This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final
rules. 

# Proposed Rules Federal Register 

### 57543

Vol. 80, No. 185

Thursday, September 24, 2015

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3634; Directorate Identifier 2014–NM–203–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 supersede Airworthiness Directive (AD) 2014–20– 01, for certain Bombardier, Inc. Model CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. AD 2014–20–01 currently requires repetitive inspections for any fuel leak in the right-hand landing lights compartment, and related investigative and corrective actions if necessary. AD 2014–20–01 also provides for an optional replacement of the connector of the fuel boost pump canister of the auxiliary power unit (APU), which terminates the repetitive inspections. Since we issued AD 2014–20–01, we have determined that a terminating action for the repetitive inspections is necessary. This proposed AD would retain the repetitive inspections for any fuel leak in the right-hand landing lights compartment and the related investigative and corrective actions, and would require replacing the connector of the fuel boost pump canister of the APU. We are proposing this AD todetect and correct fuel leaks in the righthand landing lights compartment, which, in combination with the heat generated by the taxi lights and landinglights on the ground reaching the autoignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.

**DATES :**  We must receive comments on this proposed AD by November 9, 2015. **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 Bombardier, Inc., 400 Co ˆ te-Vertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.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–2015– 3634; 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 :**  Assata Dessaline, Aerospace Engineer, Avionics and Services Branch, ANE– 172, FAA, New York Aircraft Certification Office (ACO), 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–2015–3634; Directorate Identifier 2014–NM–203–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

On September 19, 2014, we issued AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014). AD 2014– 20–01 requires actions intended to
address an unsafe condition on certain Bombardier, Inc. Model CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. The preamble of AD 2014–20–01 specified that we
considered the actions an interim action and that we were considering requiring ‘‘a replacement of the connector of the fuel boost pump canister of the APU, and applicable corrective actions, which would constitute terminating action for the repetitive inspections required by
this AD action.’’

Since we issued AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014), we have determined that further rulemaking is indeed necessary; this proposed AD follows
from that determination.

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–21, dated July 10, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. The MCAI

states:

Bombardier, Inc. has discovered fuel leakage in the auxiliary power unit (APU) fuel Boost Pump (BP) canister connector cavity. On some of those aeroplanes, leakage was also noticed at the APU fuel BP electrical conduit connection in the right hand landing light compartment. The root cause of the subject fuel leak is identified to be the


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improper length of the female connector keyway located in the fuel BP canister, causing a shift of the electrical harness and
its seals.

Available data indicates that on a hot day, due to the heat generated by the taxi light and/or landing lights on the ground, temperature in the landing light compartment can reach the fuel auto ignition temperature. Therefore, presence of any fuel in the right hand landing light compartment is considered to be a safety hazard [fuel or fumes present in the right-side landing lights compartment might ignite] that warrants mitigating action.

In order to help mitigate the potential safety hazard precipitated by any fuel leakage in the right hand landing light compartment, Bombardier, Inc., has revised the Aircraft Flight Manual (AFM) through Temporary Revisions (TRs) 604/38 and 605/20 dated 16 June 2014 to restrict the operation of Taxi and Landing lights on the ground. Transport Canada issued Emergency [Canadian] AD CF–2014–17 [(http://ad.easa.europa.eu/ad/

CF-2014-17) which corresponds to FAA AD 2014–15–17, Amendment 39–17919 (79 FR 44268, July 31, 2014] to mandate incorporation of the above AFM TRs.

To address the root cause of the subject fuel leakage from the APU fuel boost pump canister wiring conduit, Bombardier, Inc. issued Alert Service Bulletin (ASB) A605– 28–008 that requires periodic [repetitive general visual] inspection[s] for fuel leaks and [applicable related investigative and corrective actions and] eventual the replacement of the discrepant fuel BP canister connectors [including related investigative and corrective actions] on affected aeroplanes. The ASB has been revised to include an additional inspection of the new connector wiring for damage and this [Canadian] AD is issued to mandate the compliance with ASB A605–28–008 Revision 2 requirements.

We also included compliance times for the terminating action. 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–

3634.
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 92 airplanes of U.S. registry.

The actions required by AD 2014–20– 01, Amendment 39–17974 (79 FR 59640, October 3, 2014), and retained inthis proposed AD take about 2 workhours per product, at an average labor rate of $85 per work-hour. Required parts cost $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2014– 20–01 is $170 per product.

We also estimate that it would take about 22 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $172,040, or $1,870 per product.

According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our
cost estimate.
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.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014), and adding the following new AD:

Bombardier, Inc.: Docket No. FAA–2015– 3634; Directorate Identifier 2014–NM–

203–AD.

(a) Comments Due Date

We must receive comments by November
9, 2015.

(b) Affected ADs

This AD replaces AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014).

(c) Applicability

This AD applies to Bombardier, Inc. Model CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes, certificated in any category, serial numbers 5906, 5910, 5912, 5917, 5919 through 5932 inclusive, 5934, 5935, 5939, 5940, 5942, and 5948.

(d) Subject

Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

This AD was prompted by a report of fuel leaks in the auxiliary power unit (APU) fuel boost pump canister connector cavity and in the right-hand landing lights compartment from the APU fuel boost pump electrical conduit connection and by a determination that terminating action for the repetitive inspections is necessary. We are issuing this
AD to detect and correct fuel leaks in the right-hand landing lights compartment,


### 57545 Federal Register / Vol. 80, No. 185 / Thursday, September 24, 2015 / Proposed Rules

which, in combination with the heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Retained Repetitive Inspections for Fuel Leaks With No Changes

This paragraph restates the requirements of paragraph (g) of AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014) with no changes. Within 25 flight hours after October 20, 2014, (the effective date of AD 2014–20–01): Do a general visual inspection for any fuel leak in the right-hand landing lights compartment, and do all applicable related investigative and corrective actions, in accordance with Part A of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A605–28– 008, Revision 02, dated July 9, 2014, except as required by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 8 flight hours until the replacement specified in paragraph (j) of this AD has been accomplished.

(h) Retained Corrective Action if Fuel Leak Is Found During Related Investigative Actions With No Changes

This paragraph restates the requirements of paragraph (h) of AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014) with no changes. If any fuel leak is found during the related investigative actions required by paragraph (g) of this AD: Before further flight, do the terminating action specified in paragraph (j) of this AD, or do corrective actions using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO,the approval must include the DAOauthorized signature.

(i) Retained Inspection of Connector Wiring With No Changes

This paragraph restates the requirements of paragraph (j) of AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014) with no changes. For airplanes having new connectors installed, in accordance with Part B of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A605–28– 008, dated April 21, 2014: Within 6 months or 150 flight hours after October 20, 2014, (the effective date of AD 2014–20–01), whichever occurs first, do a detailed inspection for damage (cuts) of the connector wiring, in accordance with Part B of the Accomplishment Instructions of Bombardier Alert Service Bulletin A605–28–008, Revision 02, dated July 9, 2014. If any damage (cuts) is found on the wires, before further flight, replace the wire with a new wire identified in kit 605K28–008A, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A605–28–008, Revision 02, dated July 9, 2014.

(j) New Requirement: Terminating Action— Replacement of Connector

Within 5 months, or 150 flight hours after the effective date of this AD, replace the connector of the fuel boost pump canister of the APU and do all applicable related investigative actions, in accordance with Part B of the Accomplishment Instructions of
Bombardier Alert Service Bulletin A605–28– 008, Revision 02, dated July 9, 2014. Accomplishing this replacement terminates the repetitive actions required by paragraph (g) of this AD provided that the following actions are done, as applicable.

(1) If any damage (cuts) is found on the wires, before further flight, replace the wire
with a new wire identified in kit 605K28– 008A, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A605–28–008, Revision 02, dated July 9, 2014.

(2) If any damage is found on an O-ring, before further flight, replace the O-ring with a new O-ring, in accordance with the Accomplishment Instructions of Bombardier Alert Service Bulletin A605–28–008, Revision 02, dated July 9, 2014.

(3) If any fuel leak is found, before further flight, do corrective actions 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 DAOauthorized signature.

(k) Retained Credit for Previous Actions With a Redesignated Paragraph

This paragraph restates paragraph (k) of AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014) with a redesignated paragraph. This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before October 20, 2014, (the effective date of AD 2014–20–01, Amendment 39–17974 (79 FR 59640, October 3, 2014) using Bombardier Alert Service Bulletin A605–28–008, Revision 01, dated May 28, 2014, 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, 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: As of the effective date of this AD, 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.

(m) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–21, dated July 10, 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–

2015–3634.

(2) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu 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 September 15, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–24020 Filed 9–23–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3629; Directorate Identifier 2015–NM–011–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Dassault Aviation 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
Dassault Aviation Model MYSTERE– FALCON 50, MYSTERE–FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This proposed AD was prompted by a report of an in-flight lightning strike to the WHELEN anti-collision light located on the top of the vertical fin tip that caused severe damage and induced the loss of some airplane functions. This proposed AD would require modification of the anti-collision light bonding. We are