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, 


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32064 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

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–2015–1422; Directorate Identifier 

2014–NM–125–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 

On August 28, 1998, we issued AD 

98–18–26, Amendment 39–10742 (63 

FR 47423, September 8, 1998). AD 98– 

18–26 requires repetitive inspections to 

detect fatigue cracking of the front spar 

vertical stringers on the wings, which 

could result in the reduced structural 

integrity of the airframe on certain 

Airbus Model A320 series airplanes. AD 

98–18–26 contains a modification that 

provides a terminating action for the 

repetitive inspection requirements. 

Since we issued AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998), 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 where shims 

were installed under the heads of 2 

fasteners at the top end of the front spar 

vertical stringers using Airbus Service 

Bulletin A320–57–1017, dated 

September 3, 1991; or Airbus Service 

Bulletin A320–57–1017, Revision 01, 

dated March 17, 1997, or on which 

modification 21290P1546 was 

accomplished during production. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0069, dated March 19, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Airbus 

Model A320–211, –212, and –231 

airplanes. The MCAI states: 

During center fuselage certification full 

scale fatigue test, cracks were found on the 

front vertical stringer at frame 36. Analysis of 

these findings indicated that a number of inservice aeroplanes could be similarly 

affected. 

This condition, if not detected and 

corrected, could lead to crack propagation 

and consequent deterioration of the 

structural integrity of the aeroplane. 

To address this potential unsafe condition, 

[Directorate General for Civil Aviation] 

DGAC France AD 97–311–105 [which 

corresponds to FAA AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998)] was issued to require 

repetitive [HFEC] inspections [for cracking] 

in accordance with the instruction of Airbus 

Service Bulletin (SB) A320–57–1016. At the 

same time, the modification provided by 

Airbus SB A320–57–1017 was considered to 

be terminating action for the repetitive 

inspections required by DGAC France AD 

97–311–105. 

Since that [DGAC] AD was issued, and 

following new analysis, modification per 

Airbus SB A320–57–1017 is no longer 

considered to be terminating action for the 

repetitive inspections as required by DGAC 

France AD 97–311–105. 

Aeroplanes with [manufacturer serial 

number] MSN 0080 up to 0155 inclusive 

have been delivered with the addition of a 5 

[millimeter] mm thick light alloy shim under 

the heads of 2 fasteners at the top end of the 

front spar vertical stringers (Airbus 

modification 21290P1546, which is the 

production line equivalent to in-service 

modification through Airbus SB A320–57– 

1017). From MSN 0156 and higher, all 

aeroplanes are delivered with vertical 

stiffeners of the forward wing spar upper end 

with stiffener cap thickness increased from 4 

to 6 mm (Airbus modification 21290P1547). 

Prompted by these findings, Airbus issued 

SB A320–57–1178 to introduce new 

repetitive inspections with new thresholds 

and intervals. 

For the reasons described above, DGAC 

France AD 97–311–105 is superseded and 

this [EASA] AD requires the repetitive 

inspections at new thresholds and intervals. 

After EASA issued [proposed 

airworthiness directive] PAD 14–021, it was 

discovered that additional work [HFEC 

inspections for cracking of the radius of spar 

vertical stringers and horizontal beam in the 

center fuselage of frame 36, and a rototest 

inspection for cracking of the fastener holes 

of the spar vertical stringers radius on Frame 

36 and repair if necessary], to be included in 

Revision 01 of Airbus SB A320–57–1178, is 

required to accomplish the inspections. This 

Final [EASA] AD has been amended 

accordingly. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1422. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1178, Revision 01, including 

Appendix 01, dated May 28, 2014. The 

service information describes 

procedures for inspecting the radius of 

the front spar vertical stringers and the 

horizontal floor beam on frame 36 for 

cracking. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 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 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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Although EASA AD 2014–0069, dated 

March 19, 2014, specifies to accomplish 

an HFEC inspection for cracking of the 

vertical stiffeners radius, this proposed 

AD would require accomplishing an 

HFEC inspection for cracking of the 

radius of the front spar vertical 

stringers, since Airbus Service Bulletin 

A320–57–1178, Revision 01, Appendix 

01, dated May 28, 2014, specifies the 

inspection is of the front spar vertical 

stringers. 

Costs of Compliance 

We estimate that this proposed AD 

affects 17 airplanes of U.S. registry. 

We also estimate that it would take 

about 24 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 


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rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $34,680, or $2,040 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 49 work-hours and require parts 

costing $1,210, for a cost of $5,375 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); 

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 

removing Airworthiness Directive (AD) 

98–18–26, Amendment 39–10742 (63 

FR 47423, September 8, 1998), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–1422; 

Directorate Identifier 2014–NM–125–AD. 

(a) Comments Due Date 

We must receive comments by July 20, 

2015. 

(b) Affected ADs 

This AD replaces AD 98–18–26, 

Amendment 39–10742 (63 FR 47423, 

September 8, 1998). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, and –231 airplanes, certificated in 

any category, manufacturer serial numbers 

0001 through 0155 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by cracks found on 

the front vertical stringer at frame 36. This 

AD was also prompted by 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. We are issuing 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Within the applicable compliance times 

specified in paragraphs (h)(1) through (h)(4) 

of this AD, do a high frequency eddy current 

(HFEC) inspection for cracking of the radius 

of the front spar vertical stringers and the 

horizontal floor beam on frame 36, and do a 

rototest inspection for cracking of the 

fastener holes of the front spar vertical 

stringers on frame 36, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1178, Revision 01, 

including Appendix 01, dated May 28, 2014. 

Repeat the inspections thereafter at the 

compliance times specified in paragraphs 

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

(1) For Configuration 1 airplanes identified 

in paragraph (h)(1) of this AD: At intervals 

not to exceed 8,800 flight cycles or 17,700 

flight hours, whichever occurs first. 

(2) For Configuration 2, 3, and 4 airplanes 

identified in paragraphs (h)(2) through (h)(4) 

of this AD: At intervals not to exceed 24,900 

flight cycles or 49,800 flight hours, 

whichever occurs first. 

(h) Compliance Times for Initial Inspections 

Required by Paragraph (g) of This AD 

Do the initial inspections required by 

paragraph (g) of this AD within the 

applicable compliance times specified in 

paragraphs (h)(1) through (h)(4) of this AD. 

(1) For Configuration 1 airplanes, having 

manufacturer serial number (MSN) 0001 

though MSN 0079 inclusive, on which the 

modification specified by Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated March 17, 1997, has 

not been accomplished: At the later of the 

times specified by paragraphs (h)(1)(i) 

through (h)(1)(iii) of this AD: 

(i) The later of the times specified by 

paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this 

AD: 

(A) Within 24,000 flight cycles or 48,000 

flight hours, whichever occurs first since 

airplane first flight. 

(B) Within 60 days after the effective date 

of this AD. 

(ii) Within 8,800 flight cycles or 17,700 

flight hours, whichever occurs first, since the 

last inspection specified in Airbus Service 

Bulletin A320–57–1016 was accomplished. 

(iii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD, without exceeding 

14,000 flight cycles after the last inspection 

specified in Airbus Service Bulletin A320– 

57–1016 was accomplished. 

(2) For Configuration 2 airplanes, having 

MSN 0001 to 0079 inclusive, on which the 

actions specified by Airbus Service Bulletin 

A320–57–1016, have not been done prior to 

accomplishing the actions specified by 

Airbus Service Bulletin A320–57–1017, 

dated September 3, 1991; or Airbus Service 

Bulletin A320–57–1017, Revision 01, dated 

March 17, 1997: At the later of the times 

specified by paragraphs (h)(2)(i) and (h)(2)(ii) 

of this AD: 

(i) Within 8,800 flight cycles or 17,700 

flight hours, whichever occurs first, since the 

modification specified in Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated December 6, 1995, 

was accomplished. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(3) For Configuration 3 airplanes, having 

MSN 0001 to 0079 inclusive, on which the 

actions specified by Airbus Service Bulletin 

A320–57–1016, have been done prior to 

accomplishing the actions specified by 

Airbus Service Bulletin A320–57–1017, 

dated September 3, 1991; or Airbus Service 

Bulletin A320–57–1017, Revision 01, dated 


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March 17, 1997: At the later of the times 

specified by paragraphs (h)(3)(i) and (h)(3)(ii) 

of this AD: 

(i) Within 24,900 flight cycles or 49,800 

flight hours, whichever occurs first, since the 

modification specified in Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated March 17, 1997, was 

accomplished. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(4) For Configuration 4 airplanes, having 

MSN 0080 to 0155 inclusive: 

At the later of the times specified in 

paragraphs (h)(4)(i) or (h)(4)(ii) of this AD: 

(i) Before exceeding 54,300 flight cycles or 

108,600 flight hours, whichever occurs first 

since airplane first flight. 

(ii) Within 60 days after the effective date 

of this AD. 

(i) Repair 

If any crack is detected during any 

inspection required by paragraph (g) of this 

AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0069, dated 

March 19, 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 Docket No. FAA– 

2015–1422. 

(2) For service information identified in 

this 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 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. 2015–13342 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–2015–1421; Directorate 

Identifier 2014–NM–177–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 767–300 

and –300F series airplanes. This 

proposed AD was prompted by reports 

of fatigue cracking on airplanes with 

Aviation Partners Boeing winglets 

installed. This proposed AD would 

require a high frequency eddy current 

(HFEC) inspection for cracking of the 

lower outboard wing skin, and repair or 

modification if necessary. This 

proposed AD would also require one of 

three follow-on actions: Repeating the 

HFEC inspections; modifying certain 

internal stringers and oversizing and 

plugging the existing fastener holes of 

the lower wing; or modifying the 

external doubler/tripler and doing 

repetitive post-modification inspections. 

We are proposing this AD to prevent 

fatigue cracking in the lower outboard 

wing skin, which could result in failure 

and subsequent separation of the wing 

and winglet and consequent reduced 

controllability of the airplane. 

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 Aviation 

Partners Boeing, 2811 S. 102nd Street, 

Suite 200, Seattle, WA 98168; telephone 

206–762–1171; Internet https://

www.aviationpartnersboeing.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– 

1421; 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

Allen.Rauschendorfer@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– 

2015–1421; Directorate Identifier 2014– 

NM–177–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 


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