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

53078 

Vol. 78, No. 167 

Wednesday, August 28, 2013 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0704; Directorate 

Identifier 2013–NM–074–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 747–200B, 

–200C, –200F, –300, and 747SR series 

airplanes. This proposed AD was 

prompted by reports of cracks of both 

lower chords and web on certain 

outboard struts. This proposed AD 

would require repetitive inspections for 

cracking of the lower spar chords and 

web, web lower spar chord 

modification, which includes 

inspections for cracking of the lower 

spar chords, and repetitive post 

modification inspections for cracking of 

the lower spar web and chord; and 

applicable corrective actions. We are 

proposing this AD to prevent cracked 

chords and web on certain outboard 

struts, which, if the chord severs, could 

result in reduced structural integrity of 

the diagonal brace load path and of the 

strut-to-wing attachment, and 

consequent separation of a strut and 

engine from the airplane during flight. 

DATES: We must receive comments on 

this proposed AD by October 15, 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 Avenue 

SW., Renton, Washington. 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

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

425–917–6590; email: 

nathan.p.weigand@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– 

2013–0704; Directorate Identifier 2013– 

NM–074–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 reports of cracks at 

nacelle station 300 on both lower chords 

and the web on outboard strut no. 1. 

Outboard strut no. 1 had approximately 

41,300 total flight cycles and 63,300 

total flight hours. The cracking was due 

to fatigue from normal operating loads. 

The chords are the main load path for 

the diagonal brace attach fitting. 

Cracked and severed chords and web on 

certain outboard struts could result in 

reduced structural integrity of the 

diagonal brace load path, and 

compromise the strut-to-wing 

attachment, which could result in 

consequent separation of a strut and 

engine from the airplane during flight. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–54A2237, dated March 14, 

2013. For information on the procedures 

and compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0704. 

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 these same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

The phrase ‘‘corrective actions’’ is 

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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 167 / Wednesday, August 28, 2013 / Proposed Rules 53079 

Differences Between the Proposed AD 

and the Service Information 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 25 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Inspections .................... 27 work-hours × $85 per hour = $2,295 per inspection cycle.$0 $2,295 per inspection 

cycle.

$57,375 per inspection 

cycle. 

Modification ................... 11 work-hours × $85 per hour = $935 ............... 95 1,030 ............................ 25,750. 

Post Modification Inspection.27 work-hours × $85 per hour = $2,295 per inspection cycle.0 2,295 per inspection 

cycle.

$57,375 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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– 

2013–0704; Directorate Identifier 2013– 

NM–074–AD. 

(a) Comments Due Date 

We must receive comments by October 15, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–200B, 747–200C, 747–200F, 747– 

300, and 747SR series airplanes, certificated 

in any category, as identified in Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

of both lower chords and web on certain 

outboard struts. We are issuing this AD to 

prevent cracked chords and web on certain 

outboard struts, which, if the chord severs, 

could result in reduced structural integrity of 

the diagonal brace load path and of the strutto-wing attachment, and consequent 

separation of a strut and engine from the 

airplane during flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial and Repetitive Inspections 

(1) Except as required by paragraph (j)(1) 

of this AD, at the compliance time specified 

in table 1 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

54A2237, dated March 14, 2013: Do a 

detailed inspection for cracking of the lower 

spar chords and web, a high frequency eddy 

current (HFEC) inspection for cracking of the 

lower spar chords, and all applicable repairs 

and modifications, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013, except as required by paragraph 

(j)(2) of this AD. If no cracking is found, 

repeat the inspections thereafter at intervals 

not to exceed 600 flight cycles, until the 

actions specified in paragraph (h) of this AD 

have been accomplished. Do all applicable 

corrective actions before further flight. 

Accomplishing a repair and modification, 

including open-hole HFEC inspections for 

cracking and applicable corrective actions 

required by this paragraph terminates the 

actions required by paragraphs (g) and (h) of 

this AD for the repaired and modified strut 

only. The open-hole HFEC inspection for 

cracking must be done before the 

modification. 

(h) Inspection and Modification 

Except as required by paragraph (j)(1) of 

this AD, at the compliance time specified in 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
53080 Federal Register / Vol. 78, No. 167 / Wednesday, August 28, 2013 / Proposed Rules 

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

Alert Service Bulletin 747–54A2237, dated 

March 14, 2013: Do a detailed inspection for 

cracking of the lower spar chords and web, 

an HFEC inspection for cracking of the lower 

spar chords, a lower spar chord modification, 

including open-hole HFEC inspections for 

cracking in the chord and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2237, dated March 

14, 2013, except as required by paragraph 

(j)(2) of this AD. Do all applicable corrective 

actions before further flight. Doing the 

actions specified in this paragraph terminates 

the requirements of paragraph (g) of this AD 

for the modified strut only. The open-hole 

HFEC inspection for cracking must be done 

before the modification. 

(i) Post Modification Repetitive Inspections 

For airplanes on which a modification 

required by paragraph (g) or (h) of this AD 

has been done: At the compliance time 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2237, dated March 14, 

2013, do a detailed inspection for any 

cracking of the lower spar web and chord, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, except 

as required by paragraph (j)(2) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed 18 months. Do all applicable 

corrective actions before further flight. 

(j) Exceptions 

(1) Where Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, 

specifies a compliance time after the original 

issue date on the service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–54A2237, dated March 14, 2013, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

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, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on August 

21, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20969 Filed 8–27–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0703; Directorate 

Identifier 2013–NM–004–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 DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 series airplanes. This proposed AD 

was prompted by a report of a pilot 

commanding an in-flight engine shut 

down in response to a low oil pressure 

warning indication. Further 

investigation revealed the mounting 

studs in the engine mounted alternating 

current (AC) generator mounting plate 

were pulled out of position and the 

threaded interface in the plate was 

corroded. This proposed AD would 

require repetitive inspections for 

discrepancies on certain AC generator 

mounting adapters, and replacing 

discrepant adapters with serviceable 

ones. This proposed AD would also 

require revising the maintenance 

program to incorporate a repetitive task 

specified in certain temporary revisions. 

We are proposing this AD to detect and 

correct corrosion in the AC generator 

mounting plate, which could result in a 

gap between the AC generator and the 

generator mounting plate, and cause 

loss of engine oil and consequent engine 

failure. 

DATES: We must receive comments on 

this proposed AD by October 15, 2013 

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 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. 

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 

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 Flight Test Branch, ANE– 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS