triggered after the landing 

gear extension: 

When all landing gear doors are indicated 

closed on ECAM WHEEL page, reset the 

BSCU: 

—A/SKID&N/W STRG---------------------------- 

OFF THEN ON 

If the WHEEL N/W STRG FAULT ECAM 

caution is no longer displayed, this indicates 

a successful nose wheel re-centering and 

steering recovery. 

—Rearm the AUTO BRAKE, if necessary. 

If the WHEEL N/W STRG FAULT ECAM 

caution remains displayed, this indicates that 

the nose wheel steering remains lost, and that 

the nose wheels are not centered. 

—During landing, delay nose wheel 

touchdown for as long as possible. 

—Refer to the ECAM STATUS. 

› If the WHEEL N/W STRG FAULT 

ECAM caution appears, without the L/G 

SHOCK ABSORBER FAULT ECAM caution: 

—No specific crew action is requested by the 

WHEEL N/W STRG FAULT ECAM caution 

procedure. 

—Refer to the ECAM STATUS. 

Accomplishment of the actions required by 

paragraph (r) of this AD terminates the 

requirements of this paragraph, and the AFM 

limitation required by this paragraph must be 

removed. 

Note 1 to paragraph (i) of this AD: When 

a statement identical to that in paragraph (i) 

of this AD has been included in the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, and the copy 

of this AD or AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007), 

may be removed from the AFM. 

(j) Retained Inspection Thresholds 

This paragraph restates the requirements of 

paragraph (i) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007). 

For airplanes that are not specified in 

paragraph (h) of this AD, at the earlier of the 

times specified in paragraphs (j)(1) and (j)(2) 

of this AD: Do a special detailed inspection 

(boroscopic) for broken or cracked NLG 

upper support lugs and missing cylinder 

lugs, and do all applicable related 

investigative/corrective actions before further 

flight. Do all actions in accordance with 

Airbus Technical Note 957.1901/05, dated 

October 18, 2005; or the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1310, dated February 8, 2006. After 

October 11, 2007 (the effective date of AD 

2007–18–09), only Airbus Service Bulletin 

A320–32–1310, dated February 8, 2006, may 

be used. Where Airbus Service Bulletin 

A320–32–1310, dated February 8, 2006, 

specifies that restoring the NLG is necessary 

in accordance with Airbus recommendations, 

this AD requires restoring the NLG in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). Repeat the inspection 

thereafter at the applicable interval specified 

in paragraph (k) or (l) of this AD until the 

inspection required by paragraph (t) of this 

AD is accomplished. 

(1) Within 100 flight cycles following an 

electronic centralized aircraft monitoring 

(ECAM) caution ‘‘L/G SHOCK ABSORBER 

FAULT’’ associated with at least one of the 

following centralized fault display system 

(CFDS) messages specified in paragraph 

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

of the effective date of this AD, for the 

conditions specified in paragraph (j)(1) of 

this AD, do the actions required by paragraph 

(r) of this AD. 

(i) ‘‘N L/G EXT PROX SNSR 24GA TGT 

POS.’’ 

(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT 

POS.’’ 

(iii) ‘‘N L/G SHOCK ABSORBER FAULT 

2526GM.’’ 

(2) At the later of the times specified in 

paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. 

(i) Within 20 months, 6,000 flight hours, or 

4,500 flight cycles since the date of issuance 

of the original French standard airworthiness 

certificate, or the original French export 

certificate of airworthiness, whichever occurs 

first. 

(ii) Within 6 months, 1,800 flight hours, or 

1,350 flight cycles after October 11, 2007 (the 

effective date of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007)), whichever occurs first. 

(k) Retained Repetitive Inspection Intervals 

for BSCU Standard L4.1 or L4.5 

This paragraph restates the requirements of 

paragraph (j) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007). 

For airplanes not specified in paragraph (h) 

of this AD that are equipped with EMM 

BSCU standard L4.1 or L4.5: Repeat the 

inspection specified in paragraph (j) of this 

AD thereafter at intervals not to exceed the 

earliest of 6 months; 1,800 flight hours; 1,350 

flight cycles; or 100 flight cycles following 

certain ECAM cautions and CFDS messages, 

as specified in paragraph (j)(1) of this AD. 

(l) Retained Repetitive Inspection Intervals 

for BSCU Standard L4.8 or Non-EMM BSCU 

This paragraph restates the requirements of 

paragraph (k) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). For airplanes not 

specified in paragraph (h) of this AD that are 

equipped with EMM BSCU standard L4.8 or 

a non-EMM BSCU: Repeat the inspection 

specified in paragraph (j) of this AD 

thereafter at intervals not to exceed the 

earliest of 20 months; 6,000 flight hours; 

4,500 flight cycles; or 100 flight cycles 

following certain ECAM cautions and CFDS 

messages, as specified in paragraph (j)(1) of 

this AD. 

(m) Retained Optional Terminating Action 

With Limiting Date Restriction 

This paragraph restates the requirements of 

paragraph (l) of AD 2007–18–09, Amendment 

39–15189 (72 FR 51164, September 6, 2007) 

with a limiting date restriction. For airplanes 

that are not specified in paragraph (h) of this 

AD: Installation of an NLG with new upper 

support anti-rotation lugs and new cylinder 

lugs, or installation of an NLG that was never 

driven by EMM BSCU standard L4.1 or L4.5; 

combined with installation of EMM BSCU 

standard L4.8 or a non-EMM BSCU; before 

the effective date of this AD; constitutes 

terminating action for the requirements of 

paragraphs (g), (h), (i), (j), (k), and (l) of this 

AD. Do the installations in accordance with 

a method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). Chapter 32 of 

the Airbus A318/A319/A320/A321 Aircraft 

Maintenance Manual (AMM) is one approved 

method for doing the installations before the 

effective date of this AD. 

(n) Retained Statement of No Reporting 

Required 

This paragraph restates the requirements of 

paragraph (m) of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007). Although Airbus Service 

Bulletin A320–32–1310, dated February 8, 

2006, specifies sending certain inspection 

results to Airbus, this AD does not include 

that requirement. 

(o) Part Number Identification 

For the purpose of this AD, the following 

part numbers are identified. 

(1) P/N E21327001: installed by Airbus 

Modification 26965 or by Airbus Service 

Bulletin A320–32–1912 in service: EMM 

BSCU L4.1. 

(2) P/N E21327003: installed by Airbus 

Modification 33376 or Airbus Service 


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Bulletin A320–32–1261 in service: EMM 

BSCU L4.5. 

(3) P/N E21327004: installed by Airbus 

modification 35216 or Airbus Service 

Bulletin A320–32–1305 or Airbus Service 

Bulletin A320–32–1343/AOT A320–32A1343 

in service: EMM BSCU L4.8. 

(4) P/N E213270B1: installed by Airbus 

modification 31931 or Airbus Service 

Bulletin A320–32–1206: EMM BSCU L5–2. 

(5) P/N E21327006: installed by Airbus 

modification 38973 or Airbus Service 

Bulletin A320–32–1350 or Airbus Service 

Bulletin A320–32–1361: EMM BSCU L4.9B. 

(6) P/N E21327106: installed by Airbus 

modification 151575 or Airbus Service 

Bulletin A320–32–1387: EMM BSCU L4.9B. 

(7) P/N C202163392E34: installed by 

Airbus Service Bulletin A320–32–1336 or 

Airbus Service Bulletin A320–32–1360: 

conventional BSCU standard (std) 10. 

(8) P/N C202163392E35: installed by 

Airbus Service Bulletin A320–32–1369: 

conventional BSCU std 10.1. 

(p) Records Review 

Within 5 days after the effective date of 

this AD: Perform a records review to 

determine whether the airplane is equipped 

with or has ever been equipped with an EMM 

BSCU having P/N E21327001 (standard L4.1, 

installed by Airbus modification 26965, or 

Airbus Service Bulletin A320–32–1912) or P/ 

N E21327003 (standard L4.5, installed by 

Airbus modification 33376, or Airbus Service 

Bulletin A320–32–1261), or P/N E21327004 

(standard L4.8, installed by Airbus 

modification 35216, or Airbus Service 

Bulletin A320–32–1305, or Airbus Service 

Bulletin A320–32–1343/AOT A320– 

32A1343), or P/N E213270B1 (standard L5– 

2, installed by Airbus modification 31931, or 

Airbus Service Bulletin A320–32–1206). 

Note 2 to paragraph (p) of this AD: 

Accomplishment of the actions specified in 

Airbus Mandatory Service Bulletin A320–32– 

1310, Revision 01, dated June 23, 2011, 

before the effective date of this AD, provides 

a method for doing the records review. 

(q) No Further Action Required for Certain 

Paragraphs 

For airplanes on which a records review 

required by paragraph (p) of this AD 

conclusively determines that the airplane is 

not and never has been equipped with an 

EMM BSCU having P/N E21327001, or P/N 

E21327003, or P/N E21327004, or P/N 

E213270B1, no further action is required by 

paragraphs (r) and (s) of this AD. 

(r) Airplane Flight Manual Revision 

For airplanes that are not identified in 

paragraph (q) of this AD and on which 

Airbus Modification 31152 has not been 

incorporated in production (i.e., applicable 

only to aircraft with steering powered by the 

green hydraulic system): Within 10 days after 

the effective date of this AD, revise the 

Limitation Section of the Airbus A318/319/ 

320/321 AFM to include the following 

information. This revision may be done by 

inserting a copy of this AD into the AFM. 

The ECAM message, in case of a nose 

wheel steering failure, will be worded as 

follows: 

—‘‘WHEEL N/W STRG FAULT’’ for airplanes 

with Flight Warning Computer (FWC) 

software post E3P. 

—‘‘WHEEL N.W. STEER FAULT’’ for 

airplanes with FWC software pre E3P. 

› If the L/G SHOCK ABSORBER FAULT 

ECAM caution is triggered at any time in 

flight, and the WHEEL N/W STRG FAULT 

ECAM caution is triggered after the landing 

gear extension: 

• When all landing gear doors are 

indicated closed on ECAM WHEEL page, 

reset the BSCU: 

—A/SKID&N/W STRG---------------------------- 

OFF THEN ON 

• If the WHEEL N/W STRG FAULT ECAM 

caution is no longer displayed, this indicates 

a successful nose wheel re-centering and 

steering recovery. 

—Rearm the AUTO BRAKE, if necessary. 

• If the WHEEL N/W STRG FAULT ECAM 

caution remains displayed, this indicates that 

the nose wheel steering remains lost, and that 

the nose wheels are not centered. 

—During landing, delay nose wheel 

touchdown for as long as possible. 

—Refer to the ECAM STATUS. 

› If the WHEEL N/W STRG FAULT 

ECAM caution appears, without the L/G 

SHOCK ABSORBER FAULT ECAM caution: 

—No specific crew action is requested by the 

WHEEL N/W STRG FAULT ECAM caution 

procedure. 

—Refer to the ECAM STATUS. 

Note: For airplanes fitted with pre FWC 

E3P standard, read N.W STEER instead of N/ 

W STRG. 

Accomplishment of the actions required by 

this paragraph terminates the requirements of 

paragraph (i) of this AD and the AFM 

revision required by paragraph (i) of this AD 

must be removed. 

Note 3 to paragraph (r) of this AD: When 

a statement identical to that in paragraph (r) 

of this AD has been included in the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, and the copy 

of this AD may be removed from the AFM. 

(s) Inspection Following Certain Centralized 

Fault Display System Messages 

(1) For airplanes other than those 

identified in paragraph (q) of this AD: Within 

100 flight cycles following an ECAM caution 

‘‘L/G SHOCK ABSORBER FAULT’’ 

associated with at least one of the following 

CFDS messages specified in paragraph 

(s)(1)(i), (s)(1)(ii), or (s)(1)(iii) of this AD, do 

the actions in paragraph (s)(2) of this AD. 

(i) ‘‘N L/G EXT PROX SNSR 24GA TGT 

POS.’’ 

(ii) ‘‘N L/G EXT PROX SNSR 25GA TGT 

POS.’’ 

(iii) ‘‘N L/G SHOCK ABSORBER FAULT 

2526GM.’’ 

(2) For airplanes identified in paragraph 

(s)(1) of this AD: Do the actions specified in 

paragraphs (s)(2)(i) and (s)(2)(ii) of this AD. 

(i) Check the NLG strut inflation pressure, 

weight-off- and weight-on-wheels, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–32–1310, Revision 01, dated 

June 23, 2011, and before further flight, do 

all applicable corrective actions and 

adjustments, in accordance with Airbus 

A318/A319/A320/A321, Task 12–12–32– 

610–001–A Check NLG Shock Absorber 

Fluid Level and Charge Pressure (‘‘Two-Point 

Check’’—Aircraft on Jacks to start), Revision 

August 1, 2012. 

(ii) Do a boroscopic inspection for broken 

or cracked NLG upper support lugs and 

missing or cracked cylinder lugs, and do all 

applicable related investigative and 

corrective actions before further flight. Do all 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–32–1310, 

Revision 01, dated June 23, 2011. Where 

Airbus Mandatory Service Bulletin A320–32– 

1310, Revision 01, dated June 23, 2011, 

specifies restoring the NLG in accordance 

with Airbus recommendations, this AD 

requires restoring the NLG before further 

flight, in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA (or its delegated agent). 

(t) Initial Boroscopic Inspection 

At the applicable times specified in 

paragraphs (t)(1) and (t)(2) of this AD: Do a 

boroscopic inspection for broken or cracked 

NLG upper support lugs and missing or 

cracked cylinder lugs, and do all applicable 

related investigative and corrective actions 

before further flight. Do all actions in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–32–1310, Revision 01, dated 

June 23, 2011. Where Airbus Mandatory 

Service Bulletins A320–32–1310, Revision 

01, dated June 23, 2011, specifies restoring 

the NLG in accordance with Airbus 

recommendations, this AD requires restoring 

the NLG before further flight, in accordance 

with a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent). Accomplishment of the 

actions required by this paragraph terminate 

the requirements of paragraphs (j), (k), and (l) 

of this AD. 

(1) For airplanes fitted with twin wheel 

main landing gear (MLG) that have been 

equipped with EMM BSCU standard L4.1, 

L4.5, or L4.8: At the later of the times 

specified in paragraphs (t)(1)(i) and (t)(1)(ii) 

of this AD. 

(i) Within 20 months, 6,000 flight hours, or 

4,500 flight cycles since first flight of the 

airplane, whichever occurs first. 

(ii) Within 6 months, or 1,800 flight hours, 

or 1,350 flight cycles after the effective date 

of this AD, whichever occurs first. 

(2) For airplanes fitted with bogie MLG: At 

the later of the times specified in paragraphs 

(t)(2)(i) and (t)(2)(ii) of this AD. 

(i) Within 20 months, or 6,000 flight hours, 

or 4,500 flight cycles after the installation of 

EMM BSCU standard L5–2, whichever occurs 

first. 

(ii) Within 6 months, or 1,800 flight hours, 

or 1,350 flight cycles after the effective date 

of this AD, whichever occurs first. 

(u) Repetitive Boroscopic Inspections 

After accomplishing the inspection 

specified in paragraph (t) of this AD: Repeat 


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the inspection required by paragraph (t) of 

this AD thereafter at the applicable interval 

specified in paragraphs (u)(1), (u)(2), and 

(u)(3) of this AD. 

(1) For airplanes fitted with twin wheel 

MLG that have been equipped with EMM 

BSCU standard L4.8: At intervals not to 

exceed 20 months, or 6,000 flight hours, or 

4,500 flight cycles, whichever occurs first. 

(2) For airplanes fitted with twin wheel 

MLG that have been equipped with EMM 

BSCU standard L4.1 or L4.5: At intervals not 

to exceed 6 months, or 1,800 flight hours, or 

1,350 flight cycles, whichever occurs first. 

(3) For airplanes fitted with bogie MLG: At 

intervals not to exceed 20 months, or 6,000 

flight hours, or 4,500 flight cycles, whichever 

occurs first. 

(v) Modification 

For airplanes fitted with twin wheel MLG: 

Within 6 months after the effective date of 

this AD, modify the airplane by installing 

EMM BSCU standard L4.9B, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–32–1350, 

dated July 3, 2008. 

(w) Optional Method of Modification 

Doing a modification specified in 

paragraph (w)(1), (w)(2), or (w)(3) of this AD, 

is acceptable for compliance with the 

requirements of paragraph (v) of this AD. 

(1) Modification of the airplane by 

installing EMM BSCU standard L4.9B, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1387, dated April 7, 2011. 

(2) Modification of the airplane by 

installing conventional EMM BSCU standard 

10, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1360, dated March 18, 2009; or Airbus 

Mandatory Service Bulletin A320–32–1336, 

Revision 01, dated January 10, 2008. 

(3) Modification of the airplane by 

installing conventional EMM BSCU standard 

10.1 in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1369, Revision 01, dated March 31, 2010. 

(x) Terminating Action 

In-service modification of an airplane fitted 

with twin wheel MLG as required by 

paragraph (v) of this AD constitutes 

terminating action for the initial and 

repetitive inspections required by paragraph 

(t) of this AD. In addition, the AFM changes 

required by paragraph (r) of this AD may be 

removed from the AFM; and the 

requirements of paragraph (s) of this AD are 

no longer required. 

(y) Exemption From Certain Actions 

Except for paragraph (y) of this AD, 

airplanes that have been delivered with 

Airbus modification 38973 and/or Airbus 

modification 151575 that install EMM BSCU 

standard L4.9B are not affected by the 

requirements of this AD, provided that no 

installation of previous EMM BSCU 

standards L4.1, L4.5, or L4.8 has been 

performed since the airplane first flight. 

(z) Parts Installation 

For airplanes that do not have EMM BSCU 

L4.1, or EMM BSCU L4.5, or EMM BSCU 

L4.8 installed: As of the effective date of this 

AD, no person may modify an airplane by 

installing EMM BSCU standards L4.1, L4.5, 

or L4.8 on any airplane. 

(aa) Credit for Previous Actions 

(1) This paragraph restates the 

requirements of paragraph (n) of AD 2007– 

18–09, Amendment 39–15189 (72 FR 51164, 

September 6, 2007). This paragraph provides 

credit for the inspections required by 

paragraph (j) of this AD, if those inspections 

were performed before October 11, 2007 (the 

effective date of AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007)) using Chapter 12, 

Subject 12–14–32 of the Airbus A318/A319/ 

A320/A321 AMM, as revised by Airbus 

A318/A319/A320/A321 AMM Temporary 

Revision 12–001, dated November 13, 2005. 

(2) This paragraph provides credit for the 

inspections and related investigative/ 

corrective actions required by paragraphs (j), 

(k), and (l) of this AD, if those inspections 

were performed before the effective date of 

this AD using Airbus Service Bulletin A320– 

32–1310, dated February 8, 2006. 

(3) This paragraph provides credit for the 

modifications specified in paragraph (w)(2) 

of this AD, if those modifications were 

performed before the effective date of this AD 

using Airbus Mandatory Service Bulletin 

A320–32–1336, dated September 19, 2007. 

(4) This paragraph provides credit for the 

modifications required by paragraph (w)(3) of 

this AD, if those modifications were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–32–1369, 

dated March 22, 2009. 

(bb) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; 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 previously in 

accordance with AD 2007–18–09, 

Amendment 39–15189 (72 FR 51164, 

September 6, 2007), are not approved as 

AMOCs with 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. 

(cc) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0201, dated October 13, 2011, 

and the service information service 

information identified in paragraphs (cc)(1)(i) 

through (cc)(1)(viii) for related information. 

(i) Airbus A318/A319/A320/A321, Task 

12–12–32–610–001–A Check NLG Shock 

Absorber Fluid Level and Charge Pressure 

(‘‘Two-Point Check’’—Aircraft on Jacks to 

start), Revision August 1, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A320–32–1310, Revision 01, dated June 23, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A320–32–1336, Revision 01, dated January 

10, 2008. 

(iv) Airbus Service Bulletin A320–32– 

1350, dated July 31, 2008. 

(v) Airbus Service Bulletin A320–32–1360, 

dated March 18, 2009. 

(vi) Airbus Service Bulletin A320–32– 

1369, Revision 01, dated March 31, 2010. 

(vii) Airbus Service Bulletin A320–32– 

1387, dated April 7, 2011. 

(viii) Airbus Technical Note 957.1901/05, 

dated October 18, 2005. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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 January 

31, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02898 Filed 2–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0090; Directorate 

Identifier 2012–NM–149–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 adopt a new 

airworthiness directive (AD) for certain 


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