Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations 44457 

Conclusion 

This action affects only certain novel 

or unusual design features on the 

balloon models specified in these 

special conditions. It is not a rule of 

general applicability and it affects only 

the applicant who applied to the FAA 

for approval of these features on the 

airplane. These special conditions are 

identical in intent to the EASA special 

conditions, although the formatting has 

been altered to meet these special 

condition requirements. 

List of Subjects in 14 CFR Part 31 

Aircraft, Aviation safety. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701– 

44702, 44704. 

The Special Conditions 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the following special conditions are 

issued as part of the type certification 

basis for Ultramagic S.A. Model M–56, 

M–56C, M–65, M–65C, M–77, M–77C, 

M–90, M–105, M–120, M–130, M–145, 

M–160, N–180, N–210, N–250, N–300, 

N–355, N–425, S–70, S–90, S–105, S– 

130, S–160, T–150, T–180, T–210, V–56, 

V–65, V–77, V–90, and V–105 balloons 

with a basket Model no. CV–08. 

1. Hot Air Balloon Crashworthiness 

Requirements for Seat Installations and 

Restraints for Seated and Restrained 

Occupants 

a. Occupant Mass 

For calculation purposes, it should be 

assumed the mass of an occupant is at 

least 86 kilograms (190 pounds). 

b. Seats, Safety Belts, and Harnesses 

Factor of Safety 

For each seat, safety belt, and harness, 

its attachment to the structure must be 

shown, by analysis, tests, or both, to be 

able to withstand the inertia forces 

prescribed in paragraph (c) of these 

special conditions multiplied by a 

fitting factor of 1.33. 

c. Emergency Landing Conditions— 

General 

The balloon—although it may be 

damaged under emergency landing 

conditions—must be designed to give 

each occupant every reasonable chance 

of avoiding serious injury in a crash 

landing—when seat belts provided for 

in the design are properly used—and 

the occupant is subject to the following 

ultimate inertia forces acting relative to 

the surrounding structure as well as 

independently of each other. 

(1) Forward 6g 

(2) Sideways 6g 

(3) Downward 6g 

d. Seats and Seatbelts 

(1) Each seat and its supporting 

structure must be designed for an 

occupant mass in accordance paragraph 

(a) of these special conditions and for 

the maximum load factors 

corresponding to the specified flight and 

ground load conditions, including the 

emergency landing conditions 

prescribed in paragraph (c) of these 

special conditions. 

(2) Each seat or berth shall be fitted 

with an individual approved seat belt or 

harness. 

(3) Seat belts installed on the balloon 

must not fail under flight or ground load 

conditions or emergency landing 

conditions in accordance with 

paragraph (c) of these special 

conditions, taking into account the 

geometrical arrangement of the belt 

attachment and the seat. 

Issued in Kansas City, Missouri, on August 

23, 2018. 

Pat Mullen, 

Manager, Small Airplane Standards Branch, 

Aircraft Certification Service. 

[FR Doc. 2018–18885 Filed 8–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0169; Product 

Identifier 2017–NM–095–AD; Amendment 

39–19372; AD 2018–17–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–02– 

17, which applied to all Airbus Model 

A330–200, A330–200 Freighter, and 

A330–300 series airplanes. AD 2015– 

02–17 required revising the electrical 

emergency configuration procedure in 

the Emergency Procedures section of the 

airplane flight manual (AFM) to include 

procedures for deploying the ram air 

turbine manually to provide sufficient 

hydraulic power and avoid constant 

speed motor/generator (CSM/G) 

shedding. Since we issued AD 2015–02– 

17, we have determined that 

replacement or modification of the two 

flight warning computers (FWCs) is 

necessary to address the identified 

unsafe condition. This AD requires the 

replacement or modifications of the two 

FWCs. This AD also removes airplanes 

from the applicability. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective October 5, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 5, 2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of February 13, 2015 (80 FR 

4762, January 29, 2015). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, Rond-Point Emile Dewoitine No: 

2, 31700 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. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0169. 

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–2018– 

0169; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Docket Operations, 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3229. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2015–02–17, 


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44458 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations 

Amendment 39–18084 (80 FR 4762, 

January 29, 2015) (‘‘AD 2015–02–17’’). 

AD 2015–02–17 applied to all Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes. The 

NPRM published in the Federal 

Register on April 16, 2018 (83 FR 

16248). The NPRM was prompted by a 

determination that replacement or 

modification of the two FWCs is 

necessary to address the identified 

unsafe condition. The NPRM proposed 

to require the replacement or 

modification of the two FWCs. The 

NPRM also proposed to remove 

airplanes from the applicability. We are 

issuing this AD to address the identified 

unsafe condition. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017– 

0105R1, dated July 17, 2017 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A330–200, 

A330–200 Freighter, and A330–300 

series airplanes. The MCAI states: 

The Constant Speed Motor/Generator 

(CSM/G), as installed on Airbus A330 

aeroplanes, is qualified for an overload 

condition of 9.5 kVA [kilovolt-ampere] for 30 

minutes. This duration is sufficient to 

perform safe landing and go-around. 

However, electrical load analysis revealed 

that the hydraulic power might not be 

sufficient to supply the CSM/G during slat/ 

flap extension, when only one engine is 

running. 

This condition, if not corrected, and in 

conjunction with the loss of main system, 

could lead to a scenario where the crew is 

not clearly warned that the electrical system 

has switched on the battery and thus has a 

limited duration to support a safe landing. 

To initially address this potential unsafe 

condition, Airbus issued an Aircraft Flight 

Manual (AFM) Temporary Revision (TR) to 

amend the electrical emergency configuration 

‘‘ELEC EMER CONFIG’’ procedure to require 

the pilot to deploy the ram air turbine 

manually before setting the Landing 

Recovery to ‘‘ON’’ position, which provides 

sufficient hydraulic power and avoids CSM/ 

G shedding under worst-case operational 

conditions. Consequently, EASA issued AD 

2014–0273 to require amendment of the AFM 

by incorporating the applicable Airbus TR. 

After finding that [EASA] AD 2014–0273 

contained some incorrect and incomplete 

information, EASA issued AD 2014–0281 

[which corresponds to FAA AD 2015–02–17], 

retaining the requirements of EASA AD 

2014–0273, which was superseded, but 

correcting the information related to premod/ 

pre Service Bulletin (SB) or post-mod/post 

SB aeroplane configurations. 

Since EASA AD 2014–0281 was issued, in 

order to improve the ‘‘ELEC EMER CONFIG’’ 

procedure, Airbus developed modifications 

to install improved FWCs, which is 

embodied in production through Airbus 

modification (mod) 205228, and to be 

embodied in service with Airbus SB A330– 

31–3232 * * *. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0281, which is superseded, and 

requires installation of a software standard 

upgrade [or replacement] of the two FWCs 

and removal of the applicable AFM TR once 

the aeroplane is modified. 

Since EASA AD 2017–0105 was issued, it 

was identified that there was no need to 

require removal of applicable AFM TR, nor 

incorporation of a later AFM revision, as the 

contents are identical. This revised [EASA] 

AD deletes the requirement of paragraph (3) 

[of EASA AD 2017–0105]. 

* * * * * 

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–2018– 

0169. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. The Air Line 

Pilots Association, International 

(ALPA), indicated its support for the 

NPRM. 

Request for Additional Credit 

Delta Air Lines requested that 

paragraph (l) of the proposed AD, 

‘‘Credit for Previous Actions,’’ include 

Airbus Service Bulletin A330–31–3232, 

Revision 01, dated February 14, 2017, as 

well as Airbus Service Bulletin A330– 

31–3232, dated May 4, 2016. 

We disagree this change is necessary. 

Paragraph (f) of this AD requires 

compliance with this AD unless already 

done. Paragraph (j) of this AD mandates 

actions in accordance with Airbus 

Service Bulletin A330–31–3232, 

Revision 01, dated February 14, 2017. 

Therefore, as specified in paragraph (f) 

of this AD, having previously 

accomplished the actions specified in 

Airbus Service Bulletin A330–31–3232, 

Revision 01, dated February 14, 2017, 

means compliance with paragraph (j) of 

this AD has already been established. In 

paragraph (l) of this AD, we give credit 

to operators that have previously 

accomplished an earlier revision of the 

required service information identified 

in paragraph (j) of this AD; therefore, as 

specified in paragraph (l) of this AD, 

having accomplished Airbus Service 

Bulletin A330–31–3232, dated May 4, 

2016, prior to the effective date of this 

AD means compliance with paragraph 

(j) of this AD has already been 

established. We have not changed this 

AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. We have determined 

that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing 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 SAS has issued A330/A340 

Airplane Flight Manual (AFM) 

Temporary Revision (TR) TR427, 

UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated 

November 7, 2014; and A330/A340 

AFM TR TR428, UPDATE OF ELEC— 

EMER CONFIG PROCEDURE, Issue 1.0, 

dated November 7, 2014. This service 

information describes updated electrical 

emergency configuration procedures in 

the AFM. This service information is 

distinct because it applies to airplanes 

in different configurations. 

Airbus SAS has issued Service 

Bulletin A330–31–3232, Revision 01, 

including Appendix 01, dated February 

14, 2017. This service information 

describes procedures for replacement or 

modification of the FWCs. 

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 105 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations 44459 

ESTIMATED COSTS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

4 work-hour × $85 per hour = $340 ............................................................................................ $0 $340 $35,700 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

Division. 

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) 

2015–02–2017, Amendment 39–18084 

(80 FR 4762, January 29, 2015), and 

adding the following new AD: 

2018–17–18 Airbus SAS: Amendment 39– 

19372; Docket No. FAA–2018–0169; 

Product Identifier 2017–NM–095–AD. 

(a) Effective Date 

This AD is effective October 5, 2018. 

(b) Affected ADs 

This AD replaces AD 2015–02–17, 

Amendment 39–18084 (80 FR 4762, January 

29, 2015) (‘‘AD 2015–02–17’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

manufacturer serial numbers, except those 

airplanes with Airbus modification 205228 

embodied in production. 

(1) Airbus SAS Model A330–201, –202, 

–203, –223, and –243 airplanes. 

(2) Airbus SAS Model A330–223F and 

–243F airplanes. 

(3) Airbus SAS Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical power. 

(e) Reason 

This AD was prompted by an electrical 

load analysis that revealed that hydraulic 

power might not be sufficient to supply the 

constant speed motor/generator (CSM/G) 

during slat/flap extension when only one 

engine is running and a determination that 

replacement or modification of the two flight 

warning computers (FWCs) is necessary to 

address the identified unsafe condition. We 

are issuing this AD to prevent such a 

condition which, in conjunction with the 

loss of the main electrical system, could lead 

to the scenario where the flight crew is not 

clearly warned that the electrical system has 

switched on the battery and thus has a 

limited duration that would allow a safe 

landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Airplane Flight Manual (AFM) 

Revision, With a New Exception 

This paragraph restates the requirements of 

paragraph (g) of AD 2015–02–17, with a new 

exception. Except for airplanes identified in 

paragraph (h) of this AD: Within 15 days after 

February 13, 2015 (the effective date of AD 

2015–02–17), revise the Emergency 

Procedures section of the Airbus A330/A340 

AFM to include the information in the 

applicable Airbus temporary revision (TR) 

specified in paragraph (g)(1) or (g)(2) of this 

AD. This may be done by inserting a copy of 

the applicable TR specified in paragraph 

(g)(1) or (g)(2) of this AD into the AFM. 

Operate the airplane according to the 

procedures in the applicable TR. When the 

information in the applicable TR has been 

included in the general revisions of the AFM, 

the general revisions may be inserted into the 

AFM, provided the relevant information in 

the general revision is identical to that in the 

TR, and the TR may be removed. 

(1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067 

configuration: Airbus A330/A340 AFM TR 

TR427, UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 

(2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067 

configuration: Airbus A330/A340 AFM TR 

TR428, UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 


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44460 Federal Register / Vol. 83, No. 170 / Friday, August 31, 2018 / Rules and Regulations 

(h) New Airplanes Not Affected by the 

Retained AFM Revision 

Airplanes operated with an AFM that 

incorporates the information in Airbus 

EMERGENCY PROCEDURES/24– 

ELECTRICAL POWER/ELEC—EMER 

CONFIG Documentary Unit (DU) 

00005218.0001001 (for airplanes in Airbus 

pre-modification 47930 configuration and 

pre-Airbus Service Bulletin A330–28–3067 

configuration), or DU 00005218.0002001 (for 

airplanes in an Airbus post-modification 

47930 configuration or post-Airbus Service 

Bulletin A330–28–3067 configuration), as 

applicable, are compliant with the 

requirements of paragraph (g) of this AD, 

provided that the applicable DU is not 

removed from the AFM. 

(i) New Definitions 

(1) For the purposes of this AD, an affected 

FWC is an FWC standard lower than T7–0. 

An FWC that is not affected is an FWC 

standard T7–0 having part number (P/N) 

LA2E20202T70000, or higher standard. 

(2) For the purposes of this AD: Group 1 

airplanes are those equipped with an affected 

FWC (as defined in paragraph (i)(1) of this 

AD) as of the effective date of this AD. Group 

2 airplanes are those equipped with FWCs 

that are not affected (as defined in paragraph 

(i)(1) of this AD) as of the effective date of 

this AD. 

(j) New Requirement of This AD: FWC 

Replacement or Modification 

For Group 1 airplanes: Within 24 months 

after the effective date of this AD: Replace or 

modify an affected FWC with an FWC that 

is not affected, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–31–3232, Revision 01, 

including Appendix 01, dated February 14, 

2017. 

(k) Parts Installation Prohibition 

(1) For Group 1 airplanes: After 

accomplishing the actions required by 

paragraph (j) of this AD, no person may 

install an affected FWC on the modified 

airplane. 

(2) For Group 2 airplanes: As of the 

effective date of this AD, no person may 

install an affected FWC on any airplane. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (j) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A330–31–3232, dated May 4, 2016. 

(m) Other FAA AD Provisions 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 Section, send it 

to the attention of the person identified in 

paragraph (n)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(ii) AMOCs approved previously for AD 

2015–02–17 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 Section, Transport 

Standards Branch, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus 

SAS’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(3) Required for Compliance (RC): 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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0105R1, dated July 17, 2017, 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–2018–0169. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3229. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(5) and (o)(6) 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 October 5, 2018. 

(i) Airbus Service Bulletin A330–31–3232, 

Revision 01, including Appendix 01, dated 

February 14, 2017. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on of February 13, 2015 (80 

FR 4762, January 29, 2015). 

(i) Airbus A330/A340 Airplane Flight 

Manual (AFM) Temporary Revision TR427, 

UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 

(ii) Airbus A330/A340 AFM Temporary 

Revision TR428, UPDATE OF ELEC—EMER 

CONFIG PROCEDURE, Issue 1.0, dated 

November 7, 2014. 

(5) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, Rond-Point Emile Dewoitine 

No: 2, 31700 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 Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on 

August 17, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18736 Filed 8–30–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0361; Product 

Identifier 2017–NM–160–AD; Amendment 

39–19373; AD 2018–17–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 SAS Model A318, A319, and 

A320 series airplanes, and Model A321– 

111, –112, –131, –211, –212, –213, –231, 

–232, –251N, –253N, and –271N 

airplanes. This AD was prompted by a 

determination that more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

This AD requires revising the 

maintenance or inspection program, as 

applicable, to incorporate the specified 

maintenance requirements and 

airworthiness limitations. We are 

issuing this AD to address the unsafe 

condition on these products. 


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