## 17453 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Proposed Rules

(1) At the initial compliance times (thresholds) specified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; or Airbus A300–600 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; as applicable; with the compliance times starting from the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.

(i) Since first flight of the airplane. (ii) Since the applicable part was new or refurbished if the part’s life (in flight hours, flight cycles, landings, or calendar time, as applicable) can be conclusively determined.

(2) Within 3 months after doing the revision of the ALS of the ICA required by paragraph (h) of this AD.

Note 1: For additional guidance on the trimmable horizontal stabilizer actuator (THSA) life limits, refer to Airbus OIT SE 999.0074/05/BB, dated August 3, 2005.

Note 2: For additional guidance on the THSA life limits and calculation method for unknown history of parts, refer to Airbus OIT SE 999.0008/07/LB, dated January 16, 2007; and Airbus Service Information Letter 05– 008, Revision 01, dated February 21, 2007.

(h) Retained Revision of Airworthiness Limitation Section (ALS) To Incorporate Limitations and Maintenance Tasks for Ageing Systems Maintenance

This paragraph restates the requirements of paragraph (o) of AD 2009–06–06, Amendment 39–15842 (74 FR 12228, March 24, 2009), with revised affected airplane language. For airplanes on which any life limitation/maintenance task has been complied with in accordance with the requirements of paragraph (f), (g), (k), (l), or (m) of AD 2009–06–06: The last accomplishment of each limitation/task must be retained as a starting point for the accomplishment of each corresponding limitation/task interval now introduced Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 01, dated December 21, 2006; and Airbus A300–600 ALS Part 4— Ageing Systems Maintenance, Revision 01, dated December 21, 2006; as applicable.
(i) Retained No Alternative Inspections/ Limitations

This paragraph restates the requirements of paragraph (p) of AD 2009–06–06, Amendment 39–15842 (74 FR 12228, March 24, 2009). Except as provided by paragraph (l) of this AD: After accomplishing the actions specified in paragraphs (g) and (h) of this AD, no alternative inspection, inspection intervals, or limitations may be used, except as required by paragraph (j) of this AD.
(j) New Requirements of This AD: Maintenance Program Revision

Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated November 30, 2012 (for Model A310 series airplanes); or Airbus A300–600 ALS Part 4— Ageing Systems Maintenance, Revision 02, dated April 18, 2012 (for Model A300–600 series airplanes). For all limitation/ replacement/inspection tasks identified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated November 30, 2012; and Airbus A300–600 ALS Part 4— Ageing Systems Maintenance, Revision 02, dated April 18, 2012; the initial compliance times for the tasks are at the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, as applicable. Doing any limitation/ replacement/inspection task required by this paragraph terminates the corresponding task required by paragraph (g) of this AD.

(1) At the initial compliance times (thresholds) specified in Airbus A310 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated November 30, 2012; or Airbus A300–600 ALS Part 4—Ageing Systems Maintenance, Revision 02, dated April 18, 2012; as applicable; with the compliance times starting from the later of the times specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD.

(i) Since first flight of the airplane. (ii) Since the applicable part was new or refurbished if the part’s life (in flight hours, flight cycles, landings, or calendar time, as applicable) can be conclusively determined.

(2) Within 3 months after the effective date of this AD.

(k) New Limitation: No Alternative Actions or Intervals

After accomplishment of the revision required by paragraph (j) of this AD, no alternative actions (e.g., inspections) or intervals, may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of 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, 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval). You are required to ensure the product is airworthy before it is returned to service.
(m) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0075, dated March 20, 2013, 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–
2014–0173.

(2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@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 March 19, 2014. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–06908 Filed 3–27–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0175; Directorate Identifier 2014–NM–014–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 CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This proposed AD was prompted by reports that elevator power control unit (PCU) shear pins may fail prematurely. This proposed AD would require repetitive replacement of the elevator PCU shear pins. We are proposing this AD to prevent PCU failure of elevator PCU sheer pins. If all pins fail on one elevator, the elevator surface would become inoperative, which could reduce the controllability of the airplane and could result in a loss of redundancy for flutter prevention.

**DATES** 

### : We must receive comments on this proposed AD by May 12, 2014.


## 17454 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Proposed Rules

**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 ; 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–2014– 0175; 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**

### : Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; 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–2014–0175; Directorate Identifier 2014–NM–014–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–2014–04, dated January 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI
states:

It was found that the elevator power control unit (PCU) shear pins may fail prematurely. The failure of an elevator PCU shear pin is dormant. There are three PCUs on each elevator. If all three PCU shear pins failed on one elevator, the elevator surface would become inoperative, which could reduce the controllability of the aeroplane and could result in a loss of redundancy for flutter prevention.

This [Canadian] AD mandates the repetitive replacement of the elevator PCU shear pins to prevent premature elevator PCU shear pin failures.



### You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–
2014–0175.

Relevant Service Information

Bombardier has issued Service Bulletin 601R–55–008, Revision B, dated March 12, 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 575 airplanes of U.S. registry.

We also estimate that it would take about 4 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 about $41 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $219,075, or $381 per product. 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.


## 17455 Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Proposed Rules

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. Amend § 39.13 by adding the following new airworthiness directive (AD):
Bombardier, Inc.: Docket No. FAA–2014– 0175; Directorate Identifier 2014–NM– 014–AD.
(a) Comments Due Date

We must receive comments by May 12,
2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent.
(d) Subject

Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Reason

This AD was prompted by reports of the possibility that elevator power control unit (PCU) shear pins may fail prematurely. We are issuing this AD to prevent PCU failure of elevator PCU sheer pins. If all pins fail on one elevator, the elevator surface would become inoperative, which could reduce the controllability of the airplane and could result in a loss of redundancy for flutter prevention. (f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Repetitive Replacements

Within 6,600 flight hours or 48 months after the effective date of this AD, whichever occurs first: Replace the elevator PCU shear pins, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–55–008, Revision B, dated March 12, 2014. Repeat the replacement thereafter at intervals not to exceed 6,600 flight hours or 48 months from the most recent replacement, whichever occurs first.
(h) Optional Method for Replacement

Replacing the elevator PCU shear pins, using a method approved by the Program Manager, Continuing Operational Safety, FAA, New York ACO; or Transport Canada Civil Aviation (TCCA) (or its delegated agent, or the Design Approval Holder (DAH) with TCCA design organization approval) as applicable, is a method of compliance for any replacement required by paragraph (g) of this AD. For a replacement method to be approved, the replacement approval must specifically refer to this AD.

Note 1 to paragraph (h) of this AD: Guidance for doing replacements specified in paragraph (h) of this AD may be found in Canadair Regional Jet Model CL–600–2B19 Aircraft Maintenance Manual, CSP A–001, Task Number 55–21–27–960–802.

(i) Credit for Previous Actions

This paragraph provides credit for action required by paragraph (g) of this AD, if the action was performed before the effective date of this AD using Bombardier Service Bulletin 601R–55–008, dated July 12, 2013; or Bombardier Service Bulletin 601R–55– 008, Revision A, dated January 8, 2014, which are not incorporated by reference in this AD.
(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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the DAH with a State of Design Authority’s design organization approval). You are required to ensure the product is airworthy before it is returned to service.
(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–04, dated January 13, 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 it in Docket No. FAA–2014–0175.

(2) For service information identified in this 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 ; 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 19, 2014. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–06912 Filed 3–27–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0168; Directorate Identifier 2013–NM–208–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 certain The Boeing Company Model 787–8 airplanes. This proposed AD was prompted by failure of the anchor attachment on the occupant restraint system on the standard attendant seat due to an undersized attachment fitting. This proposed AD would require replacing the existing restraint attachment fitting on the standard attendant seat with a new, improved attachment fitting. We are proposing this AD to prevent failure of the restraint attachment fitting and consequent detachment of the attendant seat during an emergency landing, which could cause injury to passengers and crew and could impede a rapid evacuation.

**DATES** 

### : We must receive comments on this proposed AD by May 12, 2014.

**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