Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32061 

(l) New Requirement of This AD: Repetitive 

Inspections for Certain Airplanes 

Repeat the inspection specified in 

paragraph (k) of this AD thereafter at the 

applicable interval specified in paragraphs 

(l)(1) and (l)(2) of this AD. 

(1) For airplanes whose flight time average 

is equal to or more than 1.5 hours, at 

intervals not to exceed 8,500 flight cycles or 

18,500 flight hours, whichever occurs first. 

(2) For airplanes whose flight time average 

is less than 1.5 hours, at intervals not to 

exceed 9,200 flight cycles or 13,700 flight 

hours, whichever occurs first. 

(m) New Requirement of This AD: Corrective 

Actions 

(1) If any cracking is detected or suspected 

during any detailed visual inspection 

required by paragraph (i) or (j) of this AD: 

Before further flight, confirm this finding and 

the length of this cracking by conducting an 

HFEC inspection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011, except as specified in paragraph (o) of 

this AD. If no cracking is confirmed during 

the HFEC inspection, accomplish the 

applicable repetitive inspections required by 

paragraphs (j) and (l) of this AD at the 

applicable time specified in those 

paragraphs. 

(2) If any cracking is found during any 

HFEC inspection required by paragraph (i), 

(j), (k) or (l) of this AD: Before further flight, 

do the applicable actions specified in 

paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. 

(i) If the cracking is 75 mm or less per each 

rib bay: Before further flight, repair the 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011, except as specified in paragraph (o) of 

this AD. Do repetitive detailed visual 

inspections of the repaired area thereafter at 

intervals not to exceed 50 flight cycles or 110 

flight hours, whichever occurs first, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6044, Revision 04, including Appendix 

01, dated August 19, 2011. Within 250 flight 

cycles or 550 flight hours, whichever occurs 

first after doing the temporary repair, do a 

permanent repair of the repaired area, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6044, Revision 04, including Appendix 

01, dated August 19, 2011. 

(ii) If the cracking exceeds 75 mm per any 

rib bay: Before further flight, install Airbus 

Modification 10089, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011. Do an LFEC inspection thereafter at the 

intervals specified in paragraph (l) of this 

AD. 

(3) If any cracking is found during any 

inspection required by this AD at fastener 

holes 1A, 1, or 2: Before further flight, repair 

the cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (i) through (l) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A300–57–6044, Revision 03, 

dated April 7, 1999, including Appendix 01, 

which is not incorporated by reference in this 

AD. 

(o) Exception to Service Information 

Specification 

Although Airbus Service Bulletin A300– 

57–6044, Revision 04, including Appendix 

01, dated August 19, 2011, specifies to 

submit information to Airbus, this AD does 

not require that submission. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0221, dated 

September 19, 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–2015–1426. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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 May 19, 

2015. 

Dionne Palmero, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13335 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1423; Directorate 

Identifier 2014–NM–173–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757–200 Series 

Airplanes Modified by Supplemental 

Type Certificate (STC) ST01529SE or 

STC ST02278SE 

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 757–200 

series airplanes modified by particular 

STCs. This proposed AD was prompted 

by reports of a main cargo door being 

blown past its full open position while 

on the ground during gusty wind 

conditions, which resulted in 

uncontrolled fall down to its closed 

position. This proposed AD would 

require installing a new placard and 

bracket, replacement of an existing 

placard, and replacement of the main 

cargo door control panel. We are 

proposing this AD to prevent damage to 

the main cargo door, which could result 

in rapid decompression, leading to inflight breakup. 

DATES: We must receive comments on 

this proposed AD by July 20, 2015. 

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 Precision 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
32062 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

Conversions LLC, 4900 SW Griffith 

Drive, Suite 133, Beaverton, OR 97005; 

ATTN: Steven A. Lopez; phone: 503– 

601–3001; email: Steven.Lopez@

precisionaircraft.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–2015– 

1423; 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: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6513; 

fax: 425–917–6590; email: 

Narinder.Luthra@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– 

2015–1423; Directorate Identifier 2014– 

NM–173–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 a main cargo 

door being blown past its full open 

position during gusty wind conditions, 

resulting in a subsequent uncontrolled 

fall down to its closed position. It was 

determined that the Precision 

Conversions freighter conversion 

installs a main cargo door that, in 

certain wind conditions, can rotate open 

past the full-open position. This can 

result in damage to the door and 

surrounding structure, which can go 

unnoticed by the crew. If a damaged 

airplane takes off and is pressurized per 

normal procedures the cargo door could 

fail. This condition, if not corrected, 

could result in rapid decompression, 

leading to in-flight breakup. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Precision Conversions 

LLC Service Bulletin PC–757–11–0023, 

dated August 1, 2014. The service 

information describes procedures for 

installing a new placard and bracket, 

replacement of an existing placard, and 

replacement of the main cargo door 

control panel. This service information 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this NPRM. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 9 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 

Installation ............................... 6 work-hours × $85 per hour = $510 ..................................... $0 $510 $4,590 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32063 

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– 

2015–1423; Directorate Identifier 2014– 

NM–173–AD. 

(a) Comments Due Date 

We must receive comments by July 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 757–200 series airplanes modified by 

the applicable supplemental type certificate 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) ST01529SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/0AF09C3701A237EE86257A5D0064B3AA?

OpenDocument&Highlight=st01529se). 

(2) ST02278SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/E54B5289A2E9F6EF86257B7F0056EDAF?

OpenDocument&Highlight=st02278se). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 11, Placards and Markings. 

(e) Unsafe Condition 

This AD was prompted by reports of a 

main cargo door being blown past its full 

open position while on the ground during 

gusty wind conditions, which resulted in 

uncontrolled fall down to its closed position. 

We are issuing this AD to prevent damage to 

the main cargo door, which could result in 

rapid decompression, leading to in-flight 

breakup. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation 

Within 90 days after the effective date of 

this AD, install a new placard and bracket, 

replace the existing placard, and replace the 

main cargo door control panel, in accordance 

with the Accomplishment Instructions of 

Precision Conversions LLC Service Bulletin 

PC–757–11–0023, dated August 1, 2014. 

(h) 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 (i)(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. 

(i) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM 120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6513; fax: 425–917–6590; 

email: Narinder.Luthra@faa.gov. 

(2) For service information identified in 

this AD, contact Precision Conversions LLC, 

4900 SW Griffith Drive, Suite 133, Beaverton, 

OR 97005; ATTN: Steven A. Lopez; phone: 

503–601–3001; email: Steven.Lopez@

precisionaircraft.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. 

Issued in Renton, Washington, on May 18, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13358 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1422; Directorate 

Identifier 2014–NM–125–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 98–18–26, 

for certain Airbus Model A320 series 

airplanes. AD 98–18–26 currently 

requires repetitive inspections to detect 

fatigue cracking of the front spar vertical 

stringers on the wings; and repair, if 

necessary. Since we issued AD 98–18– 

26, we have received reports that 

indicate new repetitive inspections 

having new thresholds and intervals are 

needed and that additional work is 

needed to accomplish the inspections 

on airplanes on which a previous 

modification has been accomplished. 

This proposed AD would require 

repetitive high frequency eddy current 

(HFEC) inspections for cracking of the 

radius of the front spar vertical stringers 

and the horizontal floor beam on frame 

36, and a rototest inspection for 

cracking of the fastener holes of the 

front spar vertical stringers on frame 36, 

and repair if necessary. We are 

proposing this AD to detect and correct 

fatigue cracking of the front spar vertical 

stringers on the wings, which could 

result in the reduced structural integrity 

of the airframe. 

DATES: We must receive comments on 

this proposed AD by July 20, 2015. 

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 Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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–2015– 

1422; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS