67254 Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Boeing Model 757 

series airplanes modified by Flight 

Structures, Inc. 

Seats With Non-Traditional, Large, 

Non-Metallic Panels 

1. Except as provided in paragraph 3 

of these special conditions, compliance 

with 14 CFR part 25, Appendix F, parts 

IV and V, heat release and smoke 

emission, is required for seats that 

incorporate non-traditional, large, nonmetallic panels that may either be a 

single component or multiple 

components in a concentrated area in 

their design. 

2. The applicant may designate up to 

and including 1.5 square feet of nontraditional, non-metallic panel material 

per seat place that does not have to 

comply with special condition Number 

1, above. A triple seat assembly may 

have a total of 4.5 square feet excluded 

on any portion of the assembly (e.g., 

outboard seat place 1 square foot, 

middle 1 square foot, and inboard 2.5 

square feet). 

3. Seats do not have to meet the test 

requirements of 14 CFR part 25, 

Appendix F, parts IV and V, when 

installed in compartments that are not 

otherwise required to meet these 

requirements. Examples include: 

a. Airplanes with passenger capacities 

of 19 or less, 

b. Airplanes that do not have § 25.853, 

Amendment 25–61 or later, in their 

certification basis and do not need to 

comply with the requirements of 14 CFR 

121.312, and 

c. Airplanes exempted from § 25.853, 

Amendment 25–61 or later. 

Issued in Renton, Washington, on 

November, 5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27370 Filed 11–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0806; Directorate 

Identifier 2012–NM–022–AD; Amendment 

39–17243; AD 2012–22–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400, 

–401, and –402 airplanes. This AD was 

prompted by reports of an in-service 

incident where the propeller de-icing 

system became unavailable due to 

burnt/chafed wires within the 

alternating current contactor box 

(ACCB). This AD requires inspection for 

chafing, damage, and loose wiring 

within an ACCB and repair if necessary; 

and requires rework and reidentification of the wiring installation 

within each ACCB. We are issuing this 

AD to detect and correct damaged, 

chafed, or loose wiring within an ACCB, 

which could affect the operation of the 

windshield heater, ice detector, angle of 

attack (AOA) vane heater, pilot probe 

heater, engine intake heater, or propeller 

de-icing system, and subsequently 

adversely affect the airplane’s flight 

characteristics in icing conditions. 

DATES: This AD becomes effective 

December 14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 14, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7301; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 16, 2012 (77 FR 

49394). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

There has been one (1) reported in-service 

incident where the propeller de-icing system 

became unavailable due to burnt/chafed 

wires within the Alternating Current 

Contactor Box (ACCB). There has also been 

a number of additional minor events of wires 

found chafed within ACCBs. 

An investigation revealed that inadequate 

clearance between the wires and metallic 

structure within the ACCB could cause 

chafed wires. 

Damaged, chafed or loose wiring within an 

ACCB could affect the operation of the 

windshield heater, ice detector, angle of 

attack (AOA) vane heater, pitot probe heater, 

engine intake heater or propeller de-icing 

system. Loss of one of these systems could 

adversely affect the aeroplane’s flight 

characteristics in icing conditions. 

This [Transport Canada Civil Aviation 

(TCCA)] Airworthiness Directive (AD) 

mandates the [visual] inspection [for 

damaged, chafed, and loose wiring within an 

ACCB and replace if necessary] and 

rectification [rework] of the wiring 

installation within each ACCB. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 49394, August 16, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

49394, August 16, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 49394, 

August 16, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

83 products of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $49,385, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $0, for a cost of $170 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 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 67255 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (77 FR 49394, 

August 16, 2012), 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2012–22–07 Bombardier, Inc.: Amendment 

39–17243. Docket No. FAA–2012–0806; 

Directorate Identifier 2012–NM–022–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 14, 2012. 

(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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24: Electrical Power. 

(e) Reason 

This AD was prompted by reports of an inservice incident where the propeller de-icing 

system became unavailable due to burnt/ 

chafed wires within the alternating current 

contactor box (ACCB) due to inadequate 

clearance. We are issuing this AD to detect 

and correct damaged, chafed, or loose wiring 

within an ACCB, which could affect the 

operation of the windshield heater, ice 

detector, angle of attack (AOA) vane heater, 

pilot probe heater, engine intake heater, or 

propeller de-icing system, and subsequently 

adversely affect the airplane’s flight 

characteristics in icing conditions. 

(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 

For airplanes having serial numbers 4001 

through 4354 inclusive, and 4356 through 

4366 inclusive: Within 6,000 flight hours or 

36 months after the effective date of this AD, 

whichever occurs first: Do a general visual 

inspection for chafing, damage, and 

insulation damage, and rework the wiring 

within the ACCB, in accordance with the 

Accomplishment Instructions of the 

applicable Bombardier service bulletin 

specified in paragraphs (g)(1) through (g)(4) 

of this AD. If any chafing, damage, or 

insulation damage is found, before further 

flight, replace the damaged wiring, in 

accordance with the Accomplishment 

Instructions of the applicable Bombardier 

service bulletin specified in paragraphs (g)(1) 

through (g)(4) of this AD. 

(1) Bombardier Service Bulletin 84–24–47, 

Revision A, dated September 14, 2011. 

(2) Bombardier Service Bulletin 84–24–48, 

Revision A, dated September 14, 2011. 

(3) Bombardier Service Bulletin 84–24–49, 

Revision A, dated September 14, 2011. 

(4) Bombardier Service Bulletin 84–24–50, 

Revision A, dated September 14, 2011. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an ACCB having the 

combination of part numbers (P/N) and series 

specified in paragraphs (h)(1), (h)(2), (h)(3), 

and (h)(4) of this AD on any airplane. 

(1) P/N 1152130–6, series 1, 2, and 4. 

(2) P/N 1152148–6, series 1, 2, 4, and 5. 

(3) P/N 1152090–6, series 1, 2, and 4. 

(4) P/N 1152124–6, series 1, 2, 4, and 5. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service bulletin specified in paragraphs (i)(1) 

through (i)(4) of this AD, which are not 

incorporated by reference in this AD. 

(1) Bombardier Service Bulletin 84–24–47, 

dated April 26, 2011. 

(2) Bombardier Service Bulletin 84–24–48, 

dated April 26, 2011. 

(3) Bombardier Service Bulletin 84–24–49, 

dated April 26, 2011. 

(4) Bombardier Service Bulletin 84–24–50, 

dated April 26, 2011. 

(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, New York 

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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–03, dated January 11, 

2012, and the service information specified 

in paragraphs (k)(1)(i) through (k)(1)(iv) of 

this AD, for related information. 


wreier-aviles on DSK5TPTVN1PROD with 
67256 Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 

(i) Bombardier Service Bulletin 84–24–47, 

Revision A, dated September 14, 2011. 

(ii) Bombardier Service Bulletin 84–24–48, 

Revision A, dated September 14, 2011. 

(iii) Bombardier Service Bulletin 84–24–49, 

Revision A, dated September 14, 2011. 

(iv) Bombardier Service Bulletin 84–24–50, 

Revision A, dated September 14, 2011. 

(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. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 84–24–47, 

Revision A, dated September 14, 2011. 

(ii) Bombardier Service Bulletin 84–24–48, 

Revision A, dated September 14, 2011. 

(iii) Bombardier Service Bulletin 84–24–49, 

Revision A, dated September 14, 2011. 

(iv) Bombardier Service Bulletin 84–24–50, 

Revision A, dated September 14, 2011. 

(3) 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. 

(4) You may review copies of the 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26774 Filed 11–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0518; Directorate 

Identifier 2010–NM–150–AD; Amendment 

39–17231; AD 2012–21–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes); and Model A310 series 

airplanes. This AD was prompted by 

events of excessive rudder pedal inputs 

and consequent high loads on the 

vertical stabilizer on several airplanes. 

This AD requires either incorporating a 

design change to the rudder control 

system and/or other systems, or 

installing a stop rudder inputs warning 

(SRIW) modification. We are issuing 

this AD to prevent loads on the vertical 

stabilizer that exceed ultimate design 

loads, which could cause failure of the 

vertical stabilizer and consequent 

reduced controllability of the airplane. 

DATES: This AD is effective December 

14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 14, 2012. 

ADDRESSES: For the service information 

identified in this 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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on May 19, 2011 (76 FR 28914). 

That NPRM proposed to require 

incorporating a design change to the 

rudder control system and/or other 

systems to address the unsafe condition. 

Relevant Service Information 

Since we issued the NPRM (76 FR 

28914, May 19, 2011), Airbus has issued 

the following service information: 

• Airbus Mandatory Service Bulletin 

A300–22–6055, Revision 01, including 

Appendix 01, dated May 31, 2012 

• Airbus Service Bulletin A300–22– 

6054, including Appendix 01, dated 

June 20, 2012 

• Airbus Service Bulletin A300–22– 

6056, dated April 25, 2012 

• Airbus Service Bulletin A300–31– 

6140, dated May 4, 2012 

• Airbus Mandatory Service Bulletin 

A310–22–2064, Revision 01, including 

Appendix 01, dated May 31, 2012 

• Airbus Service Bulletin A310–22– 

2063, including Appendix 01, dated 

June 20, 2012 

• Airbus Service Bulletin A310–22– 

2065, dated April 25, 2012 

• Airbus Service Bulletin A310–31– 

2144, dated May 4, 2012 

These service bulletins describe 

procedures related to the SRIW 

modification. The procedures include 

installing a SRIW device, activating the 

SRIW device, upgrading the flight 

control computer to introduce the SRIW 

logic, and upgrading the flight warning 

computer. We have revised paragraph 

(g) in this final rule to allow 

accomplishment of this modification as 

an optional method of compliance with 

the requirements of the AD. 


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