4878 Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / Rules and Regulations 

2013. If there is any crack at or aft of the spar 

attachment, before further flight, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; EASA; or 

Airbus’s EASA DOA. 

(l) No Terminating Action 

Accomplishment of any repair required by 

paragraph (k) this AD does not constitute 

terminating action for the repetitive 

inspections required by paragraph (j) of this 

AD. 

(m) No Reporting Required 

Although Airbus Service Bulletin A300– 

57–6045, Revision 10, dated November 13, 

2013, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (i), (j) and (k) of this 

AD, if those actions were performed before 

the effective date of this AD using the Airbus 

service bulletins specified in paragraphs 

(n)(1) through (n)(8) of this AD, which are not 

incorporated by reference in this AD. 

(1) Airbus Service Bulletin A300–57–6045, 

dated March 18, 1993. 

(2) Airbus Service Bulletin A300–57–6045, 

Revision 03, dated October 25, 1999. 

(3) Airbus Service Bulletin A300–57–6045, 

Revision 04, dated January 13, 2002. 

(4) Airbus Service Bulletin A300–57–6045, 

Revision 05, dated June 13, 2003. 

(5) Airbus Service Bulletin A300–57–6045, 

Revision 06, dated January 13, 2005. 

(6) Airbus Service Bulletin A300–57–6045, 

Revision 07, dated August 14, 2008. 

(7) Airbus Service Bulletin A300–57–6045, 

Revision 08, dated June 6, 2011. 

(8) Airbus Service Bulletin A300–57–6045, 

Revision 09, dated May 21, 2013. 

(o) 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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

98–20–27, Amendment 39–10793 (63 FR 

50981, September 24, 1998), are approved as 

AMOCs for the corresponding provisions of 

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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0232R1, dated 

October 2, 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– 

2015–0824. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 3, 2016. 

(i) Airbus Service Bulletin A300–57–6045, 

Revision 10, dated November 13, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on October 29, 1998 (63 FR 

50981, September 24, 1998). 

(i) Airbus Service Bulletin A300–57–6045, 

Revision 1, dated August 3, 1994, including 

Appendix 1, Revision 1, dated August 3, 

1994, which contains the following list of 

effective pages: Page numbers 1 through 10, 

Revision 1, dated August 3, 1994; Appendix 

1, pages 1 and 2, Revision 1, dated August 

3, 1994; and Appendix 1, pages 3 through 6, 

dated March 18, 1993. 

(ii) Airbus Service Bulletin A300–57–6045, 

Revision 02, dated April 21, 1998, including 

Appendix 1, Revision 02, dated April 21, 

1998. 

(5) 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

6, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00611 Filed 1–27–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1427; Directorate 

Identifier 2013–NM–203–AD; Amendment 

39–18380; AD 2016–02–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 96–18–06 

for certain Airbus Model A320–211 and 

–231 airplanes. AD 96–18–06 required 

visual inspections to detect cracks of the 

pressurized floor fittings at frame 36, 

and renewal of the zone protective 

finish or replacement of fittings with 

new fittings if necessary. Since we 

issued AD 96–18–06, an extended 

service goal analysis by the 

manufacturer revealed that the 

compliance times and repetitive 

inspection intervals should be reduced 

to meet the design service goal. This AD 

retains the requirements of AD 96–18– 

06, with reduced compliance times and 

repetitive inspection intervals. This AD 

also adds Model A320–212 airplanes to 

the applicability. We are issuing this AD 

to detect and correct fatigue cracking in 

the pressurized floor fittings at frame 36, 

which could result in failure of a floor 

fitting and subsequent depressurization 

of the fuselage. 

DATES: This AD becomes effective 

March 3, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 3, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 10, 1996. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1427; or in 


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person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this final rule, 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1427. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996). AD 96–18–06 

applied to certain Airbus Model A320– 

111, –211, and –231 series airplanes. 

The NPRM published in the Federal 

Register on June 5, 2015 (80 FR 32055) 

(‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agency 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0226, dated September 

23, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for Airbus Model 

A320–211, –212, and –231 airplanes. 

The MCAI states: 

During center fuselage certification full 

scale fatigue test, damage was found on the 

pressurized floor fittings at Frame 36, below 

the lower surface panel. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To prevent such damage, Airbus developed 

modification 21282, which was introduced in 

production from [manufacturer serial 

number] MSN 0105, to reinforce the 

pressurized floor fitting lower surface by 

changing material. For affected in-service 

aeroplanes, Airbus issued Service Bulletin 

(SB) A320–57–1028, introducing repetitive 

inspections, and SB A320–57–1029, which 

provides modification instructions. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued [an] AD * * * [for 

Model A320–111, –211, and –231 airplanes] 

to require these repetitive inspections and, 

depending on findings, corrective action(s), 

while the modification was specified in that 

AD as optional terminating action for these 

inspections. 

Following new analysis in the frame of 

ESG (Extended Service Goal) exercise, the 

inspection thresholds and intervals have 

been revised to meet the original DSG 

(Design Service Goal). 

For the reasons described above, this 

[EASA] AD retains the requirements of [a] 

DGAC France AD * * *, which is 

superseded, but requires these actions within 

reduced compliance times. [This EASA AD 

also adds Model A320–212 airplanes to its 

applicability.] 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1427- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for the change 

described previously and minor 

editorial changes. We have determined 

that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–57–1028, Revision 1, dated April 

19, 1996; and Revision 02, dated June 3, 

2013. The service information describes 

procedures for an inspection to detect 

cracks of the pressurized floor fittings at 

frame 36, renewal of the zone protective 

finish, and replacement of fittings with 

new fittings. 

Airbus has also issued Service 

Bulletin A320–57–1029, Revision 02, 

dated June 16, 1999. The service 

information describes procedures for 

modification of the pressurized floor 

fittings at frame 36. 

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. 

Costs of Compliance 

We estimate that this AD affects 13 

airplanes of U.S. registry. 

The actions required by AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996), and retained in this 

AD take about 3 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that are required by AD 96–18–06 is 

$255 per product. 

We also estimate that it will take 

about 11 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $12,155, or $935 per 

product. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition actions 

specified in this 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 


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4880 Federal Register / Vol. 81, No. 18 / Thursday, January 28, 2016 / Rules and Regulations 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-1427; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

96–18–06, Amendment 39–9730 (61 FR 

46703, September 5, 1996), and adding 

the following new AD: 

2016–02–01 Airbus: Amendment 39–18380. 

Docket No. FAA–2015–1427; Directorate 

Identifier 2013–NM–203–AD. 

(a) Effective Date 

This AD becomes effective March 3, 2016. 

(b) Affected ADs 

This AD replaces AD 96–18–06, 

Amendment 39–9730 (61 FR 46703, 

September 5, 1996). 

(c) Applicability 

This AD applies to Airbus Model A320– 

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

any category, manufacturer serial numbers 

0002 through 0104 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by an extended 

service goal analysis by the manufacturer, 

which revealed that the compliance times 

and repetitive inspection intervals should be 

reduced to meet the design service goal. We 

are issuing this AD to detect and correct 

fatigue cracking in the pressurized floor 

fittings at frame 36, which could result in 

failure of a floor fitting and subsequent 

depressurization of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (a) of AD 96–18–06, Amendment 

39–9730 (61 FR 46703, September 5, 1996), 

with revised service information for Airbus 

Model A320–211 and –231 airplanes. Prior to 

the accumulation of 16,000 total landings, or 

within 6 months after October 10, 1996 (the 

effective date of AD 96–18–06), whichever 

occurs later, perform a visual inspection to 

detect cracks of the 6 fittings of the 

pressurized floor at frame 36 under the lower 

surface panel, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. As of the effective date of this 

AD, use only Airbus Service Bulletin A320– 

57–1028, Revision 02, dated June 3, 2013, for 

accomplishing the actions required by this 

paragraph. Accomplishment of the initial 

inspection required by paragraph (i) of this 

AD terminates the actions required by this 

paragraph. 

(1) If no cracking is found, prior to further 

flight, renew the zone protective finish, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. Repeat 

the visual inspection thereafter at intervals 

not to exceed 12,000 landings. 

(2) If only 1 of the 6 fittings is found to be 

cracked and that crack is less than or equal 

to 0.59 inch (15 mm) in length, prior to 

further flight, replace the cracked fitting with 

a new fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. Thereafter, prior to the 

accumulation of 500 landings following 

accomplishment of this replacement, replace 

the remaining 5 fittings with new fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. 

(3) If only 1 of the 6 fittings is found to be 

cracked, and that crack is greater than 0.59 

inch (15 mm) in length, prior to further flight, 

replace all six fittings with new fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1028, Revision 1, dated April 19, 1996; or 

Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013, for accomplishing the 

actions required by this paragraph. 

(4) If 2 or more fittings are found to be 

cracked, prior to further flight, replace all 6 

fittings with new fittings, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013. As of the effective date of this 

AD, use only Airbus Service Bulletin A320– 

57–1028, Revision 02, dated June 3, 2013, for 

accomplishing the actions required by this 

paragraph. 

(h) Retained Optional Terminating Action, 

With Revised Service Information 

This paragraph restates the provisions of 

paragraph (b) of AD 96–18–06, Amendment 

39–9730 (61 FR 46703, September 5, 1996), 

with revised service information for Airbus 

Model A320–211 and –231 airplanes. 

Replacement of all 6 fittings with new 

fittings, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 1, 

dated April 19, 1996; or Airbus Service 

Bulletin A320–57–1028, Revision 02, dated 

June 3, 2013; constitutes terminating action 

for the inspection requirements of paragraph 

(g) of this AD. 

(i) New Inspection 

(1) At the latest of the times in paragraph 

(i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Do 

a detailed inspection of the pressurized floor 

fittings at frame 36, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1028, Revision 02, 

dated June 3, 2013. Repeat the inspection 

thereafter, at intervals not to exceed 9,300 

flight cycles or 18,600 flight hours, 

whichever occurs first. Accomplishment of 

the initial inspection required by this 

paragraph terminates the actions required by 

paragraph (g) of this AD. 

(i) Prior to the accumulation of 20,900 total 

flight cycles or 41,800 total flight hours, 

whichever occurs first. 

(ii) Prior to the accumulation of 9,300 flight 

cycles or 18,600 flight cycles since the most 

recent inspection required by paragraph (g) 

or (i) of this AD, whichever occurs first. 

(iii) At the earlier of the times specified in 

paragraph (i)(1)(iii)(A) and (i)(1)(iii)(B) of this 

AD. 

(A) Prior to the accumulation of 1,250 

flight cycles or 2,500 flight hours after the 

effective date of this AD, whichever occurs 

first. 


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(B) Prior to the accumulation of 12,000 

flight cycles since the most recent inspection 

required by paragraph (g) or (i) of this AD. 

(2) If any crack is found during any 

inspection required by paragraph (i)(1) 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) New Optional Terminating Action 

Modification (replacement of aluminum 

fittings with titanium fittings) of the 

pressurized floor fittings at frame 36, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1029, Revision 02, dated June 16, 1999, 

is terminating action for the repetitive 

inspections required by paragraphs (g) and (i) 

of this AD. 

(k) 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: 

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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

96–18–06, Amendment 39–9730 (61 FR 

46703, September 5, 1996), are approved as 

AMOCs for the corresponding provisions of 

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. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0226, dated 

September 23, 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–2015–1427. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 3, 2016. 

(i) Airbus Service Bulletin A320–57–1028, 

Revision 02, dated June 3, 2013. 

(ii) Airbus Service Bulletin A320–57–1029, 

Revision 02, dated June 16, 1999. 

(4) The following service information was 

approved for IBR on October 10, 1996 (61 FR 

46703, September 5, 1996). 

(i) Airbus Service Bulletin A320–57–1028, 

Revision 1, dated April 19, 1996, which 

contains the following list of effective pages: 

Pages 1 through 3, Revision 1, dated April 19, 

1996; Pages 4 through 15, dated August 12, 

1991. 

(ii) Reserved. 

(5) 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. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

9, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00949 Filed 1–27–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–3674; Airspace 

Docket No. 15–ANM–18] 

Amendment of Class E Airspace; 

Boise, ID 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class E 

surface area airspace designated as an 

extension to Class C airspace, and Class 

E airspace extending upward from 700 

feet above the surface at Boise Air 

Terminal/Gowen Field Airport, formerly 

Boise Air Terminal (Gowen Field), 

Boise, ID. After reviewing the airspace, 

the FAA found standard instrument 

approach procedures are not fully 

contained in controlled airspace, 

thereby necessitating airspace redesign 

for the safety and management of 

Instrument Flight Rules (IFR) operations 

at the airport. This action also corrects 

the name of the airport to match the 

FAAs aeronautical database. 

DATES: Effective 0901 UTC, March 31, 

2016. The Director of the Federal 

Register approves this incorporation by 

reference action under Title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.9Z, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at http://www.faa.gov/ 

air_traffic/publications/. For further 

information, you can contact the 

Airspace Policy Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 29591; 

telephone: 202–267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of FAA 

Order 7400.9Z at NARA, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federalregulations/ibr_locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. 

FOR FURTHER INFORMATION CONTACT: 

Steve Haga, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA 98057; 

telephone (425) 203–4563. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 


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