### 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 thatincorporate 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 toand 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 alsoestimate 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


### 67255 Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations

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.


### 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.