8566 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 

applicable corrective actions, using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA. 

Note 1 to paragraph (g) of this AD: 

Guidance on operational tests of the aileron 

disconnect system can be found in the BD– 

100–1A10 Time Limits/Maintenance Checks 

(TLMC) Manual. 

(h) Modification of the SECU 

Within 1,600 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first: Modify and re-identify the 

SECU, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–27–16, dated October 

31, 2013. Doing the actions required by this 

paragraph terminates the actions required by 

paragraph (g) of this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an SECU, P/N C47330– 

006, C47330–007, or C47330–008, on any 

airplane. 

(j) 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 (ACO), 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–24, dated 

August 5, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

FAA–2015–0088. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02695 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0242; Directorate 

Identifier 2014–NM–100–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 B4–603, B4–605R, 

B4–620, B4–622, B4–622R airplanes; all 

Airbus Model A300 C4–605R Variant F 

airplanes; and certain Airbus Model 

A300 F4–605R airplanes. This proposed 

AD was prompted by the manufacturer’s 

review of all repairs accomplished using 

the structural repair manual. This 

review was done using revised fatigue 

and damage tolerance calculations. This 

proposed AD would require an 

inspection of the surrounding panels of 

the left and right forward passenger 

doors, and corrective actions if 

necessary. We are proposing this AD to 

detect and correct previous incomplete 

or inadequate repairs to the surrounding 

panels of the left and right forward 

passenger doors and the fail-safe ring, 

which could negatively affect the 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 6, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0242; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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; 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–2015–0242; Directorate Identifier 

2014–NM–100–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. 

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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8567 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0101, dated May 2, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A300 

B4–603, B4–605R, B4–620, B4–622, B4– 

622R airplanes; all Airbus Model A300 

C4–605R Variant F airplanes; and 

certain Airbus Model A300 F4–605R 

airplanes. The MCAI states: 

In the frame of the Ageing Airplane Safety 

Rule (AASR), all existing Structural Repair 

Manual (SRM) repairs were reviewed. 

This analysis, which consisted in new 

Fatigue and Damage Tolerance calculations, 

revealed that some repairs in the area 

surrounding the forward passenger/crew 

door and the fail safe ring are no longer 

adequate. 

These repairs, if not reworked, could affect 

the structural integrity of the aeroplane. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A300– 

53–6173 (later revised), to provide 

instructions for the inspection of repairs on 

the left-hand (LH) and right-hand (RH) 

forward door surrounding panels. 

For the reasons described above, and 

further to the AASR implementation, this 

[EASA] AD requires a one-time inspection of 

the forward door surrounding panels to 

identify SRM repairs in these areas and, 

depending on findings, accomplishment of 

applicable corrective action(s). 

Corrective actions include contacting 

the manufacturer for rework approval or 

repair instructions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0242. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–53–6173, Revision 01, dated 

February 28, 2014. The service 

information describes procedures for a 

one-time detailed of the area 

surrounding the forward passenger/crew 

door and the fail safe ring to determine 

if any repairs have been done, and 

corrective actions. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available; see 

ADDRESSES for ways to access this 

service information. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The actions specified in the 

service information identified 

previously include procedures and tests 

that are identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a Note under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

tests that are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 65 airplanes of U.S. registry. 

We also estimate that it would take 

about 120 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 

this proposed AD on U.S. operators to 

be $663,000, or $10,200 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

up to 730 work-hours and require parts 

costing up to $72,250, for a cost of up 

to $134,300 per product, depending on 

configuration. We have no way of 

determining the number of aircraft that 

might 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. 

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, 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

8568 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–0242; 

Directorate Identifier 2014–NM–100–AD. 

(a) Comments Due Date 

We must receive comments by April 6, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category. 

(1) Model A300 B4–603, B4–605R, B4–620, 

B4–622, and B4–622R airplanes, all 

manufacturer serial numbers. 

(2) Model A300 C4–605R Variant F 

airplanes, all manufacturer serial numbers. 

(3) Model A300F4–605R airplanes, all 

manufacturer serial numbers, except those on 

which Airbus Modification 12699 was 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the 

manufacturer’s review of all repairs 

accomplished using the structural repair 

manual. This review was done using revised 

fatigue and damage tolerance calculations. 

We are issuing this AD to detect and correct 

previous incomplete or inadequate repairs to 

the surrounding panels of the left and right 

forward passenger doors and the fail-safe 

ring, which could negatively affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the time specified in paragraph (g)(1) or 

(g)(2) of this AD, whichever is later: Do a 

detailed inspection of the surrounding panels 

of the left and right forward passenger doors 

to determine if any repairs have been done, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(1) Prior to the accumulation of 30,000 

total flight cycles or 67,500 total flight hours, 

whichever occurs first. 

(2) Within 28 months after the effective 

date of this AD. 

(h) Identification of Repairs 

If any affected repair is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, identify the 

reworked area(s), the percentage of the 

rework, and the limits of the rework, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(i) Corrective Actions 

During the repair identification required by 

paragraph (h) of this AD, if any rework is 

found that is outside the allowable damage 

limits specified in Airbus Service Bulletin 

A300–53–6173, Revision 01, dated February 

28, 2014: Before further flight, rework or 

repair, as applicable, using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(j) Exception to Service Information 

Specifications 

Although Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014, specifies to contact Airbus for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; EASA; or 

Airbus’s EASA DOA. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

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

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A300–53–6173, 

dated August 1, 2013, which is not 

incorporated by reference in this AD. 

(l) 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, WA 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) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD, if the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(3) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0101, dated 

May 2, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–0242. 

(2) For service information identified in 

this 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 view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02920 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0245; Directorate 

Identifier 2014–NM–135–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

mstockstill on DSK4VPTVN1PROD with PROPOSALS