### 21495 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules

under the criteria of the Regulatory Flexibility Act.

We prepared an economic 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 airworthiness directive (AD):
Airbus Helicopters: Docket No. FAA–2015– 5807; Directorate Identifier 2015–SW– 063–AD. (a) Applicability

This AD applies to Airbus Helicopters Model AS355NP helicopters, certificated in any category, with an Arrius 1A1 fire extinguishing system installed.
(b) Unsafe Condition

This AD defines the unsafe condition as an incorrectly connected fire extinguishing discharge system. This condition could result in the fire extinguishing system discharging to the wrong engine compartment, failure of the fire extinguishing system to contain a fire, and loss of control of the helicopter.

(c) Comments Due Date

We must receive comments by June 13,
2016. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Within 600 hours time-in-service or at the next annual inspection, whichever occurs first, remove and install the fire extinguishing system, and remove any placards on the instrument panel if installed, in accordance with the Accomplishment Instructions, paragraph 3.B. and 3.B.1 through 3.B.2, of Airbus Helicopters Alert Service Bulletin No. AS355–26.00.10, Revision 0, dated July 2, 2015.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: George Schwab, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(g) Additional Information

(1) Eurocopter Emergency Alert Service Bulletin No. 26.00.09, Revision 0, dated September 15, 2011, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2015–0181, dated August 31, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in the AD Docket.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 2620, Extinguishing System.

Issued in Fort Worth, Texas, on April 4,
2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016–08247 Filed 4–11–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–5044; Directorate Identifier 2014–NM–166–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–8–102, –103, and –106 airplanes, and Model DHC–8–200 and –300 series airplanes. This proposed AD was prompted by a report of heat damage found on a nacelle firewall after an unsuccessful engine ground start and several events of heat damage found on direct current starter/generator terminal block assemblies. This proposed AD would require an inspection for damage on the nacelle firewalls and the terminal block assemblies and to make sure the insulating sleeves are installed and have no damage, and corrective action if necessary. We are proposing this AD to prevent arcing between the firewall and terminal blocks that are missing insulating sleeves on the conductive bushings, which could, in combination with a fuel or hydraulic fluid leak, be an ignition source for a fire.

**DATES :**  We must receive comments on this proposed AD by May 27, 2016.

**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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified inthis NPRM, contact Bombardier, Inc., QSeries 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 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–2016– 5044; 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


### 21496 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules

be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Assata Dessaline, Aerospace Engineer, Avionics and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7301; 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–2016–5044; Directorate Identifier 2014–NM–166–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–2014–03R1, dated July 24, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model DHC–8–102, –103, and –106 airplanes, and Model DHC–8–200 and –300 series airplanes. The MCAI states:

There has been one in-service report of heat damage on a nacelle firewall found after an unsuccessful engine ground start. There have also been several reports of heat damage found on Direct Current Starter/Generator terminal block assemblies, part number (P/N)
82450075–001.

The investigation determined that in all cases, the heat damage was caused by arcing between the firewall and terminal blocks with missing insulating sleeves on the conductive bushings. The insulating sleeves may have been inadvertently omitted during the incorporation of Modsum 8/1926, or during the installation of terminal blocks P/ N 82450075–001.

Arcing with the firewall becomes an ignition source, creating a potential fire hazard when combined with a fuel or hydraulic fluid leak.

The original issue of this [Canadian] AD mandated the [detailed visual] inspection [for damage to the nacelle firewalls and to make sure the insulating sleeves are installed and have no damage] and rectification [corrective actions such as installing or replacing insulating sleeves, or replacing a terminal block], as required, of the nacelle firewall and terminal block assembly P/N 82450075– 001 installed with Modsum 8/1926.

Revision 1 of this [Canadian] AD is issued to revise the Applicability to ensure that the terminal blocks have the insulating sleeves installed.

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–2016–
5044.

Relevant Service Information Under 1 CFR Part 51

Bombardier has issued Service Bulletin 8–24–92, Revision A, dated April 11, 2014. This service information describes procedures for an inspection for damage on the nacelle firewalls and the terminal block assemblies and to make sure the insulating sleeves are installed and have no damage, and corrective action if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section. 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

We estimate that this proposed AD affects 75 airplanes of U.S. registry.

We also estimate that it would take about 2 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 $12,750, or $170 per product.

In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $551, for a cost of $636 per product. 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, 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.


### 21497 Federal Register / Vol. 81, No. 70 / Tuesday, April 12, 2016 / Proposed Rules

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
Bombardier, Inc.: Docket No. FAA–2016– 5044; Directorate Identifier 2014–NM– 166–AD.
(a) Comments Due Date

We must receive comments by May 27,
2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc. airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, serial numbers 003 through 672 inclusive, on which terminal block part number 82450075–001 is installed.

(1) Model DHC–8–102, –103, and –106 airplanes.

(2) Model DHC–8–201 and –202 airplanes. (3) Model DHC–8–301, –311, and –315 airplanes.
(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical Power.
(e) Reason

This AD was prompted by a report of one event of heat damage found on a nacelle firewall after an unsuccessful engine ground start and several events of heat damage found on direct current starter/generator terminal block assemblies. We are issuing this AD to prevent arcing between the firewall and terminal blocks that are missing insulating sleeves on the conductive bushings, which could, in combination with a fuel or hydraulic fluid leak, be an ignition source for a fire.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspection and Corrective Action

Within 2,500 flight cycles or 14 months after the effective date of this AD, whichever occurs first, perform a detailed visualinspection of the right-hand side and lefthand side nacelle firewalls and terminal block assemblies, as defined in Bombardier Service Bulletin 8–24–92, Revision A, dated April 11, 2014, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–24–92, Revision A, dated April 11, 2014.

(1) If the inspection finds no damage on the engine firewalls and the terminal blocks, and that the insulating sleeves are installed on both terminal blocks, no further action is required by this AD.

(2) If the inspection finds that no insulating sleeves are installed, or the existing sleeves are damaged, and there is no damage to the nacelle firewall and terminal block, before further flight, install the replacement insulating sleeves, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–24–92, Revision A, dated April 11, 2014. (3) If the inspection finds that no insulating sleeves are installed, or any existing sleeve is damaged, and there is no damage to the nacelle firewall, but there is damage to the terminal block, before further flight, replace the terminal block assembly (which includes insulating sleeves), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–24–92, Revision A, dated April 11, 2014.

(4) If the inspection finds that no insulating sleeves are installed and there is damage to the nacelle firewall and the terminal block, repair the damage using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO).
(h) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 8–24–92, dated September 25, 2013, which is not incorporated by reference in this AD.
(i) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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, Engine and Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature.
(j) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–03R1, dated July 24, 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–2016–5044.

(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 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 March 26, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–08266 Filed 4–11–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–5468; Directorate Identifier 2015–NM–021–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company 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 The Boeing Company Model 737–600, –700, –700C, –800, and –900 series airplanes. This proposed AD was prompted by reports of paint deterioration on the surface of the main landing gear (MLG) and the early onset of corrosion in the trunnion bore of the MLG outer cylinder. This proposed AD would require identifying affected parts, repetitive external surface detailed inspection for damage of affected parts, and related investigative and corrective actions if necessary. For certain airplanes, this AD also would require a detailed inspection and bushing replacement of the trunnion bore, and related investigative and corrective action if necessary. We are proposing this AD to prevent stress corrosion cracking of the external surfaces of the MLG, which could result in a fracture of the MLG and consequent MLG collapse.

**DATES :**  We must receive comments on this proposed AD by May 27, 2016.

**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–