28156 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

(1) If kits 25A1555A01 thru A05 are 

available, contact the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA for instructions, and do the 

repair. 

(2) Do the actions specified in paragraph 

(k)(1) and (k)(2) of this AD. 

(p) New Requirement of this AD: Repetitive 

Inspection of Upper Fittings and Shelves 

Concurrently with each special detailed 

inspection required by paragraphs (m) and 

(o) of this AD: Do a general visual inspection 

for damage (cracking or deformation) of the 

upper fittings and shelves of the 80VU rack, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012. If any damage is found: 

Before further flight, repair the damage using 

a method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

(q) New Requirement of This AD: Corrective 

Action for Previous Findings 

For airplanes that have been inspected 

before the effective date of this AD as 

specified in Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007; Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 01, dated February 18, 2008; or 

Airbus Mandatory Service Bulletin A320– 

25A1555, Revision 02, dated November 5, 

2008; and on which damage of the fittings 

was found, except for airplanes specified in 

paragraph (q)(1) or (q)(2) of this AD: At the 

applicable time given in paragraph E.(2)., 

‘‘Accomplishment Timescale,’’ of Airbus 

Mandatory Service Bulletin A320–25A1555, 

Revision 03, dated February 28, 2012, 

accomplish the applicable corrective actions, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–25A1555, Revision 03, dated 

February 28, 2012, except where this service 

information specifies to contact Airbus for 

further instructions, before further flight, 

contact either the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA (or its delegated 

agent) for instructions; and follow those 

instructions. Accomplishing the actions 

required by this paragraph terminates the 

requirements of paragraph (h) of this AD. 

(1) Airplanes on which Airbus 

Modification 34804 has been embodied in 

production. 

(2) Airplanes on which the terminating 

action specified in paragraph (k) of this AD 

has been done. 

(r) Credit for Previous Actions 

This paragraph restates the credit given in 

paragraph (l) of AD 2010–24–07, Amendment 

39–16526 (75 FR 75878, December 7, 2010). 

(1) This paragraph provides credit for 

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

(i) of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

(r)(1)(i)or (r)(1)(ii) of this AD. 

(i) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 01, dated February 

18, 2008. 

(ii) Airbus Service Bulletin A320– 

25A1555, dated June 14, 2007. 

(2) This paragraph provides credit for 

actions required by paragraphs (g) and (k)(2) 

of this AD, if those actions were performed 

before January 11, 2011 (the effective date of 

AD 2010–24–07, Amendment 39–16526 (75 

FR 75878, December 7, 2010)), using the 

service bulletins specified in paragraph 

(r)(2)(i) or (r)(1)(ii) of this AD. 

(i) Airbus Service Bulletin A320–25–1557, 

dated June 14, 2007. 

(ii) Airbus Service Bulletin A320–25–1557, 

Revision 01, dated February 7, 2008. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

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: 

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 2010–24–07, 

Amendment 39–16526 (75 FR 75878, 

December 7, 2010), are approved as AMOCs 

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. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0134, dated 

July 18, 2012, and the service information 

listed in paragraphs (t)(1)(i) through (t)(1)(iv) 

of this AD; for related information. 

(i) Airbus Service Bulletin A320–53–1215, 

dated November 05, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 02, dated 

November 5, 2008. 

(iii) Airbus Mandatory Service Bulletin 

A320–25A1555, Revision 03, dated February 

28, 2012. 

(iv) Airbus Service Bulletin A320–25– 

1557, Revision 02, dated November 5, 2008. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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.airwortheas@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 May 6, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11381 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0419; Directorate 

Identifier 2012–NM–129–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This proposed AD was 

prompted by reports of excessive wear 

on the lower latch surface of the main 

landing gear (MLG) up-lock hook. This 

proposed AD would require revising the 

maintenance program. We are proposing 

this AD to detect and correct up-lock 

hooks worn beyond the wear limit, 

which could prevent the successful 

extension of the MLG using the primary 

landing gear extension system, which in 

combination with an alternate extension 

system failure could result in the 

inability to extend the MLG. 

DATES: We must receive comments on 

this proposed AD by June 28, 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. 

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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 28157 

• 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., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@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, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

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–2013–0419; Directorate Identifier 

2012–NM–129–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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–21, 

dated June 25, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

The main landing gear up-lock assembly 

part number (P/N) 46500–7 was introduced 

as the terminating action to [Canadian] AD 

CF–2002–13R2. The main landing gear uplock assembly P/N 46500–9 was later 

introduced as a product improvement and 

has the same up-lock hook as P/N 46500–7. 

Due to a delay in the release of the new 

Maintenance Review Board (MRB) task 

associated with P/Ns 46500–7 and 46500–9, 

it is anticipated that in-service aeroplanes 

may be operating with up-lock hooks worn 

beyond the wear limit. An up-lock hook 

worn beyond the wear limit could prevent 

the successful extension of the main landing 

gear using the primary landing gear extension 

system. In combination with an alternate 

extension system failure, this could result in 

the inability to extend the main landing gear. 

This [Canadian] AD mandates the 

incorporation of the MRB task number 

323100–202. 

MRB task number 323100–202 adds a 

functional check of the main landing 

gear up-lock assembly latch to the 

maintenance program. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued the 

following service information. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

• Bombardier Repair Drawing 8/4– 

32–0190, Issue 2, dated January 14, 

2013. 

• Bombardier Q400 All Operator 

Message No. 515, DHC8–400–AOM– 

515, Revision 2009–06–24, dated April 

4, 2012. 

• Bombardier Temporary Revision 

MRB–66, dated December 7, 2011, to 

Section 1–32, ‘‘Systems/Powerplant 

Maintenance Program,’’ of Part 1 of the 

Bombardier Dash 8 Series 400 

Maintenance Requirements Manual, 

PSM 1–84–7. 

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 83 products of U.S. registry. 

We also estimate that it would take 

about 1 work-hour 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 

$7,055, or $85 per product. 

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 

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28158 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

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: 

Bombardier, Inc.: Docket No. FAA–2013– 

0419; Directorate Identifier 2012–NM– 

129–AD. 

(a) Comments Due Date 

We must receive comments by June 28, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes; 

certificated in any category; serial numbers 

4001 and subsequent; equipped with a main 

landing gear (MLG) up-lock having part 

number 46500–7 or 46500–9. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of 

excessive wear on the lower latch surface of 

the MLG up-lock hook. We are issuing this 

AD to detect and correct up-lock hooks worn 

beyond the wear limit, which could prevent 

the successful extension of the MLG using 

the primary landing gear extension system, 

which in combination with an alternate 

extension system failure could result in the 

inability to extend the MLG. 

(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) Maintenance Program Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance program to 

incorporate the information specified in Task 

Number 323100–202 as specified in 

Bombardier Temporary Revision MRB–66, 

dated December 7, 2011, to Section 1–32, 

‘‘Systems/Powerplant Maintenance 

Program,’’ of Part 1 of the Bombardier Dash 

8 Series 400 Maintenance Requirements 

Manual, PSM 1–84–7. Do the initial 

functional check at the applicable time 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

Note 1 to Paragraph (g) of this AD: The 

maintenance program revision required by 

paragraph (g) of this AD may be done by 

inserting a copy of Bombardier Temporary 

Revision MRB–66, dated December 7, 2011, 

to Section 1–32, ‘‘Systems/Powerplant 

Maintenance Program,’’ into Part 1 of the 

Bombardier Dash 8 Series 400 Maintenance 

Requirements Manual, PSM 1–84–7. When 

this temporary revision (TR) has been 

included in general revisions of the PSM, the 

general revisions may be inserted in the PSM, 

provided the relevant information in the 

general revision is identical to that in TR 

MRB–66. 

(1) For up-lock hook assemblies that have 

15,000 total flight cycles or more as of the 

effective date of this AD: Do the initial 

functional check within 600 flight cycles 

after the effective date of this AD. 

(2) For up-lock hook assemblies that have 

12,000 total flight cycles or more, but less 

than 15,000 total flight cycles, as of the 

effective date of this AD: Do the initial 

functional check within 1,200 flight cycles 

after the effective date of this AD, but before 

the accumulation of 15,600 total flight cycles 

on the assembly. 

(3) For up-lock hook assemblies with less 

than 12,000 total flight cycles as of the 

effective date of this AD: Do the initial 

functional check within 6,000 flight cycles 

after the effective date of this AD, but before 

the accumulation of 13,200 total flight cycles 

on the assembly. 

(h) Method of Compliance 

For any up-lock assembly outside the wear 

limit specified in the Inspection Notes of 

Bombardier Repair Drawing, 8/4–32–0190, 

Issue 2, dated January 14, 2013; and on 

which the up-lock roller on the MLG shock 

strut is free to rotate and free of any damage 

or flat spots on the riding surface: In lieu of 

doing the initial functional check, as required 

by paragraph (g) of this AD, accomplishing 

the actions specified in paragraphs (h)(1) 

through (h)(4) of this AD in accordance with 

Bombardier Repair Drawing, 8/4–32–0190, 

Issue 2, dated January 14, 2013, may be done. 

However, as of 36 months after the effective 

date of this AD, the initial functional check 

must be done in accordance with the 

requirements of paragraph (g) of this AD. 

(1) Do a detailed inspection for 

deformation, corrosion, or broken springs of 

the up-lock assembly of the MLG. If 

deformation, corrosion, or broken springs are 

found, before further flight, replace the 

spring. 

(2) Measure the groove depth of the lower 

latch working surface. 

(i) If the groove depth is greater than or 

equal to 0.022 inch, before further flight, 

replace the up-lock assembly part number (P/ 

N) 46500–7 or 46500–9 with a new assembly, 

or an assembly with a new or reworked hook 

installed. 

(ii) If the groove depth is greater than 0.017 

inch and less than or equal to 0.0215 inch: 

Within 600 flight cycles after accomplishing 

the measurement, do the up-lock inspection 

as specified in paragraph (h)(1) and (h)(2) of 

this AD, and repeat the inspections thereafter 

at intervals not to exceed 600 flight cycles. 

Replacing the up-lock hook with a new or 

reworked hook, or installing a new up-lock 

assembly, terminates the repetitive 

inspections. 

(iii) If the groove depth is between 0.0215 

and 0.0220 inch: Within 300 flight cycles 

after the measurement, replace the up-lock 

hook with a new or reworked hook, or with 

a new up-lock assembly. 

(3) Unless already accomplished, within 

6,000 flight hours or 36 months after doing 

the initial inspection specified in paragraph 

(h)(1) of this AD: Replace the up-lock 

assembly with a new assembly, or a new or 

reworked hook installed, in accordance with 

the Inspection Notes of Bombardier Repair 

Drawing 8/4–32–0190, Issue 1, dated April 2, 

2012. 

(4) Inspect the up-lock roller on both main 

gear shock struts for freedom of movement. 

(i) If the up-lock roller cannot be freely 

rotated by finger force, or any flat spots 

exceeding 0.060 inch (across the flats) are 

found, before further flight, replace the uplock roller. 

(ii) Repeat the inspections thereafter at 

intervals not to exceed 50 flight hours until 

the up-lock has been replaced with a new 

assembly, or a new or reworked up-lock hook 

has been installed. Replacing the up-lock 

with a new assembly, or installing a new or 

reworked up-lock hook, terminates the 

repetitive inspection requirements. 

(i) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used, except as provided by paragraph (h) of 

this AD unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(j) Reporting 

Submit a report of the initial functional 

check findings at the applicable time 

specified in paragraph (j)(1) or (j)(2) of this 

AD using Form No ISETS–03–AOM Q400 in 

Bombardier Q400 All Operator Message 

DHC8–400–AOM–515, Revision 2009–06–24, 

dated April 4, 2012. Send the report to 

Bombardier, Inc., Technical Help Desk, 

phone: 416–375–4000; fax: 416–375–4539; 

email: thd.qseries@aero.bombardier.com. 

(1) If the functional check was done on or 

after the effective date of this AD: Submit the 

report within 30 days after the functional 

check. 

(2) If the functional check was done before 

the effective date of this AD: Submit the 

report within 30 days after the effective date 

of this AD. 

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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 28159 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–21, dated June 25, 2012; 

and the service information specified in 

paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of 

this AD for related information. 

(i) Bombardier Repair Drawing 8/4–32– 

0190, Issue 2, dated January 14, 2013. 

(ii) Bombardier Q400 All Operator Message 

No. 515, DHC8–400–AOM–515, Revision 

2009–06–24, dated April 4, 2012. 

(iii) Bombardier Temporary Revision 

MRB–66, dated December 7, 2011, to Section 

1–32, ‘‘Systems/Powerplant Maintenance 

Program,’’ of Part 1 of the Bombardier Dash 

8 Series 400 Maintenance Requirements 

Manual, PSM 1–84–7. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@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, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on May 6, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11382 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0418; Directorate 

Identifier 2012–NM–200–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 certain 

Airbus Model A300 series airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). This proposed AD was 

prompted by a report that cracking was 

found in area 2 of the frame base fittings 

between frame 41 and frame 46. This 

proposed AD would require a check of 

maintenance records to determine if 

certain repairs were done in area 1 of 

the frame brace fittings, and, for affected 

airplanes, a detailed inspection for 

cracking in area 2 of the frame base 

fittings between frame 41 and frame 46, 

and repair if necessary. We are 

proposing this AD to detect and correct 

cracking in area 2 of the frame base 

fittings between frame 41 and frame 46, 

which could adversely affect the 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 28, 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—EAW, 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 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–2013–0418; Directorate Identifier 

2012–NM–200–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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS