Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 16245 

(l) New Post-Floor Beam Hole Zero-Timing 

Inspections 

Within 15,000 flight cycles after 

accomplishing the floor beam hole zerotiming required by paragraph (k) of this AD: 

Accomplish the inspections required by 

either paragraph (l)(1) or (l)(2) of this AD; if 

any cracking is found during any inspection, 

before further flight, repair as required by 

paragraph (h)(1) of this AD. 

(1) Accomplish detailed and surface HFEC 

inspections for cracking of the web, upper 

chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 4 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 1,000 flight cycles. 

(2) Accomplish detailed and open-hole 

HFEC inspections for cracking of the web, 

upper chord, and straps of the Station 340 to 

Station 520 upper deck floor beams, by doing 

all the applicable actions, in accordance with 

Part 5. of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2443, 

Revision 2, dated August 2, 2013. If no 

cracking is found, repeat the inspections at 

intervals not to exceed 5,000 flight cycles. 

(m) Exception to Service Information 

Where Boeing Service Bulletin 747– 

53A2443, Revision 2, dated August 2, 2013, 

specifies a compliance time ‘‘after the 

revision date on this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

inspections, repairs, and modification 

required by paragraphs (g) through (j) of this 

AD, if the corresponding actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 747–53A2443, 

Revision 1, dated June 25, 2009. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (p)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2005–13–05, 

Amendment 39–14141 (70 FR 35989, June 

22, 2005), are approved as AMOCs for the 

corresponding requirements of paragraphs (g) 

through (j) (the retained actions) of this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the 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. 

Issued in Renton, Washington, on March 

17, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–06494 Filed 3–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0144; Directorate 

Identifier 2013–NM–232–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 Model DHC–8–400, –401, 

and –402 airplanes. This proposed AD 

was prompted by reports of rudder 

bearings falling out of the fore rudder 

hinge bracket during assembly. This 

proposed AD would require a proof load 

test and detailed inspections; and 

installation of a new bearing, reaming, 

or repair of the bearing if necessary. We 

are proposing this AD to detect and 

correct improper bearing installation, 

which could result in abnormal wear 

and potential increased freeplay in the 

rudder system, and resultant airframe 

vibration, leading to compromise of the 

flutter margins of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 9, 2014. 

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., 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 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– 

0144; 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: 

Ricardo Garcia, 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 516–228–7331; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


tkelley on DSK3SPTVN1PROD with PROPOSALS
16246 Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0144; Directorate Identifier 

2013–NM–232–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–2013–34, 

dated November 1, 2013 (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 reported that rudder bearings were 

falling out of the fore rudder hinge bracket 

during assembly. Investigation revealed the 

root cause as improper application of the 

adhesive compound and the lack of 

application of sealant during the installation 

of the rudder bearings into the fore rudder 

hinge bracket. The improper bearing 

installation, if not corrected, could result in 

abnormal wear and could potentially 

increase the freeplay in the rudder system. 

This may result in airframe vibration, 

eventually compromising the flutter-margins 

of the aeroplane. 

This [Canadian] AD mandates the 

inspection, and rectification as required, of 

the fore rudder bearings in the hinge bracket 

assembly. 

Required actions include a proof load 

test for slippage and freeplay. Related 

investigative actions include a detailed 

inspection of a certain bearing for 

damage, corrosion, and dimension 

conformity; and a detailed inspection of 

the fitting bore of the fore rudder hinge 

bracket for wear, damage, corrosion, and 

dimension conformity. Corrective 

actions include installation of a new 

bearing, reaming, or repair of the 

bearing. 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– 

2014–0144. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 84–27–44, Revision ‘A,’ dated 

June 10, 2009. 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. 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, this 

proposed AD would require that the 

repair approval specifically refer to the 

FAA AD. This change is intended to 

clarify the method of compliance and to 

provide operators with better visibility 

of repairs that are specifically developed 

and approved to correct the unsafe 

condition. In addition, we use the 

phrase ‘‘its delegated agent, or the DAH 

with State of Design Authority design 

organization approval, as applicable’’ in 

this proposed AD to refer to a DAH 

authorized to approve required repairs 

for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 78 airplanes of U.S. registry. 

We also estimate that it would take 

about 7 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 $46,410, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 8 work-hours and require parts 

costing $155, for a cost of $835 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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); 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 57 / Tuesday, March 25, 2014 / Proposed Rules 16247 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Bombardier, Inc.: Docket No. FAA–2014– 

0144; Directorate Identifier 2013–NM– 

232–AD. 

(a) Comments Due Date 

We must receive comments by May 9, 

2014. 

(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 

4166 through 4175, inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of 

rudder bearings falling out of the fore rudder 

hinge bracket during assembly. We are 

issuing this AD to detect and correct 

improper bearing installation, which could 

result in abnormal wear and potential 

increased freeplay in the rudder system, and 

resultant airframe vibration, leading to 

compromise of the flutter margins of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Proof Load Test 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first, do a proof load test for slippage 

and freeplay (relative movement between the 

bearing and fitting), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–44, Revision ‘A,’ 

dated June 10, 2009. If no slippage or 

freeplay is detected during the proof load test 

required by this paragraph, before further 

flight, identify the area with a marker and 

apply sealant if missing, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘A,’ dated June 10, 2009; and after 

identifying the area with a marker and 

applying sealant, no further action is 

required by this AD. 

(h) Rectification 

If any slippage or freeplay (relative 

movement between the bearing and fitting) is 

detected during the test required by 

paragraph (g) of this AD, before further flight, 

do the actions specified in paragraphs (h)(1) 

and (h)(2) of this AD. 

(1) Do a detailed inspection of bearing 

DSC8–6 for damage, corrosion, and 

dimension conformity, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘A,’ dated June 10, 2009. If damage, 

corrosion, or dimension non-conformity is 

found, before further flight, install new 

bearing DSC8–6, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–44, Revision ‘A,’ 

dated June 10, 2009. 

(2) Do a detailed inspection of the fitting 

bore of the fore rudder hinge bracket 

assembly for wear, damage, corrosion, and 

dimension conformity, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–27–44, 

Revision ‘A,’ dated June 10, 2009. 

(i) If damage, corrosion, or dimension nonconformity is found during the inspection 

required by paragraph (h)(2) of this AD, 

before further flight, ream the inside 

diameter, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–44, Revision ‘A,’ 

dated June 10, 2009. 

(ii) If bore wear or damage beyond 0.8140- 

inch diameter is found during the inspection 

required by paragraph (h)(2) of this AD, 

before further flight, repair using a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent, or the Design Approval 

Holder (DAH) with TCCA design 

organization approval). For a repair method 

to be approved, the repair approval must 

specifically refer to this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 84–27–44, dated April 13, 

2009, which is 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 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 New York 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). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. 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–2013–34, dated 

November 1, 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–2014–0144. 

(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 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06493 Filed 3–24–14; 8:45 am] 

BILLING CODE 4910–13–P 


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