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

(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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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 Coˆte 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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 60 / Friday, March 28, 2014 / Proposed Rules 17455 

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 Coˆte 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS