Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules 8157 

(2) Contacting the Manufacturer: 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h) of this AD: If 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0202R1, dated September 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–2016–0466. 

(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 February 

6, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03135 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3697; Directorate 

Identifier 2015–NM–143–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 supersede 

Airworthiness Directive (AD) 2011–01– 

15, which applies to certain The Boeing 

Company Model 757–200, –200CB, and 

–300 series airplanes. AD 2011–01–15 

currently requires repetitive inspections 

for cracking of the fuselage skin of the 

crown skin panel along the chem-milled 

step at stringers S–4L (left) and S–4R 

(right), from stations (STA) 297 through 

STA 439, and repair, if necessary. AD 

2011–01–15 also includes terminating 

action for the repetitive inspections of 

the repaired areas only. Since we issued 

AD 2011–01–15, we received reports of 

the initiation of new fatigue cracking in 

the fuselage skin of the crown skin 

panel along locally thinned channels 

adjacent to the chem-milled steps. This 

proposed AD would add repetitive 

inspections for cracking in additional 

areas and repair if necessary. This 

proposed AD would also remove 

airplanes from the applicability in AD 

2011–01–15. This proposed AD would 

also add an optional skin panel 

replacement which would terminate all 

inspections and an optional 

preventative modification that would 

terminate certain inspections. We are 

proposing this AD to detect and correct 

fatigue cracking of the fuselage skin of 

the crown skin panel, which could 

result in pressure venting and 

consequent rapid decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by April 4, 2016. 

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 NPRM, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, 

CA 90846–0001; telephone: 206–544– 

5000, extension 2; fax: 206–766–5683; 

Internet https://

www.myboeingfleet.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3697. 

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–2016– 

3697; 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: Eric 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5348; fax: 562–627–5210; 

email: eric.schrieber@faa.gov. 

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–2016–3697; Directorate Identifier 

2015–NM–143–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 

On December 28, 2010, we issued AD 

2011–01–15, Amendment 39–16572 (76 

FR 1351, January 10, 2011), for certain 

The Boeing Company Model 757–200, 

–200CB, and –300 series airplanes. AD 

2011–01–15 requires repetitive 

inspections for cracking of the fuselage 

skin of the crown skin panel along the 


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chem-milled step at stringers S–4L and 

S–4R, from stations (STA) 297 through 

STA 439, and repair if necessary. AD 

2011–01–15 also includes terminating 

action for the repetitive inspections of 

the repaired areas only. AD 2011–01–15 

resulted from reports of cracking in the 

fuselage skin of the crown skin panel. 

We issued AD 2011–01–15 to detect and 

correct fatigue cracking of the fuselage 

skin of the crown skin panel, which 

could result in pressure venting and 

consequent rapid decompression of the 

airplane. 

Actions Since AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, 

January 10, 2011), Was Issued 

The preamble to AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, 

January 10, 2011), specifies that we 

consider the requirements ‘‘interim 

action.’’ AD 2011–01–15 explains that 

we might consider further rulemaking if 

final action is later identified. We now 

have determined that it is necessary to 

initiate further rulemaking to add 

repetitive inspections for cracking in 

additional areas for certain airplanes, 

and repair if necessary. 

We have removed Model 757–200 CB 

series airplanes from the applicability 

because the crown skins on those 

airplanes are manufactured differently 

and therefore are not affected by the 

identified unsafe condition. 

We have also determined that the 

external detailed inspection that is 

allowed as an option in AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, 

January 12, 2011), does not adequately 

address the identified unsafe condition. 

Only eddy current inspections are 

adequate to address the identified 

unsafe condition. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 757–53– 

0097, Revision 2, dated July 28, 2015. 

The service information describes 

procedures for repetitive external 

sliding probe eddy current (EC) and 

external spot-probe-medium-frequency 

EC inspections for cracking of the crown 

skin panel, repair, a preventive 

modification, and replacement of the 

crown skin 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. 

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. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3697. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as RC 

(required for compliance) in any service 

information identified previously have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 652 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 (Zone 1) [Retained actions 

from AD 2011–01–15, Amendment 

39-16572 (76 FR 1351, January 10, 

2011)].

2 work-hour × $85 per hour = $170 

per inspection cycle.

$0 .......................... $170 per inspection cycle.$110,840 per inspection cycle. 

Inspections (Zones 2 and 3) [new proposed action].Up to 4 work-hours × $85 per hour = 

Up to $340 per inspection cycle.

$0 .......................... Up to $340 per inspection cycle.$221,680 per inspection cycle. 

Optional modification ............................ Up to 615 work-hours × $85 per hour 

= Up to $52,275.

Up to $26,496 ....... Up to $78,771 ....... Up to $51,358,692. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the optional replacement 

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 have 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 that the proposed regulation: 


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Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules 8159 

(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) 

2011–01–15, Amendment 39–16572 (76 

FR 1351, January 10, 2011), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2016–3697; Directorate Identifier 2015– 

NM–143–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by April 4, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, January 

10, 2011). 

(c) Applicability 

(c) This AD applies to The Boeing 

Company Model 757–200 and –300 series 

airplanes, certificated in any category, as 

identified in Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of the 

initiation of fatigue cracking in the fuselage 

skin of the crown skin panel along locally 

thinned channels adjacent to the chemmilled steps. We are issuing this AD to detect 

and correct fatigue cracking of the fuselage 

skin of the crown skin panel, which could 

result in pressure venting and consequent 

rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Do the applicable inspections required by 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) For all airplanes: At the applicable time 

specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015: Do the inspection 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 2, dated July 28, 2015. Repeat 

the inspection thereafter at the applicable 

times specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015. Accomplishing the 

preventative modification specified in 

paragraph (j)(1) of this AD or the replacement 

specified in paragraph (j)(2) of this AD 

terminates the inspections required by this 

paragraph. 

(i) Do an external sliding probe eddy 

current (EC) inspection for cracking of the 

crown skin panel at stringers S–4L (left) and 

S–4R (right). 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel at stringers S–4L and S–4R. 

(2) For airplanes on which any crack is 

found during any inspection required by 

paragraph (g)(1) of this AD; or any repair is 

installed that covers the Zone 1 inspection 

area specified in Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015; or any preventive 

modification is installed as specified in Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015: At the applicable time specified in 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015, except as required by paragraph (k)(1) 

of this AD: Do the inspection specified in 

paragraph (g)(2)(i) or (g)(2)(ii) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015. Repeat the inspection 

thereafter at the applicable times specified in 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015. Accomplishing the replacement 

specified in paragraph (j)(2) of this AD 

terminates the inspections required by this 

paragraph. 

(i) Do an external sliding probe EC 

inspection for cracking of the crown skin 

panel at stringers S–2L, S–3L, and S–3R, as 

applicable. 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel at stringers S–2L, S–3L, 

and S–3R, as applicable. 

(3) For airplanes on which any crack is 

found during any inspection required by 

paragraph (g)(1) of this AD; or any repair is 

installed that covers the Zone 1 inspection 

area specified in Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015; or any preventive 

modification is installed as specified in Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015: At the applicable time specified in 

table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015, except as required by paragraph (k)(1) 

of this AD: Do the inspection specified in 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015. Repeat the inspection 

thereafter at the applicable times specified in 

table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015. Accomplishing the replacement 

specified in paragraph (j)(2) of this AD 

terminates the inspections required by this 

paragraph. 

(i) Do an external sliding probe EC 

inspection for cracking of the crown skin 

panel at stringers S–3L and S–3R. 

(ii) Do an external spot-probe-mediumfrequency EC inspection for cracking of the 

crown skin panel at stringers S–3L and S–3R. 

(h) Post-Preventive Modification 

Supplemental Inspections 

For airplanes on which a preventive 

modification has been installed as specified 

in Part 3 of the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015: At the applicable time specified in 

table 4 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 2, dated July 28, 

2015; do eddy current and detailed 

inspections for cracking of the applicable 

areas of the fuselage skin of the doublers, 

triplers, and fillers of the preventive 

modification, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 2, dated July 28, 2015. Repeat 

the inspection thereafter at the applicable 

times specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 757–53–0097, Revision 2, 

dated July 28, 2015. 

(i) Repair 

If any cracking is found during any 

inspection required by paragraph (g)(1), 

(g)(2), (g)(3), or (h) of this AD, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. Doing the repair 

ends the repetitive inspections for the 

repaired area only. 

(j) Optional Terminating Actions 

(1) Accomplishing the preventative 

modification, including doing high frequency 

EC inspections for cracking around existing 

fastener holes, in accordance with Part 3 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0097, Revision 2, dated July 28, 2015, except 


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as required by paragraphs (k)(2) and (k)(3) of 

this AD, terminates the inspections required 

by paragraph (g)(1) of this AD, provided the 

preventative modification is done before 

further flight after accomplishing an 

inspection required by paragraph (g) of this 

AD. 

(2) Replacing the crown skin panel 

between STA 297 and STA 439, S–4L to S– 

4R, using a method approved in accordance 

with the procedures specified in paragraph 

(m) of this AD, terminates the inspections 

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

(g)(3) of this AD. 

(k) Exceptions to Service Information 

Specifications and Preventative Modification 

(1) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 2, dated July 

28, 2015, specifies a compliance time ‘‘after 

the Revision 2 date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 2, dated July 

28, 2015, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(3) If any cracking is found during any 

inspection specified in paragraph (j)(1) of this 

AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for Zone 

1 inspections required by paragraph (g) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Special Attention Service Bulletin 

757–53–0097, dated November 22, 2010, 

which was incorporated by reference in AD 

2011–01–15, Amendment 39–16572 (76 FR 

1351, January 10, 2011). 

(2) This paragraph provides credit for the 

Zone 1 inspection required by paragraph (g) 

of this AD, if those actions were performed 

before the effective date of this AD, using 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 1, dated January 6, 

2011, which is not incorporated by reference 

in this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (m)(1) of this AD. Information may 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair. 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane and the approval must 

specifically refer to this AD. 

(4) AMOCs approved for AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, January 

10, 2011), are not approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(5) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (m)(5)(i) and (m)(5)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(n) Related Information 

(1) For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5348; fax: 562– 

627–5210; email: Eric.Schrieber@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone: 206–544–5000, extension 2; fax: 

206–766–5683; Internet https://

www.myboeingfleet.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 February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03297 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0465; Directorate 

Identifier 2015–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A330–200 and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. This proposed AD 

was prompted by a determination that 

the compliance times for certain postrepair inspections and certain allowable 

damage limits (ADLs) must be reduced 

in order to address fatigue. This 

proposed AD would require identifying 

any repairs and ADLs used to assess or 

control any structural damage on certain 

structural areas, and corrective action if 

necessary. We are proposing this AD to 

prevent fatigue damage on primary 

structure and structural repairs, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 4, 2016. 

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: 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 NPRM, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone: +33 5 61 93 

36 96; fax: +33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet: http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 


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