5728 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0041; 

Directorate Identifier 2011–NM–167–AD. 

(a) Comments Due Date 

We must receive comments by March 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A300 

B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203 airplanes, certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by analysis that in 

a specific failure case of the upper primary 

attachment of the trimmable horizontal 

stabilizer actuator (THSA); the THSA upper 

secondary attachment would engage because 

it could only withstand the loads for a 

limited period of time. We are issuing this 

AD to prevent failure of the secondary load 

path, which could result in 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) Actions 

Within 30 months after the effective date 

of this AD, install 3 retention plates for the 

gimbal bearings on the THSA upper primary 

attachment, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–27–0204, 

dated March 11, 2011. 

(h) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer 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. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0112, dated June 15, 2011; and Airbus 

Mandatory Service Bulletin A300–27–0204, 

dated March 11, 2011; for related 

information. 

Issued in Renton, Washington, on January 

23, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2622 Filed 2–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012 0040; Directorate 

Identifier 2011–NM–121–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A300 series airplanes; all 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model C4– 

605R Variant F airplanes (collectively 

called A300–600 series airplanes). This 

proposed AD was prompted by reports 

of an inoperative fire shut-off valve 

(FSOV) as a result of damage due to 

over-length of the bonding lead. This 

proposed AD would require a one-time 

detailed inspection for length of the 

FSOV bonding leads and for contact or 

chafing of the wires, and corrective 

actions, if necessary. We are proposing 

this AD to detect and correct contact or 

chafing of wires and bonding leads 

which, if not detected could be a source 

of sparks in the wing trailing edge, and 

could lead to an uncontrolled engine 

fire. 

DATES: We must receive comments on 

this proposed AD by March 22, 2012. 

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– 

EAW (Airworthiness Office), 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, Washington. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2012–0040; Directorate Identifier 

2011–NM–121–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 5729 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2011– 

0084, dated May 24, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During a scheduled maintenance check, 

one operator reported inoperative FSOV [fire 

shut-off valve]. Investigations showed 

damage at wire located between engine 2 

Hydraulic FSOV and wing rear spar, in the 

zones 575/675, and at bonding lead, located 

between wing Rib 7A and Rib 8 below 

Hydraulic Pressure Lines. 

Similar inspections on different aeroplanes 

have shown that one of the causes of damage, 

is the contact between bonding lead and the 

harness, due to over length of the bonding 

lead. 

As the affected wire is not powered during 

normal operation, no defect had been 

detected. The defect was detected when a test 

was performed on the FSOV during 

maintenance check by the operator. 

This condition, in the scope of published 

FAA SFAR88 and JAA Internal Policy INT/ 

POL/25/12, is considered to be a potential 

source of sparks in the wing trailing edge 

area and if not detected, could lead to an 

uncontrolled engine fire. 

For the reasons stated above, this [EASA] 

AD requires a one-time [detailed] inspection 

of the wires [for contact or chafing] located 

between LH/RH engines Hydraulic FSOV and 

wing rear spar in the zones 575/675, and the 

bonding lead [for length] that is located 

between Rib 7A and Rib 8 below Hydraulic 

Pressure Lines, and corrective actions [repair 

wires or replace bonding leads] depending on 

findings. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A300–24–0106 (for Model 

A300 series airplanes); and A300–24– 

6108 (for Model A300–600 series 

airplanes); both including Appendices 

01 and 02, both dated July 9, 2010. 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 125 products of U.S. 

registry. We also estimate that it would 

take about 8 work-hours per product to 

comply with the 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 

$85,000, or $680 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $50, for a cost of $135 per 

product. 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 adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0040; 

Directorate Identifier 2011–NM–121–AD. 

(a) Comments Due Date 

We must receive comments by March 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to airplanes specified in 

paragraphs (c)(1), (c)(2) and (c)(3) of this AD; 

certificated in any category; all certificated 

models; all serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, and F4–622 airplanes. 

(3) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24: Electrical Power. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
5730 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 

(e) Reason 

This AD was prompted by reports of an 

inoperative fire shut-off valve (FSOV) as a 

result of damage due to over-length of the 

bonding lead. We are issuing this AD to 

detect and correct contact or chafing of wires 

and bonding leads which, if not detected, 

could be a source of sparks in the wing 

trailing edge, and could lead to an 

uncontrolled engine fire. 

(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) Inspection of the FSOV Bonding Leads 

Within 4,500 flight hours or 30 months 

after the effective date of this AD, whichever 

occurs first: Do a one-time detailed 

inspection for length of the FSOV bonding 

leads, and for contact or chafing of the wires 

located on left hand (LH) side and right-hand 

(RH) side of the wing rear spar, in accordance 

with Accomplishment Instructions of the 

Airbus Mandatory Service Bulletin A300–24– 

0106, dated July 9, 2010 (for Model A300 

series airplanes); or Airbus Mandatory 

Service Bulletin A300–24–6108, dated July 9, 

2010 (for Model A300–600 series airplanes). 

(h) Corrective Action for FSOV Bonding 

Leads 

If, during the inspection required by 

paragraph (g) of this AD, the length of the 

bonding lead(s) is more than 80 mm (3.15 

inches), before further flight, replace the 

bonding lead(s) with a new bonding lead 

having a length equal to 80 mm (3.15 inches), 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–24–0106, dated July 9, 2010 

(for Model A300 series airplanes); or Airbus 

Mandatory Service Bulletin A300–24–6108, 

dated July 9, 2010 (for Model A300–600 

series airplanes). 

(i) Repair of the Wires of the LH and RH 

Sides 

If, during the inspection required by 

paragraph (g) of this AD, contact(s) or 

chafing(s) of the wires is found, repair the 

wires in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–0106, 

dated July 9, 2010 (for Model A300 series 

airplanes); or Airbus Mandatory Service 

Bulletin A300–24–6108, dated July 9, 2010 

(for Model A300–600 series airplanes). 

(j) Parts Installation 

As of the effective date of this AD, no 

person may install any bonding lead longer 

than 80 mm (3.15 inches), located between 

LH/RH engine hydraulic FSOV and wing rear 

spar in the zones 575/675 on any airplane. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. 

(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. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0084, dated May 24, 2011; and the 

service information identified in paragraphs 

(l)(1), and (l)(2) of this AD; for related 

information. 

(1) Airbus Mandatory Service Bulletin 

A300–24–0106, dated July 9, 2010. 

(2) Airbus Mandatory Service Bulletin 

A300–24–6108, dated July 9, 2010. 

Issued in Renton, Washington, on January 

12, 2012. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2625 Filed 2–3–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0042; Directorate 

Identifier 2011–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 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 Bombardier, Inc. 

Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702), CL–600–2D15 

(Regional Jet Series 705), and CL–600– 

2D24 (Regional Jet Series 900) airplanes. 

The existing AD currently requires a 

one-time inspection of the main landing 

gear (MLG) shock strut assemblies for 

part and serial numbers; for certain 

MLG shock strut assemblies, a one-time 

inspection of the torque link apex joint, 

and corrective actions if necessary; and, 

for certain MLG shock strut assemblies, 

replacement or rework of the apex nut. 

Since we issued that AD, we have 

determined that part and serial numbers 

for MLG shock strut assemblies for 

Model CL–600–2D15 and CL–600–2D24 

airplanes were inadvertently omitted 

from certain requirements of the 

existing AD. This proposed AD would 

continue to require the actions in the 

existing AD, and would add the 

previously omitted part and serial 

numbers. We are proposing this AD to 

detect and correct improper assembly 

and damage of the MLG torque link 

apex joint, which could cause heavy 

vibration during landing, consequent 

damage to MLG components, and 

subsequent collapse of the MLG. 

DATES: We must receive comments on 

this proposed AD by March 22, 2012. 

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 Bombardier, 

Inc., 400 Cote-Vertu Road West, Dorval, 

Quebec H4S 1Y9, Canada; phone: 514– 

855–5000; fax: 514–855–7401; email: 

thd.crj@aero.bombardier.com; Internet: 

http://www.bombardier.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS