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

8155 

Vol. 81, No. 32 

Thursday, February 18, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0466; Directorate 

Identifier 2014–NM–188–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 A300 B4–603, B4–605R, 

and B4–622R airplanes; and Model 

A310–304, –324, and –325 airplanes. 

This proposed AD was prompted by a 

report of a crack found on door frame 

(FR) 73A between stringers 24 and 25. 

This proposed AD would require 

inspections around the rivet heads of 

the seal retainer run-out holes at certain 

frames and corrective actions if 

necessary. We are proposing this AD to 

detect and correct cracking of the door 

frame, 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—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 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–2016– 

0466; 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 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: 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. 

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–2016–0466; Directorate Identifier 

2014–NM–188–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014– 

0202R1, dated September 19, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Airbus Model 

A300 B4–603, B4–605R, and B4–622R 

airplanes; and Model A310–304, –324, 

and –325 airplanes The MCAI states: 

During the preparation phase for 

conversion of an A300–600 aeroplane from 

passenger to freighter configuration, a crack 

was detected on door frame (FR) 73A, 

between stringer (STRG) 24 and STRG 25. 

DGAC France had issued AD 1999–013– 

276R1 [http://ad.easa.europa.eu/ad/F-1999- 

013-276R1] to require inspections at FR 73A 

in accordance with the instructions of Airbus 

Service Bulletin (SB) A310–53–2107 or SB 

A300–53–6116, as applicable. However, the 

new crack was found in an area not covered 

by the existing inspection and is therefore 

addressed by this new [EASA] AD. (DGAC 

France AD 1999–013–276R1 remains in 

place). 

Further investigations identified that, on 

A300–600 aeroplanes, the areas at FR 56A 

and FR 57A have the same design and 

material as at FR 73A. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the airframe. 

For the reasons described above, this 

[EASA] AD requires repetitive [high 

frequency eddy current (HFEC)] inspections 

of the rivet heads of the seal retainer run out 

holes to detect cracks and, depending on 

findings, accomplishment of corrective 

actions [repair]. 

Even though no crack has been identified 

at FR 56A and FR 57A, as a preventive 

measure, the inspection is extended to these 

areas. On A310 aeroplanes, only the area at 

FR 73A needs to be inspected. 

This [EASA] AD is revised to reduce the 

applicability to aeroplanes in post-MOD 

06924 configuration. 

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–2016– 

0466. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletins 

A300–53–6175, and A310–53–2138, 

both dated May 28, 2014. The service 


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8156 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules 

information describes procedures to do 

HFEC inspections around the rivet 

heads of the seal retainer run-out holes 

at certain frame locations on the lefthand and right-hand sides. 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 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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 24 airplanes of U.S. registry. 

We also estimate that it would take 

about 11 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $22,440, or $935 per product. 

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): 

Airbus: Docket No. FAA–2016–0466; 

Directorate Identifier 2014–NM–188–AD. 

(a) Comments Due Date 

We must receive comments by April 4, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300B4– 

603, A300B4–605R, A300B4–622R, A310– 

304, A310–324, and A310–325 airplanes; 

certificated in any category; all manufacturer 

serial numbers (MSNs) in post-modification 

(MOD) 06924 configuration, except MSN 464, 

477, 479, 481, 482, 483, 484, and 488. 

Note 1 to paragraph (c) of this AD: MSNs 

464, 477, 479, 481, 482, 483, 484 and 488 

partially embodied MOD 06924 by means of 

modification proposal D05902. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found on door frame (FR) 73A between 

stringers 24 and 25. We are issuing this AD 

to detect and correct cracking, which could 

reduce the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the later of the compliance times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD: Do a high frequency eddy current 

(HFEC) inspection for any crack around the 

rivet heads of the seal retainer run-out holes 

at FR 56A, FR 57A, and FR 73A, left-hand 

(LH) and right-hand (RH) sides on Model 

A300–600 airplanes; and at FR 73A, LH and 

RH sides on Model A310 airplanes; in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

53–2138, dated May 28, 2014; or Airbus 

Service Bulletin A300–53–6175, dated May 

28, 2014; as applicable. Repeat the HFEC 

inspection thereafter at intervals not to 

exceed 7,500 flight cycles. 

(1) Before the accumulation of 32,000 total 

flight cycles. 

(2) Within 36 months after the effective 

date of this AD, or before the accumulation 

of 36,000 total flight cycles, whichever 

occurs first. 

(h) Corrective Actions 

If any crack is found during any inspection 

required by paragraph (g) of this AD, repair 

before further flight 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). 

(i) 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. 


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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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