Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26677 

docket on the Internet at http:// 

www.regulations.gov/ 

#!documentDetail;D=FAA-2015-7490-0001. 

(i) 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 the AD specifies otherwise. 

(i) Turbomeca S.A. Service Bulletin No. 

283 72 0811, Version A, dated August 25, 

2015. 

(ii) Reserved. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; fax: 33 (0)5 59 74 45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

April 21, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–10279 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5811; Directorate 

Identifier 2014–NM–158–AD; Amendment 

39–18489; AD 2016–08–13] 

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) 2004–19– 

11 for certain Airbus Model A320 series 

airplanes. AD 2004–19–11 required 

modification of the inner rear spar web 

of the wing, cold expansion of the 

attachment holes of the forward pintle 

fitting and the actuating cylinder 

anchorage of the main landing gear 

(MLG), repetitive ultrasonic inspections 

for cracking of the rear spar of the wing, 

and corrective action if necessary. AD 

2004–19–11 also provided optional 

terminating action for the repetitive 

inspections. This new AD retains the 

requirements of AD 2004–19–11, and 

requires the previously optional 

terminating action. This AD was 

prompted by a determination that the 

previously optional terminating action 

is necessary to address the unsafe 

condition. We are issuing this AD to 

prevent fatigue cracking of the inner 

rear spar, which may lead to reduced 

structural integrity of the wing and the 

MLG. 

DATES: This AD becomes effective June 

8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 5, 2004 (69 FR 58828, 

October 1, 2004). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of June 30, 2000 (65 FR 

34069, May 26, 2000). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 14, 1994 (59 FR 1903, 

January 13, 1994). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 11, 1993 (58 FR 

27923, May 12, 1993). 

ADDRESSES: 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– 

5811. 

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– 

5811; 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 address for the 

Docket Office (telephone 800–647–5527) 

is 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 20590. 

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 2004–19–11, 

Amendment 39–13805 (69 FR 58828, 

October 1, 2004) (‘‘AD 2004–19–11’’). 

AD 2004–19–11 applied to certain 

Airbus Model 320 series airplanes. The 

NPRM published in the Federal 

Register on November 27, 2015 (80 FR 

74058) (‘‘the NPRM’’). The NPRM was 

prompted by a determination that the 

previously optional terminating action 

is necessary to address the unsafe 

condition. The NPRM proposed to 

retain the requirements of AD 2004–19– 

11, and requires the previously optional 

terminating action. We are issuing this 

AD to prevent fatigue cracking of the 

inner rear spar, which may lead to 

reduced structural integrity of the wing 

and the MLG. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0169, dated July 17, 

2014, corrected July 22, 2014 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition on certain Airbus Model 320 

series airplanes. The MCAI states: 

During centre fuselage certification full 

scale fatigue test, cracks were found on the 

inner rear spar at holes position 52 on the 

right hand wing due to fatigue aspects. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To prevent such cracks, Airbus developed 

modifications, which were introduced in 

production and in service through several 

Airbus Service Bulletins (SB). 

DGAC France issued * * * [an earlier AD], 

which was subsequently superseded by 

[DGAC] AD 2001–249 [which corresponds 

with FAA AD 2004–19–11, Amendment 39– 

13805 (69 FR 58828, October 1, 2004)], to 

require modification of the rear spar on some 


asabaliauskas on DSK3SPTVN1PROD with RULES
26678 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 

aeroplanes, post-modification repetitive 

inspections and, depending on findings, 

accomplishment of a repair. DGAC France 

AD 2001–249 also specified that modification 

in accordance with Airbus SB A320–57–1089 

(in-service equivalent to Airbus mod 24591) 

constituted (optional) terminating action for 

the repetitive inspections. 

Since that [DGAC] AD [2001–249] was 

issued, in the framework of the A320 

Extended Service Goal (ESG), it has been 

determined that Airbus mod 24591 is 

necessary to allow aeroplanes to operate up 

to the new ESG limit. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 2001–249, which is superseded, 

and requires modification of all pre-mod 

24591 aeroplanes. 

The modification includes modifying 

all specified fastener holes in the inner 

rear spar of the wing. 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–2015–5811. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

United Airlines provided its support for 

the content of the NPRM. 

Explanation of Changes Made to This 

AD 

We have added a new paragraph (l)(1) 

to this AD to provide credit for actions 

required by paragraph (h) of this AD, if 

those actions were performed before the 

effective date of this AD using Airbus 

Service Bulletin A320–57–1060, 

Revision 1, dated April 26, 1993. We 

have redesignated paragraphs (l)(1) and 

(l)(2) of the proposed AD as paragraphs 

(l)(2) and (l)(3) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor 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 Airbus Service 

Bulletin A320–57–1089, Revision 03, 

dated February 9, 2001. This service 

information describes procedures for 

modification of the airplane by 

accomplishing cold re-expansion of the 

holes in the inner rear spar for the 

attachment of gear rib 5, forward pintle 

fitting, and actuating cylinder 

anchorage; and the installation of 

interference fit fasteners in the rear spar 

and gear rib 5. 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 84 

airplanes of U.S. registry. 

The actions required by AD 2004–19– 

11, and retained in this AD take about 

684 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $13,644 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2004–19–11 is $71,784 

per product. 

We also estimate that it takes about 

980 work-hours per product to comply 

with the basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$32,727 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $9,746,268, or 

$116,027 per product. 

We have received no definitive data 

that would 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: 

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. 

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) 

2004–19–11, Amendment 39–13805 (69 

FR 58828, October 1, 2004), and adding 

the following new AD: 

2016–08–13 Airbus: Amendment 39–18489. 

Docket No. FAA–2015–5811; Directorate 

Identifier 2014–NM–158–AD. 

(a) Effective Date 

This AD becomes effective June 8, 2016. 

(b) Affected ADs 

This AD replaces AD 2004–19–11, 

Amendment 39–13805 (69 FR 58828, October 

1, 2004) (‘‘AD 2004–19–11’’). 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes, certificated in any category, all 

manufacturer serial numbers, except those on 

which Airbus modification (mod) 24591 has 

been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

fatigue cracking of the inner rear spar of the 

wing and also by a determination that the 

modification of the inner rear spar is 

necessary to address the unsafe condition. 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26679 

We are issuing this AD to prevent fatigue 

cracking of the inner rear spar, which may 

lead to reduced structural integrity of the 

wing and the main landing gear (MLG). 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification of Inner Rear Spar 

Web of the Wing, With Change to Acceptable 

Service Information 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–19–11, with a 

change to acceptable service information. For 

airplanes having manufacturer’s serial 

numbers (MSNs) 003 through 008 inclusive, 

and 010 through 021 inclusive, except 

airplanes modified as specified in Airbus 

Service Bulletin A320–57–1089, dated 

December 22, 1996; Revision 01, dated April 

17, 1997; Revision 02, dated November 6, 

1998; or Revision 03, dated February 9, 2001: 

Prior to the accumulation of 12,000 total 

flight cycles, or within 500 flight cycles after 

June 11, 1993 (the effective date of AD 93– 

08–15, Amendment 39–8563 (58 FR 27923, 

May 12, 1993)), whichever occurs later, 

modify the inner rear spar web of the wing 

in accordance with Airbus Service Bulletin 

A320–57–1004, Revision 1, dated September 

24, 1992; or Revision 2, dated June 14, 1993. 

As of the effective date of this AD, only 

Airbus Service Bulletin A320–57–1004, 

Revision 2, dated June 14, 1993, may be used 

for the actions required by this paragraph. 

(h) Retained Cold Expansion of Holes at 

Forward Pintle Fitting and Actuating 

Cylinder Anchorage of the Main Landing 

Gear, With Change to Acceptable Service 

Information 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–19–11, with a 

change to acceptable service information. For 

airplanes having MSNs 002 through 051 

inclusive, except airplanes modified as 

specified in Airbus Service Bulletin A320– 

57–1089, dated December 22, 1996; Revision 

01, dated April 17, 1997; Revision 02, dated 

November 6, 1998; or Revision 03, dated 

February 9, 2001: Prior to the accumulation 

of 12,000 total flight cycles, or within 2,000 

flight cycles after February 14, 1994 (the 

effective date of AD 93–25–13, Amendment 

39–8777 (59 FR 1903, January 13, 1994)), 

whichever occurs later, accomplish the 

requirements of paragraphs (h)(1) and (h)(2) 

of this AD in accordance with Airbus Service 

Bulletin A320–57–1060, dated December 8, 

1992; Revision 1, dated April 26, 1993; or 

Revision 2, dated December 16, 1994. As of 

the effective date of this AD, only Airbus 

Service Bulletin A320–57–1060, Revision 2, 

dated December 16, 1994, may be used for 

the actions required by this paragraph. 

(1) Perform a cold expansion of all the 

attachment holes for the forward pintle 

fitting of the main landing gear (MLG), except 

for the holes that are for taper-lok bolts. 

(2) Perform a cold expansion of the holes 

at the actuating cylinder anchorage of the 

MLG. 

(i) Retained Repetitive Ultrasonic 

Inspections for Cracking of the Rear Spar of 

the Wing, With No Changes 

This paragraph restates the requirements of 

paragraphs (c), (d), and (e) of AD 2004–19– 

11, with no changes. Except for airplanes 

modified as specified in Airbus Service 

Bulletin A320–57–1089, dated December 22, 

1996; Revision 01, dated April 17, 1997; 

Revision 02, dated November 6, 1998; or 

Revision 03, dated February 9, 2001: Do the 

actions specified in paragraphs (i)(1) and 

(i)(2) of this AD. 

(1) Do an ultrasonic inspection for cracking 

of the rear spar of the wing, in accordance 

with Airbus Service Bulletin A320–57–1088, 

Revision 04, dated August 6, 2001. Inspect at 

the applicable time specified in paragraph 

1.E. of Airbus Service Bulletin A320–57– 

1088, Revision 04, dated August 6, 2001, 

except as required by paragraphs (i)(1)(i) and 

(i)(1)(ii) of this AD. 

(i) For any airplane that has not been 

inspected but has exceeded the applicable 

specified compliance time in paragraph 1.E. 

of Airbus Service Bulletin A320–57–1088, 

Revision 04, dated August 6, 2001, as of 

November 5, 2004 (the effective date of AD 

2004–19–11): Inspect within 18 months after 

November 5, 2004. 

(ii) For any airplane that has been 

inspected before November 5, 2004 (the 

effective date of AD 2004–19–11): Repeat the 

inspection within 3,600 flight cycles after the 

most recent inspection. 

(2) Repeat the inspection required by 

paragraph (i)(1) of this AD at intervals not to 

exceed 3,600 flight cycles or 6,700 flight 

hours, whichever occurs first, until the 

requirements of paragraph (k) of this AD have 

been done. 

(j) Retained Corrective Action for 

Inspections Required by Paragraphs (i)(1) 

and (i)(2) of This AD, With Specific 

Delegation Approval Language 

This paragraph restates the requirements of 

paragraph (f) of AD 2004–19–11, with 

specific delegation approval language. If any 

crack is found during any inspection 

required by paragraph (i)(1) or (i)(2) of this 

AD: Before further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (or its delegated agent); or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). 

Accomplishment of a repair as required by 

this paragraph does not constitute 

terminating action for the repetitive 

inspections required by paragraph (i)(2) of 

this AD. 

(k) New Requirement of This AD: 

Modification of the Inner Rear Spar 

Before exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since first flight of the airplane: Modify all 

specified fastener holes in the inner rear spar 

of the wing, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1089, Revision 03, 

dated February 9, 2001; except, where Airbus 

Service Bulletin A320–57–1089, Revision 03, 

dated February 9, 2001, specifies to contact 

Airbus for certain conditions, before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. Modification 

of all specified fastener holes in the rear spar 

of the wing terminates the initial and 

repetitive inspections required by paragraphs 

(i)(1) and (i)(2) of this AD. If the modification 

is done both before the airplane accumulates 

12,000 total flight cycles and before the 

effective date of this AD, the modification 

also terminates the actions required by 

paragraphs (g) and (h) of this AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–57–1060, Revision 1, dated 

April 26, 1993. This service information is 

not incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (i) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–57–1088, Revision 02, dated 

July 29, 1999; or Revision 03, dated February 

9, 2001. This service information is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for 

actions required by paragraph (k) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–57–1089, Revision 02, dated 

November 6, 1998. This service information 

is not incorporated by reference in this AD. 

(m) 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 in 

accordance with AD 2004–19–11 are 

approved as AMOCs for the corresponding 

provisions of paragraphs (g) through (j) of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 


asabaliauskas on DSK3SPTVN1PROD with RULES
26680 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 

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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0169, dated 

July 17, 2014, corrected July 22, 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–2015–5811. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(8) and (o)(9) of this AD. 

(o) 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 June 8, 2016. 

(i) Airbus Service Bulletin A320–57–1089, 

Revision 03, dated February 9, 2001. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 5, 2004 (69 

FR 58828, October 1, 2004). 

(i) Airbus Service Bulletin A320–57–1088, 

Revision 04, dated August 6, 2001. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on June 30, 2000 (65 FR 

34069, May 26, 2000). 

(i) Airbus Service Bulletin A320–57–1004, 

Revision 2, dated June 14, 1993. This service 

bulletin contains the following list of 

effective pages: Pages 1, 4, 12, 14, 17 through 

20, 22, 23, 28, 29, Revision 2, dated June 14, 

1993; page 15, Revision 1, dated September 

24, 1992; and pages 2, 3, 5 through 11, 13, 

16, 21, 24 through 27, 30, Original Issue, 

dated July 9, 1991. 

(ii) Airbus Service Bulletin A320–57–1060, 

Revision 2, dated December 16, 1994. 

(6) The following service information was 

approved for IBR on February 14, 1994 (59 

FR 1903, January 13, 1994). 

(i) Airbus Service Bulletin A320–57–1060, 

dated December 8, 1992. 

(ii) Reserved. 

(7) The following service information was 

approved for IBR on June 11, 1993 (58 FR 

27923, May 12, 1993). 

(i) Airbus Service Bulletin A320–57–1004, 

Revision 1, dated September 24, 1992. This 

service bulletin contains the following list of 

effective pages: Pages 1, 4, 12, 14 through 15, 

17 through 18, 20, Revision 1, dated 

September 24, 1992; and pages 2 through 3, 

5 through 11, 13, 16, 19, 21 through 30, 

Original Issue, dated July 9, 1991. 

(ii) Reserved. 

(8) 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. 

(9) 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. 

(10) 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 April 8, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08956 Filed 5–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3990; Directorate 

Identifier 2014–NM–255–AD; Amendment 

39–18478; AD 2016–08–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A320–214, –232, and 

–233 airplanes; and Airbus Model 

A321–211 and –231 airplanes. This AD 

was prompted by reports of incorrect 

installation of jiffy joint connectors on 

cables connected to certain passenger 

service units (PSUs), which could cause 

the passenger oxygen container to 

malfunction if the connector becomes 

disengaged during flight due to 

vibration. This AD requires 

identification of the affected PSUs, and 

depending on findings, doing applicable 

related investigative and corrective 

actions. We are issuing this AD to 

prevent failure of the door of the 

passenger oxygen container to open in 

the event of airplane decompression, 

resulting in lack of oxygen supply and 

consequent injury to occupants. 

DATES: This AD becomes effective June 

8, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 8, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-3990; or in 

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 Airbus 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. 

For Airbus Operations GmbH service 

information identified in this final rule, 

contact Airbus Operations GmbH, Cabin 

Electronics, Lueneburger Schanze 30, 

21614 Buxtehude, Germany; telephone 

+49 40 7437 46 32; telefax +49 40 7437 

16 80; email ruediger.jansen@

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– 

3990. 

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 by adding an AD that would 

apply to certain Airbus Model A320– 

214, –232, and –233 airplanes; and 

Airbus Model A321–211 and –231 

airplanes. The NPRM published in the 

Federal Register on October 19, 2015 

(80 FR 63134) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0256, dated November 

26, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 


asabaliauskas on DSK3SPTVN1PROD with RULES