23694 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 

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 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. F– 

2004–176 and AD No. F–2004–178, both 

dated November 10, 2004. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail rotor blades. 

Issued in Fort Worth, Texas, on April 11, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09417 Filed 4–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0334; Directorate 

Identifier 2013–NM–027–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 757 airplanes. 

This proposed AD was prompted by a 

report of a broken forward support 

fitting at the inboard track of the 

inboard flap. This proposed AD would 

require repetitive inspections of the 

forward support fitting assemblies of the 

inboard track of the left and right 

inboard flaps for cracking, and 

corrective actions if necessary. We are 

proposing this AD to detect and correct 

cracking of the forward support fitting 

assembly, which could result in loss of 

inboard flap control and subsequent loss 

of airplane control. 

DATES: We must receive comments on 

this proposed AD by June 6, 2013. 

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 in 

this proposed 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 Ave 

SW., Renton, WA 98057. 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; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6440; 

fax: (425) 917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0334; Directorate Identifier 2013– 

NM–027–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 because of 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 

We received a report of a broken 

forward support fitting assembly at the 

inboard track of the inboard flap. During 

a post-flight taxi, pilots noticed a FLAP 

TE DISAGREE message on the engine 

indication and crew alerting system 

(EICAS). Maintenance personnel found 

that both components of the forward 

support fitting assembly had broken, 

causing the inboard track and 

transmission to drop 8 inches into the 

wheel well. The airplane had 

accumulated 22,328 total flight cycles. 

Metallurgical analysis found that cracks 

had initiated at a compound radius in 

each component flange common to the 

main landing gear (MLG) beam. Each 

crack was propagated by fatigue and 

was followed by final ductile rupture. 

This condition, if not detected and 

corrected, could result in loss of inboard 

flap control and subsequent loss of 

airplane control. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 757–57– 

0071, dated September 12, 2012. For 

information on the procedures and 

compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0334. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

In addition, the phrase ‘‘corrective 

actions’’ might be used in this proposed 

AD. ‘‘Corrective actions’’ are actions 

that correct or address any condition 

found. Corrective actions in an AD 

could include, for example, repairs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 690 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 23695 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

High-frequency eddy current 

inspection.

11 work-hours × $85 per hour 

= $935, per inspection 

cycle 

None ............... $935, per inspection cycle .... $645,150, per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement ............................. 7 work-hours × $85 per hour = $595, per assembly ................... $10,000 $10,595, per assembly. 

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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2013–0334; Directorate Identifier 2013– 

NM–027–AD. 

(a) Comments Due Date 

We must receive comments by June 6, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200, –200PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 5753, Trailing edge flaps. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

broken forward support fitting at the inboard 

track of the inboard flap. We are issuing this 

AD to detect and correct cracking of the 

forward support fitting assembly, which 

could result in loss of inboard flap control 

and subsequent loss of airplane control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Except as provided by paragraph (h) of this 

AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 757–57– 

0071, dated September 12, 2012: Do a high 

frequency eddy current (HFEC) inspection for 

cracking in the forward support fitting 

assemblies of the inboard track of the left and 

right inboard flaps, and do all applicable 

corrective actions, in accordance with 

paragraph 3.B.2. of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–57–0071, dated 

September 12, 2012. Do all applicable 

corrective actions before further flight. 

Thereafter, repeat the inspections at intervals 

not to exceed 6,000 flight cycles, except as 

required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) For Group 1 airplanes as identified in 

Boeing Special Attention Service Bulletin 

757–57–0071, dated September 12, 2012, on 

which any forward support fitting assembly 

is replaced: Do the next inspection before 

15,000 flight cycles has accumulated on that 

assembly. 

(2) For Group 2 airplanes as identified in 

Boeing Special Attention Service Bulletin 

757–57–0071, dated September 12, 2012, on 

which any forward support fitting assembly 

is replaced: Do the next inspection before 

18,000 flight cycles has accumulated on that 

assembly. 

(h) Exception to the Service Information 

(1) Where Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 12, 

2012, specifies compliance times ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance times ‘‘after the 

effective date of this AD.’’ 

(2) Paragraphs 3.B.1. and 3.B.3. of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–57– 


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23696 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 

0071, dated September 12, 2012, are not 

required by this AD. 

(i) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 the 

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. 

(j) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6440; fax: (425) 917–6590; 

email: nancy.marsh@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 Ave. NW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on April 12, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09407 Filed 4–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0020; Directorate 

Identifier 2010–SW–107–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH (ECD) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for ECD 

Model MBB–BK 117 C–2 helicopters. 

This proposed AD would require 

inspecting the rigging of the powerboosted control system and, if there is 

a nonparallel gap between the rigging 

wedges and the inner sleeves, 

performing a rigging procedure. This 

proposed AD is prompted by the 

discovery, during rigging of the main 

rotor controls, of movement of the 

longitudinal main rotor actuator piston 

after shut-down of the external pump 

drive. Such movement could cause 

incorrect rigging results. The proposed 

actions are intended to prevent incorrect 

rigging results, which could impair 

freedom of movement of the upper 

controls and subsequent reduced 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by June 21, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic 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 service information identified in 

this proposed AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http:// 

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Manager, FAA, Rotorcraft 

Directorate, Safety Management Group, 

2601 Meacham Blvd., Fort Worth, TX 

76137; telephone (817) 222–5110; email 

jim.grigg@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued AD No. 2010–0248, 

dated November 26, 2010 (AD 2010– 

0248), to correct an unsafe condition for 

the ECD Model MBB–BK 117 C–2 

helicopters. EASA advises that during 

rigging of the main rotor controls, it was 


tkelley on DSK3SPTVN1PROD with PROPOSALS